Dynamic and Thermodynamic Analysis of Film-Cooling

Nor Azwadi Che Sidik(1*), Ehsan Kianpour(2), Iman Golshokouh(3)

(1) Keio University, Japan
(2) Malek Ashtar University of Technology, Iran, Islamic Republic of
(3) Khuzestan Azad University, Iran, Islamic Republic of
(*) Corresponding author


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Abstract


This study was done to extend database knowledge about the film cooling action at the end of combustor and inlet of turbine. The well-known Brayton cycle plays a key role to get higher engine efficiency in gas turbine engines. But the high temperature of the combustor exit flow creates unpleasant environment. These surroundings lead to a reduction in the expected life of critical parts. There are two separate ways for Gas turbine cooling: internal cooling and external cooling. Film cooling is one of the most effective external cooling methods. In this system, a low temperature thin boundary layer such as buffer zone is formed and attached on the protected surface. In this study, a literature survey was done on the limited surveys that considered the effects of flow structure variations on film cooling, particularly from the first of 21th century.
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Keywords


Gas Turbine Engine; Combustor; Film Cooling; Cooling Holes; Turbine Vanes

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References


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