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Title: Gas turbine vane cooling system

Abstract

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.

Inventors:
;
Publication Date:
OSTI Identifier:
27700
Patent Number(s):
US 5,394,687/A/
Application Number:
PAN: 8-161,032
Assignee:
Dept. of Energy, Washington, DC (United States)
Resource Type:
Patent
Resource Relation:
Other Information: PBD: 7 Mar 1995
Country of Publication:
United States
Language:
English
Subject:
42 ENGINEERING NOT INCLUDED IN OTHER CATEGORIES; GAS TURBINES; VANES; COOLING; HEAT RECOVERY; COOLING SYSTEMS; DESIGN; AIR HEATERS; THERMAL EFFICIENCY; OPTIMIZATION; OPERATION

Citation Formats

Chen, A G, and McQuiggan, G G. Gas turbine vane cooling system. United States: N. p., 1995. Web.
Chen, A G, & McQuiggan, G G. Gas turbine vane cooling system. United States.
Chen, A G, and McQuiggan, G G. 1995. "Gas turbine vane cooling system". United States.
@article{osti_27700,
title = {Gas turbine vane cooling system},
author = {Chen, A G and McQuiggan, G G},
abstractNote = {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.},
doi = {},
url = {https://www.osti.gov/biblio/27700}, journal = {},
number = ,
volume = ,
place = {United States},
year = {1995},
month = {3}
}