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-806
巻
806
ページ
10
発行年
1984-04
抄録（英）
Since the dynamic performance of fluid machines is closely related to various kinds of fluid system instabilities, such as the “POGO” phenomena of liquid rockets, the dynamic characteristics of cavitating inducers, pumps and hydraulic turbines have been of great interest. In the present study, transfer matrix methods, which have been successfully applied to cavitating inducers, were used in order to examine the dynamic response of a centrifugal liquid oxygen pump with an inducer. An ultrasonic flow meter was used to measure the dynamic flow rate. A slit type perturbing valve was used to cause periodical oscillations in the pump flow. The major results of the present study were as follows : 1.Linearity of amplitude and phase existed in most parts of the experiment under high NPSH conditions. 2.The Z11 component of the pump transfer matrix was determined by two independent sets of data obtained by varying the helium gas volume in a vacuumjacketed cryogenic accumulator. 3.The test results of the Z12 component of the pump transfer matrix showed that dependency of Z12 on frequency was small, and it was concluded that a quasistatic treatment of Z12 is applicable on a centrifugal pump such as the one used in this study up to relatively high frequency regions.
ロケット用液酸ポンプの動特性の研究(その2)
naltr00806.pdf
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