Numerical Simulation And Optimization Design Research For Film Cooling On Gas Turbine

Gas turbine is a new powerplant which has been used widely on aviation,electric power generation,metallurgy,chemical industry,dissemination,energy and power engineering and such areas and play a very important part in national economy and national defense construction.At present,turbine inlet temperature of advanced engine has reached about 2000K which is 400K higher than the metal melting point of high-pressure turbine blades.Therefore,we must take a certain cooling measures to reduce the temperature of the parts surface and heat load.The current heat proof methods of high temperature engine parts are perturbation cooling,ballistic cooling and film cooling in which film cooling technology is used most widely has a bright future,so the design of film cooling holes is very important.However,most foreigners home and abroad make researches largely though experiments and experience design,few of them make design from optimization design.With the rapid development of computational fluid dynamics and computer,Numerical simulation of cooling effectiveness at different sites on turbine blade surface has been possible,and exactly simulate the characteristic of flow field in turbine and surface cooling effectiveness,thus do not need many experiment.Using numerical simulation method to analysis and research the cooling effectiveness on turbine blade surface can improve reliability and reduce the cost.So numerical simulation method is a important means to research the inner mechanism of turbine.In this article,numerical simulation is carried out to the turbine cascade without film cooling using the Fine/Turbo software of the Belguimcompany NUMECA,it turns out that static pressure distribution and heat flow rate with the experimental results have been very good accord and verify the feasibility of a numerical simulation.Thus we select the appropriate turbulence model.Under condition of changing aperture and injection angle, numerical simulation are carried out respectly to the turbine cascade with one row cooling holes in front of leading edge,and get the changing relationship of useful effect area and air coolant flow on lower holes with different aperture and injection angle.And on this basis,a numerical analysis is performed in Matlab to get the changing relationship of specific discharge with aperture and injection angle under temperature constraint,so as to make a firm foundation of film cooling design and provide a new design method and valuable reference. At last,we also make a brief introduction of design and analysis of controller in hybrid electric vehicle during the time of postgraduate.