Institute of Space and Aeronautical Science, University of Tokyo
Institute of Space and Aeronautical Science, University of Tokyo
Institute of Space and Aeronautical Science, University of Tokyo
Institute of Space and Aeronautical Science, University of Tokyo
Institute of Space and Aeronautical Science, University of Tokyo
Institute of Space and Aeronautical Science, University of Tokyo
We have developed the gas-generator to drive the turbo-pump for a LH2/LOX rocket engine of 7,000 kg-thrust level. The present gas-generator is the reverse-flow type which is composed of a spherical combustion chamber with a turbulence ring, uniform mixture ratio-coaxial injectors and a start valve. The performance characteristics and functions of the gas-generator have been verified through eight running tests of gas-generators themselves and ten running tests of the second gas-generator assembled to a turbine. Total burning duration is 204 seconds. Here are presented the design details of gas-generators developed at the Institute of Space and Aeronautical Science (ISAS), University of Tokyo, the test facilities and the test results obtained up to date.
<論文>液水/液酸ターボポンプ用ガスジェネレーターの開発研究
SA0125878.pdf
(2MB)
