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A Louver Cooling Scheme for Gas Turbines Multiple Rows

DOI: 10.1615/ICHMT.2006.TurbulHeatMassTransf.1600
pages 735-738

X.-Z. Zhang
Department of Mechanical and Industrial Engineering, Concordia University, Montreal, Quebec, Canada, H3G1M8

Ibrahim Hassan
Department of Mechanical and Industrial Engineering, Concordia University, Montreal, Quebec, Canada, H3G1M8; Mechanical Engineering Department, Texas A&M University at Qatar P O Box 23874, Doha, Qatar

T. Lucas
Pratt and Whitney Canada, Longueuil, Quebec, Canada, J4G1A1


The arrangements of two and three rows of holes of a new advanced cooling scheme for gas turbine blades have been studied numerically in this paper and their performance compared with other cooling schemes such as traditional circular holes and discrete slots. The new hole was designed in such a way that the coolant must go through a bend before exiting the blade, thus impinging on the blade material. The flared hole exit was also designed to reduce the coolant momentum in the normal direction and to ensure wide lateral spreading of the coolant on the downstream surface, making the use of coolant air more efficient. Turbulence was modeled using realizable k-ε turbulence model. Three configurations have been studied: two rows of inline holes, two rows of staggered holes, and three rows of staggered holes with holes equally distanced in the span-wise direction. The new scheme produces the highest cooling effectiveness and lowest heat transfer levels among the cooling schemes compared since jet liftoff is avoided. The staggered arrangement offers a much higher laterally averaged cooling effectiveness with a slightly lower heat transfer coefficient than its inline arrangement counterpart. Key words: film cooling, heat transfer, shaped holes, rows of holes, CFD, gas turbines.

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