Gas turbine structural component

Abstract

The present invention relates to a structural component for a gas turbine, comprising: an outer shell (1), an inner shell (2), and a support structure (31-33) connecting the outer shell and inner shell and comprising: a first disk arrangement with circumferentially spaced first disks (31), a second disk arrangement with circumferentially spaced second disks (32), and a rib arrangement with circumferentially spaced ribs (33), wherein the first and second disk arrangements are spaced apart from one another in the axial direction, at least one of the second disks at least partially covers a gap (312) between two circumferentially adjacent first disks, and at least one rib of the rib arrangement is arranged on this second disk and one of these two first disks,and at least one of the first disks at least partially covers a gap (321) between two circumferentially adjacent second disks, and at least one rib of the rib arrangement is arranged on this first disk and one of these two second disks. The invention also relates to a gas turbine assembly with the structural component and a method for producing the structural component.

Description

[0001] The present invention relates to a structural component for a gas turbine, a gas turbine assembly with the structural component and a method for producing the structural component.

[0002] Gas turbine structural components, for example compressor center frames or the like, are often intended to transfer loads between inner and outer shells, for example (rotor) bearing forces on struts or a casing or the like.

[0003] An object of an embodiment of the present invention is to improve a gas turbine structural component and / or its manufacture.

[0004] This object is achieved by a structural component having the features of claim 1 and a method having the features of claim 11. Claim 10 protects a gas turbine assembly having at least one structural component described herein. The subclaims relate to advantageous developments.

[0005] According to one embodiment of the present invention, a structural component for a gas turbine, in one further development, a structural component of a gas turbine assembly, in one embodiment, a structural component for a compressor and / or aircraft engine gas turbine assembly, in particular for an aircraft engine compressor gas turbine assembly, comprises a single-part or multi-part outer shell. In a particularly preferred embodiment, the structural component can comprise a section of a (gas) flow channel of the gas turbine, in particular a so-called compressor intermediate case. The (gas) flow channel can be arranged or formed, in particular, between the outer and inner shells mentioned below, or radially outside the outer shell, or radially inside the inner shell; in particular, the outer or inner shell can delimit the (gas) flow channel radially inside or outside.The invention is particularly advantageous for such applications, particularly due to the mechanical, thermal and / or structural boundary conditions, but is in no way limited thereto.

[0006] According to one embodiment of the present invention, the structural component has a single-part or multi-part inner shell which, in a further development, is arranged, preferably concentrically, (radially) within the outer shell, wherein the outer and inner shells are axially flush with one another, or the outer shell projects axially beyond the inner shell on both sides, or the inner shell projects axially beyond the outer shell on both sides, or the outer shell and inner shell can each project axially beyond the other of the two shells at one (axial) end.

[0007] In one embodiment, the outer shell is designed as a welded component. Additionally or alternatively, in one embodiment, the inner shell is designed as a welded component. For such components, the present invention is particularly advantageous because it can facilitate the execution, inspection, and / or repair of weld seams. In one embodiment, the outer shell can also be designed as a cast component or an additively or generatively manufactured component and / or the inner shell can also be designed as a cast component or an additively or generatively manufactured component. For such components, the present invention is particularly advantageous because it can facilitate inspection and / or repair, in particular repair welding.

[0008] According to one embodiment of the present invention, the structural component comprises a single-part or multi-part support structure that connects the outer shell and inner shell (to each other), preferably transferring loads, in particular radial loads, circumferential loads, and / or axial loads, between the outer shell and inner shell or is designed to do so. In one embodiment, the support structure is or will be connected to the outer shell and / or the inner shell in a material-to-material manner, in a further development by welding, soldering, gluing, or the like, or is integrally formed, in particular by additive or generative manufacturing or casting.

[0009] According to one embodiment of the present invention, the support structure has, and can in particular consist of, a disk arrangement with disks which are spaced apart from one another, preferably evenly, in the circumferential direction and are each made up of one or more parts, and which is / are referred to here without restriction of generality as the first disk arrangement or first disks, another disk arrangement with disks which are spaced apart from one another, preferably evenly, in the circumferential direction and are each made up of one or more parts, and which is / are referred to here without restriction of generality as the second disk arrangement or second disks, and a rib arrangement with ribs which are spaced apart from one another in the circumferential direction and are each made up of one or more parts, and can in particular consist of these. The first disk arrangement can in particular be an upstream disk or a front disk in the flow direction of the gas turbine, or a downstream disk orrear disc arrangement in the flow direction of the gas turbine.

[0010] In one embodiment, an axial direction is parallel to a (main) machine axis and / or rotational axis of the gas turbine and / or longitudinal and / or (rotational) symmetry axis of the structural component, a circumferential direction is correspondingly a circumferential or rotational direction around this (main) machine or rotational axis or axial direction, and a radial direction is perpendicular to the axial and circumferential direction.

[0011] In one embodiment, one or more of the first disks and / or one or more of the second disks are flat or curved once or multiple times and / or extend (in each case) radially from the inner to the outer shell and / or extend (in each case) predominantly in the circumferential and / or radial direction. Additionally or alternatively, in one embodiment, one or more of the ribs are flat or curved once or multiple times and / or extend (in each case) radially from the inner to the outer shell and / or extend (in each case) predominantly in the axial and / or radial direction, wherein ribs inclined against the axial direction can also be advantageous, in particular for connecting first and second disks with different dimensions to one another.

[0012] According to one embodiment of the present invention, the first and second disk arrangements are spaced apart from one another in the axial direction, in a further development the first disk arrangement is arranged in the region of an (axial) end of the outer and / or inner shell and / or the second disk arrangement is arranged in the region of an (other axial) end of the outer and / or inner shell.

[0013] According to one embodiment of the present invention, at least one of the second discs covers or overlaps a gap between two circumferentially adjacent first discs, completely or partially, wherein at least one rib of the rib arrangement is arranged on this second disc and on one of these two first discs, preferably adjoining it, and at least one other rib of the rib arrangement is arranged on this second disc and on the other of these two first discs, preferably adjoining it, preferably in such a way that these two first discs, these ribs and this second disc form a blind hole-like depression when viewed in the circumferential direction.two or more, particularly preferably all, of the second discs each completely or partially overlap a gap between two circumferentially adjacent first discs, wherein at least one rib of the rib arrangement is arranged on the respective second disc and on one of these respective two first discs, preferably adjoining it, and at least one other rib of the rib arrangement is arranged on this second disc and on the other of these respective two first discs, preferably adjoining it.

[0014] According to one embodiment of the present invention, at least one of the first discs covers or overlaps a gap between two second discs adjacent in the circumferential direction, completely or partially, wherein at least one rib of the rib arrangement is arranged on this first disc and on one of these two second discs, preferably adjoining it, and at least one other rib of the rib arrangement is arranged on this first disc and on the other of these two second discs, preferably adjoining it, preferably in such a way that these two second discs, these ribs and this first disc form a blind hole-like depression when viewed in the circumferential direction.two or more, particularly preferably all, of the first discs each completely or partially overlap a gap between two circumferentially adjacent second discs, wherein at least one rib of the rib arrangement is arranged on the respective first disc and on one of these respective two second discs, preferably adjoining it, and at least one other rib of the rib arrangement is arranged on this first disc and on the other of these respective two second discs, preferably adjoining it.

[0015] Particularly preferably, first and second discs (offset relative to them in the circumferential direction) are arranged alternately in the circumferential direction, wherein at least one of the ribs is arranged, in particular adjoined, on discs which follow one another in the circumferential direction, so that the support structure in one embodiment runs or is formed in a meandering manner in the circumferential direction.

[0016] In one embodiment, this makes it possible to achieve, on the one hand, a particularly advantageous load distribution in the structural component and / or a particularly advantageous load transfer between the inner and outer shell and, on the other hand, access to the space between the inner and outer shell, in particular for producing and / or checking and / or repairing the structural component, in particular for producing and / or checking weld seams or the like.

[0017] In one embodiment, one or more of the first discs and / or one or more of the second discs and / or one or more of the ribs (each) has at least one hollow space or is at least partially hollow or not formed as a solid component. This advantageously allows for weight reduction in one embodiment.

[0018] Additionally or alternatively, in one embodiment, one or more of the first discs and / or one or more of the second discs are (each) trapezoidal, preferably in the manner of an isosceles trapezoid.

[0019] Additionally or alternatively, in one embodiment, one or more of the disks (each) have an outer shell-facing or radially outer end face and an inner shell-facing or radially inner end face, wherein a, in particular minimum and / or maximum and / or average, extent of this outer shell-facing end face in the circumferential direction is greater than a, in particular minimum and / or maximum and / or average, extent of this inner shell-facing end face in the circumferential direction. Additionally or alternatively, in one embodiment, one or more (other) of the disks (each) have an outer shell-facing or radially outer end face and an inner shell-facing or radially inner end face,radially inner end face, wherein a, in particular minimum and / or maximum and / or average, extension of this outer shell-facing end face in the circumferential direction is smaller than a, in particular minimum and / or maximum and / or average, extension of this inner shell-facing end face in the circumferential direction.

[0020] Accordingly, in one embodiment, one or more of the first discs (each) have an outer shell-facing end face that is longer in the circumferential direction than their inner shell-facing end face, and / or one or more of the second discs (each) have an outer shell-facing end face that is shorter in the circumferential direction than their inner shell-facing end face, or conversely, one or more of the first discs (each) have an outer shell-facing end face that is shorter in the circumferential direction than their inner shell-facing end face, and / or one or more of the second discs (each) have an outer shell-facing end face that is longer in the circumferential direction than their inner shell-facing end face.

[0021] Accordingly, in a particularly advantageous combination of the aforementioned features, one or more of the first and / or second panes are trapezoidal, preferably in the manner of an isosceles trapezoid, wherein, in a particularly advantageous manner, in these first panes, the end face facing the outer shell forms the, preferably curved, base and the end face facing the inner shell forms the, preferably curved, other or shorter base side of the trapezoid and / or in these second panes, the end face facing the inner shell forms the, preferably curved, base and the end face facing the outer shell forms the, preferably curved, other or shorter base side of the trapezoid, or conversely, in these first panes, the end face facing the inner shell forms the, preferably curved, base and the end face facing the outer shell forms the, preferably curved, other or shortershorter base side of the trapezoid and / or in the case of these second panes, the end face facing the outer shell forms the, preferably curved, base and the end face facing the inner shell forms the, preferably curved, other or shorter base side of the trapezoid.

[0022] Additionally or alternatively, in one embodiment, one or more disks of one of the two disk arrangements are (respectively) longer in the circumferential direction, in particular absolutely and / or relatively or in relation to a, in particular minimum, maximum or average, circumference of the (respective) disk arrangement, than one or more, preferably all, disks of the other of the two disk arrangements in the circumferential direction. Accordingly, in one embodiment, first disks are longer in the circumferential direction than second disks or, conversely, second disks are longer in the circumferential direction than first disks. If one of the two disk arrangements has a larger maximum outer diameter or circumference than the other of the two disk arrangements, for example, disks of the disk arrangement with the larger outer diameter or circumference can be absolutely longer than disks of the disk arrangement with the smaller outer diameter or circumference, but relatively orshorter relative to the larger outer circumference of their disc arrangement. In particular, the "longer" can refer to the (maximum) angular range swept by the respective disc or correspond to a larger angular range swept.

[0023] Additionally or alternatively, one or more of the disks of one of the two disk arrangements, which (each) at least partially cover a gap between two disks of the other of the two disk arrangements that are adjacent in the circumferential direction, at least partially cover or overlap one or both of these (respective) two disks of the other disk arrangements in the circumferential direction. Additionally or alternatively, one or more of the disks of one of the two disk arrangements, which (each) at least partially cover a gap between two disks of the other of the two disk arrangements that are adjacent in the circumferential direction, do not (at all) or do not partially cover or overlap one or both of these (respective) two disks of the other disk arrangements in the circumferential direction. In other words, first disks can be arranged (completely or only) in the gaps between second disks and / or second disks (completely or only) in the gaps between second disks and / oronly) be arranged in the gaps between first panes and / or first panes at least partially cover or overlap second panes on one or both sides and / or second panes at least partially cover or overlap first panes on one or both sides. In this case, (partial) overlapping is generally understood, in particular in the usual way, to mean that projections in the axial direction (partially) lie one above the other.

[0024] Additionally or alternatively, in one embodiment, the first shell and / or the second shell covers the rib arrangement, in a further development also the first discs and / or second discs, in one embodiment accordingly the (entire) support structure, in particular from the radial outside or inside.

[0025] Additionally or alternatively, the support structure extends in one embodiment over the entire inner circumference of the outer shell and / or over the entire outer circumference of the inner shell.

[0026] By means of one or more of the aforementioned (geometric) features, a particularly advantageous load distribution in the structural component and / or a particularly advantageous load transfer between the inner and outer shell can be realized in one embodiment.

[0027] In one embodiment, one or more of the first discs are or will be integrally formed or materially connected to one or more of the ribs arranged on the (respective first disc).

[0028] Additionally or alternatively, in one embodiment, one or more of the second panes are or will be integrally formed or materially connected to one or more of the ribs arranged on the (respective second pane). Additionally or alternatively, in one embodiment, one or more of the first panes and / or one or more of the second panes are or will be integrally formed or materially connected to the outer shell.

[0029] Additionally or alternatively, in one embodiment, one or more of the first panes and / or one or more of the second panes are or will be integrally formed with the inner shell or connected by a material bond.

[0030] Additionally or alternatively, in one embodiment, one or more of the ribs are or will be integrally formed with the outer shell or connected by a material bond.

[0031] Additionally or alternatively, in one embodiment, one or more of the ribs are or will be integrally formed with the inner shell or connected by a material bond.

[0032] An integral design can improve load flow in one embodiment, and a material connection can particularly improve manufacturing.

[0033] In one embodiment, the inner shell is connected to an inner bearing, preferably for a rotor of the gas turbine, and / or the outer shell is connected directly or indirectly, in one embodiment via struts, to a housing, preferably a housing of the gas turbine, preferably secured thereto. The present invention is particularly advantageous for such load flows.

[0034] According to one embodiment of the present invention, a method for producing a structural component described here comprises a materially bonding of two or more of the components of the structural component to one another, in one embodiment of ribs with first and / or second discs and / or of ribs, first discs and / or second discs to the outer shell and / or the inner shell, and / or an integral formation of two or more of the components of the structural component to one another, in one embodiment of ribs with first and / or second discs and / or of ribs, first discs and / or second discs to the outer shell and / or the inner shell.

[0035] 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 structural component according to an embodiment of the present invention in a side view; Fig. 2 shows the structural component in an axial plan view; Fig. 3 shows an axial section along the line III-III in Fig. 2 through a first disc arrangement of the structural component; Fig. 4 an axial section along the line IV-IV in Fig. 2 between the first and a second disc arrangement of the structural component; Fig. 5 an axial section along the line VV in Fig. 2 through the second pane arrangement; and Fig. 6 shows a structural component according to a further embodiment of the present invention in a side view.

[0036] Fig. 1, 2 show a structural component for a gas turbine according to an embodiment of the present invention in a view from the side ( Fig. 1 ) or axial top view ( Fig. 2 ), Fig. 3-5 Axial sections perpendicular to (in Fig. 1 horizontal) (main) machine or longitudinal axis.

[0037] The structural component comprises an outer shell 1, an inner shell 2 and a support structure which connects the outer shell 1 and inner shell 2 and comprises a first disc arrangement with circumferentially spaced first discs 31, a second disc arrangement with circumferentially spaced second discs 32 and a rib arrangement with circumferentially spaced ribs 33.

[0038] As particularly the axial sections of the Fig. 3 - 5 illustrate, the first and second disc arrangements are spaced apart from each other in the axial direction.

[0039] As particularly the axial top view of the Fig. 2 in conjunction with the axial sections of the Fig. 3 - 5 illustrated, each of the second disks 32 at least partially covers a gap 312 between two circumferentially adjacent first disks 31, wherein in each case a rib 33 of the rib arrangement is arranged on the respective second disk 32 and one of the two respective first disks 31 and a circumferentially adjacent rib 33 of the rib arrangement is arranged on this second disk 32 and the other of the two respective first disks 31, and each of the first disks 31 at least partially covers a gap 321 between two circumferentially adjacent second disks 32, wherein in each case a rib 33 of the rib arrangement is arranged on the respective first disk 31 and one of the two respective second disks 32 and a circumferentially adjacent rib 33 of the rib arrangement is arranged on this first disk 31 and the other of the two respective second disks 32.

[0040] The discs 31, 32 are trapezoidal in shape, wherein in the exemplary embodiment, the first discs 31 each have an outer shell-facing end face 31A and an inner shell-facing end face 31B, wherein an extension of the outer shell-facing end face 31A in the circumferential direction is greater than an extension of the inner shell-facing end face 31B in the circumferential direction. Conversely, in the second discs 32, an extension of an outer shell-facing end face 32A in the circumferential direction is smaller than an extension of the inner shell-facing end face 32B in the circumferential direction.

[0041] In the exemplary embodiment, the first discs 31 of the first disc arrangement are longer in the circumferential direction than the second discs of the second disc arrangement in the circumferential direction.

[0042] As in particular Fig. 1 As illustrated, the shells 1, 2 cover the support structure 31-33, which in turn extends over the complete (radial) inner circumference of the outer shell and the complete (radial) outer circumference of the inner shell.

[0043] The inner shell can be connected to an inner bearing 40 of the gas turbine, the outer shell, for example via struts 42, to a casing 41 of the gas turbine, which only in Fig. 2 are indicated schematically and in dashed lines.

[0044] The embodiment illustrates in particular that the majority of the inner circumferential surface of the outer shell 1 and the outer circumferential surface of the inner shell 2 is each advantageously accessible through one of the gaps 312, 321 between circumferentially adjacent ribs 33.

[0045] 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.

[0046] For the sake of simplicity, the outer and inner shells 1, 2 are shown as cylindrical; one or both shells can, of course, also be particularly advantageously conical, tapered, or otherwise shaped. Accordingly, in a preferred embodiment, the first disk arrangement has a first (maximum) outer diameter, and the second disk arrangement has a larger or smaller (maximum) outer diameter. As an example, Fig. 6 for this purpose, a structural component according to a further embodiment of the present invention in a view from the side, which otherwise corresponds to the above embodiment of the Fig. 1-5 can match.

[0047] 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

[0048] 1Outer shell 2Inner shell 31First disc(s) 32Second disc(s) 33Rib(s) 31A, 32AEnd face facing the outer shell 31B, 32End face facing the inner shell 40Bearing 41Housing 42Strut 312Gap between adjacent first discs 321Gap between adjacent second discs

Claims

1. A structural component for a gas turbine, comprising: - an outer shell (1); - an inner shell (2); and - a support structure (31-33) connecting the outer shell and inner shell and comprising: - a first disk arrangement with first disks (31) spaced apart from one another in the circumferential direction; - a second disk arrangement with second disks (32) spaced apart from one another in the circumferential direction; and - a rib arrangement with ribs (33) spaced apart from one another in the circumferential direction; wherein - the first and second disk arrangements are spaced apart from one another in the axial direction; - at least one of the second disks at least partially covers a gap (312) between two circumferentially adjacent first disks, and at least one rib of the rib arrangement is arranged on this second disk and one of these two first disks;and - at least one of the first discs at least partially covers a gap (321) between two circumferentially adjacent second discs and at least one rib of the rib arrangement is arranged on this first disc and one of these two second discs; 2. Structural component according to claim 1, characterized in that at least one of the discs is trapezoidal and / or that at least one of the discs and / or at least one of the ribs has at least one cavity.

3. Structural component according to one of the preceding claims, characterized in that at least one of the discs has an end face facing the outer shell and an end face facing the inner shell, wherein an extension of the end face facing the outer shell in the circumferential direction is greater than an extension of the end face facing the inner shell in the circumferential direction.

4. Structural component according to one of the preceding claims, characterized in thatat least one of the panes, in particular of the other pane arrangement, has an end face facing the outer shell and an end face facing the inner shell, wherein an extension of the end face facing the outer shell in the circumferential direction is smaller than an extension of the end face facing the inner shell in the circumferential direction.

5. Structural component according to one of the preceding claims, characterized in that Discs of one of the two disc arrangements are longer in the circumferential direction than discs of the other of the two disc arrangements in the circumferential direction; and / or that at least one of the discs of one of the two disc arrangements, which at least partially covers a gap between two circumferentially adjacent discs of the other of the two disc arrangements, at least partially covers at least one of these two discs of the other disc arrangements.

6. Structural component according to one of the preceding claims, characterized in thatat least one of the discs of one of the two disc arrangements, which at least partially covers a gap between two circumferentially adjacent discs of the other of the two disc arrangements, does not cover at least one of these two discs of the other disc arrangements and / or that at least one of the shells covers the rib arrangement, in particular the support structure.

7. Structural component according to one of the preceding claims, characterized in that the support structure extends over the entire inner circumference of the outer shell and / or the entire outer circumference of the inner shell.

8. Structural component according to one of the preceding claims, characterized in that- at least one of the first discs is integrally formed with or materially connected to at least one of the ribs arranged thereon; and / or - at least one of the second discs is integrally formed with or materially connected to at least one of the ribs arranged thereon; and / or - at least one of the first discs is integrally formed with or materially connected to the outer shell and / or the inner shell; and / or - at least one of the second discs is integrally formed with or materially connected to the outer shell and / or the inner shell; and / or - at least one of the ribs is integrally formed with or materially connected to the outer shell and / or the inner shell.

9. Structural component according to one of the preceding claims, characterized in that the inner shell is connected to an inner bearing (40) and / or the outer shell is connected to a housing (41), in particular via struts (42).

10. Gas turbine assembly, in particular compressor and / or aircraft engine gas turbine assembly, with at least one structural component according to one of the preceding claims.

11. A method for producing a structural component according to one of the preceding claims, comprising at least one of the following steps: - materially joining at least two of the components of the structural component to one another; and / or - integrally forming at least two of the components of the structural component.

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