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Tip Leakage Flow and Heat Transfer Predictions for Turbine Blades

[+] Author Affiliations
Dianliang Yang, Zhenping Feng

Xi’an Jiaotong University, Xi’an, Shaanxi, China

Paper No. GT2007-27728, pp. 589-596; 8 pages
  • ASME Turbo Expo 2007: Power for Land, Sea, and Air
  • Volume 4: Turbo Expo 2007, Parts A and B
  • Montreal, Canada, May 14–17, 2007
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 0-7918-4793-4 | eISBN: 0-7918-3796-3
  • Copyright © 2007 by ASME


A numerical study was performed to simulate the tip leakage flow and heat transfer on the first stage rotor blade in GE-E3 engines. Calculations were performed for both flat and squealer blade tips by means of solving Reynolds-averaged N-S equations in conjunction with the k-ω two-equation turbulence model. For squealer tip blades, several cases were considered with five different tip gap-blade span ratios of 0.4%, 0.7%, 1.0%, 1.3%, and 1.6%, and four different groove depth-blade span ratios of 1%, 2%, 3%, and 4%. A linear experimental cascade was calculated first to validate this turbulence model, and the results show good agreement with that of the experiment. With the results of several cases discussed and compared, flow structure and heat transfer characteristics in the tip gap are illustrated. The effects of the tip gap and groove depth on flow and heat transfer are significant. The leakage flow is weakened by deepening the tip groove. However, when the groove depth is larger than 3% of the blade span, no further leakage flow reduction will occur. The average heat transfer rate on the tip surface reduces as groove depth increases. An increase in tip gap height will increase the leakage flow, and thus lead to an increase in average heat transfer rate on the tip surface.

Copyright © 2007 by ASME



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