Numerical Investigation of Thermohydraulic Processes in the Cooling Channels of the Nozzle Vane of a High-Temperature Gas Turbine

This study describes investigation of a cooled vane trailing edge part devoted to the temperature distribution smoothening without the film cooling addition. The investigation subject is a slot channel with a perforated deflector. The cooling air is supplied through corridor located orifices and its wall cooled with streams. The side flow influence may be mitigated by shading ribs installed upstream the last three rows of the air supply orifices. The computer simulation with ANSYS CFX code at fixed pressure drops at the channel inlet and exit shows a 40–45% heat flux increase combined with the 24% cooling air massflow reduction. The intensive flow turbulence after the ribs reduces the area with low heat transfer efficiency. The turbine operation analysis shows that the ribs may improve the cooling efficiency for 25–30%.