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A Dual-Plane PIV Study of Turbulent Heat Transfer FlowsThin film cooling is a widely used technique in turbomachinery and rocket propulsion applications, where cool injection air protects a surface from hot combustion gases. The injected air typically has a different velocity and temperature from the free stream combustion flow, yielding a flow field with high turbulence and large temperature differences. These thin film cooling flows provide a good test case for evaluating computational model prediction capabilities. The goal of this work is to provide a database of flow field measurements for validating computational flow prediction models applied to turbulent heat transfer flows. In this work we describe the application of a Dual-Plane Particle Image Velocimetry (PIV) technique in a thin film cooling wind tunnel facility where the injection air stream velocity and temperatures are varied in order to provide benchmark turbulent heat transfer flow field measurements. The Dual-Plane PIV data collected include all three components of velocity and all three components of vorticity, spanning the width of the tunnel at multiple axial measurement planes.
Document ID
20160003685
Document Type
Technical Memorandum (TM)
Authors
Wernet, Mark P.
(NASA Glenn Research Center Cleveland, OH United States)
Wroblewski, Adam C.
(NASA Glenn Research Center Cleveland, OH United States)
Locke, Randy J.
(Vantage Partners, LLC Brook Park, OH, United States)
Date Acquired
March 23, 2016
Publication Date
March 1, 2016
Subject Category
Fluid Mechanics And Thermodynamics
Aerodynamics
Report/Patent Number
E-19203
GRC-E-DAA-TN40240
E-19203-1
NASA/TM-2016-219074
GRC-E-DAA-TN30053
Funding Number(s)
CONTRACT_GRANT: NNC12BA01B
WBS: WBS 109492.02.03.01.01.55
Distribution Limits
Public
Copyright
Public Use Permitted.
Keywords
Turbulent heat transfer
Particle Image Velocimetry
Computational Fluid Dynamics

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