Method for additive manufacturing nacelle inlet lipskins

Patent metadata

Field	Value
Publication number	US-11819945-B2
Application number	US-201916670278-A
Country	US
Kind code	B2
Filing date	Oct 31, 2019
Priority date	Sep 29, 2017
Publication date	Nov 21, 2023
Grant date	Nov 21, 2023

Abstract

An apparatus for fabricating a part, comprising a curved shaft; a build plate connected to the curved shaft; a motor; and a transmission connecting the motor and the curved shaft. The build plate moves along a curved path having a radius of curvature originating on an axis when the transmission transfers power from the motor to the curved shaft. Material deposited on the build plate along the curved path forms the part comprising a solid of revolution around the axis. In one or more examples, the part is an aircraft engine inlet.

First claim

What is claimed is:

1. An engine inlet, composing:
an additively manufactured part comprising arc segments comprising a plurality of layers deposited by additive manufacturing one on top of another, each of the layers having an inlet cross-sectional profile including a cross-sectional profile of a lipskin and a cross-sectional profile of a forward bulkhead, wherein the layers comprise an edge comprising an arc.

2. The engine inlet of claim 1 , wherein the arc comprises a radius of curvature R originating on an axis, and an outermost end of each of the layers furthest from the axis is thicker than an innermost end of each of the layers closest to the axis.

3. The engine inlet of claim 1 , further comprising a plurality of the additively manufactured parts joined together.

4. The engine inlet of claim 3 , wherein the parts comprise a first part and a second part, the engine inlet further comprising a joint joining the first part to the second part, the joint comprising a first end of one of the layers in the first part overlapping with a second end of another of the layers in the second part.

5. The engine inlet of claim 3 , wherein:
the parts include a first part and a second part,
the layers in the first part include a first layer and the layers in the second part comprise a second layer,
the first layer comprises a first tab,
the second layer comprises a second tab, and
the first tab overlaps the second tab.

6. The engine inlet of claim 5 , further comprising a fastener attaching the first tab to the second tab.

7. An aircraft including the engine inlet of claim 5 , wherein the layers comprise melted metal particles.

8. The engine inlet of claim 1 further comprising:
the additively manufactured part having the edge including the arc, the additively manufactured part comprising an entire cross-section of the engine inlet, the part manufactured using a process comprising:
driving a curved shaft connected to a build plate, the build plate moving along a curved path having a radius of curvature R originating on the axis; and
depositing the layers comprising material on the build plate along the curved path, wherein the material forms the additively manufactured part comprising the edge including the arc having a center coinciding with the axis.

9. The engine inlet of claim 1 , wherein the layers include a tab for joining to an additional part.

10. The engine inlet of claim 1 , wherein the layers comprise melted metal particles.

11. An engine inlet comprising:
a plurality of parts each comprising a plurality of layers deposited by additive manufacturing one on top of another, each of the layers having an inlet cross-sectional profile including a cross-sectional profile of a lipskin and a cross-sectional profile of a forward bulkhead, wherein the parts are joined together.

12. The engine inlet of claim 11 , wherein each of the layers include a cross-sectional profile of an outer barrel connected to the cross-sectional profile of the lipskin.

13. The engine inlet of claim 12 , wherein one or more of the layers further comprise:
a cross-sectional profile of a stiffener connected to the cross-sectional profile of the outer barrel;
a cross-sectional profile of an inner barrel attached to the cross-sectional profile of the forward bulkhead;
a cross-sectional profile of the inner barrel connected to the cross-sectional profile of the outer barrel; and
a cross-sectional profile of an inlet attach flange connected to the cross-sectional profile of the inner barrel.

14. The engine inlet of claim 11 , wherein the layers each comprise a thickness of 1-500 micrometers.

15. The engine inlet of claim 11 , wherein one or more of the plurality of the layers comprise an end including an overlap for joining one of the parts to another one of the parts.

16. The engine inlet of claim 11 , wherein the one or more layers comprise a tab for attaching to an additional part.

17. The engine inlet of claim 11 , wherein the parts each comprise an edge comprising an arc having a radius of curvature originating on an axis, wherein an outermost end of each of the layers furthest from the axis is thicker than an innermost end of each of the layers closest to the axis.

18. A part, comprising:
an engine inlet comprising a plurality of sections, each of the plurality of the sections comprising a single additively manufactured piece having an inlet cross-sectional profile including a cross-sectional profile of a lipskin connected to a cross-sectional profile of a forward bulkhead.

19. The part of claim 18 , wherein each of the sections includes a tab overlapping with the tab in an adjacent one of the sections so as to join the sections.

20. The engine inlet of claim 11 , wherein the parts comprise a first part and a second part, the engine inlet further comprising a joint joining the first part to the second part, the joint comprising a first end of one of the layers in the first part overlapping with a second end of another of the layers in the second part.

Assignees

• Boeing Co

Inventors

• Bol Eric D

Classifications

• B23K26/342 Primary

  Build-up welding · CPC title

• B22F10/47

  characterised by structural features · CPC title

• B23K26/0006

  taking account of the properties of the material involved (B23K26/32, B23K26/40 take precedence) · CPC title

• B23K26/0861

  in at least three axial directions · CPC title

• B23K26/0876

  in at least two axial directions · CPC title