Design study and component tests on a subscale precooled turbojet engine for flight experiments

Hideyuki Taguchi, Takayuki Kojima, Kazuhisa Fujita, Hiroaki Kobayashi, Keiichi Okai, Tetsuya Satou

Research output: Chapter in Book/Report/Conference proceedingConference contribution

2 Citations (Scopus)

Abstract

Components of the small scale precooled turbojet engine such as variable intake, air pre-cooler, core engine, ram combustor, and variable nozzle are designed and tested for flight experiments and high enthalpy wind tunnel tests. The engine is expected to be operative from lift-off to Mach 6 by applying the precooling system and using LH2 as a fuel. Length of the engine is 2m. Hypersonic and supersonic wind tunnel experiments are conducted to acquire and improve the intake aerodynamic performances. Total pressure recovery of the intake is 0.22 at Mach 5. Variable intake with advanced composite material is designed to realize the intake without cooling under Mach 6 flight condition. The shape of the intake and the precooler is determined using FEM analysis. Mixed compression type compressor is designed by CFD analyses. Component test of the main combustor is performed using gas hydrogen. A variable mechanism and cooling mechanism of the rectangular nozzle is designed. After the wind tunnel and combustion tests of the engine components, total engine system is designed by 3 dimensional CAD. The weight of the engine satisfies the requirement of the flight test.

Original languageEnglish
Title of host publicationInternational Astronautical Federation - 56th International Astronautical Congress 2005
Pages4592-4598
Number of pages7
Volume7
Publication statusPublished - 2005
Externally publishedYes
EventInternational Astronautical Federation - 56th International Astronautical Congress 2005 - Fukuoka
Duration: 2005 Oct 172005 Oct 21

Other

OtherInternational Astronautical Federation - 56th International Astronautical Congress 2005
CityFukuoka
Period05/10/1705/10/21

Fingerprint

turbojet engines
Turbojet engines
engines
engine
flight
Engines
Mach number
Wind tunnels
wind tunnel
experiment
Experiments
combustion chambers
Combustors
nozzles
Nozzles
precooling
hypersonic wind tunnels
supersonic wind tunnels
pressure recovery
Cooling

ASJC Scopus subject areas

  • Space and Planetary Science
  • Aerospace Engineering

Cite this

Taguchi, H., Kojima, T., Fujita, K., Kobayashi, H., Okai, K., & Satou, T. (2005). Design study and component tests on a subscale precooled turbojet engine for flight experiments. In International Astronautical Federation - 56th International Astronautical Congress 2005 (Vol. 7, pp. 4592-4598)

Design study and component tests on a subscale precooled turbojet engine for flight experiments. / Taguchi, Hideyuki; Kojima, Takayuki; Fujita, Kazuhisa; Kobayashi, Hiroaki; Okai, Keiichi; Satou, Tetsuya.

International Astronautical Federation - 56th International Astronautical Congress 2005. Vol. 7 2005. p. 4592-4598.

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Taguchi, H, Kojima, T, Fujita, K, Kobayashi, H, Okai, K & Satou, T 2005, Design study and component tests on a subscale precooled turbojet engine for flight experiments. in International Astronautical Federation - 56th International Astronautical Congress 2005. vol. 7, pp. 4592-4598, International Astronautical Federation - 56th International Astronautical Congress 2005, Fukuoka, 05/10/17.
Taguchi H, Kojima T, Fujita K, Kobayashi H, Okai K, Satou T. Design study and component tests on a subscale precooled turbojet engine for flight experiments. In International Astronautical Federation - 56th International Astronautical Congress 2005. Vol. 7. 2005. p. 4592-4598
Taguchi, Hideyuki ; Kojima, Takayuki ; Fujita, Kazuhisa ; Kobayashi, Hiroaki ; Okai, Keiichi ; Satou, Tetsuya. / Design study and component tests on a subscale precooled turbojet engine for flight experiments. International Astronautical Federation - 56th International Astronautical Congress 2005. Vol. 7 2005. pp. 4592-4598
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