Investigation Of Film Cooling On The Surface Of Blade In A Turbine Cascade

Film cooling of the surface of a gas turbine blade was studied in a large-scale low-speed opening wind tunnel according to actual Requirement of the design of aero-engine. The surface of a gas turbine blade was cooled by cylindrical holes in the experiment,with the hole number of fifteen in stator and eight in rotor.Above all, the surface of the gas turbine blade including stator and rotor heat transfer coeficience with no film cooling hole was studied with the main stream Reynolds number of 150000,200000 50000,300000,350000,400000. Then, the heat transfer coefficience when all cooling holes opened and only one cooling hole opened was studied partly. And it's studied how the mainstream Reynolds number, blowing ratio and the position of holes affect the heat transfer coefficience of the surface of blade. Results show that the influence of mainstream Reynolds numbers on heat transfer coefficience is little and the heat transfer coefficience raise with the increase of Reynolds numbers. The influence of the position of holes on heat transfer coefficience is complex and correlate with the mainstream speed and the balde surface curvature. And the influence of blowing ratio on heat transfer coefficience is more great (especially to stator) ,and show a complex relation to mainstream Reynolds number and the position of holes.A simulation fomular was studied to accord the heat transfer experimental data.