Patent ID: 8827637
Filing Date: 2014-09-09
Classification: F01D,F16J

Abstract:
1. A seal arrangement for a gas turbine engine, the seal arrangement comprising: a stationary housing structure having an axis, a seal support mounted to the stationary housing structure, the seal support having an inner cylindrical part and a diaphragm extending radially outwardly from said inner cylindrical part, the inner cylindrical part projecting axially within the stationary housing structure, at least one seal member mounted to a radially inner surface of said inner cylindrical part of the seal support, and a first set of circumferentially spaced-apart channel segments projecting from a radially outer peripheral portion of the diaphragm for mating engagement with a corresponding second set of circumferentially spaced-apart channel segments provided on a radially outer surface of the stationary housing structure, the diaphragm at least partly flexibly isolating the first and second sets of channel segments from the at least one seal member, when axially aligned, the first and second set of circumferentially spaced-apart channel segments cooperating to define a circumferentially extending channel, and wherein at least one retaining ring is engaged in the circumferentially extending channel to axially retain the seal support on the stationary housing structure of the gas turbine engine.