Investigation of Squeeze Film Damper Forces Produced by Circular Centered Orbits

[+] Author and Article Information
E. Feder, P. N. Bansal, A. Blanco

Structures Technology and Research (Rotor Dynamics), Commercial Products Division, Pratt & Whitney Aircraft Group, Division of United Technologies Corp., East Hartford, Conn.

J. Eng. Power 100(1), 15-21 (Jan 01, 1978) (7 pages) doi:10.1115/1.3446313 History: Received December 15, 1976; Online July 14, 2010


This paper presents the results of an experimental and analytical investigation of the dynamic forces generated by a squeeze film bearing damper constrained to move in circular centered orbits. These orbits were mechanically produced in a specially designed, end sealed, test rig. Aircraft engine damper geometry and operating conditions were simulated. The effect of journal speed, oil viscosity, inlet pressure, and eccentricity ratio on the damper performance was studied. The pressure distributions about the journal were measured for each test condition by high-response diaphragm-type pressure transducers. These pressure profiles were numerically integrated to determine the force components of the squeeze film. Experimental results were compared to an analysis which is summarized in this paper and included the effects of inlet and cavitation pressures. The “long bearing theory” was found to be reasonably accurate in predicting the shape and magnitude of the pressure distribution. Considerable emphasis was directed to the study of the circumferential pressure distributions between 180 deg and 360 deg since aircraft engine dampers generally operate in this region. For the cavitated film (i.e., pressure distributions less than 360 deg), accurate prediction of the damper forces was found to be critically dependent on the effect of inlet and cavitation pressures.

Copyright © 1978 by ASME
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