Architecture for an electric power generator for aviation

Patent metadata

Field	Value
Publication number	US-12334785-B2
Application number	US-202318150570-A
Country	US
Kind code	B2
Filing date	Jan 5, 2023
Priority date	Jan 5, 2022
Publication date	Jun 17, 2025
Grant date	Jun 17, 2025

Abstract

A system, apparatus, and/or method for an aircraft that provides a novel independent-speed variable-frequency generator for aviation power generation. The generator architecture utilizes a 2-stage generator architecture with a wound rotor PM exciter (PME) that provides excitation to the rotor of a generator. A rotating bi-directional AC/DC/AC electric power converter connects the rotor windings of the exciter and the generator.

First claim

What is claimed is:

1. An electric power generator for an aircraft, comprising:
a two-stage variable-frequency generator including a main generator, a permanent magnet exciter, a rotating bi-directional AC/DC/AC electric power converter system, and a controller;
wherein the rotating bi-directional AC/DC/AC electric power converter system is coupled to a rotatable shaft;
wherein the rotating bi-directional AC/DC/AC electric power converter system includes a first rotating bi-directional electric power converter for AC/DC conversion and a second rotating bi-directional electric power converter for DC/AC conversion;
wherein the first rotating bi-directional electric power converter and the second rotating bi-directional electric power converter are disposed adjacent to one another along the rotatable shaft; and
wherein the first rotating bi-directional electric power converter is electrically coupled to the second rotating bi-directional electric power converter via a DC power link.

2. The electric power generator of claim 1 , wherein the two-stage variable-frequency generator comprises a two-stage independent-speed variable-frequency generator.

3. The electric power generator of claim 1 , wherein the two-stage variable-frequency generator comprises a two-stage variable-speed variable-frequency generator.

4. The electric power generator of claim 1 , wherein the rotating bi-directional AC/DC/AC electric power converter system being coupled to the rotatable shaft includes comprises a first rotor winding of the permanent magnet exciter and a second rotor winding of the main generator being coupled to the rotatable shaft.

5. The electric power generator of claim 1 , wherein the controller includes a first controller for controlling the first rotating bi-directional electric power converter for AC/DC conversion, and a second controller for controlling the second rotating bi-directional electric power converter for DC/AC conversion.

6. The electric power generator of claim 5 , wherein the first controller for controlling the first rotating bi-directional electric power converter for AC/DC conversion monitors voltage of a first rotor winding of the permanent magnet exciter and monitors voltage of the DC power link, and controls the first rotating bi-directional electric power converter to control voltage level of the DC power link based upon the voltage of the first rotor winding of the permanent magnet exciter and the voltage of the DC power link.

7. The electric power generator of claim 5 , wherein the second controller for controlling the second rotating bi-directional electric power converter for DC/AC conversion monitors voltage of a first stator winding of the main generator and monitors voltage of a first rotor winding of the main generator, and controls the second rotating bi-directional electric power converter based upon the voltage of the first rotor winding of the main generator and the voltage of the first stator winding of the main generator.

8. The electric power generator of claim 5 , wherein the first controller communicates wirelessly with the first rotating bi-directional electric power converter.

9. The electric power generator of claim 5 , wherein the second controller communicates wirelessly with the second rotating bi-directional electric power converter.

10. The electric power generator of claim 1 , wherein the main generator includes a first stator winding that is electrically connected to an AC power bus and a first rotor winding;
wherein the permanent magnet exciter includes a second rotor winding;
wherein the second rotor winding is controllable to a variable frequency; and
wherein the controller controls the first stator winding to provide an output to the AC power bus at a constant frequency.

11. The electric power generator of claim 10 , wherein the permanent magnet exciter is decoupled from the main generator by the rotating bi-directional AC/DC/AC electric power converter system.

12. The electric power generator of claim 11 , wherein the permanent magnet exciter is operable to generate electric power at a frequency that is variable coincident with the operation of the first rotor winding of the main generator at the constant frequency.

13. An electric power generator for an aircraft, comprising:
a two-stage variable-frequency generator including a main generator and a permanent magnet exciter, a controllable rectifier, and a controller;
wherein the permanent magnet exciter includes a first rotor winding that is coupled to a rotatable shaft;
wherein a first rotating bi-directional electric power converter and a second rotating bi-directional electric power converter are disposed adjacent to one another along the rotatable shaft;
wherein the controllable rectifier is arranged to rectify electric power between the first rotor winding of the permanent magnet exciter and a field winding of the main generator; and
wherein the controller regulates a stator output voltage of the main generator according to a control law.

14. The electric power generator of claim 13 , wherein the control law operates in accordance with the following relationship:
V 6 =( M 1 ·ω sh 2 −M 2 ·I 3 ·ω sh )· D

wherein:
V 6 represents the stator output voltage of the main generator,
I 3 represents current through the first rotor winding of the permanent magnet exciter,
ω sh represents rotating speed of the shaft,
D represents duty cycle, value from 0 to 1, and
M 1 and M 2 represent constants.

15. A system for electric power generation in an aircraft, comprising:
an electric power generator having a rotatable shaft coupled to an engine, and a controller;
the electric power generator including a two-stage variable-frequency generator including a main generator, a permanent magnet exciter, a rotating bi-directional AC/DC/AC electric power converter system;
wherein the rotating bi-directional AC/DC/AC electric power converter system is coupled to the rotatable shaft;
wherein the rotating bi-directional AC/DC/AC electric power converter system includes a first rotating bi-directional electric power converter for AC/DC conversion and a second rotating bi-directional electric power converter for DC/AC conversion; and
wherein the first rotating bi-directional electric power converter and the second rotating bi-directional electric power converter are disposed adjacent to one another along the rotatable shaft.

16. The system of claim 15 , wherein the two-stage variable-frequency generator comprises a two-stage variable-speed variable-frequency generator.

17. The system of claim 15 , wherein the rotating bi-directional AC/DC/AC electric power converter system being coupled to the rotatable shaft comprises a first rotor winding of the permanent magnet exciter and a second rotor winding of the main generator being coupled to the rotatable shaft.

18. The system of claim 15 , wherein the controller includes a first controller for controlling the first rotating bi-directional electric power converter for AC/DC conversion, and a second controller for controlling the second rotating bi-directional electric power converter for DC/AC conversion.

19. The system of claim 18 , wherein the first controller for controlling the first rotating bi-directional electric power converter for AC/DC conversion monitors voltage of a first rotor winding of the permanent magnet exciter and monitors voltage of the DC power link, and controls the first rotating bi-directional electric power converter to control voltage level of the DC

Assignees

• Boeing Co

Inventors

• Vannest Jeremiah
• Gao Lijun
• Zhang Julia
• Liu Shengyi

Classifications

• H02J2105/32

  for aircrafts · CPC title

• B64D27/24

  using steam or spring force (jet aircraft B64D27/16) · CPC title

• B64D27/34

  All-electric aircraft · CPC title

• B64D31/16

  for electric power plants · CPC title

• B64D2221/00

  Electric power distribution systems onboard aircraft · CPC title