Abstract: An air separator in a gas turbine engine includes a cylindrical member and a seal flange having a flange body extending radially outward at a rearward end of the cylindrical member. A head portion is located at a radially outer free end of the flange body and includes an axial flange located axially rearward of the flange body and defining a rearward seal face for engagement with a blade disc forward face, and a forward cantilevered head mass extending axially forward from the flange body. An axial dimension of the head mass, from a connection with the forward side of flange body to an axially forward face of the head mass, is greater than a maximum radial dimension of the head mass, from a radially inner side of the head mass to a radially outermost side of the head mass.

Abstract: A seal assembly is provided for a turbine engine and includes an annular labyrinth seal holder supported on a radially inner end of vanes A plurality of radially extending labyrinth seal elements are supported on the labyrinth seal holder, and a brush seal assembly is supported to the labyrinth seal holder downstream from the labyrinth seal elements. The brush seal assembly includes a brush seal holder and a brush seal located adjacent to an axially rearward one of the rotor arms. The brush seal holder is attached to an axially facing surface of the labyrinth seal holder. A seal plate defining a detachable labyrinth seal element extends radially inward from the axially facing surface of the labyrinth seal holder to the rearward rotor arm at a location upstream of the brush seal.

Abstract: A seal assembly is provided for a turbine engine and includes an annular labyrinth seal holder supported on a radially inner end of vanes A plurality of radially extending labyrinth seal elements are supported on the labyrinth seal holder, and a brush seal assembly is supported to the labyrinth seal holder downstream from the labyrinth seal elements. The brush seal assembly includes a brush seal holder and a brush seal located adjacent to an axially rearward one of the rotor arms. The brush seal holder is attached to an axially facing surface of the labyrinth seal holder. A seal plate defining a detachable labyrinth seal element extends radially inward from the axially facing surface of the labyrinth seal holder to the rearward rotor arm at a location upstream of the brush seal.

Abstract: An air separator in a gas turbine engine includes a cylindrical member and a seal flange having a flange body extending radially outward at a rearward end of the cylindrical member. A head portion is located at a radially outer free end of the flange body and includes an axial flange located axially rearward of the flange body and defining a rearward seal face for engagement with a blade disc forward face, and a forward cantilevered head mass extending axially forward from the flange body. An axial dimension of the head mass, from a connection with the forward side of flange body to an axially forward face of the head mass, is greater than a maximum radial dimension of the head mass, from a radially inner side of the head mass to a radially outermost side of the head mass.