Structural and Thermal Analysis of Gas Turbine Blade for in-Line and Zig-Zag Arrangement of Cooling Holes by FEM

Force or Pressure is applied to a material, the material deforms and the effect of Pressure is transmitted all over the material. The external induced pressure and reactions to compose the material into a state of equilibrium. In this project work by using Finite element analysis, Static structural and Steady state thermal analysis will be done for two different arrangement of radial cooling holes one is In-Line and another is Zig-Zag, with different pitches of 7, 8, 9, & 10 numbers models were designed, in Static structural analysis calculates Total Deformation and Equivalent (Von-Mises) Stress, and In Steady State Thermal analysis calculates Temperature Distribution and Total Heat Flux, From the results it is observed that Total deformation of the gas turbine blade is minimum 5.5865E-2 in Zig-Zag arrangement of cooling holes and is maximum 5.6386E-2 in In-Line arrangement and Equivalent (Von-Mises) stress of the gas turbine blade is minimum 1.2504E10 in Zig-Zag arrangement of cooling holes and is maximum 1.3022E10 in In-Line arrangement of cooling holes, Temperature distribution is minimum 934.120C in In-Line arrangement of cooling holes and is maximum 955.990C in Zig-Zag arrangement of cooling holes, and Total heat flux or energy transfer is minimum 1.1418E5 in In-Line arrangement of cooling holes and is maximum 1.2742E5 in Zig-Zag arrangement of cooling holes. From the above results the blade with Zig-Zag arrangement of radial cooling holes has given optimum performance than the In-Line arrangement of cooling holes.