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TECHNICAL PAPERS

Performance and Flow Characteristics of an Optimized Supercritical Compressor Stator Cascade

[+] Author and Article Information
Bo Song1

Department of Mechanical Engineering, Virginia Polytechnic Institute and State University, Blacksburg, VA 24061

Wing F. Ng

Department of Mechanical Engineering, Virginia Polytechnic Institute and State University, Blacksburg, VA 24061

1

Currently with Gardner Denver, Inc.

J. Turbomach 128(3), 435-443 (Feb 01, 2005) (9 pages) doi:10.1115/1.2183316 History: Received October 01, 2004; Revised February 01, 2005

An experimental and numerical study was performed on an optimized compressor stator cascade designed to operate efficiently at high inlet Mach numbers (M1) ranging from 0.83 to 0.93 (higher supercritical flow conditions). Linear cascade tests confirmed that low losses and high turning were achieved at normal supercritical flow conditions (0.7<M1<0.8), as well as higher supercritical flow conditions (0.83<M1<0.93), both at design and off-design incidences. The performance of this optimized stator cascade is better than those reported in the literature based on Double Circular Arc (DCA) and Controlled Diffusion Airfoil (CDA) blades, where losses increase rapidly for M1>0.83. A two-dimensional (2D) Navier-Stokes solver was applied to the cascade to characterize the performance and flow behavior. Good agreement was obtained between the CFD and the experiment. Experimental loss characteristics, blade surface Mach numbers, shadowgraphs, along with CFD flowfield simulations, were presented to elucidate the flow physics. It is found that low losses are due to the well-controlled boundary layer, which is attributed to an optimum flow structure associated with the blade profile. The multishock pattern and the advantageous pressure gradient distribution on the blade are the key reasons of keeping the boundary layer from separating, which in turn accounts for the low losses at the higher supercritical flow conditions.

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Copyright © 2006 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

The Virginia Tech High Speed Cascade Wind Tunnel

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Figure 2

Blade profile and cascade nomenclature

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Figure 3

Aerodynamic measurements

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Figure 4

Computation domain and grid

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Figure 5

Cascade performance at the design inlet flow angle (α1=48.4deg)

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Figure 6

Tested cascade performance with AVDR control at the design condition (M1=0.87, α1=48.4deg)

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Figure 7

Loss-incidence characteristics

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Figure 8

Blade surface isentropic Mach number at the design inlet flow angle (α1=48.4deg)

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Figure 9

Blade surface isentropic Mach number at the off-design inlet flow angle (α1=45.4deg)

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Figure 10

Flowfield at the design condition (M1=0.87, α1=48.4deg)

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Figure 11

Shock pattern at the design condition (M1=0.87, α1=48.4deg)

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Figure 12

Flow development with M1 at α1=48.4deg

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Figure 13

Flow variation with incidence at M1=0.87

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Figure 14

Shadowgraph at M1=0.87, α1=45.4deg

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