Method for producing, repairing and/or exchanging a housing, in particular an engine housing, and a corresponding housing

Patent metadata

Field	Value
Publication number	US-10066508-B2
Application number	US-201214233817-A
Country	US
Kind code	B2
Filing date	Jul 25, 2012
Priority date	Jul 29, 2011
Publication date	Sep 4, 2018
Grant date	Sep 4, 2018

Abstract

The invention relates to a method for producing, repairing and/or exchanging a housing, in particular an engine housing of an aircraft engine, comprising at least two shells, between which a structural part is formed, wherein the method comprises the following step: layer-by-layer construction of the at least two shells jointly with the structural part by means of a generative manufacturing system, wherein the structural part comprises at least one porous structure and/or honeycomb structure. The invention relates furthermore to such a housing.

First claim

The invention claimed is:

1. A method for producing a component, comprising:
layer-by-layer constructing a housing of an aircraft engine, the housing having an inner shell part and an outer shell part together with a structural part therebetween, by a generative manufacturing method, wherein the generative manufacturing method comprises applying a powder layer and solidifying the powder layer by energy radiation, wherein the structural part has at least one porous structure and/or one honeycomb structure, wherein the step of the layer-by-layer constructing further comprises:
layer-by-layer constructing an auxiliary support structure by the generative manufacturing method on a base plate;
subsequently forming the housing on the auxiliary support structure by the generative manufacturing method, wherein the auxiliary support structure and housing are integrally connected; and
removing the auxiliary support structure from the housing after finishing the housing.

2. The method according to claim 1 , wherein the step of the layer-by-layer constructing further comprises the step of forming at least one shell part as a shell part with solid walls.

3. The method according to claim 1 , wherein the at least one porous structure and/or one honeycomb structure is formed as an auxetic structure and the porous structure is formed as a foam structure.

4. The method according to claim 3 , wherein the auxetic structure is aligned in a direction of a principal load of the housing.

5. The method according to claim 1 , wherein the step of layer-by-layer constructing further comprises the step of forming the housing with at least one intermediate shell part between the outer shell part and the inner shell part, wherein a first structural part is formed between the inner shell part and the intermediate shell part, and a second structural part is formed between the intermediate shell part and the outer shell part.

6. The method according to claim 5 , wherein the first and second structural parts have the same structure or the same combination of structures.

7. The method according to claim 1 , wherein the step of layer-by-layer constructing further comprises the step of forming the housing with a terminal part on at least one end.

8. An engine housing, comprising an inner shell part, an outer shell part and a structural part formed between the inner and outer shell parts, and lower and upper terminal parts enclosing the structural part within the inner and outer shell parts, wherein the engine housing is produced by a generative manufacturing method and the structural part has at least one porous structure and/or one honeycomb structure, wherein the generative manufacturing method of the housing comprises:
layer-by-layer constructing an auxiliary support structure by the generative manufacturing method on a base plate;
subsequently forming the housing on the auxiliary support structure by the generative manufacturing method, wherein the auxiliary support structure and housing are integrally connected; and
removing the auxiliary support structure from the housing after finishing the housing.

9. The engine housing according to claim 8 , wherein the porous structure and/or the honeycomb structure is formed as an auxetic structure.

10. The engine housing according to claim 9 , wherein the porous structure is a foam structure.

11. The engine housing according to claim 8 , wherein at least one shell part is produced from metal, a metal alloy, and/or ceramics.

12. A method for producing an engine housing of an aircraft engine, the housing having an inner shell part and an outer shell part, between which a structural part is formed, and a plurality of guide vanes extending radially inward from the inner shell part, comprising the step of:
layer-by-layer constructing the inner and outer shell parts together with the structural part and the plurality of guide vanes by a generative manufacturing method, wherein the structural part has at least one porous structure and/or one honeycomb structure, wherein the generative manufacturing method comprises applying a powder layer and solidifying the powder layer by energy radiation.

13. The method of claim 12 , wherein the generative manufacturing method of the housing comprises the steps of:
layer-by-layer constructing an auxiliary support structure by the generative manufacturing method by applying a powder layer to a base plate and subsequently to an auxiliary support structure, wherein the powder layer is solidified by energy radiation;
subsequently forming the housing on the auxiliary support structure by the generative manufacturing method, wherein the auxiliary support structure and housing are integrally connected; and
removing the auxiliary support structure from the housing after finishing the housing.

14. The method according to claim 12 , wherein the porous structure and/or honeycomb structure is formed as an auxetic structure, and the porous structure is formed as a foam structure.

15. The method according to claim 14 , wherein the auxetic structure is aligned in a direction of a principal load of the housing.

16. The method according to claim 12 , wherein the step of layer-by-layer constructing further comprises the step of forming the housing with at least one intermediate shell part between the outer shell part and the inner shell part, wherein a first structural part is formed between the inner shell part and the intermediate shell part, and a second structural part is formed between the intermediate shell part and the outer shell part.

17. The method according to claim 12 , wherein the step of layer-by-layer constructing further comprises the step of forming the housing with a terminal part on at least one end.

18. The method according to claim 16 , wherein the first and second structural parts have the same structure or the same combination of structures.

19. The method according to claim 12 , wherein the step of the layer-by-layer constructing further comprises the step of forming at least one shell part as a shell part with solid walls.

20. A method for manufacturing an engine housing of an aircraft engine, the engine housing having an inner shell part and an outer shell part, between which a structural part is formed, comprising the step of:
layer-by-layer constructing the inner and outer shell parts together with the structural part by a generative manufacturing method, wherein the generative manufacturing method comprises applying a powder layer and solidifying the powder layer by energy radiation, wherein the structural part is an auxetic structure.

21. The method according to claim 20 , further comprising the steps of:
layer-by-layer of an auxiliary support structure by a generative manufacturing method;
subsequently forming the housing on the auxiliary support structure by the generative manufacturing method; and
removing the auxiliary support structure from the housing after finishing the housing.

22. The method according to claim 20 , wherein the step of the layer-by-layer constructing further comprises the step of forming at least one shell part as a shell part with solid walls.

23. The method according to claim 20 , wherein the auxetic structure is aligned in a direction of a principal load of the housing.

24. The method according to claim 20 , wherein the step of layer-by-layer constructing further comprises the step of forming the housing with at least one intermediate shell part betwee

Assignees

• Geiger Peter
• MTU Aero Engines AG

Inventors

• Geiger Peter

Classifications

• F01D25/26

  Double casings; Measures against temperature strain in casings · CPC title

• Y10T29/4973

  Replacing of defective part · CPC title

• F01D25/24 Primary

  Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) · CPC title

• F05D2230/22

  by sintering · CPC title

• F01D21/045

  special arrangements in stators or in rotors dealing with breaking-off of part of rotor · CPC title