Numerical simulations of flow and heat transfer are presented for a GE-E3 turbine blade with a film-cooled tip. Results are presented for both a flat tip and a squealer tip. Straight-through coolant holes are considered, and the calculation domain includes the flow development in the coolant delivery tubes. Results are presented with three different tip gaps representing 1%, 1.5% and 2.5% of blade span, a blowing ratio (ratio of coolant-jet-exit velocity to average passage flow velocity) of 1, and an inlet turbulence intensity of 6.1%. On a flat tip, film coolant injection is shown to lower the local pressure ratio and alters the nature of the leakage vortex. High film cooling effectiveness and low heat transfer coefficients are obtained along the coolant trajectory; these values increase slightly with increasing tip clearances. For a squealer tip, the flow inside the squealer cavity exhibits streamwise directed flow, which alters the trajectory of the coolant jets and reduces their effectiveness.
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ASME Turbo Expo 2002: Power for Land, Sea, and Air
June 3–6, 2002
Amsterdam, The Netherlands
Conference Sponsors:
- International Gas Turbine Institute
ISBN:
0-7918-3608-8
PROCEEDINGS PAPER
Numerical Simulation of Film Cooling on the Tip of a Gas Turbine Blade Available to Purchase
Sumanta Acharya,
Sumanta Acharya
Louisiana State University, Baton Rouge, LA
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Huitao Yang,
Huitao Yang
Louisiana State University, Baton Rouge, LA
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Srinath V. Ekkad,
Srinath V. Ekkad
Louisiana State University, Baton Rouge, LA
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Chander Prakash,
Chander Prakash
GE Aircraft Engines, Cincinnati, OH
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Ron Bunker
Ron Bunker
GE Corporate Research, Schenectady, NY
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Sumanta Acharya
Louisiana State University, Baton Rouge, LA
Huitao Yang
Louisiana State University, Baton Rouge, LA
Srinath V. Ekkad
Louisiana State University, Baton Rouge, LA
Chander Prakash
GE Aircraft Engines, Cincinnati, OH
Ron Bunker
GE Corporate Research, Schenectady, NY
Paper No:
GT2002-30553, pp. 1051-1062; 12 pages
Published Online:
February 4, 2009
Citation
Acharya, S, Yang, H, Ekkad, SV, Prakash, C, & Bunker, R. "Numerical Simulation of Film Cooling on the Tip of a Gas Turbine Blade." Proceedings of the ASME Turbo Expo 2002: Power for Land, Sea, and Air. Volume 3: Turbo Expo 2002, Parts A and B. Amsterdam, The Netherlands. June 3–6, 2002. pp. 1051-1062. ASME. https://doi.org/10.1115/GT2002-30553
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