@techreport{oai:jaxa.repo.nii.ac.jp:00045279,
 author = {山田, 仁 and 渡辺, 義明 and 吉田, 誠 and 長谷川, 敏 and 上條, 謙二郎 and YAMADA, Hitoshi and WATANABE, Yoshiaki and YOSHIDA, Makoto and HASEGAWA, Satoshi and KAMIJO, Kenjiro},
 month = {Apr},
 note = {The development of a large launch vehicle (H-II)started in 1985. The first stage of the launch vehicle uses a liquid oxygen/hydrogen engine (LE-7), which generates 1,180 KN in thrust with a two-stage combustion cycle. The liquid oxygen turbopump consists of a main pump, a preburner pump and a single stage turbine. The design rotational speed is 20,000 rpm and the delivery pressure of the main pump is 20.3 MPa and that of the preburner pump is 31.7 MPa. The flow rate is 229.1 kg/s and NPSH is 30 m. These high rotational speed, large flow rate and low suction pressure require combination of a cavitating inducer and a main impeller. In order to design a high pressure delivery pump with a high pump efficiency, it is necessary to analyze the pump blade passage flows in detail, using a three dimensional flow analysis method. This paper describes the initial design of the liquid oxygen pump of the LE-7 engine and also presents the results of some experiments which were carried out using liquid oxygen and liquid nitrogen as the pump fluid, at the turbopump test facility of the National Aerospace Laboratory, Kakuda Branch. The predicted pump head coefficient was in reasonable agreement with the experimental results considering the pump efficiency. Furthermore, we developed a method which calculates blade shapes correctly, and it was very useful in analyzing flows in impeller blade passages., 資料番号: NALTR1020000, レポート番号: NAL TR-1020},
 title = {Investigation of Fluid Dynamic Performance of LE-7 Liquid Oxygen Pump},
 year = {1989}
}