Patent ID: 8752395

Claim:
A combination comprising: a gas turbine engine extending along an axis and including an annular combustor having a combustor liner; a plurality of projections extending from said combustor liner and spaced from one another circumferentially about said axis, wherein each of said plurality of projections extends from a base to a distal end and includes a flange projecting along said axis from the distal end, wherein a notch cutout extends through each of said flanges from the plurality of projections along said axis in an at least partially radial direction relative to said axis, and wherein said flange includes a radially inward facing surface; a free-standing ring disposed about said combustor liner and positioned adjacent to said plurality of projections along said axis, wherein said free-standing ring includes a plurality of slots formed therein; a leaf seal having a radially outer surface; and a plurality of pins, each pin being integrally formed with one of said plurality of projections and extending along said axis, wherein each of said plurality of pins is received into one of said plurality of slots, wherein said plurality of pins engage said free-standing ring via said plurality of slots, and wherein said plurality of pins and said plurality of slots are positioned to circumferentially support said combustor liner by virtue of the engagement of the plurality of pins with the plurality of slots while allowing relative radial displacement between said combustor liner and said free-standing ring; wherein said radially inward facing surface is positioned to radially constrain the leaf seal against outward radial movement via the radially outer surface and said notch is positioned to constrain the leaf seal against circumferential movement; and wherein the leaf seal does not include an opening therein.