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.

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