Patent classifications
F16H57/0486
GEARED GAS TURBINE ENGINE WITH COMBINED SPRAY BAR AND SCAVENGE COMPONENT
A gear reduction includes a sun gear that engages a plurality of planet gears mounted on a carrier. The planet gears are engaged with a ring gear. The ring gear is fixed against rotation such that rotation of the sun gear causes rotation of the planet gears to cause rotation of the carrier. There are spray bars positioned circumferentially between adjacent ones of the planet gears. The spray bars have jet openings, such that lubricant can be passed directly onto teeth on the sun gear. One of the side faces has a plurality of windows such that oil can be scavenged. There are side surfaces between plurality of windows that do not have an opening. A gas turbine engine and a spray bar are also disclosed.
Planetary gear and gas turbine engine
A planetary gearbox includes a planet carrier, with a planetary gear rotatably disposed on the planet carrier, and a gear that meshes with the planetary gear, as well as a gas turbine engine having such a planetary gearbox. The planet carrier has an oil supply installation including a supply line for oil to an opening. The oil is directed out of the opening in the direction of the planetary gear and/or the gear. The oil supply installation in relation to a primary rotating direction of the planetary gear and/or the gear in front of the opening includes a shielding region which protrudes from an external side of the oil supply installation and which by way of the external side of the oil supply installation on a side that faces the primary rotating direction of the planetary gear and/or the gear, delimits an oil collection groove.
Variable speed and reversible dual path fan drive system
A drive system includes a planetary gear set having first and second rotatable input members connected in driven relation with respective first and second power sources, and a rotatable output member connected in driving relation with a working piece, the first and second rotatable input members being connected in differentially rotatable communication with the output member. The input members are operable to vary the rotation and direction of the output member and the connected working piece. In an aspect, the output member is rotatable about an axis for driving the working piece, and the first and second input members are also rotatable about the axis. In a further aspect, the first and second input members include coupling regions for coupling the first and second power sources on-axis with the drive system. In a further aspect, the second power source is a hydraulic input motor concentric with the first input member.
Gearboxes for aircraft gas turbine engines
The present disclosure relates to gearboxes for aircraft gas turbine engines, in particular to arrangements for journal bearings such gearboxes, and to related methods of operating such gearboxes and gas turbine engines. Example embodiments include a gearbox for an aircraft gas turbine engine, the gearbox comprising: a sun gear; a plurality of planet gears surrounding and engaged with the sun gear; and a ring gear surrounding and engaged with the plurality of planet gears, each of the plurality of planet gears being rotatably mounted around a pin of a planet gear carrier with a journal bearing having an internal sliding surface on the planet gear and an external sliding surface on the pin.
TURBOMACHINES AND EPICYCLIC GEAR ASSEMBLIES WITH LUBRICATION CHANNELS
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.
MECHANICAL PART FOR AN AIRCRAFT TURBOMACHINE
A mechanical part for an aircraft turbomachine is made of metal and includes at least one profiled surface configured to ensure an oil flow during operation. The surface has a hydrophobic and/or lipophobic coating or a surface texturing rendering the surface hydrophobic and/or lipophobic.
MECHANICAL PART FOR AN AIRCRAFT TURBOMACHINE AND CORRESPONDING TURBOMACHINE
A mechanical part for an aircraft turbomachine, the mechanical part being made of metal and comprising at least one profiled surface configured to ensure an oil flow during operation. According to the invention, the surface includes a more hydrophobic and/or lipophobic coating than the surface or a surface texturing rendering the surface more hydrophobic and/or lipophobic
Power transmitting system of vehicle
A vehicular power transmitting system including a power transmitting member, an oil pump, and an oil piping assembly, and the oil piping assembly includes an oil piping body having an oil inlet and fixed, and a branch pipe. The branch pipe has a width direction parallel to a longitudinal direction of the oil piping body, and includes proximal and distal end portions. The proximal end portion is connected to the oil piping body, and the distal end portion has a delivery nozzle from which the oil is delivered toward the lubricated portion. The branch pipe has an opening formed in the proximal end portion, for communication of the branch pipe with the oil piping body, the opening having a dimension in a width direction of the branch pipe, which dimension is larger than a dimension of the distal end portion in the width direction of the branch pipe.
Lubrication arrangement for a transmission
A lubrication arrangement includes at least one housing, at least one shaft, at least one bearing system configured to hold the at least one shaft in the at least one housing and to permit the at least one shaft to rotate, lubricant distributed in the at least one housing with the rotation of the at least one shaft, and a lubricant deflector provided in a stationary manner relative to the at least one housing above the at least one shaft. The lubricant strikes against the lubricant deflector and, by action of gravity, the lubricant is conducted to the at least one bearing system of the at least one shaft so that the at least one bearing system is supplied with the lubricant.
Lubrication Distribution System
A lubrication distribution system is provided for mechanical systems, including gearboxes, to evenly and precisely apply lubricant to system structures during operation. The system includes a rotating lubrication distribution component that functions both to pump and to precisely direct lubricant. Machined locator elements enable accurate positioning of the rotating lubrication distribution component within the system. A plurality of lateral ports and surface features in the rotating lubrication distribution component receive and distribute lubricant transferred during rotation from one or more lubricant collection components with profiled lubricant transfer elements that enables collection of lubricant from eddies produced by profiles of the lubricant transfer elements during rotation of the rotating lubrication distribution component. Collected lubricant is directed into the rotating lubrication distribution component ports and distributed evenly and precisely to mechanical system or gearbox structures requiring lubrication. An existing gearbox thrust bearing may be modified to receive and precisely distribute lubricant.