Firing test of a hypersonic turbojet engine installed on a flight test vehicle

Hideyuki Taguchi, Kenya Harada, Hiroaki Kobayashi, Takayuki Kojima, Motoyuki Hongoh, Daisaku Masaki, Shujiro Sawai, Yusuke Maru, Tetsuya Sato

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

14 Citations (Scopus)

Abstract

Hypersonic turbojet engine with pre-cooling system is tested under sea level static condition. The engine is installed on a flight test vehicle, which will fly at Mach 2 speed by a free fall experiment from a stratospheric balloon. Liquid hydrogen fuel and gas hydrogen fuel is supplied to the engine from a tank and cylinders installed in the vehicle. Designated operation of major components of the engine is confirmed. Corrected rotation speed, corrected air flow rate and pressure ratio of the compressor is raised by pre-cooling with liquid hydrogen fuel. Corrected air flow rate and pressure ratio at the pre-cooling operation is reduced comparing from that without pre-cooling on the same corrected rotation speed. There is a deep temperature distortion at the inlet of the compressor and it may cause the performance reduction. Large amount of liquid hydrogen is supplied to the pre-cooler in order to obtain enough pre-cooling performance for Mach 5 flight. Then, fuel rich combustion at the after-burner is adopted. Cowl part of variable geometry nozzle is made with C/C composite material and it has no damage after the combustion test. Operation of the core engine by liquid hydrogen is attained by using a control valve with small effective diameter.

Original languageEnglish
Title of host publication16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference
Publication statusPublished - 2009 Dec 1
Event16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference - Bremen, Germany
Duration: 2009 Oct 192009 Oct 22

Publication series

Name16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference

Conference

Conference16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference
CountryGermany
CityBremen
Period09/10/1909/10/22

ASJC Scopus subject areas

  • Engineering(all)

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  • Cite this

    Taguchi, H., Harada, K., Kobayashi, H., Kojima, T., Hongoh, M., Masaki, D., Sawai, S., Maru, Y., & Sato, T. (2009). Firing test of a hypersonic turbojet engine installed on a flight test vehicle. In 16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference [2009-7311] (16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference).