Japan Aerospace Exploration Agency Institute of Aerospace Technology
Japan Aerospace Exploration Agency Institute of Aerospace Technology
Japan Aerospace Exploration Agency Institute of Aerospace Technology
Japan Aerospace Exploration Agency Aviation Program Group
Japan Aerospace Exploration Agency Institute of Aerospace Technology
Japan Aerospace Exploration Agency Space Technology Development Dept., Institute of Space and Astronautical Science
This paper describes the development and test results of a small hydrogen-fueled reverse-flow annular combustor for a scaled pre-cooled turbojet engine. The Japan Aerospace Exploration Agency is encouraging the development of this turbojet engine, and a practical demonstration will be made under both ground and in-flight conditions up to Mach 6. Due to the limited size of the entire engine, a small reverse-flow annular combustor has been adopted for this demonstration. The particular type of pre-mixer that we use is important for achieving favorable degree of mixing and combustion. In the paper, the procedure used to arrive at the present design is briefly described, and the results of the combustion test are reported in detail. The combustion test was performed under a wide range of conditions: from sea level static conditions to in-flight conditions up to Mach 6. The test result shows that the overall combustion characteristics, such as exit temperature profile and pressure loss, are within the allowable limits under all test conditions. It was shown that the restrictions arising from the geometry in a flyable small gas-turbine engine were overcome in the composition of gaseous fuels with the introduction of the radial-injection pre-mixer configuration.
極超音速飛行試験用小型水素燃料逆流アニュラ燃焼器の開発と試験
49796000.pdf
(6.36MB)
