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Experimental Study of Leakage Flow on Flow Field and Film Cooling of High Pressure Turbine Blade Platform

[+] Author Affiliations
Kenichiro Takeishi

Tokushima Bunri University, Sanuki, Kagawa, Japan

Yutaka Oda

Kansai University, Suita, Osaka, Japan

Shintaro Kozono

Fuji Heavy Industries Ltd., Mitaka, Tokyo, Japan

Paper No. GT2015-42898, pp. V05BT12A026; 13 pages
doi:10.1115/GT2015-42898
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 ASME

abstract

An experiment has been conducted to study stator/rotor disc cavity leakage flow on the platform of a highly loaded stationary linear blade cascade. The linear cascade consists of a scaled-up model of the high-pressure turbine blades of an E3 (Energy efficient engine) and leakage slot models installed under the platform. Experiments have been conducted to investigate the effect of the slot injection angle, leakage flow rates, distance between the leading edge of the blade and the slot, and spacing of the blades. The film-cooling effectiveness was measured by pressure sensitive paint (PSP), and the temperature fields and flow fields were investigated using laser-induced fluorescence (LIF) and particle image velocimetry (PIV), respectively. It was observed from the experiments that the leakage flow covered the surface of the blade platform when the distance between the leading edge and the slot was zero; however, with increasing distance, the horseshoe vortex dominates near the junction of the blade leading edge, and the leakage flow could not cover the region. It was also found that the leakage flow has an effect that promotes the formation of the horseshoe vortex for some experimental conditions.

Copyright © 2015 by ASME

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