Space Shuttle Main Engine Turbopump Design

Document Number: 730926

Date Published: February 1973

Author(s):
R. B. Furst - Rocketdyne Div., Rockwell International

Abstract:
This paper presents the unique constraints imposed upon the turbopumps for the space shuttle main engine. Operating requirements are listed and the mechanical and fluid dynamic design features evolved to satisfy the performance requirements within the constraints imposed by the engine system are discussed. The constraints include the high-chamber pressure and staged-combustion cycle, along with weight restrictions and low propellant tank pressures. The turbopumps must raise the orbiter fuel tank and oxidizer tank propellant pressures to the level required by the engine. The turbopumps designed feature integral impeller balance pistons, a double-entry oxidizer pump, and low-pressure pumps driven by compatible turbine fluids. These are described in detail.

Product Status: In Stock

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