Journal of the Korean Society of Propulsion Engineers (한국추진공학회지)

The Korean Society of Propulsion Engineers (한국추진공학회)
권호 표지
DOI QR코드

DOI QR Code

Hot Firing Tests of a Gas Generator for Liquid Rocket Engine using a Turbine Manifold Simulator

터빈 매니폴드 모사장치를 이용한 액체로켓엔진 가스발생기 연소시험

  • Lim, Byoungjik (Combustion Chamber Team, Korea Aerospace Research Institute) ;
  • Kim, Munki (Combustion Chamber Team, Korea Aerospace Research Institute) ;
  • Kim, Jonggyu (Combustion Chamber Team, Korea Aerospace Research Institute) ;
  • Choi, Hwan-Seok (Combustion Chamber Team, Korea Aerospace Research Institute)
  • Received : 2015.06.01
  • Accepted : 2015.08.03
  • Published : 2015.10.01
Download PDF
⟨ Previous Next ⟩

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.

개방형 사이클의 액체로켓엔진에서는 추진제 중 일부를 연소시켜 터빈 구동용 가스를 생성시키는 가스발생기가 사용되며, 개방형 사이클 액체로켓엔진의 주요 구성품으로서 가스발생기 자체의 연소성능 및 특성을 파악하기 위한 연소시험이 요구된다. 하지만, 가스발생기에서 생성된 연소가스는 터빈 매니폴드의 터빈 노즐에서 질식이 이루어지기 때문에 가스발생기뿐만 아니라 터빈 매니폴드 내부 부피를 고려해야만 가스발생기의 연소 성능 및 특성, 그리고 음향 특성을 정확히 파악할 수 있다. 따라서, 본 논문에서는 터빈 매니폴드 모사장치를 이용한 가스발생기 연소시험 결과를 기술하고 가스발생기 단독 연소시험 결과를 이용한 특성 예측을 설명한다.

Keywords

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.