Turbine shroud segment apparatus for reusing cooling air

F - Mech Eng,Light,Heat,Weapons – 01 – D

Patent

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Details

F01D 25/12 (2006.01) F01D 9/04 (2006.01) F01D 11/08 (2006.01)

Patent

CA 2509852

A cooled turbine shroud segment (12) for a gas turbine engine, having an axially extending shroud ring segment (18) with an inner surface (19), an outer surface (20) an upstream flange (21) and a downstream flange (22) . The flanges mount the shroud ring within an engine casing. A perforated cooling air impingement plate (23) is disposed on the outer surface of the shroud ring between the upstream flange (21) and the downstream flange (22) with an impingement plenum (24) defined between the impingement plate (23) and the outer surface (20) . Axially extending cooling bores (25) in the ring segment extend between the impingement plenum (24) and an outlet. A trough (27) adjacent the outlet directs cooling air from the outlet towards a downstream stator vane to cool the stator vane.

L'invention concerne un segment de l'anneau de cerclage d'une turbine refroidi (12) et destiné à une turbine à gaz, comprenant un segment d'anneau de renforcement s'étendant de manière axiale (18) et présentant une surface interne (19), une surface externe (20), un bord amont (21) et un bord aval (22). Les bords montent l'anneau de renforcement dans un carter réacteur. Un plateau de contact perforé d'air de refroidissement (23) est disposé sur la surface externe de l'anneau de renforcement entre le bord amont (21) et le bord aval (22), une chambre de tranquilisation à choc (24) étant définie entre le plateau de contact (23) et la surface externe (20). Des alésages de refroidissement s'étendant de manière axiale (25) dans le segment de l'anneau s'étendent entre la chambre de tranquilisation à choc (24) et un orifice d'évacuation. Une auge (27) adjacente à l'orifice d'évacuation dirige de l'air de refroidissement à partir de celui-ci vers une aube de stator aval, aux fins de refroidissement de celle-ci.

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