Abstract
This paper presents the computational methodology developed to simulate monomethyl hydrazine/nitrogen tetroxide (MMH/NTO) combustion. A three-dimensional rocket scale combustor domain with multi-element triplet injectors is utilized to study hypergolic flow and flame features. A Eulerian–Lagrangian framework is invoked for continuous phase treatment of combustion gas and discrete phase treatment for both MMH and NTO droplets. A discrete particle-based method (DPM) with finite rate chemistry is employed to study droplet injection, evaporation, and combustion. A description of flow and flame characteristics in three-dimensional RANS framework is presented in this paper. The model captures im**ing jets from multiple triplet injectors, and MMH film cooling injection appropriately. It presents physical trends on the core combustion process, as well as the global evolution of temperature, pressure, and droplet spray in the combustor. The focus of the study is to develop a hypergolic combustion model which can be used to predict combustion performance under off-nominal operating conditions. The aim is to extend the model to study the combustion instability aspects of MMH/NTO-based combustors.
Access this chapter
Tax calculation will be finalised at checkout
Purchases are for personal use only
Abbreviations
- \(\sim\):
-
Favre average (−)
- \(\rho\):
-
Density (kg/m3)
- \(u\):
-
Velocity (m/s)
- \(p\):
-
Pressure (Pa)
- \(t\):
-
Time (s)
- \(x\):
-
Dimension (m)
- T:
-
Temperature (K)
- \(i,j,k\):
-
Index (–)
References
Catoire L, Chaumeix N, Paillard C (2004) Chemical Kinetic model for mono methyl hydrazine/nitrogen tetroxide gas-phase combustion and hypergolic ignition. J Propul Power 20(1):87–92. https://doi.org/10.2514/1.9234
Catoire L, Chaumeix N, Pichon S, Paillard C (2006) Visualizations of gas-phase NTO/MMH reactivity. J Propul Power 22(1):120–126. https://doi.org/10.2514/1.10417
Jiang TL, Chiu H-H (1992) Bipropellant combustion in a liquid rocket combustion chamber. J Propul Power 8(5):995–1003 (1992)
Habiballah M, Lourme D, Pit F (1991) PHEDRE-numerical model for combustion stability studies applied to the Ariane viking engine. J Propul Power 7(3):322–329. https://doi.org/10.2514/3.23330
Knab O, Preclik D, Estublier D (1998) Flow field prediction within liquid film cooled combustion chambers of storable bi-propellant rocket engines. In: 34th AIAA/ASME/SAE/ASEE joint propulsion conference and exhibit. AIAA-98-3370. Cleveland, OH
Zhuang FC, Nie WS, Zou Q (1999) Numerical simulation of MMH/NTO rocket engine combustion instability. In: 35th AIAA/ASME/SAE/ASEE joint propulsion conference and exhibit. AIAA-99-2779. Los Angeles, CA
Ishikawa Y, McQuaid MJ (2007) Reactions of NO2 with CH3NHNH and CH3NNH2: a direct molecular dynamics study. J Mol Struct Theochem 818(1–3):119–124. https://doi.org/10.1016/j.theochem.2007.05.014
Hou L, Fu P, Ba Y (2018) Chemical mechanism of MMH/NTO and simulation in a small liquid rocket engine. Combust Sci Technol. https://doi.org/10.1080/00102202.2018.1551214
Qin J, Zhang H (2020) Numerical analysis of self-excited combustion instabilities in a small MMH/NTO liquid rocket engine. Hindawi Int J Aerosp Eng 2020:17. Article ID 3493214. https://doi.org/10.1155/2020/3493214
Xu KM, Cai GB, Zhou YT (2006) Flow field numerical study within thrust chamber of aerospace small liquid propellant rocket engine. In: AIAA 57th international astronautical congress, IAC, vol 10. Valencia, Spain, pp 6510–6519
Harvazinski ME, Huang C, Sankaran V, Feldman TW, Anderson WE, Merkle CL, Talley DG (2015) Coupling between hydrodynamics, acoustics, and heat release in a self-excited unstable combustor. Phys Fluids 27:045102
Zhang LB, Chu M, Xu X (2014) Performance prediction of apogee attitude and orbit control thruster for MMH/NTO hypergolic bipropellant. In: 50th AIAA/ASME/SAE/ASEE joint propulsion conference, Cleveland, OH, July 2014, p 3572
Ohminami K, Ogawa H, Uesugi KT (2009) Numerical bipropellant thruster simulation with hydrazine and NTO reduced kinetic reaction model. In: 47th AIAA aerospace sciences meeting including the 9ew horizons forum and aerospace exposition. AIAA-2009-452
Fluent ANSYS (2021) Ansys fluent 21 user’s guide. ANSYS, Inc., Canonsburg, PA
Sharma A, Tharakan JT, Kumar SS (2022) Analysis for design optimization of high thrust liquid engine hot test facility, Acta Astronaut 193:653–666. ISSN 0094-5765. https://doi.org/10.1016/j.actaastro.2021.07.047
Qiang W, Guozhu L (2019) Numerical simulation of ignition process for the monomethyl hydrazine–nitrogen tetroxide thrusters. J Propul Power 35(2):1–16. https://doi.org/10.2514/1.B37136
Acknowledgements
The technical help provided by ANSYS, India, team to conduct this study is kindly acknowledged.
Author information
Authors and Affiliations
Corresponding author
Editor information
Editors and Affiliations
Rights and permissions
Copyright information
© 2024 The Author(s), under exclusive license to Springer Nature Singapore Pte Ltd.
About this paper
Cite this paper
Sharma, A., Thannickal, V.M., John Tharakan, T., Sunil Kumar, S. (2024). Computational Modelling of MMH/NTO Combustion in a Multi-element Triplet Injector Combustor. In: Singh, K.M., Dutta, S., Subudhi, S., Singh, N.K. (eds) Fluid Mechanics and Fluid Power, Volume 4. FMFP 2022. Lecture Notes in Mechanical Engineering. Springer, Singapore. https://doi.org/10.1007/978-981-99-7177-0_25
Download citation
DOI: https://doi.org/10.1007/978-981-99-7177-0_25
Published:
Publisher Name: Springer, Singapore
Print ISBN: 978-981-99-7176-3
Online ISBN: 978-981-99-7177-0
eBook Packages: EngineeringEngineering (R0)