Numerical investigation of heat transfer on film cooling with shaped holes
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PurposeTo develop a reliable methodology and procedure of simulating the jetincrossflow using the current turbulence models and numerically investigate the cooling performance of a new scheme for the engines of next generation.Design/methodology/approachA new advanced film cooling scheme is proposed based on the literature survey and a systematic methodology developed to successfully predict the right level of heat transfer in the CFD simulation of film cooling.FindingsThe proposed cooling scheme gives considerable lower heat transfer coefficient at the centerline in the near hole region than the traditional cylindrical hole, especially at a high blowing ratio when traditional cylindrical hole undergoes liftoff.Research limitations/implicationsThe number of cooling holes in the computational domain is limited by the speed of the computers used.Practical implicationsThe new methodology can be used to numerically test new cooling schemes in the design of turbine blades and to provide useful information/data under actual working conditions to design engineers.Originality/valueThis paper provides some useful information on the simulation of film cooling in terms of the performance of different turbulence models and wall treatments and also sends some valuable messages regarding the design of cooling scheme of turbine blades to the technical community.
