Starting methods for hybrid-electric aircraft

Patent metadata

Field	Value
Publication number	US-11939073-B2
Application number	US-202017085006-A
Country	US
Kind code	B2
Filing date	Oct 30, 2020
Priority date	Oct 30, 2020
Publication date	Mar 26, 2024
Grant date	Mar 26, 2024

Abstract

A method includes using an electric motor to start a thermal engine. The electric motor and thermal engine are connected to one another as the electric motor and the thermal engine of a hybrid-electric power plant in an aircraft. The electric motor can be connected to a combining gear box. The thermal engine can be connected to the combining gear box so that the electric motor and the thermal engine can provide torque to the combining gear box in a parallel hybrid-electric configuration. The combining gearbox can output torque to an air mover for providing thrust to the aircraft.

First claim

What is claimed is:

1. A method comprising:
setting a start speed for a thermal engine of a hybrid-electric power plant in an aircraft based on ambient conditions;
using an electric motor to start the thermal engine by bringing the thermal engine to the start speed and limiting a torque output of the electric motor to prevent mechanical failure when mechanical rotation of the electric motor is hindered, wherein:
the electric motor and thermal engine are connected to one another as the electric motor and the thermal engine of the hybrid-electric power plant in the aircraft;
the electric motor is connected to a combining gear box;
the thermal engine is connected to the combining gear box so that the electric motor and the thermal engine can provide torque to the combining gear box in a parallel hybrid-electric configuration;

flying the aircraft through a mission of take-off, climb, cruise, and landing without using the electric motor as a generator;
after using the electric motor to start the thermal engine:
powering the aircraft with the hybrid-electric power plant with combined power from the electric motor and the thermal engine driving the combining gear box through take-off; and
powering the aircraft with the hybrid-electric power plant with combined power from the electric motor and the thermal engine driving the combining gear box while climbing to cruise altitude.

2. The method as recited in claim 1 , wherein the combining gear box outputs torque to an air mover for providing thrust to the aircraft.

3. The method as recited in claim 2 , wherein using the electric motor to start the thermal engine includes providing torque from the electric motor to the combining gear box, and providing the torque from the combining gear box to the thermal engine to drive rotation in the thermal engine starting from a state of rest to reach a compression ratio where combustion can be initiated in the thermal engine.

4. The method as recited in claim 1 , further comprising powering the aircraft with the hybrid-electric power plant with power exclusively from the thermal engine after reaching cruise altitude.

5. The method as recited in claim 1 , further comprising issuing a command from an engine control unit (ECU) to an electrical system coupled to the electric motor to bring the thermal engine to the start speed.

6. The method as recited in claim 5 , wherein bringing the thermal engine to the start speed includes using engine speed feedback to the ECU.

7. The method as recited in claim 5 , wherein the ECU commands the electric motor to decrease torque after the start speed is reached.

8. The method as recited in claim 1 , comprising:
using a first torque output from the electric motor to start the thermal engine at a first ambient temperature; and
using a second torque output from the electric motor higher than the first torque output to start the thermal engine at a second ambient temperature colder than the first ambient temperature.

9. A system comprising:
an electric motor;
a thermal engine connected to the electric motor as a hybrid-electric power plant in an aircraft; and
an engine control unit (ECU) connected to set a start speed for the thermal engine based on ambient conditions, use the electric motor to start the thermal engine by bringing the thermal engine to the start speed, and limit a torque output of the electric motor during starting of the thermal engine to prevent mechanical failure when mechanical rotation of the electric motor is hindered, wherein:
the electric motor is connected to a combining gear box;
the thermal engine is connected to the combining gear box so that the electric motor and the thermal engine can provide torque to the combining gear box in a parallel hybrid-electric configuration,
the ECU is configured for flying the aircraft through a mission of take-off, climb, cruise, and landing without using the electric motor as a generator, and after using the electric motor to start the thermal engine:
powering the aircraft with the hybrid-electric power plant with combined power from the electric motor and the thermal engine driving the combining gear box through take-off; and
powering the aircraft with the hybrid-electric power plant with combined power from the electric motor and the thermal engine driving the combining gear box while climbing to cruise altitude.

10. The system as recited in claim 9 , wherein the electric motor and the thermal engine have horse power ratings within one order of magnitude of each other.

11. The system as recited in claim 10 , wherein the combining gear box is connected to an air mover for providing thrust to the aircraft.

12. The system as recited in claim 9 , further comprising an electrical system coupled to the electric motor to bring the thermal engine to the start speed.

13. The system as recited in claim 12 , further comprising a feedback loop connected to use engine speed feedback to the ECU to bring the thermal engine to the start speed.

Assignees

• Pratt & Whitney Canada

Inventors

• Imel Paul C
• Bergeron Sebastien
• Plamondon Etienne
• Gosselin-Brisson Samuel
• Guerchkovitch Leonid

Classifications

• B64D35/025

  of parallel type · CPC title

• B64D35/023

  of series-parallel type · CPC title

• B64D31/18

  for hybrid-electric power plants · CPC title

• B64D27/33

  Hybrid electric aircraft · CPC title

• B64D31/14 Primary

  Transmitting means between initiating means and power plants · CPC title