Hydrostatic Damper for the Space Shuttle Main Engine (SSME) High Pressure Oxidizer Turbopump (HPOTP)

[+] Author and Article Information
D. G. Goggin, J. K. Scharrer, R. F. Beatty

Rocketdyne Division, Rockwell International, Canoga Park, CA 91303

J. Tribol 112(1), 141-146 (Jan 01, 1990) (6 pages) doi:10.1115/1.2920219 History: Received March 24, 1989; Revised August 23, 1989; Online June 05, 2008


Alternative methods were evaluated for increasing rotor damping on the SSME HPOTP to reduce bearing dynamic loads and extend their useful life. A unique application of a hydrostatic damper was developed by incorporating a hydrostatic element between stationary turbine bearing support components. Damper design is shown to be dependent on accurate rotordynamic response analysis. Optimization to achieve maximum damper performance under high loading conditions and limited supply flow is discussed. Damping levels approaching critical damping were achieved without major modifications. Bearing dynamic loads are reduced up to 70 percent and rotor mode logarithmic decrement was increased from 0.085 to as much as 1.0. Possible opportunities for further improvements in damper performance are also discussed.

Copyright © 1990 by The American Society of Mechanical Engineers
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