Abstract: A transmission controller comprises an actuator which changes a roller position of a toroidal CVT to adjust the tilt motion angle of a power roller; a tilt motion angle information generation unit which generates information of the tilt motion angle; a position estimation unit which derives an estimated value of the roller position; and a position control unit which derives an operation command value of the actuator so that a deviation between a command value of the roller position and the estimated value of the roller position is cancelled. The position estimation unit is configured to derive the estimated value based on the information of the tilt motion angle which is generated by the tilt motion angle information generation unit, and the operation command value, and to compensate the estimated value based on an environment parameter which affects an operation of the power roller.

Abstract: An electric power generating device for an aircraft, which is driven by an output of an aircraft engine, comprises an input shaft to which a driving force of the engine is transmitted; a transmission arranged with the input shaft; an electric power generator arranged with the input shaft and the transmission and driven by an output of the transmission; a driving force transmission mechanism disposed on a first end side of the input shaft in an axial direction thereof, the driving force transmission mechanism being configured to transmit the output from the transmission to the electric power generator; and a casing including a mounting section on the first end side of the input shaft in the axial direction, wherein the transmission includes an input section provided on a second end side of the input shaft in the axial direction, the input section being configured to receive as an input a rotational driving force from the input shaft, and an output section provided on the first end side of the input shaft in th

Abstract: A hydraulic circuit for controlling a continuously variable transmission includes: a lubrication line provided with a lubrication pump, and configured to supply oil from an oil tank to a lubrication target by using the lubrication pump; a high pressure line provided with a high pressure pump, branching from the lubrication line, and configured to supply, by using the high pressure pump, high-pressure oil to a hydraulic control section that controls oil pressure of the oil to be supplied to the continuously variable transmission; and a cooling return line branching from the high pressure line, and configured to return the oil to a downstream side of the lubrication pump in the lubrication line, a portion of the cooling return line forming a cooling path to cool a generator connected to the continuously variable transmission.

Abstract: In a transmission device, a power roller transmits a rotational driving force from an input disc to an output disc in a transmission ratio (transmission gear ratio) corresponding to a tilt motion angle. The power roller allows the transmission ratio to be changed in such a manner that the position of the trunnion on which the power roller is tiltably supported is changed by a trunnion drive mechanism. Hydraulic oil is supplied from a hydraulic pump to the trunnion drive mechanism via a direction selector valve. The direction selector valve selects a flow direction of the hydraulic oil to supply the hydraulic oil to a speed reduction chamber or a speed increase chamber of the trunnion drive mechanism, and discharge the hydraulic oil from the other. In a case where a discharge condition is met, the controller controls a movement of the discharge valve to discharge the hydraulic oil from the speed increase chamber.

Abstract: An electric power generating device (1) capable of suppressing an increase of a frontal surface area of an aircraft engine includes a transmission (22) connected with a rotary shaft (9) of the engine (E), an electric power generator (34) driven by an output of the transmission (22), an input shaft (27) having a shaft axis extending in a direction crossing the rotary shaft (9) and connected with the rotary shaft (9), and a transmitting mechanism (21) connected with the input shaft (27) to drive the transmission (22) about an axis extending in a direction perpendicular to the input shaft (27). The transmission (22) and the electric power generator (34) are disposed spaced a distance from each other in a direction circumferentially of the rotary shaft (9).

Abstract: An aircraft engine apparatus (1) includes: a rotating shaft (6); a fan (10) driven by the rotating shaft; a fan case surrounding the fan; aircraft equipment (28) disposed upstream of the fan and, in a radial direction of the rotating shaft, disposed inward of a peripheral edge of the fan case; a casing (2) that accommodates at least part of the rotating shaft and supports the fan case; a first motive force transmitter (9) coupled to the rotating shaft and the fan; a second motive force transmitter (32) disposed inward of the first motive force transmitter in the radial direction of the rotating shaft and coupled to the rotating shaft and the aircraft equipment; and a support member (12) disposed between the first motive force transmitter and the second motive force transmitter, the support member coupling the casing and the aircraft equipment and supporting the aircraft equipment.

Abstract: An aircraft engine apparatus (1) includes: a rotating shaft (6); a fan (10) driven by the rotating shaft; a fan case surrounding the fan from outside in a radial direction of the rotating shaft; a nose cone (13) disposed upstream of the fan; a casing (2) that accommodates at least part of the rotating shaft and supports the fan case; a first motive force transmitter (9) that transmits motive force of the rotating shaft to the fan; and a support member (12) disposed inward of the first motive force transmitter in the radial direction, the support member coupling the nose cone to the casing such that the support member supports the nose cone in a stationary state.

Abstract: To provide an aircraft engine in which an accessory can be directly supported with no accessory gearbox intervening to thereby suppress an increase in size thereof, the aircraft engine (E) includes a take-out shaft (11) having a first end portion, connected with an engine rotary shaft (9) and extending in a radially outward direction, and also having a second end portion connected with an accessory (1), and a mounting pad (12) provided in an engine main body (EB) and to which the accessory (1) is fitted. The mounting pad (12) forms an outer perimeter of an opening (48) through which the take-out shaft (11) extends. The opening (48) is sealed by a covering (47), through which the take-out shaft (1) extends, and a sealing member (49) to seal between the covering (47) and the take-out shaft (11).

Abstract: In a continuously variable transmission including: a first transmission unit including a first input disc and a first output disc disposed coaxially and a power roller tiltably interposed between these discs; and a second transmission unit disposed coaxially with the first transmission unit, including a second input disc and a second output disc disposed coaxially and a second power roller tiltably interposed between these discs, and disposed such that a back surface of the second input disc is opposed to a back surface of the first input disc, a tubular back surface cylinder wall is provided on each of the back surfaces of the first input disc and the second input disc so as to project therefrom.

Abstract: In a toroidal continuously variable transmission including at least one transmission unit including: an input disc and an output disc disposed coaxially; and a power roller tiltably interposed between the input disc and the output disc and configured to transmit a driving force from the input disc to the output disc, an integrally rotating member disposed so as to be spaced apart in an axial direction from at least one disc of the input disc and the output disc of each transmission unit and configured to rotate together with the at least one disc, and an annular interposed member provided between the at least one disc and the integrally rotating member and configured to rotate together with the at least one disc, are provided, and the interposed member is formed with a balance adjustment portion capable of adjusting weight balance in a circumferential direction.

Abstract: A power generation unit is connected with an engine rotary shaft via an accessory gearbox. A rotor extends through the accessory gearbox and a drive gear is disposed at an intermediate portion of the rotor for driving the latter. Permanent magnet elements are mounted on opposite side portions with the intermediate portion intervening therebetween, and stator coils are disposed so as to confront respective outer peripheries of the permanent magnet elements.

Abstract: A hydraulic circuit for controlling a continuously variable transmission includes: a lubrication line provided with a lubrication pump, and configured to supply oil from an oil tank to a lubrication target by using the lubrication pump; a high pressure line provided with a high pressure pump, branching from the lubrication line, and configured to supply, by using the high pressure pump, high-pressure oil to a hydraulic control section that controls oil pressure of the oil to be supplied to the continuously variable transmission; and a cooling return line branching from the high pressure line, and configured to return the oil to a downstream side of the lubrication pump in the lubrication line, a portion of the cooling return line forming a cooling path to cool a generator connected to the continuously variable transmission.

Abstract: A toroidal-type stepless transmission includes: at least a pair of an input disc and an output disc; a power roller tiltably provided between the pair of the input disc and the output disc, the power roller being configured to transmit a driving force from the input disc to the output disc; and disc shrouds covering the input disc and the output disc, respectively. Each of the disc shrouds has an outer peripheral portion formed with an oil discharge groove configured to discharge an oil within each disc shroud to the outside, the oil discharge groove penetrating from an inner surface of the disc shroud to an outer surface of the disc shroud and extending in a circumferential direction of the disc shroud.

Abstract: A lubricating device for a gear train (5) including a plurality of gears meshing with each other includes a shroud (7) configured to cover the gear train (5) and a housing (9) configured to cover the shroud (7). The shroud (7) includes: an oil supply nozzle (25) configured to supply oil (OL) to a meshing position (21) of the gear train (5); and oil-drain ports (41) through which the oil (OL) is discharged from the shroud. The housing (9) includes, at its lower part, a draw-out port (43) through which the oil (OL) discharged from the oil-drain ports (41) is drawn to the outside of the housing. Guide members (47) are provided between the shroud (7) and the housing (9). The guide members (47) guide the oil (OL) discharged from the respective oil-drain ports (41) of the shroud (7) such that the oil (OL) flows downward through space (S) between the shroud (7) and the housing (9).

Abstract: A power generation unit is connected with an engine rotary shaft via an accessory gearbox. A rotor extends through the accessory gearbox and a drive gear is disposed at an intermediate portion of the rotor for driving the latter. Permanent magnet elements are mounted on opposite side portions with the intermediate portion intervening therebetween, and stator coils are disposed so as to confront respective outer peripheries of the permanent magnet elements.

Abstract: A gear train lubricating device configured to supply lubricating oil OL to a gear included in a gear train is provided. The gear train lubricating device includes: a shroud covering, among components constituting the gear, at least teeth of the gear; and a lubricating oil supply port through which the lubricating oil OL is supplied to a meshing position of the gear. The shroud has an outlet port formed therein, through which the supplied lubricating oil OL is discharged. The outlet port is formed in a portion of the shroud that is positioned radially outward from the gear, such that the outlet port is disposed at an angular position that is 90°±15° forward from the meshing position in a rotation direction R1 of the gear.

Abstract: Provided is a planetary gear reducer including: a sun gear fixed concentrically to a power input shaft; a plurality of planet gears meshing with the sun gear; a ring gear meshing with the planet gears; a planet carrier configured to support a plurality of planet shafts, each of which is a rotational axis of a corresponding one of the planet gear, and to output revolution of the plurality of planet gears as first power; and a cylindrical support connected to the ring gear, non-rotatable relative to the ring gear, and configured to output rotation of the ring gear as second power. The cylindrical support includes, at one part along the direction of a central axis, a flexible structure which is curved radially inward and has a V-shaped longitudinal section. This configuration improves rigidity and prevents misalignment without increasing the weight of the gear reducer.

Abstract: A planetary gear system (1) includes: a sun gear (5) having external teeth; a plurality of planet gears (7) having external teeth, each planet gear meshing with the sun gear; a ring gear (9) having internal teeth, the ring gear meshing with the planet gears; and a baffle unit (35) disposed between the planet gears which are adjacent to each other, the baffle unit having side faces (37F, 37R) positioned near the respective planet gears. The baffle unit (35) has: oil supply holes (47) which are formed in a tip portion (41) facing an outer periphery of the sun gear (5) and which jet out lubricating oil (OL) to mesh positions (43, 45) between the sun gear and the planet gears; and a collection opening (55) which is formed in at least one of the side faces and through which the lubricating oil (OL) that has been jetted out is collected into the baffle unit (35).

Abstract: A planetary gear system (1) includes: a sun gear (5) having external teeth; a ring gear (9) having internal teeth; at least one planet gear (7) having external teeth meshed with the external teeth of the sun gear and the internal teeth of the ring gear. The planet gear (7) has, at its outer circumferential face, the external teeth which are formed of a pair of sets of teeth aligned in an axial direction and an annular groove (17) which is formed between the pair of sets of teeth.

Abstract: An electric power generating device (1) capable of suppressing an increase of a frontal surface area of an aircraft engine includes a transmission (22) connected with a rotary shaft (9) of the engine (E), an electric power generator (34) driven by an output of the transmission (22), an input shaft (27) having a shaft axis extending in a direction crossing the rotary shaft (9) and connected with the rotary shaft (9), and a transmitting mechanism (21) connected with the input shaft (27) to drive the transmission (22) about an axis extending in a direction perpendicular to the input shaft (27). The transmission (22) and the electric power generator (34) are disposed spaced a distance from each other in a direction circumferentially of the rotary shaft (9).