Aircraft power and propulsion systems comprising permanent magnet electrical machines

Patent metadata

Field	Value
Publication number	US-12431748-B2
Application number	US-202318204112-A
Country	US
Kind code	B2
Filing date	May 31, 2023
Priority date	Jun 27, 2022
Publication date	Sep 30, 2025
Grant date	Sep 30, 2025

Abstract

Reconfigurable permanent magnet electrical machines and aircraft power and propulsion systems comprising such electrical machines are described. In one aspect, an aircraft power and propulsion system comprises: a gas turbine engine; a permanent magnet electrical machine comprising a rotor drivingly coupled to a spool of the gas turbine engine, and a stator comprising windings controllably switchable between a star configuration and a delta configuration; a DC electrical network; an AC:DC power electronics converter, an AC side of which is connected to terminals of the stator windings of the electrical machine and a DC side of which is connected to the DC electrical network; and a control system. The control system is configured to monitor at least one operating condition of the power and propulsion system and to control the switching of the stator windings between the star configuration and the delta configuration based on the at least one operating condition.

First claim

The invention claimed is:

1. An aircraft power and propulsion system, comprising:
a gas turbine engine;
a DC electrical network;
a permanent magnet electrical machine comprising a rotor drivingly coupled to a spool of the gas turbine engine, and a stator comprising windings controllably switchable between a star configuration and a delta configuration;
an AC:DC power electronics converter, an AC side of which is connected to terminals of the stator windings of the electrical machine and a DC side of which is connected to the DC electrical network;
a controllable switching arrangement, the switching arrangement having a first switching state in which the stator windings are in the star configuration, a second switching state in which the stator windings are in the delta configuration and a third switching state in which the terminals of the stator windings are connected together; and
a control system configured to
monitor at least one operating condition of the power and propulsion system and to control the switching of the stator windings between the star configuration and the delta configuration based on the at least one operating condition,
control the switching state of the switching arrangement to switch the stator windings between the star configuration and the delta configuration, and
monitor the power and propulsion system for faults and, in response to detecting to a fault, switch the switching arrangement to the third switching state.

2. The aircraft power and propulsion system of claim 1 , wherein the at least one operating condition is indicative of a terminal voltage at terminals of the stator windings, and the control system is configured to:
switch the stator windings from the star configuration to the delta configuration in response to an increase in the terminal voltage; and
switch the stator windings from the delta configuration to the star configuration in response to a decrease in the terminal voltage.

3. The aircraft power and propulsion system of claim 1 , wherein the at least one operating condition comprises one or more of: terminal voltage at the terminals of the stator windings of the electrical machine; a speed of the rotor of the electrical machine; and/or a speed of the spool of the gas turbine engine.

4. The aircraft power and propulsion system of claim 1 , wherein the at least one operating condition is indicative of an electrical power demand of one or more electrical loads connected to the DC electrical network, and the control system is configured to:
switch the stator windings from the delta configuration to the star configuration in response to an increase in the electrical power demand; and
switch the stator windings from the star configuration to the delta configuration in response to a decrease in the electrical power demand.

5. The aircraft power and propulsion system of claim 1 , wherein the at least one operating condition is indicative of both a terminal voltage at the terminals of the stator windings of the electrical machine and an electrical power demand of one or more electrical loads connected to the DC electrical network; and the control system is configured to control the switching of the stator windings between the star configuration and the delta configuration based on both the terminal voltage and the electrical power demand.

6. The aircraft power and propulsion system of claim 1 , wherein
the switching arrangement comprises a first set of switches and a second set of switches,
in the star configuration of the stator windings, the first set of switches are closed and the second set of switches are open; and
in the delta configuration of the stator windings, the first set of switches are open and the second set of switches are closed.

7. The aircraft power and propulsion system of claim 1 , wherein the AC:DC power electronics converter is a passive AC:DC power electronics converter.

8. The aircraft power and propulsion system of claim 1 , wherein the control system is further configured to control a voltage level at the DC side of the AC:DC power electronics converter by controlling the AC:DC power electronics converter to implement one or more of modulation index control, field weakening control or fielding strengthening control.

9. The aircraft power and propulsion system of claim 1 , wherein the permanent magnet electrical machine has an impedance of at least 1.0 per-unit.

10. The aircraft power and propulsion system of claim 1 , wherein the rotor of the electrical machine and the spool of the gas turbine engine are drivingly coupled in a direct drive arrangement, whereby a rotational speed of the rotor and the spool are equal.

11. The aircraft power and propulsion system of claim 1 , wherein the spool is a high-pressure spool of a multi-spool gas turbine engine.

12. The aircraft power and propulsion system of claim 1 , wherein the DC network has a voltage of at least 270 V.

13. An aircraft comprising the aircraft power and propulsion system of claim 1 .

14. A method of controlling an aircraft power and propulsion system, the system comprising a gas turbine engine; a permanent magnet electrical machine comprising a rotor drivingly coupled to a spool of the gas turbine engine and a stator comprising windings controllably switchable between a star configuration and a delta configuration; a DC electrical network; an AC:DC power electronics converter, an AC side of which is connected to terminals of the stator windings of the electrical machine and a DC side of which is connected to the DC electrical network; a switching arrangement, the switching arrangement having a first switching state in which the stator windings are in the star configuration, a second switching state in which the stator windings are in the delta configuration, and a third switching state in which the terminals of the stator windings are connected together, the method comprising:
monitoring at least one operating condition of the power and propulsion system;
controlling, based on the at least one operating condition, the switching of the stator windings of the electrical machine between the star configuration and the delta configuration by controlling the switching state of the switching arrangement;
monitoring the DC electrical network for faults; and
responsive to detecting a fault in the DC electrical network, switching the switching arrangement to the third switching state.

15. The method of claim 14 , wherein the at least one operating condition is indicative of a terminal voltage at the terminals of the stator windings of the electrical machine and/or an electrical power demand of one or more electrical loads connected to the DC electrical network.

16. The method of claim 15 , wherein controlling the switching of the stator windings of the electrical machine between the star configuration and the delta configuration comprises:
switching the stator windings from the star configuration to the delta configuration in response to an increase in the terminal voltage at the terminals of the stator windings and/or a decrease in the electrical power demand; and
switching the stator windings from the delta configuration to the star configuration in response to a decrease in the terminal voltage at the terminals of the stator windings and/or an increase in the electrical power demand.

Assignees

• Rolls Royce Plc

Inventors

• Trainer David R
• Chong Ellis F H
• Sweet Mark
• Incerpi Gian

Classifications

• H02K7/1823

  structurally associated with turbines or similar engines · CPC title

• H02K3/28

  Layout of windings or of connections between windings (windings for pole-changing H02K17/06, H02K17/14, H02K19/12, H02K19/32) · CPC title

• B64D2221/00

  Electric power distribution systems onboard aircraft · CPC title

• B64D27/10

  of gas-turbine type  (jet aircraft B64D27/16) · CPC title

• H02K11/33

  Drive circuits, e.g. power electronics (H02K11/38 takes precedence) · CPC title