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Aero-Thermal Coupled Throughflow Method With Cooling Model Based on Flow Network Analysis

[+] Author Affiliations
Wei Ba, Xiaodong Ren

Tsinghua University, Beijing, China

Paper No. GT2017-63614, pp. V02BT41A021; 12 pages
  • ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition
  • Volume 2B: Turbomachinery
  • Charlotte, North Carolina, USA, June 26–30, 2017
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-5079-4
  • Copyright © 2017 by ASME


The aero-thermal coupled phenomenon is significant in the modern cooled turbine, and it is necessary to consider the cooling effect in the throughflow design phase. A new cooling model based on flow network analysis for the aero-thermal coupled throughflow method was developed to consider the film cooling effect and predict the blade wall temperature downstream of the film cooling holes. The flow network analysis is introduced into the cooling model to determine the flow rate of each cooling hole. The mixing loss caused by film cooling is investigated as local total pressure loss, and the heat transfer influence caused by film cooling is considered by the film cooling effectiveness estimated by empirical correlation. The blade heat transfer downstream the film cooling holes is calculated from pressure and suction surfaces separately, based on main flow parameters calculated by the streamline curvature method. The experimental data of the C3X profile is selected for the cooling model verification. The film cooling flow rate calculated by the flow network analysis agrees well with the experimental data, and the calculated temperatures of both the pressure and suction surfaces downstream the film cooling holes are also in accordance with the experimental data. Therefore, aero-thermal coupled throughflow method with this cooling model can be a powerful tool for preliminary design of cooled turbine.

Copyright © 2017 by ASME



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