Development of high performance oxidizer turbo-pump

J. Takida*, K. Yoshikawa, A. Ogawara, M. Atsumi, K. Miyagawa, K. Kobayashi, T. Miyawaki

*この研究の対応する著者

研究成果: Conference contribution

2 被引用数 (Scopus)

抄録

In order to develop a high performance turbo-pump which consists of many components such as pump, turbine, bearings, shaft seals, etc., it is necessary not only to improve the performance of such component but also to reach good balance in performance and strength as a system, in other words, integration of performance and reliability is important. Efficiency of turbo-pump for rocket engines is generally around 30%, and its performance does not usually become a problem for the engine system. An important thing is to reduce an unstable dynamic load by cavitation of a pump. In addition, it is also important that there is an enough operation margin for components such as shaft seals and bearings. Mitsubishi Heavy Industries (MHI) has developed an oxidizer turbo-pump in the in-house research program. Through this development, new approach was tried for these problems. In this paper, the technical feature of this oxidizer turbo-pump and the results of component tests and turbo-pump tests are presented. The development approach for the oxidizer turbo-pump enabled achievement of the stable operation of the oxidizer turbo-pump in a short development period and few tests, and its effectiveness has demonstrated.

本文言語English
ホスト出版物のタイトルCollection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference
ページ4870-4876
ページ数7
出版ステータスPublished - 2007 12月 10
外部発表はい
イベント43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference - Cincinnati, OH, United States
継続期間: 2007 7月 82007 7月 11

出版物シリーズ

名前Collection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference
5

Conference

Conference43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference
国/地域United States
CityCincinnati, OH
Period07/7/807/7/11

ASJC Scopus subject areas

  • 宇宙惑星科学

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