Patent ID: 9181877
Filing Date: 2015-11-10
Classification: F01D,F02C,F04D,F05D,Y02T

Abstract:
1. A compressor section for use in a gas turbine engine, comprising: a compressor blade for rotating about an axis; a seal positioned radially outwardly of said compressor blade, and said seal having a seal hook facing in a downstream direction; a seal mount, said seal mount having a mount hook for receiving said seal hook in a gap, and said mount hook facing in an upstream direction, with said seal mount having an upstream portion extending from an upstream end into said gap, said mount hook then extending into a web which extends in a downstream direction; and a thermal barrier coating on said upstream portion of said seal mount from an upstream end and extending to a downstream end, and there being thermal barrier coating on a radially inner surface of said mount hook, and along said web with an upstream end of said coating on said radially inner surface of said hook being formed axially upstream of said downstream end of said coating on said upstream portion.