DE102018210397A1 - Method for additive manufacturing of a structure with coolant guidance, component and device - Google Patents

Abstract

A method for additively producing a structure (10, 10 ') is specified, in particular by means of a powder bed method. The method comprises in layers: a) the application of a layer (S) of a, in particular powdery, base material (P) to a production surface (HF), b), the additive construction of the structure by selective irradiation of the applied layer in accordance with a predetermined structural geometry, wherein within a cross section of the structure (10, 10 ') an area (B1, B2, 204) is left free from the radiation, in which a coolant (210) is guided during the additive construction of the structure (10) in order to remove the layer or to cool the built structure. Furthermore, a correspondingly manufactured component and a corresponding device are specified.

Description

The present invention relates to a method for the layer-by-layer additive production of a structure, in particular by a powder bed-based method, a coolant and / or heat-conducting medium for cooling the structure being provided during the additive construction of the structure. Furthermore, the present invention relates to a correspondingly producible or manufactured component and a device for performing the method.

The component is preferably intended for use in a turbomachine, preferably in the hot gas path of a gas turbine. The component accordingly preferably consists of a super alloy, in particular a nickel or cobalt-based super alloy.

The alloy can be precipitation hardened or dispersion hardened.

The component can also be made of a titanium, aluminum or iron-based material and be intended for applications in the automotive or aerospace industry. The component according to the present invention preferably designates a component or a structure with a cavity or a cavity, for example a component to be cooled during operation.

In gas turbine plants, thermal energy and / or flow energy is generated by burning a fuel, e.g. of a gas, hot gas generated, for example, converted into kinetic energy of a shaft or a turbine rotor. For this purpose, a flow channel is formed in the gas turbine, in the axial direction of which the shaft is supported. The shaft has a number of wheel disks, on the radially outer end faces of which a number of moving blades are arranged in the form of a blade ring. The blades are mostly inserted into the grooves of the end faces by means of their blade feet. Modern gas turbines are subject to constant improvement and further development in order to increase their efficiency. Increases in efficiency usually mean higher temperatures in the hot gas path according to which the components must be designed accordingly, be it with regard to the material and / or the geometry, for example comprising cooling channels. There are also efforts to improve metallic materials for turbine blades with regard to their strength, creep load at high temperatures and thermomechanical fatigue.

Generative or additive manufacturing is becoming increasingly interesting due to its disruptive potential for industry and also for the industrial series production of the above-mentioned turbine components, such as turbine blades or burner components.

Additive manufacturing processes include, for example, as a powder bed process, selective laser melting (SLM) or laser sintering (SLS), or electron beam melting (EBM).

A method for selective laser melting is known for example from EP 2 601 006 B1 ,

A method for additive manufacturing of a component comprising influencing or detecting properties of the component during the additive construction is described for example in DE 10 2015 225 652 ,

Additive manufacturing processes (English: "additive manufacturing") have also proven to be particularly advantageous for complex or complex or filigree designed components, such as labyrinthine structures, cooling structures and / or lightweight structures. Additive manufacturing through a particularly short chain of process steps is particularly advantageous, since a manufacturing or manufacturing step of a component can take place directly on the basis of a corresponding CAD file and the selection of corresponding manufacturing parameters.

Although the degree of design freedom offered by additive manufacturing also offers great potential for the industrial manufacture of components, there are restrictions with regard to the material structure of additively manufactured components. In particular, the additively manufactured components are significantly inferior to the conventional components produced by casting processes in terms of strength and creep properties. This is due, among other things, to the high temperature gradients inherent in the powder bed process, the corresponding tendency of the built-up material to crack, and disadvantageous, in particular polycrystalline, material properties.

In particular, the high temperature gradients involved in the SLM welding process very often result in hot or solidification cracks during the additive construction. The problem described exists in particular in the case of superalloys which are difficult or difficult to weld, for example nickel-based or cobalt-based alloys with a large proportion of intermetallic phase, for example γ and / or γ 'phases.

It is therefore an object of the present invention to provide means which solve the problems described above, in particular to prevent the formation of hot and / or solidification cracks in the additive production of components exposed to high temperatures.

This object is achieved by the subject matter of the independent claims. Advantageous refinements are the subject of the dependent claims.

One aspect of the present invention relates to a method for, in particular layer by layer, additive manufacture of a structure or a component, in particular by means of a powder bed method. The method comprises, preferably in layers or layers, the application of a layer of a, in particular powdery, base material on a production surface.

The production area can be defined or represented, for example, by the surface of a building platform, the surface of a corresponding powder bed and / or the surface of a structure that has already been set up, which can be flush with the powder bed, for example.

The method further comprises additively building up the structure by selectively irradiating the applied layer in accordance with a predetermined structure or component geometry, for example by means of selective laser melting or electron beam melting.

After the additive construction, the method can include lowering a construction platform, expediently by an amount corresponding approximately to a layer thickness of the layer.

In the case of the additive structure, an area is left free of the radiation within a cross section of the structure in which a coolant is guided during the additive structure of the structure in order to cool the layer and / or the built-up structure. In the area left free, the layer is therefore deliberately not irradiated in order not to selectively build up a structure, but rather to form a cavity or path to the coolant guide.

The area mentioned is preferably defined by the structure.

In the present case, the coolant preferably describes any medium or agent suitable for cooling or heat dissipation, for example a pasty heat-conducting agent or filler material, which preferably has a particularly large heat capacity as well as good thermal conductivity. Alternatively, the coolant can refer to a granular and / or liquid material during operation.

The method presented is characterized in that it advantageously enables active and / or targeted cooling of an additively constructed structure or of the component, preferably right down to the location of the actual melt pool. This enables targeted and efficient control and / or influencing of the temperature of the structure during its additive manufacturing for the first time, regardless of the overall height (Z direction). In particular, the present invention enables intelligent “heat management” to be carried out and powder bed-based processes (“powder bed fusion”) to be decisively improved in such a way that it is possible to process alloys that are not currently weldable.

Efficient and tailor-made cooling in additive processes is so important because it enables a particularly favorable material structure or material phase to be formed, caused or provoked in the component or its structure. This is particularly important in the case of high-performance alloys, such as superalloys, which cannot be built up in sufficient structural quality from the powder bed due to a strong tendency to hot and / or solidification cracks during the additive construction. As a result, the present invention can only open the additive manufacturing route of certain connections that are difficult or not yet weldable, such as so-called “Alloy 247”, in which the temperature gradients caused by the cooling favor solidification conditions in the base material and / or in the weld pool in such a way that excessive cracking is prevented during assembly.

In particular in the case of nickel-base superalloys that are difficult or not yet weldable, the method presented allows, through the cooling functionality, an efficient suppression of the formation or elimination of the so-called γ- and / or γ'-phase, which is particularly responsible for the crack formation described. The phase mentioned can be a metastable and / or intermetallic phase.

In the present case, an “intermetallic phase” preferably denotes a mixed bond in an alloy with a metallic bond component and lower atomic bond or ion bond proportions. Intermetallic compounds are preferably harder, stronger, more corrosion-resistant and have a higher melting point than chemically homogeneous metals or alloys.

It goes without saying that the temperature and also a tendency to cracks in the additive process strongly depend on the underlying material, the radiation parameters, but also on the geometry of the structure or the component.

In one embodiment, after the additive structure of the structure, a heat treatment is carried out, which effects intermetallic precipitates, in particular γ- and / or γ '- (phase) precipitates, in the structure. The heat treatment, which may or may include solution or diffusion annealing, aging or removal of the phases described, is preferably suitable for causing the corresponding deposits in the structure.

The method presented advantageously initially suppresses elimination of intermetallic phases, thus greatly reducing the risk of crack formation during the actual additive structure. However, in order to ensure the required strength in the structure, for example in the case of superalloys for components exposed to high temperatures, the heat treatment described can be carried out below, which only causes the intermetallic phases to separate. In contrast to the additive build-up process, there is no risk of hot or solidification cracks occurring in solution annealing or heat treatment, especially due to the much smaller temperature gradients involved.

In one configuration, the structure is constructed in such a way that the regions in the structure that are left free in layers form a coherent cooling channel. In other words, the cooling channel can be defined by the areas left free.

In one configuration, the cooling channel is formed in such a way that it extends parallel to a mounting direction, for example the vertical Z direction, of the structure. Individual layers or cross sections of the structure preferably define only a part of the cooling channel corresponding to a layer thickness.

In one embodiment, the cooling channel is successively, i.e. Gradually, layer by layer or gradually filled with the coolant from below on a construction platform or through.

In one embodiment, displaced or removed coolant and / or base material (powder) is removed, in particular successively, on the production surface, for example by a removal device.

With this configuration (s), the cooling can take place in a controlled manner and thus a material structure can also be carried out in layers, in a locally resolved manner and / or appropriately.

In one configuration, the coolant forms an interface or interface with the (applied) layer of the base material on the production surface. With this configuration, the cooling can advantageously take place (in-situ) where the need is greatest, namely in the vicinity of the melting bath. Furthermore, this configuration makes it possible to simplify removal of excess or residual powder from cavities in the component.

In one configuration, the structure comprises the construction of two or more components, with two or more of these components defining the cooling channel. For example, according to this embodiment, two or more components can be built on the construction platform next to one another and along a common construction direction in such a way that the cooling channel is formed in an intermediate space between the components.

In one embodiment, the cooling channel is at least partially defined or formed by a space in the wall of an additive manufacturing system. According to this configuration, cooling can be carried out particularly expediently at the edge of the construction platform.

In one configuration, the coolant comprises a thermal paste, for example FEROTHERM®. The heat-conducting paste of the coolant makes it particularly expedient for the structure to be cooled or cooled. In particular, the thermal paste can represent the coolant. Alternatively, the thermal paste can be added to the coolant, for example to improve heat transfer from the structure to the coolant or medium.

In one embodiment, a thermal paste is used as the coolant.

In one embodiment, the base material comprises one or more of the following materials: PWA795, Merl72, MAR-509, Stellite-31, Hastelloy X, Haynes 230, Haynes 625, IN939, IN738, IN713, IN792, IN718, Alloy 247 and Rene 80. These materials are used particularly in the components used in the hot gas path of turbomachines. The method presented is particularly suitable for the additive construction of the materials mentioned last, since a reliable and reproducible production of these materials by means of an additive method, which was previously hardly possible, is made possible by the method described.

Another aspect of the present invention relates to a component that can be produced or produced by the described method. The component also includes the structure, whereby the The component is also intended for use in the hot gas path of a gas turbine, for example as a metallic, high-temperature-resistant component.

The finished component can, for example, emerge from the additively constructed structure. Accordingly, the component preferably differs from the structure only in that mechanical post-processing steps and removal of excess powder material have been carried out.

In one configuration, the component is made of a superalloy, in particular nickel- or cobalt-based, and has, for example in comparison to a component of the prior art, a lower density of structural defects, such as hot cracks or solidification cracks.

A further aspect of the present invention relates to a device for carrying out the described method, further comprising a coolant reservoir, a coolant connection and a control unit, the device being further designed to provide the coolant, for example via a valve and / or a bore through or via a construction platform a (conventional) additive manufacturing system, into an installation space or onto a corresponding manufacturing area. The control unit can, for example, comprise a computer or a data processing device and in particular be designed to control or optimize the method step of successively filling the cooling channel with the coolant.

In one embodiment, the device is a retrofit kit for conventional additive manufacturing plants.

Refinements, features and / or advantages, which in the present case relate to the method or the component, can also concern the device, or vice versa.

Further features, properties and advantages of the present invention are explained in more detail below on the basis of exemplary embodiments with reference to the attached figures. All the features described so far and below are advantageous both individually and in combination with one another. It is understood that other embodiments may be used and structural or logical changes may be made without departing from the scope of the present invention. The following description is, therefore, not to be taken in a limiting sense, and the scope of the present invention is defined by the appended claims.

The term "and / or" used here when used in a series of two or more elements means that each of the listed elements can be used alone, or any combination of two or more of the listed elements can be used.

• 1 deutet anhand einer schematischen Schnittansicht einen pulverbett-basierten additiven Herstellungsprozess eines Bauteils an,
• 2 deutet erfindungsgemäße Verfahrensschritte sowie eine erfindungsgemäße Vorrichtung an,
• 3 deutet erfindungsgemäße Verfahrensschritte im Detail an,
• 4 deutet alternativ zur 3 erfindungsgemäße Verfahrensschritte im Detail an.

Further details of the invention are described below with reference to the figures.

• 1 indicates a powder bed-based additive manufacturing process of a component on the basis of a schematic sectional view,
• 2 indicates method steps according to the invention and a device according to the invention,
• 3 indicates process steps according to the invention in detail,
• 4 alternatively to 3 Method steps according to the invention in detail.

In the exemplary embodiments and figures, elements that are the same or have the same effect can each be provided with the same reference symbols. The elements shown and their size relationships among one another are fundamentally not to be regarded as true to scale; rather, individual elements can be shown in an exaggeratedly thick or large size for better representation and / or for better understanding.

1 shows a schematic sectional or side view of an additive manufacturing system 100 , The attachment 100 is preferably a device for additive manufacturing of a component 10 from a powder bed P, for example by selective laser melting or electron beam melting. The attachment 100 has a substrate plate or build platform 1 on. On the build platform 1 becomes a structure 10 built up, ie preferably also directly bonded or "welded" to the construction platform.

The component (for simplicity and clarity also with the reference number 10 is preferably built in a space BR.

The structure 10 is preferably provided for the component, which is preferably a component that is used in the hot gas path of a turbomachine, for example a gas turbine. In particular, the component can be a moving or guide vane, a segment or ring segment, a burner part or a burner tip, a frame, a shield, a heat shield, a nozzle, seal, a filter, a mouth or lance, a resonator, stamp or a swirler designate, or a corresponding transition, use, or a corresponding retrofit part.

The component 10 is in 1 shown for the sake of simplicity only partially constructed, for example from only two layers S of a component material P ,

With the component material P it is preferably a powder of γ- and or γ ' -Hardened, nickel or cobalt based super alloy.

Individual layers of the material P for the layers S of the component are preferably via a coating device 30 in one space BR on a manufacturing area HF applied and then by means of an energy beam 21 for the assembly of the component 10 selectively melted and solidified. The energy beam is preferably from an irradiation device 20 , for example representing or comprising an electron beam or a laser source.

After a layer S has been built up, the substrate plate 11 preferably lowered by a dimension SD corresponding to the layer thickness S. Then a new powder layer is used to build the component 10 applied, for example starting from a powder supply 40 which is on the left in 1 is shown.

The additive build-up process is preferably carried out under an inert or protective gas atmosphere or at least in an atmosphere with a reduced oxygen content, in order to prevent corrosion, oxidation or other influences affecting the quality of the component material, that is to say the powder P, or the finally produced component 10 influence, avoid.

A mounting direction AR for the component 10 corresponds to in 1 a vertical upward direction (vertical Z direction).

2 shows in a schematic sectional or side view similar to the illustration of the 1 a device according to the invention 200 , The device 200 can be used, for example, as a retrofit kit or spare parts kit in conventional additive manufacturing systems (see reference numerals 100 ) to be built in. Still points 2 Steps of a method according to the invention.

The device 200 enables a cooling medium or a coolant by the described method according to the invention 210 in the installation space BR the plant 100 to lead or lead to a layer or built structure 10 to cool appropriately and efficiently. The device 200 includes a coolant reservoir 201 , a coolant connection or a valve 202 and a control unit 50 , which preferably to the valve 202 is coupled and designed to regulate a coolant supply. This can be done, for example, by interacting with a technician or user of the system 100 and a corresponding graphical user interface.

The construction platform is preferred 1 provided with an opening or a hole (not explicitly marked). The valve is preferably in the bore 202 arranged, via which a predetermined coolant volume, preferably successively or in layers and controlled by the control unit 50 , through the build platform 1 can be guided into the installation space.

The coolant 210 can, for example, comprise or represent a heat conducting medium. The heat conducting medium can be a thermal paste, for example FEROTHERM® X (FEROTHERM® X, in particular FEROTHERM® X, FEROTHERM®1, FEROTHERM®3, FEROTHERM®4, FEROTHERM®10-U, FEROTHERM®BG, FEROTHERM®5, FEROTHERM®6 FEROTHERM®5-n * and / or FEROTHERM®6-300 *).

The method according to the invention comprises layers (compare also 3 and 4 below), a), applying a layer S one, in particular powdery, base material P on a manufacturing area HF (compare also 1 ).

The process also includes b ), the additive construction of the structure of the component by selective irradiation of the applied layer in accordance with a predetermined structure geometry, being within a cross section of the structure 10 an area B is released from the radiation or is selectively excluded, during which during the additive construction of the structure 10 a coolant 210 is led to the layer S or the built structure 10 to cool.

Through the blank areas B or the corresponding non-irradiated areas of a layer or a cross section for the component 10 preferably becomes a channel gradually during additive construction 204 or cooling channel formed, which is preferably continuous or continuous from the construction platform 1 down to the manufacturing area HF extends.

The channel preferably extends 204 at least mainly parallel to the direction of construction AR the structure.

On the manufacturing area HF that forms in the channel 204 powdery Base material (powder) preferably an interface 203 for each newly applied layer S for the component 10 ,

According to the present invention, the powder or base material P is selected, for example, from at least one of the following known alloy materials: PWA795, Merl72, MAR-509, Stellite-31, Hastelloy X, Haynes 230, Haynes 625, IN939, IN738, IN713, IN792, IN718 , Alloy 247 and Rene 80.

In the right part of the 2 is at least part of the channel 204 shown enlarged. It can be seen that the channel extends vertically parallel to the mounting direction AR and with the coolant 210 and powder, as the base material for the structure 10 is filled. The powder can serve as a binder for the coolant and, for example, for better flowability and thus for controlled cooling at an interface 203 contribute. Furthermore, in the right part of the 2 areas B1 . B2 shown. The second area B2 is above the range B1 shown. For each layer there is therefore preferably an area with an extension SD in the direction of assembly AR excluded from the radiation to form the cooling channel.

In the right part of the 2 it can also be seen that the device 200 a removal device 205 has, for example a squeegee or a powder pusher. By means of this removal device 205 can, for example, upward material comprising the powder P as well as coolant 210 be removed or removed laterally on the manufacturing surface. In particular, the area of the interface 203 , which is preferably in the same layer plane as a molten bath of the layer which is currently selectively irradiated, is efficiently cooled or excess heat is removed. In this way, the formation of unfavorable material phases can advantageously be suppressed, so that cracking, in particular hot or solidification cracks, can furthermore advantageously be prevented by preventing the separation of intermetallic phases.

Components that are particularly suitable for industrial additive manufacturing (and not only for the production of prototypes) usually have complex structures, including internal cavities or cavities. By means of the described method, these cavities can advantageously be used for cooling during the manufacturing process. For this purpose, in 2 a turbine blade, with the cooling channel 204 as a cavity, shown only as an example. The flow of coolant through the channel 204 according to the method described, in many cases this means that there is no significant restriction on the design of the component 10 , so that the method presented can be used in very many cases.

According to the method described, the cooling channel 204 preferably successively or in layers during the additive production of the structure 10 from below over a construction platform 1 with the coolant 210 filled (see reference number c ) in the 3 and 4 ).

Furthermore, displaced coolant 210 as well as displaced basic material P then successively on the manufacturing surface HF be removed (see reference number d ) in the 3 and 4 ).

If a component geometry to be built does not provide a sufficient internal hollow structure, that is to say the method described according to the invention cannot be used or can only be used with difficulty, a structure to be built can be used 10 for example, comprise two or more components, two or more of these components then comprising the cooling channel 204 define. This embodiment of the present invention is by the different reference numerals 10 and 10 ' the structures or components in 2 indicated. In other words, structures for 2 components 10 and 10 ' built up.

As an alternative or in addition, the channel can also be at least partially surrounded by a space 101 an additive manufacturing plant 100 are defined so that - in other words - a space in the installation space can also be used to guide the coolant.

Because by means of the described method and to avoid possibly structurally catastrophic hot or solidification cracks in the structure 10 , in particular the outsourcing or excretion of intermetallic phases, such as in particular γ - and / or γ'-phases, is prevented, in the case of components subject to high temperatures, the correspondingly constructed structures for production after the additive assembly may still have to be subjected to a heat treatment, for example solution annealing. As a result, in particular the phase separations mentioned necessary for the strength of the finished components can be formed again. The heat treatment is expediently chosen and carried out in such a way that the phase precipitations are formed in the component in an optimal or favorable manner, size and arrangement.

According to the described method and according to the described device, a component which consists of a, in particular nickel or cobalt-based superalloy exists, for example in comparison to a component of the prior art, with a lower density of structural defects, such as hot cracks or solidification cracks. Alternatively, with a similar quality, a reject of the components can be greatly reduced or completely avoided, since the additive manufacturing process can be carried out in a much more reproducible manner and less prone to defects.

According to the present invention, the filling of the channel described above must 204 with the coolant 210 do not necessarily take place in layers after the additive structure or the irradiation. Based on 3 For example, a further embodiment of the method according to the invention is illustrated.

3 shows a section of the structure in the left part 10 (compare also 2 above) with the channel 204 and the interface described above 203 , For example, it is the device 200 shown, after applying a new layer of powder S a new portion of coolant is gradually being added 210 in the channel 204 is introduced. This will make one up in the channel 204 part of the coolant over the interface 203 in the area of a previously applied powder layer P crowded, which can form a meniscus (see dashed line).

Irradiation can then take place, for example, as on the basis of the energy beam 21 indicated. Only after the irradiation is part of the channel preferably removed 204 crowded coolant 210 and the powder dissolved in it P on the manufacturing area HF away.

In the right part of the 3 a corresponding sequence of this embodiment of the method is shown on the basis of a schematic flow diagram, with after the application step, a ), first the coolant 210 in the channel 204 is filled c ). The irradiation or the actual additive structure then takes place (see step b )) and finally the removal takes place (see step d )) of the displaced coolant 210 , as described above.

The in the 3 The embodiment shown advantageously allows cooling before the actual irradiation of the layer and thus particularly efficient and targeted cooling of the melt pool (in-situ) in order, as described above, to achieve high temperature gradients in the subsequent build-up step and thus the formation / elimination of intermetallic phases prevention.

4 shows alternative to 3 another possible process sequence as an embodiment of the method described. According to this embodiment, a powder layer is also first applied, method step a ). Then, as described above, selective irradiation is carried out (see step b )) to part of the structure in the corresponding layer 10 to form for the component. Then a small new portion of coolant 210 in the cooling channel 204 filled (see step c)), so that in the upper area of the channel 204 (at the interface 203 ) excess coolant 210 as well as powder P ousted (see step d )) becomes. Then this superfluous material is removed using a removal device 205 which, for example, in the 4 moved from left to right, from the manufacturing area HF away. The layer labeled with the reference number S ' according to the representation corresponds to that layer which was irradiated last and thus has already been built up and solidified.

According to this configuration ( 4 ) will remove excess material (powder P and coolant 210 ) compared to the embodiment of 3 possibly simplified.

The invention is not restricted to the exemplary embodiments by the description based on these, but rather encompasses every new feature and every combination of features. This includes in particular any combination of features in the patent claims, even if this feature or this combination itself is not explicitly specified in the patent claims or exemplary embodiments.

QUOTES INCLUDE IN THE DESCRIPTION

This list of documents listed by the applicant has been generated automatically and is only included for the better information of the reader. The list is not part of the German patent or utility model application. The DPMA assumes no liability for any errors or omissions.

Patent literature cited

• EP 2601006 B1 [0008]
• DE 102015225652 [0009]

Claims (13)

Method for additively producing a structure (10, 10 '), in particular by a powder bed method, comprising in layers: - a) applying a layer (S) of a, in particular powdery, base material (P) to a production area (HF), - b) additive construction of the structure by selective irradiation of the applied layer in accordance with a predetermined structure geometry, an area (B1, B2, 204) being left free of the radiation within a cross section of the structure (10, 10, 20 '), in which during the additive Structure of the structure (10) a coolant (210) is guided to cool the layer and / or the structure built. Procedure according to Claim 1 The structure is constructed in such a way that the areas in the structure which are left free in layers form a coherent cooling channel (204). Procedure according to Claim 2 , wherein the cooling channel (204) is formed in such a way that it extends parallel to a mounting direction (AR) of the structure (10). Procedure according to Claim 2 or 3 , wherein the cooling channel (204) is successively filled from below via a construction platform (1) with the coolant (210) (c)) and displaced coolant (210) and base material (P) on the production surface (HF) are removed (d)) , Method according to one of the preceding claims, wherein the coolant (201) forms a boundary layer on the production surface (HF) to the layer of the base material (P). Method according to one of the preceding claims, wherein the structure (10) comprises the construction of two or more components, and two or more of these components define the cooling channel (204). Method according to one of the preceding claims, wherein the cooling channel (204) is at least partially defined by a space (101) of an additive manufacturing system. Method according to one of the preceding claims, wherein after the additive construction of the structure (10), a heat treatment is carried out, which effects intermetallic precipitates, in particular γ and / or γ 'phases, in the structure (10). Method according to one of the preceding claims, wherein the coolant (210) represents or comprises a thermal paste, for example FEROTHERM® X. Method according to one of the preceding claims, wherein the base material (P) comprises one or more of the following materials: PWA795, Merl72, MAR-509, Stellite-31, Hastelloy X, Haynes 230, Haynes 625, IN939, IN738, IN713, IN792, IN718, Alloy 247 and Rene 80. Component (10) which is produced or can be produced according to the method according to one of the preceding claims, further comprising the structure, the component being intended for use in the hot gas path of a gas turbine. Component (10) according to Claim 11 , which consists of a, especially nickel or cobalt-based, superalloy and has a lower density of structural defects, such as hot cracks or solidification cracks, compared to a component of the prior art. Device (200) for performing the method according to one of the Claims 1 to 10 , comprising a coolant reservoir (201), a coolant connection (202) and a control unit (50), the device (200) being further designed to coolant (210), for example via a valve (202), by means of a construction platform (1) an additive manufacturing system (100) to lead into a space (BR).

Images