Tip leakage flow in high speed turbine induce significant thermal loads and give rise to intense thermal stresses on blade tip, while increasing inlet pressure tends to accelerate leakage velocity beyond transonic regime. The present research quantifies heat transfer and film cooling effect on a squealer tip with three film cooling layouts named as the suction side (SS) layout, camber line (CAM) layout and pressure side (PS) layout, three coolant mass flow rates and a relative casing movement. The results indicate that the area-averaged heat transfer coefficient (HTC) of PS layout is higher than that of CAM layout by 6.9% and that of SS layout by 5.7% when coolant flow rate equals to 0.6% mainstream flow rate. By comparison, it is clearly observed that the area of the high heat transfer coefficient regions are significantly enlarged when the flow rate of coolant is increased. With relative casing movement, a significant high HTC stripe parallel to the pressure side rim is formed. In the case of the PS layout, the heat transfer coefficient is reduced by 7.3% with the casing movement. While in the case of CAM layout and SS layout, the heat transfer coefficient increased by 4.8% and 2.3% with the casing movement, respectively. Detailed tip leakage flow patterns with three film cooling layouts are also illustrated.


Numerical Investigations on the Heat Transfer Performance of Transonic Squealer Tip With Different Film Cooling Layouts

Division / Sponsor:
International Gas Turbine Institute (IGTI)

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

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