Detailed heat transfer coefficient distributions on a gas turbine squealer tip blade were measured using a hue detection based transient liquid-crystals technique. The heat transfer coefficients on the shroud and near tip regions of the pressure and suction sides of a blade were also measured. Squealer rims were located along (a) the camber line, (b) the pressure side, (c) the suction side, (d) the pressure and suction sides, (e) the camber line and the pressure side, and (f) the camber line and the suction side, respectively. Tests were performed on a five-bladed linear cascade with a blow down facility. The Reynolds number based on the cascade exit velocity and the axial chord length of a blade was and the overall pressure ratio was 1.2. Heat transfer measurements were taken at the three tip gap clearances of 1.0%, 1.5%, and 2.5% of blade span. Results show that the heat transfer coefficients on the blade tip and the shroud were significantly reduced by using a squealer tip blade. Results also showed that a different squealer geometry arrangement changed the leakage flow path and resulted in different heat transfer coefficient distributions. The suction side squealer tip provided the lowest heat transfer coefficient on the blade tip and near tip regions compared to the other squealer geometry arrangements.
Skip Nav Destination
e-mail: jchan@mengr.tamu.edu
Article navigation
October 2003
Technical Papers
Heat Transfer Coefficients on the Squealer Tip and Near-Tip Regions of a Gas Turbine Blade With Single or Double Squealer
Jae Su Kwak,
Jae Su Kwak
Turbine Heat Transfer Laboratory, Department of Mechanical Engineering, Texas A&M University, College Station, TX 77843-3123
Search for other works by this author on:
Jaeyong Ahn,
Jaeyong Ahn
Turbine Heat Transfer Laboratory, Department of Mechanical Engineering, Texas A&M University, College Station, TX 77843-3123
Search for other works by this author on:
Je-Chin Han,
e-mail: jchan@mengr.tamu.edu
Je-Chin Han
Turbine Heat Transfer Laboratory, Department of Mechanical Engineering, Texas A&M University, College Station, TX 77843-3123
Search for other works by this author on:
C. Pang Lee,
C. Pang Lee
GE Aircraft Engines, 1 Neumann Way, MD A406, Cincinnati, OH 45215-6301
Search for other works by this author on:
Ronald S. Bunker,
Ronald S. Bunker
GE Corporate R&D, K-1, ES-119, P.O. Box 8, Schenectady, NY 12301
Search for other works by this author on:
Robert Boyle,
Robert Boyle
NASA Research Center, 21000 Brookpark Road, MS 5-11, Cleveland, OH 44135
Search for other works by this author on:
Raymond Gaugler
Raymond Gaugler
NASA Research Center, 21000 Brookpark Road, MS 5-11, Cleveland, OH 44135
Search for other works by this author on:
Jae Su Kwak
Turbine Heat Transfer Laboratory, Department of Mechanical Engineering, Texas A&M University, College Station, TX 77843-3123
Jaeyong Ahn
Turbine Heat Transfer Laboratory, Department of Mechanical Engineering, Texas A&M University, College Station, TX 77843-3123
Je-Chin Han
Turbine Heat Transfer Laboratory, Department of Mechanical Engineering, Texas A&M University, College Station, TX 77843-3123
e-mail: jchan@mengr.tamu.edu
C. Pang Lee
GE Aircraft Engines, 1 Neumann Way, MD A406, Cincinnati, OH 45215-6301
Ronald S. Bunker
GE Corporate R&D, K-1, ES-119, P.O. Box 8, Schenectady, NY 12301
Robert Boyle
NASA Research Center, 21000 Brookpark Road, MS 5-11, Cleveland, OH 44135
Raymond Gaugler
NASA Research Center, 21000 Brookpark Road, MS 5-11, Cleveland, OH 44135
Contributed by the International Gas Turbine Institute and presented at the International Gas Turbine and Aeroengine Congress and Exhibition, Atlanta, GA, June 16–19, 2003. Manuscript received by the IGTI December 2002; final revision March 2003. Paper No. 2003-GT-38907. Review Chair: H. R. Simmons.
J. Turbomach. Oct 2003, 125(4): 778-787 (10 pages)
Published Online: December 1, 2003
Article history
Received:
December 1, 2002
Revised:
March 1, 2003
Online:
December 1, 2003
Citation
Kwak, J. S., Ahn , J., Han, J., Lee, C. P., Bunker, R. S., Boyle , R., and Gaugler, R. (December 1, 2003). "Heat Transfer Coefficients on the Squealer Tip and Near-Tip Regions of a Gas Turbine Blade With Single or Double Squealer ." ASME. J. Turbomach. October 2003; 125(4): 778–787. https://doi.org/10.1115/1.1626684
Download citation file:
Get Email Alerts
Related Articles
Effect of Squealer Geometry Arrangement on a Gas Turbine Blade Tip
Heat Transfer
J. Heat Transfer (June,2002)
Heat Transfer and Pressure Distributions on a Gas Turbine Blade Tip
J. Turbomach (October,2000)
Heat Transfer and Flow on the Squealer Tip of a Gas Turbine Blade
J. Turbomach (October,2000)
Heat Transfer Coefficients on the Squealer Tip and Near Squealer Tip Regions of a Gas Turbine Blade
J. Heat Transfer (August,2003)
Related Proceedings Papers
Related Chapters
Control and Operational Performance
Closed-Cycle Gas Turbines: Operating Experience and Future Potential
Numerical Simulation and Analysis on Gas Turbine Static Blade Erosion Caused by Particle Flow
International Conference on Mechanical and Electrical Technology, 3rd, (ICMET-China 2011), Volumes 1–3
Introduction
Consensus on Operating Practices for Control of Water and Steam Chemistry in Combined Cycle and Cogeneration