並列タイトル等Suction Performance of LOX/LH2 Inducers for a Rocket Engine
タイトル（掲載誌）航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-716
一般注記The turbopump of a liquid rocket engine has to be able to operate with a low tank pressure in order to minimize the tank pressure. To provide this capability, the turbopump generally employs an inducer stage ahead of the main impeller. So it is important to predict the suction performance of the inducer itself. In the past the prediction of the net positive suction head(NPSH) of the inducer operating in cryogenic propellants, such as liquid hydrogen, liquid oxygen and so on, has often been investigated. However, little research has been done on the prediction of NPSH of inducers between different cryogenic liquids or different pump sizes. The present study deals with these problems. Two different inducers, one for liquid hydrogen, and the other for liquid oxygen, were tested in liquid nitrogen and another inducer was tested in liquid hydrogen for various rotative speeds, flow coefficients, and liquid temperatures. NPSH was measured for these three inducers for variopus flow conditions. The thermodynamic effect of cavitaion of liquid hydrogen and liquid nitrogen was compared. The measured values of NPSH in liquid hydrogen tests were in reasonable agreement with those predicted by using test data of liquid nitrogen.
資料番号: NALTR0716000
レポート番号: NAL TR-716
一次資料へのリンクURLhttps://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=44973&item_no=1&attribute_id=31&file_no=1
連携機関・データベース国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）
提供元機関・データベース宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ