An elevator system has an elevator shaft, an elevator car and a drive device for displacing the elevator car within the elevator shaft. The drive device is a linear motor that has a stationary part secured to a shaft wall of the elevator shaft and a movable part secured to the elevator car. The drive device has an air bearing between the stationary part and the movable part that keeps the stationary part spaced apart from the movable part via an air gap therebetween.

Gearboxes for aircraft gas turbine engines, in particular arrangements for journal bearings such gearboxes, and related methods of operating such gearboxes and gas turbine engines. A gearbox for an aircraft gas turbine engine includes: 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.

A seal assembly (10, 110) has an inner seal carrier (14, 114) with seals (16, 116, 18, 118), an outer carrier (30, 130) with inner curved surface (144) matching an outer curved surface (146) of the inner seal carrier for angular pitch adjustment of 3° to 5° for the inner seal carrier within the outer carrier, a flexible seal (36, 136) between the outer carrier and the bearing housing (28, 128), and oil within a cavity (20, 120) between the seals, preferably above atmospheric pressure. Shoulder bolts (140) allow lateral movement of the seal assembly with respect to the bearing housing. The seal assembly allows for misalignment and lack of parallelism of the shaft relative to the bearing housing whilst preventing contamination of the bearing.

A sliding member of the present invention includes a coating on a base material. The coating contains hard metal particles and corrosion-resistant metal particles that have hardness lower than that of the hard metal particles. The hard metal particles contain particles that have at least Vickers hardness of 600 Hv or higher. The corrosion-resistant metal particles are made of at least one kind of metal selected from the group consisting of copper (Cu), cobalt (Co), chromium (Cr), and nickel (Ni), or are made of an alloy containing said metal. The coating has a cross section in which the hard metal particles are dispersed in an island manner in a particle aggregate of the corrosion-resistant metal particles and in which an area ratio of the corrosion-resistant metal particles is 30% or larger. Thus, corrosion of the hard metal particles in the coating is prevented, whereby the sliding member maintains wear resistance for a long time.

Gearboxes for aircraft gas turbine engines, in particular arrangements for journal bearings such gearboxes, and related methods of operating such gearboxes and gas turbine engines. A gearbox for an aircraft gas turbine engine includes: 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.

A seal assembly (10, 110) has an inner seal carrier (14, 114) with seals (16, 116, 18, 118), an outer carrier (30, 130) with inner curved surface (144) matching an outer curved surface (146) of the inner seal carrier for angular pitch adjustment of 3° to 5° for the inner seal carrier within the outer carrier, a flexible seal (36, 136) between the outer carrier and the bearing housing (28, 128), and oil within a cavity (20, 120) between the seals, preferably above atmospheric pressure. Shoulder bolts (140) allow lateral movement of the seal assembly with respect to the bearing housing. The seal assembly allows for misalignment and lack of parallelism of the shaft relative to the bearing housing whilst preventing contamination of the bearing.

A journal shaft for a journal bearing assembly of an aircraft engine includes a shaft body extending along a longitudinal axis. The shaft body has a radially outer surface and a radially inner surface radially spaced apart from the longitudinal axis to define an inner cavity. An oil pocket is defined in the radially outer surface. One or more passages extend through the shaft body from the radially inner surface to the oil pocket to provide fluid communication between the inner cavity and the oil pocket. The oil pocket includes a radially inner base surface and interconnecting transition surfaces extending between the radially inner base surface of the oil pocket and the radially outer surface of the shaft body. The interconnecting transition surfaces form a fluid-dynamically smooth and edgeless transition to the radially outer surface of the journal shaft.

An apparatus and a method are shown for removing or moving a viscous fluid such as grease from a first unit such as a bearing e.g. a ball bearing to a second unit via a hose or pipe. The apparatus includes a hose or pipe (7) through which the viscous fluid is pumped during operation from an outlet (11) of the first unit (1) to an inlet (10) of the second unit (2), wherein the apparatus further includes a pump connected to the hose or pipe (7) in such a way that the viscous fluid during operation is moved through the hose or pipe (7), and the hose or pipe (7) includes an inlet (8) for gas such as air, and the flow of gas through the inlet (8) is controlled by a valve (9).

Gearboxes for aircraft gas turbine engines, in particular arrangements for journal bearings such gearboxes, and related methods of operating such gearboxes and gas turbine engines. A gearbox for an aircraft gas turbine engine includes: 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.

Gearboxes for aircraft gas turbine engines, in particular arrangements for journal bearings such gearboxes, and related methods of operating such gearboxes and gas turbine engines. A gearbox for an aircraft gas turbine engine includes: 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.