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

Author:

Yoon Yong Sang1,Song Seung Jin1,Shin Hyoun-Woo2

Affiliation:

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

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

Abstract

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.

Publisher

ASME International

Subject

Mechanical Engineering

Reference21 articles.

1. Rains, D. A. , 1954, “Tip Clearance Flow in Axial Flow Compressors and Pumps,” Hydrodynamics and Mechanical Engineering Laboratories Report, No. 5.

2. Endwall Blockage in Axial Compressors;Khalid;ASME J. Turbomach.

3. An Approximate Analysis and Prediction Method for Tip Clearance Loss in Axial Compressors;Storer;ASME J. Turbomach.

4. Tip Clearance Flow in a Compressor Rotor Passage at Design and Off-Design Conditions;Lakshminarayana;ASME J. Eng. Gas Turbines Power

5. Martinez-Sanchez, M., and Gauthier, R. P., 1990, “Blade Scale Effects of Tip Leakage,” Gas Turbine Laboratory Report #202, M.I.T.

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