In gas turbine engines, film cooling holes are often fed by an internal cross-flow, with flow normal to the direction of the external flow around the airfoil. Many experimental studies have used a quiescent plenum to feed model film cooling holes and thus do not account for the effects of internal cross-flow. In this study, an experimental flat plate facility was constructed to study the effects of internal cross-flow on a row of cylindrical compound angle film cooling holes. Operating conditions were scaled, based on coolant hole Reynolds number and turbulence level, to match realistic turbine engine conditions. A cross-flow channel allowed for coolant to flow alternately in either direction perpendicular to the mainstream flow. Film cooling holes were operated at blowing ratios ranging from 0.5 to 2.0 at a density ratio of 1.5. There are relatively few studies available in literature that focus on the effects of cross-flow on film cooling performance, with no studies examining the effects of internal cross-flow on film cooling with round, compound angled holes. This study showed that significantly greater adiabatic effectiveness was achieved for cross-flow in the opposite direction of the span-wise direction of the coolant holes and provides possible explanations for this result.
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ASME Turbo Expo 2014: Turbine Technical Conference and Exposition
June 16–20, 2014
Düsseldorf, Germany
Conference Sponsors:
- International Gas Turbine Institute
ISBN:
978-0-7918-4572-1
PROCEEDINGS PAPER
The Effect of Internal Cross-Flow on the Adiabatic Effectiveness of Compound Angle Film Cooling Holes
John W. McClintic,
John W. McClintic
University of Texas at Austin, Austin, TX
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Sean R. Klavetter,
Sean R. Klavetter
University of Texas at Austin, Austin, TX
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Joshua B. Anderson,
Joshua B. Anderson
University of Texas at Austin, Austin, TX
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James R. Winka,
James R. Winka
University of Texas at Austin, Austin, TX
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David G. Bogard,
David G. Bogard
University of Texas at Austin, Austin, TX
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Jason E. Dees,
Jason E. Dees
GE Global Research, Niskayuna, NY
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Gregory M. Laskowski,
Gregory M. Laskowski
GE Aviation, Cincinnati, OH
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Robert Briggs
Robert Briggs
GE Aviation, Cincinnati, OH
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John W. McClintic
University of Texas at Austin, Austin, TX
Sean R. Klavetter
University of Texas at Austin, Austin, TX
Joshua B. Anderson
University of Texas at Austin, Austin, TX
James R. Winka
University of Texas at Austin, Austin, TX
David G. Bogard
University of Texas at Austin, Austin, TX
Jason E. Dees
GE Global Research, Niskayuna, NY
Gregory M. Laskowski
GE Aviation, Cincinnati, OH
Robert Briggs
GE Aviation, Cincinnati, OH
Paper No:
GT2014-25975, V05BT13A035; 12 pages
Published Online:
September 18, 2014
Citation
McClintic, JW, Klavetter, SR, Anderson, JB, Winka, JR, Bogard, DG, Dees, JE, Laskowski, GM, & Briggs, R. "The Effect of Internal Cross-Flow on the Adiabatic Effectiveness of Compound Angle Film Cooling Holes." Proceedings of the ASME Turbo Expo 2014: Turbine Technical Conference and Exposition. Volume 5B: Heat Transfer. Düsseldorf, Germany. June 16–20, 2014. V05BT13A035. ASME. https://doi.org/10.1115/GT2014-25975
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