Dynamic response analysis of high-pressure rocket pumps

Sang In Jun, Takashi Tokumasu, Kenjiro Kamuo

Research output: Contribution to journalArticle

Abstract

With regard to the development of a liquid-fuel rocket engine, knowledge of unsteady characteristics of turbopumps is essential in attempts to increase rocket reliability. Numerical simulation is very advantageous in determining the unsteady characteristics of turbopumps, and knowledge thus obtained can contribute to decreasing the cost and the number of experiments. In the present study, the effect of compressibility of cryogenic propellants, such as liquid hydrogen (LH2) and liquid oxygen (LOX), and the effect of nonlinearity of flow on the dynamic response of a high-pressure turbopump were considered. The results of calculation were compared with a nonlinear incompressible mathematical model. The effects of dynamic characteristics of a cavitating inducer, such as cavitation compliance and mass flow gain factor, as well as the effect of pipe elasticity and that of an accumulator for the POGO suppressor, were also analyzed.

Original languageEnglish
Pages (from-to)181-188
Number of pages8
JournalTransactions of the Japan Society for Aeronautical and Space Sciences
Volume47
Issue number157
DOIs
Publication statusPublished - 2004 Nov 1

Keywords

  • Cavitating Inducer
  • Compressibility
  • Cryogenic Propellants
  • Dynamic Response
  • Nonlinear Model

ASJC Scopus subject areas

  • Aerospace Engineering
  • Space and Planetary Science

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