Abstract: There is provided a blade angle feedback system for an aircraft-bladed rotor rotatable about a longitudinal axis and having an adjustable blade pitch angle. A feedback device is coupled to rotate with the rotor and to move along the axis with adjustment of the blade pitch angle. The feedback device comprises a body having position marker(s) embedded therein, the body made of a first material having a first magnetic permeability and the position marker(s) comprising a second material having a second magnetic permeability greater than the first. Sensor(s) are positioned adjacent the feedback device and configured for producing, as the feedback device rotates about the axis, sensor signal(s) in response to detecting passage of the position marker(s). A control unit is communicatively coupled to the sensor(s) and configured to generate a feedback signal indicative of the blade pitch angle in response to the sensor signal(s) received from the sensor(s).

Abstract: A machine includes a liquid lubrication system and a shaft, the shaft being rotatable about a rotation axis, the shaft including a first part, a second part engaged coaxially with the first part, and a journal bearing between the first part and the second part, the first part being rotatable relative to the second part about the rotation axis, a helical feature disposed between the first part and the second part and configured to define a helical pump between the first part and the second part, the pump being hydraulically connected to the liquid lubrication system, the journal bearing being disposed adjacent to the helical feature.

Abstract: There is provided a pitch control assembly for a rotor of an aircraft, the rotor rotatable about a longitudinal axis and having blades each rotatable about a span-wise axis to adjust a blade pitch angle thereof, the assembly comprising a plurality of position markers spaced circumferentially around the longitudinal axis and having lengths along the longitudinal axis which vary monotonically and incrementally, at least one sensor configured for producing at least one sensor signal in response to detecting a relative movement between the plurality of position markers and the at least one sensor, and a control unit communicatively coupled to the at least one sensor and configured to generate a feedback signal indicative of the blade pitch angle in response to the at least one sensor signal received from the at least one sensor.

Abstract: There is provided a rotor bow mitigation system and method for an aircraft engine. At least one value of at least one engine parameter prior to a shutdown of the engine is obtained, the at least one engine parameter comprising a first temperature internal to the engine. A second temperature external to the engine is measured and a motoring duration and a motoring interval for the engine are determined based on at least the first temperature and on the second temperature. Upon detecting a start indication for the engine, the engine is motored for the motoring duration and at the motoring interval.

Abstract: A blade angle feedback assembly for a variable-pitch rotor of an aircraft engine, the rotor rotatable about an axis and having rotor blades rotatable about respective spanwise axes to adjust a blade angle thereof, is provided. A sensor is configured to provide feedback on the blade angle of the rotor blades by detecting a relative movement between the sensor and a feedback device having at least one position marker thereon. The sensor comprises a magnet having a magnetic field and a first pole and a second pole opposite the first pole. A magnetic shield is configured to define a magnetic return path for at least a portion of a magnetic flux of the magnetic field exiting from the first pole of the magnet toward the second pole, the magnetic shield comprising at least one wall member spanning a distance of relative displacement between the feedback device and the sensor.

Abstract: A method of priming a pump includes supplying lubricant, via a priming flow path, into an interface defined between a first part of a shaft of the pump and a second part of the shaft coaxially engaged with the first part of the shaft to define the pump, the first part of the shaft rotatable about a rotation axis relative to the second part of the shaft, and supplying lubricant into the interface via a lubrication flow path that is different from the priming flow path. A method of lubricating an aircraft motor of an aircraft engine, and a machine for an aircraft engine are also described.

Abstract: A blade angle feedback system for an aircraft-bladed rotor rotatable about a longitudinal axis and having an adjustable blade pitch angle is provided. A feedback device is coupled to rotate with the rotor and to move along the axis with adjustment of the blade angle. At least one position marker is affixed to a core of the feedback device and extends along a direction angled relative to the axis. The core is made of a first material having a first magnetic permeability and the position marker comprises a second material having a second magnetic permeability greater than the first magnetic permeability. A sensor is positioned adjacent the feedback device and produces, as the feedback device rotates about the axis, a sensor signal in response to detecting passage of the position marker. A control unit generates a feedback signal indicative of the blade angle in response to the sensor signal.

Abstract: 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.

Abstract: A blade angle feedback assembly for an aircraft-bladed rotor, the rotor rotatable about a longitudinal axis and having an adjustable blade pitch angle, is provided. The assembly comprises a feedback device coupled to rotate with the rotor and to move along the longitudinal axis with adjustment of the blade pitch angle, the feedback device comprising a plurality of position markers circumferentially spaced around the feedback device, a plurality of sensors positioned adjacent the feedback device and each configured for producing a sensor signal in response to detecting passage of the position markers as the feedback device rotates about the longitudinal axis, the sensors circumferentially spaced around the feedback device and axially offset along the longitudinal axis, and a control unit communicatively coupled to the sensors and configured to generate a feedback signal indicative of the blade pitch angle in response to the sensor signals received from the sensors.

Abstract: A lubrication system for an aircraft engine includes an engine lubricant tank including at least a supply port hydraulically connectable to the aircraft engine, a lubricant makeup port, and an overfill port, an auxiliary lubricant tank, a lubricant makeup conduit hydraulically connecting the auxiliary lubricant tank to the lubricant makeup port. The lubricant makeup conduit includes a pump operable to move lubricant from the auxiliary lubricant tank to the lubricant makeup port, and an overfill conduit hydraulically connecting the overfill port to the auxiliary lubricant tank. A method of operating a lubrication system of an aircraft engine of an aircraft is also disclosed.

Abstract: A feedback device for use in a gas turbine engine, and methods and systems for controlling a pitch for an aircraft-bladed rotor, are provided. The feedback device is composed of a circular disk and a plurality of position markers. The circular disk is coupled to rotate with a rotor of the gas turbine engine, to move along a longitudinal axis of the rotor, and has first and second opposing faces defining a root surface that extends between and circumscribes the first and second faces. The plurality of position markers extend radially from the root surface, are circumferentially spaced around the circular disk, and extending along the longitudinal axis from a first end portion to a second end portion. At least part of the first end portion and/or of the second end portion comprises a material having higher magnetic permeability than that of a remainder of the position markers.

Abstract: A system and method for providing feedback for an aircraft-bladed rotor about a longitudinal axis and having an adjustable blade pitch angle. At least one position marker is provided at the rotor, extends along an axial direction, from a first end to a second end, and has varying magnetic permeability from the first end to the second end. At least one sensor is coupled to the rotor and configured for producing, as the rotor rotates about the longitudinal axis, at least one sensor signal in response to detecting passage of the at least one position marker. A control unit is communicatively coupled to the at least one sensor and configured to generate a feedback signal indicative of the blade pitch angle in response to the at least one sensor signal received from the at least one sensor.

Abstract: There is provided a dynamic motoring system and method for an aircraft engine. Motoring of the engine is initiated for an initial motoring duration and at an initial motoring interval. At least one engine parameter is measured in real-time during the motoring, the at least one engine parameter comprising a temperature of the engine. The initial motoring duration and the initial motoring interval are modified in real-time, based on a value of the at least one engine parameter during the motoring, to obtain a modified motoring duration and a modified motoring interval. The motoring continues for the modified motoring duration and at the modified motoring interval, with a speed of rotation of the engine being controlled using the modified motoring interval.

Abstract: A feedback device is coupled to rotate with a rotating component of an aircraft engine. The feedback device comprises a body having cavities defined therein and circumferentially spaced thereabout, each cavity configured to receive therein a position marker, the body made of a non-ferromagnetic material and the position markers comprising a ferromagnetic material. A sealing member is configured to be secured to the body for retaining the position markers within the cavities. At least one sensor is positioned adjacent the feedback device and configured for producing, as the feedback device rotates about a longitudinal axis with the rotating component, at least one sensor signal in response to detecting passage of the position markers. A processing unit is communicatively coupled to the at least one sensor and configured to determine a rotational speed of the rotating component from the at least one sensor signal received from the at least one sensor.

Abstract: There is provided a blade angle feedback system for an aircraft-bladed rotor rotatable about a longitudinal axis and having an adjustable blade pitch angle. A feedback device is coupled to rotate with the rotor and to move along the axis with adjustment of the blade pitch angle. The feedback device comprises a body having position marker(s) embedded therein, the body made of a first material having a first magnetic permeability and the position marker(s) comprising a second material having a second magnetic permeability greater than the first. Sensor(s) are positioned adjacent the feedback device and configured for producing, as the feedback device rotates about the axis, sensor signal(s) in response to detecting passage of the position marker(s). A control unit is communicatively coupled to the sensor(s) and configured to generate a feedback signal indicative of the blade pitch angle in response to the sensor signal(s) received from the sensor(s).

Abstract: A sensor signal comprising a first signal pulse having a first voltage amplitude and a second signal pulse having a second voltage amplitude greater than or substantially equal to the first voltage amplitude is obtained from a sensor positioned adjacent a feedback device coupled to rotate with an aircraft-bladed rotor about a longitudinal axis and to move along the axis with adjustment of the rotor's blade pitch angle. The feedback device comprises a reference feature configured to generate the second signal pulse and varying detectable feature(s) configured to generate the first signal pulse and to cause a change in the first voltage amplitude as a function of an axial position of the feedback device along the axis. A voltage ratio is determined based on the first voltage amplitude and the second voltage amplitude, and the axial position of the feedback device is determined from the voltage ratio.

Abstract: A plate cooler or heat exchanger includes a channel plate defining first cooling channels on a first side of the channel plate and second cooling channels on a second side of the channel plate opposite to the first side. The first cooling channels are arranged side-by-side in a first direction of coolant flow from a first common inlet to a first outlet. The second cooling channels are arranged side-by-side in a second direction of coolant flow from a second common inlet separate from the first common inlet to a second outlet separate from the first outlet. The second direction of coolant flow is transverse or counter to the first direction of coolant flow.

Abstract: A feedback device for use in a gas turbine engine, and methods and systems for controlling a pitch for an aircraft-bladed rotor, are provided. The feedback device is composed of a circular disk and a plurality of position markers. The circular disk is coupled to rotate with a rotor of the gas turbine engine, to move along a longitudinal axis of the rotor, and has first and second opposing faces defining a root surface that extends between and circumscribes the first and second faces. The plurality of position markers extend radially from the root surface and are circumferentially spaced around the circular disk. The position markers have a top surface elevated with respect to the root surface and opposing first and second side surfaces. The side surfaces of the position markers have a curved concave profile extending toward the root surface.

Abstract: A heat exchanger for aircraft electronic components includes a first plate having channels arranged with side-by-side channel inlets fed from a common fluid supply manifold extending to the channel inlets from a manifold inlet. The channel inlets include a first set of inlets spaced further away from the manifold inlet than a second set of inlets. The fluid supply manifold has a flow divider positioned fluidly between the manifold inlet and the channel inlets. The flow divider is configured in use to direct heat exchange fluid entering the manifold from the manifold inlet preferentially toward the first set of inlets. A second plate is coupled with the first plate to seal the channels and the fluid supply manifold.

Abstract: There is provided a blade angle feedback system for an aircraft-bladed rotor rotatable about a longitudinal axis and having an adjustable blade pitch angle. A feedback device is coupled to rotate with the rotor and to move along the axis with adjustment of the blade pitch angle. The feedback device comprises a body having position marker(s) embedded therein, the body made of a first material having a first magnetic permeability and the position marker(s) comprising a second material having a second magnetic permeability greater than the first. Sensor(s) are positioned adjacent the feedback device and configured for producing, as the feedback device rotates about the axis, sensor signal(s) in response to detecting passage of the position marker(s). A control unit is communicatively coupled to the sensor(s) and configured to generate a feedback signal indicative of the blade pitch angle in response to the sensor signal(s) received from the sensor(s).