Pratt-whitney Canada Corp

Jean-Gabriel Gauvreau

David Gagnon-Martin

Bruno Villeneuve

Etienne Plamondon

Sebastien Bergeron

Benjamin James Renaud

Johnny Vinski

Jean Thomassin

David Waddleton

Andre Julien

Sebastien Bolduc

Vincent Savaria

Stephane Berube

Roger Huppe

Julien Simard-Bergeron

André Julien

Jean-Philippe Simoneau

Sébastien Bolduc

Jean-Phillippe Simoneau

A housing assembly has: a rotor housing extending around a rotation axis and from a first side to a second side, and having an inner face; a housing secured to the first side; and a seal received within a groove at an interface between the rotor housing and the housing, the groove extending around a perimeter of the first side and located radially outwardly of the inner face, the seal including: an elastomeric member; and a shield disposed inwardly of the elastomeric member and in contact with both the housing and the rotor housing, the shield including a thermoset plastic member extending along at least a portion of a perimeter of the groove and axially overlapping the elastomeric member, the thermoset plastic member circumferentially overlapping a combustion region of the rotor cavity where combustion occurs during operation of the rotary internal combustion engine.

Rotary engine with seal having shield and elastomeric member

During a manufacturing method, a protective coating is applied to a first chamber surface of a first component to provide a coated first chamber surface. The protective coating is applied to a second chamber surface of a second component to provide a coated second chamber surface. The second component is configured with the first component to provide a pilot chamber structure. The pilot chamber structure includes a pilot chamber, a pilot aperture, a fuel aperture and an ignitor aperture. The pilot chamber is formed by the coated first chamber surface and the coated second chamber surface within the pilot chamber structure. The pilot aperture projects into the first component from a distal end of the pilot chamber structure to the pilot chamber. The fuel aperture projects into the pilot chamber structure to the pilot chamber. The ignitor aperture projects into the pilot chamber structure to the pilot chamber.

Internal combustion engine with coated ignition system component(s)

An assembly is provided for a powerplant. This assembly includes a housing, a primary fuel injector and an ignition system. The housing forms a combustion volume within the housing. The primary fuel injector is configured to inject primary fuel into the combustion volume. The ignition system is configured to ignite the primary fuel within the combustion volume. The ignition system includes a pilot fuel injector, a pilot ignitor, a pilot chamber, a first component and a second component. The pilot fuel injector is configured to inject pilot fuel into the pilot chamber. The pilot ignitor is configured to ignite the pilot fuel within the pilot chamber. The pilot chamber is fluidly coupled with the combustion volume through an aperture in the first component. The pilot chamber is formed by and disposed between the first component and the second component. The first component is configured from or otherwise include a ceramic.

Internal combustion engine with ceramic pilot chamber component(s)

There is described a ventilator for ventilating an airway of a patient. The ventilator is generally configured to perform a series of respiration cycles, wherein each respiration cycle includes the delivery of a main volume of fresh respiratory gas into the patient's airway, followed by the evacuation of a corresponding volume of used respiratory gas, and to further perform a series of subcycles during a corresponding one of the respiration cycles, wherein each subcycle includes the delivery of an auxiliary volume of fresh respiratory gas into the patient's airway, followed by the evacuation of a corresponding volume of used respiratory gas, the auxiliary volume being smaller than, and distinct from, the main volume.

Patient ventilator, method of ventilating an airway of a patient, and associated computer program product

A rotary internal combustion engine has: a rotor; a housing circumscribing a rotor cavity, the rotor received within the rotor cavity, the housing having a peripheral wall and a side housing assembly secured to the peripheral wall, the side housing assembly having plates located at spaced apart ends of the peripheral wall, the plates defining seal running surfaces in sealing engagement with opposed end faces of the rotor, the plates made of silicon carbide.

Rotary engine with housing having silicon carbide plate

A rotodynamic pump for pumping a fluid includes an impeller, a housing surrounding the impeller, and a pressure regulating mechanism. The pressure regulating mechanism is configured to adjust the clearance between the impeller and the impeller housing to regulate pressure of the fluid downstream of the impeller. A method of regulating the delivery pressure is also disclosed.

Rotodynamic pump having a body defining a body cavity with a first and second housing portion defining a portion of an impeller cavity and disposed within the body cavity wherein the body cavity extends at least in part around the second housing portion and the housing portions defining an impeller clearance

A method of controlling a delivery pressure of an aircraft engine fuel system includes operating a rotodynamic fuel pump hydraulically connected to the fuel system to pump a fluid from an inlet of the rotodynamic pump and out of an outlet of the rotodynamic pump for delivery to the fuel system. The method further includes varying an angular relationship between the inlet and the outlet of the pump to control the delivery pressure. An aircraft engine fuel system and a rotodynamic pump are also described.

Rotodynamic pump and method

A liquid fuel system for an aircraft engine includes a first fuel supply conduit hydraulically connected to a fuel source, a second fuel supply conduit hydraulically connected to the engine, a fuel return conduit hydraulically connected to the second fuel supply conduit, and a fuel pump. The fuel pump has a main inlet hydraulically connected to the first fuel supply conduit, an outlet hydraulically connected to the second fuel supply conduit, and an intermediate inlet hydraulically connected to the fuel return conduit. The intermediate inlet is located between the main inlet and the outlet and in use has a pressure between the main inlet pressure and the outlet pressure. A method of supplying a liquid fuel to an aircraft engine is also described.

Aircraft engine fuel system and method

A rotor assembly for a rotary internal combustion engine is provided. The rotor assembly includes a rotor having a radial groove defined radially in a peripheral surface of the rotor. The groove has a depth and an intermediate shoulder at an intermediate depth. The groove has a first width therealong that is narrower than an intermediate width at the shoulder. An apex seal is received in the groove and protrudes from the peripheral face of the rotor. The apex seal is configured to move radially between a first position and a second position outward of the first position. A biasing member biases the apex seal toward the second position. A platform is disposed in the groove between the apex seal and the biasing member and has a width greater than the first width.

Apex seal arrangement for rotary internal combustion engine

A method of operating an aircraft engine of an aircraft, the aircraft engine having a common-rail fuel injection system for injecting fuel into a combustion chamber of the aircraft engine, including: pressurizing fuel for circulation through the common-rail injection system; circulating a portion of the pressurized fuel through a motive flow inlet of an ejector pump; and entraining a flow through the ejector pump with the portion of the pressurized fuel circulating through the motive flow inlet.

Common-rail fuel system with ejector pump and method of use thereof

A rotary engine casing having at least one end wall of an internal cavity for a rotor including a seal-engaging plate sealingly engaging the peripheral wall to partially seal the internal cavity and a member mounted adjacent the seal-engaging plate outside of the internal cavity. The member and seal-engaging plate having abutting mating surfaces which cooperate to define between them at least one fluid cavity communicating with a source of liquid coolant. When the casing includes a plurality of rotor housings, the end wall may be between rotor housings. A method of manufacturing a rotary engine casing is also discussed.

Method of manufacturing a rotary engine casing

There is disclosed a method of operating an engine assembly including a combustion engine and a common-rail injector. The method includes: injecting fuel into a combustion chamber of the combustion engine via the common-rail injector thereby generating a backflow of fuel; and powering an actuator using at least a portion of the backflow of fuel. An engine assembly including the combustion engine is disclosed; the engine assembly having a fuel circuit fluidly connecting a fuel source, the common-rail injector, and the second injector outlet together. The fuel circuit has an actuator sub-circuit operatively connected to an outlet of the common-rail injector and an actuator fluidly connected to the actuator sub-circuit.

Method of using backflow from common-rail fuel injector

There is disclosed a method of de-icing a component of an engine assembly having a common-rail fuel injection system, including: pressurizing fuel to circulate the fuel through the common-rail injection system; drawing a portion of the fuel upstream of common-rail injectors of the common-rail injection system and directing a remainder of the fuel toward the common-rail injectors; and transferring heat from the drawn portion of the fuel to the component.

Method of using heat from fuel of common-rail injectors

A rotary engine where the rotor cavity has a peripheral inner surface having a peritrochoid configuration defined by a first eccentricity and the rotor has a peripheral outer surface having a peritrochoid inner envelope configuration defined by a second eccentricity larger than the first eccentricity. Also, a rotary engine where the rotor cavity has a peripheral inner surface having a peritrochoid configuration defined by an eccentricity, and a rotor with a peripheral outer surface between adjacent ones of the apex portions being inwardly offset from a peritrochoid inner envelope configuration defined by the eccentricity. The engine may have an expansion ratio with a value of at most 8. The rotary engine may be part of a compound engine system.

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Varennes, Canada

Jean-Gabriel Gauvreau