Abstract: A low-pressure (LP) turbine includes an LP shaft, one or more stages of LP turbine stator vanes and LP turbine rotor blades, and one or more interstage seals. The LP turbine rotor blades are coupled to, and rotate with, the LP shaft. The one or more interstage seals are disposed between the one or more stages. The one or more interstage seals each includes a seal disk that extends radially inward of the LP turbine stator vanes. Each seal disk includes an outer shell that supports one or more seal teeth, and the outer shell rotates as the LP shaft rotates.

Abstract: A gearbox assembly for a turbine engine. The gearbox assembly includes a gearbox having a plurality of gears, and a scavenge gutter radially outward of the gearbox and mounted to a fan frame flange of a fan frame of the turbine engine, the scavenge gutter being configured to collect lubricant that is ejected by the plurality of gears of the gearbox during rotation of the plurality of gears. An interface between the fan frame flange and the scavenge gutter is located at a first radial distance R1 relative to a longitudinal centerline axis of the turbine engine and the scavenge gutter is located at a second radial distance R2 relative to the longitudinal centerline axis. The second radial distance R2 is greater than the first radial distance R1. The scavenge gutter is segmented and includes a plurality of sector portions joined together to form the scavenge gutter.

Abstract: A turbine engine includes a high-pressure (HP) compressor and a bleed system. The HP compressor includes an HP compressor flowpath and a plurality of stages of HP compressor rotor blades and HP compressor stator vanes. The bleed system includes a plurality of bleed flowpaths including at least three bleed flowpaths in fluid communication with the HP compressor flowpath. The plurality of bleed flowpaths direct compressed air from the HP compressor flowpath. At least two of the bleed flowpaths are at successive stages of the plurality of stages.

Abstract: A turbine engine includes a high-pressure (HP) compressor and a bleed system. The HP compressor includes an HP compressor flowpath and a plurality of stages of HP compressor rotor blades and HP compressor stator vanes. The bleed system includes a plurality of bleed flowpaths including at least three bleed flowpaths in fluid communication with the HP compressor flowpath. The plurality of bleed flowpaths direct compressed air from the HP compressor flowpath. At least two of the bleed flowpaths are at successive stages of the plurality of stages.

Abstract: A low-pressure (LP) turbine includes an LP shaft, one or more stages of LP turbine stator vanes and LP turbine rotor blades, and one or more interstage seals. The LP turbine rotor blades are coupled to, and rotate with, the LP shaft. The one or more interstage seals are disposed between the one or more stages. The one or more interstage seals each includes a seal disk that extends radially inward of the LP turbine stator vanes. Each seal disk includes an outer shell that supports one or more seal teeth, and the outer shell rotates as the LP shaft rotates.