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Film cooling for a closed loop cooled airfoil

United States Patent

January 14, 2003
View the Complete Patent at the US Patent & Trademark Office
Turbine stator vane segments have radially inner and outer walls with vanes extending therebetween. The inner and outer walls are compartmentalized and have impingement plates. Steam flowing into the outer wall plenum passes through the impingement plate for impingement cooling of the outer wall upper surface. The spent impingement steam flows into cavities of the vane having inserts for impingement cooling the walls of the vane. The steam passes into the inner wall and through the impingement plate for impingement cooling of the inner wall surface and for return through return cavities having inserts for impingement cooling of the vane surfaces. At least one film cooling hole is defined through a wall of at least one of the cavities for flow communication between an interior of the cavity and an exterior of the vane. The film cooling hole(s) are defined adjacent a potential low LCF life region, so that cooling medium that bleeds out through the film cooling hole(s) reduces a thermal gradient in a vicinity thereof, thereby the increase the LCF life of that region.
Burdgick; Steven Sebastian (Schenectady, NY), Yu; Yufeng Phillip (Simpsonville, SC), Itzel; Gary Michael (Simpsonville, SC)
General Electric Company (Schenectady, NY)
09/ 561,865
April 28, 2000
This invention was made with Government support under Government contract No. DE-FC21-95-MC31176 awarded by the Department of Energy. The Government has certain rights in this invention.