Numerical Simulation Of Aero-engine Blade Internal Channel Cooling

The blade inner channel cooling is very important in the design of turbine blade, with the ever-increasing inlet temperature , the new heat transfer enhancement structures of higher performance are demanded .Because of the complexity of the flow and heat transfer of the blade inner channel cooling , the numerical modulation is superior to the experiment .This thesis studied the blade inner channel cooling with the method of numerical modulation .The blade inner channel cooling is a complex convection-conductioncoupling problem .This thesis build a three-dimension .compressibleturbulence model, and give a general solve method .With the geometricalmodel of the glossily rectangle straight channel , the rectangle straightchannel with in-line arrays disturb plates , the rectangle straightchannel with staggered arrays disturb plates , the rectangle straightchannel with slant disturb plates , this thesis compute the flow and heattransfer condition when the cold air path though these channels, and gainthe temperature field , pressure field , velocity filed , in addition . Thisthesis also analyze the influence of the different channel height , thedifferent channel materials , the different channels, and gain thefunction relation between he Nusselt number , friction factor andReynolds number. This thesis is emphasis on the new heat transferenhancement structure , that is , disturb plates , with the comparison withthe glossily channel and channel with pin fins , the heat transferenhancement effect of the former is better , and the conclusion can beused in the design of aircraft blade.