Effect of Squealer Tip on Rotor Heat Transfer and Efficiency

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

AYT Corporation, Brook Park, OH 44135

E. Steinthorsson

Institute for Computational Mechanics in Propulsion (ICOMP), NASA Lewis Research Center, Brook Park, OH 44142

D. L. Rigby

NYMA, Inc., NASA Lewis Group, Brook Park, OH 44142

J. Turbomach 120(4), 753-759 (Oct 01, 1998) (7 pages) doi:10.1115/1.2841786 History: Received February 01, 1997; Online January 29, 2008


Calculations were performed to simulate the tip flow and heat transfer on the GE-E3 first-stage turbine, which represents a modern gas turbine blade geometry. Cases considered were a smooth tip, 2 percent recess, and 3 percent recess. In addition, a two-dimensional cavity problem was calculated. Good agreement with experimental results was obtained for the cavity calculations, demonstrating that the k–ω turbulence model used is capable of representing flows of the present type. In the rotor calculations, two dominant flow structures were shown to exist within the recess. Also areas of large heat transfer rate were identified on the blade tip and the mechanisms of heat transfer enhancement were discussed. No significant difference in adiabatic efficiency was observed for the three tip treatments investigated.

Copyright © 1998 by The American Society of Mechanical Engineers
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