| 摘要 |
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 (202) 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). |
