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Film Cooling for Slot Injection in Separated Flows

[+] Author Affiliations
Y. Okita, C. Nakamata

Ishikawajima-Harima Heavy Industries, Tokyo, Japan

H. Kamiya, M. Kumada

Gifu University, Gifu, Japan

Paper No. GT2005-68119, pp. 207-215; 9 pages
doi:10.1115/GT2005-68119
From:
  • ASME Turbo Expo 2005: Power for Land, Sea, and Air
  • Volume 3: Turbo Expo 2005, Parts A and B
  • Reno, Nevada, USA, June 6–9, 2005
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 0-7918-4726-8 | eISBN: 0-7918-3754-8
  • Copyright © 2005 by ASME

abstract

This experimental work is to investigate film cooling for slot injection in separated flows. The purpose of this research is to study the feasibility of a highly loaded very thin turbine blade which has been devised in order to reduce weight and to save the coolant amount by simplifying the complicated internal cooling passages. With such a thin airfoil, a considerable flow separation is expected to occur on the pressure-side and film cooling practice in that kind of flow field has not been well established. In order to clarify the film cooling mechanism in the separated flows, experiments with a simple back-facing step flow with a single slot injection simulating the separated pressure-side flows were carried out. Very high lip thickness to slot height ratio up to 8 was considered. Adiabatic effectiveness as well as velocity and turbulence profiles downstream of the step was measured in detail. The experimental results showed that there is a clear improvement in the film effectiveness with the largest lip thickness case for whole range of the tested blowing ratio. The flow field measurements suggested that a large recirculation zone acted as buffer or resistance for flow mixing, which contributed to the improvement in the film effectiveness.

Copyright © 2005 by ASME

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