Aircraft Engine Turbine Vane Thermal Barrier Coating Design And Experimental Research

Researches all over the world has revealed that TBCs is a validated way to lower the temperature of the base of guide vanes, to increase the operating temperature, to reduce the flow of cooling air and also to enhance the efficiency of the gas turbine. The development of TBCs is as crucial as that of the development of the new materials and structures for the vanes.The TBCs used in guide vanes of high pressure gas turbine was carried out. Based on the investigation of double-layers TBCs which use MCrAlY as bond coat and yttria partially stablished zirconia (Y-PSZ) as ceramic layer, a innovational method to study techniques and fatigue problem of Electron Beam Physical Vapor Deposition (EB-PVD) is presented.The performance of structures and technical situations of different TBCs were analyzed. Double-layers TBCs is chosen to be used in guide vanes and EB-PVD is selected to be the technique.According to the feature of the guide vanes, a series of hollow cylindrical simulating tests components were designed and manufactured. The fatigue tests on the components with and without TBCs were conducted to evaluate the techniques feasibility.According to tests on the simulating test components, the TBCs techniques were used on the guide vanes of a high pressure turbine. The thickness of the coat on deferent areas are measured. The heat analyses of the thickness model were made to research high temperature performance of high pressure turbine guide vanes with TBCs.Flow tests was made to reveal the effect of the smaller holes caused by TBCs spray. Based on the data measured after coating, the thermal field analysis of the guide vanes with TBCs was carried out.Fatigue test of coated guide vanes was made to analysis the performance and reliability of TBCs.