Researchers in gas turbine field take great interest in the cooling performance on the first-stage vane because the complex flow characteristics and intensive heat load that comes from the exit of the combustion chamber. A better understanding is needed on how the coolant flow interacts with the mainstream and the resulting cooling effect in the real engine especially for the first-stage vane. An authentic flow channel and condition should be achieved. In this study, three full-scale turbine vanes are used to construct an annular-sector cascade. The film-cooling design is attained through numerous layback fan-shaped and cylindrical holes dispersed on the vane and both end-walls. With the three-dimensional vane geometry and corresponding wind tunnel design, the true flow field can thus be simulated as in the engine. This study targets the film-cooling effectiveness on the inner end-wall (hub) of turbine vane. Tests are performed under the mainstream Reynolds number 3.5 × 105; the related inlet Mach number is 0.09 and the free stream turbulence intensity is 8%. Two variables, coolant-to-mainstream mass flow ratios (MFR = 2%, 3%, 4%) and density ratios (DR = 1.0, 1.5) are examined. Pressure-sensitive paint (PSP) technique is utilized to capture the detail contour of film-cooling effectiveness on the inner end-wall and demonstrate the coolant trace. The presented results serve a comparison basis for other sets of vanes with different cooling designs. The results are expected to strengthen the promise of PSP technique on evaluating the film-cooling performance of the engine geometries.
Full-Scale Turbine Vane End-Wall Film-Cooling Effectiveness Distribution Using PSP Technique
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Shiau, C, Chen, AF, Han, J, Azad, S, & Lee, C. "Full-Scale Turbine Vane End-Wall Film-Cooling Effectiveness Distribution Using PSP Technique." Proceedings of the ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. Volume 5B: Heat Transfer. Montreal, Quebec, Canada. June 15–19, 2015. V05BT12A007. ASME. https://doi.org/10.1115/GT2015-42206
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