Contours of heat transfer coefficient and effectiveness have been measured on the tip of a generic cooled turbine blade, using the transient liquid crystal technique. The experiments were conducted at an exit Reynolds number of 2.3 × 105 in a five-blade linear cascade with tip clearances of 1.6% and 2.8% chord and featuring engine-representative cooling geometries. These experiments were supported by oil flow visualisation and pressure measurements on the tip and casing and by flow visualisation calculated using CFX, all of which provided insight into the fluid dynamics within the gap. The data were compared with measurements taken from the uncooled tip gap, where the fluid dynamics is dominated by flow separation at the pressure-side edge. Here the highest levels of heat transfer are located where the flow reattaches on the tip surface downstream of the separation bubble. A quantitative assessment using the Net Heat Flux Reduction (NHFR) revealed a significant benefit of ejecting coolant inside this separation bubble. Engine-representative blowing rates of approximately 0.6 – 0.8 resulted in good film cooling coverage and a reduction in heat flux to the tip when compared to both the flat tip profile and the squealer and cavity tip geometries discussed in Part 1 of this paper. Of the two novel coolant-hole configurations studied, injecting the coolant inside the separation bubble resulted in an improved NHFR when compared to injecting coolant at the location of reattachment.
Aero-Thermal Investigation of Tip Leakage Flow in Axial Flow Turbines: Part III — Tip Cooling
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Newton, PJ, Lock, GD, Krishnababu, SK, Hodson, HP, Dawes, WN, Hannis, J, & Whitney, C. "Aero-Thermal Investigation of Tip Leakage Flow in Axial Flow Turbines: Part III — Tip Cooling." Proceedings of the ASME Turbo Expo 2007: Power for Land, Sea, and Air. Volume 4: Turbo Expo 2007, Parts A and B. Montreal, Canada. May 14–17, 2007. pp. 317-327. ASME. https://doi.org/10.1115/GT2007-27368
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