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Multi-Objective Optimization of the Cooling Configuration of a High Pressure Turbine Blade

[+] Author Affiliations
Frank Wagner, Arnold Kühhorn

Brandenburg University of Technology Cottbus-Senftenberg, Cottbus, Germany

Timm Janetzke, Ulf Gerstberger

Rolls-Royce Deutschland Ltd. & Co KG, Blankenfelde-Mahlow, Germany

Paper No. GT2018-75616, pp. V05CT20A001; 10 pages
doi:10.1115/GT2018-75616
From:
  • ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition
  • Volume 5C: Heat Transfer
  • Oslo, Norway, June 11–15, 2018
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-5110-4
  • Copyright © 2018 by Rolls-Royce Deutschland Ltd & Co KG

abstract

Due to the increasing turbine inlet temperature and in order to improve the overall efficiency it is necessary to optimize the cooling design of the hot gas components of an aero engine.

The current paper discusses the strategy of optimizing a rotor blade cooling configuration of a small civil aero engine, comprising of films and internal turbulators (ribs). An insight into the parametrization is given including the location of the films and ribs as well as the number of the films and ribs. The parameter reduction results in 18 input parameters for the optimizations to limit the number of parameters to an acceptable level.

Two optimizations are carried out with the primary objectives of non-dimensional mass flow and overall cooling effectiveness. Different optimization algorithms are used, namely AMGA and NSGA-II, and compared afterwards. A further optimization is carried out with direct objectives of mass flow and mean surface temperature using the AMGA algorithm.

The outputs from the optimizations are presented as a pareto-front. These plots are used for a comparison of the optimization algorithms and formulations respectively. Finally, the differences are discussed and the advantages and disadvantages of the algorithms used are highlighted.

Copyright © 2018 by Rolls-Royce Deutschland Ltd & Co KG

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