EP3191690A1

EP3191690A1 - Turbine blade having an inner module and method for producing a turbine blade

Info

Publication number: EP3191690A1
Application number: EP15778642.7A
Authority: EP
Inventors: Jan Münzer
Original assignee: Siemens AG
Current assignee: Siemens AG
Priority date: 2014-10-14
Filing date: 2015-10-08
Publication date: 2017-07-19
Also published as: WO2016058900A1; CN107075954A; US20170306766A1; DE102014220787A1

Abstract

The invention relates to a turbine blade having a shell and an inner module, wherein the inner module can be flown through by a cooling medium both in the longitudinal and radial direction, the inner module being mounted with the shell by means of a fixed bearing and a floating bearing. The invention further relates to a method for producing a turbine blade having an inner module and a shell by means of selective laser melting.

Description

description

TURBINE BUCKET WITH INTERNAL MODULE AND METHOD FOR PRODUCING A TURBINE BUCKET

The invention relates to a turbine blade with an inner module and a method for its production by means of selective laser melting.

Gas turbines are used as engines for various facilities, such as power plants, engines u. ä. gas turbine components, particularly turbine vanes and blades ^¬, but also ring segments or components of the Be ^¬ reaching the combustion chamber are subjected to during their operation high ther ^¬ mix and mechanical loads. These are often cooled with compressor air and in the case of the combustion chamber with unburned fuel. Sometimes water vapor is used for cooling.

Turbine blades usually form a cavity formed by their outer shell, also referred to as a jacket, which cavity is often subdivided by side walls. For cooling, the components are flowed through, for example, in an interior space formed by the side walls of the cooling medium, the heat being removed from the component inside and the component is thus actively cooled ^¬ . For this purpose, for example, cooling air is directed out of the nenraum In ^¬ by so-called impingement channels in a space between the interior and the jacket and rebounds there on the inside of the thermally highly loaded jacket. The technology in this application is intended primarily for cooling air as a cooling medium. Therefore, the term cooling air is used in the following, but excluding other cooling media. Following this, the cooling air is often blown out through holes in the jacket. The cooling air thereby carries heat from the interior or the component wall and also forms a film on the blade surface, which forms an insulating layer between the blade surface and the hot gas.

In current designs of gas turbines are also taken in the interests of effective cooling in terms of cost, component life, efficiency and performance disadvantages. Thus, a full-on mechanical integrity and cooling air guide ^¬ put internal geometry is produced by the casting core in the form of a vacuum, for example, in turbine blades. Here it was possible for example by microsystems technology, the cores and the subsequent construction ^¬ some more complex, more stable and more precise ser perform microscale. In Turbinenleitschaufein the internal geometry is often in addition to the image of the casting core by cooling air inserts, usually so-called impingement cooling sets Darge ^¬ provides. As Cutting Edge Technology for applies the so-called savings ^¬ shell technology from Florida turbine tech- nologies.

However, the solutions of the prior art have some disadvantages. Conventional core manufacturing processes for turbine blades ^¬ ^¬ core stability, geometry part resolution and others are in terms core geometry complexity, limited in terms of other criteria. Also, micro cores have limitations in optimization design, particularly in terms of the dimensions and stability of the complex ceramic cores during the manufacturing process. The manufacturing process is also relatively expensive due to the high exclusion rate. In blades with cores from conventional micro-processes, the cooling air flow is mainly in the radial direction, which ensures optimum utilization. The cooling air potential can be limited within limits, especially with the view that, with increased local heat transfer, a general increase in the cooling air mass flow of the blades is often necessary in order to be able to dissipate the heat from the component. In particular when running, but also for routing ^¬ shovels of turbines, the problem often occurs that due to thermal stress on the one hand and by effective cooling on the other hand occurring stresses in the component reduce the life or the interpretation is limited because there are areas in the component, where very hot areas, such as outer walls, in very cold regions, such as very strong ge ^¬ cooled inner walls, boundaries, because the turbine blades manufactured with conventional or micronucleus form an integral, consisting also of mating, similar materials Hendes component. Approaches to thermally isolate some area, for example, by local ceramic interior coatings, and thus at least partially solve the problem, could not previously been implemented manufacturing technology.

In Turbinenleitschaufein also occurs the problem that the cooling air supply pressure there is usually the same level in all areas of a component, which is not ^{necessary ¬} agile. In this way, given away to a large extent Kühlpo ^¬ tential and expensive compressor air for cooling ver ^¬ spent. The savings Shell technology offers by the Tat thing, that the cooling air flows through the component not only radially, son ^¬ countries in and against the flow direction, advantages with regard to the cooling air utilization, and thus the efficiency. However, the production of Kühlein ^¬ rates (Spar) is quite complex and therefore expensive and limits of manufacturing technology in its complexity. In addition, the subsequent insertion into the component (shell) is also complex, and the component design by Best ^¬ ing joining technologies in the component design by necessary Retractability into the component before joining or limited during assembly.

The object of the invention is therefore to provide a turbine blade with an insert ensuring optimum cooling, which is complex, stable and easy to produce. There is furthermore the object, a method ^¬ bereitzu with which may be a turbine blade with a corresponding insert made. The first object is achieved by a turbine blade with the features of claim 1. The second object is achieved by a method having the features of claim 10. Further advantageous variants and embodiments of the invention will become apparent from the dependent claims, the embodiments and the figures. A first aspect of the invention relates to a turbine blade with a jacket and an inner module adapted to the shape of the jacket, wherein the inner module has an inner space through which an inflow opening can flow in a longitudinal direction of the inner module and an inner wall with a number of openings which can be flowed through in the radial direction with a outside of the wall of the inner module connecting channels in which between the outer side of the wall of the inner ^¬ module and an inner side of the shell, a peripheral Zwi ^¬ is available space, and between the inside and an outer side of the shell in a certain angle of inclination to the outside of the shell a number of perforations is present, characterized in that the outside of the inner module is connected by means of at least one fixed bearing and min ^¬ least one loose bearing with the inside of the shell.

The component according to the invention is so Artwork that it ^¬ so well in the longitudinal as well as in the radial direction of cooling air can be flowed through. The cooling air passes through fine Ka ^¬ ducts in the peripheral intermediate space and meets accurately dimensioned as impingement cooling air to the inside of the jacket of the turbine blade. The air then flows through perforations in the jacket to the outside of the jacket, where a

Film formation and further convective heat dissipation takes place. The turbine blade according to the invention is advantageous because, in addition to the optimized internal cooling of the blade, by utilizing the cooling potential of the cooling air, it also allows the implementation of lightweight structures, since cooling and structural functions can be decoupled. The modular design of the construction ^¬ part and the use of different materials for outer shell and the module have an advantageous effect on thermal ^¬ clamping voltages in the component. The advantage of the design of at least one connection of the inner module with the shell of the turbine blade at some points as a movable bearing is mainly in the prevention of static overdetermination of the integration of the inner module in the turbine blade. Furthermore, this design allows for free thermal expansion or centrifugal force expansion in a mainly radial direction. It allows the compensation of manufacturing gungs- and joint tolerances, facilitates the positioning of the inner module in the blade and favors the vibration damping ^¬. The advantage of designing at least one connection of the

Inner module with the jacket as a fixed bearing serves mainly the load absorption of the inner module in the component. The connection Zvi ^¬ rule the inner module and the turbine blade is caused mainly by the support sections of the inner module. It is therefore preferred that support profiles are formed on the outside of the wall of the inner module. These support profiles typically have a supporting flank and a free flank. The Connection of jacket and inner module by means of a fixed bearing is advantageous because the remaining freedom ^¬ grade can be determined, especially in the radial direction. The fixed bearing also serves for load absorption (centrifugal force), damping and positioning of the inner module in the blade.

It is preferred if the material of the inner module is a ^metal . It may ideally be an alloy or a superalloy. It may be the same material as the shell of the turbine blade, but also different from this. A metal advantageously allows a metallurgical bond between the indoor module and the casing of the turbine blade, which is typically also made from Me ^¬ tall, ideally, an alloy or a super alloy.

In a further preferred embodiment, the jacket and the inner module are metallurgically connected. This can be done by melting during the casting process of the ^turbine blade, for example. However, it is also preferred if the inner module and the jacket of the turbine blade are connected by means of the fixed bearing by positive engagement or frictional connection.

Preferably, the angles of inclination of the perforations in the casing of the turbine blade are designed relative to the outside of the shell so that film formation on the outside of the shell can be effected by the air flowing out via the perforations. The film formation is advantageous because it causes cooling on the outside of the shell and thus on the upper surface ^¬ the turbine blade. The interior of the inner module is preferably in at least two by at least one through-flow opening divided into interconnected chambers. The division into chambers serves, among other things, the stability of the internal volume.

Furthermore, the interior module in the distal wall, i. in the wall in the region of the turbine blade tip, preferably additional channels in its wall. These are not flowed through in the radial direction of the inner module or the turbine blade, but in the longitudinal direction. These channels are also designed for impingement cooling.

It is particularly preferred if the inner module of the turbine blade is produced by selective laser melting. With ^¬ means of selective laser melting, the inner module is Artwork due to the possibilities of the process of selective melting, in particular by the layer-wise building up, in a relatively simple manner with a complex and stable structure that it can be flowed through both in the radial and in the direction of flow of cooling air can. The advantage of such interior modules is that they can be made complex, but they are optimally designed. Especially in connection with ceramic core for component production of the turbine blade, the representation of components with ^¬ tels Selective laser melting is particularly advantageous.

A second aspect of the invention is directed to a method for producing a turbine blade, which comprises the following steps S1 to S5 for producing an inner module: S1) providing a construction platform in a powder bed,

52) applying a powdered material in a certain amount,

53) distributing the material over the build platform, 54) local fusion of powder particles by action of a laser beam,

55) lowering the platform.

During local fusion of powder particles, the powder particles are also fused with an underlying layer. The steps S2 to S5 are repeated in a number, as is necessary for the completion of the inner module ^¬ . The method for the production by means of selective laser melting is advantageous because it is a formless production, and thus no tools or forms are not ^¬ agile. Furthermore, the method is advantageous because there is a large freedom of geometry, the component forms he ^¬ allows, which are not or only with great effort can be produced with form-bonded method. Thus, the indoor unit, particularly with respect to complex structures, because of the Mög ^¬ possibilities of this process is so Artwork that it can be flowed through both in the radial and in the direction of flow of cooling air and this accurately dimensioned to the entspre ^¬ required positions by fine channels can be performed as impact cooling air on the inside of the jacket. In addition, ^¬ light of the manufacturing process enabling the design of complex structures in the outside that allow the mounting of the inner module to the shell via fixed and floating bearings. It is particularly preferred if the powdery material comprises a metal. It is further preferred if the powdery material is a metal, and also preferably given ^¬ if the powdery material is a metal alloy. This is advantageous because thereby a metal lurgical ^¬ connection between the indoor module and the casing of the turbine blade, which is typically also made of metal, is possible. It is further preferred if generated in the outside of the inner support module ^¬ profile during the selective La ^¬ serschmelzprozesses. The support profiles have bearing flanks and free flanks. About this support profiles a fastening ^¬ tion of the inner module with the jacket is possible.

Preferably, the method according to the invention further comprises the following steps S6 to S10 for producing a shell of the turbine blade, which join at step S4 of the production of the inner module when it is completed:

56) applying a ceramic casting core to the inner module, wherein the supporting and free flanks are not covered by a ceramic core material in at least one provided for a fixed bearing support profile,

57) embedding the ceramic core containing the inner module in a wax model of the blade,

58) producing a casting mold for the shell from a wax model,

59) stabilizing the casting core in the casting mold by fixing by means of ceramic and / or metallic pins,

- S10) casting the metal mold.

The support profile, which is not covered by ceramic core material, is intended to form the fixed bearing during the casting of the jacket, by way of which the inner module is connected to the shell of the turbine blade. The tip of the support profiles is thus left metal ^¬ lish blank to create the conditions for a positive or, especially, metallurgical bond Zvi ^¬ rule indoor unit and coat. It is preferred if the outside of the inner module to the inside of the jacket verbun by mechanical form fit ^¬ is the. This is achieved by the design of the supporting profiles with ^¬ means of selective laser melting and the casting mold of the shell with the corresponding interlocking structures, so corresponding bulges possible.

It is further preferred if the outside of the inner ^¬ module is metallurgically connected to the inside of the shell. This is also made possible by the formation of the carrier profile by means of selective laser melting and the casting mold of the jacket. When the shell is cast, the high temperatures of the hot metal cause a metallurgical bond in the area of the supporting profile.

An interior module in the present invention is an insert for turbine blades. The term indoor module underlines the modular design.

The inside of the inner module refers to its inwardly directed surface, which bounds the interior of the inner ^¬ module. The outer side of the inner module refers to its outwardly facing surface, which faces in the radial direction of the inside of the shell and forms an inner Begren ^¬ wetting of the peripheral gap.

The inside of the jacket refers to its inward facing surface, which delimits the peripheral gap in ra ^¬ dialer outward direction.

The outside of the shell refers to its radially outwardly directed surface, which may also be referred to as the outside or surface of the shell or turbine blade. A fixed bearing is a so-called fixed bearing, which prevents all translational movements of the stored body, in the present application of the inner module. No torques are transmitted, the inner module is fixed in three spatial directions.

A floating bearing prevents only one or two Translationsbewe ^¬ conditions and lets the others. Accordingly, there is no fixed connection with or between the inner module and the jacket, at least in one or in two directions. The longitudinal direction of the indoor module and the equally oriented turbine blade and the shell of the ^turbine blade refers to the extent of the turbine show ^¬ fel from the root portion of the turbine blade, where it is attached to the Turbi ^¬ nenrotor until the tip of the turbine blade leaf.

The radial direction is directed perpendicular to the longitudinal direction to the outside.

The invention will be explained in more detail with reference to FIGS. 1 shows a longitudinal section of an exemplary embodiment of a turbine blade showing the internal geometry of an inner module and a shell of the turbine blade.

FIG. 2 shows a longitudinal section of a section of the turbine blade according to FIG. 1.

3 shows a longitudinal section of a portion of the ^turbine blade of FIG. 1.

4 shows a longitudinal section of a portion of the ^turbine blade of FIG. 1. 5 shows a longitudinal section of an apparatus for producing the inner module of the turbine blade according to FIG

Fig. 1.

6 shows a longitudinal section of the inner module of

Turbine blade according to FIG. 1.

FIG. 7 shows a wax mold for producing the jacket of the turbine blade according to FIG. 1.

Figure 8 is a flow chart of an exemplary

Embodiment of a method for producing the turbine blade according to FIG. 1.

The turbine blade 1 as shown in Fig. 1 embodiment shown by way of example comprises a shell 2 and an inner module 3. The indoor unit 3 is substantially matched to the shape of means of Man ^¬ 2. The interior module 3 has an interior space 4, which can be flowed through in the longitudinal direction 17 of the interior module 3, with an inflow opening 5 and a wall 6 with a number of openings that can be flowed through in the radial direction 18, an inside 61 with an outside 62 of the wall 6 of the interior module 3

on connecting channels 7. Furthermore, the illustrated inner module 3 in the distal region of the wall 6 has a number of channels 8 which can be flowed through in the longitudinal direction 17 and are arranged here in addition to the channels 7 which can be flowed through in the radial direction in the lateral area of the wall 6.

Between the inner module 3 and the jacket 2 there is a peripheral interspace 9, which is delimited by the outer side 62 of the inner module 3 and the inner side 21 of the jacket 2. Through the channels 7 and 8 from the interior 4 cooling air in the peripheral gap 9 can be flowed, where they bounce on the inside 21 of the shell 2 and thereby can cause the effect of impingement cooling. In the jacket 2, a number of perforations 10 are arranged, through which the cooling air from the space 9 on the outside 22 of the shell 2 is flowable, where it can form a cooling film.

The inner module 3 is connected by means of fixed bearings 11 and movable bearings 12 with the jacket 2. In each case at least one bearing is present, but preferably a plurality of fixed bearing 11 and a plurality of floating bearing 12 are provided for connecting the inner module 3 and 2 sheath. For the connection via fixed bearing 11, the inner module 3 at least one support profile 15 and for the connection via movable bearing 12 at least one support section 16, wherein the number of support profiles 15 and 16 according to the length of the turbine blade 1 and accordingly of the inner ^¬ module 3 is directed , The jacket 2 has at the points of the pre ^¬ seen fixed bearing 11 to the support profiles 15 corresponding bulges 19 and at the locations of the provided

Loslager 12 the support profiles 16 corresponding bulges 20th

The support profiles 15 and 16 and the bulges 19 and 20 preferably extend annularly around an entire area around the outer side 62 of the inner module 3 or the inner side 21 of the shell 2, but can also be arranged only at individual locations. The fixed bearing 11 and floating bearing 12 are accordingly preferably closed annular, but can also be arranged only at individual points.

By the fixed bearing 11 of the peripheral gap 9 is interrupted, as long as they run around the entire outer side 62 of In ^¬ nenmoduls 3 and thereby by positive engagement or metal ^¬ lurgical connection with the inner side 21 of the shell 2 are un ^¬ permeable to cooling air. The loose bearings 12 interrupt the peripheral gap 9, provided that they run in a region around the outer side 62 of the inner module 3 and there ^¬ firmly abut an area of the inner side 21 of the shell 2. The inner space 4 of the inner module 3 consists of a plurality of chambers 14 which are separated by the material of the inner module 3 and which are connected to one another via openings 13 which can be flowed through in the longitudinal direction. In this case, the inner module 3 preferably 2 chambers 14, also preferably 3, also preferably 4, and also preferably 5 or more.

At the foot, the turbine blade 1 a Tannenbaumstruk ^¬ tur 31, which serves the stable connection via a correspondingly shaped structure with the turbine rotor (not shown).

The peri ^¬ pheren intermediate space 9 essential for the cooling of the turbine blade 1 is formed between the outer side 61 of the wall 6 of the inner module 3 and the inner side 21 of the shell 2, as shown in Fig. 2. In this case, the channels 7 are formed so that cooling air in radia ^¬ ler direction 18 can flow from the interior 4 through the channels 7 in the peripheral gap 9, where it meets the inside 21 of the shell 2. The perforations 10 in the shell 2 are formed with respect to number and angle of inclination so that through the perforations from the peripheral gap 9 on the outside 22 of the shell 2 flowing cooling air can form a cooling film there. The angle of inclination of the perforations relative to the outside 22 is between 10 and 80 degrees, preferably between 20 and 70 degrees, more preferably between 30 and 60 degrees, even more preferably between 40 and 50 degrees, and even more preferably 45 degrees.

The connection of the inner module 3 with the jacket 2 by means of fixed bearings 11 is shown in detail in FIG. The support section 15 of the indoor unit 3 and the corresponding education book tung 19 in the shell 2 are dimensionally successive abge ^¬ true, so that they match one another form-fitting manner. Due to the resulting complete positive connection, the nenmodul 3 at the location of the fixed bearing 11 in any direction movable.

The connection of the inner module 3 with the jacket 2 by means of floating bearings 12 is shown in detail in Fig. 4. The supporting profile 16 of the inner module 3 and the corresponding recess 20 in the shell 2 are matched to each other dimensional, las ^¬ sen However, degrees of freedom, ie, a certain mobility or a certain margin of the supporting profile 16 within the bulge 20 to. The manufacture of the inner module 3 of the turbine blade 1 is carried out in a molten bath 100 according to the steps of the flow chart in FIG. 8. In step S 1, a build platform 101 is provided according to FIG. A powdery material 102, preferably of a metal or a metal alloy, for example of the same material as the door ^¬ binenschaufel, but optionally also from another Mate ^¬ rial, in step S2 in a certain quantity by means of the filling device 103 on the build platform 101 applied. In step S3, the deposited material 102 is spread on the build platform 101, for example, by a slider or a wiper, so that it forms a layer in a thickness that can be well melted by laser beams 105 according to the desired structure. Preferred layer thicknesses are 20-100 μm. In step S4, the powder particles 103 are locally melted by the action of a laser beam 105 which is generated by a laser 104 and guided by the rotating mirror 106 in software-controlled manner over the build platform 101 in such a way that the desired solid structures are formed, for example the support profiles 15 and 16. The pulverulent material 102 is completely converted at the locations of the laser radiation. Melted and forms a solid material ^¬ layer after solidification.

After step S4 is checked whether the indoor unit is completed ^¬. If it is not finished, in step S5, the build platform is lowered to the appropriate height with a layer thickness 101, and the process from step S2 to again gestar tet ^¬. The cycle of the steps S2 - S5 as long again ^¬ obtained until the indoor unit is completed in the desired pattern. 3 If it is determined in step S4 that the inner module is completed ^¬ to the indoor unit 3 around a ceramic casting core 110 is produced at this step, then in step S6. For the casting core while conventional ceramic material is used. In this case, as shown in Fig. 6, the support profiles 15, which are provided for the formation of fixed bearings 11, not encased in ceramic. The support profiles 16, which are provided for the formation of movable bearings 12, however, are encased in ceramic.

In step S7, the ceramic core casting 110 containing the inner module 3 is embedded in a wax model 120 of the turbine blade 1, in which it is surrounded by wax 121, as shown in FIG. Then, in step S8, a casting mold, so-called casting shell, for the shell 2 is produced. In step S9, the ceramic core 110 with inner module 3 in the casting shell is stabilized by means of ceramic and / or metallic pins.

In step S10, the shape of the shell 2 is poured. In this case, the area of the ceramic casting core 110 forms the peripheral gap 9 between the inner module 3 and the jacket 2. As the material of the shell 2, for example, metals before Trains t ^¬ alloys and superalloys. By the form-fitting design of the support profiles 15 and the corre ^¬ sponding bulges 19, the outer side 62 of the inner module 3 with the inner side 21 of the shell 2 in the region of the fixed bearing 11 is preferably connected by mechanical positive connection.

Through the form-fitting design of the supporting profiles 15 and the corresponding lobes 19 and by the preferred metal of the powdery material 102, the Au ^¬ ßenseite 62 of the indoor module 3 with the inner side 21 of the Man ^¬ means of 2 in the region of the fixed bearing 11 is also preferably a metallurgical bond connected. The metallurgical connection is made possible by the high temperatures of the liquid metal of the shell 2, which cause melting of exposed areas of the inner module.

Variations and changes of the invention which are obvious to a person skilled in the art fall within the scope of the patent claims.

Claims

claims

1. turbine blade (1) having a jacket (2) and an inner module (3) adapted to the shape of the jacket (2),

wherein the inner module (3) has an interior space (4) through which an inflow opening (5) can flow in a longitudinal direction (17) and a wall (6) with a number of openings (61) which can be flowed through in the radial direction (18) (62) the channel (6) of the inner module (3) comprises connecting channels (7),

wherein between the outer side (62) of the wall (6) of the inner module (3) and an inner side (21) of the shell (2) a peripheral gap (9) is present, and between the inner side (21) and an outer side (22 ) of the jacket (2) at a certain angle of inclination to the outside (22) of the

Mantels (2) a number of perforations (10) is present,

characterized in that

the outer side (62) of the inner module (3) is connected to the inner side (21) of the jacket (2) by means of at least one fixed bearing (11) and at least one loose bearing (12).

2. turbine blade (1) according to claim 1,

at the outside (62) of the wall (6) of the interior module

(3) supporting profiles (15, 16) are formed.

3. turbine blade (1) according to any one of claims 1 or 2, wherein the material of the inner module (3) is a metal.

4. turbine blade (1) according to one of the preceding Ansprü ^¬ che,

at the inner module (3) and jacket (2) are metallurgically connected.

5. turbine blade (1) according to any one of claims 1 - 3,

in the inner module (3) and jacket (2) by means of Festla ^¬ gers (11) are connected by positive locking.

6. turbine blade (1) according to one of the preceding Ansprü ^¬ che,

wherein the inclination angle of the perforations (10) in the shell (2) relative to the outside are designed such forms ^¬ (22) of the casing (2) that by via the perforations (10) flowing air film formation on the outside (22) of the jacket (2) is effected.

7. turbine blade (1) according to any preceding Ansprü ^¬ che,

in which the interior (4) of the inner module (3) is subdivided into at least two chambers (14) which are interconnected by at least one opening (13) through which they can flow.

8. turbine blade (1) according to claim 1 or 2,

in which in the distal wall of the inner module (3) in addition in the longitudinal direction (17) of the inner module (3) can be flowed through

Channels (8) are arranged.

9. turbine blade (1) according to one of the preceding Ansprü ^¬ che,

in which the inner module (3) is produced by selective laser melting.

10. A method for producing a turbine blade according to one of claims 1 - 9,

comprising the steps of creating an interior module

51) providing a build platform in a powder bed,

52) applying a powdered material in a certain amount,

53) distributing the material over the build platform,

54) Local fusion of powder particles by action of a laser beam,

55) lowering the platform, wherein the steps S2 - S5 are repeated in a number as necessary to complete the interior module.

11. The method according to claim 10,

wherein the powdery material comprises a metal.

12. The method according to claim 10 or 11,

wherein support profiles are produced in the outer side of the inner module.

13. The method according to any one of claims 10 - 12,

additionally comprising the steps subsequent to step S4 for generating a cladding

56) applying a ceramic casting core around the inner module, wherein the support and relief flanks at least a ^¬ min foreseen for a fixed bearing support section is not encased in a ceramic core material,

58) producing a casting mold for the shell from the wax model,

- S10) casting the shell mold.

14. The method according to claim 13,

wherein the outer side of the inner module is connected to the inside of the jacket in the region of the fixed bearing by mechanical form fit.

15. The method according to claim 13,

wherein the outside of the inner module is metallurgically bonded to the inside of the shell in the region of the fixed bearing.