Stationary blade of gas turbine

Details Stationary blade of gas turbine Stationary blade of gas turbine

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 9/02 (2006.01) F01D 5/18 (2006.01) F01D 11/04 (2006.01) F02C 7/16 (2006.01)

Patent

CA 2263576

In a stationary blade of a gas turbine, the pressure resisting strength can be decreased by using low-pressure cooling air, and effective cooling can be performed by means of a simple construction. An inside shroud 1 and an outside shroud 2 are cooled by cooling air passing through an impingement plate. A trailing edge portion of a blade portion 6, which is thin in shape, is cooled by cooling air flowing in an air passage 10. Part of this air is discharged through a hole 12 on the side of the inside shroud 1 as inside seal air for a combustion gas passage.

L'invention concerne une aube fixe de turbine à gaz, de construction simple, capable d'assurer un refroidissement efficace dans un état où de l'air de refroidissement sous faible pression atténue une force de résistance à la pression. Un anneau intérieur (1) et un anneau extérieur (3) sont refroidis par de l'air de refroidissement, qui traverse un plateau de contact, et une extrémité arrière de partie d'aube (6) à configuration mince est refroidie par de l'air de refroidissement, lequel passe par un conduit d'air (10). Une partie de cet air est évacuée, en guise d'air isolant pour un conduit de gaz de combustion, depuis un orifice (12) placé sur un côté de l'anneau intérieur (1).

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