The gas turbine has an assembly gap between the combustion chamber and the first stage vane, and there is a need for cold air inside to ensure that the high temperature gas does not invade, and the cold air leakage flow can enter the slot to cool the endwall. The study of the cooling effect of the leakage flow on the endwall can provide important guidance for gas turbine design.

In this paper, the effect of slot jet on the cooling performance of turbine blade endwall under the condition of Mach number near real machine is studied by the combination of experiment and numerical method.  At the tilt angles of 30°, 45°, and 60°, the experimental and numerical calculations of the blow ratios of 0.3, 0.6, 1.0, 1.4, 1.7, and 2.0 were performed under near real machine conditions. The results show that in the experimental coverage conditions, the cooling efficiency increases with the increase of the blowing ratio. At the same time, the increase in the blowing ratio results in a more uniform cold air coverage on the endwall surface; as the blowing ratio increases, the degree of increase in the endwall cooling efficiency tends to be gentle. Under the same working conditions, there is no significant difference in the cooling efficiency of the endwall with different inclination angles, which indicates that the angle of inclination angle has no significant effect on the cooling effect of the endwall under the condition of near real machine.


Effect of Inlet Mach Number on Aerothermodynamics of Sealing Leakage Flow Cooling on Endwall

Division / Sponsor:
International Gas Turbine Institute (IGTI)

Paper Proceedings: https://asmedigitalcollection.asme.org/GT/GT2020/volume/84058

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