Numerical Simulation Of Compound Air-cooling Turbine Blade With Parallel Computation

With the development of modern numerical heat transfer,the need for high performance and high capacity becomes more and more urgent,computation becomes more and more complex,scale develops with positive exponent.For such tremendous calculation tasks,a single computer is not able to complete these computations obviously:one is the limited capability of single processor;the other is those special expensive parallel computers are too expensive and formerly resource have to be abandoned,which is waste.Therefore,it is necessary and realistic meaning for us to develop an effective parallel calculating technology,platform and realizing method for different researchers,at the same time we can use present computer software and hardware resources fully.Using the existing computers,this paper has constructed a parallel PC cluster-based system with 3 computers;also can extending more computer nodes easily.This parallel platform uses Windows XP system and is specially to the numerical simulation of compound air-cooling turbine blade.Then this paper tests the performance of the parallel platform.In the basis of upwards work,this paper simulates the flow and heat transfer of a compound air-cooling guide vane.And gets the interaction of convective cooling and film cooling.This paper simulates four cases such as convective cooling,convective/filmcooling,intensified convective/film cooling and film cooling,and gets the flow and heat transfer of the turbine cascade respectively under three blowing ratios.On every cases the flow of turbine cascade is similer.The cooling efficiency of film cooling is complex while The cooling efficiencies of other three cases increase with increasing blow ratios.With the same blowing ratio,the cooling efficiency of convective/film cooling is highest and intensified convective/film cooling can not increase the cooling efficiency.At last, numerical simulation about flow and heat transfer of rotating turbine blade heated by hot gas is carried out in actual aeroenging condition. Numerical results show that rotation affect the pressure,mach number and temperature of the fluid.Rotation changes the flow direction of the fluid,makes the pressure in the turbine cascade have an average tendency and changes the average cooling efficiency of the surface of turbine blade.