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)
Tohoku University
Former 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-415
巻
415
ページ
41
発行年
1975-08
抄録（英）
Recently, high performance liquid rocket engines tend to require oxygen pumps of higher speed and higher head. In order to develop oxygen pumps to meet these requirements, various problems must be overcome. In this study, a small, high speed, high head centrifugal liquid oxygen pump(N=20,000 rpm, Hp=1,051m, Q=18 l/s, Ns=118) was designed and experiments were conducted in many aspects using water and liquid nitrogen as test fluids. A preliminary experiment with cambered inducers was conducted in a water cavitation tunnel and it was clarified that the attack angle of inducers decisively determines the cavitation performance. The inducer of the pump investigated was designed according to the results of this preliminary experiment and showed good suction performance. The validity of the other design procedures discussed in this report was also clarified because of the good general performance of the pump. Liquid nitrogen and water tests showed a little difference in general performance. In particular, liquid nitrogen brought about a little better pump efficiency but lower volumetric efficiency than water. The former may be attributed to the decrease of disk friction and hydraulic losses and the latter to the increase of leakage loss, due to the extremely lower viscosity of liquid nitrogen. In the test using liquid nitrogen, the amount of required NPSH(net positive suction head) decrease due to the thermodynamic effects of cavitation was measured and two-phase operation was experienced. Some unsteady characteristics of the pump were investigated by measuring pressure oscillations at the pump inlet and outlet. The pressure oscillations of low and medium frequencies occurred in the pump circuit and these oscillations became more serious at lower flow rate. In this experiment, also, the radial and axial thrusts were examined and confirmation of ball bearings, mechanical seals and plastic wearings lubricated with cryogenic fluids was made.
ロケット用小型高速高揚程液体酸素ポンプの実験的研究
naltr00415.pdf
(10.46MB)
