Progress on high-temperature protective coatings for aero-engines

Guo, Lei; He, Wenting; Chen, Wenbo; Xue, Zhaolu; He, Jian; Guo, Yiqian; Wu, Yang; Gao, Lihua; Li, Dongqing; Zhang, Zhao; Wei, Liangliang; Gao, Yuyi; Zhang, Tiehao; Qiao, Jiao; Li, Qianhui; Guo, Hongbo

doi:10.1007/s44251-023-00005-6

Progress on high-temperature protective coatings for aero-engines

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Published: 27 September 2023

Volume 1, article number 6, (2023)
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Progress on high-temperature protective coatings for aero-engines

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Lei Guo^1,2^na1,
Wenting He^1,3^na1,
Wenbo Chen^1,4^na1,
Zhaolu Xue^1,5^na1,
Jian He^3,6^na1,
Yiqian Guo¹^na1,
Yang Wu^1,7^na1,
Lihua Gao¹^na1,
Dongqing Li^1,8^na1,
Zhao Zhang^1,9^na1,
Liangliang Wei^3,6^na1,
Yuyi Gao¹^na1,
Tiehao Zhang¹^na1,
Jiao Qiao¹^na1,
Qianhui Li¹^na1 &
…
Hongbo Guo^1,3

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Abstract

Aero-engine is a key part of aircraft, the operating temperature of which is being pushed to unprecedented levels for higher engine efficiency and performance. To accomplish higher gas-inlet temperature of aero-engines, applying thermal barrier coatings (TBCs) on hot-section metallic components, or even replacing some of the metallic components in aero-engines with ceramic-matrix composites (CMCs) and applying environmental-barrier coatings (EBCs) on them, are effective methods and have been widely accepted. On the other hand, increasing aero-engines operating temperature causes the aircraft more easily be detected, thus stealth coatings are necessary for engines. Except the hottest part in aero-engines, other parts may not need TBCs or EBCs due to the relatively low operating temperature, but they still need protection from oxidation and corrosion. Hence, corrosion-resistant coatings are essential. In this paper, the latest progress of the above high-temperature protective coatings, i.e., TBCs, EBCs, stealth coatings and corrosion-resistant coatings is reviewed, mainly including their materials, fabrication technologies and performance. In addition, due to the harsh operating environment, these protective coatings face many threats such as calcia-magnesia-aluminosilicates (CMAS) attack, causing premature failure of the coatings, which is also concerned in this paper. The work would provide a comprehensive understanding on the high-temperature protective coatings in aero-engines and guidance for develo** advanced protective coatings for next-generation aero-engines.

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1 Introduction

For more advanced aircraft, there is insatiable demand for more powerful aero-engines, which can be accomplished by increasing the turbine gas-inlet temperature [1, 2]. Over several decades, the hot-section structural materials have developed from wrought, conventionally cast, directionally solidified to single-crystal alloys [3, 4]. This considerably elevates the gas-inlet temperature. However, this method faces “bottleneck” due to the high-temperature capability limit of superalloys. For further significant increase in the gas-inlet temperature, thermal barrier coating (TBC) in conjunction with advanced cooling technology have been employed for hot-section components of aero-engines [5,6,7]. A TBC system is composed of a ceramic top coat, a bond coat and the substrate. Usually, there is a thermally grown oxide (TGO) layer forming on the bond coat during TBCs operation. The ceramic top coat provides thermal insulation, which has large thermal expansion mismatch to the substrate. Hence, a metallic bond coat is prepared between the top coat and substrate to alleviate the thermal expansion mismatch, and also protect the substrate from oxidation.

The research on TBCs could trace back to the 1950s, and the first usage was reported in the 1960s [8]. After the identification of partially yttria-stabilized zirconia (YSZ) in the 1980s, TBCs development has made a major step forward [9, 10]. YSZ has many unique properties fit excellently to the requirements of a TBC system, such as low thermal conductivity, high thermal expansion coefficient (TEC), high toughness, good phase stability, good compatibility with the TGO layer, and low sintering rate [4, 7, 11,12,13]. However, with ever-increasing demands for higher gas-inlet temperature, YSZ TBCs face severe limitations. The as-fabricated YSZ coatings exhibit a non-transformable metastable tetragonal (t′) phase, which has high toughness resulting from a ferroelastic toughening effect. At temperatures higher than 1250 °C, t′ phase decomposes to tetragonal (t) and cubic (c) phases, and the former transforms to a monoclinic (m) phase during cooling accompanied with excessive volume expansion, which would cause cracks in the coating leading to premature failure of TBCs. Additionally, high-temperature accelerates the coating sintering and causes severe corrosion to TBCs. Therefore, search is underway for develo** TBC materials that have even better phase stability, higher sintering resistance, lower thermal conductivity and better corrosion resistance.

Although TBCs in combination with the cooling technology largely enhance the operating temperature of hot parts of aero-engines, superalloys still have their temperature-capability limit. It is thus not optimistic that the gas-inlet temperature achieves the goal of above 1700 °C [2]. In response to this, SiC_f/SiC ceramic matrix composites (CMCs) have been proposed and designed to gradually replace nickel-based superalloys for aero-engine hot-end parts. However, one notable challenge hindering the practical implementation of CMCs is their insufficient environmental durability within combustion environments [14,15,16]. The presence of water vapor, a byproduct of the combustion reaction, triggers chemical reaction with the protective silica scale that forms on the CMCs, resulting in the formation of gaseous reaction products such as Si(OH)₄. In high-pressure and high-velocity combustion environments, this reaction accelerates the degradation of CMCs materials. Additionally, CMCs are susceptible to other severe corrosion when exposed to combustion environments. Therefore, environmental barrier coatings (EBCs) have been developed, which play a critical role in protecting SiC_f/SiC hot-section components from the harsh conditions encountered in aircraft engines. EBCs are applied to surfaces of components such as turbine shrouds, combustors, seal segments, vanes, and blades, in conjunction with CMCs, to protect against corrosion, oxidation and thermal cycling, and provide thermal insulation [17,18,19,20]. Thereby EBCs effectively improve the durability and reliability of CMCs components, ensuring optimal performance and extending their service life, which contributes to the safe and efficient operation of aircraft engines.

Increasing operation temperature of aero-engines leads to aircraft more easily be detected in modern information technology warfare. The stealth of aero-engines and aircraft has become crucial to their capabilities to survive and penetrate defenses [21]. Therefore, stealth technology, also known as low detection technology, has become a prominent feature of next-generation fighter and a key focus of military powers [22,23,24]. Due to the high application ratio of radar wave and infrared detection, accounting for 60% and 30% respectively, radar and infrared stealth is particularly important. For the aeroengine of fighters, the radar scattering signals generated by the engine aft compartments, and the infrared radiation signals generated by hot-end components of the aft compartment and the exhaust jet account for over characteristic 95% of signals at the rear of the aircraft. Therefore, the aft compartments of engines must be made of high-temperature stealth materials to achieve low detection and also a high thrust-weight ratio [36, 37]. EB-PVD technology utilizes high-energy electron beams to bombard evaporative materials under vacuum conditions, rapidly heating them to convert into atomic and molecular forms, which then condense onto the preheated substrate surface to form a coating. EB-PVD coatings have a unique columnar crystal structure, which enables the coating to have high strain tolerance [38,62, 63]. For example, Guo et al. [64] selected Gd₂O₃ and Yb₂O₃ to co-dope YSZ, and confirmed that it exhibits better phase stability and lower thermal conductivity than the YSZ counterpart.

In order to meet the requirements of next-generation aeroengines, within the last decades much work has been done to explore novel promising TBCs candidates, which is generally restricted by some basic principle: 1) low thermal conductivity, 2) high fracture toughness, 3) no phase transformation from room temperature to the operating temperature, 4) TEC matching the metallic substrate, 5) high corrosion resistance against CMAS and molten salt, and 6) good sintering resistance. Several ceramic materials suitable for the topcoat of TBCs are summarized as follows.

2.1.1 Hexaaluminates

Lanthanate hexaaluminates (LnMAl₁₁O₁₉, M = Mg, Mn to Zn, Cr, Sm) with a magnetoplumbite-type structure are regarded as potential TBC materials due to the low thermal conductivity, high phase stability, excellent sintering resistance and high melting point [65, 66]. In particular, LaMgAl₁₁O₁₉ (LaMA) is the most interesting one [67]. LaMA/YSZ double-ceramic-layer (DCL) coatings produced via APS have long thermal cycling lifetime of ~ 11,749 cycles at ~ 1370 °C [68]. Note that during the spraying process, LaMA partially decomposes and forms much amorphous phase upon rapid cooling. In service, recrystallization of the amorphous phase at high temperatures probably affects the reliability of the coating [69].

2.1.2 Rare earth phosphates

Rare earth phosphates (REPO₄) exhibit low thermal conductivity, good chemical compatibility with TGO and high phase stability, which have been considered as promising candidates for TBC applications [70, 71]. Specially, it has been reported that REPO₄ (RE = Nd, Sm, Gd) is highly resistant to CMAS attack [72]. In addition, GdPO₄ has outstanding anti-corrosion behavior in the presence of V₂O₅ and V₂O₅ + Na₂SO₄ at 900 °C [73].

2.1.3 Rare earth zirconates

Rare earth zirconates (RE₂Zr₂O₇), first reported by Vaßen [74], possess lower thermal conductivity, higher melting point and better phase stability than traditional YSZ for application at high temperatures (> 1300 °C) [75]. RE₂Zr₂O₇ commonly has pyrochlore structure or defect fluorite structure (Fig. 1), which is determined by the r(RE³⁺):r(Zr⁴⁺) ratio, i.e., the former is formed when the value falls into the range between 1.46 and 1.78, otherwise the latter is formed [76]. The pyrochlore structure is generally written as A₂B₂O₆O´, in which A, B, O and O´ ions is located in 16c, 16d, 48f and 8b sites, respectively. Note that there is an unoccupied 8b site and the neighboring O^2– deviates from the common site. In comparison, the cations in defective fluorite structure are completely disordered and there is only one 8c site for O^2–.

Among these zirconates, Gd₂Zr₂O₇ has been reported to be the most promising one. The thermal conductivity of APS Gd₂Zr₂O₇ coating varies from 0.6 to 1.4 W m^–1 K^–1 depending on the temperature [77]. The TEC ranges between 10.4 × 10^–6 and 10.6 × 10^–6 K^–1, slightly lower than that of the YSZ coating [65, 78]. The distinct disadvantages of Gd₂Zr₂O₇ are its relatively low fracture toughness and chemical incompatibility with TGO. In order to extend the service life of Gd₂Zr₂O₇ coatings, Doleker et al. designed a Gd₂Zr₂O₇/YSZ DCL coating, and confirmed that its thermal cycles are nearly twice that of simple Gd₂Zr₂O₇ counterpart [79]. Furthermore, Guo et al. selected Yb₂O₃ to modify Gd₂Zr₂O₇, aiming to improve its thermophysical properties [80]. The optimized (Gd_0.9Yb_0.1)₂Zr₂O₇ exhibits very low thermal conductivity (0.8–1.1 W m^–1 K^–1, 20–1600 °C), and has been regarded as one of the most promising RE₂Zr₂O₇ materials (Fig. 2).

2.2 Thermal barrier coating fabrication technologies

Nowadays, EB-PVD and APS are the two main methods used for TBCs preparation [81,82,83]. During EB-PVD processing, the working pressure is low and can vary from 5 to 0.1 Pa, and sometimes even lower [84]. The high energy electron beam heats ingots, producing a steam that subsequently deposits on the surface of the substrate. This enables to produce columnar structured coatings with both intra- and inter-columnar porosities. EB-PVD TBCs exhibit high-strain tolerance and good erosion resistance but high thermal conductivity as compared to APS TBCs. Figure 3 shows a typical EB-PVD YSZ TBC microstructure in cross section [85]. EB-PVD has also been used to produce new ceramic compositions such as alternative stabilizers doped zirconia, fluorites, and pyrochlores [80, 86,87,88]. EB-PVD is a line-of-sight process. Only surfaces which are in direct line-of-sight to the coating source can be coated. Therefore, components with complex geometries and shadowed areas are very difficult to be coated homogeneously.

During APS processes, ceramic powder particles injected into the plasma jet are heated into molten or semi-molten splat, and accelerated simultaneously followed by deposition onto the substrate. A lamellar microstructure is obtained by the stacking of splats. It allows rapid coating manufacturing, and the produced coatings are thick (300 ~ 3000 μm) and porous (10–25%) which exhibits good thermal insulation [89, 90]. As reported, the thermal conductivity of APS YSZ can reach 0.8–1.2 W/(mK) [91]. However, APS coatings are unavoidable to have drawbacks, i.e., low thermal shock resistance especially for thick TBCs. In recent years, with the introduction of segmentation cracks, which run perpendicular to the coating surface, the thermal shock resistance of thick TBCs has been improved, however compromising the thermal insulation performance. Figure 4 shows the SEM micrographs of cross-section of APS YSZ coating with segmentation cracks from Ref. [89]. The segmentation cracks were accompanied by horizontally oriented branching cracks (as marked by arrows in Fig. 4). These cracks improve the strain tolerance of the coating as an opening of the cracks during tensile loading, similar to the behavior of inter-column gaps of EB-PVD coatings. Besides, APS is also a line-of-sight process.

PS-PVD is a newly emerging processing technology, which combines the advantages of APS (high deposition rates and cost-efficiency) and EB-PVD technologies [92]. It is developed based on the low-pressure plasma spray process (LPPS, also known as vacuum plasma spraying, VPS). However, the plasma jet of PS-PVD is greatly different from that of LPPS due to the lower working pressure (ranging from 1 ~ 2 mbar) and higher power plasma gun [93]. The plasma plume of PS-PVD can expand to more than 2 m long and 200–400 mm in diameter [41, 94]. Moreover, the temperature of supersonic plume can exceed 6000 K due to the high power level (> 100 kW). With this technology, the injected powder is not only molten into liquid droplets but evaporated to build up a columnar coating. By adjusting the spray parameters, different microstructures of coatings could be obtained [95,96,97], as shown in Fig. 5. Among the coatings investigated, the quasi-columnar coating exhibits the lowest thermal conductivity of around 1.1 W/mK at 1200 °C, and is highly strain tolerant during thermal shock tests [44]. Its erosion resistance is lower than that of EB-PVD coatings but at a level of standard APS TBCs with 15% porosity [93]. Besides, due to its high velocity and large dimension, the plasma gas stream is able to flow around complex geometries and “forced” to go through the shadowed areas, thereby making the PS-PVD a non-line-of-sight coating process [93]. This allows the complete coverage of parts having complex geometries and shadowed areas, such as multiple turbine air foils or double vanes. So far, with the use of suitable feedstock materials, many types of TBCs can be produced by PS-PVD such as La₂Ce₂O₇ and modified Gd₂Zr₂O₇ coatings [98,99,100].

Suspension Plasma Spraying (SPS) and solution precursor plasma spraying techniques (SPPS) are also very attractive for producing TBCs. Here by using liquid feedstock instead of solid particles, delivering finer particles was realized. This allows the generation of unique microstructures such as nano-sized architectures, high density of segmentation cracks, and columnar structures [101,102,103]. The unique structure imparts SPS/SPPS coatings superior properties as compared to conventional coatings, such as lower thermal conductivity, higher fracture toughness and higher strain tolerance. Since the last two decades, increasing work has been devoted to understand the SPS/SPPS process and properties of the obtained coatings. So far, SPS has also successfully been used to deposit novel TBCs like perovskites and pyrochlores coatings [104,105,106].

2.3 Thermal barrier coating corrosion and protection

High-temperature corrosion is a key factor causing TBCs premature failure, involving CMAS corrosion, molten salt corrosion, and their coupling corrosion. CMAS corrosion behavior of YSZ TBCs was first reported by Stott et al. [107], who collected natural CMAS from the Middle East and deposited it on APS TBCs, followed by heat treatment at 1300–1600 °C for 120 h. They found that the stabilizer Y₂O₃ is prior to dissolve into molten CMAS as compared to ZrO₂, causing the coating deficient in Y. As a result, the coatings undergo a phase transformation to m phase accompanied with excessive volume expansion. Then, Kramer et al. systematically investigated the CMAS corrosion mechanisms of TBCs, and proposed a dissolution–reprecipitation model [61], which has been accepted by many researchers in an aspect of thermo-chemical interaction. Besides, CMAS destroys TBCs in a thermal–mechanical interaction aspect. Molten CMAS penetrates the coating through its pores and micro-cracks, and solidifies during cooling. This causes the coating become compact, degrading its strain tolerance and producing large stress in the coating. When the stress is accumulated to a certain extent, the coating would spall off.

In view of the molten salt corrosion to TBCs, it occurs when the low-grad fuels are used. Na, S, V and other impurities in fuels are extremely corrosive to TBCs, especially at 600–1050 °C. Exposure to molten salt, rare earth elements in YSZ and other rare earth contained novel TBC candidates have high tendency to leach out [108,109,110,111,112]. This induces phase destabilization and microstructure destruction of TBCs, and also degrades thermo-physical and mechanical properties of the coating. As a result, the coating faces performance degradation and premature failure.

CMAS and molten salt coexist further aggravates the corrosion to TBCs. Naraparaju et al. found that in the presence of CMAS, CaSO₄ decomposes at much lower temperature, and the penetration ability of CMAS containing CaSO₄ in EB-PVD 7YSZ is stronger than its calcium sulfate-free counterpart [113]. Before, it was considered that CMAS attack only occurs in aero-engines, there was no CMAS issue in ship engine components because the probable operating temperature of marine engines is 200 ~ 400 °C below CMAS melting temperature (≥ 1100 °C). However, Shifler from Office of Naval Research (USA) and Choi from Naval Air Systems Command (USA) observed CMAS attack in ship engine components [114], and they first indicated that in marine environment, CMAS melts at much lower temperature due to the coupling of sea salt. When operated in inshore environment, the air with high humidity and high salt spray inhaled by gas engines contains much salt. Accordingly, CMAS and sea salt can be coupled attacking the TBCs. Guo et al. found that CMAS + salt (NaVO₃, Na₂SO₄ or NaCl) has lower melting point and viscosity than CMAS, e.g., the melting temperature of NaVO₃ + CMAS mixture is lower than that of CMAS by ~ 50 °C [123,124,125,126]. Some newly developed TBC materials, such as rare earth phosphate and Sc₂O₃ doped Gd₂Zr₂O₇, were reported to have some resistance to molten salt corrosion [127, 130]

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3 Environmental barrier coatings

3.1 Environmental barrier coating materials

Figure 8 shows schematic illustration of CMCs-EBCs system. They consist of a CMC substrate, a bond coat and an environmental barrier subsystem. This section introduces relevant typical coating materials according to different functional layers in the EBC system. Some materials which have not been studied maturely are not be discussed here.

3.1.1 Bond coat

Currently, silicon (Si) is the most commonly used bond coat material for EBC systems. It has relatively suitable physical and chemical properties, with some significant advantages as a bond coat material, as listed below [131].

1) Adhesion strength: silicon exhibits excellent adhesion to both the substrate and top coat material, providing structural integrity to the coating system (especially during thermal cycling). 2) Low thermal expansion: silicon exhibits low TEC ranging from 3.5 to 4.5 × 10^–6 K⁻¹, which closely matches that of SiC_f/SiC. This could minimize the generation of thermal stress during thermal cycling, thereby promoting the integrity and structural stability of the coating. 3) Oxidation resistance: Si bond coat forms a protective layer of silicon dioxide (SiO₂) upon exposure to high temperatures, which acts as a barrier against oxidation, preventing further degradation of the underlying substrate. 4) Compatibility: Si bond coat demonstrates good compatibility with a wide range of EBC interlayer materials, allowing for versatile coating design and system integration. 5) Ductility at high temperature: although silicon is a non-metal, it has ductility above the critical temperature of transformation. This is conducive to plastic deformation under stress, releasing stress and maintaining the integrity of the coating.

On the other hand, Si also has disadvantages as listed below. 1) Low operating temperature: the melting point of silicon is around 1410 °C, so the upper limit of its operating temperature does not exceed 1350 °C. Otherwise, the coating loses its adhesion in the high-speed high-pressure flame, and even silicon melts and loses. 2) Brittle behavior at low temperature: Si bond coat has relatively low fracture toughness and exhibits brittle behavior, making it susceptible to crack or damage under certain mechanical stress or thermal gradient [132]. 3) Limited erosion resistance: Si bond coat may be susceptible to erosion in harsh environments containing high-velocity particles or aggressive gases, potentially leading to coating degradation.

3.1.2 Environmental barrier subsystem

Barium-Strontium-Aluminosilicate

Barium-Strontium-Aluminosilicate (1-xBaO·xSrO·Al₂O₃·2SiO₂, 0 ≤ x ≤ 1, BSAS) has some key properties suitable for a successful EBCs material, e.g., low elastic modulus (70 ~ 100 GPa for dense BSAS [133]), matched CTE (4–5 × 10^–6 K⁻¹) with SiC_f/SiC CMCs, and excellent thermal cycle crack resistance. BSAS can be used alone or in combination with mullite, both of which have better performance than mullite coating.

Advantages of BSAS layer are as followings: 1) Chemical stability: BSAS demonstrates excellent chemical stability, making it resistant to the attack of corrosive gas and molten salts. This property helps protect the underlying substrate from degradation caused by chemical reactions. 2) Thermal expansion compatibility: BSAS has TEC that are relatively close to those of substrate materials, such as SiC_f/SiC CMCs or rare earth silicates. This compatibility reduces the risk of thermal stress-induced delamination or cracking. 3) Environmental durability: BSAS exhibits good environmental durability, enabling it to withstand harsh operating conditions, including thermal cycling, oxidation and erosion.

Disadvantages of BSAS layer are as followings: 1) Brittleness: BSAS is a brittle material, which means that it is prone to crack or damage under mechanical stress or impact. This limitation requires careful handling and consideration during manufacturing and application. 2) Limited high-temperature capability: at higher temperatures, its performance and stability can be affected by factors such as thermal gradients, phase transitions, or scoured by high-temperature, high-speed airflow [134].

Mullite

Mullite, an aluminosilicate compound, represents a continuous solid solution, and is the only stable compound within the Al₂O₃-SiO₂ binary system at atmospheric pressure. Its precise chemical composition is not fixed, which can be described as Al_4+2xSi_2-2xO_10-x, where x represents the loss of oxygen atoms in the unit cell, typically ranging from 0.2 to 0.9. Mullite exhibits a composition between 2Al₂O₃-SiO₂ and Al₂O₃-SiO₂, and the commonly encountered composition is 3Al₂O₃·2SiO₂, which is also the mullite component studied in EBCs research [135].

Mullite possesses several remarkable properties, including high melting point, low thermal conductivity, good resistance to creep, excellent chemical stability, and superior mechanical properties at high temperatures. Notably, its low TEC (~ 5 × 10^–6 K⁻¹) closely matches that of SiC_f/SiC CMCs, which enables mullite to be selected as a key material in the initial generation of EBC systems.

Advantages of Mullite layer are as followings: 1) Thermal stability: mullite exhibits excellent thermal stability, making it capable of withstanding high temperatures without significant degradation. 2) Low TEC: mullite has a relatively low TEC, which helps reduce thermal stress during thermal cycling. 3) Good chemical resistance: mullite is chemically inert and resistant to a lot of corrosive gas and molten salts. It forms a protective layer, preventing the penetration of corrosive species. 4) Mechanical strength: mullite possesses good mechanical strength, enabling it to withstand mechanical stress and resist deformation under normal operating conditions.

Disadvantages of mullite layer are as followings: 1) Limited high-temperature capability: at very high temperatures (≥ 1350 °C), Mullite would undergo phase transformation or grain boundary oxidation, which compromises its performance [19]. 2) Limited erosion resistance: mullite may not offer optimal erosion resistance in harsh environment with water vapor or high-velocity particles conditions. It is susceptible to erosion and mechanical wear, leading to coating degradation over time.

Rare earth silicates

Rare earth silicates (RE₂O₃·nSiO₂, RE-silicates, RE: Yb, Er, Lu, Y, etc.) are a class of materials with high melting points and high stability in water vapor. Compared to BSAS and mullite, RE-silicates possess moderate TECs (ranging 3–9 × 10^–6 K⁻¹), excellent high-temperature stability, chemical stability, and corrosion resistance in water vapor. These desirable properties render RE-silicates highly suitable for EBC applications [18]. They can be classified into two categories based on their chemical formula: rare earth monosilicate (RE₂SiO₅) and rare earth disilicate (RE₂Si₂O₇). Rare earth monosilicate can be divided into two crystal forms X1 phase (space group P2₁/C) and X2 phase (space group C2/c) due to the difference in RE elements [136, 137]. Rare earth disilicate, according to RE³⁺ ionic radius and sintering temperature, there are seven different crystal structures: A, B (or α), C (or β), D (or γ), E (or δ), F and G types [138].

Advantages of rare earth silicates layer are as followings: 1) wide-range TECs: the TEC gradient EBCs structure can be designed, which helps to minimize thermal stress and strain mismatch during thermal cycling. 2) high-temperature stability: RE-silicates demonstrate good thermal stability at elevated temperatures, allowing them to maintain their protective properties and withstand thermal cycling and high-temperature environment. 3) chemical stability: RE-silicates possess excellent chemical stability, making them resistant to corrosion and oxidation in harsh environment. 4) environmental durability: RE-silicates are highly resistant to water vapor, corrosive gases and molten salts, which provide effective environmental protection and help extend the lifespan of the coated components.

Disadvantages of rare earth silicates layer are as followings: 1) limited resource reserves and cost: some rare earth elements may be scarce and expensive, leading to cost consideration in large-scale applications. 2) limited operating temperature: the melting point of RE-silicates is generally in the range of 1700 ~ 1900 °C. As a result, the sintering of the coating becomes a critical factor in determining the upper limit of the operating temperature (usually within 1450 °C). 3) potential phase instability: depending on the specific composition and conditions, rare earth silicates may exhibit phase transformation or other forms of instability at high temperatures, which could affect their performance as EBCs materials.

3.1.3 Thermal barrier subsystem

In recent years, the development of thermal/environmental barrier coatings (TEBCs) with enhanced thermal insulation properties has gained attention as a mean to increase the surface temperature, as displayed in Fig. 9. TEBCs are an extension of traditional EBCs, and are currently in the emerging phase of research, focusing on exploring suitable coating materials and structures.

Currently, there are limited research reports in this field. The primary technical approach involves around utilizing oxides with an ultra-high melting point and low thermal conductivity as the surface layer. This design aims to create a significant temperature gradient within the coating, effectively increasing the surface temperature without elevating the temperature of the substrate. Compared with the traditional TBC material (YSZ), the operating temperature of the top coat of TEBCs is increased by at least 200 °C to 1450 °C and above, which has extremely stringent requirements on top coat and bond coat materials. Currently, candidates for research include but are not limited to hafnium oxide [139], hafnates [140], zirconates [141], LnMeAl₁₁O₁₉ [142], RE₃Al_xFe_5-xO₁₂ [143], and modified silicon-based bond coat [144], etc.

3.2 Environmental barrier coating fabrication technologies

3.2.1 Plasma spraying (PS)

PS method mainly includes atmospheric plasma spraying (APS), vacuum plasma spraying (VPS), and suspension plasma spraying (SPS). APS is widely used to prepare thermal/environmental barrier coatings on the surface of hot end parts of aero-engines and gas turbines. Chen et al. prepared (Yb_0.2Y_0.2Lu_0.2Ho_0.2Er_0.2)₂Si₂O₇ high-entropy rare earth double silicate coating by APS [145]. The phase structure of the coating is basically consistent with that of the powder, and the rare earth elements in the coating are evenly distributed on the atomic scale. The coating has excellent phase stability in high-temperature environment, and it also exhibit good resistance to water vapor corrosion at 1350 °C and CMAS corrosion at 1300 °C. Gao et al. fabricated Si/mullite/BSAS EBCs by APS on 2D SiC/SiC composites and studied their oxidation and corrosion behavior at 1200 °C in dry oxygen and water vapor [146]. They found that only a small part of SiC/SiC is oxidized and corroded, and the weight gain is much lower than the SiC/SiC without the protection of EBCs. Li et al. found that in a 90%H₂O-10%O₂ environment at 1300 °C, APS Si/Yb₂SiO₅/LaMgAl₁₁O₁₉ EBCs exhibit excellent resistance to water-oxygen corrosion [147]. ** at 1350 °C, while vertical cracks and cracks at the TGO-Si interface decreases [149]. Additionally, the formed Yb₂Si₂O₇ has good phase stability, TEC compatibility with Si, and is well adhered to TGO. Liu et al. prepared Yb₂SiO₅/Yb₂Si₂O₇/Si triple-layered EBCs by VPS, and investigated their corrosion behavior and mechanisms at 1300 °C /1400 °C from 25 to 50 h. The corrosion resistance of the EBCs at 1300 °C is good, and the temperature has a prominent effect on the EBC performance [150]. Compared with APS, the plasma jet speed and temperature of the VPS are significantly increased. Thus, the spray powder is heated more uniformly and its flight speed is higher, and the prepared coating is denser, the residual stress is reduced, the bond strength is higher, and especially the crystallinity of the silicate coating is improved to a certain extent.

SPS utilizes suspensions as the spray material, injecting them into the plasma flame through a specific feeding system. Rye et al. found that high-crystallinity Yb₂Si₂O₇ coatings prepared by SPS could be obtained by reducing the enthalpy of the plasma [151]. Li et al. studied the SPS Hf₆Ta₂O₁₇/Ta₂O₅ EBCs [168]. It was found that the coating shrinks significantly at 1500 °C, which is not suitable for EBC applications. Lee et al. chose the Yb₂Si₂O₇ as the top coat, Yb₂Si₂O₇ + mullite + Si for the bond coat, using the slurry impregnation method to prepare the EBC, and its water-oxygen corrosion behavior at 1427 °C was studied [169]. The results indicated that the coatings have good resistance to water oxygen corrosion. The advantage of slurry impregnation method is that the preparation process is simple, the coating bonding strength is high, and uniform EBC can be prepared on the complex shape workpieces. The disadvantage is that slurry impregnation method has relatively high requirements for slurry preparation (such as the particle size of EBC powder material and the concentration of slurry). Slurry impregnation method is similar to sol–gel method, which requires repeated impregnation and sintering to obtain EBCs with a certain thickness, resulting in high porosity and loose structure. More importantly, repeated high temperature sintering may also cause some damage to the fiber of CMCs.

3.2.6 Electron beam physical vapor deposition (EB-PVD)

The coating prepared by EB-PVD has a unique columnar crystal structure, which enables the coating to have high strain tolerance. Yokoi et al. utilized EB-PVD to prepare Yb₂Si₂O₇ coatings with single-phase and single-orientation structure under heating conditions of 1523 K, using high-purity Yb₂O₃ and SiO₂ ingots as the source materials [170]. The coating has a high-density columnar structure distributed perpendicular to the substrate surface, effectively isolating the erosion of corrosive substances. The EBC prepared by EB-PVD technology has high bonding strength, low surface roughness and high strain damage tolerance due to its columnar crystal structure, which leads to excellent thermal cycle life. However, the disadvantage is that the columnar crystal structure of the coating may provide channels for water–vapor and molten salt corrosion, and the preparation cost is high and the process is complicated. Due to the different saturated vapor pressure of each component in the coating material, the actual composition of the coating would be greatly different from that of the target material.

3.3 Corrosion and performance evaluation of environmental barrier coatings

3.3.1 Water vapor corrosion

Water vapor corrosion, also known as steam oxidation or water vapor attack, refers to the degradation or deterioration of materials when exposed to an environment containing water vapor. In the context of EBCs, water vapor corrosion refers to the corrosion or deterioration of the coating material itself due to interactions with water vapor. Water vapor corrosion occurs through various mechanisms, including oxidation, hydrolysis, and chemical reactions with the coating material. When water vapor contacts the SiC_f/SiC CMCs or EBCs surface, it reacts with the coating components, leading to the formation of corrosive products or compounds [171,172,173]. The reactions can be described as followings.

$$Si{O}_{2}+2{H}_{2}O\to Si{\left(OH\right)}_{4}(g)$$

(1)

$${RE}_{2}{Si}_{2}{O}_{7}+2{H}_{2}O\left(g\right)\to {RE}_{2}Si{O}_{5}+Si{\left(OH\right)}_{4}(g)$$

(2)

$${RE}_{2}Si{O}_{5}+2{H}_{2}O\left(g\right)\to {RE}_{2}{O}_{3}+Si{\left(OH\right)}_{4}(g)$$

(3)

These reactions change the coating's chemical composition, structural integrity, and protective properties, especially in the high temperature and pressure environment of aero-engines.

To safeguard SiC_f/SiC CMCs against corrosion and other detrimental factors, careful consideration must be given to both the coating structure and the materials utilized. EBCs aim to create a dense envelo** structure around the CMCs, as depicted in Fig. 13, providing a protective barrier against water vapor corrosion. Simultaneously, the EBCs material is selected to have a slow water vapor corrosion rate, and one determining factor is the activity of silica. The larger the silica activity, the higher the level of volatilization, which eventually leads to unacceptable recession levels on coatings.

Mullite not only has high activity of silica activity (0.3–0.4, 1300 °C [174]), but also has alumina activity, which is corroded to form Si(OH)₄ and Al(OH)₃. Monoclinic BSAS performs better, and its silica activity (< 0.1, 1300 °C [175]) is much lower than that of mullite. Therefore, BSAS can be modified or used to replace mullite, which can bring higher water vapor corrosion resistance. Rare earth silicates exhibit superior water vapor corrosion resistance compared to BSAS and Mullite. However, there is considerable variability in the volatilization rates of rare earth silicates. Nevertheless, a general consensus can be reached that, under similar conditions, monosilicates display lower volatility than disilicates, and disilicates exhibit volatility similar to that of BSAS [176].

3.3.2 CMAS attack

CMAS deposits are commonly observed on engine components. When CMAS melts, it triggers severe chemical and mechanical degradation of coatings, leading to delamination and peeling of the EBCs. Consequently, addressing the CMAS corrosion issue for EBCs is of utmost importance [177,178,179]. BSAS is vulnerable to CMAS corrosion. Even in dense BSAS, CMAS can corrode along grain boundaries to form anorthite (CaAl₂Si₂O₈), diopside (CaMgSi₂O₈) and celsian phase. Silicate is also corroded by CMAS to form RE-Ca–Si apatite phase, but the corrosion rate is slower than BSAS.

Two degradation mechanisms have been identified. One involves the reaction between molten CMAS and topcoat of EBCs. CMAS dissolves the EBCs and subsequently recrystallizes as a solid solution of RE-Ca–Si apatite with the appearance in occasions of β-SiO₂ cristobalite, forming a distinctive needle-like structure. The second mechanism is associated with the penetration of molten CMAS along grain boundaries, the growth proceeds with continuous re-nucleation of new crystals at the interface, reaching deeper regions of the EBCs and resulting in damage to the coating. It has been reported that the CaO content plays a crucial effect in the corrosion behavior and severity, and higher CaO content leads to a more nefarious interaction with the top coat in terms of recession rates and precipitation of RE-Ca–Si apatite [179,180,181,182,183].

The ionic radius of rare earth has an effect on corrosion products. Comparing the reaction products of different RE₂SiO₅ (Y, Lu, Yb, Eu, Gd and La) with CMAS at 1200 °C, RE₂SiO₅ with smaller RE³⁺ radius is easier to precipitate garnet phase, and RE₂SiO₅ with larger RE³⁺ radius is more likely to precipitate apatite phase. Hence, RE₂SiO₅ with smaller RE³⁺ radius is more effective in resisting CMAS corrosion than that with larger RE³⁺ radius [184].

3.3.3 Thermal cycling

Thermal cycling behavior is a critical performance indicator for EBCs, which can be evaluated through high-temperature furnaces or combustion devices. By subjecting the coating to repeated heating–cooling cycles and examining its durability under such condition, valuable insights can be gained regarding the longevity of EBCs. Analyzing the failure mechanisms could provide valuable guidance in optimizing the EBCs composition and manufacturing process.

EBCs often fail at the TGO interface during thermal cycling. In a high-temperature environment, the interface of Si bond coat undergoes oxidation, resulting in the formation of TGO. The oxidation rate is influenced by the ambient temperature and properties of the coating. During thermal cycling, thermal stress due to thermally grown low TEC silica scale could cause crack in the silica scale. From the perspective of reducing thermal stress, it is very important to choose materials with TECs close to that of CMCs and low modulus [185,186,187].

Furnaces testing

In the case of mullite coatings, Lee et al. reported that Mullite/YSZ coatings have reduced silica volatilization caused by water vapor [174]. The coatings were subjected to 1200, 1230 and 1300 °C thermal cycles for 500 times (cumulative time 1000 h), and all coatings are intact without failure. Furthermore, Basu et al. prepared Mullite/YSZ coatings and put them to a higher testing temperature of 1400 °C [188]. These coatings successfully survive 100 thermal cycles without exhibiting any signs of failure.

In the case of RE-silicates coatings, they perform well at 1300–1400 °C and in water vapor. Richards et al. reported that the Yb₂SiO₅/Mullite/Si coating system by APS has thermal cycle life of 725 times at 1316 °C in water vapor (90%H₂O-10%O₂, 1 atm) (60 min at 1316 °C, and 10 min at 110 °C) [189, 190]. A EBC system with a novel bond coat, consisting of layers of (Mulite + Yb₂Si₂O₇ + Al₂O₃ + Si)/(HfSiO₄ + Si)/(Mullite + Yb₂Si₂O₇), as developed by Lee et al. [169], was cycled at 1427 °C for 500 h (500 times) in water vapor, and its microstructure and composition remain stable, and the interface is bonded well.

Burner rig testing

Thermal cycling studies mentioned previously were conducted in high-temperature furnaces, where both the substrate and coating were exposed to the same temperature. However, in practical applications, temperature gradient exists between the coating and substrate along the thickness direction. In such scenarios, burner tests offer distinct advantages. This testing method involves applying a heat source, such as a flame or laser, to the sample's surface while cooling the backside of the sample, shown in Fig. 14. This approach generates a temperature gradient along the sample's thickness direction, simulating the conditions experienced in real-world usage environments.

Nevertheless, due to the consideration related to cost and safety, there is few research on burner rig testing about EBCs. A EBC system Si/Yb₂SiO₅/LaMgAl₁₁O₁₉, as studied by Hu et al., underwent 2718 cycles at a surface temperature of 1200 °C by burner rig [191]. In investigation of higher temperatures, Chen et al. conducted tests on the EBC systems of SiC/Yb₂Si₂O₇ and SiC/Yb₂Si₂O₇/La₂Zr₂O₇, featuring SiC as the bond coat [163]. The thermal cycling life at 1500 °C was determined to be 20 and 24 cycles, respectively (15 min heating and 1 min cooling).

Burner rig can not only test thermal cycle performance, but also inject various corrosive media, such as water, CMAS, etc., to evaluate the corrosion behavior caused by the coupling of multiple factors in the high temperature process. Bakan et al. investigated the impact of water vapor and im**ement angle on the thermal cycling performance of Si/Yb₂Si₂O₇ coating by burner rig tests [192]. The standard condition involved subjecting the coating surface to a 1250 °C flame in a dry state. Additional tests were conducted by injecting water into the flame at 90° and 45° angles for 500 cycles (5 min heating and 2 min cooling). Despite these conditions, the microstructure of the coating remains stable. Steinke et al. conducted an experimental study where H₂O and 0.1% CMAS solution were injected into the flame [193]. The thermal cycling was tested at 1230 ± 10 °C (5 min heating, 2 min cooling). The results demonstrated that the average cycle life of the YSZ coating without liquid injection is 3634 cycles, whereas the cycle life with H₂O injection exceeds 500 cycles (stopped). In the case of CMAS injection, the average cycle life is 81 cycles.

The above burner tests are carried out under normal pressure, but EBCs coatings are used in high-pressure and high-speed environment in aero-engines. Limited by the conditions of the simulation equipment, it is very rare to test the thermal cycle behavior of EBCs in a high-pressure burner. Currently, there are limited reports available from NASA that provides vague details [194]. These reports indicate that the test conditions employed by NASA can reach T ~ 1650 °C, P_total ~ 30 atm, P_H2O ~ 3 atm, v_gas ~ 30 m/s [195].

4 Stealth coatings

4.1 Microwave absorbing coating materials

When the flight speed of aircraft exceeds the sound velocity, the aircraft surface temperature increases significantly. For example, the front surface temperature of the aircraft reaches 350 °C when its flight speed is Mach 3 even though at a high altitude, and it further increases as the flying speed increases. Furthermore, the temperature of engine end components can even exceed 1000 °C due to the demand for a higher thrust-to-weight ratio of advanced aero-engines. The rear chamber of aero-engine is a large radar scattering source. Therefore, the application of high-temperature microwave-absorbing materials (MAMs) is urgently required on the surface of a high-speed-flying aircraft and hot-end engine parts.

In general, absorption mechanisms of MAMs on electromagnetic waves mainly include conductivity dissipation, dielectric dissipation and magnetic dissipation. However, due to the limitation of Curie temperature, MAMs at high-temperatures mainly rely on the dielectric and conductivity dissipation mechanisms [196]. According to Debye relaxation theory, the imaginary part of the permittivity (${\varepsilon }^{{\prime}{\prime}}$) indicating electromagnetic loss ability can be expressed by the following equation [197].

$${\varepsilon }^{{\prime}{\prime}}=\frac{{\varepsilon }_{s}-{\varepsilon }_{\infty }}{1+{\omega }^{2}{\tau }^{2}}\omega \tau \tau +\frac{\sigma }{\omega {\varepsilon }_{0}}$$

(4)

where ω is the angular frequency, τ is the polarization relaxation time, ε_s is the static permittivity, ε_∞ is the relative dielectric permittivity at the high-frequency limit, σ is the electrical conductivity, and ε₀ is the dielectric constant in vacuum. It can be inferred that a good conductivity of MAMs is beneficial for enhancing their ability to dissipate electromagnetic waves. This has been confirmed in many high-temperature conductive materials, such as SiC, TiC, and so on.

SiC has high strength, high hardness, lightweight, and good high-temperature resistance, making it an ideal material used in high-temperature conditions. However, pure SiC does not pose good dielectric performance, which can be enhanced through methods such as do** elements [198,199,200], adjusting SiC morphology [201,202,216]. Yang et al. prepared LSM/Al₂O₃ coatings with different LSM contents [217]. A good microwave absorption property is achieved when the LSM content is 80 wt.% and the coating thickness is 1.6 mm. Wu et al. [219] studied composites of (La_1-xSr_x)FeO₃ (LSF) and Al₂O₃, and found that the 80wt%-(La_0.3Sr_0.7)FeO₃/20wt%-Al₂O₃ composite presents the best electromagnetic wave absorption property (Fig. 15). The composite has minimum reflection loss of -38 dB (as shown in Fig. 15a) and effective absorption bandwidth (EAB: RL < -10 dB) up to 2.78 GHz.

Benefited from the various electromagnetic loss mechanisms, (La_0.3Sr_0.7)FeO₃/Al₂O₃ pseudo-binary composite shows excellent microwave absorbing performance with thin thickness, strong absorption and tunable EAB superiorities compared with traditional MAMs as shown in Fig. 16a. It was revealed that its superior microwave absorbing property is originated from space charge polarization caused by plenty of heterogeneous interfaces, dipole polarization introduced by do**, and conductive loss attributed to directional movement of charge carriers, as schematically illustrated in Fig. 16b.

Research on high-temperature MAMs primarily focuses on X and Ku bands, with less emphasis on electromagnetic wave absorption in the low-frequency range. To fulfill the future demand on lightweight, broadband materials with small thickness for absorbing low-frequency microwaves, metamaterials and frequency selective surfaces (FSS) has already been initiated, which exhibit enhanced reflection loss and widened frequency range compared to traditional microwave absorbing coatings. Wherein, the FSS are composed of periodic arrangements of subwavelength-sized elements, such as patches, on a conducting or dielectric substrate, as shown in Fig. 17 [220]. The geometry and spacing of these elements are carefully designed to create a desired response to incident electromagnetic waves, which can also be used in infrared stealth and microwave-infrared compatible stealth. Zhu et al. produced microwave-infrared compatible stealth via high-temperature NiCrAlY frequency selective surface upon Al₂O₃-TiC coating [220], and the well compatible performance reveled that the introduction of FSS improves the impedance matching within the different layers and decreases the thickness of the composite coating as low as 0.95 mm.

4.2 Infrared stealth coating materials

Objects at any temperature radiate infrared waves with a wavelength of 0.78 ~ 1000 μm. Due to the absorption by atmospheric molecules, the wavelengths that can be used for detection are only 0.76 ~ 1.1, 3 ~ 5 and 8 ~ 14 μm. According to Boltzmann's law, the energy radiated by an object is proportional to its surface temperature to the fourth power and its emissivity. In order to maintain a high thrust-to-weight ratio of the aero-engine, the service temperature of the engine's aft components is high, and thus applying coatings made of low-emissivity materials on high-temperature components is one of the effective approaches for achieving infrared stealth.

The interaction of metallic materials with electromagnetic waves is manifested as an in-band transition of free electrons, and its absorption wavelength is usually in the visible or ultraviolet band, and almost no absorption occurs in the infrared band. According to Kirchhoff's law, the emissivity of an object in thermal equilibrium is equal to the absorption rate. Therefore, metals exhibit extremely low infrared emissivity, and the emissivity of several typical metal materials at different temperatures is shown in Table 1. For high-temperature applications, metals with high melting temperature, low emissivity and good oxidation resistance are preferred such as Au, Pd, Pt and Rh [221]. As early as the 1960s, American Machin & Foundry company deposited Au films on the surface of Ni substrates realizing a surface emissivity of 0.05, but increased to 0.18 after 20 h at 800 °C [222]. Huang et al. studied emissivity of Au, Pt and Au/Ni composite films on Ni-based superalloys systematically. After high-temperature heat treatment, the average emissivity in 3 ~ 14 μm of Au film deposited on the rough surface increases from 0.15 to 0.69, while increases from 0.003 to 0.27 on the polished surface [223]. After annealing at 600 °C, the average emissivity of Pt film keeps 0.1, while that of Au/Ni composite film is still lower than 0.1 [224]. When the heat treatment temperature is elevated to 750 °C, the average emissivity increases sharply to about 0.6 [225]. Although the above noble metal has low emissivity, they undergo mutual diffusion with alloys at high-temperatures, and there are also disadvantages such as non-erosion and high costs.

Table 1 Typical melting point and infrared emissivity of metallic materials [226]

Full size table

The free carriers of some ceramic materials interacting with infrared light is similar to metals in the mid- and far-infrared wavelength range, thus they also have low emissivity. Moreover, ceramic coating materials have obvious advantages on high melting temperature, oxidation and corrosion resistance compared with metal coatings, so they are favored in the field of high-temperature infrared stealth. Emissivity of some metal non-oxides have been studied, such as ZrB₂. Zhang et al. successfully prepared ZrB₂ film by magnetron sputtering, and the average infrared emissivity in the 3 ~ 5 μm band and 8 ~ 14 μm band are 0.05 and 0.01, respectively, after annealing at 1000 °C in vacuum [227]. Nonetheless, if in an oxide environment, ZrB₂ is easily oxidized at temperatures higher than 600 °C as shown in Fig. 18, and consequently loses its low emissivity characteristic.

Because metal non-oxides would be oxidized at high-temperatures, oxides are also preferred for high-temperature applications. Similarly, do** and morphology control are commonly used to control the infrared properties of ceramics. Zhang et al. prepared YSZ coating on nickel-based alloy [228]. Within the temperature range of 900–1100 °C, the emissivity of the coating remains between 0.2 and 0.35 in the wavelength range of 3–5 μm. Zhao et al. prepared Y³⁺ and Ca²⁺ co-doped CeO₂ powder, in which CeO_0.8Y_0.15Ca_0.05O_2-δ exhibits a 3 ~ 5 μm infrared emissivity of only 0.24 at 600 °C [229]. Guo et al. studied the infrared emissivity of ZnO, and found that the flake structure powder prepared by sol–gel method has the lowest infrared emissivity, and the emissivity in the 3 ~ 5 um band does not exceed 0.55 below 600 °C [230]. On this basis, they continued to dope ZnO with Ce⁴⁺, which significantly changes the band structure of ZnO crystals, thus increases the carrier concentration in the crystals, effectively reducing the infrared emissivity to 0.329 at 500 °C [231]. Indium tin oxide (ITO) films prepared by magnetron sputtering shows an emissivity less than 0.2, and remains stable after 150 h of service at 700 °C [232]. Li et al. prepared different Al-doped SrZrO₃ perovskite powder, in which SZAO (SrZr_0.85Al_0.15O_2.925) is able to obtain an emissivity of about 0.33 in the 3 ~ 5 μm even after heat treatment at 900 °C for 200 h [233].

In addition to the intrinsic low emissivity of material, structure manipulation is another approach to achieve low emissivity. Through spectral selectivity design, coatings can maintain low emissivity in the infrared detection range (3 ~ 5 and 8 ~ 14 μm) while achieves high emissivity in the non-detection range (such as 5 ~ 8 μm) for efficient heat dissipation, further enhances infrared stealth effectiveness. Currently, the methods for achieving spectral selectivity mainly include photonic crystals and FSS.

Photonic crystals are man-made materials formed by the periodic arrangement of various dielectric materials with different dielectric constants (or refractive indexes) in space. Zhang et al. prepared a Mo/Si one-dimensional photonic crystal with a period number of 2. It reveals a good spectral selectivity characteristic, in which the emissivity in 3 ~ 5 μm and 8 ~ 14 μm are 0.26 and 0.36, respectively, and is as high as 0.75 in 5 ~ 8 μm when heated to 650 °C [234]. Liu et al. prepared a coating composed of a protective Ge layer, an ultra-thin Ag layer, a dielectric Ge layer and an Ag layer, and the TEM image is shown in Fig. 19a [235]. Results showed that the emissivity of the system is spectral selective as given in Fig. 19b, 0.18 in 3 ~ 5 μm, 0.31 in 8 ~ 14 μm, and 0.82 in 5 ~ 8 μm. Such structural design utilizes the combination of the tunneling effect of ultra-thin metal and the multi-beam interference effect of Fabry–Perot interferometer. Lee et al. designed and prepared frequency-selective surfaces using Au and ZnS (Fig. 20a and b), forming a metamaterial selective absorber/emitter through bands with wavelengths of 3–5, 5–8, and 8–14 μm, as given in Fig. 20c [236].

Certainly, whether it is FSS or photonic crystals, the ultimate operating temperature of the coating depends on the selected materials. Therefore, utilizing high-temperature stable materials in the fabrication process will be the future direction for the development of high-temperature infrared stealth coatings.

4.3 Stealth coating fabrication technologies

Although there is difference in the thickness between microwave absorbing coatings (millimeter-scale) and infrared stealth coatings (micron-scale), their fabrication techniques differ slightly. In many cases, the fabrication techniques for microwave-absorbing and infrared stealth coatings can be shared.

APS is the most common technology for fabricating microwave-absorbing coatings owing to its feasibility and low cost [21]. The center temperature of plasma jet can reach as high as 15,000 K, which can effectively melt almost any materials, and is thus very suitable for preparing oxide ceramic coatings such as LSM. Non-oxide ceramic coatings can also be deposited using APS such as TiC and MAX phase by carefully control spraying parameters. Yin et al. utilized APS to spray YSZ coating, and found that its emissivity can be as low as 0.46 in 3–5 μm [237]. Moreover, SPS was employed to prepare Al₂O₃-TiC based microwave-absorbing coatings by Zhu [220].

High-velocity oxygen fuel (HVOF) or High-velocity Air fuel (HVAF) technology possesses advantages of high velocity and low temperature (2400 K in HVAF) deposition. Accordingly, coatings prepared by HVOF have low oxygen content, good coating adhesion, and low porosity. Therefore, HVOF and HVAF are more suitable for producing oxidizable materials. Screen printing combined with sintering is also a common method for preparing microwave-absorbing coatings with FSS. Due to the typically intricate and complex structural design of FSS, screen printing is highly suitable and convenient to fabricate FSS structural coatings, as shown in Fig. 21 [238]. Besides screen printing, laser etching could be used for the fabrication of FSS coatings. For example, Cr₂O₃-TiO₂ [250, 251]. Christensen et al. pointed out that the addition of REs eliminates scale rumpling through releasing internal stress by changing the scale microstructure or forming a buffer layer between the scale and substrate and increasing their compatibility [252, 253]. Allam et al. reported that the formation of oxide pegs consisting of RE-rich oxide core and alumina sheath at the scale/alloy interface helps mechanically pin the scale [254, 255].

For the reduction of alumina scale growth rate, one of the broadly accepted mechanisms is the “modification of ion transport processes”, which has been verified by a combined characterization of O¹⁸ tracer and secondary ion mass spectroscopy (SIMS) [256, 257]. Pint et al. suggested that a continuous flux of RE ions diffusing from the alloy substrate to alumina grain boundaries under oxygen potential gradient during thermal exposure is critical to realize the reduction in alumina scale growth rate, and defined this mechanism as dynamic segregation theory (DST) [258]. Since grain boundary diffusion is dominant at temperatures below 0.6T_m of alumina, the alumina scale growth on NiAl alloys below 1573 K is usually completed by a simultaneous outward diffusion of Al and inward diffusion of O along alumina grain boundaries [259]. The segregation of RE ions at alumina grain boundaries inhibits Al outward diffusion in view of their larger size and slower diffusion rate, and the alumina growth mechanism is consequently transformed to inward diffusion of O. Since the diffusion rate of anions is slower than that of cations, the reduction in alumina scale growth rate is realized [260].

Li et al. conducted comparative research on different RE-doped NiAl alloys which has a guiding significance for composition design of NiAl coating materials [261]. It is found that all the alumina scales on the RE-doped NiAl alloys displays a double-layer structure comprised of inner equiaxed grains and outer columnar grains with close sizes rather than typical single-layer equiaxed grain structure due to the alternation of growth mechanism, and similar sizes revealed that similar amounts of RE ions are segregated on alumina grain boundaries producing similar grain refinement effects (Fig. 22) [258, 262]. Therefore, ion size should be the first order factor affecting the blocking effect of REs on the outward diffusion of Al. Dynamic segregation theory predicts that larger RE ion size has more remarkable effects on obstructing outward diffusion of Al ions because larger ions diffuse at a slower rate and occupy more of the diffusion pathway. However, Li et al. discovered that La ion has the largest radius, but its corresponding alumina scale growth rate is the highest. In contrast to this, the smallest Hf ion leads to the lowest alumina scale growth rate surprisingly (Fig. 23). This implies that physical obstruction is only one aspect of the blocking effect, and chemical interaction inevitably exists between RE and Al ions. A concept of effective ion radius proposed by Pint et al. can be introduced to explain the above abnormal phenomenon [263]. Hf ions may have larger effective radius due to additional interaction between Hf and Al. This interaction includes the influence of Hf ions on the electronic structure and diffusion activation energy of Al ions on alumina grain boundaries, which makes the blocking effect on outward diffusion of Al more significant.

With deepening the optimization work on NiAl coating materials, increasing studies confirmed that RE single-do** provides limited benefits in improving the cyclic oxidation resistance [257, 261, 264]. RE over-do** directly results in severe internal oxidation and accelerated alumina scale growth owing to its high oxygen affinity and low solid solubility in β-NiAl, while too low do** level takes no obvious effect on ameliorating the cyclic oxidation performance. A co-do** strategy has been proposed to solve this problem. An interesting work by Hou et al. indicated that Y and Al co-do** further reduces the oxidation rate of Tribaloy T-800 alloy as compared to Y single-do** [265]. Dryepondt et al. reported that the mass gain level of the Hf and Y co-doped FeCrAl alloy is remarkably lower than that of the single-doped alloys [245]. Lan et al. found that a combined addition of Dy and Pt leads to more effective reduction of oxidation rate than Dy or Pt single addition [266]. Furthermore, combined addition of RE dopants are already found in commercial alloys including René N5 and Haynes alloy 214 [267].

Based on the previous work, Guo et al. clarified the prospect of Hf + Zr and Y + La co-do** in reducing the alumina scale growth rate, and established fundamental understanding of the synergistic effect of two REs on the oxidation mechanism of alumina-formers [268]. It is proposed that Hf and Zr as well as Y and La ions co-segregate on alumina grain boundaries and act as an entire ionic cluster, which has stronger interaction with Al ions than two individual ions (Fig. 24a), thus producing a synergistic effect further reducing the alumina scale growth rate as compared to the single-doped alloys (Fig. 24b). Therefore, the RE co-do** strategy should be emphatically considered for composition design of future corrosion-resistant coating materials.

5.2 Corrosion-resistant coating fabrication technologies

There are two main categories of bond coats based on the fabrication techniques: diffusion coatings and overlay coatings [269]. The former can be further classified into simple aluminide coatings and platinum modified aluminide coatings (PtAl coatings). Simple aluminide coatings produced by aluminizing process from 1950s [270,271,272]. Usually, PtAl coatings are formed in four steps [273,274,275,276]. First, a thin layer of Pt (3–10 μm) is electro-deposited onto the surface of the superalloy. Secondly, Pt coating is diffused in vacuum, which is a heat treatment process for improving the adhesion between the Pt coating and substrate, and also diluting the Pt concentration. Thirdly, aluminizing process forms Al-rich coating, which includes many methods, such as slurry process [277,278,279], pack cementation [280, 281], above pack process [282, 283] and chemical vapor deposition (CVD) process [284, 285]. Finally, a suitable post heat treatment is conducted for coating formation, which also helps the superalloy recovering the lost mechanical properties, if any, caused by the high temperature exposure during the coating steps. Figure 25 shows the CVD equipment made by Beihang University.

Overlay coatings are typified by M-CrAl-X type coatings, where M represents Ni, Co or Fe (or a combination thereof), and X represents the reactive element additions, such as Y, Hf, Zr, Ce, La and so on. Overlay coatings can be manufactured by EB-PVD [286, 287], LPPS [288], HVOF/HVAF [289, 290], ion plating [291, 292], cold spray [293, 294] and electro deposition [295, 296]. EB-PVD is a coating process where the coating material is evaporated by electron beams and deposited on the substrate surface. The coating has a columnar microstructure, giving rise to excellent strain tolerance and thermal shock resistance. Figure 26 shows the EB-PVD 100 equipment made by Beihang University. However, the disadvantage of EB-PVD is that they have low deposition rate.

LPPS is a thermal spray process, which enables M-CrAl-X materials that are sensitive to oxidation to be sprayed. But the equipment is also expensive and the spray chamber needs to be pumped down every time. In order to reduce the running cost and enhance the efficiency, HVOF/HVAF spraying has been developed, which works by mixing fluid fuel and oxygen/air into a combustion chamber. The resultant gas has an extremely high temperature and pressure, and the stream of hot gas and powder is directed towards the surface. The obtained coating has low porosity and high bond strength, providing good corrosion resistance. HVOF/HVAF are operated in atmosphere, so its cost is much cheaper than LPPS and EB-PVD.

Ion plating is also known for its three-dimensional coverage and strong throwing power, which enable non-sight deposition for double vanes. Ion plating coating has high adhesion by sputter cleaning the substrate. Cold spray utilizes kinetic energy to project particles onto a surface through convergent – divergent De-Laval nozzle, accelerating the particles up to 200 ~ 1200 m/s, which produces dense and adherent coatings. Recently, electrolytic co-deposition has become a promising alternative method for applying M-CrAl-X coatings. This process involves co-depositing particles in an electroplated metal matrix by suspending fine powders within the solution, which in turn are embedded in the deposited matrix. This method was patented by BAJ Ltd. And purchase by Praxair later.

6 First-principles calculation used for high-temperature protective coatings

Premature failure of corrosion-resistant coatings and TBCs frequently manifests around the TGO layer, where chemical bonds are susceptible to deterioration. This degradation is typically initiated by microcrack nucleation, followed by propagation and coalescence, ultimately resulting in the peeling and delamination of coatings. To mitigate the premature failure of coatings, enhancing the interface strength between the TGO layer and underlying coating is of paramount importance. Consequently, researchers have endeavored to employ the first-principles calculation method to elucidate the bonding mechanism at the interface, from the aspect of density functional theory (DFT).

Carling et al. observed that the presence of impurity element S, alloy element Pt, and reactive element Hf at the interface of the corrosion-resistant coating results in the segregation of S, leading to a weakening of the interface and a reduction in the interface bonding strength [297]. This finding was further supported by Jiang, who obtained a similar conclusion [298]. Additionally, it is noted that the influence of Pt on the interface is minimal, and it even slightly decreases the interface bonding strength [297]. Furthermore, Guo et al. discovered that the formation of Dy-S bonds between Dy and S reduces the harmful effects of S, while also enhances the adhesion of the interface through bonding [299]. The reactive element Hf forms a direct bond with O atom in Al₂O₃ at the interface, resulting in enhanced interface bonding strength. The movement of Hf towards the oxide film further contributes to this improvement [297,298,299,300]. Comparing the effects of do** with Hf, Zr, Dy, Y, and La on the NiAl interface, it is observed that the α-Al₂O₃/β-NiAl interface bonding strength follows the order of Hf > Zr > Dy > Y > La > clean interface, as depicted in Fig. 27. This trend can be explained from an electronic perspective. Zhang's calculation demonstrated that the presence of impurity sulfur must be taken into account, and it was found that La and Y have the most significant impact on α-Al₂O₃/β-NiAl-S interface adhesion and mechanical stability [301]. The application of the first-principles allows for examining the enhanced interface adhesion of binary doped reactive elements in comparison to single do** (Fig. 28). The improvement on the interface adhesion could be attributed to the increased formation of chemical bonds at the interface and the synergistic effect resulting from the combination of (Hf + Zr) and (Hf + Y) co-do** [301, 302].

Corrosion of TBCs by molten CMAS results in the development of cracks and spallation failure, leading to a significant decrease in the TBCs' lifespan. Therefore, it is crucial to investigate the corrosion issue of TBCs when exposed to molten CMAS. Zheng et al. conducted first-principles calculation to determine the crack propagation mechanism of YSZ corroded by CMAS [303]. The weak atomic bond between ZrO and CaO facilitates crack nucleation, while cracks grow along the interface of CaAl₂Si₂O₈/Al₂O₃ and propagate along the interfaces of CaAl₂Si₂O₈/MCrAlY and MgAl₂O₄/Al₂O₃. The interfacial bond strength is relatively weak, and the atomic diffusion coefficient of CMAS surpasses that of YSZ. The splitting and spalling of TBCs primarily arise from the volume change of YSZ and the development of thermal stress [304]. Zheng et al. also conducted calculation on the penetration mechanism of high-temperature CMAS melt on YSZ, and determined that the surface of YSZ [(010) × (010)] exhibits high chemical activity, making it susceptible to corrosion by CMAS [305]. Additionally, the wettability of CMAS on the surface of YSZ (110) is found to be the highest [306]. Zhou et al. observed similar phenomenon in which CMAS melt infiltrates YSZ due to the strong aggregation ability of Y and Ca, enabling penetration into the coating [307].

To mitigate CMAS corrosion, TBCs have been modified through elements do**. For instance, Guo et al. discovered that Sc doped Gd₂Zr₂O₇/YSZ coating reveals enhanced separation of CMAS on the reaction layer's surface and reduces wettability, effectively inhibiting secondary CMAS penetration into TBCs [308]. The inclusion of Yb into GdPO₄ has been observed to expedite the development of the coating/CMAS interface reaction layer [309]. First-principles calculation revealed that Yb do** in Gd_0.75Yb_0.25PO₄ could reduce the apatite formation enthalpy when exposed to molten CMAS, which causes the apatite easy to form. This leads to a more compact and thicker interface reaction layer on the CMAS attacked Gd_0.75Yb_0.25PO₄ than that on the CMAS attacked GdPO₄, giving rise to enhanced CMAS resistance of Gd_0.75Yb_0.25PO₄ compared to GdPO₄. Additionally, the interface of the pellet/interface reaction layer of the CMAS attacked Gd_0.75Yb_0.25PO₄ is stronger than that of the CMAS attacked GdPO₄, which is also confirmed based on First-principles calculation by calculating the interface separation work. The incorporation of Yb into YSZ coating has an effect of diminishing the rate of atomic diffusion and augmenting the contact angle between CMAS and the coating, thereby mitigating the detrimental impact of CMAS onto the coating [310]. Furthermore, employing first-principles calculation, it has been determined that the inclusion of Gd in YSZ significantly diminishes the diffusion coefficient of elements. Additionally, the reduced Griffith fracture work at the YSZ/CMAS interface facilitates the flow of CMAS melt on the coating surface, thereby impeding osmotic corrosion of CMAS melt [311].

7 Outlook

YSZ has been the standard material for TBC applications since 1980s. Due to the continuous pursuit of higher operating temperatures of aero-engines for higher efficiency and performance, YSZ TBCs face many limitations. Future research should be focused on develo** TBC materials with better phase stability above 1250 °C, lower thermal conductivity and suitable fracture toughness and TECs, and designing novel coating microstructure and its fabrication technologies. Additionally, CMAS is still a major issue for at least the next decade, and thus its protection strategies need much attention. In marine environment, the coupling corrosion of CMAS and sea salt may emerge as a severe threat to TBCs. Some researchers have started to concern this, but the research is far from enough, especially the protection methods.

For higher gas-inlet temperature and thus higher efficiency and performance of aero-engines, CMCs are used to replace the hot-section metallic components, which need EBCs to provide protection against environmental degradation. The investigation on EBCs is not as mature as TBCs, and there is large research space. Various environmental factors, such as steam, CMAS and thermal cycling, cause degradation and failure of EBCs, which is a major hurdle for EBCs application. The understanding of all the interrelated failure mechanisms and development of protection methods are key to making progress in this field. EBCs is an application trend in advanced aero-engines. Therefore, by continuous investment in research, a fruitful and impactful research area is accepted to come.

The stealth of aero-engines is crucial to the capability of fighter to survive, and thus stealth technology is important, especially the radar and infrared stealth, which needs advanced high-temperature stealth materials and coating fabrication technologies. For the metallic components with relatively low operating temperature, thermal protection may be not necessary, but they still need protection against oxidation and corrosion. Hence, corrosion-resistant coatings are vital for aero-engines. Until now, at least three generations of corrosion-resistant coating system have emerged. For more efficient corrosion resistance, new coating materials and coating fabrication technologies need to develop. First-principles calculation is a useful tool, which can be used not only to design coating compositions, but also to clarify the coating failure modes and mechanisms.

High-temperature protective coatings including TBCs, EBCs, stealth coatings and corrosion-resistant coatings, are vital for aero-engines for higher efficiency and performance. To obtain effective, reliable, and manufacturable coatings, there is much work needing to be done. Although the road is obstructed and long, the work is of high significance and value, and would be an exciting and fruitful research field.

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Lei Guo, Wenting He, Wenbo Chen, Zhaolu Xue, Jian He, Yiqian Guo, Yang Wu, Lihua Gao, Dongqing Li, Zhao Zhang, Liangliang Wei, Yuyi Gao, Tiehao Zhang, Jiao Qiao and Qianhui Li contributed equally to this work.

Authors and Affiliations

School of Materials Science and Engineering, Beihang University, Bei**g, 100191, China
Lei Guo, Wenting He, Wenbo Chen, Zhaolu Xue, Yiqian Guo, Yang Wu, Lihua Gao, Dongqing Li, Zhao Zhang, Yuyi Gao, Tiehao Zhang, Jiao Qiao, Qianhui Li & Hongbo Guo
School of Materials Science and Engineering, Tian** University, Tian**, 300072, China
Lei Guo
Key Laboratory of High-Temperature Structural Materials and Coatings (Ministry of Industry and Information Technology), Beihang University, Bei**g, 100191, China
Wenting He, Jian He, Liangliang Wei & Hongbo Guo
State Key Laboratory of Silicate Materials for Architectures, Wuhan University of Technology, Wuhan, 430070, China
Wenbo Chen
Key Laboratory of Green Fabrication and Surface Technology of Advanced Metal Materials (Anhui University of Technology), Ministry of Education, Maanshan, 243002, China
Zhaolu Xue
Research Institute for Frontier Science, Beihang University, Bei**g, 100191, China
Jian He & Liangliang Wei
Faculty of Materials and Manufacturing, Bei**g University of Technology, Bei**g, 100124, China
Yang Wu
China Electric Power Research Institute, Bei**g, 102401, China
Dongqing Li
School of Materials Science and Engineering, Liaocheng University, Liaocheng, 252059, China
Zhao Zhang

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Lei Guo
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Wenting He
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Wenbo Chen
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Zhao Zhang
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Liangliang Wei
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This article is a result of group efforts. Lei Guo and Yiqian Guo wrote Sections 1 and 2.3; Yang Wu wrote Section 2.1; Lihua Gao wrote Section 2.2; Wenbo chen and Jian he wrote Sections 3.1 and 3.3; Zhaolu Xue wrote Section 3.2; Wenting He, Yuyi Gao, Tiehao Zhang, Jiao Qiao and Qianhui Li wrote Section 4; Dongqing Li wrote Section 5.1; Liangliang Wei wrote Section 5.2; Zhaozhang wrote Section 6; Hongbo Guo and Lei Guo designed the whole structure of the paper, wrote Abstract and Section 7, and also rewrote and reorganized the whole paper and made the final check.

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Correspondence to Hongbo Guo.

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Hongbo Guo is a member of the editorial board of this journal. He was not involved in the editorial review or the decision to publish this article. All authors declare that there are no competing interests.

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Guo, L., He, W., Chen, W. et al. Progress on high-temperature protective coatings for aero-engines. Surf. Sci. Tech. 1, 6 (2023). https://doi.org/10.1007/s44251-023-00005-6

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Received: 21 July 2023
Revised: 14 August 2023
Accepted: 15 August 2023
Published: 27 September 2023
DOI: https://doi.org/10.1007/s44251-023-00005-6

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Progress on high-temperature protective coatings for aero-engines

Abstract

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1 Introduction

2.1.1 Hexaaluminates

2.1.2 Rare earth phosphates

2.1.3 Rare earth zirconates

2.2 Thermal barrier coating fabrication technologies

2.3 Thermal barrier coating corrosion and protection

3 Environmental barrier coatings

3.1 Environmental barrier coating materials

3.1.1 Bond coat

3.1.2 Environmental barrier subsystem

Barium-Strontium-Aluminosilicate

Mullite

Rare earth silicates

3.1.3 Thermal barrier subsystem

3.2 Environmental barrier coating fabrication technologies

3.2.1 Plasma spraying (PS)

3.2.6 Electron beam physical vapor deposition (EB-PVD)

3.3 Corrosion and performance evaluation of environmental barrier coatings

3.3.1 Water vapor corrosion

3.3.2 CMAS attack

3.3.3 Thermal cycling

Furnaces testing

Burner rig testing

4 Stealth coatings

4.1 Microwave absorbing coating materials

4.2 Infrared stealth coating materials

4.3 Stealth coating fabrication technologies

5.2 Corrosion-resistant coating fabrication technologies

6 First-principles calculation used for high-temperature protective coatings

7 Outlook

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