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TECHNICAL PAPERS

Influence of Flow Coefficient, Stagger Angle, and Tip Clearance on Tip Vortex in Axial Compressors

[+] Author and Article Information
Yong Sang Yoon

School of Mechanical and Aerospace Engineering,  Seoul National University, San 56-1, Shillim dong, Kwanak gu, Seoul, 151-744, Koreaperfect1@snu.ac.kr

Seung Jin Song

School of Mechanical and Aerospace Engineering,  Seoul National University, San 56-1, Shillim dong, Kwanak gu, Seoul, 151-744, Korea

Hyoun-Woo Shin

 GE Transportation, Aircraft Engines, 1 Neumann Way, Cincinnati, Ohio, 45215

J. Fluids Eng 128(6), 1274-1280 (Mar 27, 2006) (7 pages) doi:10.1115/1.2354522 History: Received April 27, 2005; Revised March 27, 2006

Experiments have been performed on the low speed research compressor (LSRC) at General Electric Aircraft Engines to investigate the effects of flow coefficient, stagger angle, and tip clearance on tip vortex. Time resolved casing pressure distributions over the third stage rotor have been acquired with high-frequency-response pressure transducers. Also, tip vortex strength and trajectory have been estimated from the casing pressure fluctuations which have been obtained simultaneously from various axial locations. As flow coefficient decreases, tip vortex gets strengthened and migrates upstream. The stagger angle increase weakens the tip vortex and moves it downstream slightly because the blade loading is decreased. However, tip leakage vortex is influenced mainly by tip clearance, and there exists a “critical” tip clearance which determines the type of tip vortex trajectory (“straight” or “kinked”). As predicted by others, tip vortex gets strengthened with increasing tip clearance. However, unlike the predictions, the tip vortex trajectory moves upstream with increasing tip clearance. Furthermore, with tip clearance above a “critical” value, the tip vortex trajectory is no longer straight but shows a kink in the passage.

Copyright © 2006 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

Tip leakage vortex

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Figure 2

Low speed research compressor (LSRC) at GE aircraft engines (GEAE)

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Figure 3

Pressure transducer locations on the casing wall of Stage 3 rotor

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Figure 4

Data acquisition system

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Figure 5

Stagger angle setting

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Figure 6

Compressor characteristic curves

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Figure 7

C¯p(t) distributions for the baseline configuration

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Figure 8

C¯p(t) distributions for the stagger configuration

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Figure 9

C¯p(t) distributions for the tip configuration

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Figure 10

C¯pdev distributions for the baseline configuration

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Figure 11

C¯pdev distributions for the stagger configuration

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Figure 12

C¯pdev distributions for the tip configuration

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Figure 13

Tip vortex trajectory kink

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Figure 14

Vortex trajectory angle versus flow coefficient for all configurations

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Figure 15

Pressure random unsteadiness versus flow coefficient for all configurations

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