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TECHNICAL PAPERS

Unsteady Aerodynamics and Interactions Between a High-Pressure Turbine Vane and Rotor

[+] Author and Article Information
Ryan M. Urbassik

Department of Mechanical and Materials Engineering,  Wright State University, Dayton, OH 45435

J. Mitch Wolff

Department of Mechanical and Materials Engineering,  Wright State University, Dayton, OH 45435mitch.wolff@wright.edu

Marc D. Polanka1

 Air Force Research Laboratory, Turbines Branch, Wright-Patterson Air Force Base, Wright-Patterson AFB, OH 45433marc.polanka@wpafb.af.mil

1

Corresponding author.

J. Turbomach 128(1), 35-42 (Mar 01, 2004) (8 pages) doi:10.1115/1.2098752 History: Received October 01, 2003; Revised March 01, 2004

A set of experimental data is presented investigating the unsteady aerodynamics associated with a high pressure turbine vane (HPV) and rotor blade (HPB). The data was acquired at the Turbine Research Facility (TRF) of the Air Force Research Laboratory. The TRF is a transient, blowdown facility generating several seconds of experimental data on full scale engine hardware at scaled turbine operating conditions simulating an actual engine environment. The pressure ratio and freestream Reynolds number were varied for this investigation. Surface unsteady pressure measurements on the HPV, total pressure traverse measurements downstream of the vane, and surface unsteady pressure measurements for the rotor blade were obtained. The unsteady content of the HPV surface was generated by the rotor potential field. The first harmonic decayed more rapidly than the second harmonic with a movement upstream causing the second harmonic to be most influential at the vane throat. The blade unsteadiness appears to be caused by a combination of shock, potential field, and vane wake interactions between the vane and rotor blade. The revolution averaged data resulted in higher unsteadiness than a passing ensemble average for both vane and rotor indicating a need to understand each passage for high cycle fatigue (HCF) effects.

Copyright © 2006 by American Society of Mechanical Engineers
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References

Figures

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Figure 2

(a) Schematic of test section with vane only. (b) Schematic of test section with vane and rotor

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Figure 3

Baseline HPV total pressure exit traverse

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Figure 4

Harmonic comparison for baseline vane exit flow

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Figure 5

Reynolds number effects on the HPV total pressure exit flow

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Figure 6

Reynolds number effects on HPV 1st harmonic exit flow

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Figure 7

Unsteady pressure on the HPV for the baseline condition at 50% span

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Figure 8

Unsteady pressure on the pressure side of the HPB for the baseline condition at 50% span

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Figure 9

Harmonic comparison of unsteady vane surface pressure for baseline

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Figure 10

1st harmonic Reynolds number and pressure ratio effects of unsteady surface pressure acting on the vane

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Figure 11

2nd harmonic Reynolds number and pressure ratio effects of unsteady surface pressure acting on the vane

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Figure 16

Comparison between revolution ensemble and vane pass ensemble at the rotor stagnation point

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Figure 15

Comparison between revolution ensemble and blade pass ensemble at 94% vane axial chord

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Figure 14

Comparison of the 1st harmonic of the unsteady pressure on the rotor at 96.5% span

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Figure 13

Comparison of the 1st harmonic of unsteady pressure on the rotor at 50% span

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Figure 12

Comparison of unsteady harmonics on the rotor at 50% span

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