Abstract
Numerical calculation of conjugate heat transfer was carried out to study the effect of combined film and swirl cooling at the leading edge of a gas turbine vane with a cooling chamber inside. Two cooling chambers (C1 and C2 cases) were specially designed to generate swirl in the chamber, which could enhance overall cooling effectiveness at the leading edge. A simple cooling chamber (C0 case) was designed as a baseline. The effects of different cooling chambers were studied. Compared with the C0 case, the cooling chamber in the C1 case consists of a front cavity and a back cavity and two cavities are connected by a passage on the pressure side to improve the overall cooling effectiveness of the vane. The area-averaged overall cooling effectiveness of the leading edge () was improved by approximately 57%. Based on the C1 case, the passage along the vane was divided into nine segments in the C2 case to enhance the cooling effectiveness at the leading edge, and was enhanced by 75% compared with that in the C0 case. Additionally, the cooling efficiency on the pressure side was improved significantly by using swirl-cooling chambers. Pressure loss in the C2 and C1 cases was larger than that in the C0 case.
Highlights
Gas turbines are widely used in aero-propulsion system, ship power, and industrial power generation
Almost no work was done to use conjugate heat transfer models to investigate the overall cooling effectiveness of film-swirl cooling for a gas turbine vane
A numerical calculation of conjugate heat transfer (CHT) was carried out to study the effect of overall cooling incorporating film and swirl cooling at the leading edge of a gas turbine vane on the flow structure and heat transfer
Summary
Gas turbines are widely used in aero-propulsion system, ship power, and industrial power generation. The authors of [28,29] investigated the cooling performance of a turbine blade leading edge with a simplified three-dimensional vortex chamber structure and film holes, their work focused on swirl cooling effectiveness and adiabatic film cooling effectiveness, not overall cooling. Conjugate heat transfer models accurately predict overall cooling performance of gas turbine vane. Almost no work was done to use conjugate heat transfer models to investigate the overall cooling effectiveness of film-swirl cooling for a gas turbine vane. A numerical calculation of conjugate heat transfer (CHT) was carried out to study the effect of overall cooling incorporating film and swirl cooling at the leading edge of a gas turbine vane on the flow structure and heat transfer. The pressure loss due to designed cooling chambers was studied
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