Electric machine having notched magnets and integrated cooling

Patent metadata

Field	Value
Publication number	US-2026081504-A1
Application number	US-202519373137-A
Country	US
Kind code	A1
Filing date	Oct 29, 2025
Priority date	Nov 17, 2022
Publication date	Mar 19, 2026
Grant date	—

Abstract

Aircraft and aircraft electric motors include a rotor assembly having a plurality of magnets arranged in magnet Halbach arrays on a magnet support. The magnet support includes a plurality of protrusions defined on surface thereof and each magnet Halbach array includes a respective cut-out notch configured to engage with a respective protrusion. An output shaft is operably coupled to the rotor assembly. A stator having a support structure and at least one winding wrapped about a plurality of stator teeth is configured to generate an electromagnetic field to cause rotation of the rotor assembly. A heat pipe is arranged within each protrusion and configured to transfer heat away from the magnets.

First claim

What is claimed is:

1 . An aircraft electric motor comprising:
a rotor assembly comprising a plurality of magnets arranged in magnet Halbach arrays on a magnet support, wherein the magnet support comprising a plurality of protrusions defined on surface thereof and each magnet Halbach array comprises a respective cut-out notch configured to engage with a respective protrusion; an output shaft operably coupled to the rotor assembly; a stator comprising a support structure and at least one winding wrapped about a plurality of stator teeth, the stator configured to generate an electromagnetic field to cause rotation of the rotor assembly; and a heat pipe arranged within each protrusion of the plurality of protrusions, the heat pipe configured to transfer heat away from the magnets.

2 . The aircraft electric motor of claim 1 , wherein the notch is formed in at least one center magnet of each magnet Halbach array.

3 . The aircraft electric motor of claim 1 , wherein the notch is formed between two split-magnets at ends of adjacent magnet Halbach arrays.

4 . The aircraft electric motor of claim 1 , wherein each heat pipe comprises a forward heat pipe section and an aft heat pipe section arranged between a forward end face and an aft end face of the magnet support.

5 . The aircraft electric motor of claim 4 , wherein the forward heat pipe section is circumferentially offset from the aft heat pipe section.

6 . The aircraft electric motor of claim 4 , wherein the magnet support defines a forward end face and an aft end face and wherein the forward heat pipe section is angled radially inward in a direction from an inflection point between the forward end face and the aft end face to the forward end face and the aft heat pipe section is angled radially inward in a direction from the inflection point to the aft end face.

7 . The aircraft electric motor of claim 1 , further comprising a rotor wrap arranged about the magnet support and configured to structurally support the magnet support.

8 . The aircraft electric motor of claim 1 , wherein the rotor assembly comprises:
an outer rotor and an inner rotor, wherein the stator is arranged radially between the inner rotor and the outer rotor.

9 . The aircraft electric motor of claim 8 , wherein:
each of the inner rotor and the outer rotor comprise magnet Halbach arrays sets with cut-out notches, and each of the inner rotor and the outer rotor comprise respective magnet supports having protrusions engaged with the cut-out notches.

10 . The aircraft electric motor of claim 1 , further comprising one or more thermal dissipation elements on an end face of the magnet support, the thermal dissipation elements configured to increase a surface area of the respective end face of the magnet support.

11 . The aircraft electric motor of claim 10 , wherein the one or more thermal dissipation elements comprise a plurality of pins, fins, and/or protrusions.

12 . The aircraft electric motor of claim 10 , wherein the one or more thermal dissipation elements comprise a surface texturing or surface roughness of the respective end face of the magnet support.

13 . The aircraft electric motor of claim 1 , wherein each heat pipe extends axially from a forward end face of the magnet support to an aft end face of the magnet support and is skewed at an angle relative to a motor axis defined by the rotor assembly.

14 . The aircraft electric motor of claim 1 , wherein each heat pipe is defined by a bore defined in the material of the magnet support that is filled with a phase-change material and plugged at at least one end of the respective heat pipe.

15 . An aircraft comprising:
at least one aircraft electric motor; at least one electrical device; and a power distribution system configured to distribute power from the at least one electric motor to the at least one electrical device, wherein the at least one aircraft electric motor comprises:
a rotor assembly comprising a plurality of magnets arranged in magnet Halbach arrays on a magnet support, wherein the magnet support comprising a plurality of protrusions defined on surface thereof and each magnet Halbach array comprises a respective cut-out notch configured to engage with a respective protrusion;
an output shaft operably coupled to the rotor assembly;
a stator comprising a support structure and at least one winding wrapped about a plurality of stator teeth, the stator configured to generate an electromagnetic field to cause rotation of the rotor assembly; and
a heat pipe arranged within each protrusion of the plurality of protrusions, the heat pipe configured to transfer heat away from the magnets.

16 . The aircraft of claim 15 , wherein the rotor assembly comprises:
an outer rotor and an inner rotor, wherein the stator is arranged radially between the inner rotor and the outer rotor.

17 . The aircraft of claim 15 , further comprising one or more thermal dissipation elements on an end face of the magnet support, the thermal dissipation elements configured to increase a surface area of the respective end face of the magnet support.

18 . The aircraft of claim 15 , wherein each heat pipe comprises a forward heat pipe section and an aft heat pipe section arranged between a forward end face and an aft end face of the magnet support.

19 . The aircraft of claim 15 , wherein each heat pipe extends axially from a forward end face of the magnet support to an aft end face of the magnet support and is skewed at an angle relative to a motor axis defined by the rotor assembly.

20 . The aircraft of claim 15 , wherein each heat pipe is defined by a bore defined in the material of the magnet support that is filled with a phase-change material and plugged at at least one end of the respective heat pipe.

Assignees

• Hamilton Sundstrand Corp

Inventors

• Kuczek Andrzej E
• Tangudu Jagadeesh K

Classifications

• H02K11/33

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

• H02K9/225 Primary

  Heat pipes · CPC title

• H02K9/20

  wherein the cooling medium vaporises within the machine casing · CPC title

• H02K7/116

  with gears · CPC title

• H02K1/30

  using intermediate parts, e.g. spiders · CPC title