Sealing assembly for the aft end of a ceramic matrix composite liner in a gas turbine engine combustor

摘要

An assembly (36) for providing a seal at an aft end (38) of a combustor liner (18) for a gas turbine engine including a longitudinal centerline axis extending therethrough. The sealing assembly (36) includes a substantially annular first sealing member (44) positioned between an aft portion (40) of a support member (34) and the liner aft end (38) so as to seat on a designated surface portion (46) of the liner aft end (38) and a substantially annular second sealing member (51) positioned between the support member aft portion (40) and a turbine nozzle (41) located downstream of the liner aft end (38) so as to seat on a designated surface portion (53) of the support member aft portion (40). Accordingly, the first sealing member (44) is maintained in its seated position as the support member aft portion (40/98) moves radially with respect to the liner aft end (38) and the second sealing member (51) is maintained in its seated position as the support member aft portion (40) moves axially with respect to the turbine nozzle (41). The first and second sealing members (44, 51) are also maintained in their respective seating positions as the support member aft portion (40) moves axially with respect to the liner aft end (38) and radially with respect to the turbine nozzle (41).