Optimization of film cooling holes on the suction surface of a high pressure turbine blade

Carole El Ayoubi, Wahid Ghaly, Ibrahim Hassan

Research output: Chapter in Book/Report/Conference proceedingConference contribution

5 Citations (Scopus)

Abstract

This paper aims to optimize film coolant flow parameters on the suction surface of a high-pressure gas turbine blade in order to obtain an optimum compromise between a high film cooling effectiveness and a low aerodynamic loss. An optimization algorithm coupled with three-dimensional Reynolds-averaged Navier Stokes (RANS) analysis is used to determine the optimum film cooling configuration. The VKI blade with two staggered rows of axially oriented, conically flared, film cooling holes on its suction surface is considered. Two design variables are selected; the coolant to mainstream temperature ratio and total pressure ratio. The effect of varying these coolant flow parameters on the film cooling effectiveness and the aerodynamic loss is analyzed using an optimization method and three dimensional steady CFD simulations. The optimization process involves a genetic algorithm and a response surface approximation of the artificial neural network type to provide low-fidelity predictions of the objective function. The CFD simulations are performed using the commercial software CFX. The numerical predictions of the aerodynamics and wall heat transfer are validated against experimental data. The optimization objective consists of maximizing the spatially averaged film cooling effectiveness and minimizing the aerodynamic penalty produced by film cooling. The results of this optimization are reported in terms of the aerodynamic loss and adiabatic cooling effectiveness.

Original languageEnglish
Title of host publicationASME Turbo Expo 2012: Turbine Technical Conference and Exposition, GT 2012
Pages1683-1693
Number of pages11
Volume4
EditionPARTS A AND B
DOIs
Publication statusPublished - 2012
Externally publishedYes
EventASME Turbo Expo 2012: Turbine Technical Conference and Exposition, GT 2012 - Copenhagen, Denmark
Duration: 11 Jun 201215 Jun 2012

Other

OtherASME Turbo Expo 2012: Turbine Technical Conference and Exposition, GT 2012
CountryDenmark
CityCopenhagen
Period11/6/1215/6/12

Fingerprint

Turbomachine blades
Turbines
Cooling
Aerodynamics
Coolants
Computational fluid dynamics
Gas turbines
Genetic algorithms
Neural networks

ASJC Scopus subject areas

  • Engineering(all)

Cite this

El Ayoubi, C., Ghaly, W., & Hassan, I. (2012). Optimization of film cooling holes on the suction surface of a high pressure turbine blade. In ASME Turbo Expo 2012: Turbine Technical Conference and Exposition, GT 2012 (PARTS A AND B ed., Vol. 4, pp. 1683-1693) https://doi.org/10.1115/GT2012-69773

Optimization of film cooling holes on the suction surface of a high pressure turbine blade. / El Ayoubi, Carole; Ghaly, Wahid; Hassan, Ibrahim.

ASME Turbo Expo 2012: Turbine Technical Conference and Exposition, GT 2012. Vol. 4 PARTS A AND B. ed. 2012. p. 1683-1693.

Research output: Chapter in Book/Report/Conference proceedingConference contribution

El Ayoubi, C, Ghaly, W & Hassan, I 2012, Optimization of film cooling holes on the suction surface of a high pressure turbine blade. in ASME Turbo Expo 2012: Turbine Technical Conference and Exposition, GT 2012. PARTS A AND B edn, vol. 4, pp. 1683-1693, ASME Turbo Expo 2012: Turbine Technical Conference and Exposition, GT 2012, Copenhagen, Denmark, 11/6/12. https://doi.org/10.1115/GT2012-69773
El Ayoubi C, Ghaly W, Hassan I. Optimization of film cooling holes on the suction surface of a high pressure turbine blade. In ASME Turbo Expo 2012: Turbine Technical Conference and Exposition, GT 2012. PARTS A AND B ed. Vol. 4. 2012. p. 1683-1693 https://doi.org/10.1115/GT2012-69773
El Ayoubi, Carole ; Ghaly, Wahid ; Hassan, Ibrahim. / Optimization of film cooling holes on the suction surface of a high pressure turbine blade. ASME Turbo Expo 2012: Turbine Technical Conference and Exposition, GT 2012. Vol. 4 PARTS A AND B. ed. 2012. pp. 1683-1693
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