WO2012113369A2

WO2012113369A2 - Method for generatively producing or repairing a component, and component

Info

Publication number: WO2012113369A2
Application number: PCT/DE2012/000139
Authority: WO
Inventors: Erwin Bayer; Thomas Hess
Original assignee: Mtu Aero Engines Gmbh
Priority date: 2011-02-16
Filing date: 2012-02-16
Publication date: 2012-08-30
Also published as: WO2012113369A3; DE102011011325A1

Abstract

The invention relates to a method for generatively producing or repairing a component (1), in particular a turbomachine, comprising a layered material structure, which can be produced directly or indirectly on a construction platform (6) and/or on a component to be repaired, wherein a first material structure (8) having a first construction direction (10) and a second material structure (16) having a second construction direction (18) different from the first construction direction (10) are produced in order to form a load-optimized structure. The invention further relates to a component (1), in particular for a turbomachine, comprising at least one generatively produced first material structure (8) having a first construction direction (10) and at least one second generatively produced material structure (16) having a second construction direction (18) different from the first construction direction.

Description

description

Method for generative production or repair of a component and component

The invention relates to a method for the generative production or repair of a component according to the preamble of patent claim 1 and a component according to claim 12.

Generatively manufactured or repaired components have a preferred direction of the material properties due to their layered structure. In this case, the microstructure grows in a construction direction through several layers such that an inhomogeneous material structure is formed. From DE 20 2009 012 628 Ul, for example, a device for the generative, layer-by-layer production of a three-dimensional object by means of a selective, powder-bed-based laser sintering method is known. Generative manufacturing methods based on other layered build up methods, such as laser powder buildup welding, are also known in the art.

A disadvantage of these conventional generative methods is that the

Component properties of such manufactured or repaired components are directional dependent, but are not adapted to the loading direction and therefore the mechanical

Characteristics in particular in lightweight structures, such as a barrel or stator blade of an aircraft gas turbine, as well as panels od. The like., Many times the high demands on the

Component strength with the lowest possible structural weight is not enough.

In contrast, the invention has for its object to provide a method for producing or repairing a component and a component, according to which a

load-optimized material structure is achieved, the high demands on the

mechanical component properties is sufficient.

This object is achieved by means of a method for producing or repairing a component with the method steps according to patent claim 1 and by a component according to claim 12.

CONFIRMATION COPY The method according to the invention for the generative production or repair of a component, in particular a turbomachine, comprises a layered material structure which can be effected directly or indirectly on a construction platform or a component to be repaired. According to the invention, a first material structure having a first construction direction and at least one second material structure having at least one second construction direction, which differs from the first construction direction, are used to form a total

produced stress-optimized material structure. According to the invention, it has been recognized that the material structure can be designed optimized for load by means of different mounting directions. In such manufactured or repaired components preferably occurring during operation of the component power flow is considered course. As a result, components, such as in particular lightweight structures, such as running or stator blade one

Aircraft gas turbine, as well as panels od. Like. Produced with optimized mechanical properties that meet high demands on the component strength with reduced structural weight and long life.

According to a particularly preferred embodiment of the invention, the at least two mounting directions are angled relative to each other to form a load-optimized material structure. The orientation of the mounting directions is preferably carried out as a function of the force flow curve, which occurs in the subsequent operation of the component. It is advantageous if the preferred direction in the component follows the power flow.

It has proved to be particularly advantageous if the component, a construction platform, an application head and / or an action direction of a beam of at least one radiation source, preferably a laser, electron or microwave source, are pivoted relative to each other. The relative movement can be multiaxial depending on the load-optimized construction direction to be produced. For example, in the case of a guide blade, due to the adapted assembly directions; opttamle-mechartrsehe properties, can be achieved simultaneously in the airfoil and in the shroud. Because of the optimal

Material utilization lightweight structures with reduced weight while maintaining strength can be produced. Kraftflussoptimierte component structures similar to the biological

Bone growth is possible. In particular, with components rotated only about an axis, the load-optimized construction direction can be further achieved by an exposure strategy. According to the invention, it is preferred if the second mounting direction and / or further mounting directions are set freely in three-dimensional space relative to the first mounting direction. The mechanical adjustability of the generative structure

used components is designed accordingly. In addition to the degrees of freedom required for the conventional construction of a component, the system can have at least one further degree of freedom for at least one further construction direction.

The change in the mounting directions is carried out in a run as the method preferably straight. According to this variant, it is possible to advantageously produce components which have angular regions. The inventive method can be used for example for holders for attachments of aircraft gas turbines. Such holders may for example have an approximately L-shaped or C-shaped cross-section, wherein the mounting directions according to the profile of the profile legs extend, so that according to the power flow curve a weight and load optimized profile structure is achieved.

According to an alternative embodiment of the method, the change of the

Mounting directions according to a curved path, At least one mounting direction can be bent simply or repeatedly arcuate. This variant is in particular for the production of at least partially arcuately curved components, such as

Blades of an aircraft gas turbine or the like, suitable. A continuous, approximately spiral curved path can be provided for producing a load-optimized spiral spring or components with similar geometry. For example, in a powder bed process, the construction platform is rotated and at the same time continuously lowered, whereby the laser beam strikes the component section to be generated inclined.

A 'combination ¹ of straight and arcuate construction directions- to. Production of a component is also advantageously possible according to the method according to the invention.

Preferably, components with rectilinearly extending and with arcuately curved sections are thereby produced. The material is built up in an embodiment according to the invention by means of a selective sintering process, for example a selective laser, electron and / or microwave sintering process. As a construction method, a selective, powder bed-based build-up method can be used. Here, a fluid layer, in particular a powder layer, gradually in

Layers applied to the build platform and by means of the beam at least one

Radiation source, preferably a laser, electron or microwave source, solidified to form the first material structure with the first construction direction. Subsequently, the building platform is pivoted relative to an angle of incidence of the radiation to form the second material structure with the second construction direction. Such a method enables contour-accurate production of gas turbine components made of highly heat-resistant materials, wherein the component geometry due to the generative process implementation quickly and inexpensively, for example, to optimize the component, can be adjusted.

In this method, the construction platform for forming a load-optimized material structure is preferably pivoted relative to the angle of incidence of the beam.

According to a further embodiment of the method according to the invention, the material is built up by means of a laser powder application method, such as laser powder buildup welding.

Preferably, the component is to form a load-optimized

Material construction pivoted relative to the angle of incidence of the beam.

Alternatively, the beam is pivoted relative to the component to form a load-optimized material structure

An inventive component, in particular for a turbomachine, such as an aircraft gas turbine, has at least a first generatively produced material structure with a first construction direction and at least one second generatively produced

Material construction with a second different from the first construction direction

Construction direction for the formation of a load-optimized material structure. The components may preferably have two or more successive, force flow dependent changes in the construction direction.

Other advantageous developments of the invention are part of the further

Dependent claims.

In the following, a preferred embodiment of the invention is based on

schemati shear drawings explained in more detail. FIG. 1 shows a side view of a component designed as a holder and FIG

2 shows a side view of a first portion of the holder of Figure 1.

Figure 1 shows a component 1, which is formed in the illustrated embodiment as a holder for attachments of an aircraft gas turbine. The holder 1 has an approximately L-shaped

Cross-section, wherein the main body of the holder 1 has been prepared by means of a generative, layered layer structure. The layer structure is shown schematically by means of parallel lines which define individual construction levels. The holder 1 has a short profile leg 2 and a perpendicular to this extending long profile leg 4. The manufacture of the holder 1 will be explained in more detail below with reference to FIG 1.

As can be seen in particular from FIG. 2, which shows a schematic side view of a first subregion of the holder 1 from FIG. 1, first the short profile limb 2 of the holder 1 is constructed in layers on a flat construction platform 6. As a construction method, laser powder buildup welding is used in the illustrated embodiment, in accordance with the powder, for example, by means of a coaxially executed applicator head and simultaneously by means of a center. Laser beam: is melted. Subsequently, further layers are applied for the formation of build-up planes. The individual layers are shown schematically as parallel lines. This process is repeated until a first, the profile leg 2 forming material structure 8 is reached. The construction direction 10 extends at right angles to the building platform 6 in the direction of an arrow. In the region of an end portion 12, an inclined surface 14 is formed on the profile limb 2. Subsequently, the component, ie the Profikelkel 2 is pivoted by an angle of 90 ° relative to the first mounting direction 10. The profile leg 2 is now arranged according to Figure 1 lying such that the inclined surface 14 as a basis for the other

Component structure is usable. A second material structure 16 with a second construction direction 18, which differs from the first construction direction 10, is used to form a load-optimized structure of the holder 1 by means of laser powder build-up welding

applied. The second construction direction 18 is represented by the direction of an arrow. The orientation of the mounting directions takes place in dependence of the power flow curve, which occurs in the subsequent operation of the holder 1. The change in the mounting directions 10, 18 relative to the component takes place here in a straight line, wherein the second material structure 16 is used to form the long profile leg 4. The mounting directions 10, 18 extend in the finished component at an angle of 90 ° to each other according to the course of the two profile legs 2, 4, so that according to the force flow curve a weight and load optimized profile structure of the holder 1 is achieved.

In an embodiment variant, not shown, for the production of

Assembly directions not the component rotated but the laser powder deposition welding head ver pivots. The relative movement can be multiaxial depending on the

load-optimized body directions are carried out.

The inventive method is not limited to the example described laser powder order process, but the material structure in an advantageous variant of the invention by means of a selective sintering process, for example, a selective, powder bed-based laser, electron and / or Mikrowellensinterverfahren done. The components may also have more than two consecutive changes in the construction direction.

Disclosed is a method for generative production or repair of a component 1, in particular a turbomachine comprising a layered material structure, which can be done directly on a construction platform 6 and / or a component to be repaired, wherein a first material structure 8 with a first construction direction 10th and a second material structure 16 having a second construction direction 18, which differs from the first construction direction 10, for forming a load-optimized structure becomes. Further disclosed is a component 1, in particular for a turbomachine, having at least one generatively produced first material structure 8 with a first construction direction 10 and at least one second generatively produced material structure 16 with a second construction direction 18 that differs from the first construction direction.

Claims

claims

1. A method for the generative production or repair of a component (1), in particular a turbomachine comprising a layered material structure, preferably directly or indirectly on a construction platform (6) and / or a component to be repaired, comprising the steps of: a) forming a first Material structure (8) with a first construction direction (10) and b) forming at least one second material structure (16) with at least one of the first construction direction (10) different second construction direction (18) for forming a load-optimized structure.

2. The method of claim 1, wherein the mounting directions (10, 18) are angled relative to each other to form a load-optimized material structure.

3. The method according to claim 1 or 2, wherein after step a) the component (1), a

Construction platform, a gun and / or a direction of action of a beam of at least one radiation source, preferably a laser, electron or microwave source, are pivoted relative to each other.

4. The method according to any one of the preceding claims, wherein the second construction direction (18) relative to the first construction direction (10) is set freely in the three-dimensional space.

5. The method according to any one of the preceding claims, wherein the change of the mounting directions (10, 18) in a straight line, and / or takes place according to a KuEvenbahn:

6. The method according to any one of the preceding claims, wherein the material structure (8, 16) by means of a selective sintering process, preferably a selective laser, electron and / or microwave sintering process, takes place.

7. The method of claim 6, wherein a fluid layer, in particular a powder layer, gradually applied to the build platform (6) and by means of the beam at least one radiation source, preferably a laser, electron or microwave source, to form the first material structure (8) wherein the construction platform (6) and the angle of incidence of the beam for forming the second material structure (16) with the second construction direction (18) are pivoted relative to each other.

8. The method according to any one of claims 3 to 7, wherein the building platform (6) for

Training a load-optimized material structure is pivoted relative to the angle of incidence of the beam.

9. The method according to any one of claims 1 to 5, wherein the material structure by means of a laser powder application method, preferably a laser powder build-up welding, takes place.

10. The method according to any one of claims 3 to 9, wherein the component (1) for forming a load-optimized material structure is pivoted relative to the angle of incidence of a jet.

11. The method according to any one of claims 3 to 10, wherein the beam for forming a load-optimized material structure is pivoted relative to the component (1).

12. component, in particular for a turbomachine, characterized by at least one generatively produced first material structure (8) with a first construction direction (10) and at least one second generatively produced material structure (16) with a second mounting direction differing from the first construction direction (10) (18) to form a load-optimized structure;