Louver cooling scheme for gas turbines : Multiple rows

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