Abstract: A gas turbine engine includes a fan located at a forward portion of the gas turbine engine, and a compressor section and a turbine section arranged in serial flow order. The compressor section and the turbine section together define a core airflow path. A rotary member is rotatable with the fan and with a low pressure turbine of the turbine section. The low pressure turbine includes a rotating drum to which a first airfoil structure is connected and extends radially inward toward the rotary member. A torque frame connects the rotating drum to the rotary member and transfers torque from the first airfoil structure mounted to the rotating drum to the rotary member. The torque frame includes an inner disk mounted to the rotary member, an outer ring and a second airfoil structure formed separately from the outer ring and connected thereto by a releasable connecting structure. The second airfoil structure extends radially inward from the outer ring toward the inner disk.

Abstract: A turbomachine having an engine centerline and a first rotor. The first rotor having a first annular drum and being connected to a first plurality of blades. At least one blade of the first plurality of blades having a blade root, a blade tip, a first arm, a second arm and a first seal. The first arm extending from the blade root and having a radial retention hook. The second arm extending from the blade tip.

Abstract: A fastener cover for a flanged joint including first and second annular flanges extending about an axis, comprising: an annular, axially-extending, inboard wall; an annular, axially-extending outboard wall positioned radially outboard of the inboard wall; and a first radial wall interconnecting the inboard and outboard walls, wherein, collectively, the inboard and outboard walls and the first radial wall define a cavity for receiving a portion of a fastener; at least one fastener pocket including sidewalls extending axially away from the first radial wall and defining a tubular shape, which is closed off opposite the first radial wall by a floor plate having a clearance hole passing therethrough for accepting a shank of the fastener; and wherein the cover includes a balance weight receptacle for accepting at least one balance weight.

Abstract: A turbomachine, a computing system for a turbomachine, and a method for overspeed protection are provided. The turbomachine includes a first rotor assembly interdigitated with a second rotor assembly together operably coupled to a gear assembly. A plurality of sensors is configured to receive rotor state data indicative of one or more of a speed, geometric dimension, or capacitance, or change thereof, or rate of change thereof, relative to the first rotor assembly or the second rotor assembly. A controller executes operations including receiving rotor state data from the plurality of sensors; comparing rotor state data to one or more rotor state limits; and contacting one or more of the first rotor assembly or the second rotor assembly to a contact surface adjacent to the respective first rotor assembly or the second rotor assembly if the rotor state data exceeds the rotor state limit.

Abstract: A method of servicing a gas turbine engine, the method including preparing the gas turbine engine for service; installing a shaft protection cover to an aft end of a fan shaft of the gas turbine engine; installing an oil collector drum at least partially around a gearbox of the gas turbine engine; and removing at least a portion of the gearbox from the gas turbine engine.

Abstract: A turbomachine having an engine centerline and a first rotor. The first rotor having a first annular drum and being connected to a first plurality of blades. At least one blade of the first plurality of blades having a blade root, a blade tip, a first arm, a second arm and a first seal. The first arm extending from the blade root and having a radial retention hook. The second arm extending from the blade tip.

Abstract: A blade for a turbomachine includes a blade root portion for securing the blade to a rotatable annular outer drum rotor. The blade root portion includes one or more radial retention features for radially retaining each of the blade root portions within the rotatable annular outer drum rotor. Further, at least one of the radial retention feature(s) includes at least one sealing member integrated therewith.

Abstract: A fastener cover for a flanged joint including first and second annular flanges extending about an axis, comprising: an annular, axially-extending, inboard wall; an annular, axially-extending outboard wall positioned radially outboard of the inboard wall; and a first radial wall interconnecting the inboard and outboard walls, wherein, collectively, the inboard and outboard walls and the first radial wall define a cavity for receiving a portion of a fastener; at least one fastener pocket including sidewalls extending axially away from the first radial wall and defining a tubular shape, which is closed off opposite the first radial wall by a floor plate having a clearance hole passing therethrough for accepting a shank of the fastener; and wherein the cover includes a balance weight receptacle for accepting at least one balance weight.

Abstract: A turbomachine includes a rotatable annular outer drum rotor connected to a first plurality of blades. The rotatable annular outer drum rotor is constructed of, at least, a first drum segment and a second drum segment. The turbomachine further includes a retaining ring arranged and secured between the first and second drum segments of the rotatable annular outer drum rotor for radially retaining each of the first plurality of blades via their respective blade root portions within the rotatable annular outer drum rotor.

Abstract: A turbomachine, a computing system for a turbomachine, and a method for overspeed protection are provided. The turbomachine includes a first rotor assembly interdigitated with a second rotor assembly together operably coupled to a gear assembly. A plurality of sensors is configured to receive rotor state data indicative of one or more of a speed, geometric dimension, or capacitance, or change thereof, or rate of change thereof, relative to the first rotor assembly or the second rotor assembly. A controller executes operations including receiving rotor state data from the plurality of sensors; comparing rotor state data to one or more rotor state limits; and contacting one or more of the first rotor assembly or the second rotor assembly to a contact surface adjacent to the respective first rotor assembly or the second rotor assembly if the rotor state data exceeds the rotor state limit.

Abstract: A method of servicing a gas turbine engine, the method including preparing the gas turbine engine for service; installing a shaft protection cover to an aft end of a fan shaft of the gas turbine engine; installing an oil collector drum at least partially around a gearbox of the gas turbine engine; and removing at least a portion of the gearbox from the gas turbine engine.

Abstract: A method for engine assembly is provided, the method including forming an interdigitated rotor assembly comprising an inner rotor assembly rotatable at a first speed different from an outer rotor assembly rotatable at a second speed; fastening a gear assembly to the interdigitated rotor assembly to form an interdigitated turbine assembly; and coupling the interdigitated turbine assembly to a gas generator, wherein coupling the interdigitated turbine assembly to the gas generator includes coupling a planet carrier assembly of the gear assembly to a static frame of the gas generator.

Abstract: A turbomachine includes a rotatable annular outer drum rotor connected to a first plurality of blades. Each of the first plurality of blades includes a blade root portion secured to the rotatable annular outer drum rotor. Each of the blade root portions includes one or more structural radial retention features for radially retaining each of the blade root portions within the rotatable annular outer drum and one or more axial retention features for axially retaining each of the blade root portions within the rotatable annular outer drum.

Abstract: A turbomachine includes a rotatable annular outer drum rotor connected to a first plurality of blades. Each of the first plurality of blades includes a blade root portion secured to the rotatable annular outer drum rotor. Each of the blade root portions includes one or more structural radial retention features for radially retaining each of the blade root portions within the rotatable annular outer drum and one or more axial retention features for axially retaining each of the blade root portions within the rotatable annular outer drum.

Abstract: A shroud assembly for a rotary component of a gas turbine engine defining a central axis extending along an axial direction, a radial direction extending perpendicular to the axial direction, and a circumferential direction perpendicular to both the central axis and the radial direction. The shroud assembly includes a plurality of tip shrouds, and each of the plurality of tip shrouds includes a shroud band. Further, each tip shroud of the plurality of tip shrouds is coupled to one of the plurality of rotor blades at a tip end. The plurality of tip shrouds includes a first tip shroud defining a first length in a first direction and a second tip shroud defining a second length in the first direction. Moreover, the second length is different than the first length.

Abstract: A turbomachine includes a rotatable annular outer drum rotor connected to a first plurality of blades. The rotatable annular outer drum rotor is constructed of, at least, a first drum segment and a second drum segment. The turbomachine further includes a retaining ring arranged and secured between the first and second drum segments of the rotatable annular outer drum rotor for radially retaining each of the first plurality of blades via their respective blade root portions within the rotatable annular outer drum rotor.

Abstract: A blade for a turbomachine includes a blade root portion for securing the blade to a rotatable annular outer drum rotor. The blade root portion includes one or more radial retention features for radially retaining each of the blade root portions within the rotatable annular outer drum rotor. Further, at least one of the radial retention feature(s) includes at least one sealing member integrated therewith.