Patent ID: 8534673

Claim:
A seal assembly for a turbine engine, comprising: a seal housing having a circumferential groove located along an edge of said seal housing, said circumferential groove having a plurality of through holes; a plurality of segments strips, each having at least one threaded hole, an upstream sealing surface, a downstream sealing surface, a right circumferential sealing surface and a left circumferential sealing surface, and a plurality of fasteners for securing each of said plurality of segments strips in said circumferential groove in an annular manner to form a seal, wherein said circumferential groove is configured to accept the geometry of each of said plurality of secured segments strips, said upstream sealing surface of each of said plurality of secured segment strips forms an upstream contact sealing surface with said seal housing, said downstream sealing surface of each of said plurality of secured segment strips is arranged to form a downstream contact sealing surface with a stationary member of said turbine engine, said right circumferential sealing surface of a first of said plurality of secured segment strips forms a first circumferential contact sealing surface with a left circumferential sealing surface of a second of said plurality of secured segment strips, and said left circumferential sealing surface of said first of said plurality of secured segment strips forms a second circumferential contact sealing surface with a right circumferential sealing surface of the second of said plurality of secured segment strips.