Rotor wheel disc and aero-engine
By using an integrated rotor disk, the problems of large weight and insufficient reliability of existing aero-engine rotor disks have been solved, achieving both lightweighting and improved reliability of the engine.
Patent Information
- Application Number
- CN202520177806.1
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-01-27
- Publication Date
- 2025-11-25
- Estimated Expiration
- 2035-01-27
AI Technical Summary
In existing aero-engine rotor disks, each stage of the rotor is manufactured independently, resulting in large overall weight, complex manufacturing, and insufficient reliability of the inter-stage connection structure, which affects engine weight reduction and reliability.
The rotor disk with an integrated structure, including hub, bladed disk and fused web, is manufactured by 3D printing or laser cladding, which reduces axial joints, lowers rotor weight and improves reliability.
The rotor structure was simplified, the engine rotor mass was reduced, the overall economy and reliability of the engine were improved, and the assembly and maintenance difficulty was reduced.
Smart Images
Figure CN223594239U_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The utility model belongs to the field of aero-engine, concretely relates to a rotor wheel disc and aero-engine. BACKGROUND
[0002] The aero-engine rotor disc usually comprises a multi-stage structure, the high-pressure compressor disc of a large-bypass-ratio turbofan engine can reach 8-10 stages, and the low-pressure turbine usually has 4-6 stages. In the existing engine, each stage rotor disc is usually independently manufactured, and then is axially connected together by welding or mechanical connection. Since each stage rotor has a hub structure, the overall weight of the rotor is large, and the manufacturing process is complex, the inter-stage connection structure has insufficient reliability, and is not conducive to the weight reduction and reliability improvement of the aero-engine. Therefore, providing a multi-stage rotor integrated rotor disc has positive significance for reducing the weight of the engine and improving the economy of the engine. SUMMARY
[0003] The utility model discloses a rotor wheel disc and aero-engine, and aims at reducing the weight of the aero-engine rotor.
[0004] According to the embodiment of one aspect of the utility model, a rotor wheel disc is provided.
[0005] The rotor wheel disc comprises a hub, a blade disc and a fusion web, and the hub, the blade disc and the fusion web are configured as an integral forming structure.
[0006] The blade disc comprises a plurality of stages of blade discs arranged along the axial direction, and a plurality of blades are arranged on the blade disc in the circumferential direction.
[0007] The fusion web comprises a first end located on the radially inner side and a second end located on the radially outer side, the second end is formed with a plurality of butt joint branches arranged in parallel, the first end is connected to the hub, and each butt joint branch of the second end is connected to one blade disc, and a hollow cavity is formed between the butt joint branches.
[0008] The rotor wheel disc adopts a single hub and a fusion web, which can effectively simplify the structure of the rotor wheel disc, improve the reliability of the rotor wheel disc by reducing the welding and mechanical connection structure, effectively reduce the mass of the engine rotor, and be conducive to improving the overall economy of the aero-engine.
[0009] Further, in some embodiments, the axial position of the hub coincides with the axial position of the center of mass of the rotor wheel disc.
[0010] Further, in some embodiments, one of the butt joint branches is arranged on the radial extension line of the hub.
[0011] Further, in some embodiments, the cross-sectional shape of the fusion web is rectangular, triangular, semicircular, arc-triangular or polygonal.
[0012] Further, in some embodiments, the rotor disc comprises at least three stages of the blade disc.
[0013] Further, in some embodiments, the abutment branch is arranged on the radial extension line of the hub at the position close to the connection position of the one end of the hub.
[0014] Further, in some embodiments, at least part of the hollow chamber is provided with a through hole, so that the hollow chamber is in communication with the outside.
[0015] Further, in some embodiments, the corner position of the hollow chamber is provided with a filling structure, and the filling structure has a porous structure.
[0016] Further, in some embodiments, the porous structure comprises a grid structure, a three-periodic curved surface single cell hollow structure or a lattice structure.
[0017] According to an embodiment of the other aspect of the utility model, an aero-engine is provided, comprising a rotor disc, wherein the rotor disc adopts the rotor disc adopted in any of the foregoing embodiments. BRIEF DESCRIPTION OF DRAWINGS
[0018] Figure 1 Fig. 1 is a schematic view of the cross-sectional structure of an aero-engine in an embodiment;
[0019] Figure 2 Fig. 2 is a schematic view of the cross-sectional structure of an aero-engine in a comparative example;
[0020] Figures 3a-3f Fig. 3 is a schematic view of the cross-sectional structure of a rotor disc in a plurality of embodiments;
[0021] Figure 4a Fig. 4 is a schematic view of the cross-sectional structure of a rotor disc in another embodiment;
[0022] Figure 4b Fig. 5 is a schematic view of the cross-sectional structure of a rotor disc in still another embodiment;
[0023] Figure 5 Fig. 6 is a schematic view of the cross-sectional structure of a rotor disc in yet another embodiment;
[0024] Figure 6 Fig. 7 is a schematic view of the through hole of a rotor disc in an embodiment.
[0025] Meaning of reference signs: 1-hub; 2-fusion web; 21-first end; 22-abutment branch; 23-hollow chamber; 3-blade disc; 4-rotor axis; 5-through hole; 6-filling structure.
[0026] The above-mentioned drawings are intended to make a detailed description of the present application, so that those skilled in the art can understand the technical concept of the present application, and are not intended to limit the present application. In order to express concisely, the above-mentioned drawings only schematically draw the structures related to the technical features of the present application, and do not draw the complete structures and all details strictly according to the actual proportion. DETAILED DESCRIPTION
[0027] The present application will be further described in detail below with reference to the drawings.
[0028] Reference herein to "an embodiment" means that a particular feature, structure, or characteristic described in connection with the embodiment can be included in at least one embodiment. The appearances of the phrase "in an embodiment" or "in other embodiments" in various places in the specification are not necessarily referring to the same embodiment, nor are separate or alternative embodiments mutually exclusive of other embodiments. Those skilled in the art will appreciate that embodiments of the present application can be combined with other embodiments in various ways without resulting in contradictions in structure.
[0029] In the description of the present application, unless otherwise explicitly specified and limited, the technical terms "mounting", "connection", "connecting" and the like should be understood in a broad sense, for example, can be movable connection, can also be fixed connection or integral. For those skilled in the art, the specific meaning of the above terms in the embodiments of the present application can be understood according to the specific circumstances.
[0030] In the description of the present application, the terms indicating the orientation or position relationship such as "upper", "lower", "left", "right", "transverse", "longitudinal", "height", "length", "width" and the like are intended to accurately describe the embodiments and simplify the description, and are not intended to limit the parts or structures involved to have a specific orientation, to be installed or operated in a specific orientation, and cannot be understood as a limitation on the embodiments herein.
[0031] In the description of the present application, the terms "first", "second" and the like are only used to distinguish different objects, and cannot be understood as indicating relative importance or limiting the number, specific order or primary and secondary relationship of the described technical features. In the description of the present application, the meaning of "a plurality of" is at least two.
[0032] The aero-engine includes a multi-stage rotor, and at present, its structure is generally as shown in Figure 2As shown, a plurality of rotor discs are arranged axially along the rotor axis 4, each rotor disc has an independent hub 1, the hub 1 is fixedly connected with the blade disc 3 radially outside, and the adjacent rotor discs need to be axially connected through welding or bolts and other mechanical structures. This structure not only increases the overall weight of the engine rotor, but also is prone to failure at the welding joint or mechanical connection position under long-term high-temperature and high-frequency working conditions, affecting the overall reliability of the engine. And the existing engine rotor disc is usually manufactured by casting or forging process, which is difficult to further optimize the overall structure due to process limitations.
[0033] With the development of advanced manufacturing processes such as 3D printing technology and laser cladding forming technology, it creates conditions for designing and manufacturing rotor wheels with more complex structures. The embodiment of the utility model provides an engine rotor wheel, which simplifies the structure of the aero-engine rotor, connects the multi-stage blade disc to the same hub by using an integrated structure, reduces the number of axial joints, and reduces the weight of the rotor part.
[0034] In one embodiment, the aero-engine structure using the rotor wheel is as shown in Figure 1 Two engine rotor wheels are arranged axially along the rotor axis 4, each rotor wheel includes a hub 1, a fusion web 2 and a plurality of blade discs 3, and specifically in the embodiment shown in Figure 1 Each rotor wheel has three blade discs 3. Among them, the hub 1, the fusion web 2 and the three blade discs 3 are configured as an integrated structure, which can be manufactured by 3D printing or laser cladding forming process. The hub 1 in each rotor wheel is sleeved on the engine rotating shaft (not shown) and is coaxially arranged with the rotor axis 4. The blade discs 3 are arranged axially, and a plurality of rotor blades are arranged circumferentially on the blade discs. The radially inner side of the fusion web 2 is the first end 21, which is connected with the hub 1; the radially outer side is divided into a plurality of butt branches 22, each butt branch 22 is connected with one blade disc 3, and a hollow chamber 23 is formed between adjacent butt branches 22.
[0035] Compared with the scheme shown in Figure 2 The rotor wheel reduces the number of hubs 1 in the axial direction, effectively reduces the overall weight of the engine, reduces the number of parts on the rotor axis 4, and reduces the assembly and maintenance difficulty; at the same time, since the blade discs 3 belonging to the same rotor wheel are integrally formed, the welding interface or mechanical connection structure in the axial direction is reduced, the structure such as tenon, mortise and locking device is simplified, the reliability of the part under long-term service condition is effectively improved, and the overall aerodynamic performance of the rotor wheel is improved; the hollow chamber 23 further reduces the overall weight of the rotor wheel, and effectively improves the overall economy of the engine.
[0036] In a preferred embodiment, the position of the hub 1 in the axial direction coincides with the position of the overall center of mass of the rotor disc in the axial direction, so as to avoid additional torque caused by the non-coincidence of the center of mass and the hub 1, which affects the stability of the engine.
[0037] In different embodiments, the cross section of the fusion web 2 can be configured in different shapes, such as Figure 3a as shown, can be configured as a rectangle; as shown in Figure 3b , Figure 3c as shown, can be configured as a polygon; as shown in Figure 3d as shown, can be configured as a triangle; as shown in Figure 3e as shown, can be configured as a semicircle; as shown in Figure 3f as shown, can also be configured as an arc-triangle. The specific structure and size of the fusion web 2 can be flexibly designed by using topology or shape optimization methods according to the load distribution of the rotor disc, stress analysis under specified working conditions.
[0038] In a preferred embodiment, each rotor disc includes at least three stages of blade discs 3. In some embodiments, as shown in Figure 1 the butt-joining branches 22 of the fusion web 2 correspond one-to-one to the blade discs 3. In other embodiments, as shown in Figure 4a the number of blade discs 3 can also be greater than the number of butt-joining branches 2, the fusion web 2 of the rotor disc has two butt-joining branches 22, and each butt-joining branch is connected to one blade disc 3 at its radially outer end, and another blade disc 3 is arranged between the two blade discs 3.
[0039] In a further preferred embodiment, as shown in Figure 4b one of the butt-joining branches 22 of the fusion web 2 is arranged on the radial extension line a of the hub 1.
[0040] In a further preferred embodiment, as shown in Figure 4b the rotor disc has five butt-joining branches 22 and five stages of blade discs 3 corresponding one-to-one to the butt-joining branches 22, and four hollow chambers arranged in the axial direction are formed between adjacent butt-joining branches 22. Among the five butt-joining branches 22 of the fusion web 2, one butt-joining branch 22 is arranged along the radial extension line a of the hub 1 as a whole, and the connection positions of the remaining four butt-joining branches 22 close to one end of the hub 1 also fall on the radial extension line a of the hub 1. Such a structure is conducive to the force balance of the rotor disc as a whole.
[0041] In a preferred embodiment, as shown in Figure 5As shown, the corner positions formed between the butt-joining branches 22 and between the butt-joining branches 22 and the blade disc 3 in the hollowed-out cavity 23 are provided with a filling structure 6 having a porous structure, which in different embodiments can be provided as a grid structure, a dot matrix structure or a three-periodic curved surface unit hollow structure. The filling structure 6 serves to improve the stress concentration of the transition zone of the fusion web 2, while not significantly increasing the overall weight of the structure. The filling structure 6 can be integrally formed with other structures of the rotor disc by a 3D printing process, and the specific shape and filling range thereof can be determined according to the stress analysis results of the rotor disc.
[0042] In a preferred embodiment, as shown in Figure 6 As shown, the axial wall of the fusion web 2 is provided with a through hole 5, so that the hollowed-out cavity 23 is connected to the outside, so as to improve the overall cooling performance of the rotor disc. The through hole 5 can be a circular hole, an oval hole or a long hole, and the shape of the hole should be parallel to the main stress direction of the disc to avoid sharp angles and prevent stress concentration. The through hole 5 should be symmetrically distributed in the circumferential direction to ensure the stability of the rotor disc during high-speed rotation. The through hole 5 can further reduce the overall weight of the rotor disc, and can also be used to discharge the powder remaining in the hollowed-out cavity 23 during the 3D printing process. The through hole 5 can be formed during the 3D printing process, or can be formed by mechanical processing after the rotor disc is integrally formed.
[0043] The rotor disc provided in the above embodiments can be integrally manufactured using the same material, or can be manufactured using different materials. For example, the hub 1, the fusion web 2 and the blade disc 3 can be formed using different alloy powders by 3D printing or laser cladding process; or different alloy powders with a gradient transition from the center to the outer edge of the rotor disc can be used for manufacturing.
[0044] In different embodiments, the aero-engine using the rotor disc provided in the above embodiments can use a single rotor disc, or a plurality of rotor discs can be used in series, or the rotor disc can be used in cooperation with a traditional single-blade rotor disc. When a plurality of rotor discs are used in series, each rotor disc can have the same number of blade stages, or different numbers of blade stages.
[0045] The aero-engine using the rotor disc can effectively reduce the structural weight and improve the aerodynamic efficiency and reliability of the engine.
[0046] In other embodiments, the rotor disc provided in the above embodiments can be used in a high-bypass-ratio turbofan engine, and can also be used in a small-bypass-ratio turbofan engine, a turbojet engine, a turboshaft engine or a gas turbine power device.
[0047] The purpose of the above embodiments is to make further detailed description of the utility model in combination with the drawings, so that the technical concept of the utility model can be understood by the person skilled in the art. Within the scope disclosed by the utility model, the optimization or equivalent replacement of the parts structure involved, and the combination of the implementation manners in different embodiments without structural and principle conflicts, all fall within the protection scope of the utility model.
Claims
1. A rotor wheel, characterized in that, the rotor wheel comprises a hub, a blade disc and a fusion web, the hub, the blade disc and the fusion web are configured as an integrally formed structure; the blade disc comprises a plurality of stages of blade discs arranged in an axial direction; the fusion web comprises a first end located at a radially inner side and a second end located at a radially outer side, the second end is formed with a plurality of butt-joining branches arranged in parallel, the first end is connected to the hub, each of the butt-joining branches of the second end is connected to one of the blade discs respectively; hollow cavities are formed between the butt-joining branches.
2. The rotor wheel disc according to claim 1, characterized in that The axial position of the hub coincides with the axial position of the center of mass of the rotor wheel.
3. A rotor wheel disc according to claim 1 or 2, characterised in that One of the butt-joining branches is arranged on the radial extension line of the hub.
4. A rotor wheel disc according to claim 1 or 2, characterised in that The cross-sectional shape of the fusion web is rectangular, triangular, semicircular, arc-triangular or polygonal.
5. The rotor wheel disc according to claim 1 or 2, characterized in that The rotor wheel comprises at least three stages of the blade discs.
6. The rotor wheel disc according to claim 1 or 2, characterized in that The connection position of one end of the butt-joining branch close to the hub is arranged on the radial extension line of the hub.
7. A rotor wheel disc according to claim 1 or 2, characterised in that At least part of the hollow cavities is provided with a through hole, so that the hollow cavities are connected to the outside.
8. The rotor wheel disc according to claim 1 or 2, characterized in that The corner position of the hollow cavity is provided with a filling structure, and the filling structure has a porous structure.
9. The rotor wheel disc according to claim 8, characterized in that The porous structure comprises a grid structure, a three-periodic curved surface single cell hollow structure or a lattice structure.
10. An aeroengine comprising a rotor disc, characterised in that, The rotor wheel adopts the rotor wheel of any one of claims 1 to 9.