Effect of Squealer Geometry Arrangement on a Gas Turbine Blade Tip Heat Transfer

Author:

Azad Gm Salam1,Han Je-Chin1,Bunker Ronald S.2,Lee C. Pang3

Affiliation:

1. Department of Mechanical Engineering, Turbine Heat Transfer Lab, Texas A&M University, College Station, TX 77843-3123

2. GE R&D Center, Schenectady, NY 12301

3. GE Aircraft Engines, Cincinnati, OH 45215

Abstract

This study investigates the effect of a squealer tip geometry arrangement on heat transfer coefficient and static pressure distributions on a gas turbine blade tip in a five-bladed stationary linear cascade. A transient liquid crystal technique is used to obtain detailed heat transfer coefficient distribution. The test blade is a linear model of a tip section of the GE E3 high-pressure turbine first stage rotor blade. Six tip geometry cases are studied: (1) squealer on pressure side, (2) squealer on mid camber line, (3) squealer on suction side, (4) squealer on pressure and suction sides, (5) squealer on pressure side plus mid camber line, and (6) squealer on suction side plus mid camber line. The flow condition during the blowdown tests corresponds to an overall pressure ratio of 1.32 and exit Reynolds number based on axial chord of 1.1×106. Results show that squealer geometry arrangement can change the leakage flow and results in different heat transfer coefficients to the blade tip. A squealer on suction side provides a better benefit compared to that on pressure side or mid camber line. A squealer on mid camber line performs better than that on a pressure side.

Publisher

ASME International

Subject

Mechanical Engineering,Mechanics of Materials,Condensed Matter Physics,General Materials Science

Reference29 articles.

1. Bunker, R. S., and Bailey, J. C., 2000, “Blade Tip Heat Transfer and Flow With Chordwise Sealing Strips,” International Symposium on Transport Phenomena and Dynamics of Rotating Machinery (ISROMAC), Honolulu, Hawaii, pp. 548–555.

2. Bunker, R. S., and Bailey, J. C., 2000, “An Experimental Study of Heat Transfer and Flow on a Gas Turbine Blade Tip with Various Tip Leakage Sealing Methods,” 4th ISHMT / ASME Heat and Mass Transfer Conference, India.

3. Heyes, F. J. G., Hodson, H. P., and Dailey, G. M., 1991, “The Effect of Blade Tip Geometry on the Tip Leakage Flow in Axial Turbine Cascades,” ASME Paper No. 91-GT-135.

4. Azad, G. S., Han, J. C., and Boyle, R. J., 2000, “Heat Transfer and Flow on the Squealer Tip of a Gas Turbine Blade,” ASME Paper No. 2000-GT-195.

5. Dunn, M. G., and Haldeman, C. W., 2000, “Time-Averaged Heat Flux for a Recessed Tip, Lip, and Platform of a Transonic Turbine Blade,” ASME Paper No. GT-0197.

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