Abstract: A seal assembly for a gas turbine engine defining a central axis extending along an axial direction and including a rotating shaft extending at least partially along the axial direction. The seal assembly includes a first component coupled to a fixed structure or drivingly coupled to the rotating shaft. The seal assembly further includes a rotating component drivingly coupled to the rotating shaft of the gas turbine engine. Additionally, the first component and rotating component define an annular gap therebetween. The seal assembly also includes one or more flanges extending from the stationary component, the rotating component, or both. The flange(s) include a base and an external surface extending into the annular gap from the base to a tip. Additionally, the flange(s) defines an inlet port on the external surface fluidly coupled to an outlet port at the tip. As such, the flange(s) forms a seal within the annular gap.

Abstract: A gas turbine engine including a frame assembly; a turbine assembly; and a nozzle disposed in the turbine assembly, wherein the nozzle defines an inner end along a radial direction and an outer end along the radial direction, wherein the outer end of the nozzle is supported by the frame assembly, wherein the inner end of the nozzle is supported by the frame assembly, and wherein the inner end of the nozzle is displaceable relative to the frame assembly in at least the radial direction.