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Experimental Study on the Heat Transfer in the Compound Cooling Passage

[+] Author Affiliations
Li Li, Shui-Ting Ding, Guo-Qiang Xu, Zhi Tao, Hong-Wu Deng

Beijing University of Aeronautics and Astronautics, Beijing, China

Paper No. GT2006-90250, pp. 241-247; 7 pages
doi:10.1115/GT2006-90250
From:
  • ASME Turbo Expo 2006: Power for Land, Sea, and Air
  • Volume 3: Heat Transfer, Parts A and B
  • Barcelona, Spain, May 8–11, 2006
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 0-7918-4238-X | eISBN: 0-7918-3774-2
  • Copyright © 2006 by ASME

abstract

An experimental study was carried out to comprehend the passage configuration for better the cooling effectiveness on the trailing edge of high-pressure turbine blade. Thermochromic liquid crystal technology was employed to measure the endwall temperature of the trapezoidal compound passage and the resistance coefficients of the internal ducts. It can be concluded that the configuration with suitable ejection holes in the divider wall can get higher heat transfer coefficient of the compound passage than that of the tradition configuration with a straight divider wall which form a sharp turn. This is because the spanwise impinging jets flowing through the orifices distributed at the radial orientation in the divider wall between the first passage and the second one, can improve the heat transfer of a certain low heat transfer region. Better effectiveness of heat transfer could be obtained when the straight divider wall was designed into zigzag divider wall.

Copyright © 2006 by ASME

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