WO2020099184A1

WO2020099184A1 - Method for producing a component for a turbomachine

Info

Publication number: WO2020099184A1
Application number: PCT/EP2019/080225
Authority: WO
Inventors: Sebastian Motsch; Wolfgang Rothkegel; Björn HINZE
Original assignee: Rolls-Royce Deutschland Ltd & Co Kg
Priority date: 2018-11-15
Filing date: 2019-11-05
Publication date: 2020-05-22

Abstract

The present disclosure concerns a method (50) for the operation of a turbomachine, particularly for an aircraft engine, the turbomachine having a component produced by the steps: providing (52) at least one first component (32a) having a first connecting element (40a); providing (54) at least one second component (32b) having a second connecting element (40b); providing (56) a base element (38); fastening (58) at least one of the at least one first components (32a) on the base element (38); fastening (60) one of the at least one second components (32b) on the base element (38), wherein the one second component (32b) is fastened adjacent to the one first component (32b) or between two first components (32a), and wherein, during the operation (62) of the turbomachine, connecting elements (40a, b) of the first component (32a) and of the second component (32b) are frictionally and/or interlockingly connected in a particular operating mode (62) of the turbomachine. The present disclosure further relates to a method for producing a corresponding component, to a corresponding component and to a gas turbine engine.

Description

Method for producing a component for a turbomachine

The present disclosure relates generally to engine technology. In particular, the present disclosure relates to the production of engine components with a configuration suitable for friction welding production. More particularly, the present disclosure relates to a manufacturing method for an engine component with reduced vibration properties. Especially in the low-pressure area or in the case of low-pressure turbines and in contrast to medium-pressure turbines, high-pressure turbines or compressor modules, rotor blades, mounted on a ring, are used which, compared to rotor blades in the medium or high-pressure region of a turbine, have comparatively long dimensions, at least in one direction of extension. exhibit. These comparatively long moving blades, which are used above all at rear stages in a turbine, usually have comparatively narrow configurations at the same time and are used in a turbine in a relatively low speed range or relatively low temperature range.

To reduce weight, integral blade-disc connections or blade-ring connections, so-called blisks or blings, are used, in particular in the area of the low or medium pressure compressor. A conventional manufacturing process for such blisks or blings consists of full machining

Material. This results in a high expenditure of material and time, and blisks produced in this way can only be repaired in a complex manner.

Another possibility for the manufacture of rotor blades consists in a friction welding process of the blade and disk or ring, which leads to a reduction in material and time expenditure in comparison to the machining, and at the same time improves the repairability. However, friction welding in the turbine area is only used for joining comparatively short blades in the high pressure area, due to the less complex geometry that occurs here in comparison to blades in the low pressure area. Such short blades have an uncritical vibration behavior and therefore do not require any further toothing or connection between adjacent blades, for example tensioning straps such as so-called snubbers, interlocking shrouds or Z-shrouds, which conventionally make it impossible to produce a friction weld due to the complex geometric structure or simply because of the fact that long blades with tensioning straps would already be connected and would therefore not be able to be attached to the disc individually using a friction welding process. The space required for friction welding in the vicinity of the rotor blade in the axial and circumferential directions makes it impossible to use known tension band concepts in the manufacture of rotor blades in the low-pressure range with their comparatively large dimensions. Rather, in the case of an attempt at friction welding, there would be an unauthorized overlap of adjacent tension band segments, as a result of which conventional solutions for reducing vibrations of long moving blades, such as the provision of the aforementioned tension bands, cannot be realized with known friction welding processes.

Thus, there may be a need to connect relatively long moving blades in a suitable manner to reduce vibrations, the connection allowing a fastening method by means of friction welding.

This need may be met with the subject matter of the independent claims. Preferred embodiments result from the dependent claims and are explained in more detail in the further description.

According to a first aspect of the present disclosure, a method for operating a turbomachine, in particular for an aircraft engine, is provided, the turbomachine having a component, produced by the steps of providing at least one first component with a first connecting element, providing at least one second component with one second connecting element, providing a base element, attaching at least one of the at least one first component to the base element, attaching one of the at least one second component to the base element, the second component being attached next to the first component or arranged between two first components, and wherein connecting elements of the first component and the second component are non-positively and / or positively connected in an operating state of the turbomachine. According to a second aspect of the present disclosure, a method for producing a component for a turbomachine, in particular for an aircraft engine, is provided, comprising the steps of providing at least one first component with a first connecting element, providing at least one second component with a second connecting element, providing one

Base element, attaching at least one of the at least one first component to the base element, attaching one of the at least one second component to the base element, the second component being attached adjacent to the first component or between two first components, and wherein

Connecting elements of the first component and the second component after fastening the at least one first component and the second component are non-positively and / or positively connected.

According to a third aspect of the present disclosure, there is provided a component for a gas turbine engine for an aircraft, comprising a first component with a first connecting element, a second component with a second connecting element, and a base element, the first component and the second component on the base element are attached adjacent, wherein connecting elements of the first component and the second component are non-positively and / or positively connected, or wherein connecting elements of the first component and the second component are non-positively and / or positively connected in an operating state of the turbomachine.

According to a fourth aspect of the present disclosure, a gas turbine engine for an aircraft is provided, comprising at least one component according to an embodiment of the present disclosure, produced according to an embodiment of a method of the present disclosure.

Ideas and concepts of the present disclosure may be considered to be based on the following observations and knowledge.

According to the present disclosure, an operating method and a manufacturing method for rotor blades for low-pressure compressor areas in turbines are provided, as a result of which even complex, geometrically designed rotor blades can be fastened to a disk using a friction welding process and still have a preferred vibration behavior, in particular during operation. The vibration behavior is influenced by the use of connecting elements, which are arranged essentially in the circumferential direction between two adjacent rotor blades and at least connect them appropriately during operation or are in contact by means of the connecting elements in order to be able to influence the vibration behavior of the rotor blades .

Conventionally, these connections or contacts have been formed integrally and thus an integral connection between two moving blades, in particular in the case of a machining production process, made from the solid material. In other words, the connecting element between two rotor blades or components has conventionally already been produced from the solid during the manufacture of the individual rotor blades. According to the disclosure, the individual components or blades of a complex component have connecting elements in the radial circumferential direction, which are in contact with one another at least during operation, in particular in a form-fitting manner. By a suitable geometric design of the connection surfaces between the adjacent connection elements, hereinafter also as

Designated contact points or contact surfaces, a non-positive connection, which can thus be subjected to pressure, for example, can be realized, or a form-fitting connection is also possible through a suitably complex geometric configuration.

Components or rotor blades according to the disclosure have a comparatively large geometric length in a longitudinal direction in comparison to other rotor blades or components in a compressor. The direction of longitudinal extension refers here to the radial direction starting from the disk or a base element, thus the inner attachment point of a component or rotor blade to its radially outer position, thus the length of the rotor blade in the radial direction Extension direction. The connecting elements of adjacent rotor blades have essentially corresponding radial positions. This ensures that after the individual components or at least two adjacent components have been fastened, the connecting elements are arranged in a comparable radial position and can thus come into contact with one another, for example in contact with one another or rest on the adjacent surfaces of the connecting elements and thereby the contact between the connecting elements manufacture.

By means of a suitable, in particular complementary, surface geometry, for example a zigzag or Z-shape of the surfaces, interlocking elements of adjacent connecting elements of two moving blades and / or a beveling of the contact surfaces, a positive connection can be achieved.

Components according to the present disclosure may have connecting elements at extreme radial positions or alternatively or additionally at intermediate radial positions of the longitudinal extension direction of the individual components. As part of the friction welding process, individual components may be attached to a base element or a disk, which friction welding connection represents a first connection or fastening point of the component. In order to have a positive influence on the vibration behavior of individual components or of the entire component, neighboring components may be connected to one another at further contact points or further contact surfaces. This connection may provide a non-positive or positive connection. For this purpose, a component has at least one, preferably two or a multiple of two connecting elements with which one

Component is in contact with neighboring components. A preferred embodiment of such a connecting element is, for example, the provision of a shroud in an external radial position. Each component may have a portion of the shroud that is designed and dimensioned to come into contact with the corresponding shrouds of adjacent components. In the case of a completely circumferential component for a turbomachine, the individual partial shrouds of the individual components may be joined together to form an overall shroud, at least during operation of the turbomachine, and thus form a substantially circumferentially closed shroud, by partial shrouds lying on top of one another, in particular with contact surfaces in the contact point .

As an alternative or in addition to a shroud as a connecting element, components according to the present disclosure may have further connecting elements at further suitable radial positions. The connecting elements can be designed in such a way that they come into contact with complementarily designed connecting elements of adjacent components or directly with the surface of an adjacent component.

In other words, the non-positive or positive contact between two components can only be established by means of the connecting elements when the component is in an operating state, thus when the engine is operating. This may be possible, for example, by means of suitably dimensioned or constructed components by means of centrifugal expansion or thermal expansion.

Alternatively, the contact areas may be configured such that adjacent contact areas after the assembly on the

Stand in contact with the base element and form the positive or non-positive connection. The effect of so-called shortening, for example, may be exploited here Radial shortening of a component in the friction welding process, so that connecting elements which are not yet in contact before carrying out a friction welding process abut or rest on one another after completion of the friction welding process.

It is also conceivable that a component, as explained above, has a plurality of connecting elements which are formed on opposite sides of the component. As a result of the requirement to align connecting elements with neighboring components, these connecting elements essentially extend in the circumferential direction. Two, three, four or five or more connecting elements per component are thus conceivable, which may be arranged at the same or different radial positions on the opposite sides of the component. As a result, not all adjacent components or blades may have connecting elements with essentially the same radial positions. Rather, the connecting elements can, for example, alternately have alternating or generally different radial positions. As a result, the overall vibration behavior or the individual vibration behavior of a plurality of components can be improved compared to an embodiment with essentially the same radial positions of the connecting elements, and thus a minimization or optimization of the vibration behavior can be realized. Adjacent and thus complementarily designed connecting elements on adjacent components may, in particular, have the same radial position.

In this way, adjacent components can also be connected with two or more connecting elements. Adjacent components may thus not only touch at contact points or a contact surface, but at several contact points and thereby transmit forces. When using several connecting elements between two neighboring components, the connecting elements may be the same or of different types are in contact, in other words may be in a non-positive and / or positive contact. Further optimization of the vibration behavior of the component may be possible through a suitable configuration of the contact types, thus the points of attack or types of attack or connection types of connecting elements of adjacent components.

In order to further reduce and optimize the vibration behavior, a mixture of the non-positive and / or positive connections occurring at different times is also conceivable. In other words, it may be possible to form a plurality of connections between adjacent components, at least one first connection occurring after assembly and at least one second connection only being realized during operation.

The radial position of a connecting element may be selected or determined in particular taking into account the vibration behavior of the component, in particular to reduce the tendency to vibrate of the individual components. A suitable selection of the radial positions of connecting elements can thus be used to detune a dynamic overall system, so that a reduction or optimization of the vibration behavior of the component can be achieved. Such a targeted influencing of the vibration behavior of individual rotor blades may have a positive influence on the tendency of a complex component to vibrate for a turbomachine, so that blades with larger dimensions than those conventionally suitable for a friction welding process may also be used for the production of a component by means of a friction welding process.

According to an embodiment of the present disclosure, first connecting elements and second connecting elements like one another have directed contact surfaces, the contact surfaces of first connecting elements and second connecting elements in the

Are essentially complementary, in particular for

Realization of a non-positive and / or positive connection in the company.

A complementary configuration of contact areas enables preferred power transmission between adjacent components, at least during operation. The contact surfaces may also be suitably discontinuous, for example having indentations and complementary shapes which are brought into engagement with one another and thereby form a non-positive or positive connection. According to a further embodiment of the present disclosure, the contact areas may be in a non-operating state

Turbo machine can be arranged at a distance.

In a non-operating state, the contact surfaces may be arranged slightly spaced apart, thus have a so-called cold gap, and are not (yet) non-positively or positively connected. In turn, in an operating state, that is to say when the turbomachine is in operation, the gap between the contact surfaces may be reduced to zero, and thereby realize the non-positive or positive connection.

According to a further embodiment of the present disclosure, the majority of the first and second components may form a non-positive and / or positive connection in the circumferential direction, separately from, by means of the connecting elements, at least in operation

Fastening points of the components on the base element. The term "separate" in this context may appear as the formation of one further, alternative frictional connection or positive connection for fastening the components on the base element can be understood.

In other words, the entirety of the connecting elements of the components attached to a base element or ring may result, for example, in a self-contained cover band, and thereby realize the frictional connection or positive connection. For example, this is achieved by filling gaps between connecting elements of first components with the suitably designed connecting elements of second components, so that the connecting elements of adjacent components are in contact with one another and are set up for power transmission.

According to a further embodiment, the fastening of the first component and / or the second component may be designed as a fastening by means of friction welding.

Friction welding may be a preferably simple connection of the first component and the second in connection with the desired or intended area of use of the components according to the disclosure

Represent component and base element. As part of the friction welding process, the component to be welded moves towards the base element or towards the base element due to the shortening effect and melts with it.

According to a further embodiment of the present disclosure, the first component and / or the second component may be designed as a moving blade. According to a further embodiment of the present disclosure, the first component and / or the second component may be formed with a length in the direction of the longitudinal extent of less than 250 mm, in particular less than 100 mm, furthermore in particular less than 10 mm. Such lengths of the components may be particularly suitable for providing a component for use in a low-pressure compressor area.

According to a further embodiment of the present disclosure, the component may be designed as a component used in a speed range of less than 40,000 revolutions per minute (rpm), in particular less than 15,000 rpm, furthermore in particular less than 10,000 rpm.

According to a further embodiment of the present disclosure, the component may be designed as a component used in a temperature range of less than 1,400 ° C., in particular less than 1,100 ° C., more particularly less than 750 ° C.

According to a further embodiment of the present disclosure, a plurality of first components may first be attached to the base element and subsequently a plurality of second components.

In particular when using a ring as a base element, a plurality of or all of the first components to be attached can thus first be attached in the circumferential direction on the surface of the ring, these being spaced apart from one another in such a way that in each case a further component can be received between two applied components. In other words, first components 1, 3, 5 etc. may thus first be fastened and the gaps between the first components may subsequently be filled with second components 2, 4, 6 etc. When attaching a second

Component between two first components at the end of the friction welding process may be the contact surfaces of the connecting element or the connecting elements of the second component Contact surfaces or connecting elements of the first two components are brought into connection. In other words, first components and second components thus have an alternating sequence on the ring as an example.

Exemplary embodiments of the present disclosure are described below with reference to the figures.

It shows:

1 is a side sectional view of a gas turbine engine in accordance with the present disclosure;

2A shows a first embodiment of a component for a gas turbine engine according to the present disclosure;

2B, C show further configurations of a component according to the present disclosure;

3A-C show details of the connection of two components in accordance with the present disclosure;

4 shows a further embodiment of a component according to the present disclosure; and

5 shows an exemplary embodiment of the method for setting a component for a turbomachine according to the present disclosure. FIG. 1 shows a gas turbine engine 10 with a flaup rotation axis 9.

The engine 10 includes an air inlet 12 and a fan 23 that generates two air streams: a core air stream A and a bypass air stream B. The gas turbine engine 10 includes a core 11 that receives the core air stream A. The core engine 11 comprises, in axial flow order, a low pressure compressor 14, a high pressure compressor 15, a

Combustion device 16, a high-pressure turbine 17, a low-pressure turbine 19 and a core thrust nozzle 20. An engine nacelle 21 surrounds the gas turbine engine 10 and defines a bypass duct 22 and a bypass thrust nozzle 18. The bypass air flow B flows through the bypass duct 22. The fan 23 is attached to the low-pressure turbine 19 via a shaft 26 and is driven by the latter. In operation, the core air flow A is accelerated and compressed by the low pressure compressor 14 and passed into the high pressure compressor 15, where further compression takes place. The compressed air discharged from the high pressure compressor 15 is conducted into the combustion device 16, where it is mixed with fuel and the mixture is burned. The resulting hot combustion products then propagate through and drive the high pressure and low pressure turbines 17, 19 before being expelled through the nozzle 20 to provide some thrust. The high-pressure compressor 15 is driven by the high-pressure turbine 17 through a connecting shaft. Fan 23 generally provides most of the thrust.

It is noted that the terms "low pressure turbine" and "low pressure compressor" as used herein can be understood to mean the turbine stage with the lowest pressure and the compressor stage with the lowest pressure (ie that they are not the fan 23) and / or the turbine and compressor stage connected by the lowest speed connecting shaft 26 in the engine (ie, that it does not include the transmission output shaft that drives the fan 23). In some publications, the "low pressure turbine" and the "low pressure compressor" referred to here may alternatively be known as the "medium pressure turbine" and "medium pressure compressor". When using such alternative nomenclature, the fan 23 can be referred to as a first compression stage or compression stage with the lowest pressure.

Other gas turbine engines to which the present disclosure may apply may have alternative configurations. For example, such engines can have an alternative number Compressors and / or turbines and / or an alternative number of connecting shafts. As another example, this is shown in Figure

I shown gas turbine engine on a split flow nozzle 20, 22, which means that the flow through the bypass duct 22 has its own nozzle, which is separate from the engine core nozzle 20 and radially outside thereof. However, this is not limitative and any aspect of the present disclosure may apply to engines in which the flow through the bypass channel 22 and the flow through the core

I I before (or upstream) a single nozzle, which can be referred to as a mixed flow nozzle, mixed or combined. One or both nozzles (whether mixed or dividing stream) can have a fixed or variable range. For example, although FIG. 1 relates to a turbofan engine, the disclosure may be applicable to any type of gas turbine engine, such as a gas turbine engine. B. in an open rotor (in which the fan stage is not surrounded by an engine nacelle) or a turboprop engine.

The geometry of the gas turbine engine 10 and components thereof is defined by a conventional axis system that has an axial direction (which is aligned with the axis of rotation 9), a radial one

Direction (in the direction from bottom to top in Figure 1) and a circumferential direction (perpendicular to the view in Figure 1). The axial (X direction), the radial (Y direction) and the circumferential direction (Z direction) are perpendicular to each other.

2A, a first embodiment of a component for a gas turbine engine according to the present disclosure is illustrated as above. 2A shows a component 30 consisting of two as an example

Components 32a, b, which are arranged on a base element 38. The base element 38 is only shown in sections and provides an essentially circumferential direction 36 for the entire component 30 completely closed disc 44. Components 32a, b have a longitudinal extent 34a, b which points radially outwards from the base element 38. The components 32a, b can, for example, be blades of a component of an engine turbine. The components 32a, b are on their inner side, thus in a first radial position

connected to the base element 38.

As an example, this connection can be formed in the context of the present disclosure by a friction weld connection 46, as a result of which each of the components 32a, b independently with the

Base element 38 or a disc 44 is connectable. In the radially outer position r ₂ , the component 30 or the components 32a, b has connecting elements 40a, b, designed as partial sections of a shroud which connect the components 32a, b to one another in the radial position r ₂ . The cover band 40a, b is only shown schematically in FIG. 2A and forms a closed force or form fit in the finished component 30 in the circumferential direction 36. For the assembly of a component 32a, b on the base element 38 in the context of a friction welding process, a component 32a, b in the direction of the

Base element 38 moves what is indicated by arrow 48 as a so-called shortening.

The representation in FIG. 2A is only qualitative, since, in particular within the scope of the present disclosure, comparatively long components 32a, b can be used, so that in particular the radial positions h and r ₂ may be further apart than the representation in FIG. 2A. Connecting elements 40a, b are by means of contact point 41 or

Contact surface 41 in contact with each other. The surfaces of the connecting elements 40a, b in the contact point are complementary formed so that the best possible contact or transition between two connecting elements 40a, b is realized.

With further reference to FIGS. 2B, C, further configurations of a component according to the present disclosure are illustrated.

FIGS. 2B, C furthermore show various assembly configurations of components, for example configured as rotor blades on a disk for an engine turbine.

In FIG. 2B, components 32a, b are attached to an independent base element 38a, b. This can be done via a friction welding connection, or it can also be realized by further, conventional connection methods. As an example, the components 32a, b are arranged next to one another and subsequently attached to the disk 44 using a friction weld connection 46. For example, a friction weld connection 46 can first be formed for component 32a and then component 32b can be attached by means of a friction weld connection between base element 38b and washer 44.

In Fig. 2C the assembly of a so-called pair of blades on disc 44 is shown. Components 32a, b are first attached to a common base element 38 in accordance with the method described in FIG. 2A. A plurality of pairs of moving blades can thus be provided, which can be attached to the disk 44 in a subsequent step, for example using a friction welding connection 46. As an alternative to the friction weld connection 46, however, conventional further connection methods are also conceivable. 3A to C, detailed representations of the connection of two components according to the present disclosure are presented. 3A to C show possible configurations of contact surfaces 41 of adjacent connecting elements 40a, b and thus of the adjacent components 32a, b, which are not shown in detail in FIGS. 3A to C.

FIGS. 3A, B each show the circumferential direction 36 and the longitudinal directions 34a, b of the components 32a, b, only connecting elements 40a, b being shown of components 32a, b. The connecting element 40a is arranged schematically in the radial position r ₂ and can therefore be regarded as a component already fastened on the base element 38. Component 32b is initially shown in a radial position r ₂ ·, which is offset radially outwards by the amount of shortening 48. After the friction welding step has been carried out, connecting element 40b approaches radial position r ₂ or also assumes the same as connecting element 40a. The thickness d of the connecting element 40b can be greater or less than the amount of shortening 48. In the event that the thickness d of the connecting element 40b is greater than the amount of shortening 48, the connecting elements 40a, b can be at least partially in contact before the friction welding process is carried out. This may result in a preferred assembly, since the partially overlapping or connected connecting elements 40a, b may provide a certain stability through power transmission before the friction welding step is carried out. After performing the friction welding joining step of

Component 32b, the connecting elements 40a, b are arranged essentially at the same radial position r ₂ . 3B shows a different type of configuration of the contact surfaces 41 of adjacent components. 3B shows an exemplary 45 ° beveled contact surface, the mutually aligned contact surfaces still being complementary. A discontinuous transition 42, for example a kink or jump in the contact surface 41, supports a positive connection of adjacent connecting elements 40a, b. A beveled configuration of the contact surface as shown in FIG. 3B provides a simple positioning of adjacent components 32a, b for performing a friction welding step. The radial offset r ₂ · before the friction welding step is carried out together with the beveled contact surface makes it possible to position one another with a maximum degree of freedom, with the beveled contact surface resulting in an essentially automatic final positioning of the component to be added when carrying out the friction welding step. This effect can be seen in particular in FIG. 3C.

3C shows four components 32a, b by way of example after their fastening, these being arranged alternately, thus a first component alternating with a second component. Of the components 32a, b, only the connecting elements 40a, b are shown, while the remaining elements of the components 32a, b are only indicated. The connecting elements 40ab are in contact with one another via contact surfaces 41. 3C shows in particular the beveled configuration of the contact surfaces. If a first plurality of first components 32a are first attached to the base element 38, these components are spaced apart or have a gap for introducing the second components 32b. According to the effect shown in FIG. 3B in the context of shortening, components 32b, introduced into the gap between the first components 32a, are initially arranged in a radial position r ₂ · before the friction welding step is carried out. When performing the friction welding step, using the shortening 48, fill the second components 32b successively fill the gap between the first components 32a by reducing the radial position from r ₂ - to r ₂ and thus successively form the fully closed positive or positive connection in the circumferential direction, in particular when all second components 32b are fastened on the base element. In this case, a cover band, which is made up of individual elements but is now self-contained, is formed, which provides the non-positive or positive connection in the circumferential direction. As can be seen in FIG. 3C, the introduced components 32b brace with the first components 32a and thereby form the shroud which is made up of individual elements.

4, another embodiment of a component according to the present disclosure is shown.

FIG. 4 shows an embodiment of two components 32a, b fastened on the base element 38 or the disk 44 with connecting elements 40a, b, which are not in the radial end position r ₂ , but alternatively or additionally in the radial position r _z between adjacent components 32a, b are arranged. The statements made above with regard to the contact surfaces 41 of the connecting elements 40a, b arranged with respect to one another apply unchanged. 3B, C, in particular, a plurality of connecting elements 40a, b between the radial positions

and r ₂ are provided. Adjacent components may have connecting elements in different radial positions. In other words, connecting _elements to the adjacent components, not shown in FIG. 4, can be formed in the same radial position r _z or different radial position r _z1 , r _z2 .

With such a flexible and largely free arrangement of connecting elements, the vibration behavior of the Optimize overall system of component 30 with a view to reducing vibrations.

5, an exemplary embodiment of a method 50 for operating a component in a turbomachine according to the present disclosure is illustrated.

The method 50 for operating a turbomachine, in particular for an aircraft engine, has a component of the turbomachine, produced by the steps of providing 52 at least one first component 32a with a first connecting element 40a, providing 54 at least one second component 32b with a second connecting element 40b, Provision 56 of a base element 38, fastening 58 of at least one of the at least one first component 32a on the base element 38, fastening 60 of one of the at least one second component 32b on the base element 38, the second component 32b next to the first component 32b or between two first components 32a arranged. During the operation 61 of the turbomachine, the respective connecting elements 40a, b of the first component 32a and the second component 32b are non-positively and / or positively connected in a respective operating state 61 of the turbomachine.

It is understood that the invention is not limited to the above-described embodiments and various modifications and

Improvements can be made without deviating from the concepts described here. Any of the features may be used separately or in combination with any other features, unless they are mutually exclusive, and the disclosure extends to and includes all combinations and subcombinations of one or more features described herein. Finally, it is pointed out that terms such as "showing" or "comprehensive" do not exclude other elements or steps and that "a" or "one" does not exclude a plural. Elements described in connection with various embodiments can be combined. Reference signs in the claims are not to be interpreted as a restriction.

REFERENCE SIGN LIST

9 main axis of rotation

10 engine

11 core

12 air intake

14 low pressure compressors

15 high pressure compressors

16 combustion device

17 high pressure turbine

18 Bypass thrust nozzle

19 low pressure turbine

20 core thrust nozzle

21 engine nacelle

22 bypass channel

23 fan

A core airflow

B bypass air flow

26 connecting shaft

30 component

32a, b first, second component

34a, b longitudinal extent

36 circumferential direction

38, 38a, b base element

40a, b connecting element / cover band

d Thick connector

r radial position

41 contact point / contact surface

42 discontinuous transition / jump / kink

44 disc

46 Friction welding connection

48 shortening

50 Procedure for operating a turbomachine

52 Deploy a first component

54 Provision of a second component

56 Provision of a base element

58 Attaching the first component to the base element 60 Attaching the second component to the base element Operation of the turbomachine, operating state of the turbomachine

Method of manufacturing a component

Claims

EXPECTATIONS

Method (50) for operating a turbomachine, in particular for an aircraft engine, the turbomachine having a component, produced by the steps:

Providing (52) at least one first component (32a) with a first connecting element (40a),

Providing (54) at least one second component (32b) with a second connecting element (40b),

- Providing (56) a base element (38),

Fixing (58) at least one of the at least one first component (32a) to the base element (38),

- fastening (60) one of the at least one second component (32b) to the base element (38),

the one second component (32b) being fastened next to the one first component (32b) or arranged between two first components (32a), and

wherein during operation (62) of the turbomachine, connecting elements (40a, b) of the first component (32a) and the second component (32b) are connected in a non-positive and / or positive manner in a respective operating state (62) of the turbomachine.

Method according to the preceding claim, wherein the first connecting elements (40a) and the second connecting elements (40b) have respective mutually directed contact surfaces (41); and wherein the contact surfaces (41) of the first connecting elements (40a) and second connecting elements (40b) are essentially complementary.

Method according to at least one of the preceding claims, wherein the respective contact surfaces (41) of the first and second Connecting elements (40a, b) are arranged spaced apart from one another in a non-operating state of the turbomachine.

4. The method according to the preceding claim, wherein the plurality of first and second components (32a, b) by means of

At least during operation, connecting elements (40a, b) form a non-positive and / or positive connection in the circumferential direction, separately from fastening points of the components on the base element (38).

5. The method according to at least one of the preceding claims, wherein the fastening step is designed as a fastening by means of friction welding. 6. The method according to at least one of the preceding claims, wherein the first component (32a) and / or the second component (32b) is designed as a moving blade.

7. The method according to at least one of the preceding claims, wherein the first component (32a) and / or the second component

(32b) is formed with a length in the direction of the longitudinal extent of less than 250mm, in particular less than 100mm, furthermore in particular less than 10mm. 8. The method according to at least one of the preceding

Claims, wherein the component (30) is designed as a component, used in a speed range of less than 40,000 rpm, in particular less than 15,000 rpm, furthermore in particular less than 10,000 rpm.

9. The method according to at least one of the preceding claims, wherein the component (30) is designed as a component used in a temperature range of less than 1,400 ° C, in particular less than 1,100 ° C, more particularly less than 750 ° C.

10. A method (62) for producing a component for a turbomachine, in particular for an aircraft engine, comprising the steps:

- Providing (56) a base element (38),

- fixing (58) at least one of the at least one first component (32a) to the base element (38),

the one second component (32b) being fastened adjacent to the one first component (32a) or arranged between two first components (32a), and

wherein connecting elements (40a, b) of the first component (32a) and the second component (32b) are non-positively and / or positively connected after fastening the at least one first component (32a) and the second component (32b).

1 1. Method according to the preceding claim, wherein first a plurality of first components (32a) are attached to the base element (38) and subsequently a plurality of second components (32b) are attached.

12. Component (30) for a gas turbine engine (10) for an aircraft, comprising

- a first component (32a) with a first connecting element (40a), - A second component (32b) with a second connecting element (40b), and

- a base element (38),

wherein the first component (32a) and the second component (32b) are fastened adjacent to the base element (38);

wherein connecting elements (40a, b) of the first component (32a) and the second component (32b) are non-positively and / or positively connected, or

wherein connecting elements (40a, b) of the first component (32a) and the second component (32b) in an operating state of

Turbomachine are non-positively and / or positively connected.

13. Gas turbine engine (10) for an aircraft, comprising at least one component (30) according to claim 12, produced according to a method (62) according to at least one of claims 1 to 1 1.