Patent ID: 8206087
Filing Date: 2012-06-26
Classification: F01D,F05D,F16J,Y10S

Abstract:
1. A seal arrangement for reducing seal gaps within a turbine engine including a circumferentially extending structure having an axially extending surface forming a gas flow path extending parallel to an axis of said turbine engine, said seal arrangement comprising: a plurality of circumferentially disposed segments defining said circumferentially extending structure, each said segment including: said segments arranged such that a gap is defined between facing axial edges of adjacent ones of said segments; a sealing element extending within said gap from said surface portions of said adjacent segments radially along at least a portion of said facing axial edges, said sealing element comprising a compliant material in the circumferential direction to span said gap during reduction and expansion of said gap; and wherein said sealing element is non-homogeneous including a first layer and a second layer, said first layer comprising a non-woven fibrous layer compressed in the circumferential direction between said facing axial edges to a thickness reduced from its uncompressed thickness and at least a portion of said second layer defining a protective erosion resistant surface located adjacent to and spanning between said surface portions of said adjacent segments.