Turbine or compressor stage assembly

Abstract

The present invention relates to an assembly comprising a first component (110; 210; 310) and a second component (120; 220; 320; 420) for arrangement in the same turbine or compressor stage of a turbomachine, in particular an aircraft engine, wherein the first component has a first surface (111) and the second component has a second surface (121; 221; 321) opposite the first surface, wherein the first surface has a first contact area (112) for contacting the second surface and the second surface has a first contact contour (122; 222; 322) opposite this first contact area for contacting this first contact area, which has a recess (227; 327; 427; 428) or a convex edge (123; 223; 323) or a convex tip (124). The invention also relates to an assembly arrangement, a turbine and compressor stage and a turbomachine.

Description

[0001] The present invention relates to an assembly for arrangement in a turbine or compressor stage of a turbomachine, a turbine or compressor stage with the assembly, and a turbomachine, in particular an aircraft engine gas turbine, with the turbine or compressor stage.

[0002] Turbine or compressor stage components or assemblies are subjected to vibrations during operation, for example by aerodynamic and / or structural forces, which put them under stress. It is known from operational practice to reduce such vibrations through energy dissipation and / or energy absorption.

[0003] One object of an embodiment of the present invention is to improve a turbine or compressor stage of a turbomachine.

[0004] This problem is solved by an assembly with the features of claim 1. Claims 8, 9, 11, and 12 protect an assembly arrangement or turbine or compressor stage for a turbomachine, in particular an aircraft engine, with at least one assembly (arrangement) described herein, or a turbomachine, in particular an aircraft engine gas turbine, with at least one such stage. The dependent claims relate to advantageous embodiments.

[0005] According to one embodiment of the present invention, an assembly comprises at least two components, which, without limitation of generality, are referred to as the first and second components.

[0006] The assembly is arranged in one embodiment in the same turbine or compressor stage, in a further development low-pressure turbine stage, a turbomachine, in a further development of an aircraft engine, preferably an aircraft engine gas turbine, or is provided or set up or used for this purpose.

[0007] The present invention makes it possible to advantageously reduce undesirable vibrations in one embodiment, in particular speed-synchronous and / or speed-asynchronous externally excited vibrations and / or self-excited vibrations, such as those that occur in turbine and especially compressor and particularly low-pressure turbine stages, especially in aircraft engine (gas turbine) stages, due to the aerodynamic, mechanical and thermal loads and design boundary conditions occurring during operation.

[0008] According to one embodiment of the present invention, the first component has a first surface, and the second component has a second surface opposite this first surface, preferably viewed in an axial and / or circumferential and / or radial direction. In one embodiment, an axial direction is parallel to a rotational or (main) machine axis of the turbine or compressor stage or turbomachine, a circumferential direction is a circumferential or rotational direction about this rotational or (main) machine axis, and a radial direction is perpendicular to these axial and circumferential directions, preferably away from the rotational or (main) machine axis. Vibration amplitudes and / or propagation can be particularly advantageously reduced by surfaces that are opposite each other viewed in at least one of the aforementioned directions and are in contact or come into contact as a result of vibration.

[0009] According to one embodiment of the present invention, the first surface has a first contact area and the second surface has a first contact contour opposite this first contact area, which contact each other at least temporarily or are provided or arranged for this purpose.

[0010] According to one embodiment of the present invention, the first contact contour has - a convex, especially funnel-shaped or spherical, depression in a further training; or - a convex or protruding edge that has been rounded off in a further training; or - a convex or protruding tip, rounded or truncated in further training.

[0011] Such contact contours can advantageously influence the vibration propagation and / or amplitudes of the two components, thereby advantageously transferring (vibrational) energy into other modes and thus advantageously reducing vibrations in certain modes that are particularly pronounced without such contact contours.

[0012] In one version, the first contact area for contacting the first contact contour is free of raised areas and depressions.

[0013] One combination claimed to be particularly advantageous is a first contact area free of protrusions and depressions, which contacts an edge of the depression of the first contact contour over a surface area or forms a surface contact point with it, or is provided or set up for this purpose.

[0014] Another combination claimed to be particularly advantageous is a first contact area free of protrusions and depressions, which contacts the edge of the first contact contour (idealized or seen from a rigid body mechanics perspective) in a line-like manner or forms a line contact point with it, or is provided or set up for this purpose.

[0015] Another combination claimed to be particularly advantageous is a first contact area free of protrusions and depressions, which contacts the tip of the first contact contour (idealized or from a rigid body mechanics perspective) at a point or forms a point contact point with it, or is provided or set up for this purpose.

[0016] In one embodiment, the first contact area for contacting the first contact contour has a depression, which in a further development is convex, in particular funnel-shaped or spherical.

[0017] A combination claimed to be particularly advantageous is a first contact area with a recess, the edge of which contacts an edge of the recess of the first contact contour over a surface area, or forms a surface contact point with it, or is provided or set up for this purpose.

[0018] In one embodiment, the first contact area for contacting the first contact contour has a convex or protruding edge, which in a further development is rounded.

[0019] A combination claimed to be particularly advantageous is a first contact area with an edge that contacts the edge of the first contact contour (idealized or seen from a rigid body mechanics perspective) in a line-like manner, or forms a line contact point with it, or is provided or set up for this purpose.

[0020] Another combination claimed to be particularly advantageous is a first contact area with an edge that contacts the edge of the first contact contour (idealized or from a rigid body mechanics perspective) at a point, or forms a point contact point with it, or is provided or set up for this purpose.

[0021] In one embodiment, the first contact area for contacting the first contact contour has a convex or protruding tip, which in a further development is rounded or truncated.

[0022] A combination claimed to be particularly advantageous is a first contact area with a tip that contacts the edge of the first contact contour (idealized or from a rigid body mechanics perspective) at a point or forms a point contact point with it, or is provided or set up for this purpose.

[0023] The aforementioned combinations and designs allow vibration propagation and / or excitation between the two components to be influenced particularly advantageously, thereby advantageously transferring (vibrational) energy into other modes and thus advantageously (further or particularly strongly and / or reliably) reducing vibrations in certain modes that are particularly pronounced without such contact contours.

[0024] In one embodiment, the first surface has one or more further contact areas for contacting the second surface, and the second surface has (each) a further contact area opposite the (respective) further contact area, separated from the first contact contour and, if applicable, the second surface.the other further contact contour(s) spaced apart, contact contour for contacting the (respective) further contact area, in a further development thus the first surface a first further contact area for contacting the second surface and the second surface a first further contact contour opposite this first further contact area, spaced apart from the first contact contour, for contacting this first further contact area and the first surface a second further contact area for contacting the second surface and the second surface a second further contact contour opposite this second further contact area, spaced apart from the first and first further contact contour, for contacting this second further contact area and possibly one or more further contact area(s) and contact contour(s).

[0025] In one version, the further contact contour - a convex, especially funnel-shaped or spherical, depression in a further training; or - a convex or protruding edge that has been rounded off in a further training; or - a convex or protruding tip, rounded or truncated in further training.

[0026] In a further development, one or more of the additional contact contours each have a convex, in particular funnel-shaped or spherical, depression. Additionally or alternatively, in a further development, one or more of the additional contact contours each have a rounded, convex or protruding edge. Additionally or alternatively, in a further development, one or more of the additional contact contours each have a rounded or truncated, convex or protruding tip.

[0027] In one version, the or one or more of the further contact area(s) for contacting the (corresponding) further contact contour are (each) free of embossing and indentation.

[0028] A combination claimed to be particularly advantageous is / are one or more additional contact area(s) free of protrusions and depressions, which / the each contact / contact an edge of the depression of the (corresponding) additional contact contour over a surface area or form / form a surface contact point with it or are provided or set up for this purpose.

[0029] Another combination claimed to be particularly advantageous is / are one or more additional contact area(s) free of protrusions and depressions, which contact(s) the edge of the (corresponding) additional contact contour (idealized or seen from a rigid body mechanics perspective) in a line-like manner or form a line contact point with it or are provided or arranged for this purpose.

[0030] Another combination claimed to be particularly advantageous is / are one or more additional contact area(s) free of protrusions and depressions, which (ideally or in terms of rigid body mechanics) contact the tip of the (corresponding) additional contact contour at a point or form a point contact point with it, or are provided or equipped for this purpose.

[0031] In one embodiment, the or one or more of the further contact area(s) for contacting the (corresponding) further contact contour (each) has a recess, which in a further development is convex, in particular funnel-shaped or spherical.

[0032] A combination claimed to be particularly advantageous is / are one or more further contact area(s) with (each) a recess, the edge of which (each) contacts an edge of the recess of the (corresponding) further contact contour over a surface or forms a surface contact point with it or is provided or set up for this purpose.

[0033] In one embodiment, the or one or more of the further contact area(s) for contacting the (corresponding) further contact contour (each) has a convex or protruding edge, which in a further development is rounded.

[0034] A combination claimed to be particularly advantageous is / are one or more further contact area(s) with (each) an edge that (idealized or from a rigid body mechanics perspective) contacts the edge of the (corresponding) further contact contour in a line-like manner or forms a line contact point with it or is provided or arranged for this purpose.

[0035] Another combination claimed to be particularly advantageous is / are one or more further contact area(s) with (each) an edge that (idealized or from a rigid body mechanics perspective) makes point-like contact with the edge of the (corresponding) further contact contour or forms a point contact point with it or is provided or set up for this purpose.

[0036] In one embodiment, the or one or more of the further contact area(s) for contacting the (corresponding) further contact contour (each) has a convex or protruding tip, which in a further development is rounded or truncated.

[0037] A combination claimed to be particularly advantageous is / are one or more further contact area(s) with (each) a tip that (idealized or from a rigid body mechanics perspective) makes point contact with the edge of the (corresponding) further contact contour or forms a point contact point with it or is provided or arranged for this purpose.

[0038] The aforementioned combinations and designs allow vibration propagation and / or excitation between the two components to be influenced particularly advantageously, thereby advantageously transferring (vibrational) energy into other modes and thus advantageously (further or particularly strongly and / or reliably) reducing vibrations in certain modes that are particularly pronounced without such contact contours.

[0039] It can be particularly advantageous if two or more pairs of contact areas and contact contours of the first and second components, in particular the pair (first contact area; first contact contour) and the pair or at least one pair (further contact area; further contact contour), are similar, for example, if two or more point contact points are formed by a tip and a contact area free of protrusions and depressions, or a contact area with a convex edge or tip, or the like. Accordingly, these combinations are claimed to be particularly advantageous.

[0040] It can also be particularly advantageous if two or more pairs of contact area and contact contour of the first and second components, in particular the pair (first contact area; first contact contour) and the pair or at least one pair (further contact area; further contact contour), are different. Accordingly, these combinations are claimed to be particularly advantageous.

[0041] In one version, for one or more of the contact contours, in a further development, the first and / or the or one or more further contact contours, and the contact area opposite them (in each case), in a further development accordingly, the first or (corresponding) further contact area, - the convex tip of this contact contour and - the opposite surface free of elevations and depressions or - convex edge or - convex tip this contact area or - the convex edge of this contact contour and - the convex edge of this contact area together form a point of contact.

[0042] In one version, for one or more of the contact contours, in a further development, the first and / or the or one or more further contact contours, and the contact area opposite them (in each case), in a further development accordingly, the first or (corresponding) further contact area, - the convex edge of this contact contour and - the opposite surface free of elevations and depressions or - convex edge this contact area together form a line contact point.

[0043] In one version, for one or more of the contact contours, in a further development, the first and / or the or one or more further contact contours, and the contact area opposite them (in each case), in a further development accordingly, the first or (corresponding) further contact area, - an edge of the depression of this contact contour and - a surface free of elevations and depressions or - a counter-surface with a depression, this contact area together a surface contact point.

[0044] The aforementioned combinations and designs allow vibration propagation and / or excitation between the two components to be influenced particularly advantageously, thereby advantageously transferring (vibrational) energy into other modes and thus advantageously reducing vibrations in certain modes that are particularly pronounced without such contact contours.

[0045] In one embodiment, one is arranged from the first and second surfaces on a running-face corner band, and the other is arranged from the first and second surfaces on an adjacent running-face corner band.

[0046] In another embodiment, one surface is arranged from the first and the second surface on a guide vane, and the other surface is arranged from the first and the second surface on a body movably arranged in a cavity of a platform of this guide vane, which is preferably designed to make contact with (an inner wall) of the cavity during operation.

[0047] In another embodiment, one is arranged from the first and second surfaces on a guide vane cluster or ("vane cluster") and the other from the first and second surfaces on a housing or sealing ring.

[0048] In another embodiment, one is arranged from the first and second surfaces on a disk with integrated guide vanes (“BladedDISK” or “Blisk”) and the other from the first and second surfaces on a damper ring or damper segment.

[0049] Particularly in these assemblies, vibration propagation and / or excitation between the two components can be influenced very advantageously, especially due to the aerodynamic, mechanical and thermal loads and design boundary conditions occurring during operation, and thereby (vibrational) energy can be advantageously transferred into other modes, thus advantageously reducing vibrations in certain modes that are particularly pronounced without such contact contours.

[0050] In one embodiment, the first surface is planar, preferably flat, outside its contact areas. In another embodiment, the first surface is cylindrical outside its contact areas. In another embodiment, the first surface is spherical outside its contact areas. In yet another embodiment, the first surface is conical outside its contact areas.

[0051] In one embodiment, the second surface is planar, preferably flat, outside its contact contours. In another embodiment, the second surface is cylindrical outside its contact contours. In another embodiment, the second surface is spherical outside its contact contours. In yet another embodiment, the second surface is conical outside its contact contours.

[0052] The aforementioned combinations and designs allow vibration propagation and / or excitation between the two components to be influenced particularly advantageously, thereby advantageously transferring (vibrational) energy into other modes and thus advantageously (further or particularly strongly and / or reliably) reducing vibrations in certain modes that are particularly pronounced without such contact contours.

[0053] According to one embodiment of the present invention, an assembly arrangement comprises several, in particular three or more, components which together form a ring, wherein, in particular viewed in the circumferential direction, adjacent components form a first and second component of an assembly described herein, and all first components have identical first contact areas (among themselves) and all second components have identical first contact contours (among themselves) which form identical contact points with these first contact areas (each). In one embodiment, all first components have identical further contact areas (among themselves) and all second components have identical further contact contours (among themselves) which form identical contact points with these further contact areas (each). In a further embodiment, the assembly arrangement has a cyclic symmetry (with respect to) contact area-contact contour pairs.

[0054] Through such cyclically symmetrical (distributed) contact points, (vibrational) energy can be transferred into higher modes, thereby advantageously reducing vibrations in fundamental or lower modes, which are particularly pronounced without such contacts.

[0055] According to one embodiment of the present invention, an assembly arrangement comprises several, in particular three or more, components which together form a ring, wherein, in particular viewed in the circumferential direction, adjacent components form a first and second component of an assembly described herein, and at least two first components have different types of first contact areas and / or at least two second components have different types of first contact contours, such that these first contact areas and first contact contours form different types of contact points. In a further embodiment, the assembly arrangement has no or a broken cyclic symmetry (with respect to) pair(s) of first contact area - first contact contour.

[0056] Through such non-cyclically symmetrical (distributed) contact points between first contact areas and first contact contours, (vibrational) energy can be transferred to other modes, in particular to the same mode family (for example, 1f (flap mode), 1cd (coupled disk mode), 1t (torsion mode), 1c (chordwise mode), or combinations thereof such as 1f + 1cd) and / or to adjacent node diameters, thereby advantageously reducing vibrations that would be particularly pronounced without such contacts. Accordingly, in one embodiment, the ring has several, preferably adjacent, node diameters.

[0057] Further advantageous embodiments of the present invention will become apparent from the dependent claims and the following description of preferred embodiments. The following is shown, in part schematically: Fig. 1 an assembly according to an embodiment of the present invention; Fig. 2 a component assembly according to a further embodiment of the present invention; Fig. 3 a component assembly according to a further embodiment of the present invention; Fig. 4 a component assembly according to a further embodiment of the present invention; Fig. 5 a component assembly according to a further embodiment of the present invention; Fig. 6 a component assembly according to a further embodiment of the present invention; Fig. 7 a body of the assembly of Fig. 6; Fig. 8 a body of a modification of the assembly of Fig. 6; Fig. 9 a body of a further modification of the assembly of Fig. 6; Fig. 10 a body of a further modification of the assembly of Fig. 6; Fig. 11 an assembly according to a further embodiment of the present invention; Fig. 12 a damper segment of the assembly of Fig. 11; Fig. 13 a damper segment of a modification of the assembly of Fig. 11; Fig. 14 a damper segment of a further modification of the assembly of Fig. 11; and Fig. 15 a second component of an assembly according to a further embodiment of the present invention.

[0058] Fig. Figure 1 shows a perspective view of an assembly according to an embodiment of the present invention. The assembly comprises a first component in the form of a rotor blade 110 with a first surface 111 on a rotor blade end strip, and a second component in the form of an adjacent rotor blade 120 with a second surface 121 opposite the first surface on a rotor blade end strip. The first surface has a first contact area 112, free of protrusions and depressions, for contacting the second surface, and the second surface has a first contact contour 122 opposite this first contact area, which has a convex edge 123, such that the convex edge 123 and the counter-surface 112, free of protrusions and depressions, form a line contact point. The rotor blades 110 and 120 are, in one embodiment, turbine rotor blades, and in a further embodiment, low-pressure turbine blades.

[0059] Fig. Figure 2 shows a section magnification of an assembly according to a further embodiment of the present invention. The assembly consists of the aforementioned (low-pressure) turbine rotor blades 110, 120, wherein, however, in contrast to the embodiment of the Fig. 1 the second surface on the running face corner band has a first contact contour 122 opposite the first contact area 112 which has no protrusion or depression and which has a convex tip 124, so that the convex tip 124 and the counter surface which has no protrusion or depression form a point contact point with each other.

[0060] Fig. Figure 3 shows an assembly according to a further embodiment of the present invention in Fig. 2 corresponding illustration. The assembly consists of the aforementioned (low-pressure) turbine rotor blades 110, 120, however, in contrast to the design of the Fig. 2 the first contact area 112 has a convex tip 114, so that the convex tips 114, 124 form a point contact point with each other.

[0061] Fig. Figure 4 shows an assembly according to a further embodiment of the present invention in Fig. 2 corresponding illustration. The assembly consists of the aforementioned (low-pressure) turbine rotor blades 110, 120, however, in contrast to the design of the Fig. 1, Fig. 2 the second surface on the running face corner belt not only has a first contact contour 122 opposite the first contact area 112 without protrusions or depressions with a convex edge 123, so that this convex edge 123 and the counter surface 112 without protrusions or depressions form a line contact point together, but the second surface additionally has a further contact contour 125 opposite a further contact area 115 without protrusions or depressions of the first surface 111 with a (further) convex edge 126, which forms a further line contact point (double line contact) together with the further counter surface without protrusions or depressions.

[0062] Fig. Figure 5 shows an assembly according to a further embodiment of the present invention in Fig. 4 corresponding illustration. The assembly consists of the aforementioned (low-pressure) turbine rotor blades 110, 120, however, in contrast to the design of the Fig. 4 the first contact area 112 has a convex edge 113 and the further contact area 115 has a (further) convex edge 116, so that the edges 113, 123 and the edges 116, 126 each form a line contact point (double line contact).

[0063] Fig. Figure 6 shows an assembly according to a further embodiment of the present invention, comprising a first component in the form of a rotor blade, in one embodiment a turbine rotor blade, in a further embodiment low-pressure turbine blades, 210, and a second component in the form of a shock body 220, which is movably arranged in a cavity 211 of a platform 212 of this rotor blade. An (inner) wall of the cavity forms a first surface or a first contact area, which in one embodiment is free of protrusions and depressions.

[0064] Fig. Figure 7 shows the impact body 220, which has a second surface 221, which has a first contact contour 222 for contacting a first contact area of ​​the (first) surface of the cavity 211 with a convex edge 223, which is oriented transversely to a longitudinal direction of the body.

[0065] Fig. Figure 8 shows the impact body 220 of an otherwise identical modification of the design of Fig. 6, where edge 223 is oriented in the longitudinal direction of the body.

[0066] Fig. Figure 9 shows the impact body 220 of an otherwise identical further modification of the design of Fig. 6, wherein the first contact contour 222 for contacting a first contact area of ​​the (first) surface of the cavity 211 has a funnel-shaped depression 227.

[0067] Fig. Figure 10 shows the impact body 220 of an otherwise identical further modification of the design of Fig. 6, in which the second surface 221 has a further contact contour 228 for contacting a further contact area of ​​the (first) surface of the cavity 211 with a further funnel-shaped depression 229.

[0068] Fig. Figure 11 shows an assembly according to a further embodiment of the present invention, comprising a first component in the form of a blisk 310 and a second component in the form of a damper segment 320. An (inner) wall of the blisk, which faces a transverse leg 320.2 projecting from a clamp 320.1 of the damper segment 320, forms a first surface or a first contact area, which in one embodiment is free of protrusions and depressions. In one embodiment, the blisk is a blisk of a compressor stage.

[0069] Fig. Figure 12 shows the damper segment 320, which or its transverse leg 320.2 has a second surface 321, which has a first contact contour 322 for contacting a first contact area of ​​a first surface of the blisk 310 with a convex edge 323.

[0070] Fig. Figure 13 shows the damper segment 320 of an otherwise identical modification of the design of the Fig. 11, wherein the first contact contour 322 for contacting a first contact area of ​​the first surface of the blisk 310 has a truncated tip 324.

[0071] Fig. Figure 14 shows the damper segment 320 of an otherwise identical further modification of the design of the Fig. 11, wherein the first contact contour 322 for contacting a first contact area of ​​the first surface of the blisk 310 has a spherical depression 327.

[0072] In a variation not shown, a damper ring, known per se, can be provided with the respective first contact contour instead of the damper segment.

[0073] Fig. Figure 15 shows a second component of an assembly according to a further embodiment of the present invention in the form of a guide vane or vane cluster 420 (for) a turbine or compressor stage in a perspective view. A first component in the form of a housing or sealing ring, in an embodiment of an inner sealing ring (“inner air seal”, IAS), is not shown for clarity.

[0074] This second component also has a second surface with a first contact contour for contacting an opposing first contact area of ​​a first surface of the first component, wherein this first contact contour has a recess 427 or 428. Furthermore, another contact contour, spaced apart from the first contact contour with recess 428, is provided for contacting a further contact area of ​​the first surface of the first component, which has a recess 429. The recess 427 is located in the outer cover band of the vane cluster, and the recesses 428 and 429 are located at the base and the interface to the IAS, respectively.

[0075] The above refers to running gear corner tapes (see above). Fig. 1-5), in one version of turbine blades, in a further development low-pressure turbine running blades, platform (shock body) damper (cf. Fig. 6-10), in one version of turbine blades, in a further development low-pressure turbine running blades, and / or radially inner platforms, blisks (see Fig. 11-14), in a version for compressor (stages), with damper segments or rings, and vane clusters in combination with a housing or sealing ring as the first component (see Fig. 15), particularly advantageous embodiments or applications of the present invention are shown, without limiting it thereto.

[0076] In the present disclosure, "has an X" does not generally imply an exhaustive list, but is a shorthand for "has at least one X" and also includes "has two or more X" as well as "has Y in addition to X". Although exemplary embodiments were explained in the preceding description, it should be noted that a multitude of variations are possible. 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, whereby various modifications, particularly with regard to the function and arrangement of the described components, can be made without leaving the scope of protection as defined by the claims and these equivalent combinations of features. Reference symbol list 110 Running blade (first component) 111 first surface 112 first contact area 113 edge 114 rounded tip 115 additional contact areas 116 edge 120 Running blade (second component) 121 second surface 122 first contact contour 123 edge 124 rounded tip 125 more contact contours 126 edge 210 Running blade (first component) 211 Cavity 212 Platform 220 impact bodies (second component) 221 second surface 222 first contact contour 223 edge 227 In-depth study 228 more contact contours 229 In-depth study 310 Blisk (first component) 320 Damper segment (second component) 320.1 bracket 320.2 Cross leg 321 second surface 322 first contact contour 323 edge 324 cut-off tip 327 In-depth study 420 Guide vane / vane cluster 427, 428, 429 In-depth study

Claims

Assembly comprising a first component (110; 210; 310) and a second component (120; 220; 320; 420) for arrangement in the same turbine or compressor stage of a turbomachine, in particular an aircraft engine, wherein the first component has a first surface (111) and the second component has a second surface (121; 221; 321) opposite the first surface, wherein the first surface has a first contact area (112) for contacting the second surface and the second surface has a first contact contour (122; 222; 322) opposite this first contact area for contacting this first contact area, which has a recess (227; 327; 427; 428) or a convex edge (123; 223; 323) or a convex tip (124). Assembly according to claim 1, characterized in that the first contact area for contacting the first contact contour is free of protrusions and depressions or has a depression or a convex edge or a convex tip (114). Assembly according to one of the preceding claims, characterized in that the first surface has at least one further contact area (115; 228) for contacting the second surface and the second surface has a further contact contour (125) opposite this further contact area, spaced apart from the first contact contour, for contacting this further contact area, which has a recess (229; 429) or a convex edge (126) or at least a convex tip. Assembly according to claim 3, characterized in that this further contact area for contacting this further contact contour is free of protrusions and depressions or has a depression or a convex edge (116) or a convex tip. Assembly according to one of the preceding claims, characterized in that for at least one contact contour and the contact area opposite it, the convex tip of this contact contour and the surface free of protrusions and depressions, or convex edge or convex tip of this contact area, or the convex edge of this contact contour and the convex edge of this contact area form a point contact point with each other; and / or the convex edge of this contact contour and the surface free of protrusions and depressions, or convex edge of this contact area form a line contact point with each other; and / or an edge of the depression of this contact contour and a surface free of protrusions and depressions or having a depression of this contact area form a surface contact point with each other. Assembly according to one of the preceding claims, characterized in that: - one surface is arranged from the first and second surfaces on a rotor blade end strip and the other surface is arranged from the first and second surfaces on an adjacent rotor blade end strip; or - one surface is arranged from the first and second surfaces on a rotor blade (210) and the other surface is arranged from the first and second surfaces on a body (220) movably arranged in a cavity (211) of a platform (212) of this rotor blade; or - one surface is arranged from the first and second surfaces on a guide vane cluster and the other surface is arranged from the first and second surfaces on a housing or sealing ring; or - one surface is arranged from the first and second surfaces on a disk with integrated guide vanes and the other surface is arranged from the first and second surfaces on a damper ring or damper segment. Assembly according to one of the preceding claims, characterized in that the first surface is planar, cylindrical, spherical, or conical outside its contact areas and / or the second surface is planar, cylindrical, spherical, or conical outside its contact contours. Assembly arrangement comprising several components which together form a ring, wherein each adjacent component forms a first and second component of an assembly according to one of the preceding claims and all first components have the same first contact areas and all second components have the same first contact contours which form the same contact points with these first contact areas. Assembly arrangement comprising several components which together form a ring, wherein adjacent components form a first and second component of an assembly according to one of the preceding claims 1 - 7 and at least two first components have different first contact areas and / or at least two second components have different first contact contours, such that these first contact areas and first contact contours form different contact points. Assembly arrangement according to claim 9, characterized in that the ring has several vibration node diameters. Turbine or compressor stage for a turbomachine, in particular an aircraft engine, comprising at least one assembly, in particular an assembly arrangement, according to one of the preceding claims. Turbomachine, in particular aircraft engine gas turbine, with at least one turbine stage according to claim 11 and / or at least one compressor stage according to claim 11.

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