Interlocking assembly

Abstract

The invention relates to a clamping assembly, wherein the clamping assembly comprises a first component (10) with a first flange (11) with first radial webs (12) and first recesses (13) between each two circumferentially adjacent first webs; a second component (20) with a second flange (21) with second radial webs (22) and second recesses (23) between each two circumferentially adjacent second webs; and a third component with a third flange; the first and second components are designed such that, in an initial assembly position, the first and second components have a first angular position relative to one another about an assembly and / or longitudinal axis of the clamping assembly, and by axial displacement of the first and second components relative to one another parallel to this axis, the second webs can be guided through the first recesses and the first webs can be guided through the second recesses in the axial direction;When the clamping assembly is assembled, the first and second components have a second angular position relative to one another around the axis of the clamping assembly, in which the second webs at least partially overlap the first webs in the circumferential direction; and the second webs are arranged in the axial direction between the first webs and the third flange and are clamped by a tie rod device (100) of the rotor. The invention also relates to a gas turbine assembly and methods for (dis)assembly.

Description

[0001] The present invention relates to a clamping composite assembly, in particular a clamping composite rotor and / or for a gas turbine, as well as a gas turbine assembly, in particular a turbine or compressor assembly and / or an aircraft engine, with the clamping composite assembly, in particular the clamping composite rotor, and a method for assembling or disassembling the clamping composite assembly or the clamping composite rotor.

[0002] Rotors, in particular, can be designed as a clamped assembly or in a tie-rod construction. In this case, (rotor) components are axially clamped one behind the other using one or more tie rods. Due to the axial pressing force of the tie rod(s), the components of such a clamped assembly, especially a clamped rotor, form a closed unit geometrically and in terms of force flow, and torque is transmitted via frictional engagement.

[0003] Due to the often high axial forces, a design that ensures an adapted force flow within the components and features favorable interfaces is advantageous. Steep cones and / or radial jumps between components are advantageously avoided, or cone angles and radial jumps are reduced. This competes with axially and / or radially limited installation space, making it sometimes impossible to achieve a force flow adapted to the tie rod principle in the design.

[0004] One object of an embodiment of the present invention is to improve a clamped composite assembly and / or its assembly and / or disassembly. This object is achieved by a clamped composite assembly having the features of claim 1 and a method having the features of claims 12 and 14, respectively. Claim 11 protects a gas turbine assembly with a clamped composite assembly described herein. The subclaims relate to advantageous developments.

[0005] According to one embodiment of the present invention, a clamping composite assembly, in a particularly preferred development a clamping composite rotor, has a component with a flange with, preferably at least four, in particular at least 10, radial webs and recesses between each two circumferentially adjacent webs, which is / are referred to here without restriction of generality as the first component or first flange or first webs or recesses, wherein the first component in turn can consist of one or more individual parts.

[0006] According to one embodiment of the present invention, the clamping composite assembly has a further component with a flange with, preferably at least four, in particular at least 10, radial webs and recesses between each two circumferentially adjacent webs, which is / are referred to here without restriction of generality as a second component or second flange or second webs or recesses, wherein the second component in turn can consist of one or more individual parts.

[0007] According to one embodiment of the present invention, the clamping composite assembly has a further component with a flange, which is referred to here without restriction of generality as a third component or third flange, wherein the third component in turn can consist of one or more individual parts.

[0008] According to one embodiment of the present invention, the first and second components are designed such that, in an initial assembly position, the first and second components have a first angular position relative to one another about an assembly and / or longitudinal axis of the clamping assembly, in a further development a rotational axis of the rotor, and by an axial displacement of the first and second components relative to one another parallel to this axis, in particular an axial displacement of the first component relative to the stationary second component or of the second component relative to the stationary first component or an axial displacement of both the first and the second component, the second webs can be guided through the first recesses and, preferably at the same time or at least partly simultaneously, the first webs can be guided through the second recesses in the axial direction.

[0009] According to one embodiment of the present invention, when the clamping assembly is mounted, the first and second components have a second angular position (rotated relative to the first angular position, preferably by at least 1°, particularly preferably at least 2°, and / or at most 30°, particularly preferably at most 15°, and / or by at least 90° / (maximum number of webs evenly distributed over the circumference) and / or by at most 180° / (maximum number of webs evenly distributed over the circumference)) relative to one another about the mounting and / or longitudinal axis of the clamping assembly, in a further development the axis of rotation of the rotor, in which second angular position the second webs engage behind the first webs in the circumferential direction.completely or partially overlap, and the second webs are arranged in the axial direction between the first webs and the third flange and are clamped by a tie rod device of the rotor (axially, preferably against each other), in a further development the first webs, second webs and the third flange are pressed against each other in this order in the axial direction by means of the tie rod device, contacting each other preferably under corresponding contact force.

[0010] In one embodiment, the overall length can be advantageously reduced by clamping the first component, in a further development a blade stage of a gas turbine, via its first flange and the frictional connection continues to be achieved by means of the tie rod force, so that in one embodiment no additional local screw connection is necessary.

[0011] According to one embodiment of the present invention, the first and second flanges or their first and second webs or recesses form a bayonet geometry or bayonet kinematics or bayonet construction.

[0012] This also enables or simplifies assembly in particular if, in one embodiment, a maximum outer diameter of the first flange is greater than a minimum inner diameter of a constriction, in one embodiment of a section, in particular a (radial) projection, of the second component that projects maximally radially inwards in a further development, and the first flange is or will be arranged between the constriction and the second flange at a distance from the constriction in the axial direction (with the clamping assembly assembled or the clamping assembly assembled): the first component or its first flange can thus be inserted into the first angular position from the side facing away from the constriction and, after this insertion, can be rotated into the second angular position and then clamped against the second flange by the tie rod device.

[0013] In one embodiment, an axial or axial direction mentioned here is parallel to a mounting and / or longitudinal axis of the clamping assembly, in particular the rotational axis of the rotor, wherein this axis is parallel to a (main) clamping direction of the tie rod device in one embodiment. In one embodiment, a circumferential direction mentioned here is a circumferential or rotational direction around this mounting or longitudinal or rotational axis, and a radial or radial direction mentioned here is perpendicular to the axis and circumferential direction, preferably pointing away from or emanating from the axis. Accordingly, in one embodiment, the mounting axis is an axis along which the webs of the first and second flange can be passed through in bayonet kinematics and about which they can then be rotated in bayonet kinematics or along which they are passed through and about which they are then rotated.

[0014] In one embodiment, the tie rod device has one or more, preferably tubular, tie rods. Additionally or alternatively, in one embodiment, the tie rod device extends through the first flange, preferably the first component, and / or the second flange, preferably the second component, and / or the third flange, preferably the third component, in the axial direction. Additionally or alternatively, in one embodiment, the tie rod device is supported in the axial direction directly or indirectly on a side of the first component facing away from the third component and / or on a side of the third component facing away from the first component. As a result, in each case, in particular in combination of two or more of these features, a particularly advantageous, in particular reliable and / or space-saving and / or easy (dis)assembly and / or force flow-optimized design can be realized.

[0015] In one embodiment, the first recesses are through-openings (in the axial direction) and / or open radially (towards) the outside. Additionally or alternatively, in one embodiment, the second recesses are through-openings (in the axial direction) and / or open radially (towards) the inside. Additionally or alternatively, in one embodiment, the second component overlaps the first webs in the axial direction, preferably radially outward. As a result, in each case, in particular in combination of two or more of these features, a particularly advantageous, in particular reliable and / or space-saving and / or easy (to dis)assemble and / or force-flow-optimized design can be realized.

[0016] In one embodiment, the clamping assembly comprises axial webs that engage in the first and / or second recesses (when the clamping assembly is mounted or during assembly of the clamping assembly), preferably extending through the first and / or second recesses. This allows for advantageous anti-rotation protection.

[0017] In a further development, two or more of these axial webs are connected to one another or are formed integrally. Additionally or alternatively, in a further development, two or more of the axial webs are arranged on the third component, in one embodiment connected to it, or are formed integrally. Additionally or alternatively, in a further development, two or more of the axial webs are arranged on an additional component, in one embodiment a separate ring, in one embodiment connected to it, or are formed integrally. This makes it possible to realize a particularly advantageous, in particular reliable and / or space-saving and / or easy (dis)assembly and / or force flow-optimized anti-twist device.

[0018] In an alternative embodiment, the axial webs on the third component can also be designed as separate components (rather than integral). For this purpose, holes can be drilled into the third component at the location of the axial web. In this case, specially shaped stud bolts (pre-screwed on the side facing away from the flange) mounted through the hole can provide the anti-rotation feature.

[0019] In one embodiment, the clamping assembly has a play-free radial fit between the second flange, preferably its second webs, and the first component. In a further development, the first component has one or more corresponding fitting or contact surfaces against which the second flange, preferably its second webs, rest to form a play-free radial fit or (in each case) a snug fit. In one embodiment, the first recesses protrude radially beyond this fitting or contact surface(s), so that the passage of the second webs is facilitated and the play-free radial fit is only formed by rotating from the first to the second angular position.

[0020] Additionally or particularly advantageously (to avoid double fits), the clamping assembly alternatively has a clearance-free radial fit between the first flange, preferably its first webs, and the second component. In a further development, the second component has one or more corresponding fitting or contact surfaces against which the first flange, preferably its first webs, rest to form a clearance-free radial fit or (in each case) a snug fit. In one embodiment, the second recesses protrude radially beyond this fitting or contact surface(s), so that the passage of the first webs is facilitated and the clearance-free radial fit is only formed by rotating from the first into the second angular position.

[0021] By means of a play-free radial fit between a flange of one of the first and second components and the other of the first and second components, a particularly advantageous, in particular reliable and / or space-saving and / or (dis)assembly-friendly and / or force-flow-optimized construction can be realized.

[0022] The fit fits do not have to be cut free, so that the recesses protrude radially beyond the fitting or contact surface(s). In particular, the first component can also have a cylindrical and / or annular fitting surface with which the second flange, preferably its second webs, form a play-free radial fit or (in each case) a fit, and / or the second component can also have a cylindrical and / or annular fitting surface with which the first flange, preferably its first webs, form a play-free radial fit or (in each case) a fit. In particular, it can be advantageous for this purpose to appropriately temperature-control these components for assembly in order to facilitate or enable an assembly gap for the webs to pass through the recesses.

[0023] In one embodiment, the clamping composite assembly comprises a fourth component with a fourth radial flange, which is arranged in the axial direction on a side of the third flange facing away from the first and / or second flange, wherein the first webs, second webs, the third flange, and the fourth flange are clamped by the tie rod device. This advantageously allows longer and / or more complex clamping composite assemblies, in particular clamping composite rotors with multiple disks, preferably rotor blade disks, to be realized in a particularly assembly- and / or production-friendly manner.

[0024] In one embodiment, the third component secures the second component in a radially positive-locking manner when the clamping assembly is mounted. In a further development, at least one outer axial projection is arranged on the third flange, which radially surrounds the second flange. This allows for a particularly advantageous, in particular reliable and / or space-saving and / or easy-to-disassemble design.

[0025] In one embodiment, the first component is an end component and / or a cone. Additionally or alternatively, in one embodiment, the second component is a rotor disk and / or is designed to support rotor blades of the gas turbine. In one development, it has corresponding interfaces for this purpose, for example grooves for fastening the rotor blades or the like, and / or is or will be equipped with rotor blades which are formed integrally with the second component or are or can be fastened to it in a material or form-fitting manner. Additionally or alternatively, in one embodiment, the third component is a rotor disk and / or is designed to support rotor blades of the gas turbine. In one development, it has corresponding interfaces for this purpose, for example grooves for fastening the rotor blades or the like, and / or is or will be equipped with rotor blades which are formed integrally with the second component or are or can be fastened to it in a material or form-fitting manner.is equipped with rotor blades that are formed integrally with the third component or are or can be fastened to it in a material or form-fitting manner. Additionally or alternatively, in one embodiment, the fourth component is a rotor disk and / or is designed to carry rotor blades of the gas turbine; in a further development, it has corresponding interfaces for this purpose, for example grooves for fastening the rotor blades or the like, and / or is or will be equipped with rotor blades that are formed integrally with the fourth component or are or can be fastened to it in a material or form-fitting manner. The present invention is particularly advantageous for such components, in particular due to the assembly and / or dynamic and / or thermal operating conditions and / or spatial boundary conditions.

[0026] The present invention is particularly suitable for gas turbines; accordingly, one embodiment of the present invention relates to a gas turbine assembly, in a further development a turbine or compressor assembly of a gas turbine assembly and / or a gas turbine assembly, in a further development turbine or compressor assembly, of an aircraft engine, with a clamping composite assembly described here, preferably a clamping composite rotor described here.

[0027] According to one embodiment of the present invention, a method for assembling a clamping composite assembly described here, in a further development of a clamping composite rotor described here, comprises the steps: Arranging the first and second components in the initial assembly position; displacing the first and second components relative to one another parallel to the assembly and / or longitudinal axis of the clamping assembly, in particular the rotational axis of the rotor, so that the second webs are guided through the first recesses and the first webs through the second recesses in the axial direction; rotating the first and second components relative to one another about this axis into the second angular position; arranging the third component, preferably after rotating; and clamping the second webs in the axial direction between the first webs and the third flange by means of the tie rod device.

[0028] In one embodiment, the fourth component is arranged and then the first webs, second webs, the third flange and the fourth flange are clamped by the tie rod device.

[0029] According to one embodiment of the present invention, a method for disassembling a clamping composite assembly described here, in a further development of a clamping composite rotor described here, comprises the steps: Releasing a tensioning of the second webs in the axial direction between the first webs and the third flange caused by the tie rod device; removing the third component, preferably before the subsequently mentioned twisting; twisting the first and second components relative to one another about the assembly and / or longitudinal axis of the clamping assembly into the first angular position; displacing the first and second components relative to one another parallel to this axis, so that the second webs are guided through the first recesses and the first webs are guided through the second recesses in the axial direction; and; removing the first and second components from one another.

[0030] In one embodiment, the second recesses are wider in the circumferential direction than the first webs and / or first recesses. Additionally or alternatively, in one embodiment, the second webs are narrower in the circumferential direction than the first recesses.

[0031] As a result, in particular in combination of two or more of these features, a particularly advantageous, in particular reliable and / or space-saving and / or (dis)assembly-friendly and / or force-flow-optimized construction can be realized.

[0032] Further advantageous developments of the present invention will become apparent from the dependent claims and the following description of preferred embodiments. The drawing shows, partially schematically: Fig. 1 shows a step of assembling a clamped composite rotor according to an embodiment of the present invention in an axial section; Fig. 2 shows a part of a second component of the rotor in a sectional perspective view; Fig. 3 shows a part of a first component of the rotor in a sectional perspective view; Fig. 4 shows a further step of the assembly in Fig. 1 corresponding representation; Fig. 5 the first and second component in Fig. 2, 3 corresponding representation in a second angular position; Fig. 6 a further step of the assembly in Fig. 1 , 4 corresponding representation; Fig. 7 a part of a third component of the rotor in a sectional perspective view; Fig. 8 the assembled clamping composite rotor in Fig. 1 , 4 , 6corresponding representation; Fig. 9 the first, second and third components in a sectional perspective view; and Fig. 10 the first, second and third components in another sectional perspective view.

[0033] Fig. 1 shows a step in the assembly of a clamped composite rotor according to an embodiment of the present invention in an axial section. The dot-dashed line indicates a Fig. 1 horizontal mounting or longitudinal or rotation axis A of the clamping compound rotor.

[0034] In Fig. 1 a first component in the form of an (end) cone 10 with a first flange 11 with first radial webs 12 and first recesses 13 between each two circumferentially adjacent first webs 12 and a second component in the form of a rotor blade disk 20 with a second flange 21 with second radial webs 22 and second recesses 23 between each two circumferentially adjacent second webs 22 are arranged in an assembly starting position.

[0035] As in Fig. 1 As indicated by an assembly or left arrow, the two components 10, 20 are mounted in the axial direction (horizontally in Fig. 1 ). The second webs 22 are guided through the first recesses 13 and the first webs 12 through the second recesses 23 in the axial direction.

[0036] Subsequently, the first and second components 10, 20 are rotated relative to each other around the assembly or longitudinal or rotational axis of the clamping compound rotor into the second angular position as shown in Fig. 4, 5 illustrated. The second webs 22 slide on fitting (seating) surfaces 15 of the cone 10 (cf. Fig. 3 ) and form a clearance-free radial fit with them. In this position, the first flange 11 is arranged in the axial direction between a constriction 24 of the second component in the form of a smallest inner diameter and the second flange and is spaced from this constriction, wherein in Fig. 1 It is illustrated that a maximum outer diameter D 1 of the first flange 11 is larger than a minimum inner diameter D 2 of the constriction.

[0037] Subsequently, a third component in the form of another rotor blade disk 30 with a third flange 31 is arranged by being arranged in the axial direction (horizontally in Fig. 6 ) is pushed onto the components 10, 20. Axial webs 37, which can be formed integrally with the third component 30, penetrate the first and second recesses 13, 23 and thus provide an anti-rotation lock. In addition, an outer axial projection 34, which is arranged on the third flange 31, surrounds the second flange 21 radially outward. Accordingly, the third component 30 secures the second component 20 radially in a form-fitting manner. This is shown in Fig. 6-10 illustrated.

[0038] Subsequently, further components, in particular a fourth component in the form of a further rotor blade disk 40 with a fourth flange 41, can be arranged accordingly and then clamped axially with one another to form the clamped composite rotor using a tie rod device 100, as in Fig. 8 illustrated. 25 (cf. Fig. 1 ), 35 (cf. Fig. 6 ) or 45 (cf. Fig. 8 ) interfaces for fastening rotor blades 26, 36 and 46, respectively, which are Fig. 8 are indicated by dashed lines.

[0039] Disassembly is carried out in the reverse order.

[0040] In the present disclosure, "has an X" generally does not imply an exhaustive list, but is a shortened form of "has at least one X" and also includes "has two or more X" and "has Y in addition to X." Although exemplary embodiments have been explained in the foregoing description, it should be noted that numerous modifications are possible.

[0041] In particular, the axial projections 37 can be arranged on a separate ring (not shown) instead of being integral with the third component 30, or they can be omitted. Alternatively, the projections can also be designed as bolts that penetrate the third component.

[0042] Furthermore, it should be noted that the exemplary embodiments are merely examples and are not intended to limit the scope of protection, applications, or structure in any way. Rather, the preceding description provides the skilled person with a guide for implementing at least one exemplary embodiment. Various modifications, particularly with regard to the function and arrangement of the described components, may be made without departing from the scope of protection as defined by the claims and equivalent combinations of features. List of reference symbols

[0043] 10First component 11First flange 12First web 13First recess 15Fitting surface 20Second component 21Second flange 22Second web 23Second recess 24Constriction 25Blade attachment interface 26Blade 30Third component 31Third flange 34Axial projection 35Blade attachment interface 36Blade 37Axial web 40Fourth component 41Fourth flange 45Blade attachment interface 46Blade 100Tie rod device ARotation axis D 1 ( / 2)(half) maximum outside diameter of the first flange D 2 ( / 2)(half) minimum inside diameter of a constriction of the second component

Claims

1. A clamping assembly, in particular for a rotor and / or for a gas turbine, wherein the clamping assembly comprises a first component (10) with a first flange (11) with first radial webs (12) and first recesses (13) between each two circumferentially adjacent first webs; a second component (20) with a second flange (21) with second radial webs (22) and second recesses (23) between each two circumferentially adjacent second webs; and a third component with a third flange;wherein the first and second components are designed such that, in an initial assembly position, the first and second components have a first angular position relative to one another about an assembly and / or longitudinal axis of the clamping assembly, in particular the rotational axis (A) of the rotor, and by axial displacement of the first and second components relative to one another parallel to this axis, the second webs can be guided through the first recesses and the first webs can be guided through the second recesses in the axial direction; wherein, when the clamping assembly assembly is assembled, the first and second components have a second angular position relative to one another about the assembly and / or longitudinal axis of the clamping assembly, in particular the rotational axis of the rotor, in which second angular position the second webs at least partially cover the first webs in the circumferential direction; and the second webs are arranged in the axial direction between the first webs and the third flange and are clamped by a tie rod device (100) of the rotor.

2. Clamping composite assembly according to claim 1, characterized in that the tie rod device passes through the first, second and / or third flange in the axial direction and / or is supported in the axial direction directly or indirectly on a side of the first component facing away from the third component and / or on a side of the third component facing away from the first component.

3. Clamping composite assembly according to one of the preceding claims, characterized in that the first recesses are open radially outwards and the second recesses are open radially inwards and / or the second component overlaps the first webs in the axial direction.

4. Clamping composite assembly according to one of the preceding claims, characterized in thata maximum outer diameter of the first flange is greater than a minimum inner diameter of a constriction of the second component, wherein the first flange is arranged in the axial direction between the constriction and the second flange and / or is spaced from the constriction.

5. Clamping composite assembly according to one of the preceding claims, characterized by axial webs (37) which engage in the first and / or second recesses.

6. Clamping composite assembly according to the preceding claim, characterized in that at least two of the axial webs are connected to one another or are integrally formed and / or arranged on the third or an additional component.

7. Clamping composite assembly according to one of the preceding claims, characterized by a clearance-free radial fit between the second flange and the first component and / or between the first flange and the second component.

8. Clamping composite assembly according to one of the preceding claims, characterized by a fourth component (40) with a fourth radial flange (41) which is arranged in the axial direction on a side of the third flange facing away from the first and / or second flange, wherein the first webs, second webs, the third flange and the fourth flange are braced by the tie rod device.

9. Clamping composite assembly according to one of the preceding claims, characterized in that the third component secures the second component in a radially positive-locking manner, in particular at least one outer axial projection (34) is arranged on the third flange, which projection surrounds the second flange radially on the outside.

10. Clamping composite assembly according to one of the preceding claims, characterized in that the first component is an end component and / or cone and / or the second and / or third and / or fourth component is a rotor disk and / or is designed to support rotor blades (26, 36, 46) of the gas turbine.

11. Gas turbine assembly, in particular turbine or compressor assembly and / or an aircraft engine, with a clamping composite assembly according to one of the preceding claims.

12. A method for assembling a clamping assembly according to one of the preceding claims, the method comprising the steps of: - arranging the first and second components in the assembly starting position; - displacing the first and second components relative to one another parallel to the assembly and / or longitudinal axis of the clamping assembly, so that the second webs are guided through the first recesses and the first webs through the second recesses in the axial direction; - rotating the first and second components relative to one another about this axis into the second angular position; - arranging the third component; and - bracing the second webs in the axial direction between the first webs and the third flange by means of the tension rod device.

13. Method according to the preceding claim, characterized in that the fourth component is arranged and then the first webs, second webs, the third flange and the fourth flange are clamped by the tension rod device.

14. A method for disassembling a clamping assembly according to one of the preceding claims, the method comprising the steps of: - releasing a tension of the second webs in the axial direction between the first webs and the third flange by the tie rod device; - removing the third component; - rotating the first and second components relative to one another about the assembly and / or longitudinal axis of the clamping assembly into the first angular position; - displacing the first and second components relative to one another parallel to this axis, so that the second webs are guided through the first recesses and the first webs are guided through the second recesses in the axial direction; and; - removing the first and second components from one another.

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