Pratt-whitney Canada Corp

Xuening Lu

Thomas Trevor Ricci

Louis-Philippe Larose

Ezzat MeshkinFam

Richard Freer

Etienne Plamondon

Carmine Lisio

Poi Loon Tang

Kevin Nguyen

Ezzat Meshkin Fam

Eric Ostiguy

A method of regenerating an electric power storage unit for an aircraft hybrid electric propulsion (HEP) system is provided. The HEP system includes a thermal engine, an electric motor, an electric power storage unit, a primary gearbox, and a propulsion unit. The electric motor is configured to selectively provide rotational drive to the propulsion unit. The method includes: controlling the electric motor to operate as the generator; controlling the primary gearbox to be in an output disengaged configuration, wherein in the output disengaged configuration the primary gearbox is disengaged from driving the propulsion unit and the primary gearbox is transfers rotational drive produced by the thermal engine to the electric motor; operating the thermal engine to drive the primary gearbox in the output disengaged configuration; and regenerating the electric power storage unit by providing electrical energy produced by the electric motor to the electric power storage unit.

Hybrid electric propulsion system with regeneration and method for operating the same

A method of operating a hybrid electric powertrain (HEP) may include determining, based on a HEP torque demand and a maximum torque limit for a gas turbine engine having a mechanical output coupled to a power shaft of the HEP, a target torque for the gas turbine engine. The method may also include controlling the gas turbine engine to operate according to a target speed or the target torque. The method may also include, while operating the gas turbine engine according to the target speed or the target torque, determining, based on the HEP torque demand and the target torque, a total torque compensation demand for an electric machine having a mechanical output controllably couplable to the power shaft of the HEP, and operating the electric machine according to the total torque compensation demand.

Master-slave hybrid-electric powertrain control architecture with supervisory power management control

An engine assembly for an aircraft propulsion system includes an engine, a rotational assembly, a gearbox assembly, and a controller. The engine includes an engine shaft. The rotational assembly includes a shaft, a bladed compressor rotor, and a bladed turbine rotor. The shaft interconnects the bladed compressor rotor and the bladed turbine rotor. The gearbox assembly includes a transmission assembly. The transmission assembly includes a first pump, a second pump, and a conduit circuit connecting the first pump and the second pump in fluid communication. The first pump is coupled with the engine shaft. The first pump is a variable displacement pump. The second pump is coupled with the rotational assembly. The controller is configured to identify a target rotation speed for the rotational assembly with an outer closed loop, identify a control signal with an inner closed loop using the target rotation speed, and controlling a displacement of the first pump using the control signal.

Transmission assembly for an aircraft engine assembly and architecture for controlling same

A system is provided for an aircraft. This aircraft system includes a heat exchanger, a lubricant flow circuit and a bypass valve. The lubricant flow circuit includes an inlet passage, an outlet passage, a heat exchanger passage and a bypass passage. The heat exchanger passage extends through the heat exchanger. The bypass passage bypasses the heat exchanger. The heat exchanger passage and the bypass passage are fluidly coupled in parallel between the inlet passage and the outlet passage. The bypass valve is fluidly coupled inline along the lubricant flow circuit. The bypass valve is operable to regulate lubricant flow through the bypass passage. The bypass valve includes a rotary electric motor.

Aircraft heat exchanger bypass flow control with electric motor

An assembly for an aircraft propulsion system includes an intercooler assembly and a controller. The intercooler assembly includes an intercooler and a flow control assembly. The intercooler includes a primary air inlet, a primary air outlet, a secondary air inlet, and a secondary air outlet. The flow control assembly is disposed at the secondary air outlet. The flow control assembly includes an actuator and at least one flap. The actuator is configured to position the at least one flap in an open position, a closed position, and intermediate positions. The controller is configured to control the actuator to position the at least one flap in the open position, determine a hot-side heat transfer effectiveness of the intercooler and a hot-side mass flow rate for the intercooler, determine a cold-side mass flow rate of the intercooler, identify a position of the actuator, and identify a successful or an unsuccessful actuator range check for the actuator.

System and method for performing an actuator range check for an intercooler flow control assembly of an aircraft propulsion system

A method is provided for operating an aircraft system. During this method, an engine is operated using first fuel provided by a first fuel source. A fuel supply for the engine is switched between the first fuel source and a second fuel source, where the switching of the fuel supply includes shutting down the engine during aircraft flight. The engine is operated using second fuel provided by the second fuel source.

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Oakville, Canada

Xuening Lu