Altitude testing of the hypersonic turbojet engine at Mach 2 flight condition

Hiroaki Kobayashi, H. Taguchi, T. Kojima, Y. Maru, S. Sawai, T. Sato

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

Abstract

Research on hypersonic turbojet engine with air-precooling system is under development in JAXA for the propulsion system of hypersonic transport. A notable feature of this engine is to use an air pre-cooling device using liquid hydrogen fuel as a coolant in order to protect the turbo-machinery from aerodynamic heating under hypersonic flight conditions. JAXA's recent model of the hypersonic turbojet engine is developed for a Mach 2 flight test with a balloon-launched missile-like vehicle. This paper reports pre-flight verification test results of the engine in altitude test facility. High altitude environment was formed in a combustion wind tunnel facility in JAXA's Akiruno Research Center. The wind tunnel consists of a vacuum chamber and a water ejector exhausting air including air-hydrogen combustion gas. Air flow rate and pressure was regulated properly with flow control valves connected in front of the engine. It was found that acceleration of rotational speed in flight conditions is larger than that in sea level condition. In the sea level static condition, turbine pressure ratio gradually increases with compressor rotational speed and pressure ratio, therefore the power for accelerating rotational speed is little at low rotational speed, while the wind-milling engine has plenty of turbine power independently from the compressor status. Turbine inlet temperature was found to be reduced by 200 K due to that the turbine power is enough.

Original languageEnglish
Title of host publication61st International Astronautical Congress 2010, IAC 2010
Pages7500-7507
Number of pages8
Publication statusPublished - 2010 Dec 1
Event61st International Astronautical Congress 2010, IAC 2010 - Prague, Czech Republic
Duration: 2010 Sep 272010 Oct 1

Publication series

Name61st International Astronautical Congress 2010, IAC 2010
Volume9

Conference

Conference61st International Astronautical Congress 2010, IAC 2010
CountryCzech Republic
CityPrague
Period10/9/2710/10/1

ASJC Scopus subject areas

  • Aerospace Engineering
  • Astronomy and Astrophysics

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  • Cite this

    Kobayashi, H., Taguchi, H., Kojima, T., Maru, Y., Sawai, S., & Sato, T. (2010). Altitude testing of the hypersonic turbojet engine at Mach 2 flight condition. In 61st International Astronautical Congress 2010, IAC 2010 (pp. 7500-7507). (61st International Astronautical Congress 2010, IAC 2010; Vol. 9).