Thermally Coupled Cmc Combustor Liner

Abstract: A combustor 26 for a gas turbine engine 10 is provided, which includes: a CMC liner 108 having a forward end 112 and an aft end 110; an annular dome 111 comprising a metal and defining an annular slot 122 within its end defined between an outer arm 200 and an inner arm 202; a feather seal 210 extending from an annularly exterior surface 219 of the annular dome 111 to an annularly exterior surface 209 of the liner 108; and a plurality of pin members 166. The forward end of the liner 108 defines a plurality of fingers 113 and a plurality of axial slots 109, and is fitted between the outer arm 200 and the inner arm 200 within the annular slot 122. Each pin member 166 extending through an aperture in the feather seal 210, through an aperture 201 in the outer arm 200 of the annular dome 111, through an opening 119 defined by the liner 108, and through an aperture 203 in the inner arm 202 of the annular dome 111. FIG. 1

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