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Electrification of nozzle in a liquid rocket engine
Combustion, Explosion, and Shock Waves, 1995A method of electrical-physical diagnostics is developed and experimental studies are conducted of the process of nozzle electrification in a liquid rocket engine operating on a hydrocarbon fuel. The highest electric potential is shown to be realized at about a stoichiometric ratio of the components, i.e., when the flow velocity, temperature, and ...
A. V. Voronetskii +2 more
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Performances Study of Liquid Rocket Engine
Applied Mechanics and Materials, 2014The article presents the performance of the liquid rocket engine. It will study the combustion reaction of the liquid hydrogen and oxygen without thermal dissociation. The main elements studied are the influence of the exces of the oxidant on firing temperature, on exhaust velocity, on the evacutation temperature from the engine and on the ishotermal ...
Daniel Eugeniu Crunteanu +2 more
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Development of a Liquid-Propellant Rocket Powered by a Rotating Detonation Engine
Journal of Propulsion and Power, 2023This paper presents work on a demonstrator rocket powered by a rotating detonation engine (RDE) fed by liquid propellants. Key to the success of the project was the development of a suitably efficient and lightweight RDE. After selecting the propellants:
M. Kawalec +3 more
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On porous liquid propellant rocket engine injectors
Aerospace Science and Technology, 2008A novel injection concept for cryogenic liquid propellant rocket engines has been tested and verified successfully using an optically accessible combustion chamber. The injector consists of a porous faceplate made from sinter metal and five LOX posts arranged in a classical parallel showerhead configuration.
Lux, Johannes +2 more
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Design of liquid-propellant rocket engines
Journal of Machinery Manufacture and Reliability, 2012A design method for liquid-propellant rocket engines is proposed, on the basis of models adjusted in response to test results. This method increases the reliability of the results and reduces ground testing of the motors. The effectiveness of the method is confirmed by ground testing and flight experience with the motors developed by Salyut Design ...
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Simulation of liquid propellant rocket engine combustion instabilities
17th Aerospace Sciences Meeting, 1979A simulation technique for studying the high frequency combustion instabilities of liquid propellant rocket engines has been developed and used to investigate various aspects of instability phenomena. Of importance was investigation of the significance of the method of coupling the combustion and the gas dynamics of the system.
M. B. Ventrice, J. C. Fang, K. R. Purdy
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Journal of Fluids Engineering, 2019
The clocking positions between the inducer and the impeller have a certain impact on the performance of the high-speed centrifugal pump, which however, is often ignored by designers.
Baofeng Yang +4 more
semanticscholar +1 more source
The clocking positions between the inducer and the impeller have a certain impact on the performance of the high-speed centrifugal pump, which however, is often ignored by designers.
Baofeng Yang +4 more
semanticscholar +1 more source
Liquid oxygen monopropellants for rocket engines
30th Joint Propulsion Conference and Exhibit, 1994A series of tests were performed to determine the feasibility of premixing fuels with liquid oxygen to form a rocket engine monopropellant. The fuels sclccted for cvaluation were kerosene, motor oil, propane, natural gas, ground automobile tires, uncurcd R45HT binder and coal.
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Single-Phase Instability in Non-Premixed Flames Under Liquid Rocket Engine Relevant Conditions
Journal of Propulsion and Power, 2019Under rocket-relevant conditions, real-gas effects and thermodynamic nonidealities are prominent features of the flow field.
C. Traxinger, J. Zips, M. Pfitzner
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Analysis of liquid rocket engine exhaust plumes
Journal of Spacecraft and Rockets, 1971Liquid rocket propellant engine exhaust plume flow field, discussing mathematical models for combustion chamber, throat region and ...
A. Ratliff +3 more
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