JOURNAL BROWSE
Search
Advanced SearchSearch Tips
Hot Firing Tests of a Gas Generator for Liquid Rocket Engine using a Turbine Manifold Simulator
facebook(new window)  Pirnt(new window) E-mail(new window) Excel Download
 Title & Authors
Hot Firing Tests of a Gas Generator for Liquid Rocket Engine using a Turbine Manifold Simulator
Lim, Byoungjik; Kim, Munki; Kim, Jonggyu; Choi, Hwan-Seok;
  PDF(new window)
 Abstract
A gas generator which generates turbine driving gas by burning a part of propellants is used in an open cycle liquid rocket engine and as a main component of an open cycle liquid rocket engine autonomous hot firing tests are required to investigate the combustion performance and characteristics of the gas generator. However, since the combustion gas generated by a gas generator is choked at the turbine nozzle in the turbine manifold, it is necessary to consider the internal volume of turbine manifold as well as that of the gas generator for correct investigation of the combustion performance, characteristics, and acoustic characteristics of the gas generator. Therefore, in the paper hot firing test results of a gas generator with a turbine manifold simulator are described and characteristic prediction using the autonomous test of a gas generator is explained.
 Keywords
Gas Generator;Liquid Rocket Engine;Turbine Manifold;Pressure Fluctuation;Choking Nozzle;
 Language
Korean
 Cited by
 References
1.
Sutton, G.P. and Oscar B., Rocket Propulsion Elements, 7th ed., John Wiley & Sons Inc., New York, USA, 2001.

2.
Thiard, B., "Vulcain Gas Generator Development Status," 26th AIAA/SAE/ASME/ASEE Joint Propulsion Conference, Orlando, F.L, USA, AIAA-90-2252, pp. 16-18, Jul. 1990.

3.
Dennis, Jr.H.J. and Sanders, T., "NASA Fastrac Engine Gas Generator Component Test Program and Results," 36th AIAA/SAE/ASME/ASEE Joint Propulsion Conference, Huntsville, A.L., USA, AIAA 2000-3401, pp. 17-19, Jul. 2000.

4.
NASA Space Vehicle Design Criteria (Chemical Propulsion), "Liquid Propellant Gas Generators, Gas Generator," NASA SP-8081, Mar., 1972.

5.
Yang, V. and Anderson, W.E., Liquid Rocket Engine Combustion Instability, AIAA Progress in Astronautics and Aeronautics, Washington, DC, USA, Vol. 169, pp. 89-112, 1995.