Patent ID: 8172514

Claim:
A rim seal and gas turbine engine arrangement, the arrangement comprising: a set of rotating blades having platforms extending axially aft therefrom, a non-rotating structure disposed adjacent to and downstream of the blade platforms and spaced apart therefrom to define an annular space between the blade platforms and the adjacent non-rotating structure, and a rim seal being mounted to the non-rotating structure and extending through the annular space towards the blade platforms, the rim seal having its outermost peripheral portion positioned radially inward of a rearwardly protruding portion of the blade platforms, the rim seal made of an abradable material, each said blade platform having a portion which, in use, is in engagement with said outermost peripheral portion of the rim seal for abrasion of the rim seal abradable material to close a gap between the protruding portion and the non-rotating structure by thermal expansion during operation to define a generally smooth gapless surface for an engine gas path.