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Leading Edge Cooling Performance of an Integrated Cooling Configuration

[+] Author Affiliations
Takahiro Bamba, Takao Kumagai, Fujio Mimura, Takashi Yamane, Yoshitaka Fukuyama

Japan Aerospace Exploration Agency, Tokyo, Japan

Taiki Usui, Toyoaki Yoshida

Tokyo University of Agriculture and Technology, Tokyo, Japan

Paper No. GT2008-50574, pp. 553-561; 9 pages
doi:10.1115/GT2008-50574
From:
  • ASME Turbo Expo 2008: Power for Land, Sea, and Air
  • Volume 4: Heat Transfer, Parts A and B
  • Berlin, Germany, June 9–13, 2008
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-4314-7 | eISBN: 0-7918-3824-2
  • Copyright © 2008 by ASME

abstract

This paper presents the experimental work on the leading edge cooling performance of an integrated impingement and pin-fin cooling configuration. Experiments are conducted for seven different spatial geometries under the simulated condition of 1400 degree Celsius-class actual turbine vane leading edge with the temperature ratio of 2.1. The Reynolds number of the hot gas side was 91000 and the cooling air Reynolds number was varied in the range of 5900–47000. The test piece surface temperature distributions were measured using an infrared camera with the correction by a thermocouple embedded on the test piece surface. The cooling effectiveness obtained from the experiments showed the superior cooling performance by the pin-fin integration. The effect of the cooling effectiveness enhancement was more than the cooling surface area increment. The detailed analyses of the cooling performance and the pressure loss characteristics are discussed.

Copyright © 2008 by ASME
Topics: Cooling

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