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TECHNICAL PAPERS

Compressor Stability Enhancement Using Discrete Tip Injection

[+] Author and Article Information
Kenneth L. Suder

NASA Glenn Research Center, Cleveland, OH 44135

Michael D. Hathaway

US Army Vehicle Technology Directorate, Cleveland, OH 44135

Scott A. Thorp, Anthony J. Strazisar, Michelle B. Bright

NASA Glenn Research Center, Cleveland, OH 44135

J. Turbomach 123(1), 14-23 (Feb 01, 2000) (10 pages) doi:10.1115/1.1330272 History: Received February 01, 2000
Copyright © 2001 by ASME
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References

Figures

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Impact of steady and controlled unsteady tip injection on the stability limit of a transonic axial compressor stage as measured by 8
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Scale drawing of a discrete wall injector
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Predicted design speed rotor performance with and without tip injection
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Comparison of predicted incidence and diffusion factor near the blade tip at the baseline stalling massflow with and without tip injection
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Comparison of predicted incidence and diffusion factor across the blade span at the stalling massflows of Configurations A, B, and C (see Fig. 3)
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Measured rotor performance at 70 and 100 percent speed with and without tip injection
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Comparison of diffusion factor measured in the injected and uninjected half of the annulus at 70 percent speed: (a) at operating points 1 and 2 depicted in Fig. 6, and (b) at operating points 1 and 3 depicted in Fig. 6
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Range extension measured at 70 percent speed as a function of injected massflow
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Range extension measured at 70 percent speed as a function of injected massflow for various arrangements of six injectors around the annulus
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Range extension measured at 70 percent speed for half-height and full-height injectors
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Range extension measured at 70 percent speed as a function of mass-averaged axial velocity over the outer 6 percent span normalized by the tip speed
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Range extension measured at 100 percent speed as a function of mass-averaged axial velocity over the outer 6 percent span normalized by the tip speed
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Unsteady compressor operating point at design speed during stall inception and stall recovery with tip injection. Blue: stall inception; gray: fully developed stall; red: stall recovery with tip injection.
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Part-speed performance characteristics of a two-stage high-speed fan with and without tip injection. Solid symbols: nominal IGV schedule with no tip injection; open symbols: IGV fixed at 0 deg (axial) with tip injection.

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