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Internal Flow and Axial Thrust Balancing of a Rocket Pump

[+] Author Affiliations
Takashi Shimura, Satoshi Kawasaki, Masaharu Uchiumi

Japan Aerospace Exploration Agency, Kakuda, Miyagi, Japan

Jun Matsui

Yokohama National University, Yokohama, Kanagawa, Japan

Paper No. AJK2011-06027, pp. 145-152; 8 pages
doi:10.1115/AJK2011-06027
From:
  • ASME-JSME-KSME 2011 Joint Fluids Engineering Conference
  • ASME-JSME-KSME 2011 Joint Fluids Engineering Conference: Volume 1, Symposia – Parts A, B, C, and D
  • Hamamatsu, Japan, July 24–29, 2011
  • Conference Sponsors: Fluids Engineering Division
  • ISBN: 978-0-7918-4440-3
  • Copyright © 2011 by ASME

abstract

Internal flow of a cryogenic rocket turbopump is rather complicated compared to ordinary pumps. In order to design and predict characteristics of the axial thrust balancing system, analyses of the internal flow system is essential. In the present study, the calculation method for analyzing the internal flow system taking into account effects of boundary layer conditions and angular momentum change in chambers is applied. The characteristic of an axial thrust balancing system, which is comprised of a balance piston and grooves on the stationary wall, was evaluated. Calculated results showed that the system has a wide self-balancing range and is suitable for rocket turbopumps.

Copyright © 2011 by ASME

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