Patent ID: 8206087

Claim:
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: an axially forward circumferential edge, an axially aft circumferential edge, and a pair of circumferentially spaced axial edges extending between said forward and aft edges; a surface portion comprising a portion of said axially extending surface and extending between said forward and aft circumferential edges and between said pair of axial edges, said surface portion extending generally parallel to said axis of said turbine engine in contact with high velocity gases flowing therethrough; and each said axial edge comprising a radial surface extending radially from said surface portion; 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.