Method for producing a component with at least one element arranged in the component

Patent metadata

Field	Value
Publication number	US-9314844-B2
Application number	US-201213441081-A
Country	US
Kind code	B2
Filing date	Apr 6, 2012
Priority date	Apr 15, 2011
Publication date	Apr 19, 2016
Grant date	Apr 19, 2016

Abstract

A method for manufacturing a component having at least one element configured in the component, in particular at least one conduit, conduit unit, or supporting element configured within an aerodynamic rib, the component having an element leadthrough for leading through the at least one element, the method including the following step: building up in layers of the component including the element leadthrough, together with the at least one element in a generative production process.

First claim

The invention claimed is:

1. A method for manufacturing an aerodynamically contoured rib of a gas turbine, at least one element configured in the aerodynamically contoured rib, the aerodynamically contoured rib having an element leadthrough for leading through the at least one element, the element leadthrough defining an opening in a wall of the aerodynamically contoured rib, the method comprising the following step:
building up in layers the aerodynamically contoured rib including the element leadthrough, together with the at least one element, in a generative production process, the step of building up in layers further comprising forming an intermediate space between the element leadthrough and the at least one element at the opening in the wall of the aerodynamically contoured rib,
wherein the building up in layers step further includes forming a structural rib to fix the element to the element leadthrough and wherein the method further comprises breaking the structural rib to render the element movable with respect to the leadthrough.

2. The method as recited in claim 1 wherein the at least one element includes at least one conduit, conduit unit, or supporting element configured within the aerodynamic rib.

3. The method as recited in claim 1 wherein the step of building up in layers further comprises:
forming a retaining structure in a predefined position at the element or the aerodynamically contoured rib for positioning the element in the element leadthrough of the aerodynamically contoured rib.

4. The method as recited in claim 1 further comprising the step of:
at least partially filling the intermediate space between the element leadthrough and the at least one element, at the opening in the wall of the aerodynamically contoured rib, with an insulation material.

5. The method as recited claim 1 wherein the intermediate space between the element leadthrough of the aerodynamically contoured rib and the at least one element is formed at least partially or completely peripherally around the element.

6. The method as recited in claim 1 wherein the step of building up in layers further comprises forming the at least one element at one or both ends of the same using a connection portion or a fastening flange, wherein the connection portion, or respectively, the fastening flange, is formed in the step of building up layers having a greater cross section or diameter than the element leadthrough of the aerodynamically contoured rib.

7. The method as recited in claim 1 wherein the aerodynamically contoured rib is part of a turbine exit case of a gas turbine of an aircraft engine, and the element is a conduit or a conduit unit having at least two conduits and the conduit or conduit unit is configured as a conduit or conduit unit for passing through a tempering medium.

8. The method as recited in claim 7 wherein the tempering medium is a cooling medium.

9. The method as recited in claim 8 wherein the cooling medium is air, water or oil.

10. The method as recited in claim 1 wherein the aerodynamically contoured rib is part of a turbine exit case of a gas turbine of an aircraft engine, and the element is a supporting element.

11. The method as recited in claim 10 wherein the supporting element is a supporting element for the transmission of force.

12. The method as recited in at claim 1 wherein the at least one element includes elements configurable separately from one another or as a shared element unit.

13. The method as recited in claim 12 wherein the elements are conduits.

14. An aerodynamically contoured rib produced by the method recited in claim 1 .

15. The aerodynamically contoured rib as recited in claim 14 wherein a cross section of the at least one element is configured in the interior of the element leadthrough of the aerodynamically contoured rib to be smaller than the cross section of the element leadthrough.

16. The aerodynamically contoured rib as recited in claim 14 wherein a cross section or diameter of at least one portion of the at least one element is configured outside of the element leadthrough of the aerodynamically contoured rib to be greater than the cross section or the diameter of the element leadthrough.

17. The aerodynamically contoured rib as recited in claim 16 wherein the at least one portion is designed as a connection portion or as a fastening flange of the element, the connection portion being configured for feeding of a tempering medium thereto, and the fastening flange being configured for fastening at least one further part.

18. The aerodynamically contoured rib as recited in claim 14 wherein the aerodynamically contoured rib is formed together with the element leadthrough, together with a plurality of elements, the elements being formed separately from one another or as a common element unit.

19. The aerodynamically contoured rib as recited in claim 18 wherein the elements are conduits and further comprising a connection for each conduit.

20. The aerodynamically contoured rib as recited in claim 14 wherein the element is a conduit, a conduit unit having at least two conduits or a supporting element.

21. The aerodynamically contoured rib as recited in claim 20 wherein the element is a supporting element for the transmission of force.

22. The method as recited in claim 1 wherein the building up in layers step further comprises forming the at least one element with two connecting end portions each having a cross section larger than the element leadthrough.

Assignees

• Geiger Peter
• Mtu Aero Engines Gmbh

Inventors

• Geiger Peter

Classifications

• B22F5/009 Primary

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

• B22F10/66

  by mechanical means · CPC title

• B22F10/47

  characterised by structural features · CPC title

• B22F10/28

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

• B33Y80/00

  Products made by additive manufacturing · CPC title