Sealing and cooling at the joint between shroud segments

Details Sealing and cooling at the joint between shroud segments Sealing and cooling at the joint between shroud segments

F - Mech Eng,Light,Heat,Weapons

02

C

F02C 7/28 (2006.01) F01D 25/14 (2006.01) F01D 25/24 (2006.01) F02C 7/12 (2006.01)

Patent

CA 2712113

A gas turbine engine shroud includes a plurality of shroud segments disposed circumferentially one adjacent to another to form a full, circumferentially segmented ring about the rotor. The radial seal between each pair of adjacent shroud segments is positioned on the back side of the shroud platform. Cooling underneath the radial seals may be done by conduction heath transfer through the platform of the shroud segments.

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