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Aerodynamic Damping Measurements in a Transonic Compressor PUBLIC ACCESS

[+] Author Affiliations
E. F. Crawley

Massachusetts Institute of Technology, Cambridge, MA

Paper No. 82-GT-287, pp. V005T13A022; 12 pages
doi:10.1115/82-GT-287
From:
  • ASME 1982 International Gas Turbine Conference and Exhibit
  • Volume 5: Manufacturing Materials and Metallurgy; Ceramics; Structures and Dynamics; Controls, Diagnostics and Instrumentation; Education; Process Industries; Technology Resources; General
  • London, England, April 18–22, 1982
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7960-3
  • Copyright © 1982 by ASME

abstract

A method has been developed and demonstrated for the direct measurement of aerodynamic damping in a transonic compressor. The method is based on the inverse solution of the structural dynamic equations of motion of the blade-disk system. The equations are solved inversely to determine the forces acting on the system. If the structural dynamic equations are transformed to multiblade or modal coordinates, the damping can be measured for blade-disk modes, and related to a reduced frequency and interblade phase angle. This method of damping determination was demonstrated using a specially instrumented version of the MIT Transonic Compressor run in the MIT Blowdown Compressor Test Facility. No regions of aeroelastic instability were found. In runs at the operating point, the rotor was aerodynamically excited by a controlled two-per-revolution fixed upstream disturbance. The disturbance was sharply terminated midway through the test. Analysis of the data in terms of multiblade modes led to a direct measurement of aerodynamic damping for three interblade phase angles.

Copyright © 1982 by ASME
Topics: Compressors , Damping
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