Computational study of the effects of shock waves on film cooling effectiveness

Chad X Z Zhang, Ibrahim Hassan

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

Abstract

The performance of a louver cooling scheme on a transonic airfoil has been studied numerically in this paper. Film cooling holes are located near the passage throat. The Mach number at the location of the jet exit is close to unity. A comparison of film cooling effectiveness between numerical prediction and experimental data for a circular hole shows that the numerical procedures are adequate. In addition to the shock wave effects and compressibility, curvature effect was also studied by comparing cooling effectiveness on the airfoil surface with that on a flat plate. Substantially higher cooling effectiveness for the louver cooling scheme on the airfoil was predicted at blowing ratios below 1 in comparison to other cooling configurations. At higher blowing ratios than 2 the advantages of the louver cooling scheme becomes less obvious. It was also found that for the same cooling configuration the cooling effectiveness on the transonic airfoil is slightly higher than that on a flat plate at moderately low blowing ratios below 1. At high blowing ratios above 2 when the oblique shock becomes detached from the leading edge of the hole exits, dramatic reduction in cooling effectiveness occurs as a result of boundary layer separation due to the strong shock waves. A coolant-blockage and shaped-wedge analogy was proposed and found to be able to qualitatively explain this phenomenon satisfactorily.

Original languageEnglish
Title of host publicationProceedings of the ASME Turbo Expo 2009: Power for Land, Sea and Air
Pages855-866
Number of pages12
Volume7
EditionPART B
DOIs
Publication statusPublished - 2009
Externally publishedYes
Event2009 ASME Turbo Expo - Orlando, FL, United States
Duration: 8 Jun 200912 Jun 2009

Other

Other2009 ASME Turbo Expo
CountryUnited States
CityOrlando, FL
Period8/6/0912/6/09

Fingerprint

Shock waves
Cooling
Blow molding
Airfoils
Wave effects
Compressibility
Coolants
Mach number
Boundary layers

ASJC Scopus subject areas

  • Engineering(all)

Cite this

Zhang, C. X. Z., & Hassan, I. (2009). Computational study of the effects of shock waves on film cooling effectiveness. In Proceedings of the ASME Turbo Expo 2009: Power for Land, Sea and Air (PART B ed., Vol. 7, pp. 855-866) https://doi.org/10.1115/GT2009-59279

Computational study of the effects of shock waves on film cooling effectiveness. / Zhang, Chad X Z; Hassan, Ibrahim.

Proceedings of the ASME Turbo Expo 2009: Power for Land, Sea and Air. Vol. 7 PART B. ed. 2009. p. 855-866.

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

Zhang, CXZ & Hassan, I 2009, Computational study of the effects of shock waves on film cooling effectiveness. in Proceedings of the ASME Turbo Expo 2009: Power for Land, Sea and Air. PART B edn, vol. 7, pp. 855-866, 2009 ASME Turbo Expo, Orlando, FL, United States, 8/6/09. https://doi.org/10.1115/GT2009-59279
Zhang CXZ, Hassan I. Computational study of the effects of shock waves on film cooling effectiveness. In Proceedings of the ASME Turbo Expo 2009: Power for Land, Sea and Air. PART B ed. Vol. 7. 2009. p. 855-866 https://doi.org/10.1115/GT2009-59279
Zhang, Chad X Z ; Hassan, Ibrahim. / Computational study of the effects of shock waves on film cooling effectiveness. Proceedings of the ASME Turbo Expo 2009: Power for Land, Sea and Air. Vol. 7 PART B. ed. 2009. pp. 855-866
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