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-570
巻
570
ページ
25
発行年
1979-04
抄録（英）
Liquid rocket engine thrust buildup follows turbopump speed buildup, which occurs in 1～3 seconds after the engine starts. In this rapid start condition, the dynamic characteristics of the turbopumps are thought to deviate considerably from their steady state characteristics. Therefore, it is very important to know the transient characteristics of the turbopumps, in order to make sure that the engine start transient is clear. In the present study, experiments with a small high speed liquid oxygen pump were performed, in order to investigate the pump transient characteristics in the rapid start. The pump tested was designed for 10 ton thrust LOX/LH2 rocket engine. The experiments were made using degassified water and liquid nitrogen, instead of liquid oxygen. Visual observations of cavitation in the pump inducer were performed, using a transparent inducer casing. The following items:transient characteristics of pump head, pump shaft power, accelerating head loss in the pump suction line, pump axial thrust, and pump chilldown, were examined in these experiments. The major results of the present study are as follows: (1)The pump head in the rapid starts tended to be higher than the steady state head. (2)The excess of the head in the rapid starts depended upon the initial flow rate. (3)The pump efficiency in the rapid starts was lower than the steady state efficiency. In addition, we were able to show the relationship between the pump inlet pressure decrease, due to the rapid start, and the cavitation occurrence in the pump inducer.
ロケット用液体酸素ポンプの過渡特性に関する実験的研究(第1報)
naltr00570.pdf
(10.71MB)
