A pump that can be a gear pump that drives a rotating body of an aircraft turbine engine such as a fan shaft, is set in rotation always in the same direction, by virtue of a transmission including an oblique double gear formed by a toothed wheel on the same side as the rotating body and meshing with two pinions connected to a shaft driving the pump through free-wheels with identical driving directions, whereas the pinions have opposite directions of rotation.

A pump that can be a gear pump that drives a rotating body of an aircraft turbine engine such as a fan shaft, is set in rotation always in the same direction, by virtue of a transmission including an oblique double gear formed by a toothed wheel on the same side as the rotating body and meshing with two pinions connected to a shaft driving the pump through free-wheels with identical driving directions, whereas the pinions have opposite directions of rotation.

An aircraft engine, has: a shaft rotatable about a central axis and engaged at an end thereof to a rotatable load via splines; a reference tube extending around the shaft and having a first end secured to the shaft and a second end free relative to the shaft for measuring a deformation of the shaft, the reference tube defining at least one tube aperture; an oil nozzle defining an exit flow axis intersecting the at least one tube aperture, the shaft defining at least one shaft aperture through the shaft, an oil flow path extending from the oil nozzle to the splines; and a drain outlet located radially outwardly of an inlet of the at least one shaft aperture for outputting excess oil out of an annular gap defined between the shaft and the reference tube.

There is provided a system and method for detecting excess flow in an engine fluid system, the method comprising sensing a temperature of a fluid flowing in a fluid line of the fluid system, the fluid line located downstream of a fluid flow restrictor configured to receive the fluid from a source upstream thereof and to flow the fluid from the source into the fluid line downstream thereof, comparing the temperature to a temperature threshold, and when the temperature is beyond the temperature threshold, detecting excess flow of the fluid in the fluid line and outputting an excess flow indication accordingly.

An oil system of a gas turbine engine, includes a first oil circuit and a second oil circuit. Via of the oil circuits, oil is supplied to a hydraulic load of a transmission of the engine. Downstream of the load, in the region of a return of the transmission, oil is introduced into the oil circuits from the transmission. Upstream of the load, in the region of inlets, oil can be introduced into the transmission from the oil circuits. The second oil circuit includes an oil accumulator between the return and the inlet of the second oil circuit. The oil accumulator is configured such that, according to a feed pressure of the oil upstream of the inlet oil is stored in the oil accumulator or oil stored in the oil accumulator is fed toward the inlet.

An oil system of a gas turbine engine, includes a first oil circuit and a second oil circuit. Via of the oil circuits, oil is supplied to a hydraulic load of a transmission of the engine. Downstream of the load, in the region of a return of the transmission, oil is introduced into the oil circuits from the transmission. Upstream of the load, in the region of inlets, oil can be introduced into the transmission from the oil circuits. The second oil circuit includes an oil accumulator between the return and the inlet of the second oil circuit. The oil accumulator is configured such that, according to a feed pressure of the oil upstream of the inlet oil is stored in the oil accumulator or oil stored in the oil accumulator is fed toward the inlet.

A system for supplying lubricant to a component of a gas turbine engine having a fan shaft is provided. The system includes a pump drivably couplable to the fan shaft for pumping lubricant to the component. The pump includes an inlet for receiving lubricant from a lubricant source, an outlet for outputting lubricant to the component and a swashplate movable between at least a first position and a second position. The system also includes a swashplate actuator for actuating the swashplate between the first position and the second position according to whether the fan shaft is rotating in a forward direction or a reverse direction opposite to the forward direction.

A system for supplying lubricant to a component of a gas turbine engine having a fan shaft is provided. The system includes a pump drivably couplable to the fan shaft for pumping lubricant to the component. The pump includes an inlet for receiving lubricant from a lubricant source, an outlet for outputting lubricant to the component and a swashplate movable between at least a first position and a second position. The system also includes a swashplate actuator for actuating the swashplate between the first position and the second position according to whether the fan shaft is rotating in a forward direction or a reverse direction opposite to the forward direction.

A gas turbine engine, has: a shaft rotatable about a central axis and engaged at an end thereof to a rotatable load via a spline; a reference tube circumferentially extending around the shaft, the reference tube secured at a first end to the shaft for rotation therewith and a second end free relative to the shaft for measuring a deformation of the shaft, the reference tube defining at least one tube aperture therethrough; an oil nozzle fluidly connected to a source of lubricant, the oil nozzle defining an exit flow axis intersecting the at least one tube aperture for injecting oil through the reference tube, the shaft defining at least one shaft aperture extending therethrough, the oil nozzle aligned with the spline via the at least one tube aperture and the at least one shaft aperture.

A bearing housing for supporting a bearing of a gas turbine engine. The bearing housing comprises an annular body extending around an axis and having an oil inlet and an oil outlet. The bearing housing further comprises an oil manifold integrated into the annular body, the oil manifold having an inner oil channel defined in the annular body and extending circumferentially around the axis, the inner oil channel in fluid communication with the oil inlet and at least one oil jet directed towards the bearing.