Abstract: A lubrication system for a gear assembly. The gear assembly includes a first gear and a second gear. The first gear and the second gear mesh with each other at a mesh. The lubrication system includes one or more lubricant injectors. The one or more lubricant injectors include one or more first lubricant outlets directed to the mesh. The one or more first lubricant outlets supply a first portion of lubricant to the mesh. The one or more lubricant injectors include one or more second lubricant outlets directed to a location that is different than the mesh. The one or more second lubricant outlets supply a second portion of lubricant to the location different than the mesh.

Abstract: A gearbox assembly includes a plurality of planet gears secured by a planet carrier. The plurality of planet gears and the planet carrier rotate about a longitudinal centerline axis. A planet pin is disposed in each planet gear. One or more journal bearings are defined by the planet pin and the planet gear, each planet gear rotating about the one or more journal bearings. The gearbox assembly includes an auxiliary lubrication system that stores lubricant therein. The auxiliary lubrication system includes one or more lubricant lines that provide fluid communication between the auxiliary lubrication system and the one or more journal bearings. Rotation of the planet carrier and the one or more journal bearings generates a suction effect that causes the lubricant in the auxiliary lubrication system to flow to the one or more journal bearings during windmilling conditions and during zero gravity conditions or negative gravity conditions.

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: An apparatus and method for reducing planet gear misalignment of planet gears mounted on a planet-carrier in an epicyclic gearing. The apparatus and method of the present disclosure specifically provide for a stiffness-reducing feature, a pillar, and a side-plate, each with a respective stiffness. In several embodiments, the feature stiffness is less than the pillar stiffness which is at least 10% less than the side-plate stiffness. The stiffness-reducing feature and the pillar may make up a pylon which has an axis. The pylon axis may form an angle with the side plate which is less than 90° and greater than 20°.

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 have a tubular shape.

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 system for torque measurement is generally provided. The system includes a sensor disposed between an outer bearing race and a static structure of a bearing assembly. The sensor is disposed adjacent along a thrust load direction to the outer bearing race. The system further includes a rotor assembly rotatably coupled to the bearing assembly, and a controller communicatively coupled to the sensor. The controller is configured to store and execute operations. The operations include determining a torque measurement from the rotor assembly based at least on an axial thrust load from the rotor assembly.

Abstract: A gear transmission for aeronautical applications including an input shaft rotating about an axis, an output shaft rotating about the axis, and a transfer group for transferring the torque from the input shaft to the output shaft. The transfer group includes a first torque splitting stage, receiving the torque from the input shaft, and a second torque splitting stage, receiving the torque from the first stage. The first stage presents at least one first rotating member and the second stage presents at least one second rotating member. The input shaft and the first rotating member cooperate with one another at respective interaction surfaces. The rotating members cooperate with one another at respective friction surfaces. One of the interaction surfaces has first engagement elements, and another of the interaction surfaces has second engagement elements that are clutch coupled to one another.

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 have a tubular shape.

Abstract: A gas turbine engine including a first frame including a first mount member defining a stiffness K1; a second frame including a second mount member defining a stiffness K2 and a third mount member defining a stiffness K3; and a gear assembly. The gear assembly includes a first rotatable component, a second rotatable component, and a torque transfer component. The first mount member is coupled to the first rotatable component. The second mount member is coupled to the second rotatable component. The third mount member is coupled to the torque transfer component. The stiffness K1 is less than or equal to 10% of the stiffness K3.

Abstract: An apparatus and method for reducing planet gear misalignment of planet gears mounted on a planet-carrier in an epicyclic gearing. The apparatus and method of the present disclosure specifically provide for a stiffness-reducing feature, a pillar, and a side-plate, each with a respective stiffness. In several embodiments, the feature stiffness is less than the pillar stiffness which is at least 10% less than the side-plate stiffness. The stiffness-reducing feature and the pillar may make up a pylon which has an axis. The pylon axis may form an angle with the side plate which is less than 90° and greater than 20°.

Abstract: An epicyclic gearbox assembly for a gas turbine engine includes a sun gear assembly; a planet gear assembly engaged with the sun gear assembly; and a ring gear assembly including one or more ring gears engaged with the planet gear assembly. The epicyclic gearbox assembly further includes a lubrication fluid collection assembly having a rotating oil scoop extending in a circumferential direction around the ring gear assembly, the rotating oil scoop coupled to the ring gear assembly at a location forward of one or more ring gears of the ring gear assembly.

Abstract: An epicyclic gearbox includes a sun gear assembly, a planet gear assembly, and a ring gear assembly engaged with a forward planet gear and an aft planet gear of the planet gear assembly. A first axial shroud is also provided positioned forward of the forward planet gear or aft of the aft planet gear along an axial direction. The first axial shroud covers substantially all of a forward side of the forward planet gear or an aft side of the aft planet gear. The planet gear assembly is coupled to a planet gear carrier, the planet gear carrier including a radial shroud including one or more radial shroud surfaces extending along at least a portion of an outer circumference of the forward planet gear and along at least a portion of an outer circumference of the aft planet gear.

Abstract: A transmission device for splitting torque between two coaxial gears, in particular for a planetary gearing for aeronautic applications, has a motion input member and two transmission members, which are coaxial and have respective shafts provided with gears at an axial end and respective external flanges, at the opposite axial end; the two flanges are axially facing and placed abutting against each other, and are fixed to the motion input member so as to split the torque transmitted from the motion input member between the two flanges; one of the two shafts is axially hollow and houses, with radial clearance, an intermediate portion of the other shaft; the latter is formed by at least two pieces which are coaxial and fixed to each other.

Abstract: A spray bar for lubricating gear meshes in an epicyclic transmission has a base having an inlet designed to receive, in use, a flow of pressurized oil. The spray bar has two tube portions, which project from the base along respective axes, define respective channels parallel to each other and permanently communicating with the inlet, and are laterally defined by respective outer surfaces having outlet nozzles for spraying oil from the channels.

Abstract: A test apparatus for testing a gear has a clamping device for clamping the gear. The device includes a single support block having one passage, extending along an axis, and a transversal first shoulder. The device further includes a securing bolt having a second shoulder provided with a pin axially extending through the passage and with a tightening member tightened on the pin so as to axially clamp the gear between the two shoulders. The support block further has a fixed protrusion axially projecting with respect to the first shoulder and having an outer surface designed to carry the gear.

Abstract: A casing for use in a turbofan engine is provided. The casing includes an inner hub, an intermediate casing positioned radially outward from the inner hub, an outer casing positioned radially outward from the intermediate casing, and a plurality of struts spaced circumferentially about the inner hub and extending between the inner hub and the outer casing. At least one strut of the plurality of struts includes a flow channel extending therethrough. The casing also includes a fluid scoop defined within the inner hub, and a collector that couples the fluid scoop in flow communication with the flow channel.

Abstract: An oil transfer unit has a rotating part extending along an axis, a stationary part provided with an oil mouth, and a floating part coupled to the stationary part; the floating part is provided with a cylindrical surface fitted onto an outer cylindrical surface of the rotating part in a non-contact configuration, with an annular groove therebetween to put the oil mouth into communication with an inner chamber of the rotating part; both sides of the groove are sealed by oil films at a radial gap between the cylindrical surfaces of the floating and rotating parts; the unit has a plurality of recesses, which are delimited outwardly by the floating part and inwardly by the rotating part, are arranged on the opposite axial sides of the groove so as to locally enlarge the radial distance with respect to the radial gap and are inwardly closed by the rotating part.

Abstract: A planet-carrier for an epicyclic gearing is provided with a ring having a plurality of plate sectors and a plurality of connection sectors, alternating with one another about a first axis; a connection structure connects in an angularly fixed manner the connection sectors to a rotating member or to a static member; the planet-carrier is also provided with a plurality of pins, which are fixed with respect to the plate sectors and protrude in opposite directions from the plate sectors along respective second axes, parallel and eccentric with respect to the first axis; each pin has two coaxial outer surfaces, adapted to support respective planet gears of the gearing and symmetrical to each other with respect to a symmetry plane orthogonal to the first axis; the plate sectors are asymmetrical with respect to this symmetry plane.

Abstract: An oil transfer unit has a rotating part extending along an axis, a stationary part provided with an oil mouth, and a floating part having a cylindrical surface fitted onto an outer cylindrical surface of the rotating part in a non-contact configuration; an annular groove is provided between the floating part and the rotating part to put the oil mouth into communication with an inner chamber of the rotating part; both sides of the groove are sealed by a hydrostatic seal defined by a radial gap between the cylindrical surfaces; the unit has at least one oil transfer tube, coupled to the stationary part and the floating part in a fluid-tight manner and with freedom of movement, and a connecting rod to prevent rotation of the floating part; the opposite ends of the connecting rod are coupled to the stationary part and floating part by respective spherical joints.