Experimental Study on Effusion Cooling with Tangential Air Inlet
Author:
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.2016-5053
Reference11 articles.
1. Full Coverage Film Cooling for Combustor Transition Sections
2. Full Coverage Discrete Hole Film Cooling: The Influence of Hole Size
3. Full Coverage Discrete Hole Film Cooling: The Influence of the Number of Holes and Pressure Loss
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3. Experimental Study on Lean Blowout of a High Temperature Rise Combustor;55th AIAA Aerospace Sciences Meeting;2017-01-05
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