Methods and system for cooling integral turbine shroud...

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

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F01D 25/14 (2006.01) F01D 25/28 (2006.01) F02C 7/18 (2006.01)

Patent

CA 2601686

A turbine shroud assembly (110) for a gas turbine engine is provided. The turbine shroud assembly includes a shroud segment (130) including a leading edge (133), a trailing edge (137) and a midsection defined therebetween, the shroud segment including a forward mounting hook (132) at the leading edge, a midsection mounting hook (134) at the midsection and an aft mounting hook (136) at the trailing edge, a shroud support (144) circumferentially spanning and supporting the shroud segment, the shroud support including a forward section (146), a midsection (148) and an aft section (150), the forward section forming a forward hanger (152) coupled to the forward mounting hook, the midsection forming a midsection hanger (154) coupled to the midsection mounting hook, the aft section forming an aft hanger (156) coupled to the aft mounting hook, an annular shroud ring structure (158) configured to support the shroud support, the annular shroud ring structure including a midsection position control ring (162) coupled to the midsection hanger and an aft position control ring (164) coupled to the aft hanger, a first active convection cooling zone (173) defined between the shroud segment and the shroud support and between the forward mounting hook and the midsection mounting hook, at least one feed hole (174) extending through the shroud support and configured to meter a first portion (171) of cooling air (170) into the first active convection cooling zone, and a first inactive convection cooling zone (211) defined between the shroud support and the annular shroud ring structure and between the midsection position control ring and the aft position control ring, the shroud support substantially preventing cooling air from entering the first inactive convection cooling zone.

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