Heat exchangers made from additively manufactured sacrificial templates

Patent metadata

Field	Value
Publication number	US-9976815-B1
Application number	US-201414185665-A
Country	US
Kind code	B1
Filing date	Feb 20, 2014
Priority date	Feb 20, 2014
Publication date	May 22, 2018
Grant date	May 22, 2018

Abstract

A method of manufacturing a heat exchanger including a heat exchanger core of a first material, the method including additive manufacturing a sacrificial scaffold of a second material, the sacrificial scaffold corresponding in shape to that of the heat exchanger core, coating the sacrificial scaffold with a layer of the first material, and removing the sacrificial scaffold to leave behind the heat exchanger core with an integrated self-aligned passage.

First claim

What is claimed is:

1. A method of manufacturing a heat exchanger core of a first material, the method comprising:
additive manufacturing a sacrificial scaffold of a second material, the sacrificial scaffold comprising a first manifold feature, a second manifold feature, and a curved passage feature extending along a curved pathway connecting the first and second manifold features, the sacrificial scaffold corresponding in shape to that of the heat exchanger core;
coating the sacrificial scaffold with a layer of the first material; and
removing the sacrificial scaffold to leave behind the heat exchanger core, the heat exchanger core comprising first and second tubesheets corresponding to the first and second manifold features, and further comprising a curved passage extending along the curved pathway and integrated with the first and second tubesheets and corresponding to the curved passage feature, the first and second tubesheets being concurrently formed with, and self-aligned to, the curved passage, in response to the removing the sacrificial scaffold,
wherein a fluid path is formed through the first and second tubesheets and the curved passage.

2. The method of claim 1 , wherein the additive manufacturing comprises one or more of fused deposition modeling (FDM), electron beam freeform fabricating (EBF 3 ), direct metal laser sintering (DMLS), electron beam melting (EBM), selective laser melting (SLM), selective heat sintering (SHS), selective laser sintering (SLS), plaster-based 3D printing (PP), laminated object manufacturing (LOM), stereolithography (SLA) manufacturing, and digital light processing (DLP).

3. The method of claim 1 , wherein the first material comprises one or more of metals, metal alloys, polymers, ceramics, and composites.

4. The method of claim 1 , wherein the coating of the sacrificial scaffold comprises one or more of electroless deposition, electroplating, chemical vapor deposition, vapor deposition, slurry coating and sintering, electrophoretic coating and sintering, plasma spraying, and dip coating.

5. The method of claim 1 , wherein the removing of the sacrificial scaffold comprises forming an opening through the layer of the first material for allowing access to the second material of the sacrificial scaffold.

6. The method of claim 1 , wherein the removing of the sacrificial scaffold comprises one or more of chemical etching, thermal depolymerizing, sublimating, vaporizing, and melting.

7. The method of claim 1 , further comprising strengthening the heat exchanger core by applying heat treatment.

8. The method of claim 1 , wherein the passage has a circular cross section.

9. The method of claim 1 , wherein the sacrificial scaffold further comprises one or more mechanical support features configured to structurally support the sacrificial scaffold during the additive manufacturing.

10. The method of claim 1 , wherein the curved passage comprises a first set of helices and a second set of helices, each of the first and second set of helices being configured to couple an inlet manifold and an outlet manifold, and
wherein each of the first and second set of helices comprise two or more individual helices having cross sections in shapes of ellipses.

11. The heat method of claim 10 , wherein axes of the two or more individual helices are collinear to within about 5° and to within about 5% of a spacing between the first and second set of helices.

12. The method of claim 1 , wherein the curved passage comprises:
a first wavy passage;
a second wavy passage;
a third wavy passage; and
a fourth wavy passage,
wherein the first, second, third, and fourth wavy passages connect at a plurality of nodes, and
wherein a cross-sectional area of each node is within 20% of a sum of cross-sectional areas of the first, second, third, and fourth wavy passages.

13. The method of claim 12 , wherein the plurality of nodes are collinear and periodically positioned along a length of the first, second, third, and fourth wavy passages.

14. The method of claim 1 , wherein the curved passage comprises a first passage, a second passage, and a third passage, each of the first, second, and third passages being configured to couple an inlet manifold and an outlet manifold, and
wherein each of the first, second, and third passages has a wavy pattern along a lengthwise direction of the first, second, and third passages and has a shape in cross-section, the shape having a first line of symmetry corresponding to a major axis of the shape, and a second line of symmetry perpendicular to the first line of symmetry and corresponding to a minor axis of the shape.

15. The method of claim 14 , wherein all shape of the heat exchanger core on planes normal to the lengthwise direction have areas varying by less than about 10% of a median value of the areas.

16. The method of claim 14 , wherein the area of the cross-section varies by less than 10% of a median value of cross section areas.

17. The method of claim 14 , wherein the shape has four quadrant splines defined by the first and second lines of symmetry, each quadrant spline having rotation symmetry about a midpoint of the quadrant spline.

18. The method of claim 14 , wherein the shape is a tapered ellipse.

19. The method of claim 14 , wherein minor axes of the first, second, and third passages are parallel,
wherein the second passage is arranged between the first and third passages along a direction of the minor axis, and
wherein for every point along a direction corresponding to a major axis of the shape, a summation of separations between the first and second passages and the second and third passages along a direction of the minor axis is within 10% of a median value.

Assignees

• Hrl Lab Llc
• Boeing Co

Inventors

• Roper Christopher S
• Page David
• Schubert Randall C
• Ro Christopher J
• Muley Arun
• Kusuda Charles

Classifications

• B22F10/66

  by mechanical means · CPC title

• B22F10/64

  by thermal means (control of energy beam parameters for post heating B22F10/364) · CPC title

• B22F10/62

  by chemical means · CPC title

• B22F10/47

  characterised by structural features · CPC title

• B22F10/43

  characterised by material · CPC title