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TECHNICAL PAPERS

Heat Transfer and Flow on the Blade Tip of a Gas Turbine Equipped With a Mean-Camberline Strip

[+] Author and Article Information
A. A. Ameri

AYT Corp., Brook Park, OH 44135-3109e-mail: ameri@grc.nasa.gov

J. Turbomach 123(4), 704-708 (Feb 01, 2001) (5 pages) doi:10.1115/1.1400114 History: Received February 01, 2001
Copyright © 2001 by ASME
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References

Figures

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Velocity vectors colored by the velocity magnitude |V|
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Simple radiused edge blade tip. Heat transfer coefficient for 2.03 mm clearance and Tu=5 percent (W/m2 /K): (a) measured 3 and (b) calculated.
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Radiused edge blade tip with mean-camberline strip. Heat transfer coefficient for 2.03 mm clearance and Tu=5 percent (W/m2 /K): (a) measured 4 and (b) calculated.
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Pressure distribution (P static/P0) over the blade tip surface
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Streamline patterns of the flow in the tip region for: (a) radius edged tip, (b) radius edged tip and mean camber line strip
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Blade tip/passage and grid construction
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Airfoil and shroud definition

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