Numerical Investigation of Work Cycle Characteristics in the Combustion Chamber of a Lox/Methane Liquid-Propellant Rocket Engine Featuring Reductant Power Gas Combustion

Authors: Sidlerov D.A., Fedorov S.A. Published: 29.06.2022
Published in issue: #2(141)/2022  

DOI: 10.18698/0236-3941-2022-2-43-53

Category: Aviation and Rocket-Space Engineering | Chapter: Thermal, Electric Jet Engines, and Power Plants of Aircrafts  
Keywords: liquid rocket engine, numerical simulation of combustion, lox/methane fuel


We performed a numerical investigation of cumulative efficiency and the structure in detail concerning the working process in the combustion chamber of a lox/methane liquid-propellant rocket engine operating in steady-state, boosted and throttled modes. In order to do it, we used tools developed by JSC SSC "Center Keldysh", that is, physical and mathematical models, numerical methods and software packages for numerical simulation of two-phase turbulent flows with combustion in liquid-propellant engine combustion chambers. The paper presents numerical simulation and investigation results concerning the specifics of fuel component flows, their mixing and combustion in the combustion chamber of a lox/methane liquid-propellant rocket engine using staged combustion cycle with reductant gas in steady-state, boosted (117 % by thrust) and throttled (30 % by thrust) operation modes. We performed a comparative analysis of work cycle parameters in combustion chambers at different fuel component consumption rates and pressure levels. The paper shows that the boosted mode increases the interaction of fuel jets, which intensifies mixing and burnout processes, while the deep throttling mode decreases the mixing and fuel burnout amplitudes as compared to the steady-state mode. The numerical simulation results may be used to investigate fuel combustion processes in combustion chambers of promising liquid-propellant rocket engines at the stages of development, design and refinement

Please cite this article in English as:

Sidlerov D.A., Fedorov S.A. Numerical investigation of work cycle characteristics in the combustion chamber of a lox/methane liquid-propellant rocket engine featuring reductant power gas combustion. Herald of the Bauman Moscow State Technical University, Series Mechanical Engineering, 2022, no. 2 (141), pp. 43--53 (in Russ.). DOI: https://doi.org/10.18698/0236-3941-2022-2-43-53


[1] Kalmykov G.P., Larionov A.A., Sidlerov D.A., et al. Numerical simulation and investigation of working process features in high-duty combustion chambers. J. Engin. Thermophys., 2008, vol. 17, no. 3, pp. 196--217. DOI: https://doi.org/10.1134/S1810232808030053

[2] Kalmykov G.P., Larionov A.A., Sidlerov D.A., et al. Numerical simulation of operational processes in the combustion chamber and gas generator of oxygen-methane liquid rocket engine. Progress in Propulsion Physics, 2009, vol. 1, pp. 185--204. DOI: https://doi.org/10.1051/eucass/200901185

[3] Koroteev A.S., Samoylov L.P. Choosing a path for development of sustainer liquid-propellant rocket engines for promising Russian launch vehicles. Kosmonavtika i raketostroenie, 1999, no. 15, pp. 111--119 (in Russ.).

[4] Klepikov I.A. Use of cooling properties of methane for increase of power of liquid propellant engines with afterburning of reducing gas. Herald of the Bauman Moscow State Technical Univtrsity, Series Mechanical Engineering, 2005, no. 1 (58), pp. 15--23 (in Russ.).

[5] Mykhalchyshyn R.V., Brezgin M.S., Lomskyi D.A. Methane, kerosene and hydrogen comparative as a rocket fuel for launch vehicle pneumohydraulic supply system development. Space Sc. & Technol., 2018, vol. 24, no. 2, pp. 12--17. DOI: https://doi.org/10.15407/knit2018.02.012

[6] Kalugin K.S., Sukhov A.V. Methane application specifics as a fuel for liquid rocket engines. Vestnik MAI [Aerospace MAI Journal], 2018, vol. 25, no. 4, pp. 120--132 (in Russ.).

[7] Lux J., Haidn O. Effect of recess in high-pressure liquid oxygen/methane coaxial injection and combustion. J. Propuls. Power, 2009, vol. 25, no. 1, pp. 24--32. DOI: https://doi.org/10.2514/1.37308

[8] Adzhyan A.P., Levochkin P.S. The peculiarities of development of fuel-rich preburner for methane multi-mode engine. Trudy NPO "Energomash" imeni akademika V.P. Glushko [Proceedings of NPO Energomash], 2012, no. 29, pp. 211--223 (in Russ.).

[9] Bregvadze D.T., Gabidulin O.V., Gurkin A.A., et al. Usage of oxygen-and-methane propellant in liquid-propellant rocket engines. Politekhnicheskiy molodezhnyy zhurnal [Politechnical Student Journal], 2017, no. 12 (17) (in Russ.).DOI: http://dx.doi.org/10.18698/2541-8009-2017-12-205

[10] Miroshkin V.V. Oxygen-methane LPRE with additional turbine. Trudy NPO "Energomash" imeni akademika V.P. Glushko [Proceedings of NPO Energomash], 2005, no. 23, pp. 256--270 (in Russ.).

[11] Voronkov A.F., Grebenyuk D.A., Ivanov V.A., et al. Oxygen-methane RD196 engine for system demonstrator of reusable first stage of MRKS-1. Trudy NPO "Energomash" imeni akademika V.P. Glushko [Proceedings of NPO Energomash], 2013, no. 30, pp. 243--259 (in Russ.).

[12] Muller H., Pitzner M. Large-eddy simulation of transcritical liquid oxygen/methane jet flames. Progress in Propulsion Physics, 2019, vol. 11, pp. 177--194. DOI: https://doi.org/10.1051/eucass/201911177

[13] Ruiz A. Unsteady numerical simulations of transcritical turbulent combustion in liquid rocket engines. Toulouse, Institut National Polytechnique, 2012.

[14] Yue C.G., Chang X.L., Yang S.J., et al. Numerical simulation of interior flow field of a variable thrust rocket engine. Adv. Mat. Res., 2011, vol. 186, pp. 215--219. DOI: https://doi.org/10.4028/www.scientific.net/AMR.186.215

[15] Wang Z. Internal combustion processes of liquid rocket engines. Singapore, Wiley, 2016.

[16] Dityakin Yu.F., Klyachko L.A., Novikov B.V., et al. Raspylivanie zhidkostey [Spraying liquids]. Moscow, Mashinostroenie Publ., 1977.