Experimental Investigation of the Effects of a Moving Shock Wave on Compressor Stator Flow

[+] Author and Article Information
Matthew D. Langford

 Techsburg, Inc., 2901 Prosperity Road, Blacksburg, VA 24060mlangford@techsburg.com

Andrew Breeze-Stringfellow

 GE Aircraft Engines, 1 Neumann Way, Cincinnati, OH 45215andy.breeze-stringfellow@ae.ge.com

Stephen A. Guillot

 Techsburg, Inc., 2901 Prosperity Road, Blacksburg, VA 24060sguillot@techsburg.com

William Solomon

 GE Aircraft Engines, 1 Neumann Way, Cincinnati, OH 45215william.solomon@ae.ge.com

Wing F. Ng

Mechanical Engineering Department, Virginia Tech, Blacksburg, VA 24060wng@vt.edu

Jordi Estevadeordal

 Innovative Scientific Solutions, Inc., 2766 Indian Ripple Road, Dayton, OH 45440jordi@innssi.com

J. Turbomach 129(1), 127-135 (Feb 01, 2005) (9 pages) doi:10.1115/1.2370745 History: Received October 01, 2004; Revised February 01, 2005

Linear cascade testing was performed to simulate the flow conditions experienced by stator blades in an axial compressor with supersonic relative Mach numbers at the inlet to the downstream embedded rotors. Experiments were conducted in a transonic blow-down wind tunnel with a nominal inlet Mach number of 0.65. A single moving normal shock introduced at the exit of the stator cascade simulated the bow shock from a downstream rotor. The shock was generated using a shock tube external to the wind tunnel. Pressure measurements indicated that the stator matched its design intent loading, turning, and loss under steady flow conditions. Effects of the passing shock on the stator flowfield were investigated using shadowgraph photography and digital particle image velocimetry (DPIV). Measurements were taken with three different shock strengths. In each case, the passing shock induced a vortex around the trailing edge of the stator. The size and strength of these vortices were directly related to the shock strength. A suction side separation on the trailing edge of the stator was observed and found to correlate with the vortex blockage.

Copyright © 2007 by American Society of Mechanical Engineers
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Figure 1

Schematic of transonic rotor shock structure under (a) design and (b) off-design operation (1-3)

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Figure 2

CAD drawing of the cascade test section in the Virginia Tech Transonic Cascade Wind Tunnel

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Figure 3

Mass-averaged total pressure loss coefficient versus incidence angle

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Figure 4

Isentropic Mach number distribution along the blade surface at design incidence

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Figure 5

Shadowgraph images of shock progression for 1.76 shock strength

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Figure 6

Schematic of the shock turning phenomenon

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Figure 7

DPIV velocity fields of the trailing edge vortex created by the moving shock (shock strength=1.76), with the corresponding shadowgraph image number from Fig. 5

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Figure 8

Trailing edge velocity vector fields for three different shock strengths

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Figure 9

DPIV measured vortex tangential velocity versus radial location within vortex and comparison to theory (shock strength=1.76)

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Figure 13

Trailing edge DPIV velocity vectors of stator suction surface separation due the vortex blockage (shock strength=1.76)

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Figure 14

PIV flow visualization of Von Karman vortex street following the shock-induced vortex

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Figure 10

Sensitivity of DPIV measured tangential velocity to error in locating vortex center (shock strength=1.76)

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Figure 11

Vortex circulation versus shock strength, measured and predicted

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Figure 12

Instantaneous streamlines for steady flow and three different shock strengths, with corresponding effective blockage



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