Patent classifications
F16H57/0456
Triple circuit lubrication device with increased reliability for a main power transmission gearbox of an aircraft
A triple circuit lubrication device for lubricating a mechanical system, the lubrication device being provided with two independent lubrication circuits, a tank common to both lubrication circuits and containing a lubrication liquid, and a tertiary circuit in which a tertiary liquid flows. Each lubrication circuit comprises pipes, and respective pressure sensors, pumps, heat exchangers, spray nozzles, and suction points for sucking up the lubrication liquid situated in the tank. The second suction point is situated below the high first suction point. The tertiary circuit comprises a third pump, a third pressure sensor, the second heat exchanger, and a third heat exchanger, thus serving to cool the lubrication liquid flowing through the second lubrication circuit.
LUBRICATING LIQUID MANIFOLD FOR A CRANKPIN OF AN EPICYCLIC GEAR TRAIN, GEARBOX AND AIRCRAFT
A lubricating liquid manifold for a crankpin of an epicyclic gear train. The epicyclic gear train is lubricated by a lubrication system conveying a first flow of a lubricating liquid towards the manifold and a second flow of the lubricating liquid towards a member to be lubricated. The manifold comprises a hollow body provided with an inlet port intended to receive the first flow and an outlet port designed such that the first flow is conveyed towards a guide device connected to the crankpin. The manifold comprises a barrier comprising a shoulder connected to the body and a deflector protruding radially outwards from the body so as to form, with the shoulder, a diversion space for diverting the second flow and preventing it from penetrating into the manifold.
Impeller for a planet carrier of an epicyclic speed reduction gear of a turbine engine
An impeller for a planet carrier of a epicyclic speed reduction gear of a turbine engine is fixed in rotation to the planet carrier and is rotatable about an axis of the reduction gear. The impeller has an annular shape about the axis and includes means for lubricating in particular planet gear bearings of the reduction gear. The lubricating means include an annular cavity located at the inner periphery of the impeller, wherein the impeller has an inner peripheral wall that closes the cavity in the radial direction. The impeller further includes an annular aperture that extends around the axis and opens in the axial direction into the cavity to supply lubricating oil thereto.
Branched lubricant line
A transmission includes at least one planetary gear stage with a planet carrier having a first toothing. The transmission further includes at least one lubricant line having a first outlet opening and a second outlet opening. The first toothing, together with a second toothing, forms a spline. The first outlet opening is configured to lubricate the spline, and the second outlet opening is configured to lubricate a sun gear of the planetary gear stage.
Differential with lubrication ports
Systems for a differential are provided. The differential includes two sets of pinion gears with an asymmetric split tooth profile. A case of the differential includes a plurality of lubrication ports which open adjacent to untoothed sections of one set of pinion gears and in a drive mode and an outboard axial load is exerted on the corresponding set of pinion gears.
METHOD FOR PRODUCING A CHANNEL IN A SHAFT TUBE
The invention relates to a method for producing a spray channel (4) on a shaft tube (1), via which with finished shaft tube (1) fluid (5) can be output from within the shaft tube (1) to the outside, having the steps introducing at least one through-opening (7) with a diameter D.sub.1≥1.5 mm into the shaft tube (1), arranging at least one additional element (8) in or on the through-opening (7) in such a manner that the spray channel (4) is at least partly formed by the additional element (8).
The invention also relates to a camshaft (2) having a shaft tube (1) produced with such a method.
GEAR ASSEMBLY FOR AERONAUTICAL ENGINE WITH LUBRICANT STORING POCKETS
A gear assembly for an aeronautical engine includes a first gear disposed at a centerline axis of the gear assembly, a second gear coupled to the first gear in adjacent radial arrangement to form a first mesh between the first gear and the second gear, a static portion coupled to the second gear in adjacent circumferential arrangement, the static portion defining a pocket, and a spraybar disposed within the static portion such that a supply opening of the spraybar is directed at the first mesh between the first gear and the second gear. The supply opening provides a flow of lubricant to the first mesh between the first gear and the second gear and at least a portion of the flow of lubricant is collected by the pocket. The flow of lubricant is continuously released from the pocket to the gear system.
Hydraulic pressure supply apparatus for automatic transmission
A hydraulic pressure supply apparatus for automatic transmission having a first and a second regulator valves 50, 52 that are installed in a first and a second oil passages 46, 48 that connect a hydraulic pump 44 for pumping and discharging hydraulic oil from a reservoir 42 and a plurality of hydraulic actuators and depressurize the hydraulic oil discharged from the pump to pressure required by the hydraulic actuators, a third and a fourth oil passages 56, 58 that convey discharged hydraulic oil to lubrication system 54 and an ejector 60 having a nozzle 60a connected to one of the third and fourth oil passages and an intake 60b connected to the reservoir 42 such that hydraulic oil merged at a diffuser 60c is conveyed to the lubrication system 54 through a fifth oil passage 62, hydraulic energy generated by the hydraulic pump can be effectively utilized in an automatic transmission having the hydraulic actuators and lubrication system.
TRANSMISSION LUBRICATING STRUCTURE OF HELICOPTER
A transmission lubricating structure includes: a main tank; an auxiliary tank; a common line to supply lubricating oil from the main or the auxiliary tank; a main line to introduce the lubricating oil in the main tank to the common line; an auxiliary line to introduce the lubricating oil in the auxiliary tank to the common line; a common nozzle configured to discharge the lubricating oil, supplied from the common line, to a transmission; a pump configured to supply the lubricating oil from the main tank to the common line; and a relay valve arranged lower than the auxiliary tank and higher than the common nozzle and provided upstream of the common line, the relay valve being configured to block the auxiliary line when the pump is operating and open the auxiliary line so the common line communicates with the auxiliary tank when the pump is in a stop state.
TRANSMISSION LUBRICATING STRUCTURE OF HELICOPTER
A transmission lubricating structure includes a power transmitting shaft, a main lubricating circuit, and an auxiliary lubricating circuit. The power transmitting shaft includes an ejection hole communicating an inside with an outside of the power transmitting shaft. The main lubricating circuit includes: a main nozzle having a nozzle hole through which lubricating oil supplied from a main tank is discharged to the internal space of the power transmitting shaft; and a hydraulic pump configured to supply the lubricating oil by pressure from the main tank to the main nozzle. The auxiliary lubricating circuit includes an auxiliary nozzle arranged lower than an auxiliary tank and higher than a lubrication target at the outside of the power transmitting shaft, the auxiliary nozzle being configured to drop the lubricating oil, supplied from the auxiliary tank by an own weight of the lubricating oil, toward the lubrication target.