Method for additively constructing internal channels

Patent metadata

Field	Value
Publication number	US-2016332229-A1
Application number	US-201515111421-A
Country	US
Kind code	A1
Filing date	Jan 14, 2015
Priority date	Jan 22, 2014
Publication date	Nov 17, 2016
Grant date	—

Abstract

A method of additively manufacturing is used to produce a component with an internal cooling channel for conveying a fluid. Powders in a powder bed are selectively fused to form a shaped layer of a body of the cooled component. The fusing is repeated on a layer-by-layer basis to form the body of the component with the internal cooling channel extending within the body, so that a peripheral wall of the internal cooling channel has a geometry that allows the peripheral wall to be self-supporting.

First claim

1 . A method of additively manufacturing a component with an internal cooling channel for conveying a fluid, the method comprising:
selectively fusing powders in a powder bed to form a shaped layer of a body of the component; and repeating the fusing on a layer-by-layer basis to form the body of the component with the internal cooling channel extending within the body, wherein at a location within the component where the internal cooling channel is to be located the fusing is done in a manner that forms a peripheral wall of the internal cooling channel having a geometry that allows the peripheral wall to be self-supporting.

2 . The method of claim 1 , wherein the peripheral wall at a portion of the internal cooling channel formed by each subsequent layer is buttressed by the peripheral wall of the internal cooling channel formed by an immediately preceding layer such that the internal cooling channel is self-supporting.

3 . The method of claim 2 , wherein the buttressing provided by the peripheral wall is formed to be of a rate that is a function of a maximum width of a bottom portion of the internal cooling channel.

4 . The method of claim 2 , wherein a top portion of the peripheral wall of the internal cooling channel includes a controlled sag, and wherein the controlled sag is at least partially controlled by the buttressing of the peripheral wall of the internal cooling channel.

5 . The method of claim 1 , wherein the internal cooling channel is a microchannel.

6 . The method of claim 2 , wherein at least part of the peripheral wall of the portion of the internal cooling channel comprises a rounded profile.

7 . The method of claim 2 , wherein at least part of the peripheral wall of the portion of the internal cooling channel comprises a squeezed profile.

8 . The method of claim 1 , wherein the component is additively manufactured to contain the internal cooling channel without the use of support material inside the internal cooling channel.

9 . The method of claim 1 , wherein the component comprises an actively cooled gas turbine engine component.

10 . A method to additively manufacture a component that utilizes a mirochannel within the component to convey a fluid internally, the method comprising:
selectively fusing powders in a powder bed to form an initial shaped layer of a body of the component; and repeating the fusing on a layer-by-layer basis to form the body of the component with the microchannel extending within the body, wherein the microchannel includes an eccentric convexity geometry such that the microchannel can self-support subsequent layers fused on top of the microchannel.

11 . The method of claim 10 , wherein the eccentric convexity geometry causes a microchannel peripheral wall formed by a subsequent layer to be buttressed by the microchannel peripheral wall formed by a previous layer.

12 . The method of claim 10 , wherein the microchannel has a cross-sectional area of approximately 0.0025 in. 2 (1.6129 mm 2 ) or less.

13 . The method of claim 10 , wherein the eccentric convexity geometry at a portion of a microchannel peripheral wall comprises a rounded profile for the portion.

14 . The method of claim 10 , wherein the eccentric convexity geometry at a portion of a microchannel peripheral wall comprises a squeezed profile for the portion.

15 . The method of claim 10 , wherein the component is additively manufactured to contain the microchannel without the use of support material inside the microchannel.

16 . The method of claim 10 , wherein the component comprises an actively cooled gas turbine engine component.

Assignees

• United Technologies Corp

Inventors

• Snyder Brooks E
• Slavens Thomas N

Classifications

• B22F10/385

  Overhang structures · CPC title

• B22F5/04 Primary

  of turbine blades · CPC title

• B22F10/28

  Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM] · CPC title

• B22F5/009

  of turbine components other than turbine blades (of turbine blades B22F5/04) · CPC title

• B22F3/1055 Primary

  Operations & Transport · mapped topic