Electric machine having multi-function cooling channels

Patent metadata

Field	Value
Publication number	US-12348084-B2
Application number	US-202218081010-A
Country	US
Kind code	B2
Filing date	Dec 14, 2022
Priority date	Dec 14, 2022
Publication date	Jul 1, 2025
Grant date	Jul 1, 2025

Abstract

Stators for aircraft electric motors include a cantilever structure having a supported end and an unsupported end, wherein the cantilever structure includes an inlet support manifold and an outlet support manifold arranged at the supported end and a plurality of cooling plates extending from the inlet support manifold and the outlet support manifold to the unsupported end. A plurality of coils are arranged between and in thermal contact with the cooling plates and a core passes through the plurality of coils and the plurality of cooling plates. Each cooling plate defines a cooling channel that fluidly couples the inlet support manifold and the outlet support manifold, and the coils and the core are structurally supported by the plurality of cooling plates in a cantilevered manner at the supported end.

First claim

What is claimed is:

1. A stator for an aircraft electric motor comprising:
a cantilever structure having a supported end and an unsupported end, wherein the cantilever structure includes an inlet support manifold and an outlet support manifold arranged at the supported end and a plurality of cooling plates extending from the inlet support manifold and the outlet support manifold to the unsupported end;
a plurality of coils arranged between and in thermal contact with the cooling plates;
a core passing through the plurality of coils and the plurality of cooling plates; and
a plurality of magnetic teeth wherein the cooling plates define gaps between adjacent cooling plates and each gap includes a coil of the plurality of coils and a magnetic tooth of the plurality of magnetic teeth,
wherein each cooling plate defines a cooling channel that fluidly couples the inlet support manifold and the outlet support manifold, and
wherein the coils and the core are structurally supported by the plurality of cooling plates in a cantilevered manner at the supported end.

2. The stator of claim 1 , wherein the cantilever structure defines an annular shape and defining an axis through a center of the annular shape.

3. The stator of claim 2 , wherein the inlet support manifold is arranged radially outward from the outlet support manifold.

4. The stator of claim 2 , wherein each of the inlet support manifold and the outlet support manifold are arranged at the same axial position relative to the axis through the center of the annular shape.

5. The stator of claim 1 , further comprising a bonding material configured to bond the plurality of cooling plates, the core, and the plurality of coils together.

6. The stator of claim 5 , wherein the bonding material comprises at least one of an epoxy material, a thermoset material, a thermoplastic material, or a polymer material.

7. The stator of claim 1 , further comprising a cooling fluid within the cooling channels of the plurality of cooling plates.

8. A stator for an aircraft electric motor comprising:
a cantilever structure having a supported end and an unsupported end, wherein the cantilever structure includes an inlet support manifold and an outlet support manifold arranged at the supported end and a plurality of cooling plates extending from the inlet support manifold and the outlet support manifold to the unsupported end;
a plurality of coils arranged between and in thermal contact with the cooling plates; and
a core passing through the plurality of coils and the plurality of cooling plates,
wherein each cooling plate defines a cooling channel that fluidly couples the inlet support manifold and the outlet support manifold,
wherein the coils and the core are structurally supported by the plurality of cooling plates in a cantilevered manner at the supported end, and
wherein the inlet support manifold defines an inlet cavity therein and the outlet support manifold defines an outlet cavity therein, wherein the inlet cavity is fluidly coupled to the outlet cavity by the cooling channels within the plurality of cooling plates.

9. The stator of claim 8 , wherein the cantilever structure defines an annular shape and defining an axis through a center of the annular shape.

10. The stator of claim 9 , wherein the inlet support manifold is arranged radially outward from the outlet support manifold.

11. The stator of claim 9 , wherein each of the inlet support manifold and the outlet support manifold are arranged at the same axial position relative to the axis through the center of the annular shape.

12. The stator of claim 8 , further comprising a bonding material configured to bond the plurality of cooling plates, the core, and the plurality of coils together.

13. The stator of claim 12 , wherein the bonding material comprises at least one of an epoxy material, a thermoset material, a thermoplastic material, or a polymer material.

14. The stator of claim 8 , further comprising a cooling fluid within the cooling channels of the plurality of cooling plates.

15. A stator for an aircraft electric motor comprising:
a cantilever structure having a supported end and an unsupported end, wherein the cantilever structure includes an inlet support manifold and an outlet support manifold arranged at the supported end and a plurality of cooling plates extending from the inlet support manifold and the outlet support manifold to the unsupported end;
a plurality of coils arranged between and in thermal contact with the cooling plates; and
a core passing through the plurality of coils and the plurality of cooling plates,
wherein each cooling plate defines a cooling channel that fluidly couples the inlet support manifold and the outlet support manifold,
wherein the coils and the core are structurally supported by the plurality of cooling plates in a cantilevered manner at the supported end, and
wherein the inlet support manifold defines a first inlet cavity and a second inlet cavity, wherein the first inlet cavity is fluidly coupled to the second inlet cavity by at least one metering aperture and the second inlet cavity is fluidly coupled to the cooling channels of the plurality of cooling plates.

16. The stator of claim 15 , wherein the cantilever structure defines an annular shape and defining an axis through a center of the annular shape.

17. The stator of claim 16 , wherein the inlet support manifold is arranged radially outward from the outlet support manifold.

18. The stator of claim 16 , wherein each of the inlet support manifold and the outlet support manifold are arranged at the same axial position relative to the axis through the center of the annular shape.

19. The stator of claim 15 , further comprising a bonding material configured to bond the plurality of cooling plates, the core, and the plurality of coils together.

20. The stator of claim 15 , further comprising a cooling fluid within the cooling channels of the plurality of cooling plates.

Assignees

• Hamilton Sundstrand Corp

Inventors

• Kuczek Andrzej E
• Tangudu Jagadeesh K
• Saviers Kimberly R
• Turney Joseph E
• Alahyari Abbas A

Classifications

• H02K9/19

  for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil · CPC title

• B64D2221/00

  Electric power distribution systems onboard aircraft · CPC title

• B64D33/08

  of power plant cooling systems · CPC title

• B64D27/24

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

• H02K1/18

  Means for mounting or fastening magnetic stationary parts on to, or to, the stator structures · CPC title