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Measurement and Modelling of Blade Tip Cooling in Gas Turbines

[+] Author Affiliations
Julio Teloxa, F. Z. Sierra, Francisco Carrillo

Universidad Autónoma del Estado de Morelos, Cuernavaca, MOR, México

Diganta Narzary, Je-Chin Han

Texas A&M University, College Station, TX

Jiang Lei

Xi’an Jiaotong University, Xi’an, Shaanxi, China

Paper No. GT2013-94812, pp. V03BT13A034; 10 pages
doi:10.1115/GT2013-94812
From:
  • ASME Turbo Expo 2013: Turbine Technical Conference and Exposition
  • Volume 3B: Heat Transfer
  • San Antonio, Texas, USA, June 3–7, 2013
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-5515-7
  • Copyright © 2013 by ASME

abstract

Blade tip cooling effectiveness simulations and measurements are reported. Measurements of metal blade surface temperature distributions were obtained in the laboratory using temperature sensitive paint technique, TSP, for mainstream Reynolds number, ReM = 200,000, and cooling Reynolds number, ReC = 10,000. The blade tip region consists of a cavity with thin walls on pressure and suction sides known as squealer rim. TSP technique is used to investigate the temperature demonstrating its applicability as cooling effectiveness measurement method on a blade tip region. Several film cooling holes placed along the airfoil camber line discharge coolant and spread over the tip cavity. Besides, conjugate cooling flow was numerically simulated, considering blade metal and mainstream contact under the effects of leakage through blade tip clearance using a finite volume program, Fluent, with good agreement between data and numerical results. Cooling effectiveness is investigated as function of blowing ratio and tip clearance.

Copyright © 2013 by ASME

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