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

C. X Z Zhang, Ibrahim Hassan

Research output: Contribution to journalArticle

9 Citations (Scopus)

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 become 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 similarity was proposed and found to be able to qualitatively explain this phenomenon satisfactorily.

Original languageEnglish
Article number031901
JournalJournal of Engineering for Gas Turbines and Power
Volume131
Issue number3
DOIs
Publication statusPublished - May 2009
Externally publishedYes

Fingerprint

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

Keywords

  • CFD
  • Film cooling
  • Flow past a wedge
  • Gas turbines
  • Louver cooling scheme
  • Shaped holes
  • Shockwave reflection
  • Transonic airfoil

ASJC Scopus subject areas

  • Nuclear Energy and Engineering
  • Fuel Technology
  • Aerospace Engineering
  • Energy Engineering and Power Technology
  • Mechanical Engineering

Cite this

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

In: Journal of Engineering for Gas Turbines and Power, Vol. 131, No. 3, 031901, 05.2009.

Research output: Contribution to journalArticle

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