Motor air flow cooling

Patent metadata

Field	Value
Publication number	US-9673673-B2
Application number	US-201314076171-A
Country	US
Kind code	B2
Filing date	Nov 9, 2013
Priority date	Sep 23, 2008
Publication date	Jun 6, 2017
Grant date	Jun 6, 2017

Abstract

In one possible embodiment, an aircraft electric motor cooling system is provided having an airflow path through a spinner which includes a first airflow path between an inner rotor and a stator, a second airflow path between an outer rotor the stator and a third airflow path along an outer surface of the outer rotor.

First claim

What is claimed is:

1. An aircraft electric motor cooling system comprising:
a) an airflow path through a spinner comprising:
i) a first airflow path between an inner rotor and a stator;
ii) a second airflow path between an outer rotor and the stator; and
iii) a third airflow path along an outer surface of the outer rotor; and

b) rear cooling fins thermally coupled to a back end of the stator, wherein the rear cooling fins are sized so as to extend into an air stream of an aircraft.

2. The system of claim 1 , wherein the first airflow path extends along inner rotor magnets.

3. The system of claim 2 , wherein the second airflow path extends along outer rotor magnets.

4. The system of claim 2 , wherein the first airflow path extends along a front stator yoke and along a rear stator yoke.

5. The system of claim 1 , wherein the second airflow path extends along outer rotor magnets.

6. The system of claim 5 , wherein the second airflow path extends along a front stator yoke and a rear stator yoke.

7. The system of claim 1 , wherein the second and third airflow paths extend through the rear cooling fins along with an air stream path.

8. The system of claim 1 , further comprising an air stream path extending through the rear stator cooling fins.

9. An electric aircraft motor comprising:
a) an inner rotor connected with an outer rotor;
b) a stator comprising a winding located between the inner rotor and the outer rotor;
c) a spinner; and
d) a cooling system comprising:
i) rear cooling fins thermally coupled to a rear portion of the stator, wherein the rear cooling fins extend into an air stream of an aircraft; and
ii) an airflow path through the spinner comprising:
(1) a first airflow path between an inner rotor and a stator;
(2) a second airflow path between an outer rotor the stator; and
(3) wherein at least a portion of the airflow path through the spinner passes through the rear cooling fins.

10. The motor of claim 9 , further comprising:
a) rear cooling fins thermally coupled to a back end of the stator; and
b) the airflow path through the spinner extending through the rear cooling fins.

11. The motor of claim 9 , wherein the first airflow path extends along inner rotor magnets, and wherein the second airflow path extends along outer rotor magnets.

12. The motor of claim 9 , wherein the first airflow path extends along a front stator yoke and along a rear stator yoke.

13. The motor of claim 9 , wherein the second airflow path extends along a front stator yoke and a rear stator yoke.

14. A method for air cooling an electric aircraft motor comprising:
a) passing an air flow through a spinner;
b) directing a first portion of the air flow to flow between the stator and the inner rotor;
c) directing a second portion of the air flow to flow between the stator and the outer rotor;
d) directing a third portion of the air flow to flow along an outer surface of the outer rotor;
e) passing an air flow from an air stream around the spinner and through rear stator cooling fins; and
f) directing at least some of the airflow that passes through the spinner, through the rear stator cooling fins.

15. The method of claim 14 , wherein the first portion flows along inner rotor magnets.

16. The method of claim 15 , wherein the first portion flows along a front stator yoke and along a rear stator yoke.

17. The method of claim 14 , wherein the second portion of the air flow flows along outer rotor magnets.

18. The method of claim 17 , wherein the second portion flows along a front stator yoke and a rear stator yoke.

19. An aircraft electric motor cooling system comprising:
a) an airflow path through a spinner comprising:
i) a first airflow path between an inner rotor and a stator;
ii) a second airflow path between an outer rotor and the stator;
iii) a third airflow path along an outer surface of the outer rotor; and

b) a front heat sink thermally coupled to a front of the stator, the front heat sink comprising fins connected together by a solid front surface;
c) wherein the airflow path through the spinner comprises a portion passing through the fins of the front heat sink and a portion passing the solid front surface without passing through the fins of the front heat sink.

20. The system of claim 19 , wherein the third airflow path comprises portions of the component path passing through the fins of the front heat sink and the component path passing the one of the solid connecting portions.

Assignees

• Aerovironment Inc

Inventors

• Sheppard Lindsay Aspinwall
• Hibbs Bart Dean

Classifications

• H02K21/12

  with stationary armatures and rotating magnets · CPC title

• Y10T29/49009

  Dynamoelectric machine · CPC title

• H02K16/02

  Machines with one stator and two {or more} rotors · CPC title

• H02K7/14

  Structural association with mechanical loads, e.g. with hand-held machine tools or fans (with fan or impeller for cooling the machine H02K9/06) · CPC title

• H02K3/32

  Windings characterised by the shape, form or construction of the insulation · CPC title