Accurately predict temperature turbine blades to improve the cooling efficiency and prolong the working life of the key issues blade

Modern aviation gas turbine engines in order to obtain a higher thrust to weight ratio and thermal efficiency , and continuously improve the turbine inlet temperature , turbine inlet temperature is currently far exceed the melting temperature of the blade material , sophisticated cooling techniques must be used to maintain the normal operation of the turbine blades , accurate predicted temperature  Electric energy meter  the cooling efficiency and prolong the working life leaves key issues , with the continuous development of computational fluid dynamics , gas thermal coupling  electric meter  technology has become the major aircraft engine engineering design tools , main work is on the aero-engine turbine blades for gas -cooled thermal coupling numerical simulation, and further improve the thermal coupling of the gas turbine blade accuracy and reliability of  Air circuit breaker  for further analysis . This paper examined how accurately predict boundary layer transition flow problems , aircraft engines are prevalent transitional flows , boundary layer transition before and after the flow state , wall shear stress and heat transfer coefficient are not the same , accurate prediction of boundary layer transition transitional flows starting position for the turbine blade aerodynamic and heat transfer design has very important significance , can accurately simulate the boundary layer transition flow is the key to how to choose a suitable physical model .