Kakuda Branch Office, National Aerospace Laboratory(NAL)
Kakuda Branch Office, National Aerospace Laboratory(NAL)
Kakuda Branch Office, National Aerospace Laboratory(NAL)
Kakuda Branch Office, National Aerospace Laboratory(NAL)
Kakuda Branch Office, National Aerospace Laboratory(NAL)
Kakuda Branch Office, National Aerospace Laboratory(NAL)
Kakuda Branch Office, National Aerospace Laboratory(NAL)
出版者
航空宇宙技術研究所
出版者（英）
National Aerospace Laboratory(NAL)
雑誌名
航空宇宙技術研究所報告
雑誌名(英)
Technical Report of National Aerospace Laboratory TR-588
巻
588
ページ
48
発行年
1979-10
抄録（英）
The development of a 10 ton thrust liquid oxygen and liquid hydrogen(LOX and LH2)rocket engine is conducted by the National Space Development Agency. The LOX/LH2 engine uses the gas-generator cycle and has dual shaft turbopums with turbines in series. The National Aerospace Laboratory has carried out the development and study of the turbopumps for the engine in co-operation with the National Space Development Agency. The present report descibes the first development and study of the LOX turbopump, which was conducted chiefly by the National Aerospace Laboratory. The LOX turbopump consists of a single stage centrifugal pump with a cavitating inducer and a single-stage two-rotor velocity compounded impulse turbine. The performance of the test turbopump, including the pump pressure rise, the pump and turbine efficiency, turbine power, etc., showed good agreement with the predicted values. The turbopump assembly and most of the components, except the gas seals, also showed good performance through out all the tests. One problem experienced with regard to the gas seals was solved by the modification of the seals. The technical data obtained in this development and study are utilized in order to make the flight type LOX turbopump.
液酸・液水ロケットエンジン用液酸ターボポンプの試作研究
naltr00588.pdf
(9.88MB)
