Research Papers

Experimental Reduction of Transonic Fan Forced Response by Inlet Guide Vane Flow Control

[+] Author and Article Information
S. Todd Bailie1

Department of Mechanical Engineering, Virginia Polytechnic Institute and State University, Blacksburg, VA 24061samuel.bailie@wpafb.af.mil

Wing F. Ng

Department of Mechanical Engineering, Virginia Polytechnic Institute and State University, Blacksburg, VA 24061wng@vt.edu

William W. Copenhaver

Propulsion Directorate, Air Force Research Laboratory, WPAFB, OH 45433william.copenhaver@wpafb.af.mil


Present address: Propulsion Directorate Air Force Research Laboratory.

J. Turbomach 132(2), 021003 (Dec 31, 2009) (8 pages) doi:10.1115/1.3140823 History: Received July 01, 2005; Revised March 07, 2008; Published December 31, 2009; Online December 31, 2009

The main contributor to the high cycle fatigue of compressor blades is the response to aerodynamic forcing functions generated by an upstream row of stators or inlet guide vanes. Resonant response to engine order excitation at certain rotor speeds can be especially damaging. Studies have shown that flow control by trailing edge blowing (TEB) can reduce stator wake strength and the amplitude of the downstream rotor blade vibrations generated by the unsteady stator-rotor interaction. In the present study, the effectiveness of TEB to reduce forced fan blade vibrations was evaluated in a modern single-stage transonic fan rig. Data were collected for multiple uniform full-span TEB conditions over a range of rotor speeds including multiple modal resonance crossings. Resonant response sensitivity was generally characterized by a robust region of strong attenuation. The baseline resonant amplitude of the first torsion mode, which exceeded the endurance limit on the critical blade, was reduced by more than 80% with TEB at 1.0% of the total rig flow. The technique was also found to be modally robust; similar reductions were achieved for all tested modal crossings, including more than 90% reduction in the second leading-edge bending response using 0.7% of the rig flow.

Copyright © 2010 by American Society of Mechanical Engineers
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Figure 1

Cross section of SMI transonic compressor rig

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Figure 2

SMI 24-WG wake velocity profiles at 26% axial spacing (from Ref. 12)

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Figure 3

Detail of SMI rig showing trailing edge blowing configuration and strain gage locations

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Figure 4

SMI rig assembly with TEB plumbing installed

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Figure 5

SMI fan Campbell diagram showing 12-WG harmonic excitations (dashed) and resonance crossings (circled) within the test range

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Figure 6

Selected SMI fan blade displacement mode shapes with signs indicating relative phase

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Figure 7

Baseline order tracks showing multiple modal resonances due to upstream WG and downstream stator excitations

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Figure 8

Baseline critical gage response for various modal resonance crossings

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Figure 9

Effect of TEB on critical blade response at the 1T/12E resonance crossing

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Figure 10

Effect of total TEB flowrate on 1T/12E resonant response

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Figure 11

Effect of total TEB flowrate on LE2B/24E resonant response

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Figure 12

Effect of TEB flowrate on multiple modal resonances showing region of substantial attenuation

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Figure 13

Comparison of optimal TEB flowrates based on resonance crossing data and aerodynamic estimates

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Figure 14

Comparison of modal resonant response reductions by TEB




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