Film cooling plays a critical role in providing effective thermal protection to components in modern gas turbine engines. A significant effort has been undertaken over the last 40 years to improve the distribution of coolant and to ensure that the airfoil is protected by this coolant from the hot gases in the freestream. This film, under conditions with high fuel-air ratios, may actually be detrimental to the underlying metal. The presence of unburned fuel from an upstream combustor may interact with this oxygen rich film coolant jet resulting in secondary combustion. The completion of the reactions can increase the gas temperature locally resulting in higher heat transfer to the airfoil directly along the path line of the film coolant jet. This secondary combustion could damage the turbine blade, resulting in costly repair, reduction in turbine life, or even engine failure. However, knowledge of film cooling in a reactive flow is very limited. The current study explores the interaction of cooling flow from typical cooling holes with the exhaust of a fuel-rich well-stirred reactor operating at high temperatures over a flat plate. Surface temperatures, heat flux, and heat transfer coefficients are calculated for a variety of reactor fuel-to-air ratios, cooling hole geometries, and blowing ratios. Emphasis is placed on the difference between a normal cylindrical hole, an inclined cylindrical hole, and a fan-shaped cooling hole. When both air and nitrogen are injected through the cooling holes, the changes in surface temperature can be directly correlated with the presence of the reaction. Photographs of the localized burning are presented to verify the extent and locations of the reaction.
Skip Nav Destination
Article navigation
Research Papers
Effects of a Reacting Cross-Stream on Turbine Film Cooling
Wesly S. Anderson,
Wesly S. Anderson
Air Force Research Laboratory, Propulsion Directorate,
Wright Patterson AFB
, Dayton, OH 45433
Search for other works by this author on:
Marc D. Polanka,
Marc D. Polanka
Air Force Research Laboratory, Propulsion Directorate,
Wright Patterson AFB
, Dayton, OH 45433
Search for other works by this author on:
Joseph Zelina,
Joseph Zelina
Air Force Research Laboratory, Propulsion Directorate,
Wright Patterson AFB
, Dayton, OH 45433
Search for other works by this author on:
Dave S. Evans,
Dave S. Evans
Naval Air Systems Command
, NAS, Patuxent River, MD 20670
Search for other works by this author on:
Scott D. Stouffer,
Scott D. Stouffer
University of Dayton Research Institute
, Dayton, OH 45469
Search for other works by this author on:
Garth R. Justinger
Garth R. Justinger
University of Dayton Research Institute
, Dayton, OH 45469
Search for other works by this author on:
Wesly S. Anderson
Air Force Research Laboratory, Propulsion Directorate,
Wright Patterson AFB
, Dayton, OH 45433
Marc D. Polanka
Air Force Research Laboratory, Propulsion Directorate,
Wright Patterson AFB
, Dayton, OH 45433
Joseph Zelina
Air Force Research Laboratory, Propulsion Directorate,
Wright Patterson AFB
, Dayton, OH 45433
Dave S. Evans
Naval Air Systems Command
, NAS, Patuxent River, MD 20670
Scott D. Stouffer
University of Dayton Research Institute
, Dayton, OH 45469
Garth R. Justinger
University of Dayton Research Institute
, Dayton, OH 45469J. Eng. Gas Turbines Power. May 2010, 132(5): 051501 (7 pages)
Published Online: March 3, 2010
Article history
Received:
March 23, 2009
Revised:
June 2, 2009
Online:
March 3, 2010
Published:
March 3, 2010
Citation
Anderson, W. S., Polanka, M. D., Zelina, J., Evans, D. S., Stouffer, S. D., and Justinger, G. R. (March 3, 2010). "Effects of a Reacting Cross-Stream on Turbine Film Cooling." ASME. J. Eng. Gas Turbines Power. May 2010; 132(5): 051501. https://doi.org/10.1115/1.3204616
Download citation file:
Get Email Alerts
Shape Optimization of an Industrial Aeroengine Combustor to reduce Thermoacoustic Instability
J. Eng. Gas Turbines Power
Dynamic Response of A Pivot-Mounted Squeeze Film Damper: Measurements and Predictions
J. Eng. Gas Turbines Power
Review of The Impact Of Hydrogen-Containing Fuels On Gas Turbine Hot-Section Materials
J. Eng. Gas Turbines Power
Effects of Lattice Orientation Angle On Tpms-Based Transpiration Cooling
J. Eng. Gas Turbines Power
Related Articles
Gas Turbine Engine Durability Impacts of High Fuel-Air Ratio Combustors: Near Wall Reaction Effects on Film-Cooled Backward-Facing Step Heat Transfer
J. Eng. Gas Turbines Power (April,2006)
Trailing Edge Film
Cooling of Gas Turbine Airfoils—External Cooling Performance of Various Internal Pin Fin
Configurations
J. Turbomach (October,2011)
High-Resolution Measurements of Local Heat Transfer Coefficients From Discrete Hole Film Cooling
J. Turbomach (October,2001)
Gas Turbine Engine Durability Impacts of High Fuel-Air Ratio Combustors—Part II: Near-Wall Reaction Effects on Film-Cooled Heat Transfer
J. Eng. Gas Turbines Power (July,2003)
Related Chapters
Outlook
Closed-Cycle Gas Turbines: Operating Experience and Future Potential
Introduction
Consensus on Operating Practices for Control of Water and Steam Chemistry in Combined Cycle and Cogeneration
Control and Operational Performance
Closed-Cycle Gas Turbines: Operating Experience and Future Potential