Review on the Relationship Between Liquid Aerospace Fuel Composition and Their Physicochemical Properties

Wang, **aoyu; Jia, Tinghao; Pan, Lun; Liu, Qing; Fang, Yunming; Zou, Ji-Jun; Zhang, **angwen

doi:10.1007/s12209-020-00273-5

Review on the Relationship Between Liquid Aerospace Fuel Composition and Their Physicochemical Properties

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Published: 21 November 2020

Volume 27, pages 87–109, (2021)
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Review on the Relationship Between Liquid Aerospace Fuel Composition and Their Physicochemical Properties

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**aoyu Wang^1,2,
Tinghao Jia^1,2,
Lun Pan^1,2,
Qing Liu^1,2,
Yunming Fang³,
Ji-Jun Zou^1,2 &
…
**angwen Zhang^1,2

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Abstract

The development of advanced air transportation has raised new demands for high-performance liquid hydrocarbon fuels. However, the measurement of fuel properties is time-consuming, cost-intensive, and limited to the operating conditions. The physicochemical properties of aerospace fuels are directly influenced by chemical composition. Thus, a thorough investigation should be conducted on the inherent relationship between fuel properties and composition for the design and synthesis of high-grade fuels and the prediction of fuel properties in the future. This work summarized the effects of fuel composition and hydrocarbon molecular structure on the fuel physicochemical properties, including density, net heat of combustion (NHOC), low-temperature fluidity (viscosity and freezing point), flash point, and thermal-oxidative stability. Several correlations and predictions of fuel properties from chemical composition were reviewed. Additionally, we correlated the fuel properties with hydrogen/carbon molar ratios (n_H/C) and molecular weight (M). The results from the least-square method implicate that the coupling of H/C molar ratio and M is suitable for the estimation of density, NHOC, viscosity and effectiveness for the design, manufacture, and evaluation of aviation hydrocarbon fuels.

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Introduction

Liquid hydrocarbon fuels are the dominant energy source in global air transportation, and they have developed rapidly in recent years. However, the sustained and steadily growing demand for air transportation has resulted in the increased aviation fuel consumption, which propels the diversified development of new alternative fuels from non-petroleum resources, e.g., oil sands, oil shale, coal, natural/shale gas, biomass, etc. [1]. Meanwhile, such development also presents new challenges to the performance of liquid hydrocarbon fuels. From a long-term and strategic perspective, the fundamental properties of hydrocarbon fuels should be further evaluated and improved to meet severe requirements. The difference in the physicochemical properties of aviation fuels should be attributed to their varied chemical composition [2]. Thus, the relationship between the chemical composition and properties of hydrocarbon fuels must be understood to support the development of new alternative fuels and enhance the properties of current aviation fuels.

Prior to being used, the physicochemical properties of aviation fuels, such as the density, net heat of combustion (NHOC), low-temperature fluidity, flash point, and thermal-oxidative stability, should be comprehensively evaluated. However, the measurement of fuel properties is time-consuming, cost-intensive, and limited to the operating conditions [3]. By contrast, fuel properties can be predicted based on their chemical composition; prediction of chemical composition requires a small amount of fuel sample. The correlations and predictions of fuel properties based on chemical composition have gained important guidance to the design and synthesis of new high-performance jet fuels.

In general, aviation fuels, such as Jet-A, mainly consist of several hydrocarbons with different molecular structures, including n-paraffins, iso-paraffins, cyclo-paraffins, and aromatics (see detailed composition in Fig. 1), coupled with trace amounts of oxygenates, olefins, and additives [4]. Although the composition–property relationship is complex due to the complex composition of fuels, the fundamental properties of aviation fuels can still be predicted based on their fuel composition [3, 5]. Vozka and Kilaz [3] provided composition analysis approaches, i.e., nuclear magnetic resonance (NMR), infrared (IR) spectroscopy, Raman spectroscopy, and gas chromatography (GC), for the prediction of jet fuel properties.

In this work, we summarized the effects of molecular structure on hydrocarbon properties and the relationship between the chemical composition and properties (including density, NHOC, low-temperature fluidity (viscosity and freezing point), flash point, and thermal-oxidative stability) of aviation fuels (Fig. 2). Additionally, we correlated the fuel properties with hydrogen/carbon molar ratios (n_H/C) and molecular weight (M). The results will be helpful for the design, manufacture, and evaluation of new aviation hydrocarbon fuels.

Density

Relationship Between Density and Fuel Composition

Density is a basic aviation fuel property that can influence the loaded fuel weight and aircraft range, which are important for the capacity of aircrafts, especially volume-limited vehicles [7]. Density is also useful in the flow rate calculation and the design of fuel metering system and fuel tank [8]. For aviation turbine fuels, the density is required to be 0.775–0.800 g/cm³ at 15 °C (ASTM D7566-18 [9] and D1655-18 [10]).

Chemical composition determines the density of hydrocarbon fuel. In general, the density of hydrocarbon fuels decreases in the order of aromatics > cyclo-paraffins > paraffins with the same number of carbon atoms, i.e., hydrocarbon fuels with a low H/C molar ratio have a high density. The density of kerosene fractions decreases linearly with the increase in paraffin content (Fig. 3a) [11]. n-Paraffins are generally denser than iso-paraffins because the branching chains can limit the molecular aggregation of hydrocarbons [12].

Fuel density can be promoted by increasing the cyclo-paraffin content. Elmalik et al. [4] observed that the density of the hydrocarbon blend composed of n-, iso-, and cyclo-paraffins showed a linear growth with the increase in cyclo-paraffin content (Fig. 3b). Cyclo-paraffins with cis configuration typically possess a higher density than their trans configurations (symmetry structure) because of the twisted structure of cis configuration, e.g., cis-decalin (0.897 g/cm³) versus trans-decalin (0.870 g/cm³) [13]. For alkyl-substituted cyclo-paraffins, such as methylcyclohexane (0.765 g/cm³), butylcyclohexane (0.796 g/cm³) [14], and l,2-dimethylcyclohexane (0.796 g/cm³) [15], the increased chain length of the alkyl substituent and alkyl substituent number can slightly increase the density. Moreover, the position of alkyl substituents affects the fuel density. Ortho-substituted cyclo-paraffins usually have a higher density compared with meta- and para-substituted cyclo-paraffins due to more compact molecules of the former, e.g., cis-l,2-dimethylcyclohexane (0.796 g/cm³) versus cis-1,4-dimethylcyclohexane (0.783 g/cm³) [15].

Aromatics possess a higher density than paraffins and cyclo-paraffins, and increasing the aromatic content can increase the fuel density [8]. Jia et al. [16] observed that the densities of RP-3 jet fuels with different hydrogenation degrees decreased linearly with the decline in the aromatic content because hydrogenation converted the aromatics into cyclo-paraffins (Fig. 3c). Similar to alkyl-substituted cyclo-paraffins, alkyl substituents in the aromatic ring influence the aromatic density. The decreased distance between alkyl substituents can improve the density of alkyl-substituted aromatic; thus, the density of ortho-substituted aromatic is higher than that of meta- and para-substituted aromatic, e.g., o-xylene (0.875 g/cm³) versus p-xylene (0.857 g/cm³) [17].

Meanwhile, the number of total carbon atoms can also influence the fuel density. As shown in Fig. 3d, the increase in the total carbon number of most hydrocarbons, except alkylbenzene and naphthalene, leads to a high density [1]. The density of alkylbenzene remains almost constant, whereas that of naphthalene declines with the increase in carbon number.

Table 1 compares the density of different hydrocarbon fuels. The relatively high density of RG-1 is possibly due to the high concentration of cyclo-paraffins. Similarly, on account of the high aromatic and cyclo-paraffin contents, JP-8, Jet A, and Jet A-1 possess higher density than JP-4 [18]. Compared with conventional jet fuels, most alternative jet fuels usually have a lower density due to their lower content of aromatics [5]. For instance, the densities of Fischer–Tropsch hydroprocessed synthesized paraffinic kerosene (FT-SPK) and hydroprocessed esters and fatty acids (HEFAs) with less than 0.5wt% of aromatics possess the density of 0.730–0.770 g/cm³, whereas the addition of 20vol% aromatics to FT-SPK can increase the density to 0.800 g/cm³ according to ASTM D7566-18 [9]. Al-Nuaimi et al. [19] used aromatic compounds as additives to improve the GTL SPK density. Although aromatics can increase the fuel density, aviation fuels with a high aromatic content can exhibit decreased ignition tendency, low resistance to extinction [20], and increased soot formation and emissions [21]. Hence, ASTM D7566-18 specifies a maximum aromatic volume content of 25.0% and a minimum content of 8.0% to ensure adequate lubricity [9].

Table 1 Properties of typical hydrocarbon fuels

Full size table

Hydrocarbons with a multi-ring molecular structure possess a high density, which is essential for high-density fuels [32]. Therefore, efforts have been exerted to synthesize high-density fuels that have a multiple-ring structure, such as RJ-4 (0.94 g/cm³), a mixture of exo- and endo-tetrahydrodimethylcyclopentadiene synthesized by hydrogenation of dimethylcyclopentadiene, and JP-10 (0.936 g/cm³) that is an almost pure component of exo-tetrahydrodicyclopentadiene synthesized by hydrogenation of endo-dicyclopentadiene (endo-DCPD) and catalytic isomerization [32,33,34]. Spiro-hydrocarbon fuels with additional rings can exhibit increased density; a high density of 0.952 g/cm³ was reported for spiro[cyclopentane-1,2′-norbornane] (C₁₁H₁₈) synthesized by the zeolite catalytic Mannich–Diels–Alder reaction of biomass and petroleum-derived feedstocks [35], whereas the density of spiro[4,5]decane (C₁₀H₁₈) can reach 0.870 g/cm³ [36]. Notably, liquid diamondoid fuels, such as alkyl adamantanes, alkyl diamantanes, and alkyl triamantanes, also present a high density due to their compact internal molecular structure [37,38,39,40,41].

Strained fuels containing three- or four-membered rings also possess high density. A typical strained fuel is quadricyclane (tetracyclo[3.2.0.0^2,7.0^4,6]heptane; QC, 0.983 g/cm³), which contains two three-membered rings and one four-membered ring [42,43,44,45]. Moreover, cyclopropanation, which was first reported by Simmons and Smith [46, 47] through the reaction of alkenes with diiodomethane and a zinc-copper couple, is an effective method for the formation of three-membered carbocyclic rings to increase the fuel density. Oh et al. [48] reported that the density of a series of cyclopropane-fused hydrocarbons synthesized by cyclopropanation of norbornene and DCPDs can reach 0.940–1.040 g/cm³. Therefore, the construction of a multi-ring structure is an important approach to obtain high-density fuels.

Based on the above demonstrations, fuel density is closely related to the molecular structure, total carbon number, and H/C molar ratio of fuels.

Correlation and Estimation of Density

On the account of a hydrocarbon fuel mixture, Eq. (1) gives an effective method to predict the density of a hydrocarbon mixture, showing a linear function of the mass fraction of each component [49].

$$\frac{1}{{\rho_{{{\text{mix}}}} }} = \sum\limits_{i = 1}^{n} {\frac{{x_{i} }}{{\rho_{i} }}}$$

(1)

where ρ_mix is the mixture density, and x_i and ρ_i are the mass fraction and density of ith component, respectively.

Correlation of Density and Composition of Fuels

Fuel density is generally dependent on the chemical composition. The fuel composition should be first analyzed by several approaches before the correlations of fuel density and the detailed composition are established.

Cookson et al. [50, 51] determined the mass fractions of n-paraffins, cyclo-paraffins combined with iso-paraffins, and aromatics through ¹³C NMR, high-performance liquid chromatography (HPLC), and GC to establish the linear expressions of composition and fuel density by multi-linear regression (MLR) analysis (Entries 1–4, Table 2). Then, the aromatic carbon and n-alkyl carbon contents were introduced to predict the fuel density (Entries 5–10, Table 2) [52, 53]. Liu et al. [54] determined the detailed composition of 80 jet fuels by GC–mass spectrometry (GC–MS) and categorized the chemical composition into eight hydrocarbon classes. With the help of an artificial neural network (ANN), they presented the multiple linear correlations of composition–property of fuels to predict fuel density (Entries 11–12, Table 2). Furthermore, Shi et al. [55] used two-dimensional GC with MS and flame ionization detector (GC × GC–MS/FID) to accurately measure the aviation fuel composition, which was sorted into 10 hydrocarbon classes and carbon numbers (C₇–C₁₉); they further developed the quantitative composition–property relationship of aviation fuels by different statistical algorithms, including weighted average (WA) method, partial least squares (PLS) analysis, genetic algorithm, and modified WA method. Moreover, the PLS regression models based on near-IR or Fourier transform IR spectroscopy (FT-IR) spectra can provide a practical method to predict fuel density [56,57,58]. Al-Nuaimi et al. [19] predicted the density of hydrocarbon mixture with mass fractions of n-, iso-, and cyclo-paraffins (Entry 13, Table 2). Gülüm et al. [59] proposed one- and two-dimensional regression models to predict the density of fuel blends based on the fuel composition and temperature. To simplify the correlations of composition–property, Yue et al. [60] proposed a unique regression model that correlates the density with H/C molar ratios and M of hydrocarbon fuels (Entry 14, Table 2).

Table 2 Correlations between density and fuel composition

Full size table

Correlation of Density Versus H/C Molar Ratio and M

The saturation degree of hydrocarbon molecular can be reflected by the H/C molar ratio. A high H/C molar ratio of hydrocarbon implies the decrease in molecular ring structures, especially aromatic ring structures, in aviation fuel [61], which will decrease the fuel density. Moreover, the M is a significant parameter for describing the molecular structure and the total carbon number of hydrocarbons. To simplify the correlation for practical application, we correlated the density data of 64 kinds of fuels, including aviation, synthetic hydrocarbon, alternative, and bio-jet fuels, with their H/C molar ratios and M (Table S1, Supporting Information, SI) by the least-square method.

Figure 4 shows the relationship between the density and n_H/C /M^0.19 of 64 hydrocarbon fuels, and Eq. (2) gives the linear regression equation for these fuels with a deviation of 6%. The result shows that the individual hydrocarbon fuels strictly follow the same tendency, i.e., the density decreases with the increase in n_H/C /M^0.19, and hydrocarbon fuels with the lower H/C molar ratio and higher M are prone to possess higher density.

$$\rho = 1.475 \pm 0.088 - 0.872 \times n_{{\text{H/C}}} /M^{0.19} \;(R^{2} = 0.92)$$

(2)

where ρ is the density of hydrocarbon fuels in g/cm³, and n_H/C and M are the hydrogen-to-carbon molar ratio and average M of selected hydrocarbon fuels, respectively.

NHOC

NHOC is the released energy obtained from the complete combustion of fuel, with products existing in the gaseous state [62]. As an indicator of the energy content of aviation fuels, NHOC directly determines the flying distance and payload of flight and is important for the combustion characteristics, stability, efficiency, and emissions of aviation fuels [63]. The NHOC can be represented by the gravimetric and volumetric NHOC. For most civil aircrafts with a restricted payload weight, the effective payload must be promoted by increasing the gravimetric NHOC. On the contrary, for volume-limited aircraft vehicles, such as rockets and missiles, in which the fuel tank must be designed to be small enough to save sufficient space for the electronic components and electrical equipment, the priority is to increase the volumetric NHOC for maximum flight range [32, 64, 65].

Gravimetric NHOC

Relationship Between Gravimetric NHOC and Fuel Composition

The gravimetric NHOC should be higher than 42.8 MJ/kg for conventional fuels and/or fuel blends to meet ASTM D7566-18 or D1655-18. However, no such restriction exists for synthetic fuels, except the synthesized iso-paraffin fuels with a minimum requirement of 43.5 MJ/kg.

The gravimetric NHOC is positively related to the hydrogen content (H/C molar ratio) of fuels [66,67,68]; more energy can be released from the complete combustion of hydrogen atoms per unit mass compared with carbon atoms. In general, the gravimetric NHOC of different types of hydrocarbons decreases in the following order: paraffins > cyclo-paraffins > aromatics with the same carbon number (Fig. 5) [1]. The molecular structure of n- and iso-paraffins and the position of alkyl substituents (e.g., 2- and 3-methylalkanes) have a minor effect on the gravimetric NHOC of paraffins due to the same H/C molar ratio. Moreover, the gravimetric NHOC of n-paraffins and iso-paraffins decreases with the increase in the carbon number owing to the reduced H/C molar ratio. However, for cyclo-paraffins and alkylbenzenes, the increase in the total carbon number leads to an almost constant and high gravimetric NHOC, respectively [1], because the H/C molar ratio of cyclo-paraffins remains constant, whereas that of the aromatics increases with the rise in carbon atom number.

Conventional jet fuels with high concentration of aromatics and cyclo-paraffins normally exhibit a low gravimetric NHOC [2] because of the low H/C ratio caused by the cyclic structure and unsaturated bonds [19]. As shown in Table 1, S-8 with 99.0 wt% saturated paraffins exhibits a higher gravimetric NHOC (44.1 MJ/kg) than other hydrocarbon fuels containing aromatics. Jia et al. [16] reported that the hydrogenation of Chinese RP-3 jet fuel can increase the gravimetric NHOC, which is negatively related to the aromatic content in linearity, from 43.0 MJ/kg to 43.2 MJ/kg. In addition, bio-jet fuels possess a higher gravimetric NHOC than conventional jet fuels due to the high concentrations of n- and iso-paraffins.

The high density of hydrocarbon fuels can be achieved at the cost of reducing the hydrogen content, leading to a low gravimetric NHOC [32]. For example, perhydrofluorene, which contains one five-membered ring and two six-membered rings, has a higher density (0.959 g/cm³) [69] than decalin (0.881 g/cm³) [60]; however, its gravimetric NHOC (41.81 MJ/kg) is lower than that of decalin (42.59 MJ/kg). Differently, strained hydrocarbon fuels (Table 3) can attain high density and gravimetric NHOC due to the extra strain energy stored in their three- or four-membered rings. The gravimetric NHOC of tricyclo[3.2.1.0^2,4]octane (0.94 g/cm³, 41.19 MJ/kg) with a three-membered ring is lower than that of tetracyclo[3.3.1.0^2,4.0^6,8]nonane (1.00 g/cm³, 43.09 MJ/kg) with two three-membered rings [48], indicating that increasing the number of strained rings leads to increased density and gravimetric NHOC. From Table 3, strained fuels with a strained ring molecular structure and low H/C molar ratio exhibit a high gravimetric NHOC, which is contrast to the result for multi-cyclic hydrocarbon fuel.

Table 3 Obtained properties of several strained hydrocarbons

Full size table

Correlation and Estimation of Gravimetric NHOC

The gravimetric NHOC of blended hydrocarbon fuels can be calculated from the NHOC of individual hydrocarbon components using Eq. (3).

$${\text{NHOC}} = \sum\limits_{i = 1}^{n} {(x_{i} \cdot {\text{NHOC}}_{i} )}$$

(3)

where NHOC_i and x_i are the NHOC in MJ/kg and mass fraction of ith fuel component, respectively.

ASTM D3338/D3338M-20 [71] and ASTM D4529-17 [72] provide the predicted gravimetric NHOC of hydrocarbon fuels (Entries 1–2, Table 4). Al-Nuaimi et al. [19] calculated the gravimetric NHOC of hydrocarbon mixtures with the mole fractions of n-, iso-, and cyclo-paraffins (Entry 3, Table 4). In view of the strong relationship between NHOC and hydrogen content, Antoine et al. [67] correlated the NHOC with the hydrogen content of different synthetic fuels (Entry 4, Table 4). Analogously, the H/C molar ratio was also used to predict the NHOC of different hydrocarbon fuels (Entry 5, Table 4) [60]. Similar to the prediction of fuel density, HPLC, ¹³C NMR, FT-IR spectra, GC, GC–MS, and GC × GC–MS/FID have been conducted to determine the fuel composition. Then, the correlations of gravimetric NHOC with the detailed composition can be established by different regression methods, such as the linear regression method, ANN approaches, and statistical algorithms. Cookson et al. [50,51,52] used HPLC, GC, and ¹³C NMR to determine the fuel composition and correlated the gravimetric NHOC with the detailed composition by the linear regression method (Entries 6–10, Table 4). Liu et al. [54] measured the fuel composition by GC–MS and further developed the relationship of composition–gravimetric NHOC by the ANN approach (Entries 11–12, Table 4). Shi et al. [55] determined the aviation fuel composition through GC × GC–MS/FID and correlated the gravimetric NHOC with the detailed composition by different statistical algorithms. In addition, PLS regression models combined with FT-IR spectra were used for the prediction of the gravimetric NHOC of hydrocarbon fuels [73].

Table 4 Correlations of gravimetric NHOC with other properties or fuel composition

Full size table

As discussed, the gravimetric NHOC of aviation hydrocarbon fuels is closely related to their hydrogen content. Thus, the H/C molar ratio is an important parameter for the correlation of gravimetric NHOC. Meanwhile, the number of total carbon atoms also affect fuel gravimetric NHOC. Thus, we correlated the gravimetric NHOC with H/C molar ratios and M of 64 hydrocarbon fuels (Table S1, SI) by the least-square method. As shown in Fig. 6, the correlation can be divided into two different groups: multi-cyclic hydrocarbon fuels containing five- or six-membered rings (red line) and strained hydrocarbon fuels with three- or four-membered rings (black line). For the former group, the relationship between gravimetric NHOC and n_H/C /M^0.02 for multi-cyclic hydrocarbon fuels containing five- or six-membered rings can be expressed as Eq. (4).

$${\text{NHOC }}({\text{MJ/kg}}) = 37.042 \pm 0.926 + 3.478 \times n_{{\text{H/C}}} /M^{0.02} \;(R^{2} = 0.78)$$

(4)

where NHOC is the net heat of combustion per unit mass for hydrocarbon fuel in MJ/kg and n_H/C is the hydrogen to carbon molar ratio.

From Eq. (4), a positively linear correlation exists between the gravimetric NHOC of most multi-cyclic hydrocarbon fuels and n_H/C /M^0.02 with an error of 2.5%, which proves that the H/C molar ratio determines the gravimetric NHOC for multi-cyclic hydrocarbons.

However, for the strained hydrocarbon fuels with three- or four-membered rings (Table 3), the correlation between gravimetric NHOC and n_H/C /M^0.02 exhibits a negatively linear correlation, as described in Eq. (5).

$${\text{NHOC }}({\text{MJ/kg}}) = 49.207 - 5.383 \times n_{{\text{H/C}}} \;/M^{0.02} \;(R^{2} = 0.61)$$

(5)

Although the increase in three- or four-membered rings reduces the H/C molar ratio, the stored strain energy contributes considerable combustion energy to the gravimetric NHOC. Thus, the gravimetric NHOC of strained fuel is negatively related to its H/C molar ratio.

Volumetric NHOC

Correlation Between Volumetric NHOC and Density

We correlated the volumetric NHOC of 59 hydrocarbon fuels (Table S1, SI) with the fuel density by using the least-square method, and the results are shown in Fig. 7. The volumetric NHOC of hydrocarbon fuels increases linearly with density (with R² of 0.98, Eq. (6)).

$${\text{NHOC }}({\text{MJ/L}}) = 5.01 + 37.064 \times \rho \;(R^{2} = 0.98)$$

(6)

where NHOC and ρ are the volumetric NHOC in MJ/L and density in g/cm³, respectively.

Given the positively linear correlation between the volumetric NHOC and fuel density, many studies attempted to synthesize high-density fuels to increase the volumetric NHOC and expand the flight distance [32, 35, 36, 69, 74, 75]. A crucial step toward high-density fuels is the synthesis of RJ-4 (39.0 MJ/L) with a density of 0.940 g/cm³ [34]. As the most widely used missile fuel, JP-10 (0.936 g/cm³) has a NHOC of 39.40 MJ/L [33], whereas QC (0.983 g/cm³), as a strained hydrocarbon fuel, has a higher NHOC (43.58 MJ/L) [45]. RJ-5 (the isomer of dihydrodinorbornadiene, 1.080 g/cm³) is the first aviation hydrocarbon fuel with a NHOC of 44.90 MJ/L; it is synthesized from cycloaddition reactions of norbornadiene, followed by hydrogenation and isomerization [34].

Correlation of Volumetric NHOC Versus H/C Molar Ratio and M

Given that the H/C molar ratio and M can serve as parameters to determine the fuel density, we correlated the volumetric NHOC with H/C molar ratios and M based on 59 hydrocarbon fuels (Table S1, SI); Eq. (7) describes the negative linear equation between the volumetric NHOC of hydrocarbons and n_H/C /M^0.19. The result in Fig. 8 shows that the volumetric NHOC decreases linearly with n_H/C /M^0.19 with R² of 0.93. Comparing Figs. 4 and 8, the density and volumetric NHOC present an excellent linear relationship with n_H/C /M^0.19, confirming the positive relationship between the volumetric NHOC and density, consistent with the result in Fig. 7.

$${\text{NHOC }}({\text{MJ/L}}) = 60.116 \pm 2.705 - 33.002 \times n_{{\text{H/C}}} \;/M^{0.19} \;(R^{2} = 0.93)$$

(7)

Low-Temperature Fluidity

Low-temperature fluidity, which can be quantitatively reflected and described by the low-temperature viscosity and freezing point of aviation fuels, is a vital character for the application of fuels, especially in environments with low temperature and high altitudes.

Viscosity

Relationship Between Viscosity and Fuel Composition

Viscosity is a fundamental physical property to quantitatively evaluate the fluidity of aviation fuel [65, 76,77,78]. ASTM D7566-18 specifies that the kinematic viscosity should not exceed 8.00 mm²/s (cst) at − 20 °C for aviation fuels, such as Jet A and Jet A-1. In general, the viscosity of hydrocarbon fuels increases with the M (total carbon number) [76]. As shown in Table 1, the viscosity of JP-5 is 6 mm²/s at − 20 °C, which is higher than those of JP-8 (4.10 mm²/s) and Jet A (5.20 mm²/s), due to its higher average M (166.3 g/mol). For aliphatic hydrocarbon fuels, the kinematic viscosity increases with the carbon chain length [77].

Cai et al. [79] proposed a quantitative structure–property relationship (QSPR) model to estimate and compare the viscosity (predicted and experimental) of different hydrocarbon class homologs (Fig. 9). The viscosity of n-paraffins, iso-paraffins, cyclo-paraffins, olefins, and aromatic homologs increases with the number of carbon atoms at a given temperature. With the same carbon number, cyclo-paraffins and aromatics are more viscous than paraffins [15, 61, 76]. Cyclo-paraffins with cis configuration have a higher viscosity than their trans configuration, e.g., cis-decalin (2.52 mm²/s) versus trans-decalin (1.75 mm²/s) at 40 °C [77], probably due to the increased molecular interaction caused by the twisted structure of cis configuration. The alkyl substituents also affect the viscosity of cyclo-paraffins. The increase in chain length of alkyl substituents increases the viscosity of alkyl-substituted cyclo-paraffins, e.g., methylcyclohexane (0.88 mm²/s) versus butyl-cyclohexane (1.22 mm²/s) at 40 °C [77]. Similar to density, viscosity can be affected by the position of alkyl substituents. Ortho-substituted cyclo-paraffins generally exhibit higher viscosity than meta- and para-substituted cyclo-paraffins possibly because of the more compact molecular structure of ortho-substituted cyclo-paraffins, e.g., cis-l,2-dimethylcyclohexane (1.40 mm²/s) versus cis-l,4-dimethylcyclohexane (1.12 mm²/s) at 20 °C [15]. n-Paraffins generally have a slightly higher viscosity than iso-paraffins. Geist and Cannon [15] evaluated the viscosity of 18 chemical isomers of octane and observed that not all isomeric octanes exhibit lower kinematic viscosity than n-octane, indicating that the branching level of saturated hydrocarbons can also affect fuel viscosity.

Aromatics can increase the aviation fuel viscosity [80], and their contributions to fuel viscosity vary with their molecular size and structures. Solash et al. [68] observed that the kinematic viscosity of coal-derived fuels increases steadily in a linear manner with the average molecular size of aromatics. Dixonand Clark [81] reported that the viscosity of alkylbenzenes increases with the number of substituted methyl groups, because the hyperconjugation effect of the aromatic ring and methyl group restricts the flow of alkylbenzenes. The position of alkyl substituents can also affect the aromatic viscosity. Similar to cyclo-paraffins, ortho-substituted aromatics usually have a higher viscosity compared with meta- and para-substituted aromatics, e.g., o-xylene (0.922 mm²/s) versus p-xylene (0.784 mm²/s) at 20 °C [15]. Overall, fuel viscosity is determined by the total carbon number, hydrocarbon class, and molecular structure.

Correlation and Estimation of Viscosity

As a thermodynamic property, the viscosity of blended fuels can be estimated by the Grunberg-Nissan equation [82,83,84]:

$$\ln \eta_{{{\text{mix}}}} = \sum\limits_{i = 1}^{n} {x_{i} \ln \eta_{i} } + \frac{1}{2}\sum\limits_{i = 1}^{n} {\sum\limits_{j = 1,j \ne i}^{n} {x_{i} x_{j} G_{ij} } }$$

(8)

where η_mix and η_i are the dynamic viscosity of fuel mixture and ith fuel component in mPa·s, respectively. x_i and x_j are the molar fractions of the fuel components i and j, respectively. G_ij is the interaction parameter between ith and jth fuel component in mPa s, and n is the total number of fuel components in the mixture.

Many studies attempted to estimate viscosity on the basis of molecular structure [56, 57, 73, 79]. Cai et al. [79] proposed a QSPR model to predict the hydrocarbon viscosity based on the basic groups, united group, and M of fuels. To simplify the relationship of viscosity and fuel composition, Yue et al. [60] correlated viscosity with the H/C molar ratios and M of hydrocarbon fuels by using an exponential regression model. To broaden the applicability of the model, we correlated the kinematic viscosities of 23 hydrocarbon fuels at − 20 °C (Table S1, SI) with H/C molar ratios and M by the exponential regression method (Fig. 10). The exponential regression (Eq. (9)) for kinematic viscosity and n_H/C /M ^0.54 indicates that the hydrocarbon fuels with low H/C molar ratios and high M preferentially have high viscosities.

$$v\;({\text{mm}}^{{2}} {\text{/s}}) = 1.898 \times 10^{4} {\text{e}}^{{ - 57.036 \times n_{{\text{H/C}}} \;/M^{0.54} }} \;(R^{2} = 0.91)$$

(9)

where v is the kinematic viscosity of hydrocarbon fuel in mm²/s.

Freezing Point

Relationship Between Freezing Point and Fuel Composition

Freezing point, as a key property to describe the low-temperature fluidity of fuel, is the temperature at which the solid wax and ice crystals formed in the previous cooling vanish when heated slowly [50, 85]. Aviation fuels operated at extremely low temperatures (or high altitudes) require a low freezing point to avoid the formation of hydrocarbon crystals that can cause clogging of the fuel supply system and other machine or operation problems [86, 87]. The freezing point of Jet A should be lower than − 40.0 °C, whereas the requirement for Jet A-1 is specified to be lower than − 47.0 °C according to ASTM D7566-18. The freezing point of hydrocarbon fuel is a crystallization behavior, in which molecular symmetry and intermolecular forces play the key roles [55, 88]. By measuring the freezing point of hydrocarbon mixtures, Affens et al. [86] reported that the data derived from Van’t Hoff equation of certain hydrocarbon mixtures were not in agreement with the literature data due to the strong intermolecular forces of the mixtures.

One important factor affecting the freezing point is the carbon chain length of hydrocarbon fuels; the freezing point of hydrocarbons increases with the number of total carbon atoms [88, 89]. Thus, catalytic hydrocracking of aviation fuels is a promising method to reduce the freezing point by shortening the carbon chain length [94])

Full size image

The effect of aromatic components on the freezing point has been also investigated. Hong et al. [94] noted that the addition of propylbenzene can reduce the freezing point of bio-jet fuel mixture (Fig. 11c). Similarly, Al-Nuaimi et al. [19] observed that GTL SPK blended with the conventional jet fuels has a low freezing point owing to the introduction of aromatics. The position of alkyl substituents can also affect the freezing point of aromatics. For instance, p-xylene (13.2 °C) exhibits a notably higher freezing point than o-xylene (− 25.2 °C) and m-xylene (− 47.9 °C) due to its better molecular symmetry.

In addition to the molecular structure, the average carbon number influences the freezing point. As shown in Table 1, JP-4 has the lowest freezing point temperature (− 62.2 °C) among the summarized fuels due to its relatively low average number of carbon atoms. S-8 and Chinese RP-3 jet fuels have a high average carbon number, but their freezing points are as low as − 59.0 °C and − 58.0 °C, respectively, owing to the high concentration of iso-paraffins, i.e. 82.0 wt% for S-8 [22] and 42.7 wt% for RP-3 [23].

Overall, hydrocarbon fuels with high molecular symmetry and intermolecular force generally have a high freezing point. Specifically, the freezing point of hydrocarbon increases with the number of total carbon atoms. For the same average carbon number, iso-paraffins and aromatics possess relatively low freezing points, whereas n-paraffin fuels show a high freezing point. Hence, the catalytic hydrocracking and hydroisomerization of aviation fuels are major methods used to reduce the freezing point.

Correlation and Estimation of Freezing Point

Al Mulla and Albahri [95] proposed an empirical method to calculate the freezing point based on the blending freezing point index (I_fr,blend), which is determined by the freezing point index of each fuel component, that can be calculated by the following equation:

$$I_{i} = 3.23 \times 10^{ - 6} \times 1.067^{{T_{{{\text{fr}},i}} }}$$

(10)

where I_i and T_fr,i are the freezing point index and the freezing point of ith fuel component in K, respectively. The blending freezing point index (I_fr,blend) can be obtained by Eq. (11).

$$I_{{\text{fr,blend}}} = \sum {(v_{i} \times I_{i} )}$$

(11)

where v_i is the volume fraction of the ith fuel component, and I_fr,blend is the freezing point index of the fuel blend. Therefore, the freezing point of fuel blends can be calculated by Eq. (12).

$$T_{{{\text{fr}}}} = 193.798 + 15.379 \times \ln (I_{{\text{fr,blend}}} )$$

(12)

where T_fr is the freezing point of the fuel blend in K.

Cookson et al. [50, 52, 53] used the MLR method to correlate the freezing point and the fuel composition detected by HPLC, GC, and ¹³C NMR (Entries 1–4, Table 5); the boiling range was introduced to develop several expressions (Entry 5, Table 5) [53]. Liu et al. [54] used GC–MS to determine the content of eight hydrocarbon classes and further correlated the freezing point by the ANN method (Entries 6–7, Table 5). Moreover, Shi et al. [55] classified the aviation fuel composition under 10 hydrocarbon classes and using the carbon number (C₇–C₁₉) obtained by GC × GC–MS/FID and used different statistical algorithms to correlate the freezing point and chemical composition. Hong et al. [94] correlated the freezing point of fuel blends with the volume content of propylbenzene (Entry 8, Table 5). Al-Nuaimi et al. [19] proposed several multiple nonlinear correlations between the freezing point and the composition of fuel blends composed of n-, iso- and cyclo-paraffins to predict the freezing points of blending fuels (Entry 9, Table 5). Analogous to the density and NHOC, PLS regression method based on FT-IR spectra can also predict the fuel freezing point [58].

Table 5 Correlations between freezing point and fuel composition

Full size table

To simplify the relationship between the freezing point and molecular structure of aviation fuels, we attempted to correlate the freezing point with H/C molar ratios and M; however, we failed to obtain a suitable model probably given the difficulty of reflecting molecular symmetry and intermolecular forces [55, 88].

Flash Point

Flash point is the minimum temperature at which a volatile fuel produces sufficient amount of vapor needed for the ignition with air upon encountering an external energy source, i.e., a spark or a flame [54, 55, 96,97,98]. In other words, flash point is the temperature at which flammable and ignitable vapor-air mixtures above the liquid fuel corresponds to a low flammable limit [54, 55, 99]. The flash point is an important physical property for the fire safety of processing, transportation, storage, and usage of fuel [100,101,102].

Relationship Between Flash Point and Fuel Composition

The flash point of hydrocarbon fuels can be measured using closed-cup or open-up methods [97, 99, 103]. For aviation fuels, the flash point obtained by closed-cup methods is greater than 38.0 °C according to ASTM D7566-18 and D1655-18. In general, the flash point, such as the 10% boiling point (T₁₀, the temperature at which the distillate volume reaches 10% of the fuel sample) which represents the initial behavior of distillation [76], is a linear function of the boiling point of hydrocarbon fuels [103]. From Table 1, the flash point is positively related to T₁₀, and JP-4 has a low flash point due to its low T₁₀.

The chemical composition of hydrocarbon fuels can affect the flash point, especially the low-flash-point fuel components [65]. Elmalik et al. [4] reported that the increase in n-paraffin concentration results in a linear decrease in the flash point of hydrocarbon blends composed of n-, iso-, and cyclo-paraffins due to the low flash point of n-paraffins, whereas the effect of cyclo-paraffin content on the flash point is unclear (Fig. 12a, b). Scheuermann et al. [58] reported that the introduction of aliphatic compounds with a low boiling point reduces the fuel flash point, whereas hydrocarbon fuels containing high-boiling-point aromatics exhibit high flash points. Typically, the flash point of iso-paraffins is lower than that of n-paraffins, and iso-paraffins with more molecular branches have a lower flash point at a given carbon number, e.g., 2,3-dimethylpentane (− 6.2 °C) versus 2,2,4-trimethylpentane (TMP) (− 12.2 °C) [104].

Cyclo-paraffins usually possess a slightly higher flash point than n-paraffins at the same carbon number, and cyclo-paraffins with cis configuration have a higher flash point than their trans configuration, e.g., cis-decalin (59.5 °C) versus trans-decalin (53.7 °C) [13] possibly due to the increased molecular interaction caused by the twisted structure of cis configuration. The position of alkyl substituent also influences the flash point of cyclo-paraffins. Ortho-substituted cyclo-paraffins generally have a higher flash point than para- and meta-substituted cyclo-paraffins, e.g., cis-1,2-dimethylcyclohexane (11.9 °C) versus cis-1,4-dimethylcyclohexane (5.9 °C) [104]. Similar to that of cyclo-paraffins, the flash point of aromatics can be influenced by the position of alkyl substituents, whereas the flash point of ortho-substituted aromatics is usually higher than that of para- and meta-substituted cyclo-paraffins, e.g., o-xylene (31.9 °C) versus m-xylene (24.9 °C) [104]. As illustrated in Fig. 12c, the flash point of all hydrocarbons (including paraffins, cyclo-paraffins, and aromatics) increases with the number of total carbon atoms [1].

Correlation and Estimation of Flash Point

Obtaining the experimental flash point of fuels is time-consuming and costly, especially for newly synthesized fuels; meanwhile, the methods for estimating and evaluating the flash point of aviation fuels are of considerable interest [97]. Wickey and Chittenden [105] proposed an experimental method to predict the flash point of fuel blends through the blending flash point index (I_fl,blend) obtained by using the flash point index of each fuel component; the calculation is as Eq. (13).

$$\lg (I_{i} ) = - 6.1188 + \frac{2414}{{T_{{{\text{fl}},i}} + 503.71}}$$

(13)

where I_i and T_fl,i are the flash point index and flash point in K of the ith fuel component, respectively. The blending flash point index can be obtained by Eq. (14).

$$I_{{\text{fl,blend}}} = \sum {(v_{i} \times I_{i} )}$$

(14)

where v_i is the volume fraction of ith fuel component, and I_fl,blend is the freezing point index of fuel blend. Therefore, the prediction of flash point can be described as Eq. (15).

$$T_{{{\text{fl}}}} = \frac{2414}{{6.118 + \lg (I_{{\text{fl,blend}}} )}} + 42.59$$

(15)

where T_fl is the flash point of fuel blend in K.

Vidal [106], Liu [107], and Phoon et al. [97] reviewed the studies on the prediction methods of flash point of flammability liquid mixtures. Such prediction methods can be categorized into boiling-point- or composition-range-based, molecular-structure-based, and vapor-pressure-based methods [97].

Given that flash point is related to the chemical composition, especially the carbon number of hydrocarbon fuels, several methods are used to predict and correlate the flash point based on fuel composition (Table 6). Liu et al. [54] used the ANN method to estimate the flash point based on the content of eight hydrocarbon classes of aviation fuels obtained from GC–MS, with a high R² of 0.90 (Entries 1–2, Table 6). Al-Nuaimi et al. [19] predicted the flash point of hydrocarbon mixtures based on the mole fractions and carbon number of n-, iso- and cyclo-paraffins, with a R² of 0.75 (Entry 3, Table 6). Shi et al. [55] further developed the quantitative composition–flash point relationship of jet fuels with statistical algorithms by determining the detailed composition based on GC × GC–MS/FID. Yue et al. [60] correlated the flash point of 14 kinds of hydrocarbon fuels with the H/C molar ratio and M by using the linear regression method, achieving a R² of 0.85 (Entry 4, Table 6).

Table 6 Correlations between flash point and fuel composition

Full size table

Furthermore, we correlated the flash point of 23 typical hydrocarbon fuels (Table S1, SI) with the H/C molar ratio and M using the least-square method (Fig. 13). The linear regression equation between the flash point and molecular structure (H/C molar ratio and M) can be described as Eq. (16), and the flash point decreases with the increase in n_H/C /M^1.79. However, the precise prediction of the flash point remains challenging, thus indicating the need for in-depth investigations.

$$T_{{{\text{fl}}}} = 131.008 - 3.548 \times 10^{5} \times n_{{\text{H/C}}} \;/M^{1.79} \;(R^{2} = 0.73)$$

(16)

Thermal-Oxidative Stability

In addition to propellants, aviation fuels are used as primary coolants to absorb the waste heat from the aero-engine system and other aircraft components. However, the rising temperature of fuels causes the formation of insoluble deposits, which may reduce the heat transfer efficiency and clog valves and filters in pi** and engine systems [108]. Thermal–oxidative stability refers to the resistance of aviation fuels to self-oxidation, decomposition, and undesirable carbon deposit formation, which can be attributed to several liquid-phase oxidation reactions, at the operating temperature for a short time. Thermal–oxidative stability can be described by thermal and oxidative stabilities, which can be assessed by the jet fuel thermal oxidation stability test (JFTOT) described in ASTM D3241 and the rapid small-scale oxidation test defined in ASTM D7545, respectively [5, 109].

Thermal Stability

The thermal stability of aviation fuels refers to their sensitivity to self-oxidation degradation and the capability to resist fuel deterioration for a certain period at elevated temperatures [110]. JFTOT is the standard test method to quantitatively measure the thermal deposit formation of aviation fuels from two aspects: the surface deposit on the test tube evaluated by visual tube rating (VTR) methods and the filter pressure drop after the test [5, 110]. The VTR color code should be less than 3 (range: 0–4; the larger the number, the heavier the deposit), and the filter pressure drop should be less than 25 mmHg (ASTM D7566-18 and D1655-18).

The thermal stability of jet fuels can be affected by numerous factors, including temperature, pressure, fuel composition, heteroatom content, and the catalytic activity of metal surfaces. Apart from temperature and pressure, thermal stability is determined by fuel composition and heteroatom content. In general, hydrocarbon fuels containing high concentration of aromatics and heteroatom-containing species exhibit intense deposit-forming tendency [111]. For instance, JP-8 exhibits poorer thermal stability than paraffinic fuels obtained from F-T synthesis or hydrogenation process due to its heteroatom-containing compounds [91], whereas synthetic fuels with low concentrations of aromatics and heteroatom components have higher thermal stability than crude fuels [111].

The presence of trace of heteroatom-containing compounds (e.g., thiophene (C₄H₄S), phenols (C₆H₆O), pyrroles (C₄H₅N), anilines (C₆H₇N), indoles (C₈H₇N), quinolines (C₉H₇N), and carbazoles (C₁₂H₉N)) has a negative influence on thermal stability [112] given their capability to form macromolecules that can enhance deposit formation. Beaver et al. [113] proposed that electron-rich heteroatom aromatic species, such as phenols, arylamines, and thiophenols, can be involved in the formation of fuel deposits. The existence of benzothiophenes (C₈H₆S) and other sulfur-containing cyclic compounds can reduce the breakpoint temperature (the highest temperature at which a fuel can meet the specification of VTR and filter pressure drop) of petroleum-based fuels, as reported by Westhuizen et al. [111]. Similarly, the breakpoint temperature of F-T fuel is notably higher than that of Jet A (370 °C for F-T fuel versus 270 °C for Jet A) due to the lower concentration of heteroatom-containing species and aromatics in F-T fuel [114]. On this basis, Jia et al. [16] applied the catalytic hydrogenation method to treat Chinese RP-3 jet fuel to remove the heteroatom components (e.g., sulfurs and phenols) and aromatic contents, thus promoting the fuel’s thermal stability.

DeWitt et al. [110] proposed that the oxidation and molecular growth of aromatics are the major routes for the deposit formation of SPK/aromatic fuel blends; these authors also stated that less steps are required for the growth of aromatics with high molecular size into insoluble deposit precursors. Ben Amara et al. [109] measured the thermal stability of HEFA aviation fuel with the addition of different aromatics by JFTOT test at 325 °C. As illustrated in Fig. 14a, the VTR color code and pressure drop of HEFA can satisfy the requirement of ASTM D7566-18, whereas the addition of xylene (25%), 1-methylnaphtalene (≥ 5%), and tetralin (≥ 15%) leads to the tube deposit rating above 3. Unexpectedly, the addition of 5% of xylene and tetralin can enhance the thermal stability of HEFA with the VTR color code less than 1. Only the pressure drop of 1-methylnaphtalene/HEFA (25/75) is higher than 25 mmHg (Fig. 14b), indicating that diaromatics can substantially reduce the thermal stability of aviation fuels.

Oxidative Stability

The oxidative stability of aviation fuels, different from thermal stability, emphasizes the propensity to react with the surrounding/dissolved oxygen at a moderate temperature to produce peroxides [115, 116]; this condition initiates thermal deposition. Although ASTM D7566-18 and D1655-18 mention no explicit stipulation for oxidative stability, the induction period (IP), which corresponds to the period needed to reach 10% oxygen pressure drop, can serve as an indicator to evaluate the oxidative stability of aviation fuels in accordance with ASTM D7545.

Fuel composition determines the oxidation stability [116, 117]. Paraffins have a poor oxidation stability, and thus, bio-jet fuels have relatively poorer oxidative stability than conventional jet fuels owing to their higher paraffin content [5]. For example, the IP (measured under 7 bar of oxygen pressure at 140 °C according to ASTM D7545) of HEFA (1 h) is considerably lower than that of Jet A (2.3 h) [109]. Chatelain et al. [118] reported that the IP of n-paraffins drastically decreases with the increase in carbon chain length and levels off at carbon numbers above 12 (Fig. 15a). The increase in tertiary carbon number can reduce the oxidative stability because the carbon–hydrogen bond dissociation energy on tertiary carbons is small, and the radicals formed are stable. Chatelain et al. also evaluated the oxidative stability of C₈ isomers (Fig. 15b) [119]; except that of TMP (2,2,4-trimethylpentane), the IP was inversely related to the increased branching level, which can be explained by the dissociation energy of carbon–hydrogen bond, where the carbon–hydrogen bond dissociation energy follows the order primary carbon > secondary carbon > tertiary carbon. For TMP, a quaternary carbon on which no hydrogen atoms can be abstracted exists.

Larsen et al. [120] reported that the oxygen consumption rate of tricyclic cyclo-paraffins at 110 °C is higher than that of n-paraffins and bicyclic cyclo-paraffins, indicating that cyclo-paraffins with more rings have poorer oxidative stability because of their increased number of tertiary carbon atoms. They also observed that alkyl-substituted cyclo-paraffins have a lower oxidative stability than unsubstituted cyclo-paraffins due to the increased number of tertiary carbon atoms (caused by the alkyl substituents).

Aromatics generally exhibit a higher oxidative stability than cyclo-paraffins and paraffins. For example, certain monoaromatics (1,3,5-trimethylbenzene) benefit the oxidative stability of synthetic fuels [121]; the addition of diaromatics can significantly improve the oxidative stability of HEFA [109]. From Fig. 16a, diaromatics have better oxidative stability than monoaromatics, indicating that the increase in aromatic molecular size can improve the oxidative stability, whereas the number and position of alkyl substitutes on benzene have minimal effect (Fig. 16b) [109]. As shown in Fig. 16c, aromatics have a higher oxidative stability than saturated cyclo-paraffins. Jia et al. [16] reported that the increase in hydrogenation degree of Chinese RP-3 jet fuel can cause the decrease in oxidation onset temperature and IP, both of which are positively correlated to the aromatic contents. Figure 16c also shows that the increase in side carbon length of aromatics or cyclo-paraffins contributes to a low IP [109], possibly due to the lower carbon–hydrogen bond dissociation energy of tertiary carbon in comparison with that of secondary carbon. These observations further confirm that aromatics have excellent oxidative stability compared with cyclo-paraffins and paraffins.

The chemical composition of aviation fuels can influence oxidative stability. For paraffins, the carbon chain length and branching level can influence oxidative stability. Cyclo-paraffins with more rings and alkyl substituents have poor oxidative stability. Aromatics possess better oxidative stability than cyclo-paraffins, and aromatics with a high molecular size exhibit a high oxidative stability. The number and position of alkyl substituents barely influence the oxidative stability of aromatics, whereas the increase in alkyl-substituent length reduces the aromatic oxidative stability. An inverse relationship exists between the oxidative and thermal stabilities of several aviation fuels, i.e., fuels that can be oxidized easily usually exhibit a desirable thermal stability. The relationship between oxidative and thermal stabilities should be further examined in detail.

Summary

The fundamental properties of aviation fuels are intrinsically affected by chemical composition. In this review, a series of physicochemical properties of aviation hydrocarbon fuels, including density, NHOC, low-temperature fluidity (viscosity and freezing point), flash point, and thermal-oxidative stability, were comprehensively summarized and evaluated from the perspective of detailed composition and molecular structure.

Fuel density is closely related to molecular structure, the total carbon number, and H/C molar ratio. The NHOC should be evaluated from two prospects: gravimetric and volumetric NHOC. For most hydrocarbon fuels, a high H/C molar ratio contributes to a high gravimetric NHOC. Strained fuels with a strained ring molecular structure and low H/C molar ratio exhibit high gravimetric NHOC. A positive correlation exists between volumetric NHOC and density. Low-temperature fluidity can be described by viscosity and freezing point. The total carbon number, hydrocarbon class, and molecular structure have significant influences on viscosity and freezing point. The flash point of aviation fuels can be influenced by low-boiling-point fuel components and the total carbon number. Thermal-oxidative stability can be categorized into thermal and oxidative stabilities. Thermal stability can be negatively affected by the contents of aromatic and heteroatom-containing species, whereas aromatics with a high molecular size can promote oxidative stability. The carbon chain length and branching level can influence the oxidative stability of paraffins. Cyclo-paraffins with multiple rings and alkyl substituents have poor oxidative stability.

Several predictions and correlations for the aviation fuel properties from the chemical composition reported in the literature were outlined. The results obtained from the least-square method indicate that the fuel density, gravimetric NHOC, volumetric NHOC, and viscosity can be feasibly estimated based on the H/C molar ratio and M. This review provided an in-depth understanding of the composition–property relationship, which is meaningful to the evaluation and improvement of fuel properties.

All these established correlations of fuel composition and property are needed to define and determine fuel chemical compositions by analysis approaches, such as ¹³C NMR, IR, GC, GC–MS, and GC × GC–MS, which show high accuracy in determining the fuel composition. Based on detailed composition, the correlations and predictions of hydrocarbon properties have meaningful implications on the development of aviation fuels. However, these predictions are significantly dependent on the analysis methods and correlation models, and certain limitations in the fuel composition determination and practical applications are still inevitable. Hence, further investigations for the detection of fuel chemical composition and the development of prediction methods need to be focused on to continuously improve the prediction accuracy.

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Acknowledgements

This work was supported by the Scientific Research Projects of the Ministry of Education of China (6141A02033522) and the National Natural Science Foundation of China (No. 21978200).

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Key Laboratory for Green Chemical Technology of the Ministry of Education, School of Chemical Engineering and Technology, Tian** University, Tian**, 300072, China
**aoyu Wang, Tinghao Jia, Lun Pan, Qing Liu, Ji-Jun Zou & **angwen Zhang
Collaborative Innovative Center of Chemical Science and Engineering (Tian**), Tian**, 300072, China
**aoyu Wang, Tinghao Jia, Lun Pan, Qing Liu, Ji-Jun Zou & **angwen Zhang
Department of Chemical Engineering, National Energy R&D Research Center for Biorefinery, Bei**g University of Chemical Technology, Bei**g, 100029, China
Yunming Fang

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**aoyu Wang
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Tinghao Jia
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Lun Pan
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Qing Liu
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Yunming Fang
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Ji-Jun Zou
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**angwen Zhang
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Correspondence to Lun Pan, Yunming Fang or Ji-Jun Zou.

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Wang, X., Jia, T., Pan, L. et al. Review on the Relationship Between Liquid Aerospace Fuel Composition and Their Physicochemical Properties. Trans. Tian** Univ. 27, 87–109 (2021). https://doi.org/10.1007/s12209-020-00273-5

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Received: 26 August 2020
Revised: 08 September 2020
Accepted: 12 September 2020
Published: 21 November 2020
Issue Date: April 2021
DOI: https://doi.org/10.1007/s12209-020-00273-5

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Review on the Relationship Between Liquid Aerospace Fuel Composition and Their Physicochemical Properties

Abstract

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About the interaction between composition and performance of alternative jet fuels

Comparative studies of oxygenated fuel synthesis with diesel from the measurements of density, speed of sound and refractive index

Response surface models for synthetic jet fuel properties

Introduction

Density

Relationship Between Density and Fuel Composition

Correlation and Estimation of Density

Correlation of Density and Composition of Fuels

Correlation of Density Versus H/C Molar Ratio and M

NHOC

Gravimetric NHOC

Relationship Between Gravimetric NHOC and Fuel Composition

Correlation and Estimation of Gravimetric NHOC

Volumetric NHOC

Correlation Between Volumetric NHOC and Density

Correlation of Volumetric NHOC Versus H/C Molar Ratio and M

Low-Temperature Fluidity

Viscosity

Relationship Between Viscosity and Fuel Composition

Correlation and Estimation of Viscosity

Freezing Point

Relationship Between Freezing Point and Fuel Composition

Correlation and Estimation of Freezing Point

Flash Point

Relationship Between Flash Point and Fuel Composition

Correlation and Estimation of Flash Point

Thermal-Oxidative Stability

Thermal Stability

Oxidative Stability

Summary

References

Acknowledgements

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