Abstract: A turbomachine engine according to aspects of the present disclosure is provided. The engine includes a fan assembly including a plurality of fan blades, and a core engine surrounded by an outer casing. The core engine includes a power output component operably connected to the fan assembly, a first input power source and a second input power source. The first input power source is counter-rotatable relative to the second input power source. The core engine includes a gear assembly operably connected to the power output component and configured to receive power from the first input power source and the second input power source.

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 hybrid electric aircraft equipped with gyroscopic stabilization control is provided. In one aspect, a hybrid electric aircraft includes a turbo-generator having a gas turbine engine and an electric generator operatively coupled thereto for generating electrical power. The turbo-generator defines a rotation axis. The aircraft also includes one or more electrically-driven propulsors for producing thrust for the aircraft. In addition, the aircraft includes a pivot mount operatively coupled with the turbo-generator. To provide gyroscopic stabilization control of the aircraft, the pivot mount is controlled to adjust the rotation axis of the turbo-generator relative to a prime stability axis of the aircraft. Additionally or alternatively, a rotational speed of the turbo-generator can be changed to provide gyroscopic stabilization control of the aircraft.

Abstract: A turbine engine with an outer rotor that circumscribes an inner rotor. The outer rotor includes circumferentially arranged components with a radial outer end and radial inner end. Inner ends of confronting sides of adjacent components include at least one damper element to dampen the relative motion of the components or to provide at least a partial seal between adjacent components.

Abstract: Methods and apparatus to produce hydrogen gas turbine propulsion are disclosed. An example apparatus to produce propulsion in a gas turbine engine includes a fluid line to transport hydrogen from a hydrogen supply and an inert gas from an inert gas supply to a gas turbine combustor. The apparatus also includes at least one heat exchanger coupled to the fluid line to heat the inert gas and the hydrogen in the fluid line.

Abstract: A gas turbine engine comprising a set of circumferentially adjacent airfoils, the airfoils having an outer wall defining a pressure side and a suction side extending between a leading edge and a trailing edge to define a stream-wise direction, and between a root and a tip to define a span-wise direction, and a set of dimples provide on the outer wall of at least one of the airfoils, the set of dimples spaced in at least one of the stream-wise or span-wise directions.

Abstract: An electronic control system (35) for a turbopropeller (2) having a gas turbine engine (20) and a propeller assembly (3) coupled to the gas turbine engine (20), the control system (35) having: a propeller control stage (35a), implementing a closed loop control for controlling operation of the propeller assembly (3) based on a scheduled propeller speed reference (Nrref) and a propeller speed measure (Nr); a gas turbine control stage (35b), implementing a closed loop control for controlling operation of the gas turbine engine (20) based on a scheduled reference (Ngdotref) and at least a feedback quantity. The control system (35) further envisages an auxiliary control stage (35c), coupling the propeller control stage (35a) and the gas turbine control stage (35b) and determining a limitation of the operation of the gas turbine engine (20), if a propeller speed overshoot is detected, with respect to the propeller speed reference (Nrref).

Abstract: Based upon a measured first resistance, a first delta curve is selected. Based upon a measured second resistance, a second delta curve is selected. A first fuel valve position (FVP) is received from a first position sensor, and the first FVP is applied to the first delta curve to obtain a first offset. A second FVP is received from a second position sensor, and the second FVP is applied to the second delta curve to obtain a second offset. The first offset is applied to the first measured FVP to obtain the first compensated FVP and the second offset is applied to the second measured FVP to obtain the second compensated FVP. The first compensated FVP and the second compensated FVP are correlated to obtain a final compensated FVP, which is applied to a desired fuel valve position to obtain a final fuel valve position.

Abstract: A gear assembly for use with a turbomachine comprises a sun gear, a plurality of planet gear layshafts that each support a first stage planet gear and a second stage planet gear, and a ring gear. The sun gear is configured to rotate about a longitudinal centerline of the gear assembly, and the plurality of planet gear layshafts comprise an interior passage that receives one or more lubrication supply lines.

Abstract: An airfoil assembly defining a primary airflow path for a turbine engine comprising a platform, an airfoil extending from the platform and into at least a portion of the primary airflow path, a secondary airflow path comprising air from the primary airflow path, and a deflector provided within the secondary airflow path.

Abstract: A differential gearbox assembly for a turbine engine having a fan shaft and a drive shaft. The differential gearbox assembly includes an epicyclic gear assembly coupling the fan shaft to the drive shaft. The epicyclic gear assembly includes a sun gear, a planet gear constrained by a planet carrier, and a ring gear. The sun gear is coupled to the drive shaft and the planet carrier is coupled to the fan shaft. The sun gear, the planet gear, and the ring gear all rotate about the drive shaft. The differential gearbox assembly includes an electric machine assembly that includes an input coupled to the epicyclic gear assembly. The electric machine assembly provides mechanical power to the fan shaft through the epicyclic gear assembly.

Abstract: A turbomachine engine can include a fan assembly, a vane assembly, a core engine, and a gearbox. The fan assembly can include a plurality of fan blades. The vane assembly can include a plurality of vanes, and the vanes can, in some instances, be disposed aft of the fan blades. The core engine can include one or more compressor sections and one or more turbine sections. The gearbox includes an input and an output. The input is coupled to the one or more turbine sections of the core engine and comprises a first rotational speed, the output is coupled to the fan assembly and has a second rotational speed. A gear ratio of the first rotational speed to the second rotational speed is within a range of 4.1-11.0, and a gearbox oil flow rate at an inlet of the gearbox within a range of 5-25 gallons per minute at a max takeoff condition.

Abstract: A rotating field machine (200) including a stator (140) and a rotor (150) are provided. In particular, a dual-winding rotating field machine (200) in which the stator (140) includes two separate windings can be provided. In one example implementation, the stator (140) can include an excitation winding (220) configured to control an excitation current and a power winding (230) configured to control power flow to an electrical system. The dual-winding rotating field machine (200) can further include a starting mode and a generating mode. During the starting mode, both the excitation winding (220) and the power winding (230) can be coupled to one or more switching power converters (170). During the generating mode, the power winding (230) can be coupled to a variable frequency bus and the power converter (170) can be used to manage excitation power only.

Abstract: A gas turbine engine includes a fan assembly having a plurality of fan blades; and a turbomachine. The turbomachine includes a compressor section, a combustion section, and a turbine section in serial flow order. The turbomachine further including a first input power source; a second input power source configured to counter-rotate relative to the first input power source; a power output component operably connected to the fan assembly; and a gear assembly located forward of the combustion section of the turbomachine, the gear assembly configured to receive power from the first input power source and the second input power source and provide power to the power output component, the gear assembly comprising a helical gear.

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 turbine engine with at least a compressor section, combustor section, turbine section and a set of airfoils. The airfoils include geometric characteristics to create a high contraction ratio (CR), a low blade turning (BT) at a radially inward location the airfoil, a low solidity, or a low aspect ratio (AR).

Abstract: A gearbox including a gear and a gutter. The gear is rotatable about a rotational axis in a rotational direction. The gear has a radial direction and an axial direction, and the gear expels oil radially outward when the gear rotates. The gutter is positioned radially outward of the gear in the radial direction of the gear to collect oil expelled by the gear when the gear rotates. The gutter includes an axial surface, a plurality of radial surfaces including a first radial surface and a second radial surface, and at least one opening to allow the oil collected in the gutter to flow therethrough. Each of the first radial surface and the second radial surface is oriented in a direction intersecting the axial surface, and the at least one opening is formed on both the axial surface and one of the first radial surface and the second radial surface.

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 variable pitch propeller assembly operatively coupled with an engine and methods for controlling the pitch of a plurality of propeller blades thereof is provided. In one example aspect, the variable pitch propeller assembly includes features for combining overspeed, feathering, and reverse functionality in a single secondary control valve. The secondary control valve is operable to selectively allow a controlled amount of hydraulic fluid to flow to or from a pitch actuation assembly such that the pitch of the propeller blades can be adjusted to operate the variable pitch propeller assembly in one of a constant speed mode, a feather mode, and a reverse mode.

Abstract: A directed energy deposition (DED) additive manufacturing system may be utilized for manufacturing a cylindrical component from a feedstock material. The DED additive manufacturing system may comprise a rotary build table, a deposition assembly for depositing melted feedstock to form the component upon rotation of the build table, and a compression rig positioned proximate the deposition assembly and operable to continuously apply a compressive load to deposited melted feedstock material during deposition of the melted feedstock material.