An apparatus is provided for providing access to one or more axial proximity probes for monitoring axial position of thrust collars of a pump shaft to enable improved adjustment of the axial proximity probes by the pump operator. The apparatus includes a plurality of side walls configured to surround one or more axial proximity probes configured to measure axial position of one or more thrust collars in a pump bearing housing, at least one access window formed through at least one side wall of the apparatus configured to provide access the one or more axial proximity probes and at least one removable access plate configured to cover the at least one access window.

An aircraft oil management system includes a generator, pump, and pump control system. The generator is mechanically coupled to a prime mover via a the rotor shaft and is configured to output three-phase power. The pump is mechanically decoupled from the rotor shaft and delivers oil to the generator. The pump control system drives the pump independent of a rotational speed of the rotor shaft.

An aircraft oil management system includes a generator, pump, and pump control system. The generator is mechanically coupled to a prime mover via a the rotor shaft and is configured to output three-phase power. The pump is mechanically decoupled from the rotor shaft and delivers oil to the generator. The pump control system drives the pump independent of a rotational speed of the rotor shaft.

A system. The system includes a valve assembly. The valve assembly includes a first port, a second port fluidically couplable with the first port upon application of negative pressure at the first port, a third port fluidically couplable with the first port upon application of positive pressure at the first port, and a first check valve positioned between the first port and the second port. The system also includes a second check valve fluidically couplable with the third port upon the application of the positive pressure at the first port. The second check valve is positioned external to the valve assembly.

A system. The system includes a valve assembly. The valve assembly includes a first port, a second port fluidically couplable with the first port upon application of negative pressure at the first port, a third port fluidically couplable with the first port upon application of positive pressure at the first port, and a first check valve positioned between the first port and the second port. The system also includes a second check valve fluidically couplable with the third port upon the application of the positive pressure at the first port. The second check valve is positioned external to the valve assembly.

A lubricant injector includes an injector body having an inlet port fluidly coupleable with a lubricant supply, an outlet port fluidly coupleable with a lubrication point, a piston chamber and a valve chamber. A piston is disposed within the piston chamber and defines a measuring section and an actuating section, the piston being linearly displaceable along an axis through the piston chamber so as to inversely vary the volume of the chamber measuring section and the volume of the chamber actuating section. A valve member disposed within the valve chamber is displaceable along an axis through the valve chamber between a first position, at which the inlet port is fluidly coupled with the piston chamber actuating and measuring sections, and a second position at which the inlet port is fluidly coupled with the piston chamber actuating section and the outlet port is fluidly coupled with the piston chamber measuring section.

The invention relates to a system (1) for lubricating an aeronautical engine (5) and a reduction gearbox (4) associated with the engine (5), the system (1) comprising an oil reservoir (2) feeding at least one first supply pump (3) supplying a first circuit (6) of the gearbox (4) opening into at least one chamber (4a) of the gearbox (4) and, in parallel, a second circuit (7) of the engine (5) opening into chambers (5a) of the engine (5). The second circuit (7) comprises a jet pump (9) of variable cross section supplied at least by the first supply pump (3), bypassing the first circuit (6), a second driven supply pump (10) being integrated into the second circuit (7) downstream of the jet pump (9), a portion of a flow (Qp) in the first circuit (6) being drawn off by the jet pump (9) to supply the second circuit (7).

A method for lubricating a sealed bearing providing a first ring and a second ring capable of rotating concentrically relative to one another, and seals delimiting together with the first and second rings a sealed chamber. The method includes a removing a first predetermined quantity of lubricant from the sealed chamber until the pressure in the sealed chamber reaches a first pressure value, and then injecting a second predetermined quantity of lubricant in the sealed chamber until the pressure in the sealed chamber reaches a second pressure value, the first pressure value and the second pressure value being determined so that the pressure inside the sealed chamber remains within a predetermined interval, the boundaries of the interval being determined according to characteristics of the seals so that the sealed chamber remains waterproof to the lubricant when lubricant is removed from or injected in the sealed chamber.

A fluid system of a machine. The fluid system includes a fluid reservoir, a pump coupled to the fluid reservoir, a filter coupled to the pump and a valve assembly. The valve assembly includes a first port, a second port coupled to the first port and to the fluid reservoir, a third port coupled to the first port, and a first check valve positioned between the first port and the second port. The fluid system further includes a second check valve positioned between the filter and the third port.

Provided are: a lubricating device for a bearing; and an exhaust turbosupercharger, wherein a bearing device (36) is provided with a housing (15) with a hollow shape, and journal bearings (21, 22) which rotatably support a rotary shaft (14) arranged inside the housing (15), the bearing device (36) being further provided with: a third feeding passage (43) and a fourth feeding passage (44) through which lubricant is fed toward outer circumferential surfaces (21b, 22b) of the journal bearings (21, 22); a sixth feeding passage (46) through which lubricant is fed toward a space section (16A) between the journal bearings (21, 22); and a guide section which guides, toward inner circumferential surfaces (21c, 22c) of the journal bearings (21, 22), the lubricant fed from the sixth feeding passage (46) to the space section (16A).