Oxidizer-rich staged combustion rocket engines use and development in Russia

1995 ◽  
Author(s):  
Boris Katorgin ◽  
Vladimir Chvanov ◽  
Felix Chelkis ◽  
Irina Lozino-Lozinskaya ◽  
Lawrence Tanner
Keyword(s):  
Rocket Engines ◽  
Staged Combustion

Combustion Test of Oxidizer-Rich Single Triplex Injector Preburner for Staged Combustion Cycle Rocket Engine

2015 ◽  
Author(s):  
Su-Ji Lee ◽  
In-Sang Moon ◽  
Il-Yoon Moon ◽  
Seong-Up Ha
Keyword(s):  
Combustion Chamber ◽  
Dynamic Pressure ◽  
Rocket Engine ◽  
Rocket Engines ◽  
Fuel Injector ◽  
Staged Combustion ◽  
Combustion Pressure ◽  
The Republic ◽  
Combustion Tests ◽  
Combustion Cycle

In the Republic of Korea, research on staged-combustion cycle liquid propellant rocket engines (LPRE) is proceeding to improve efficiency of rocket engines. Recently oxidizer-rich preburner using single triplex injector is developed in relation to the main injector development and combustion tests have been performed. This preburner is designed to operate in nominal conditions with the combustion pressure of 10 MPa, OF ratio of 60. For a stable ignition, LOx is fed in two steps. Triethylaluminum-Triethylborane (TEAB) is used as hypergolic fuel for ignition, supplied through a fuel injector. Despite the small amount of fuel flow rate and high pressure condition, the combustion pressure was stably maintained around 10 MPa as designed. As a result of Fast Fourier Transform (FFT) of the combustion chamber dynamic pressure, 1L mode frequencies related to the acoustic instability and hydraulic resistance exist in the combustion chamber. But their amplitudes are less than 1% of the combustion pressure and it does not affect the combustion. Therefore combustion test is stably completed. In the near future, coupled tests with uni-element triplex injector preburner and uni-element gas/liquid injector main combustion chamber will be carried out.

scholarly journals A Study on Anti-oxidization Coating for Staged Combustion Cycle Rocket Engines

2018 ◽  
Vol 22 (5) ◽  
pp. 125-131
Author(s):  
Young-June Kim ◽  
Byong-ho Rhee ◽  
Yong-Oh Noh ◽  
Byung-Hyun Bae ◽  
Seong-Yoon Hyun ◽  
...  
Keyword(s):  
Rocket Engines ◽  
Staged Combustion ◽  
Combustion Cycle

Experiments on an Oxidizer-Rich Preburner for Staged Combustion Cycle Rocket Engines

2014 ◽  
Vol 30 (4) ◽  
pp. 1098-1103 ◽  
Author(s):  
Sang Hun Kang ◽  
Ilyoon Moon ◽  
Soo Yong Lee
Keyword(s):  
Rocket Engines ◽  
Staged Combustion ◽  
Combustion Cycle

scholarly journals Influence of propellant leakage from pump area into turbine area on turbo-pump operation stability

2021 ◽  
Vol 27 (1) ◽  
pp. 97-102
Author(s):  
M.V. Andriievskyi ◽  
◽  
Yu.O. Mitikov ◽  
Keyword(s):  
Combustion Engine ◽  
Specific Impulse ◽  
Liquid Oxygen ◽  
Stable Operation ◽  
Rocket Engines ◽  
Staged Combustion ◽  
Pump Operation ◽  
Operation Stability ◽  
The Stability ◽  
Propellant Rocket

There is an increasing trend to liquid-propellant rocket engines which run on eco-friendly storable propellant. This trend is mostly dictated by the refusal to use traditional toxic storable propellant in many countries. The most widespread eco-friendly storable propellant is hydrogen peroxide with kerosene. Though, this propellant has a lower specific impulse in comparison with traditional liquid oxygen with kerosene. To compensate the loss of specific impulse, there is a reason to design a staged combustion engine. Evidently, the turbopump is the most complicated system in the staged combustion propulsion system. This fact makes research devoted to turbo-pumps a top priority. The paper aims to determine the influence of propellant leakage from the pump area into the turbine area and create recommendations which would allow organizing the stable operation of turbopump. As a result of turbopump staged combustion cycle testing, a conclusion had been made that leakage, which opens during the test, significantly influences the stability of turbopump operation. Depending on the amount of leakage, the turbine generated power drop was between 20 and 45%, which led to a decrease in rotation speed and outlet pressure of the pump. During the R&D process, a way of leakage influence elimination had been offered. Formulated recommendations may be used during the design process of the turbopump for staged combustion liquid propulsion systems.

Cycle optimization of the staged combustion rocket engines

2017 ◽  
Vol 89 (2) ◽  
pp. 304-313
Author(s):  
Davood Ramesh ◽  
Hasan Karimi M. ◽  
Massoud Shahheidari
Keyword(s):  
Propulsion System ◽  
Rocket Engines ◽  
Combustion Engines ◽  
Staged Combustion ◽  
Mixture Ratio ◽  
Content Type ◽  
Second Stage ◽  
C Programming Language ◽  
C Programming ◽  
Tank Pressure

Purpose The purpose of this paper is to introduce new and modified “staged combustion” cycles in the form of engineering algorithm as a possible propulsion contender for future aerospace vehicle to achieve the highest possible “total impulse” to “mass” of propulsion system. Design/methodology/approach In this regard, the mathematical cycle model is formed to calculate the engine’s parameters. In addition, flow conditions (pressure, temperature, flow rate, etc). in the chamber, nozzle and turbopump are assessed based on the results of turbo machinery power balance and initial data such as thrust, propellant mixture ratio and specifications. The developed code has been written in the modern, object-oriented C++ programming language. Findings The results of the developed code are compared with the Russian RD180 engine which demonstrates the superiority and capability of new “thermodynamic diagrams”. Research limitations/implications This algorithm is under constraint to control the critical variation of combustion pressure, turbine rpm, pump cavitation and turbine temperature. It is imperative to emphasize that this paper is limited to “oxidizer-rich staged combustion” engines with “single pre-burner”. Originality/value This study sheds light on using fuel booster turbopump and the second-stage fuel pump to moderate the effect of cavitation on pumps which reduces tank pressure and, as a consequence, decreases the propulsion system weight.

Steam generation with modified H2/O2-rocket engines

1977 ◽  
Author(s):  
J. REINKENHOF ◽  
R. SCHMUCKER
Keyword(s):  
Rocket Engines ◽  
Steam Generation
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