M.MOOVENDHAN, Mr. S Prashanth, Mr. G.Velmurugan
turbine blade, film cooling, cooling effectiveness, turbulence modeling
Film cooling is one of the cooling methodology for gas turbine blades from preventing the blade melting from the hot gases out of the combustion chamber. Gas turbines use film cooling in addition to turbulated internal cooling to protect the blades outer surface from hot gases. The present study concentrates on the experimental and numerical investigation of film cooling performance for a row of cylindrical holes in a modern turbine blade. The adiabatic film effectiveness and the heat transfer coefficient are determined experimentally on a flat plate downstream of a row of inclined different geometrical hole exit by using a single test transient IR thermography technique were used nowadays for analysis. But in this project a single turbine stator blade (IGV) was generated with different leading edge thickness with cylindrical holes have to be generated and tested by passing cold and hot air to through the corresponding places in the design and analyzed by using CFX solver in the ANSYS. The focus of this investigation is to investigate the cooling efficiency by changing the leading edge thickness of the turbine stator blade. Here the most heat affecting place in the blades are cooled by effectively changing the size and shape of the hole and other places the holes remains with same size and shape. In this project first step is planned by taking two different shapes of holes in the leading edge in the turbine blade and then the design and analysis was carried out through the CFX solver in ANSYS. Then in the second step, the trailing edge was analyzed by using different slot shape and finally the project will ends with total flow simulation in a turbine blade.
Article Details
Unique Paper ID: 149036

Publication Volume & Issue: Volume 6, Issue 10

Page(s): 231 - 239
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