A Forced Response Analysis and Application of Impact Dampers to Rotordynamic Vibration Suppression in a Cryogenic Environment

[+] Author and Article Information
J. J. Moore, A. B. Palazzolo, R. Gadangi

Texas A&M University, College Station, TX

T. A. Nale, S. A. Klusman

Allison Gas Turbines, Indianapolis, IN

G. V. Brown, A. F. Kascak

NASA Lewis, Cleveland, OH

J. Vib. Acoust 117(3A), 300-310 (Jul 01, 1995) (11 pages) doi:10.1115/1.2874452 History: Received February 01, 1993; Online February 26, 2008


A high speed damper test rig has been assembled at Texas A&M University to develop rotordynamic dampers for rocket engine turbopumps that operate at cryogenic temperatures, such as those used in the space shuttle main engines (SSMEs). Damping is difficult to obtain in this class of turbomachinery due to the low temperature and viscosity of the operating fluid. An impact damper has been designed and tested as a means to obtain effective damping in a rotorbearing system. The performance and behavior of the impact damper is verified experimentally in a cryogenic test rig at Texas A&M. Analytical investigations indicate a strong amplitude dependence on the performance of the impact damper. An optimum operating amplitude exists and is determined both analytically and experimentally. In addition, the damper performance is characterized by an equivalent viscous damping coefficient. The test results prove the impact damper to be a viable means to suppress vibration in a cryogenic rotorbearing system.

Copyright © 1995 by The American Society of Mechanical Engineers
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