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Automated Design Space Exploration of Advanced-Shaped Film Cooling Holes Using the SHERPA Algorithm

[+] Author Affiliations
Karsten Kusterer, Jens Dickhoff, Noël T. Campana, Takao Sugimoto

B&B-AGEMA, Aachen, Germany

Ryozo Tanaka, Masahide Kazari

Kawasaki Heavy Industries, Ltd., Akashi, Japan

Dieter Bohn

RWTH Aachen University, Aachen, Germany

Paper No. GT2016-56194, pp. V05CT12A004; 11 pages
doi:10.1115/GT2016-56194
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

In modern gas turbines, the film cooling technology is essential for the protection of hot parts. Today, shaped holes are widely used, but besides others, the NEKOMIMI-shaped cooling holes have shown that there is still potential to increase the film cooling effectiveness significantly by generation of Anti-Counter-Rotating Vortices (ACRV). As a result, the cooling air remains close to the wall and spreads in lateral direction along the surface. The ACRV result from the specialized shape of the expanding hole exits (NEKOMIMI-shape). Thus, the design parameters have a crucial impact to the film cooling effectiveness behind the hole.

In the present study the design parameters are varied and in order to explore the design space for a defined test case with respect to the maximum achievable averaged adiabatic film cooling effectiveness. This illustrates the capabilities of the technology. Additionally, the design space of a laidback fan-shaped film cooling configuration is explored and compared to the result obtained with the NEKOMIMI-shaped geometry. In order to show the robustness of the configurations with respect to compound angles of the cross flow, two advanced configurations — one NEKOMIMI and one shaped hole — are analysed with compound angles up to 16°.

Copyright © 2016 by ASME

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