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Full-Scale Turbine Vane End-Wall Film-Cooling Effectiveness Distribution Using PSP Technique

[+] Author Affiliations
Chao-Cheng Shiau, Andrew F. Chen, Je-Chin Han

Texas A&M University, College Station, TX

Salam Azad, Ching-Pang Lee

Siemens Energy, Inc., Orlando, FL

Paper No. GT2015-42206, pp. V05BT12A007; 13 pages
doi:10.1115/GT2015-42206
From:
  • ASME Turbo Expo 2015: Turbine Technical Conference and Exposition
  • Volume 5B: Heat Transfer
  • Montreal, Quebec, Canada, June 15–19, 2015
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-5672-7
  • Copyright © 2015 by Siemens Energy, Inc.

abstract

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.

Copyright © 2015 by Siemens Energy, Inc.

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