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Article

Experimental Investigation of a Transonic Aspirated Compressor

[+] Author and Article Information
Brian J. Schuler, Jack L. Kerrebrock, Ali Merchant

 Gas Turbine Laboratory, Department of Aeronautics and Astronautics, Massachusetts Institute of Technology, Cambridge, MA 02139

J. Turbomach 127(2), 340-348 (Mar 01, 2003) (9 pages) doi:10.1115/1.1860575 History: Received December 01, 2001; Revised March 01, 2003

The experimental investigation of a transonic aspirated stage demonstrating the application of boundary layer aspiration to increase stage work is presented. The stage was designed to produce a pressure ratio of 1.6 at a tip speed of 750fts resulting in a stage work coefficient of 0.88. The primary aspiration requirement for the stage is a bleed fraction 0.5% of the inlet mass flow on the rotor and stator suction surfaces. Additional aspiration totaling 2.8% was also used at shock impingement locations and other locations on the hub and casing walls. Detailed rotor and stator flow field measurements, which include time-accurate and ensemble-averaged data, are presented and compared to three-dimensional viscous computational analyses of the stage. The stage achieved a peak pressure ratio of 1.58 and through-flow efficiency of 90% at the design point. In addition, the stage demonstrated good performance with an aspiration lower than the design requirement, and a significant off-design flow range below that predicted by the computational analysis.

Copyright © 2005 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

3D viscous APNASA calculation grid suction configuration

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Figure 2

Rotor 95% span Mach number contours

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Figure 3

Stator 10% span Mach number contours

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Figure 4

Assembly cross section and suction scheme

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Figure 5

Comparison of experimental spanwise total pressure distribution to APNASA analysis

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Figure 6

Comparison of experimental spanwise total temperatire distribution to APNASA

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Figure 7

Pitchwise total pressure profile at 28% rotor span

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Figure 8

Pitchwise tangential angle profile at 28% rotor span

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Figure 9

Time-accurate total pressure and tangential angle at 28% rotor span

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Figure 10

Pitchwise total pressure profile for 65% rotor span

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Figure 11

Pitchwise tangential angle profile for 65% rotor span

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Figure 12

Time-accurate total pressure and tangential angle for 65% rotor span

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Figure 13

Pitchwise total pressure profile at 92% rotor span

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Figure 14

Pitchwise tangential angle profile at 92% rotor span

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Figure 15

Time-accurate total pressure and tangential flow angle at 92% rotor span

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Figure 16

Blade to blade variation in the total pressure at 65% rotor span

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Figure 17

Stator exit total pressure contour predicted by APNASA

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Figure 18

Time-averaged total pressure data from stator exit

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Figure 19

Off-design performance of aspirated fan stage

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Figure 20

Pitchwise total pressure at rotor exit for 65% span at different mass flows

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Figure 21

Time-accurate total pressure data at (a) 100% and (b) 79% mass flow

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Figure 22

Time-accurate radial Mach number distribution at 92% span

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Figure 23

Effect of spanwise transport on efficiency distribution

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