查看文章

The first high pressure stage of a modern gas turbine operates at very high temperatures that require complex blade-cooling systems to guarantee high performance and efficiency of the gas turbine while maintaining a very low level of energy losses, though using compressed air for cooling.

An accurate and efficient conjugate heat transfer (CHT) solver is thus necessary to compute the flow and temperature fields of the air within the cooling channels and of the gas around the blades—by means of the Navier—Stokes and energy equations—as well as the blade temperature field, by means of the heat conduction equation. Due to the very high geometrical complexity of the cooling channels within the blades, generating a body fitted mesh for the three domains—air, gas and blade—is extremely difficult and time consuming. Nevertheless, many turbine blade-cooling simulations have been performed with success …