Pratt-Whitney Canada Corp

Dana Tm4 Inc.

Tm4 Inc.

Pratt & Whitney Canada Corp.

Eric Latulipe

Jean Thomassin

Andre Julien

Richard Freer

Todd A Spierling

Jean Dubreuil

Luc Dionne

Martin Houle

Francois Dube

Xi Wang

Frank Becker

Jean-Philippe Dextraze

Pierre Blouin

Robert A Bayles

Richard Santerre

Yannick Philibert

Jean-Philippe Desbiens

Mathieu Lepage

An electric machine system described herein comprises a first electric machine rotor, a first gear and a second gear. The first gear is connected to the first electric machine rotor and to a first input/output shaft. The second gear is connected to the first electric machine rotor and to a second input/output shaft. The first electric machine rotor is disposed between the first gear and the second gear.

Electric machine systems

An electric machine system disclosed herein comprises first and second electric machines configured to drive a load. The first electric machine has a plurality of first rotors. The second electric machine has a plurality of second rotors. At least one of the second rotors is indexed relative to a respective one of the first rotors to, in use, provide a torque phase offset between the first and second electric machines. A shaft is coupled to the load and connects the respective one of the first rotors with the at least one of the second rotors. The respective one of the first rotors is coaxial with and axially spaced apart from the at least one of the second rotors.

Electric machine systems having magnetised bi-pole rotors

An electric machine system described herein comprises a first and second electric machines configured to drive a load. The first electric machine has a plurality of first rotors driven using electric power having a first phase. The second electric machine has a plurality of second rotors driven using electric power having a second phase. The second phase differs from the first phase. Each of one or more shafts connects a first rotor with a second rotor. The first rotor is coaxial with and axially spaced apart from the second rotor.

Electric machine systems comprising a stator common to the plurality of rotors

Multi-rotor electric machine systems

A hybrid electric aircraft propulsion system and method of operation are described. The system comprises a thermal engine, a generator coupled to the thermal engine, a first electric propulsor operatively connected to the generator to receive alternating current (AC) electric power therefrom, a second electric propulsor, a generator inverter operatively connected to the generator to convert AC electric power to direct current (DC) electric power, and a first motor inverter operatively connected to the generator inverter and selectively connected to one of the first electric propulsor and the second electric propulsor and configured to receive the DC electric power and provide the first electric propulsor and the second electric propulsor with AC electric power, respectively.

Hybrid electric propulsion system and method of operation

There is described a method and system for operating a hybrid electric aircraft propulsion system. The method comprises modulating AC electric power applied to a first electric propulsor or a second electric propulsor from at least one motor inverter to synchronize the frequency of the first electric propulsor or the second electric propulsor with the frequency of a generator.

Synchronization of generator and electric motor in a hybrid electric aircraft propulsion system

An electric machine is described herein. The electric machine includes a casing, a stator, a rotor generally coaxial with the stator, an enclosed cooling assembly circulating a first cooling fluid within the casing, and an open cooling assembly through which a second cooling assembly can flow; the open cooling assembly cooling both the stator and the first cooling fluid.

Electric machine provided with an enclosed cooling assembly paired to an open cooling assembly

Electric machine systems with gears

The electric machine includes a plurality of rotors drivingly coupled to a common shaft defining a shaft axis about which the common shaft is rotatable, and a common stator for the plurality of rotors, the common stator extending circumferentially about the common shaft. The rotors are rotatable about respective rotor axes which are substantially perpendicular to the shaft axis.

Multi-rotor electrical machine with radial configuration

Methods and systems for operating a hybrid electric aircraft propulsion system mounted to an aircraft. The method comprises driving a first rotating propulsor from a first electric motor operatively connected to a generator, driving a second rotating propulsor from a second electric motor operatively connected to the generator, and driving a third rotating propulsor from a thermal engine, the thermal engine operatively connected to the generator and configured to drive the generator.

Methods and systems for operating a hybrid electric aircraft propulsion system. The method comprises providing alternating current (AC) electric power to a first electric motor to drive a first rotating propulsor, providing the first electric motor with AC electric power from at least one motor inverter operatively coupled to a direct current (DC) power source, detecting a failure in a path to the first electric motor, and selectively rearranging a first switching arrangement between the generator, the at least one motor inverter, and the first electric motor.

Operation of a hybrid electric aircraft propulsion system

A centrifugal air/oil separation system communicates with bearing cavities of the engine and substantially isolates separated oil from contacting the gearbox.

Growing community of inventors

Ste-Julie, Canada

Eric Latulipe