Universal Journal of Mechanical Engineering Vol. 1(4), pp. 122 - 127
DOI: 10.13189/ujme.2013.010403
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Effect of Pressure Ratio on Film Cooling of Turbine Aerofoil Using CFD

Vibhor Baghel ¹, Sunil Chandel ^1,*, R. Sivasankara Reddy ^2
1 Mechanical Engg Dept, DIAT (DU), Pune, India
² Sc ‘F’, Gas Turbine Research Establishment, Bangalore, India

ABSTRACT

Gas turbine blades are cooled internally and externally and one widely used blade cooling technique is film cooling. In this type of cooling, relatively cool air is injected from the inside of the blade to the outside surface which forms a protective layer between the blade surface and hot gas streams. The present study is an attempt to establish the effect of blowing ratio and pressure ratio numerically on film cooling effectiveness in a typical nozzle guide vane with single hole on both pressure and suction surface of the vane. The commercially available CFD code “FLUENT” has been used after validating it against the experimental results reported in literature. Pressure ratio was varied from 1.1 to 1.2 with density ratio 2.0. Results obtained from the numerical investigation show that with increase in pressure ratio at constant blowing ratio, there was an increase in film cooling effectiveness. It is found that film spread is more on the pressure side as compared to suction side.

KEYWORDS
Film cooling, Blowing ratio, Pressure ratio, CFD

Cite This Paper in IEEE or APA Citation Styles
(a). IEEE Format:
[1] Vibhor Baghel , Sunil Chandel , R. Sivasankara Reddy , "Effect of Pressure Ratio on Film Cooling of Turbine Aerofoil Using CFD," Universal Journal of Mechanical Engineering, Vol. 1, No. 4, pp. 122 - 127, 2013. DOI: 10.13189/ujme.2013.010403.

(b). APA Format:
Vibhor Baghel , Sunil Chandel , R. Sivasankara Reddy (2013). Effect of Pressure Ratio on Film Cooling of Turbine Aerofoil Using CFD. Universal Journal of Mechanical Engineering, 1(4), 122 - 127. DOI: 10.13189/ujme.2013.010403.