Engine shaft integrated motor

Patent metadata

Field	Value
Publication number	US-11022004-B2
Application number	US-201715475935-A
Country	US
Kind code	B2
Filing date	Mar 31, 2017
Priority date	Mar 31, 2017
Publication date	Jun 1, 2021
Grant date	Jun 1, 2021

Abstract

A method of integrating an electric motor or generator as part of an aircraft engine shaft. The motor is used to rotate the rotor so as to cool the rotor in a temperature gradient. The generator is used to provide power to the aircraft. In one or more examples, a power generation device includes a gas turbine engine including a rotor shaft and a first casing around the rotor shaft; a transmission connecting the rotor shaft to a gearbox, the transmission comprising a drive shaft and a second casing around the drive shaft; and a brushless DC motor integrated with the engine and including one or more permanent magnets and one or more coils.

First claim

What is claimed is:

1. A power generation device, comprising:
a gas turbine engine comprising:
a rotor shaft;
a high pressure compressor driven by the rotor shaft, the high pressure compressor comprising rotor blades attached to the rotor shaft; and

a casing around the rotor shaft;
one or more permanent magnets attached to the rotor shaft;
one or more coils attached to the casing;
a power supply;
an aircraft electrical system;
a switch connecting the power supply to the coils when the power generation device is operating as a motor and connecting the aircraft electrical system to the coils when the power generation device is operating as a generator; and
the aircraft electrical system connected to the coils, wherein:
the aircraft electrical system receives electrical power when:
 the gas turbine engine is running in a combustion mode so as to turn the rotor shaft and the permanent magnets on the rotor shaft, and
 one or more first magnetic fields generated by the one or more permanent magnets interact with the one or more coils; or
the rotor shaft turns:
 the one or more coils generate one or more second magnetic fields in response to current supplied from the power supply and the one or more first magnetic fields interact with the one or more second magnetic fields; and
so as to reduce or prevent thermal bowing of the rotor shaft in a temperature gradient when the gas turbine engine is cooling down after shutdown of the gas turbine engine.

2. The power generation device of claim 1 , wherein the electrical power is used to either power an airplane system or an engine system.

3. The power generation device of claim 1 , further comprising a transmission connecting the rotor shaft to a gearbox and wherein the gearbox does not include an engine turning motor.

4. The power generation device of claim 1 , wherein the permanent magnets are on the rotor shaft and adjacent the rotor blades.

5. The power generation device of claim 1 , further comprising:
one or more electromagnets comprising the coils; and
a nacelle housing the gas turbine engine, wherein the rotor shaft has a longitudinal axis, and
the nacelle comprises trapped air creating the temperature gradient perpendicular to the longitudinal axis.

6. The device of claim 1 , further comprising a space between the one or more coils and the one or more permanent magnets, wherein nothing is in the space.

7. The device of claim 1 , wherein:
the rotor shaft has a longitudinal axis and an outer surface,
the casing has an inner surface facing the outer surface and the longitudinal axis,
the one or more permanent magnets are attached to the outer surface of the rotor shaft,
the one or more coils are attached to the inner surface of the casing, and
the gas turbine engine running in the combustion mode turns the rotor shaft about the longitudinal axis.

8. An aircraft comprising a power generation device, comprising:
a gas turbine engine including a rotor shaft and a first casing around the rotor shaft; wherein:
the rotor shaft has a first longitudinal axis and a first outer surface,
the first casing has a first inner surface facing the first outer surface and the first longitudinal axis;

a transmission connecting the rotor shaft to a gearbox, the transmission comprising a drive shaft and a second casing around the drive shaft; wherein:
the drive shaft has a second longitudinal axis and a second outer surface,

the second casing has a second inner surface facing the second outer surface and the second longitudinal axis;
a plurality of permanent magnets disposed in one or more magnet pairs each including a first magnet and a second magnet;
a plurality of coils disposed in one or more coil pairs each including a first coil and a second coil, wherein:
 the first magnet and the second magnet are attached at diametrically opposite positions on at least one of the first outer surface or the second outer surface,
 the first coil and the second coil are attached at diametrically opposite positions on at least one of the first inner surface or the second inner surface, and
 the first magnet has a north polarity facing the first inner surface or the second inner surface and the second magnet has a south polarity facing the first inner surface or the second inner surface; and
an aircraft electrical system connected to the coils when the power generation device is operating as a generator, wherein:
the aircraft electrical system receives electrical power generated using the plurality of coils when:

 the gas turbine engine is running in a combustion mode so as to turn the permanent magnets on at least one of the rotor shaft or the drive shaft, and
 first magnetic fields generated by the plurality of permanent magnets interact with the plurality of coils.

9. The power generating device of claim 8 , further comprising:
a circuit comprising the aircraft electrical system, a driving circuit, and a switch configured so that the driving circuit is connected to the coils when the power generation device is operating as a motor and the aircraft electrical system is connected to the coils when the power generation device is operating as the generator;
the driving circuit connected or comprising a power supply and providing a current to the coils so that a second magnetic field of the first coil has an opposite polarity to a third magnetic field of the second coil, the second magnetic field and the third magnetic field interacting with the permanent magnets to drive the rotor shaft when the gas turbine engine is cooling down; and
a computer connected to the driving circuit, the computer and the driving circuit energizing the coils so that the permanent magnets and the coils operate in a direct current (DC) brushless motor configuration.

10. The power generation device of claim 9 , further comprising the computer controlling the current from the power supply such that:
the electrical power is provided to the coils so as to drive the rotor shaft after engine shut down, and
an interaction of the second magnetic field and the third magnetic field with the permanent magnets rotates the rotor shaft at one or more speeds.

11. The power generation device of claim 10 , wherein the speeds are between 0.5-2.0 rpm (revolutions per minute).

12. The device of claim 10 , wherein a rotation of the rotor shaft includes pulsed rotation.

13. The device of claim 10 , wherein a rotation of the rotor shaft includes clocked rotation and/or sporadic rotation.

14. The power generating device of claim 8 , further comprising a computer connected to the gas turbine engine, wherein:
the permanent magnets include the first magnet and the second magnet attached to the rotor shaft and the first coil and the second coil attached to the first inner surface,
the electrical power generated by the coils powers the electrical system during times of peak electrical loading of the electrical system, and
the computer reduces fuel consumption in the gas turbine engine as compared to when the gas turbine engine is used to power the electrical system during the times of peak electrical loading without the electrical power from the coils.

15. A power generation device, comprising:
a gas turbine engine including a rotor shaft and a first casing around the rotor shaft;
a transmission connecting the rotor shaft to a gearbox, the transmission comprising a drive shaft and a second casing around the drive shaft; and
a brushless direct current (DC) generator, wherein the brushless DC generator comprises:
a plurality of permanent magnets, wherein:
the plurality of permanent mag

Assignees

• Boeing Co

Inventors

• Duce Jeffrey Lynn
• Karnofski Kent E
• Oehler Stephen D

Classifications

• B64D31/06

  actuated automatically · CPC title

• F01D25/36 Primary

  using electric motors · CPC title

• F01D15/10 Primary

  Adaptations for driving, or combinations with, electric generators · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F02C7/36

  Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user ({F02C3/107 - F02C3/13 and} F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H) · CPC title