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 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 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 directed energy deposition additive manufacturing system may include an apparatus for applying a compressive load to a component being built in the system with an overhanging geometry. The apparatus has a compression head that applies the compressive load. The apparatus may apply the compressive load at a compression angle that may be complementary to an inclination angle of the component. The apparatus may operate in multiple degrees of freedom.

Abstract: An additive manufacturing system for forming a component including a compression rig including a compression head supporting a top compression device applying a compressive load onto a top surface of the component, a pair of temperature sensors positioned on opposite sides of the top compression device and detecting a temperature of the top surface of the component, and a pair of distance sensors positioned on opposite sides of the top compression device and detecting a distance to the top surface of the component, and a controller configured to adjust a position of the compression rig and a load applied by the top compression device based on at least one of the detected temperatures and distances.

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.

Abstract: An additive manufacturing system for producing a component includes a deposition assembly having a deposition head through which melted feedstock material is deposited, and a compression rig comprising a compression head supporting an inside roller, an outside roller opposing the inside roller, and a top roller, the inside roller applying a compressive load onto an interior side surface of the component, the outside roller applying a compressive load onto an exterior side surface of the component, and the top roller applying a compressive load onto a top surface of the component.

Abstract: A gearbox for a gas turbine engine. The gearbox including a rotor and a gutter. The oil system is configured to supply oil to the gearbox. The rotor is rotatable about a rotation axis. The rotor expels oil radially outward when the rotor rotates. The gutter is positioned radially outward of the rotor to collect oil expelled by the rotor when the rotor rotates. The gutter is positioned eccentrically with respect to the rotor.

Abstract: An apparatus and method for a reverse flow combustor, the reverse flow combustor including a straight portion, a dilution portion and a curved portion. The reverse flow combustor receives a flow of fuel that is ignited and mixed with cooling air to form a flow of combustion gases. The flow of combustion gases travels through the reverse flow combustor to a turbine section of an engine.

Abstract: Methods for treating steel, along with the resulting treated steel, are provided. The method may comprise: nitriding a carburized Ferrium steel component such that the Ferrium steel component has a surface portion with a nitrogen content that is greater than 0% to about 5% by weight. Nitriding the Ferrium steel component may increase the surface hardness of the Ferrium steel. The surface portion may have a nitrogen content of about 0.05% to about 0.5% by weight.

Abstract: A gearbox assembly includes a gear assembly that includes a planet gear, a pin disposed within the planet gear, a first sensor, and a second sensor. The first sensor is disposed within the pin and is configured to produce a signal indicative of a strain of the pin. The second sensor is disposed within the pin and is configured to produce a signal indicative of a vibration of the pin. Another gearbox assembly includes a gear assembly including a planet gear, a pin disposed within the planet gear, and a strain sensor. The strain sensor is disposed within the pin and is configured to produce a signal indicative of a strain of the pin. The strain sensor is located within the pin at a circumferential location of the pin that is opposite to a location of a force acting on the pin when the planet gear rotates about the pin.

Abstract: A turbine blade including an airfoil portion extending between a leading edge and a trailing edge, a base portion positioned below the airfoil portion, the base portion including an outwardly-extending wing positioned below the airfoil portion, and an aero-brake feature positioned between the outwardly-extending wing and the airfoil portion and extending outward from the base portion, where the aero-brake feature is structurally configured to disrupt axial airflow across the turbine blade.

Abstract: A turbomachine engine includes a fan section having a fan shaft, and a core engine having one or more compressor sections, one or more turbine sections that includes a power turbine, and a combustion chamber in flow communication with the compressor sections and turbine sections. The turbomachine engine includes a low-speed shaft coupled to the power turbine and having a midshaft that extends from a forward bearing to an aft bearing. The low-speed shaft is characterized by a midshaft rating (MSR) between two hundred (ft/sec)1/2 and three hundred (ft/sec)1/2. The low-speed shaft has a redline speed between fifty and two hundred fifty feet per second (ft/sec). The turbomachine engine includes a gearbox assembly that couples the fan shaft to the low-speed shaft and characterized by a gearbox assembly mode less than 95% of a midshaft mode of the midshaft or greater than 105% of the midshaft mode.

Abstract: An integrated lubrication system and an engine that includes the integrated lubrication system. The system has a first and a second lubrication supply line and one or more spray bars. The first lubrication supply line extends radially inward toward a central axis of the engine, has a first plurality of jet outlets, and is configured to deliver a lubrication fluid to a first location on one or more engine components. The second lubrication supply line extends parallel to the central axis, has a second plurality of jet outlets, and is configured to deliver the lubrication fluid to a second location on the one or more engine components. The first lubrication supply line is configured to lubricate the one or more engine components in a first engine power condition and the second lubrication supply line is configured to lubricate the one or more engine components in a second engine power condition.

Abstract: In a fuel control system (10) for a gas turbine engine (1) having a gas generator (4) and a turbine (6) driven by the gas generator (4): a main fuel regulator (12) determines a demand (Wfdem) of fuel flow (Wf) to be introduced in the gas turbine engine (1), based on an input request (PLA); and a first limiter stage (14), operatively coupled to the main fuel regulator (12), causes an adjustment of the fuel flow (Wf) based on engine safety operating limits. The first limiter stage (14) is provided with a Ngdot limiter (20) to cause an adjustment of the fuel flow (Wf) when the gas generator speed rate of change (Ngdot) is determined to overcome acceleration/deceleration scheduled safety limits; the Ngdot limiter (20) implements a predictor (23), to perform a prediction (Wfdot) of the fuel flow rate of change (Wfdot), or fuel flow (Wf), allowing the gas generator speed rate of change (Ngdot) to track a scheduled reference value (Ngdotref).

Abstract: A turbomachine engine can include a fan assembly, a vane assembly, a core engine, a gearbox, and an overall engine efficiency rating. 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 a low-pressure turbine. The gearbox includes an input and an output. The input of the gearbox is coupled to the low-pressure turbine of the core engine and comprises a first rotational speed, the output of the gearbox is coupled to the fan assembly and has a second rotational speed, and a gear ratio of the first rotational speed to the second rotational speed is within a range of 2.0-4.0. The overall engine efficiency rating is greater than or equal to 0.35GR1.5 and less than or equal to 0.7GR1.5.

Abstract: An electronic control system (30) for a turbopropeller engine (12) having a gas turbine (20) and a propeller assembly (13) coupled to the gas turbine (20), controls propeller operation based on a pilot input request, via generation of a driving quantity (Ip) for an actuation assembly (29) designed to adjust a pitch angle (?) of propeller blades (2) of the propeller assembly (13).

Abstract: An electronic control system for a turbopropeller engine having a gas turbine and a propeller assembly coupled to the gas turbine is provided. The control system implements a propeller control unit to control propeller operation using an actuation assembly designed to adjust a pitch angle of propeller blades. The control unit engages a mechanical lock determining a minimum flight value for the pitch angle during a flight operating mode, and disengages the mechanical lock and controls the pitch angle below the minimum flight value, up to a minimum ground value lower than the minimum flight value, during a ground operating mode. The propeller control unit, during a transition from the ground operating mode to the flight operating mode, engages the mechanical lock. The control unit anticipates the increase of the pitch angle before the mechanical lock engagement when transitioning from the ground operating mode to the flight operating mode.

Abstract: A turbine engine having counter-rotating rotors comprising a first rotor, rotating in a first rotational direction, defining a first rotor set of blades axially spaced to define a gap, and a second rotor, rotating in a second rotational direction counter the first rotational direction. The second rotor further including a second set of blades received within the gap of the first rotor. A plurality of fluid passages is formed in the first rotor with an outlet facing the gap.

Abstract: A turbomachine engine can include a fan assembly, a vane assembly, a core engine, a gearbox, and an overall engine efficiency rating. 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 a low-pressure turbine. The gearbox includes an input and an output. The input of the gearbox is coupled to the low-pressure turbine of the core engine and comprises a first rotational speed, the output of the gearbox is coupled to the fan assembly and has a second rotational speed, and a gear ratio of the first rotational speed to the second rotational speed is within a range of 3.2-4.0. The overall engine efficiency rating is within a range of 0.57-8.0.