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TECHNICAL PAPERS

Time-Averaged Heat Flux for a Recessed Tip, Lip, and Platform of a Transonic Turbine Blade

[+] Author and Article Information
M. G. Dunn, C. W. Haldeman

The Ohio State University Gas Turbine Laboratory, Columbus, OH 43235

J. Turbomach 122(4), 692-698 (Feb 01, 2000) (7 pages) doi:10.1115/1.1311285 History: Received February 01, 2000
Copyright © 2000 by ASME
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References

Figures

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Sketch of Allison VBI model in OSU GTL shock tunnel
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Instrumented rotor of VBI turbine
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Photograph of cavity and lip heat-flux gages
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Photograph of platform heat-flux gages
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Time-averaged Nusselt number for rotor blade (50 percent span) versus vane/blade spacing
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Nusselt number on blade tip cavity
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FFT’s of heat-flux gage temperature data: 60 percent vane/blade spacing
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Nusselt number on blade tip
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FFT’s of heat-flux gage temperature data: 60 percent vane/blade spacing
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Nusselt number on blade platform
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FFT’s of heat-flux gage temperature data: 60 percent vane/blade
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Nusselt number on blade suction surface (90 percent span)
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FFT’s of heat-flux gage temperature data: 60 percent vane/blade

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