Mounting assembly for the forward end of a ceramic matrix composite liner in a gas turbine engine combustor

A mounting assembly (35/80) for a forward end (36/82) of a liner (16/18) in a combustor (10) of a gas turbine engine including a dome (20) and a cowl (24/26), wherein a longitudinal centerline axis (12) extends through the gas turbine engine. The mounting assembly (35/80) includes a pin member (48/94) extending through each one of a plurality of circumferentially spaced openings (42, 44, 46) formed in the forward end (38) of the liner (16/18), an aft portion (38) of the cowl (24/26), and a portion (40/86) of the dome (20), with each pin member (48) including a head portion (50) at one end thereof. A nut (54) is adjustably connected to an end of each pin member (48) opposite the head portion (50). A bushing (60) is located on each pin member (48) at a position intermediate the head portion (50) and the nut (54), wherein the openings (42) in the liner forward end (36/82) are sized to fit around the bushings (60). In this way, the cowl aft portion (38) and the dome portion (40) are fixedly connected together between the bushing (60) and the nut (54) so that the bushings (60) are able to slide radially through the openings (42/82) in the liner forward end (36/82) as the cowl (24/26) and the dome (20) experience thermal growth greater than the liner (16/18).