Hybrid electric propulsion system and method of operation

Patent metadata

Field	Value
Publication number	US-11283376-B2
Application number	US-201916411484-A
Country	US
Kind code	B2
Filing date	May 14, 2019
Priority date	Sep 6, 2018
Publication date	Mar 22, 2022
Grant date	Mar 22, 2022

Abstract

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.

First claim

The invention claimed is:

1. A hybrid electric aircraft propulsion system comprising:
a thermal engine;
a generator coupled to the thermal engine, wherein the generator comprises a first generator stator for powering the first electric propulsor and a second generator stator for powering the second electric propulsor;
a first electric propulsor operatively connected to the generator to receive alternating current (AC) electric power therefrom;
a second electric propulsor;
a third electric propulsor operatively connected to the first stator generator to receive AC electric power therefrom;
a fourth electric propulsor;
a generator inverter operatively connected to the generator to convert AC electric power to direct current (DC) electric power;
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; and
a second motor inverter connected between the generator inverter and the fourth electric propulsor to convert DC electric power to AC electric power and provide the AC electric power to the fourth electric propulsor;
wherein the first generator stator is selectively connected to one of the first electric propulsor and the third electric propulsor.

2. The system of claim 1 , wherein the generator inverter and the first motor inverter are operatively connected to a DC power source.

3. The system of claim 1 , wherein the second motor inverter is selectively connected to the fourth electric propulsor and the third electric propulsor.

4. The system of claim 1 , wherein the generator inverter is selectively connected to one of the second generator stator, the first electric propulsor, and the third electric propulsor.

5. The system of claim 1 , wherein the first electric propulsor and the second electric propulsor are configured for mounting to a first wing of an aircraft, and wherein the third electric propulsor and the fourth electric propulsor are configured for mounting to a second wing of the aircraft.

6. The system of claim 1 , wherein the first electric propulsor and the third electric propulsor are configured for mounting to a first wing of an aircraft, and wherein the second electric propulsor and the fourth electric propulsor are configured for mounting to a second wing of the aircraft.

7. The system of claim 1 , wherein the first electric propulsor is configured for mounting to a first wing of an aircraft, and wherein the second electric propulsor is configured for mounting to a second wing of the aircraft.

8. A method for operating a hybrid electric aircraft propulsion system, the method comprising:
generating a first source of alternating current (AC) electric power from a generator and providing the AC electric power from the generator to a first electric propulsor, wherein the first source of AC electric power is generated from a first generator stator of the generator, and the second source of AC electric power selectively from a second generator stator of the generator, and wherein the first source of AC electric power is selectively provided to the first electric propulsor and a third electric propulsor;
generating a second source of AC electric power from the generator;
converting the second source of AC electric power into direct current (DC) electric power at a generator inverter;
reconverting the DC electric power into the second source of AC electric power at a first motor inverter;
selectively providing the second source of AC electric power to a second electric propulsor and the first electric propulsor from the first motor inverter;
providing, from the generator inverter, the DC electric power to a second motor inverter;
reconverting the DC electric power into the second source of AC electric power at the second motor inverter; and
providing the second source of AC electric power to a fourth electric propulsor from the second motor inverter.

9. The method of claim 8 , further comprising providing DC electric power to the first motor inverter and to the generator inverter from a DC power source.

10. The method of claim 8 , further comprising selectively providing the second source of AC electric power to the third electric propulsor and the fourth electric propulsor from the second motor inverter.

11. The method of claim 8 , further comprising:
disconnecting the generator from the first electric propulsor;
applying the second source of AC electric power from the first motor inverter to the first electric propulsor while the generator is disconnected;
adjusting power to the first electric propulsor by the first motor inverter so as to match a frequency of the first electric propulsor to a frequency of the generator; and
reconnecting the generator to the first electric propulsor.

12. The method of claim 8 , further comprising disconnecting the generator inverter from the generator and connecting the generator inverter to one of the first electric propulsor and the third electric propulsor.

13. The method of claim 12 , further comprising:
disconnecting the generator from the one of the first electric propulsor and the third electric propulsor;
applying the second source of AC electric power from the generator inverter to the one of the first electric propulsor and the second electric propulsor;
adjusting power to the one of the first electric propulsor and the third electric propulsor so as to match a frequency of the one of the first electric propulsor and the third electric propulsor with a frequency of the generator; and
reconnecting the generator to the one of the first electric propulsor and the third electric propulsor.

14. The method of claim 12 , further comprising resynchronizing a frequency of the one of the first electric propulsor and the third electric propulsor with a frequency of the generator by modulating and applying the second source of AC electric power from the generator inverter to the one of the first electric propulsor and the third electric propulsor.

15. The method of claim 8 , further comprising resynchronizing a frequency of the first electric propulsor with a frequency of the generator by modulating and applying the second source of AC electric power from the first motor inverter to the first electric propulsor.

16. An aircraft comprising a hybrid electric aircraft propulsion system, the system comprising:
a thermal engine;
a generator coupled to the thermal engine, wherein the generator comprises a first generator stator for powering the first electric propulsor and second generator stator for powering the second electric propulsor;
a first electric propulsor operatively connected to the generator to receive alternating current (AC) electric power therefrom;
a second electric propulsor;
a third electric propulsor operatively connected to the first stator generator to receive AC electric power therefrom;
a fourth electric propulsor;
a generator inverter operatively connected to the generator to convert AC electric power to direct current (DC) electric power;
a first motor inverter operatively connected to the generator inverter and to the second electric propulsor and configured to receive the DC electric power and provide the second electric propulsor with AC electric power; and
a second motor inverter connected between the generator inverter and the fourth electric propulsor to convert DC electric power to AC electric power and provide the AC

Assignees

• Pratt & Whitney Canada

Inventors

• Latulipe Eric
• Freer Richard

Classifications

• B64D35/023

  of series-parallel type · CPC title

• 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