Annular component, aircraft engine comprising an annular component and method for producing an annular component

Abstract

The disclosure relates to an annular component (20) for an aircraft engine comprising a flange structure (1) located forward in the direction of flight (F), a flange structure (3) located aft in the axial direction (R), and an annular structure (2) arranged axially (R) between the flange structures (1, 3), characterized in that the annular structure (2) has a variable cross-sectional shape (Q1, Q2) and / or a variable material arrangement (M1, M2) in the circumferential direction (U) and / or perpendicular to the circumferential direction (U), and at least one of the flange structures (1, 3) has at least two annular sections (4, 5) in the circumferential direction (U), each arranged at a different angle (α, β) relative to the annular structure (2). The disclosure further relates to an aircraft engine with an annular component and a method for manufacturing the annular component.

Description

[0001] The invention relates to an annular component with the features of claim 1, an aircraft engine with an annular component with the features of claim 12 and a method for manufacturing an annular component with the features of claim 13.

[0002] Components in aircraft engines are subject to stringent requirements regarding strength, weight, and fire resistance, necessitating careful selection and coordination of design features to meet these demands. In many cases, these components are manufactured from or incorporating composite materials, as described, for example, in US 2016 / 0263856 A1. Examples of such components include fan housings in aircraft engines or bypass duct components. Typically, these annular components feature flanges on their side faces to connect them to other components and / or to center them. A flange can be understood as an edge projecting from the component, primarily serving to connect it to another component, with the components abutting flush or substantially flush.

[0003] The task is therefore to provide ring-shaped components that have a low weight and at the same time high strength.

[0004] The problem is solved by a ring-shaped component with the features of claim 1.

[0005] The ring-shaped component for an aircraft engine has a front flange structure in the direction of flight. Furthermore, the ring-shaped component has a rear flange structure in the axial direction and a ring structure between the flange structures. Im Essentially, the ring-shaped component has a U-shaped cross-section perpendicular to the circumferential direction. The ring structure exhibits a variable cross-sectional shape and / or a variable material arrangement in the circumferential direction and / or perpendicular to the circumferential direction. This means that the ring structure can be anisotropic with respect to the materials and / or the cross-sections. This anisotropy can be axial (perpendicular to the circumferential direction) and / or circumferential, resulting in a wide variety of design possibilities.

[0006] Furthermore, at least one of the flange structures of the annular component has at least two annular sections in the circumferential direction, wherein the annular sections are each arranged at a different angle relative to the annular structure. While a flange known per se has a bend, usually at 90°, of an annular structure, the flange structure of the object according to claim 1 is more complex in shape. The different angles result in a smoother transition from the plane of the annular structure to the distal, radially outer section of the flange structure.

[0007] This opens up several optimization possibilities. It enables structural optimization and, consequently, weight reduction. High-performance and lightweight materials (e.g., carbon fibers) can be used to meet structural requirements. This can be achieved, for example, through variable cross-sections (staggered layup) or integrated reinforcement elements. In some designs, it is also possible to arrange fibers at a 90° angle in the flange areas.

[0008] In one embodiment, a first angle between the ring structure and the first section of the flange structure, in particular the front flange structure, lies in the range between 10° and 60°, and / or a second angle of 90° lies between the ring structure and the second section of the flange structure. Thus, the first angle represents an incline extending from the ring structure. This section with the first angle then transitions into the section with the second right angle, so that the axially outer flange surface of the flange structure then forms a perpendicular flange surface.

[0009] For example, the angle between the ring structure and the rear flange structure can be between 90° and 90°. Thus, the rear flange structure can extend perpendicular to the ring structure.

[0010] The angles are measured between the central axes / central planes of the ring structure and the at least one flange structure in the direction towards the plane of the ring structure.

[0011] Furthermore, the at least one flange structure and / or the ring structure can be connected with a reinforcement structure and / or a fire protection layer, or they can be formed in one piece.

[0012] An example of anisotropy in the component is when at least one area of ​​the cross-sectional shape of the ring structure has a cross-sectional expansion in the circumferential direction around the center line.

[0013] In one embodiment, at least one connecting element, a reinforcing structure, and / or a reinforcing element is integrated on the outside of the ring structure and / or within the ring structure. The connecting element serves, for example, to connect to another component. The reinforcing element can, for example, provide targeted stiffening in an area where a load is applied to the component or where special aerodynamic conditions (e.g., due to gases) must be met.

[0014] The inner surface of the ring structure can also be at least partially aerodynamically contoured. This contour of the ring's inner surface defines the outer boundary of the airflow area of ​​the gas turbine engine's gas path. This can be achieved, for example, with a lightweight filler material (such as a plastic foam) that ensures a smooth transition / connection of the gas path from the ring's inner surface to the adjacent component, typically a fan case.

[0015] In a further embodiment, the ring structure and / or at least one of the flange structures is connected to an insert, in particular a foam core or an annular insert. The insert can, for example, serve to fill an edge or a cavity that results from the assembly with adjacent components. This allows for the creation of an aerodynamically favorable gas path.

[0016] An efficient and mechanically stable design is achieved when the component can be manufactured at least partially using a lay-up or winding process, particularly with a staggered lay-up. The lay-up method and / or the winding method and / or the respective material can differ in at least two areas of the flange structure and / or the ring structure.

[0017] The problem is also solved by an aircraft engine having the features of claim 12 and a method having the features of claim 13.

[0018] In the manufacturing process, a basic form of a ring-shaped component can be produced first.

[0019] Separately, an insert, such as a foam core or an annular insert, can be manufactured in which at least one layer of composite material is arranged in a mold, with at least one layer of the insert, in particular a foam core or an annular insert, being placed on top of this layer. The insert can then be encased by the at least one layer, so that the foam core has, for example, a resin-impregnated surface on the outside, which is suitable for bonding to a surface of the annular component. This insert is then bonded to the base shape of the annular component, in particular in an autoclave.

[0020] The invention is explained in connection with the embodiments shown in the figures. Fig. 1 a view of a first embodiment of an annular component in the axial direction; Fig. 1A a sectional view of the first embodiment along the plane AA in Fig. 1 with variable material arrangements in the axial direction; Fig. 1 Sectional view of the first embodiment perpendicular to an axis of rotation with variable material arrangements in the circumferential direction; Fig. 1C A sectional view of the first embodiment along the plane AA in Fig. 1 with variable cross-sectional shapes in the axial direction; Fig. 1 Your sectional view of the first embodiment perpendicular to the axis of rotation with variable cross-sectional shapes in the circumferential direction; Fig. 1 A detailed view of the in Fig. 1A area marked by a dashed-dotted line; Fig. 2 a view of a second embodiment of the ring-shaped component in the axial direction; Fig. 2A a sectional view of the second embodiment along line BB in Fig. 2 Fig. 3 a perspective detail view of a third embodiment with an area containing additional material in a ring structure; Fig. 4 a detail in a side view of an annular component; Fig. 4A a sectional view of the detail along line CC from Fig. 4 in the axial direction. Fig. 5 a side view of a fourth embodiment of the ring-shaped component in the axial direction; Fig. 5A a sectional view of the fourth embodiment along line DD in Fig. 5 ; Fig. 5 Legs Detail view of parts of a foam core with a dovetail joint along line EE in Fig. 5A Fig. 6 a flowchart for an embodiment of a method for manufacturing an annular component; Fig. 7A a schematic representation of an embodiment of a method step for manufacturing a foam core; Fig. 7B a schematic representation of an embodiment of a method step for joining a foam core and annular component; Fig. 7C a representation of a first embodiment of the annular component with a foam core in assembly with an adjacent component; Fig. 7D a representation of a second embodiment of the annular component with a foam core in assembly with an adjacent component.

[0021] In the Fig. 1, 1A A first embodiment of a ring-shaped component 20 for an aircraft engine is shown. Fig. 1 This shows a view in the axial direction, i.e., in the direction of a rotational axis R of the aircraft engine (not shown here). If the ring-shaped component 20 is designed, for example, as a housing for a fan (not shown here), then the axial direction would be the rotational axis R of the fan. The flight direction F (see Fig. 1A ) of the aircraft engine would be coaxial to the axis of rotation R. In the Fig. 1 A section plane AA is specified, with the corresponding section view in Fig. 1A is shown.

[0022] As in Fig. 1A As can be seen, the ring-shaped component 20 has a front flange structure 1 and a rear flange structure 3, viewed in the direction of flight F or in the direction of the axis of rotation R. A ring structure 2 is arranged between the flange structures 1 and 3, the wall of which is oriented approximately parallel to the axis of rotation R. In the illustrated view, the ring structure 2 has a slightly upwardly curved (i.e., radially outwardly curved) shape; that is, the ring structure 2 does not need to have a flat or planar base.

[0023] The embodiments described below each feature variable cross-sectional shapes Q1, Q2 and / or variable material arrangements M1, M2 in the circumferential direction U and / or perpendicular to the circumferential direction U. For example, it is possible to use only one material and vary only the cross-sectional shapes Q1, Q2.

[0024] Fig. 1A The figure shows variable material arrangements M1, M2 in a plane perpendicular to the circumferential direction U. This means that different materials can be used in the axial direction in the ring structure 2.

[0025] Thus, the first material arrangement M1, which is closer to the front flange structure 1 than the second material arrangement M2, could, for example, have higher strength and a higher weight if the mechanical and / or thermal loads on the front flange structure 1 are higher than in the rear flange structure 3. The second material arrangement M2, which is closer to the rear flange structure 3, can be adapted to the load, e.g., be made lighter.

[0026] The embodiment according to the Fig. 1A This shows a variability in the axial direction (i.e., perpendicular to the circumferential direction), where the case is shown here that the material arrangements M1, M2 extend around the circumference in the same way, i.e., the material arrangements M1, M2 form ring-shaped material arrangements M1, M2.

[0027] In other embodiments, the material arrangements M1, M2 each extend only over a partial region of the circumference, i.e., different material arrangements M1, M2 are present in the circumferential direction U, which in Fig. 1B This is illustrated. For example, a segment in the upper part of the ring structure 2 has a material arrangement M2, while the complementary segment in the lower part of the ring structure 2 has a material arrangement M1. This allows, for example, a housing to be adapted to different mechanical and / or thermal loads on the top and bottom (or also the side surfaces). Thus, it is not absolutely necessary that the material arrangements M1 and M2 each extend around the same portion of the circumference. In the illustrated embodiment, it is assumed that the different material arrangements M1 and M2 extend in the axial direction R over the entire area of ​​the ring structure 2, but this is not mandatory.

[0028] The embodiments shown here as examples feature two different material arrangements M1 and M2. However, it is possible to use more than two different material arrangements M1 and M2 to meet specific load requirements. The embodiments can also be further customized. Fig. 1A , 1B The materials M1 and M2 can be combined by arranging them differently both circumferentially and perpendicularly. This allows the materials to be used precisely where needed. In each case, an anisotropic material distribution is present in the ring structure 2.

[0029] In addition to or as an alternative to the variable material arrangements M1, M2, the cross-sectional shapes Q1, Q2 of the ring structure 2 can also be variable. That is, the cross-sectional shapes Q1, Q2 can be variable in the circumferential direction U and / or perpendicular to the circumferential direction U, which is shown in the Fig. 1C ,1D is shown.

[0030] Fig. 1C Figure 1 shows an embodiment with variable cross-sectional shapes Q1, Q2 in a plane perpendicular to the circumferential direction U. The first cross-sectional shape Q1, which is closer to the front flange structure 1, has a larger cross-section (i.e., a greater wall thickness) than the second cross-sectional shape Q2, which is located axially behind it. This is similar to the variable material arrangements M1, M2 in the embodiments of the Fig. 1A , 1B , the cross-section of the ring structure 2 can be specifically adapted to mechanical loads and / or thermal loads.

[0031] The embodiment according to the Fig. 1C This shows a variability of the cross-sections Q1, Q2 in the axial direction (i.e. perpendicular to the circumferential direction U), where the case is shown here that the cross-sectional shapes Q1, Q2 extend around the circumference in the same way.

[0032] In other embodiments, the variable cross-sectional shapes Q1, Q2 each extend only over a partial area of ​​the circumference, i.e., different cross-sectional shapes Q1, Q2 are present in the circumferential direction U, which in Fig. 1D This is illustrated. For example, a segment on the left side of the ring structure 2 has a greater wall thickness (cross-sectional shape Q1) than the complementary segment of the ring structure 2. This also allows, for example, a housing to be adapted to different mechanical and / or thermal loads on the top and bottom (or side) surfaces. Thus, it is not absolutely necessary that the different cross-sectional shapes Q1, Q2 each extend around the same portion of the circumference. In the illustrated embodiment, it is assumed that the different cross-sectional shapes Q1, Q2 extend along the entire area of ​​the ring structure 2 in the direction of the axis of rotation R, but this is not mandatory.

[0033] The embodiments shown here as examples have two different cross-sectional shapes Q1 and Q2. However, it is possible to use more than two different cross-sectional shapes Q1 and Q2 to meet specific load requirements. The embodiments can also be further customized. Fig. 1C , 1D They can be combined by arranging the cross-sectional shapes Q1 and Q2 differently both circumferentially and perpendicular to it. This allows different material thicknesses to be used precisely where needed. In any case, the different cross-sectional shapes Q1 and Q2 result in anisotropy of the shape.

[0034] The embodiments with variable material arrangement M1, M2 (see Fig. 1A , 1B ) and with variable cross-sectional shape Q1, Q2 (see Fig. 1C , 1D) can be combined with each other by, for example, the materials in a thickened wall area of ​​the ring structure 2 differing from the materials in a thinner wall area of ​​the ring structure 2.

[0035] This load-adaptive flexibility in the design of the ring structure 2 is present in all embodiments according to the Fig. 1, 1A , 1B, 1C , 1D Furthermore, at least one of the flange structures 1, 3 has at least two annular sections 4, 5 in the circumferential direction U, each of which is arranged at a different angle α, β relative to the ring structure 2.

[0036] For the sake of simplicity, this design of at least one flange structure 1, 3 is used in the Fig. 1B and 1D Only the front flange structure 1 is shown. The rear flange structure 3 can be designed in a similar way.

[0037] The designs - best in Fig. 1A and 1C The ring structure 2, recognizable in cross-section perpendicular to the circumferential direction, has a substantially U-shaped cross-section, with the front flange structure 1 extending radially outwards approximately twice as far as the rear flange structure 3. This may be configured differently in alternative embodiments. As mentioned above, the base of the ring structure 2 is slightly curved, the shape of which depends on the flow-guiding function of the ring structure.

[0038] In the illustrated embodiment, the rear flange structure 3 is positioned at an angle γ of essentially 90° from the cross-sectional area of ​​the ring structure 2. The 90° angle is defined here between the centerline / center plane of the wall of the ring structure 2 and the centerline / center plane of the wall of the rear flange structure 3, which, as shown in Fig. 1B The schematic representation shows the cut at a 90° angle. The angle γ is measured in the direction of the wall of the ring structure 2. The rear flange structure 3 is formed integrally with the ring structure 2.

[0039] In contrast, the front flange structure 1 in the illustrated embodiment has a somewhat more complex shape (see, for example, Fig. 1F). A first section 4 connects to it axially forward – i.e., in the direction of flight F – at an angle α = 45°. Here, too, the angle α is determined between the centerline / center plane of the cross-section of the ring structure 2 and the centerline / center plane of the cross-section of the first section 4; the centerlines / center planes intersect at an angle of 45°.

[0040] A second section 5 adjoins the distal end of the first section 4, extending at an angle β = 90° relative to the ring structure 2. Thus, angle β differs from the first angle α. Angle β is again measured at the intersection of the center lines (or the intersection axis of the midplanes). Angles α and β are also measured in the direction of the wall of the ring structure 2. The front flange structure 1 is also formed integrally with the ring structure 2, so that the entire ring-shaped component 20 is formed in one piece. In alternative embodiments, the ring-shaped component 20 can also be made from two or more components.

[0041] As a result, in the embodiments shown here, the front flange structure 1 is initially bent upwards in the first section 4 at a relatively shallow angle α, e.g., with α between 10 and 60°. Then the second section 5 bends more steeply outwards, with β = 90°. Ultimately, the second section 5 is then perpendicular to the ring structure 2.

[0042] The embodiments shown here can be produced, in particular, as composite materials with carbon fibers using an automated fiber placement (AFP) process. Pre-impregnated fiber composite material (primarily medium-stiffness fibers) is used. The bundles, e.g., of carbon fibers, are impregnated with epoxy resin and laid down at angles of 0°, +45°, -45°, and 90°. Through this staggered layup, the fibers can be arranged into variable cross-sections.

[0043] These manufacturing processes allow for the realization of the aforementioned variable cross-sectional shapes Q1, Q2 and / or the variable material arrangements M1, M2, as illustrated in the figures. As mentioned, this variability enables weight savings, since particularly stressed parts of the ring-shaped component 20 can be selectively reinforced.

[0044] Above all, the multi-angled (here two angles α, β) design of the first flange structure 1 allows it to be manufactured in one layer, in particular by using tapes with fibers at a 90° angle, so that the fibers are perpendicular to the axis of rotation R.

[0045] In one embodiment (see Fig. 1A The ring structure 2 is connected to a reinforcing structure 6 (e.g., by applying additional layers of the composite material or a metal part) or is formed in one piece during fiber deposition. This is particularly useful when, for example, larger mechanical loads act on a specific area of ​​the ring structure 2.

[0046] In the embodiment according to Fig. 1A A fire protection layer 13 is also arranged on the ring structure 2. Depending on the requirements, the fire protection layer 13 can be arranged partially or completely on the outer surface of the ring structure 2 to protect the outside against fire.

[0047] If the reinforcement structure 6 is made of or contains composite material, the fire-resistant layer 13 can cover the reinforcement structure 6. If the reinforcement structure 6 is made of metal or another refractory material, this is not strictly necessary; it is sufficient for the fire-resistant layer 13 to be arranged around the metal part.

[0048] In the Fig. 2, 2A A second embodiment is shown, wherein the Fig. 2 a view in the direction of the rotation axis R shows which the Fig. 1 is comparable, so the above description is generally applicable.

[0049] However, the front flange structure 1, which is shown in the sectional view of the Fig. 2A As shown, an additional feature is present, namely a foam core 8 inside the front flange structure 1 or a foam core 8 that is connectable to the front flange structure 1. The production of this foam core 8 is described in connection with the manufacturing process in the Fig. 6 , 7A und 7B more precisely shown. The integration of the ring-shaped component 20 with a foam core 8 with neighboring components is shown in Fig. 7C und 7D depicted.

[0050] As in the Fig. 2A As can be seen, the first flange structure 1 has a first angle α of 45° between the ring structure 2 and the first section 4. The second angle β between the ring structure 2 and the second section 5 of the first flange structure 1 is 90°. This allows for an efficient connection to an adjacent component.

[0051] In the Fig. 3 Figure 1 shows a detail that can be used in conjunction with one of the previously described embodiments. The perspective view shows, in the circumferential direction U of the ring structure 2, an area provided with an additional material 9 (patches), e.g., made of metal, such that the cross-section in this area is larger perpendicular to the axis of rotation R compared to the rest of the ring structure 2. The additional material 9 extends over the entire width (i.e., in the axial direction) of the ring structure 2. This corresponds approximately to the embodiment shown in Figure 2. Fig 1D as shown. In other embodiments, the additional material does not extend over the entire width.

[0052] This additional material 9 can, for example, also be a fire-resistant material to protect the underlying composite material of the ring structure 2 from high temperatures. As mentioned, this additional material does not cover the entire circumference of the ring structure 2, leaving room for further arrangements or connecting elements 7, which is described in the Fig. 4 , 4A is shown.

[0053] In Fig. 4 Figure 1 shows a side view of a portion of a ring-shaped component 20, in which additional materials 9', 9" are arranged within the ring structure 2. This results in a local increase in the cross-section in these areas. Additionally, a connecting element 7 is arranged, which is Fig. 4A The section is shown along line CC. A mounting device, not shown here, can be attached to the connecting element 7 (also called a stop element or "boss"). In the illustration of the Fig. 4A During manufacturing, the connecting element 7 is covered with a CFRP layer 18 (e.g. wound, laminated, draped, depending on the manufacturing process), and subsequently metallic threaded bushings 10 are inserted into the composite material 11.

[0054] In the Fig. 5, 5A , 5B Another embodiment is shown, wherein the view of the Fig. 5 with the view of Fig. 1 or 2 is comparable. The section line DD runs through the front flange structure 1, which is analogous to the embodiment according to Fig. 2A is equipped with a foam core 8 (see Fig. 5A The external geometry of the first flange structure 1 with the two differently angled areas corresponds to the embodiment in Fig. 2A . As in the first embodiment, the ring-shaped component 20 has a substantially U-shaped cross-sectional shape.

[0055] The cutting plane DD, which is in the Fig. 5A As shown, it passes through the axially outer area of ​​the front flange structure 1. The section line EE in Fig. 5B Figure 1 shows that individual parts of the foam filling 8 surrounding the radially inner region of the front flange structure 1 are connected by a dovetail structure 12. Thus, individual parts of the foam filling 8 can be inserted, and these are then held together by the dovetail structure 12.

[0056] In Fig. 6 A flowchart for an embodiment of a method for manufacturing a ring-shaped component 20 is shown.

[0057] In a first step 101, the base body of the ring-shaped component 20 is produced on a cone-shaped placement tool using a known AFP (Automated Fibre Placement) process.

[0058] This base body is then transferred to a flange forming machine (step 102). While the deposited laminate is heated, the base body is formed in the flange area to produce the flange structures 1 and 3 (step 103). The flange structures 1 and 3 are bent radially outwards. The formed component is then cooled (step 104).

[0059] In a subsequent step 105, a laminated foam core 8, i.e. a foam filling (see also Fig. 2A , 7A, 7B ), connected to the ring-shaped component 20.

[0060] The foam core 8 is prepared separately as a sub-assembly. In In a first step 201, CFRP layers 15 are laid / draped in a corresponding mold 14. The parts of the foam core 8 are assembled in step 202 and then, in the subsequent step 203, inserted into the mold with the prepared CFRP layers (see step 201). This is in Fig. 7A depicted.

[0061] Subsequently, in step 204, the CFRP layers 15 are folded over and draped so that they enclose the foam core 8, which in Fig. 7A as represented by the double arrow. The foam core 8 has a substantially triangular cross-sectional area, the shape of which can, in principle, be adapted to the design of the front flange structure 1.

[0062] In the Fig. 7B The joining of the foam core 8 with the ring-shaped component 20 is shown - indicated by the arrow pointing to the left - wherein the ring-shaped component 20 is arranged in a molding tool 16.

[0063] The base body of the ring-shaped component 20 and the foam core 8 are transferred to an autoclave and autoclaved under pressure and temperature (step 106). During this process, the ring-shaped component 20 made of composite material bonds with the foam core wrapped in the composite material, thus forming a single component.

[0064] After autoclaving, in step 107 the ring-shaped component 20 is demolded from the tray and in the subsequent step 108 mechanically machined. This can be done using a CNC machine. Flange bores and contours can also be produced.

[0065] As part of this manufacturing process, a fire-resistant layer 13 is also applied. This can be done after the foam core 8 is inserted in step 105. However, it is also possible for the fire-resistant layer 13 to be applied after the consolidation of the ring-shaped component 20 in the autoclave process (step 106).

[0066] In the Fig. 7C The right-hand side shows an annular component 20 with the connected foam core 8. The foam core 8 radially fills the space within the slope of the first annular section 4. Axially, the foam core 8 extends approximately to the plane of the outer surface of the front flange structure 1.

[0067] On the left, two adjacent components 30 and 31 connect to the annular component 20 with the foam core 8. The first adjacent component 30 is a structural component that can, for example, absorb mechanical loads. This component is connected to the front flange structure 1, for example, by a bolted connection. Radially inside the first adjacent component 30, a second adjacent component, namely a functional adjacent component 31, is arranged. This could, for example, be a honeycomb structure that serves to reduce the noise of a fan. The inner diameters of the annular component 20 (with the foam core) and the functional adjacent component 31 are essentially the same, so that a continuous gas path 40 is created inside. In this configuration, the foam core 8 fills the gap created by the slope of the first annular section.

[0068] In the Fig. 7D is an alternative embodiment to the embodiment according to Fig. 7C The above description can be referenced in principle. Instead of a foam core 8 in the transition area to the adjacent components 30, 31, a ring-shaped insert 17 with an angled cross-section is used. The manufacturing process according to Fig. 6 The process is particularly analogous.

[0069] Thus, the foam core 8 and the ring-shaped insert 17 are examples of inserts with which the ring-shaped component 20 can be connected. Bezugszeichenliste

[0070] 1 Front flange structure 2 Ring structure 3 Rear flange structure 4 First annular section 5 Second annular section 6 Reinforcement structure 7 Fastener 8 Foam core 9 Area with additional material (patch) 9' Area with additional material (patch) 9" Area with additional material (patch) 10 Threaded bushing in fastener 11 Composite material of fastener 12 Dovetail joint 13 Fire-resistant layer 14 Foam core mold 15 CFRP layer to encase the foam core 16 Ring-shaped component mold 17 Ring-shaped insert 18 CFRP layer to cover the fastener 20 ring-shaped component 30Adjacent structural component 31Adjacent functional component 40 continuous gas path F Flight direction M1 First material arrangement M2 Second material arrangement Q1 First cross-sectional shape Q2 Second cross-sectional shape R Axis of rotation U Circumferential direction α Angle between a first annular section of a flange structure and ring structure β Angle between a second annular section of a flange structure and ring structure γ Angle between rear flange structure and ring structure

Claims

1. Ring-shaped component (20) for an aircraft engine with a flange structure (1) at the front in the direction of flight (F), a flange structure (3) at the rear in the axial direction (R) and a ring structure (2) arranged in the axial direction (R) between the flange structures (1, 3), characterized by the fact that the ring structure (2) has a variable cross-sectional shape (Q1, Q2) and / or a variable material arrangement (M1, M2) in the circumferential direction (U) and / or perpendicular to the circumferential direction (U) and at least one of the flange structures (1, 3) has at least two annular sections (4, 5) in the circumferential direction (U), each of which is arranged at a different angle (α, β) relative to the ring structure (2).

2. Ring-shaped component (20) according to claim 1, characterized by the fact thata first angle (α) between the ring structure (2) and the first section (4) of the flange structure (1, 3), in particular the front flange structure (1), is between 10 and 60° and / or a second angle (β) between the ring structure (2) and the second section (5) of the flange structure (1, 3), in particular the front flange structure (1), is 90°.

3. Ring-shaped component (20) according to claim 1 or 2, characterized by the fact that an angle (γ) between the ring structure (2) and rear flange structure (3) is 90°.

4. Ring-shaped component (20) according to at least one of the preceding claims, characterized by the fact that at least one flange structure (1, 3) and / or the ring structure (2) is connected to a reinforcement structure (6) and / or a fire protection layer (13) or is formed in one piece with it.

5. Ring-shaped component (20) according to at least one of the preceding claims, characterized by the fact thatat least one area of ​​the cross-sectional shape (Q1, Q2) of the ring structure (2) has a cross-sectional extension in the circumferential direction around the center line.

6. Ring-shaped component (20) according to at least one of the preceding claims, characterized by the fact that at least one connecting element (7), a reinforcing structure (6) and / or a reinforcing element is arranged on the outside of the ring structure (2) and / or integrated within the ring structure (2).

7. Ring-shaped component (20) according to at least one of the preceding claims, characterized by the fact that the inside of the ring structure (2) is at least partially aerodynamically contoured.

8. Ring-shaped component (20) according to at least one of the preceding claims, characterized by the fact that the ring structure (2) and / or at least one of the flange structures (1, 3) are connected to an insert, in particular a foam core (8) or an annular insert (17).

9. Ring-shaped component (20) according to claim 8, characterized by the fact that Parts of an insert, in particular the foam core (8) and / or the ring-shaped insert (17), are connected by a dovetail joint (12).

10. Ring-shaped component (20) according to at least one of the preceding claims, characterized by the fact that it can be produced at least partially by a laying process or winding process, in particular with a staggered layup.

11. Ring-shaped component (20) according to claim 10, characterized by the fact that the laying method and / or the winding method and / or the respective material are different in at least two areas of the flange structures (1, 3) and / or the ring structure (2).

12. Aircraft engine comprising at least one annular component (20) according to at least one of the preceding claims, in particular as part of a housing for a turbofan drive, as part of a bypass channel of an aircraft engine or as part of an intermediate housing structure.

13. Method for manufacturing a ring-shaped component (20) according to at least one of claims 1 to 12, wherein at least one of the flange structures (1, 3) and / or the ring structure (2) is manufactured with wound fibers.

14. Method according to claim 13, characterized by the fact thata) a basic shape of an annular component (20) is created (101, 102), b) at least one layer (15) of composite material is arranged in a molding tool (14), wherein at least one layer (15) is placed on this layer (15) an insert, in particular a foam core (8) or an annular insert (17) (201, 202, 203), c) wherein the insert (8, 17) is encased by the at least one layer (15) (203, 204), and subsequently d) the insert (8, 17) is joined to the basic shape of the annular component (20), in particular in an autoclave.

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