Turbine nozzle support

Details Turbine nozzle support Turbine nozzle support

F - Mech Eng,Light,Heat,Weapons

02

C

F02C 7/00 (2006.01) F01D 9/04 (2006.01) F01D 11/00 (2006.01)

Patent

CA 2070511

A gas turbine nozzle includes a plurality of nozzle segments having a pair of nozzle vanes supported by inner and outer shroud segments. Each inner shroud segment includes a circumferential retention slot and a radial retention slot in generally circumferential alignment and an interlocking tab and slot arrangement at the respective ends to provide engagement between adjacent flange segments. A 360 degree retention ring includes a plurality of circumferential retention tabs and radial retention tabs to engage respective ones of the plurality of flange segments to secure the nozzle segments in a circumferential ring about the outlet of a gas turbine combustor.

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