COMBUSTOR SEAL SYSTEM AND CORRESPONDING METHOD

A combustor seal system (200) for a gas turbine engine (100) is provided that includes a rear inner discharge nozzle (RIDN) (202) configured to engage a liner (212) of a combustor (108). The system (200) further includes a nozzle guide vane (NGV) (204) positioned adjacent the RIDN (202). The NGV (204) and the RIDN (202) together define a cavity (216). The system (200) further includes a seal (206) in contact with the RIDN (202) and positioned in the cavity (216). The seal (206) curves along a surface (217) of the cavity (216) and contacts the RIDN (202) at a first point (218) and a second point (220) in the cavity (216). The seal (206) contacts the NGV (204) at a third point (222).