Patent ID: 9022390
Filing Date: 2015-05-05
Classification: F01D,F02C,F16J

Abstract:
1. A seal assembly for a gas turbine engine comprising: a first component having a threaded portion and one or more knife edges disposed adjacent the threaded portion, the threaded portion has a variable pitch, the variable pitch comprises a generally smooth transition from a coarser pitch thread to a finer pitch thread, and wherein the finer pitch thread is disposed closer to the one or more knife edges than the coarser pitch thread; a second component that interfaces with the threaded portion, wherein together the threaded portion and the second component form a seal that restricts fluid flow between a first cavity and a second cavity; wherein the second component has an abradable portion with a recessed region and wherein a tip of the one or more knife edges is disposed along a first outer extent that differs from a second outer extent of the tips of the threaded portion; and wherein the tip of the one or more knife edges is disposed along the recessed region and wherein the threaded portion is disposed away from the recessed region.