Patent ID: 6568903
Filing Date: 2003-05-27
Classification: F01D,F02C,F16J

Abstract:
A gas turbine comprising:a turbine nozzle support ring having a generally axially facing first surface; a turbine nozzle segment having at least one stator vane and including an inner band having a second surface in axial opposition to said first surface; said support ring and a portion of said inner band of said segment defining a cavity generally radially outwardly of said first surface and in part defined by generally axially extending radially opposed surfaces of said support ring and said inner band; and a flexible seal in said cavity including a seal body having a first portion extending between said first and second surfaces and second and third portions engageable with the radially opposed surfaces, respectively, to seal between high and low pressure regions on opposite sides of the axially registering first and second surfaces of said support ring and said inner band.