Gas turbine vane cooling system
A cooling system for stationary vanes in the turbine section of a gas turbine is described. Combustors for the turbine are disposed in a chamber that receives compressed air from a compressor section. This compressed air forms both combustion air and cooling air. The cooling air portion of the compressed air is recirculated through the vanes by bleeding it from the chamber and further pressurizing it, after which it flows through a cooling air flow path in the vanes, thereby resulting in the cooling of the vanes and the heating of the air. The heated air is then returned to the chamber where it mixes with the incoming combustion air, thereby giving up a portion of the heat transferred from the vane to the combustion air. As a result, the temperature of the combustion air is increased, thereby increasing the thermodynamic efficiency of the gas turbine. The cooling scheme provides cooling to the vane inner and outer shrouds, as well as the airfoil, by means of circumferentially extending holes in the shrouds that connect with a cooling air cavity in the airfoil. 5 figs.
- Assignee:
- Dept. of Energy, Washington, DC (United States)
- Patent Number(s):
- US 5,394,687/A/
- Application Number:
- PAN: 8-161,032
- OSTI ID:
- 27700
- Resource Relation:
- Other Information: PBD: 7 Mar 1995
- Country of Publication:
- United States
- Language:
- English
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