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Experimental Investigation of the Forcing Function and Forced Pitching Blade Oscillations of an Annular Compressor Cascade in Transonic Flow

[+] Author Affiliations
Joachim Belz, Holger Hennings

DLR - German Aerospace Center, Göttingen, Germany

Gerhard Kahl

MTU Aero Engines GmbH, Munich, Germany

Paper No. GT2010-23590, pp. 1277-1285; 9 pages
doi:10.1115/GT2010-23590
From:
  • ASME Turbo Expo 2010: Power for Land, Sea, and Air
  • Volume 6: Structures and Dynamics, Parts A and B
  • Glasgow, UK, June 14–18, 2010
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-4401-4 | eISBN: 978-0-7918-3872-3
  • Copyright © 2010 by ASME

abstract

The interaction between rotor blades and non-rotating stator blades is the most significant blade excitation mechanism in turbomachines. It is well documented in various numerical and experimental investigations for turbine cascades. Like turbine blades, also compressor blades are excited as well by potential fields of the following stator, the downstream flowfield of the stator of the previous stage or struts and incoming flow distortions. In this paper, experimental investigations of the excitation of a transonic compressor cascade due to gust generating struts upstream are presented. The experiments were performed in the test facility of non-rotating annular cascades at EPFL using a compressor cascade, which consists of 20 blades (NACA3506 profile) mounted on elastic spring suspensions for torsional motions at the midchord. For the non-rotating annular cascade, relative flow conditions similar to those present in a rotating cascade are generating by swirling the flow in front of the test test section. The struts are rotating in order to create a periodic excitation upstream of the cascade. The so generated pressure distribution on the cascade’s profiles as well as the measured vibration response of the blades are presented and compared for a pure subsonic and a transonic flow case.

Copyright © 2010 by ASME

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