To enhance the internal heat transfer around the airfoil leading-edge area, a combination of rib-roughened cooling channels, film cooling, and impingement cooling is often employed. Experimental data for impingement on various leading-edge geometries are reported by these and other investigators. The effects of strong cross-flows on the leading—edge impingement heat transfer, however, have not been studied to that extent. This investigation dealt with impingement on the leading edge of an airfoil in the presence of cross-flows beyond the cross-flow created by the upstream jets (spent air). Measurements of heat transfer coefficients on the airfoil nose area as well as the pressure and suction side areas are reported. The tests were run for a range of axial to jet mass flow rates ranging from 1.14 to 6.4 and jet Reynolds numbers ranging from 8000 to 48,000. Comparisons are also made between the experimental results of impingement with and without the presence of cross-flow and between representative numerical and measured heat transfer results. It was concluded that (a) the presence of the external cross-flow reduces the impinging jet effectiveness both on the nose and sidewalls; (b) even for an axial to jet mass flow ratio as high as 5, the convective heat transfer coefficient produced by the axial channel flow was less than that of the impinging jet without the presence of the external cross-flow; and (c) the agreement between the numerical and experimental results was reasonable with an average difference ranging from to .
Skip Nav Destination
Article navigation
January 2009
Research Papers
Experimental and Numerical Impingement Heat Transfer in an Airfoil Leading-Edge Cooling Channel With Cross-Flow
M. E. Taslim,
M. E. Taslim
Mechanical and Industrial Engineering Department,
Northeastern University
, Boston, MA 02115
Search for other works by this author on:
D. Bethka
D. Bethka
Mechanical and Industrial Engineering Department,
Northeastern University
, Boston, MA 02115
Search for other works by this author on:
M. E. Taslim
Mechanical and Industrial Engineering Department,
Northeastern University
, Boston, MA 02115
D. Bethka
Mechanical and Industrial Engineering Department,
Northeastern University
, Boston, MA 02115J. Turbomach. Jan 2009, 131(1): 011021 (7 pages)
Published Online: November 26, 2008
Article history
Received:
June 12, 2007
Revised:
September 26, 2007
Published:
November 26, 2008
Citation
Taslim, M. E., and Bethka, D. (November 26, 2008). "Experimental and Numerical Impingement Heat Transfer in an Airfoil Leading-Edge Cooling Channel With Cross-Flow." ASME. J. Turbomach. January 2009; 131(1): 011021. https://doi.org/10.1115/1.2950058
Download citation file:
Get Email Alerts
Evaluating Thin-Film Thermocouple Performance on Additively Manufactured Turbine Airfoils
J. Turbomach (July 2025)
Thermohydraulic Performance and Flow Structures of Diamond Pyramid Arrays
J. Turbomach (July 2025)
Related Articles
Investigation of Flow and Heat Transfer of an Impinging Jet in a Cross-Flow For Cooling of a Heated Cube
J. Electron. Packag (June,2006)
Experimental and Numerical Investigation of Impingement on a Rib-Roughened Leading-Edge Wall
J. Turbomach (October,2003)
Investigation of Heat Transfer and Pressure Drop of an Impinging Jet in a Cross-Flow for Cooling of a Heated Cube
J. Heat Transfer (December,2008)
An Experimental Study of Impingement on Roughened Airfoil Leading-Edge Walls With Film Holes
J. Turbomach (October,2001)
Related Proceedings Papers
Related Chapters
A Computational Assessment of Gas Jets in a Bubbly Co-Flow
Proceedings of the 10th International Symposium on Cavitation (CAV2018)
Vortex-Induced Vibration
Flow Induced Vibration of Power and Process Plant Components: A Practical Workbook
Thermal Design Guide of Liquid Cooled Systems
Thermal Design of Liquid Cooled Microelectronic Equipment