Film Cooling Effectiveness for an Advanced-Louver Cooling Scheme for Gas Turbines

作者: X. Z. Zhang , I. Hassan

DOI: 10.2514/1.18898

关键词:

摘要: A novel film-cooling scheme for high temperature gas turbine applications was introduced in this paper. Compared with the traditional circular hole, new combines both advantages of film cooling those impingement cooling. The hole that transports coolant fluid from inside to outside blade is designed such a way must go through bend before exiting blade, thus impinging on material. This expected produce greatest coverage least amount mixing and possible coolant. benchmark case crossflow, fundamental problem cooling, employed validate present methodology jet liftoff effect clearly captured simulation. Turbulence modeled using four different turbulence models, namely, k-e (including its three variants), k-w, Reynolds-stress, Spalart-Allmaras wall treatments. It found proposed can prevent jets penetrating into mainstream much better provide more uniform protection surface, indicating yields superior performance.

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