Patent ID: 8186692

Claim:
A split ring seal assembly for a gas turbine engine comprising: a first stator ring and a second stator ring of the engine, the first stator ring having a circumferentially extending first radial surface and the second stator ring having a circumferentially extending second radial surface, the first and second radial surfaces being axially spaced apart, thereby defining an axial gap therebetween; a seal ring disposed around the first stator ring of the engine for sealing the axial gap, the seal ring being made of a metal material and having first and second ends defining a circumferential gap between the two ends, the seal ring defining an axially extending first circumferential sealing surface and a radially extending second circumferential sealing surface, the first circumferential sealing surface being in contact with an outer circumferential surface which extends axially and terminates at the first radial surface, the second circumferential sealing surface being in contact with the second radial surface, thereby sealing the axial gap; and a first spring element connected to and applying circumferential spring forces to the respective first and second ends of the seal ring, to bias the two ends circumferentially towards each other, thereby reducing the diameter of the seal ring to secure the seal ring in position.