Impinging jets are commonly used to enhance heat transfer in modern gas turbine engines. Impinging jets used in turbine blade cooling typically operate at lower Reynolds numbers in the range of 10,000–20,000. In combustor liner cooling, the Reynolds numbers of the jets can be as high as 60,000. The present study is aimed at experimentally testing two different styles of jet impingement geometries to be used in backside combustor cooling. The higher jet Reynolds numbers lead to increased overall heat transfer characteristics, but also an increase in crossflow caused by spent air. The crossflow air has the effect of rapidly degrading the downstream jets at high jet Reynolds numbers. In an effort to increase the efficiency of the coolant air, configurations designed to reduce the harmful effects of crossflow are studied. Two main designs, a corrugated wall and extended port, are tested. Local heat transfer coefficients are obtained for each test section through a transient liquid crystal technique. Results show that both geometries reduce the crossflow induced degradation on downstream jets, but different geometries perform better at different Reynolds numbers. The extended port and corrugated wall configurations show similar benefits at the high Reynolds numbers, but at low Reynolds numbers, the extended port design increases the overall level of heat transfer. This is attributed to the developed jet velocity profile at the tube exit. The best possible explanation is that the benefit of the developed jet velocity profile diminishes as jet velocities rise and the air has lesser time to develop prior to exiting.
Skip Nav Destination
Article navigation
June 2009
Research Papers
Novel Jet Impingement Cooling Geometry for Combustor Liner Backside Cooling
E. I. Esposito,
E. I. Esposito
Lockheen Martin Space Systems Company
, New Orleans, LA 70734
Search for other works by this author on:
Yong Kim,
Yong Kim
Solar Turbines, Inc.
, San Diego, CA 92101
Search for other works by this author on:
Partha Dutta
Partha Dutta
Solar Turbines, Inc.
, San Diego, CA 92101
Search for other works by this author on:
E. I. Esposito
Lockheen Martin Space Systems Company
, New Orleans, LA 70734
S. V. Ekkad
Yong Kim
Solar Turbines, Inc.
, San Diego, CA 92101
Partha Dutta
Solar Turbines, Inc.
, San Diego, CA 92101J. Thermal Sci. Eng. Appl. Jun 2009, 1(2): 021001 (8 pages)
Published Online: August 20, 2009
Article history
Received:
October 21, 2008
Revised:
April 28, 2009
Published:
August 20, 2009
Citation
Esposito, E. I., Ekkad, S. V., Kim, Y., and Dutta, P. (August 20, 2009). "Novel Jet Impingement Cooling Geometry for Combustor Liner Backside Cooling." ASME. J. Thermal Sci. Eng. Appl. June 2009; 1(2): 021001. https://doi.org/10.1115/1.3202799
Download citation file:
Get Email Alerts
Cited By
Related Articles
Experimental Investigation on the Heat Transfer of a Leading Edge Impingement Cooling System for Low Pressure Turbine Vanes
J. Heat Transfer (December,2010)
Experimental and Numerical Cross-Over Jet Impingement in an Airfoil Trailing-Edge Cooling Channel
J. Turbomach (October,2011)
Full Surface Local Heat Transfer Coefficient Measurements in a Model of an Integrally Cast Impingement Cooling Geometry
J. Turbomach (January,1998)
Channel Height Effect on Heat Transfer and Friction in a Dimpled Passage
J. Eng. Gas Turbines Power (April,2000)
Related Proceedings Papers
Related Chapters
Control and Operational Performance
Closed-Cycle Gas Turbines: Operating Experience and Future Potential
Outlook
Closed-Cycle Gas Turbines: Operating Experience and Future Potential
Thermodynamic Performance
Closed-Cycle Gas Turbines: Operating Experience and Future Potential