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Effects of Inlet Swirl on Pressure Side Film Cooling of Neighboring Vane Surface

[+] Author Affiliations
Yifei Li, Yang Zhang, Xin Yuan

Tsinghua University, Beijing, China

Paper No. GT2016-57527, pp. V05CT19A026; 13 pages
doi:10.1115/GT2016-57527
From:
  • ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition
  • Volume 5C: Heat Transfer
  • Seoul, South Korea, June 13–17, 2016
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-4980-4
  • Copyright © 2016 by ASME

abstract

The test cascades are based on the profile of General Electric Energy Efficient Engine (GE-E3) with the inlet Mach number of 0.1 and Reynolds number of 1.48×105. The scale ratio of the test vanes is 1.95 and the film cooling effectiveness is tested with Pressure Sensitive Painting (PSP) technology. Nitrogen is used to simulate the coolant which can provide a density ratio near to 1.0. The two adjacent passages are investigated simultaneously by which the film cooling effectiveness can be compared in the same case with pressure side and suction side respectively. The rotating flow is simulated by an upstream swirler at the inlet, fixed at 5 different positions along the pitchwise direction at the inlet. They are Blade 1 aligned, Passage 1 aligned, Blade 2 aligned, Passage 2 aligned and Blade 3 aligned. According to the experimental results, the inlet rotating flow can dominate the film cooling effectiveness distribution at Pressure Side. The averaged film cooling effectiveness changes significantly with the change in swirler position. The effect of the rotating flow at the Pressure Side region is mainly interacted with the main flow to cause the change in incidence angle. The influence of the inlet rotating flow is more obvious on the pressure side upstream part. Meanwhile the downstream part is not so sensitive to rotating flow as pressure side.

Copyright © 2016 by ASME

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