Characteristics of gaseous film cooling with hydrocarbon fuel in supersonic combustion chamber

The paper presents results of engineering studies and research and development efforts at RSC Energia to analyze and prove the feasibility of using the mass-produced oxygen-hydrocarbon engine 11D58M with 8.5 ton-force thrust as a basis for development of a high-performance multifunctional rocket engine with oxygen cooling and 5 ton-force thrust, which is optimal for upper stages (US), embodying a system that does not include a gas generator. The multi-functionality of the engine implies including in it additional units supporting some functions that are important for US, such as feeding propellant from US tanks to the engine after flying in zero gravity, autonomous control of the engine automatic equipment to support its firing, shutdown, adjustments during burn and emergency protection in case of off-nominal operation, as well as generating torques for controlling the US attitude and stabilizing it during coasting, etc. Replacing conventional engine chamber cooling that uses high-boiling hydrocarbon fuel with the innovative oxygen cooling makes it possible to get rid of the internal film cooling circuits and eliminate their attendant losses of fuel, while the use of the oxygen gasified in the cooling circuit of the chamber to drive the turbo pump assembly permits to design an engine that does not have a gas generator. Key words: Multifunctional rocket engine, oxygen cooling, gas-generatorless design, upper stage.

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Numerical study of liquid film cooling in a rocket combustion chamber

International Journal of Heat and Mass Transfer ◽

10.1016/j.ijheatmasstransfer.2005.06.017 ◽

2006 ◽

Vol 49 (1-2) ◽

pp. 349-358 ◽

Cited By ~ 24

Author(s):

H.W. Zhang ◽

W.Q. Tao ◽

Y.L. He ◽

W. Zhang

Keyword(s):

Liquid Film ◽

Combustion Chamber ◽

Film Cooling ◽

Numerical Study

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Computational investigation of multi-cavity fuel injection on hydrogen mixing at supersonic combustion chamber

International Journal of Hydrogen Energy ◽

10.1016/j.ijhydene.2020.01.096 ◽

2020 ◽

Vol 45 (15) ◽

pp. 9077-9087 ◽

Cited By ~ 19

Author(s):

Zhixiong Li ◽

Tran Dinh Manh ◽

M. Barzegar Gerdroodbary ◽

Nguyen Dang Nam ◽

R. Moradi ◽

...

Keyword(s):

Combustion Chamber ◽

Fuel Injection ◽

Supersonic Combustion ◽

Computational Investigation

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Influence of Polyisobutylene Kerosene Additive on Combustion Efficiency in a Liquid Propellant Rocket Engine

Aerospace ◽

10.3390/aerospace6120129 ◽

2019 ◽

Vol 6 (12) ◽

pp. 129 ◽

Cited By ~ 1

Author(s):

Igor Borovik ◽

Evgeniy Strokach ◽

Alexander Kozlov ◽

Valeriy Gaponov ◽

Vladimir Chvanov ◽

...

Keyword(s):

Combustion Chamber ◽

Film Cooling ◽

Rocket Engine ◽

Combustion Efficiency ◽

Liquid Propellant ◽

Gaseous Oxygen ◽

Wall Film ◽

Measurement Results ◽

Liquid Propellant Rocket Engine ◽

Propellant Rocket

The combustion of kerosene with the polymer additive polyisobutylene (PIB) was experimentally investigated. The aim of the study was to measure the effect of PIB kerosene on the efficiency of combustion chamber cooling and the combustion efficiency of the liquid propellant for a rocket engine operating on kerosene and gaseous oxygen (GOX). The study was conducted on an experimental rocket engine using kerosene wall film cooling in the combustion chamber. Fire tests showed that the addition of polyisobutylene to kerosene had no significant effect on the combustion efficiency. However, analysis of the wall temperature measurement results showed that the use of PIB kerosene is more effective for film cooling than pure kerosene, which can increase the efficiency of combustion chamber cooling and subsequently increase its reliability and reusability. Thus, the findings of this study are expected to be of use in further investigations of wall film cooling efficiency.

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Effect of cavity back height on mixing efficiency of hydrogen multi-jets at supersonic combustion chamber

International Journal of Hydrogen Energy ◽

10.1016/j.ijhydene.2020.07.001 ◽

2020 ◽

Vol 45 (51) ◽

pp. 27828-27836 ◽

Cited By ~ 1

Author(s):

Yu Jiang ◽

Amin Poozesh ◽

Seyed Maziar Marashi ◽

R. Moradi ◽

M. Barzegar Gerdroodbary ◽

...

Keyword(s):

Combustion Chamber ◽

Supersonic Combustion ◽

Mixing Efficiency

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Heat Transfer Analysis in a Modern DLN Combustor

Volume 3: Heat Transfer; Electric Power; Industrial and Cogeneration ◽

10.1115/2000-gt-0254 ◽

2000 ◽

Cited By ~ 3

Author(s):

Giovanni Ferrara ◽

Luca Innocenti ◽

Giacomo Migliorini ◽

Bruno Facchini ◽

Anthony J. Dean

Keyword(s):

Heat Transfer ◽

Combustion Chamber ◽

Film Cooling ◽

Thermal Flux ◽

Calculation Model ◽

Heat Transfer Analysis ◽

Turbine Blade Cooling ◽

Air Flows ◽

Critical Components ◽

Cooling Air

The increasingly stringent emissions standards in recent years have mandated low gas turbine emissions and thus changed the approach to combustion chamber design. In particular, lean burners based on highly premixed fuel-air flows have become more important. These combustors, termed Dry Low NOx (DLN), can now achieve emissions of 25 ppm and below in commercial operation. This development together with the inlet turbine temperature increase has resulted in less cooling air for combustion chambers and turbine blade cooling systems. The designer now needs to optimise cooling air flows that control the wall temperature of the components that confine the hot gases. Moreover, much of the air coming from the compressor is used to premix the fuel and only a smaller fraction is now available for cooling processes. In annular combustor configurations the air available for cooling the combustion chamber walls sometimes also has to cool the first stage nozzle. So the pressure loss along the combustor cooling passages has to be limited in order to assure a suitable supply pressure for these downstream cooling passages. We analysed the cooling air flow around the liner of an annular combustion chamber and we investigated the thermal flux and friction losses. In this paper we show the development of a calculation model that allows the critical components heat transfer analysis of a typical annular combustion chamber. The code developed is based on the generalised 1–D flow treatment. We have used experimental correlations for convection, film cooling and impingement borrowed from works found in literature. The code is provided with a graphical interface that helps the user during the calculation. This code was used in practical application to optimize the PGT5B combustion chamber cooling.

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