Patent ID: 6536773
Filing Date: 2003-03-25
Classification: F01D,F02C,F04D,F05D,F16J,Y02T

Abstract:
A compliant brush shroud assembly for use with a gas turbine engine, the brush shroud assembly comprising:a housing; at least two bristle strips, each comprising at least two bristle packs, each bristle pack being secured to at least one rail and including a first end defining an outer diameter and being constructed and arranged to be secured within the housing, and a second end opposite the first end defining an inner diameter, the bristle packs being constrained at the first end and free at the second end, such that the width at the outer diameter is less than that at the inner diameter and the second end is flared relative to the first end; at least two annular rings; and wherein each of the at least two bristle strips is supported within a corresponding annular ring such that an outer diameter of the at least one rail is disposed adjacent an inner diameter of the corresponding annular ring, and wherein adjacent annular rings are in contact along at least a portion of an outer surface of the adjacent annular rings, the free second ends of the bristle packs extending from the annular ring and having a width greater than the width of the bristle strip and annular ring combined such that upon securing the bristle packs within the housing the free second ends of adjacent bristle packs form a continuous surface.