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

Patent metadata

Field	Value
Publication number	US-11233470-B2
Application number	US-201916411267-A
Country	US
Kind code	B2
Filing date	May 14, 2019
Priority date	Sep 6, 2018
Publication date	Jan 25, 2022
Grant date	Jan 25, 2022

Abstract

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.

First claim

The invention claimed is:

1. A method for operating a hybrid electric aircraft propulsion system, the method comprising:
providing a first electric propulsor and a second electric propulsor with a first source of propulsion power from a generator configured for generating a first output of alternating current (AC) electric power, the first source of propulsion power provided to the first electric propulsor and the second electric propulsor through respective first motor stators of the first electric propulsor and the second electric propulsor;
providing the first electric propulsor and the second electric propulsor with a second source of propulsion power independent from the first source of propulsion power, from at least one motor inverter operatively coupled to a direct current (DC) power source, the at least one motor inverter configured to convert the DC electric power from the DC power source into a second output of AC electric power, the second source of propulsion power provided to the first electric propulsor and the second electric propulsor through respective second motor stators of the first electric propulsor and the second electric propulsor;
monitoring a frequency of the first electric propulsor or the second electric propulsor through the motor inverter and detecting desynchronization between a frequency of the generator and the frequency of the first electric propulsor or the second electric propulsor; and
modulating the second source of propulsion power applied to a desynchronized one of the first electric propulsor and the second electric propulsor from the at least one motor inverter to synchronize the frequency of the desynchronized one of the first electric propulsor and the second electric propulsor with the frequency of the generator, and maintaining, during the synchronization, a connection between the generator and the desynchronized one of the first electric propulsor and the second electric propulsor.

2. The method of claim 1 , further comprising disconnecting the at least one motor inverter from the first electric propulsor to synchronize the frequency of the second electric propulsor with the frequency of the generator, and disconnecting the at least one motor inverter from the second electric propulsor to synchronize the frequency of the first electric propulsor with the frequency of the generator.

3. The method of claim 1 , wherein modulating the second source of propulsion power applied to the desynchronized one of the first electric propulsor and the second electric propulsor is performed in response to a command from a controller.

4. The method of claim 1 , wherein providing the first electric propulsor and the second electric propulsor with the first source of propulsion power from the generator comprises providing the first electric propulsor with the first source of propulsion power from a first stator of the generator, and providing the second electric propulsor with the first source of propulsion power from a second stator of the generator.

5. The method of claim 1 , wherein the at least one motor inverter comprises a first motor inverter operatively coupled to the first electric propulsor and a second motor inverter operatively coupled to the second electric propulsor.

6. A system for operating a hybrid electric aircraft propulsion system comprising:
a processing unit; and
a non-transitory computer readable medium having stored thereon programming instructions executable by a processor for:
providing a first electric propulsor and a second electric propulsor with a first source of propulsion power from a generator configured for generating a first output of alternating current (AC) electric power, the first source of propulsion power provided to the first electric propulsor and the second electric propulsor through respective first motor stators of the first electric propulsor and the second electric propulsor;
providing the first electric propulsor and the second electric propulsor with a second source of propulsion power independent from the first source of propulsion power, from at least one motor inverter operatively coupled to a direct current (DC) power source, the at least one motor inverter configured to convert the DC electric power from the DC power source into a second output of AC electric power, the second source of propulsion power provided to the first electric propulsor and the second electric propulsor through respective second motor stators of the first electric propulsor and the second electric propulsor;
monitoring a frequency of the first electric propulsor or the second electric propulsor through the motor inverter and detecting desynchronization between a frequency of the generator and the frequency of the first electric propulsor or the second electric propulsor; and
modulating the second source of propulsion power applied to a desynchronized one of the first electric propulsor and the second electric propulsor from the at least one motor inverter to synchronize the frequency of the desynchronized one of the first electric propulsor and the second electric propulsor with the frequency of the generator and maintaining, during the synchronization, a connection between the generator and the desynchronized one of the first electric propulsor and the second electric propulsor.

7. The system of claim 6 , wherein the programming instructions are further executable for disconnecting the at least one motor inverter from the first electric propulsor to synchronize the frequency of the second electric propulsor with the frequency of the generator, and disconnecting the at least one motor inverter from the second electric propulsor to synchronize the frequency of the first electric propulsor with the frequency of the generator.

8. The system of claim 6 , wherein modulating the second source of propulsion power applied to the desynchronized one of the first electric propulsor and the second electric propulsor is performed in response to a command from a controller.

9. The system of claim 6 , wherein providing the first electric propulsor and the second electric propulsor with the first source of propulsion power from the generator comprises providing the first electric propulsor with the first source of propulsion power from a first stator of the generator, and providing the second electric propulsor with the first source of propulsion power from a second stator of the generator.

10. The system of claim 6 , wherein providing the first electric propulsor and the second electric propulsor with the second source of propulsion power from the at least one motor inverter comprises providing the first electric propulsor with the second source of propulsion power from a first inverter and providing the second electric propulsor with the second source of propulsion power from a second inverter.

11. A hybrid electric aircraft propulsion system, the system comprising:
a thermal engine configured for outputting rotational mechanical power;
a generator configured for generating a first source of alternating current (AC) electric power from the rotational mechanical power;
at least one motor inverter configured to convert DC electric power received from a DC power source to AC electric power to provide a second source of AC electric power independent from the first source of AC electric power;
a first electric propulsor and a second electric propulsor operatively coupled to the generator to receive AC electric power therefrom through respective first motor stators and operatively coupled to the at least one motor inverter to receive AC electric power therefrom, through respective second motor stators; and
a controller configured for monitoring a frequency of the

Assignees

• Pratt & Whitney Canada

Inventors

• Latulipe Eric
• Freer Richard

Classifications

• B64D35/025

  of parallel type · CPC title

• B64D35/024

  of series type · CPC title

• B64D31/18

  for hybrid-electric power plants · CPC title

• B64D27/33

  Hybrid electric aircraft · CPC title

• H02P6/12 Primary

  Monitoring commutation; Providing indication of commutation failure · CPC title