Abstract: The coupling can have a female member configured to rotate around an axis, defining an axial recess, and having a plurality of connections circumferentially arranged along a radially inner face; a male member extending inside the axial recess concentrically to the female member and having a plurality of connections circumferentially arranged along a radially outer face; and a plurality of circumferentially arranged links, each link having an inner end engaged with a corresponding one of the male member connections, and an outer end engaged with a corresponding female member connection, the links being slanted off the radial orientation, with the inner end being circumferentially offset from the outer end, the links subjected to compression when transmitting torque between the female member and male member.

Abstract: The heat exchanger includes an inner casing extending circumferentially around the central axis and securable to the shaft for concurrent rotation therewith, and an outer casing extending circumferentially around the central axis and secured to the inner casing, the outer casing located radially outwardly of the inner casing relative to the central axis. First conduits are secured to the outer casing and to the inner casing for rotation about the central axis, the first conduits located radially between the outer casing and the inner casing, and circumferentially distributed about the central axis. First passages are defined in the first conduits. Second passages are circumferentially interspaced between the first passages and are located radially between the inner casing and the outer casing. The second passages are in heat exchange relationship with the first passages.

Abstract: A turbofan engine comprising an outer bypass duct, an annular bypass flow path between the outer bypass duct and a core engine, an engine component forming an airflow obstruction adjacent the outer bypass duct, an air cooler having a tube, the tube having at least a sinuous portion extending in the annular bypass flow path, the sinuous portion extending along the outer bypass duct, downstream of the airflow obstruction, the sinuous portion configured for exchanging heat between a fluid circulating in the tube and air circulating in the bypass flow path during operation of the turbofan engine.

Abstract: The pump can have a pump body, a main cavity having an inlet and an outlet, a rotor rotatably mounted in the main cavity and configured to pump fluid from the inlet to the outlet as it rotates, a separator cavity disposed adjacent the main cavity and configured to sustain a vortex, a fluid passage fluidly connecting the main cavity to the separator cavity, the fluid passage preserving momentum of fluid from the main cavity to the separator cavity to contribute to the vortex.

Abstract: The bearing chamber assembly can have a bearing chamber wall extending annularly and having a drain aperture, the drain aperture connecting a scavenge line, and a baffle, the baffle having an apertured sheet connected at one end to the bearing chamber wall, extending from the connected end over and past the scavenge port to a free edge, the free edge spaced from the bearing chamber wall.

Abstract: A fan assembly for a gas turbine engine is described which includes a fan and a leading edge assembly mounted to the fan. The leading edge assembly includes a plurality of leading edge extensions projecting from a central core and circumferentially spaced apart to align with leading edges of the fan blades. The leading edge extensions define cavities between the leading edges and the extensions. The cavities extend radially at least partially within the leading edge extensions, and receive heated pressurized air from the engine in operation. Elongated slots extend radially along a downstream edge of the leading edge extensions, and are defined axially between the downstream edge and the leading edges of the blades. The slots provide fluid flow communication between the cavities and at least pressure surfaces of the fan blades.

Abstract: Pressure regulators together with associated methods and systems are provided. An embodiment of a pressure regulator includes a chamber having an inlet port for receiving a fluid and an outlet port for delivering the fluid at a regulated pressure. The pressure regulator includes a diaphragm defining at least part of the chamber, and the diaphragm defining a first orifice therethrough. The pressure regulator includes a spring configured to interact with the diaphragm. The pressure regulator includes an interface operatively disposed between the spring and the diaphragm. The interface includes a contact surface for contacting the diaphragm, and the contact surface is convex toward the diaphragm. The interface defines a second orifice therethrough that is in fluid communication with the first orifice in the diaphragm. The first and second orifices define a relief port for venting the chamber to an ambient environment external to the chamber.

Abstract: A valve has a housing having an inlet and an outlet. A valve element is biased towards a closed position in which the valve element restricts fluid flow from the inlet to the outlet. The valve element is axially movable by fluid pressure at the inlet towards an open position in which the inlet is in fluid flow communication with the outlet. The valve further has a damping chamber having a metering orifice in fluid communication with the inlet. The damping chamber has an axially facing surface defined by the valve element and having a variable volume varying from a minimum volume when the valve element is in its closed position to a maximum volume when the valve element is in its open position.

Abstract: A machine includes a liquid system and a shaft. The shaft is rotatable about a rotation axis and includes a first part and a second part engaged coaxially with the first part. The first part is rotatable relative to the second part about the rotation axis to define a liquid pump between the first part and the second part. The pump is hydraulically connected to the liquid system. A method of cooling the machine is also provided.

Abstract: An oil tank for a gas turbine engine. The oil tank includes an oil cavity defined within structural walls of a nacelle of the gas turbine engine, the oil cavity having an oil inlet and an oil outlet. At least one of the structural walls has an interior side facing the oil cavity and an exterior side. The interior side includes a plurality of upstanding protrusions extending into the oil cavity and fully immersed in oil when the gas turbine engine is in use during steady state operation. The exterior side includes a plurality of fins extending therefrom and exposed to an ambient air stream during steady state operation of the gas turbine engine.

Abstract: A gas turbine engine is provided, with a compressor section including a fan driven by an engine shaft about a rotation axis, the engine shaft defining a bore extending axially therethrough from a hot gas inlet to a hot gas outlet, the hot gas inlet located downstream of the compressor section, a nose cone mounted to the fan and defining a cavity therewithin, a first impeller and a second impeller mounted within the cavity, the first impeller having an inlet facing a forward direction of the gas turbine engine, the inlet of the first impeller in fluid flow communication with an air inlet defined in an outer surface of the nose cone, the second impeller having an inlet facing a rearward direction of the gas turbine engine, the inlet of the second impeller being in fluid flow communication with the hot gas outlet of the engine shaft.

Abstract: An oil supply system for supplying oil to a lubricating cavity of a gas turbine engine, the oil supply system has: a de-oiler having a de-oiler air-oil inlet, a de-oiler oil outlet hydraulically connected to the lubricating cavity, and a de-oiler air outlet in fluid flow communication with an environment outside of the oil supply system; and a closed-loop oil circuit including a main pump having a main pump inlet and a main pump outlet, the main pump outlet hydraulically connected to the lubricating cavity, a de-aerator having a de-aerator inlet hydraulically connected to a scavenge outlet of the lubricating cavity, a de-aerator air-oil outlet in fluid flow communication with the de-oiler inlet, and a de-aerator oil outlet hydraulically connected to the main pump inlet.

Abstract: An aircraft pneumatic system including a pneumatic actuator arranged to operate at a pressure value at least equal to a pressure threshold, a line fluidly connected between a pneumatic source and the pneumatic actuator, and a venturi disposed upstream of the line and downstream of the pneumatic source. The venturi is configured to receive a source flow from the source at a mass flow rate, the mass flow rate being between a lower, nominal flow rate value and a higher, graded flow rate value. The venturi is sized such that when the mass flow rate is at the nominal flow rate value, a line pressure inside the line corresponds to a source pressure upstream of the venturi, and when the mass flow rate to the venturi is at the graded flow rate value, the line pressure is less than the source pressure.

Abstract: A cooling system for a gas turbine engine comprising a closed circuit containing a change-phase fluid, the closed circuit having at least one cooling exchanger configured to be exposed to a flow of cooling air for the change-phase fluid to release heat to the cooling air. A plurality of heat exchangers in are heat exchange relation with the change-phase fluid in the closed circuit, the plurality including at least a first heat exchanger configured to receive a first coolant from a first engine system for the change-phase fluid to absorb heat from the first coolant, and a second heat exchanger configured to receive a second coolant from a second engine system for the change-phase fluid to absorb heat from the second coolant. The system is configured so that the fluid at least partially vaporizes when absorbing heat from at least one of the first coolant and the second coolant and at least partially condenses when releasing heat to the cooling air.

Abstract: A gas turbine engine includes a supply air conduit fluidly connected to an inlet of a combustion chamber to convey supply air to the combustion chamber, an exhaust conduit fluidly connected to an exit of the combustion chamber to convey exhaust gases away from the combustion chamber, and a recuperator defining a first flow path and a second flow path therethrough, the second flow path being in heat transfer communication with the first flow path, the first flow path defining part of the supply air conduit, the second flow path defining part of the exhaust conduit. Methods of operating the engine are also provided.

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 fluid system of an aircraft engine includes a first and second fluid conduits. The first conduit fluid conduit fluidly connects to the aircraft engine. A pump fluidly connects to the first fluid conduit and moves therethrough a fluid imparting an excitation frequency to the fluid. The second fluid conduit fluidly connects to the first fluid conduit and to a pressure sensor. A weight is disposed in the second fluid conduit and movable between a first and second positions. A mass of the weight and a liquid capacitance of the second fluid conduit between the second position and a second end of the second fluid conduit define a resonance frequency that is less than the excitation frequency. Fluid pressure monitoring and pressure noise filter construction methods are also disclosed.

Abstract: A fan nose cone is disclosed for impeding icing and recovering momentum in a gas turbine engine. The fan nose cone comprises: an axially symmetric shell having a convex external surface and an internal surface, the shell having an opening in a forward end of the shell for communication with a source of heated pressurized air; and an axially symmetric deflector disposed forward of the opening, the deflector being configured to direct heated pressurized air exiting from the opening radially outwardly to flow in a downstream direction over the convex external surface of the shell during operation. The shell of the fan nose cone may have a rearward circumferential vent in communication with the source of heated pressurized air for directing heated pressurized from the vent in a radially outward and downstream direction toward the fan blade platforms.

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 gas turbine engine is provided, with a compressor section including a fan driven by an engine shaft about a rotation axis, the engine shaft defining a bore extending axially therethrough from a hot gas inlet to a hot gas outlet, the hot gas inlet located downstream of the compressor section, a nose cone mounted to the fan and defining a cavity therewithin, a first impeller and a second impeller mounted within the cavity, the first impeller having an inlet facing a forward direction of the gas turbine engine, the inlet of the first impeller in fluid flow communication with an air inlet defined in an outer surface of the nose cone, the second impeller having an inlet facing a rearward direction of the gas turbine engine, the inlet of the second impeller being in fluid flow communication with the hot gas outlet of the engine shaft.