Computational Analysis on Gas Turbine Blade by Hole Modified for Optimization the Effectiveness

Author:

Kebir Farouk1

Affiliation:

1. Université des Sciences et de la Technologie d'Oran

Abstract

In order to reduce the operating costs of the engine, turbine designers must also increase the life of their components. However, high gas temperatures throughout the engine require more cooling air or better cooling efficiency to protect the parts from thermal damage. This study presents numerical research on cooling holes. Research focused on aerodynamics and thermal aspects of shallow whole angle. The numerical simulation is performed based on Reynolds Averaged Navier-Stokes (RANS) equations with SST turbulence model by using CFX. A modification has been done in the normal injection hole of 35°, by injecting the cold fluid at different blowing ratio, providing a significant change in the shape of holes which later we found in our numerical investigation giving good quality of film cooling effectiveness.

Publisher

Trans Tech Publications, Ltd.

Subject

General Chemical Engineering

Reference30 articles.

1. Bogard, D. G., and Thole, K. A., Gas Turbine Film Cooling.Journal of Propulsion and Power, vol. 22, Mar. (2006), p.249–270.

2. Bogard, D. G., Airfoil film cooling, The Gas Turbine Handbook, National Energy Technology Laboratory, (2006) Section 4.2.2.1.

3. Han, J., Dutta, S., and Ekkad, S., Gas turbine heat transfer and cooling technology, New York: CRC Press, (2000).

4. Goldstein, R., Film cooling, Advances in heat transfer Vol 7.1, (1971), p.321–379.

5. Bunker, R. S., A Review of Shaped Hole Turbine Film-Cooling Technology, Journal of Heat Transfer, vol. 127, (Apr. 2005), p.441.

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