Pratt-Whitney Canada Corp

Pratt & Whitney Canada Corp.

Michel Bousquet

Richard Freer

Kian McCaldon

Tin-Cheung John Hu

André Fortin

Kevin Nguyen

Jeremie Barberger

Johnny Vinski

Etienne Plamondon

Jérémie Barberger

Ninad Joshi

Vincent Savaria

Christopher Gover

Bruno Villeneuve

David Gagnon-Martin

Sebastien Bolduc

Stephane Berube

Thomas Trevor Ricci

Larry Lebel

Jean-Philippe Simoneau

Frederic Roy

Mathias Michaud

Ismael Bencheikh

A method of manufacturing a component of a housing defining a rotor cavity, the method includes: obtaining a body of the component of the housing, the body having a first face and a second face opposite to the first face, the second face facing away from the rotor cavity, the body made of a first material; performing a treatment to the body to increase a wear-resistance of the first material; depositing a bonding layer on the second face of the body, the bonding layer including a second material being dissimilar from the first material, the first material being more wear-resistant than the second material, the second material defining an exposed face of the bonding layer facing away from the body; and completing a shape of the body by bonding a quantity of a third material to the exposed face of the bonding layer.

Housing assembly for rotary engine and method of manufacturing thereof

An aircraft engine oil distribution system includes a system container, an oil reservoir disposed in the system container, the oil reservoir having a plurality of fins protruding from an inner-surface of a wall of the oil reservoir and extending into the oil reservoir, and a heat exchanger disposed in the system container. The heat exchanger includes a cooling fluid passage defined at least between the one or more walls of the system container and the sidewall of the oil reservoir, a matrix disposed in the cooling fluid passage in heat transfer relationship with the plurality of fins of the oil reservoirs.

Aircraft engine oil distribution system

A system is provided for an aircraft. This aircraft system includes a nacelle, an aircraft component, an aircraft propulsion system and an electric compressor. The aircraft component is arranged outside of the nacelle. The aircraft propulsion system includes a propulsor rotor and a powerplant configured to drive rotation of the propulsor rotor. The powerplant is housed within the nacelle. The electric compressor is housed within the nacelle and is fluidly discrete from the powerplant. The electric compressor is fluidly coupled with and is configured to provide compressed air to the aircraft component.

Aircraft air system with dedicated compressor(s)

A housing assembly for a rotary engine, has: a rotor housing extending around an axis, the rotor housing having an inner face facing a rotor cavity; side housings secured to opposite sides of the rotor housing, the rotor cavity bounded axially between the side housings; and a seal received within a groove at an interface between the rotor housing and a first side housing, the groove annularly extending around the axis, located outwardly of the inner face, and overlapping a peripheral section of the first side housing, the seal having: an elastomeric member compressed between the peripheral section and the rotor housing; and a shield disposed inwardly of the elastomeric member, the shield having a melting point above a temperature of combustion gases, the shield in contact with both of the peripheral section of the first side housing and the rotor housing.

Rotary engine with seal having elastomeric member and shield

A rotary engine, comprising: housings defining a rotor cavity and respective coolant passages fluidly connected in parallel to a source of coolant; a rotor within the rotor cavity; and a cooling system including: a flow regulating device in fluid communication with the respective coolant passages; a heat exchanger facilitating heat exchange between the coolant and a heat-transfer medium; and a controller operatively connected to the flow regulating device to: determine, based on an engine parameter and an environment parameter of the rotary engine, a flow rate of the coolant to be injected towards the respective coolant passages to maintain the housings within a temperature range, the engine parameter indicative of a quantity of heat generated by the rotary engine, the environment parameter indicative of a quantity of heat the heat exchanger is able to transfer to the heat-transfer medium; and cause the coolant to flow towards at the flow rate.

Rotary engine and cooling systems thereof

A rotary engine, has: housings secured to one another, the housings including a first side housing, a second side housing, and a rotor housing disposed between the first side housing and the second side housing; and a rotor rotationally received within a rotor cavity defined by the first side housing, the second side housing, and the rotor housing; wherein the first side housing, the rotor housing, and the second side housing are cooled in parallel via respective coolant passages including: a first side housing coolant passage extending through the first side housing; a second side housing coolant passage extending through the second side housing; and a rotor housing coolant passage extending through the rotor housing, and wherein the coolant passages are free of inter-passage connection between the housings.

An engine housing includes a rotor housing body, a side housing body a side plate and a seal assembly. The rotor housing body extends about an axis to form a rotor cavity. The rotor housing body extends between and to a first axial end and a second axial end. The side housing body is disposed at the first axial end. The side plate includes an inner side, an outer side, and a perimeter edge extending from the inner side to the outer side. The seal assembly includes a support ring and a spacer. The support ring and the spacer extend about the axis. The support ring is mounted to the perimeter edge by a braze joint. The spacer extends between and to a first axial spacer end and a second axial spacer end. The first axial spacer end is disposed at the support ring and the outer side.

Seal assembly for a rotary engine housing

An aircraft power plant, has: a combustion engine having an outlet outputting combustion gases; a turbine downstream of the combustion engine; a detonation combustion tube fluidly connecting the combustion engine to the turbine; a member having an open position in which the outlet of the combustion engine is fluidly connected to the turbine and a closed position in which the combustion engine is fluidly disconnected from the turbine; a fuel injector fluidly connected to the detonation combustion tube; an igniter operatively connected to the detonation combustion tube; and a controller operatively connected to the fuel injector and to the igniter, the controller configured to, in response to receiving of a command: inject fuel into the detonation combustion tube via the fuel injector, and once the member is in the closed position, power the igniter to ignite a mixture of the combustion gases and the fuel into the detonation combustion tube.

Aircraft power plant with detonation combustion tube

A rotary engine rotor and a method for supplying rotary engine rotors are provided. The rotary engine rotor has a center axis, a rotor body, a plurality of peripheral surfaces, and a plurality of recess members. The rotor body has a central bore that extends along the center axis. The plurality of peripheral surfaces are disposed around an exterior perimeter of the rotor body. Each of the plurality of recess members are disposed in a respective one of the plurality of peripheral surfaces. Each recess member includes an interior cavity open to an exterior of the rotor.

Rotary engine rotor and method

A rotor housing for an aircraft rotary engine includes a side housing body and a rail. The side housing body extends along an axis between and to an inner side and an outer side. The side housing body forms a fluid cooling passage and a plurality of ribs. The fluid cooling passage extends about the axis at the inner side. The plurality of ribs are coincident with and extend into the fluid cooling passage. The plurality of ribs are distributed about the fluid cooling passage as an array of ribs. The rail is disposed at the plurality of ribs. The rail extends about the fluid cooling passage. The side housing body and the rail form a plurality of fluid cooling channels connected in fluid communication with the fluid cooling passage.

Rotor assembly with cooling channels separated by ribs for a rotary engine

An engine housing includes a rotor housing and a side housing assembly. The rotor housing extends about an axis to form a rotor cavity of the engine housing. The side housing assembly includes a side housing body, a side plate, and an impingement cooling assembly. The side plate is disposed between the rotor housing and the side housing body. The side plate forms the rotor cavity. The impingement cooling assembly includes a first baffle plate. The first baffle plate is disposed between the side housing body and the side plate. The side housing body, the side plate, and the first baffle plate form a coolant passage. The coolant passage includes an inlet plenum and a plurality of impingement cooling holes. The first baffle plate forms the plurality of impingement cooling holes. Each impingement cooling hole of the plurality of impingement cooling holes is disposed at the inlet plenum.

Impingement cooling assembly for an aircraft rotary engine housing

A system is provided for an aircraft. This system includes a propulsor rotor and a powerplant configured to drive rotation of the propulsor rotor. The powerplant includes a turbo-compounded intermittent internal combustion engine and a dual rotor electric machine. The turbo-compounded intermittent internal combustion engine includes a turbine rotor operatively coupled to the propulsor rotor through the dual rotor electric machine. The dual rotor electric machine includes a first rotor, a second rotor, a first stator and a second stator. The first stator and the second stator are arranged radially between and axially aligned with the first rotor and the second rotor.

Aircraft powerplant with electric transmission(s)

A rotary engine side housing is provided that includes a side plate portion, a side housing body portion, a coolant chamber, and a plurality of posts. The side plate portion has exterior and interior surfaces. The coolant chamber is disposed internally within the side housing body portion. The coolant chamber is defined by a chamber base surface, the peripheral side walls, and the side plate portion interior surface. The chamber base surface and the side plate portion interior surface are spaced apart from one another and the one or more peripheral side walls extend there between. The plurality of posts extend between the chamber base surface and the side plate portion interior surface. The side plate portion, the side body housing portion, and the plurality of posts are integrally formed with one another.

Rotor engine side housing and method for producing the same

A rotary internal combustion engine is provided that includes a housing and a rotor. The housing includes first and second side housings and a center housing. The center housing is disposed between and attached to the first and second side housings. The rotor is disposed within a rotor chamber and is engaged with a rotor shaft that extends between the first and second side housings. The rotor has a peripheral side wall that extends between a pair of end face surfaces. At least one of the first side housing or the second side housing includes a side plate having a seal surface, an interior surface, and a core disposed between the seal surface and the interior surface. The core comprises a ceramic matrix composite (CMC) material. The seal surface of the side plate engages in a sealing arrangement with a respective rotor end face surface.

Rotary engine with side housing having a side plate with a ceramic matrix composite core

A rotor for an aircraft rotary engine includes a rotor body. The rotor body extends about an axial centerline. The rotor body includes an outer body portion, an annular inner body portion, and ribs. The outer body portion forms a plurality of sides and a plurality of apex portions of the rotor. The annular inner body portion is disposed radially inward of the outer body portion. The ribs extend radially between and connect the outer body portion and the annular inner body portion. The rotor body forms at least a first lubrication passage within the inner body portion and within a first rib of the ribs. The first lubrication passage includes at least one passage inlet and at least one passage outlet. The at least one passage inlet is disposed at the annular inner body portion.

Growing community of inventors

Longueuil, Canada

Michel Bousquet