Hybrid electric aircraft propulsion system with motors using induction effect

Patent metadata

Field	Value
Publication number	US-10730633-B2
Application number	US-201615358595-A
Country	US
Kind code	B2
Filing date	Nov 22, 2016
Priority date	Nov 22, 2016
Publication date	Aug 4, 2020
Grant date	Aug 4, 2020

Abstract

A hybrid electric aircraft propulsion system at least includes a motor with induction effect to drive a propeller or propulsion fan. The motor is directly supplied from the electrical output of a generator. The generator is driven by a variable speed engine and as such the generator has a output frequency proportional to the speed of the engine. A controller is operatively coupled to the motor, the generator and the engine. The controller is operable to control a speed of the engine and the excitation of the generator to provide an output at a target voltage and frequency to drive the motor at a desired torque and speed.

First claim

What is claimed is:

1. A hybrid electric aircraft propulsion system comprising:
a motor having a rotating output, the rotating output operatively coupled to drive a propeller or propulsion fan of an aircraft,
a generator having a generator output having a voltage and a frequency, the generator output being operatively coupled to the motor such that the motor is energized by the generator output to provide the rotating output, the rotating output being variable in response to the voltage and frequency of the generator output, the generator being operatively coupled for rotational drive to a variable speed turbine engine such that the generator has an output frequency proportional to the speed of the engine, and
a controller that is operatively coupled to the motor, the generator and the engine, wherein the controller is operable to control a speed of the engine and an excitation of the generator to provide the generator output at a target voltage and frequency to drive the motor to provide the rotating output, wherein
the motor is a synchronous motor with induction effect, the synchronous motor operable as an induction motor using induction effect during start up and below synchronous speed and operable as a synchronous motor at synchronous speed.

2. The system of claim 1 , the motor comprising a plurality of synchronous motors, each synchronous motor being operatively coupled with a propeller or propulsion fan, each of the plurality of motors being coupled to receive the generator output.

3. The system of claim 2 , comprising a plurality of switches and wherein each of the plurality of motors is coupled via a switch of the plurality of switches to the generator output.

4. The system of claim 3 , wherein each switch of the plurality of switches is individually operable to interrupt the coupling of the generator output with the respective motor.

5. The system of claim 3 , wherein the switches are operable to modulate thrust produced by the plurality of motors.

6. An aircraft comprising a hybrid electric aircraft propulsion system, the hybrid electric propulsion system including:
a motor having a rotating output, the rotating output operatively coupled to drive a propeller or propulsion fan of the aircraft,
a generator having a generator output having a voltage and a frequency, the generator output being operatively coupled to the motor such that the motor is energized by the generator output to provide the rotating output, the rotating output being variable in response to the voltage and frequency of the generator output, the generator being operatively coupled for rotational drive to a variable speed turbine engine such that the generator has an output frequency proportional to the speed of the engine to provide the generator output, and
a controller that is operatively coupled to the motor, the generator and the engine, wherein the controller is operable to control a speed of the engine and a excitation of the generator to provide the generator output at a target voltage and frequency to drive the motor to provide the rotating output, wherein
the motor is a synchronous motor with induction effect, the synchronous motor operable as an induction motor using induction effect during start and below synchronous speed and operable as a synchronous motor at synchronous speed.

7. The aircraft of claim 6 comprising a fixed wing, rotorcraft, tilt-rotor type, or distributed propulsion, multiple fan aircraft.

8. The aircraft of claim 6 , the motor comprising a plurality of synchronous motors, each synchronous motor being operatively coupled with a propeller or propulsion fan, each of the plurality of motors being coupled to receive the generator output.

9. The aircraft of claim 8 , comprising a plurality of switches and wherein each of the plurality of motors is coupled via a switch of the plurality of switches to the generator output.

10. The aircraft of claim 8 , wherein the switches are operable to modulate relative thrust of propulsion fans that are operably coupled with the respective motors.

11. In a hybrid electric aircraft having a motor having a rotating output, the rotating output operatively coupled to drive a propeller or propulsion fan of the aircraft, a generator having a first generator output and a second generator output, different than the first generator output coupled to the motor such that the motor is energized by the first or second generator output to provide the rotating output, and the generator being operatively coupled for rotational drive to a variable speed turbine engine, a method of controlling a thrust output of the propeller or propulsion fan comprising:
adjusting a speed of the turbine engine to drive the generator at a first rotating speed and energizing the generator to a first excitation energization such that for the first rotating speed and first excitation energization the generator provides the first generator output,
adjusting a speed of the turbine engine to drive the generator at a second rotating speed and energizing the generator to a second excitation energization such that for the second rotating speed and second excitation energization the generator provides the second generator output
providing the first or second generator output to the motor,
energizing the motor by the first generator output to operate as an induction motor below a synchronous speed of the motor, and
energizing the motor by the second generator output to operate as a synchronous motor at the synchronous speed.

12. The method of claim 11 , comprising adjusting the speed of the turbine engine to a second rotating speed different than the first rotating speed.

13. The method of claim 11 , wherein the hybrid electric aircraft comprises a plurality of motors each of which drive a respective propeller or propulsion fan, the method comprising providing the first or second generator output to each of the plurality of motors.

14. The method of claim 12 , wherein providing the first or second generator output to each of the plurality of motors comprises providing the first or second generator output to each of the plurality of motors via a respective switch.

15. The method of claim 13 comprising modulating the first generator output to the plurality of propellers or propulsion fans.

Assignees

• Honeywell Int Inc

Inventors

• Anghel Cristian
• Blumer Eric

Classifications

• B64D35/023

  of series-parallel type · CPC title

• B64D31/18

  for hybrid-electric power plants · CPC title

• B64D27/33

  Hybrid electric aircraft · CPC title

• B64D35/02

  specially adapted for specific power plants · CPC title

• B64C29/0033 Primary

  the propellers being tiltable relative to the fuselage · CPC title