Turbopumps for Gas Generator and Staged Combustion Cycle Rocket Engines

2005 ◽  
Author(s):  
Yuri Demyanenko ◽  
Anatoly Dmitrenko ◽  
Alexander Ivanov ◽  
Valeri Pershin
Keyword(s):  
Rocket Engines ◽  
Staged Combustion ◽  
Gas Generator ◽  
Combustion Cycle

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

Pogo Stability Approaches for the Strap-On Launch Vehicle with Staged Combustion Cycle Engines

2020 ◽  
Vol 57 (4) ◽  
pp. 636-641 ◽  
Author(s):  
Tao Liu ◽  
Jin-Fan Liu ◽  
Wen-Bin Di ◽  
Guo-An Tang ◽  
Lin-Yu Song
Keyword(s):  
Launch Vehicle ◽  
Staged Combustion ◽  
Combustion Cycle

scholarly journals Development Trend of Korean Staged Combustion Cycle Rocket Engine

2018 ◽  
Vol 22 (3) ◽  
pp. 109-119 ◽  
Author(s):  
Chae-hyoung Kim ◽  
Yeoung Min Han ◽  
Namkyung Cho ◽  
Seung-Han Kim ◽  
Byungil Yu ◽  
...  
Keyword(s):  
Rocket Engine ◽  
Development Trend ◽  
Staged Combustion ◽  
Combustion Cycle

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

scholarly journals Simulations and Measurements on Impulse Blades for Heat Transfer Prediction in Supersonic Turbine Applications

1998 ◽  
Author(s):  
U. Håll ◽  
J. Larsson ◽  
F. Bario ◽  
P. Kulisa ◽  
J. Slimani ◽  
...  
Keyword(s):  
Heat Transfer ◽  
Turbine Blade ◽  
Leading Edge ◽  
Navier Stokes ◽  
Rocket Engines ◽  
Gas Generator ◽  
Flow And Heat Transfer ◽  
Wide Range ◽  
Boundary Layer Method ◽  
Fundamental Insight

This paper presents an overview of a research project aimed at improving the currently available methods to predict the flow and heat transfer in uncooled supersonic impulse turbines. These turbines are typically used in rocket engines based on the gas-generator cycle. A fast boundary-layer method, suitable in the design phase, is presented. This method includes effects related to curvature, transition and separation bubbles. For more detailed analysis, Navier-Stokes methods are used. Experiences from using a wide range of two-equation models to predict turbine blade heat transfer are summarized. The experimental work uses a scaled-up, heated, linear blade cascade. The aim is to gain fundamental insight into the phenomena involved in turbine blade heat transfer and to obtain data for validation and development of new numerical methods. Detailed measurements, of both averaged and fluctuating properties of the velocity field, are made in the boundary layers down to a Y+ below 10. The results presented here are focused on the leading edge.

Full-Scale Firing Tests of Variable Flow Ducted Rocket Engines Employing Gap Solid Fuel Gas Generator

2009 ◽  
Author(s):  
Hisahiro Nakayama ◽  
Yoshiyuki Ikegami ◽  
Akihiko Yoshida ◽  
Kenji Koori ◽  
Kiyoyuki Watanabe ◽  
...  
Keyword(s):  
Solid Fuel ◽  
Full Scale ◽  
Rocket Engines ◽  
Gas Generator ◽  
Fuel Gas ◽  
Variable Flow ◽  
Ducted Rocket ◽  
Firing Tests
Sign in / Sign up

Export Citation Format

Share Document