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Numerical Investigation of Fluid Flow and Heat Transfer in a Turbine Blade With Serpentine Passage and Latticework Cooling

[+] Author Affiliations
Sheng Su, Jian-Jun Liu, Jing-Lun Fu, Jie Hu, Bai-Tao An

Chinese Academy of Sciences, Beijing, China

Paper No. GT2008-50392, pp. 383-391; 9 pages
doi:10.1115/GT2008-50392
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 describes 3D numerical simulations of a turbine rotor blade with complex internal cooling structure. Conjugate heat transfer method is used to get an accurate blade temperature distribution. The cooling structure consists of a rib roughened serpentine channel near the leading edge, latticework cooling channels in the middle part and slots at the trailing edge. Both the rib roughened channel and the latticework cooling channels can enhance the heat transfer. Furthermore, the latticework cooling channels can enhance the blade strength. Different cooling structures are simulated and analyzed, including changing the configuration of the latticework cooling channels, and whether to apply two holes to the blade tip or not. The effects of different internal cooling configurations are as follows. Firstly, blade temperature distribution is highly disordered: low temperature at the U turning of the serpentine passage, medium temperature at the location of latticework in a relatively uniform distribution, and a few hot spots on the trailing edge. Secondly, tip holes can improve the cooling in serpentine passage by improving fluid flow at the U turning with a negative impact on the cooling of latticework and trailing edge slots. Thirdly, smaller width to height ratio of the sub passage in latticework channels increases coolant flow resistance and leads to an improved latticework cooling with also a negative impact on the cooling of trailing edge slots.

Copyright © 2008 by ASME

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