Force-bearing casing structure

Abstract

The invention discloses a force-bearing casing structure, which belongs to the technical field of aero-engine design and manufacture, and comprises an integrated bearing seat integrated with a plurality of force-bearing support plates uniformly distributed along the circumferential direction; the turbine case surrounds the integrated bearing seat, and the turbine case is connected with the end, away from the integrated bearing seat, of the force bearing supporting plate so as to form a static load transmission path along the integrated bearing seat, the force bearing supporting plate and the turbine case; and the guide blade units are arranged on the bearing supporting plates respectively, all the guide blade units are combined together to form an annular whole circle of guide blades, and connecting structures allowing the guide blades to generate axial and / or radial thermal expansion are arranged between the guide blade units and the bearing seat. The technical problem that the comprehensive requirements of high-temperature adaptability and structure conciseness are difficult to consider in an existing scheme can be solved.

Description

Technical Field

[0001] The present invention relates to the technical field of aero-engine design and manufacturing, and specifically to a load-bearing casing structure. Background Art

[0002] With the continuous improvement of the thrust and thermal efficiency of aero-engines, the gas temperature continues to rise. The pre-turbine temperature of modern turbine engines has generally reached above 1600K, and some advanced models are even close to 2000K. Under the high-temperature gas working conditions, how to ensure the strength, stiffness and thermal stability of the key structures in the turbine section has become one of the key problems in engine structure design. In a three-rotor turbine engine, in order to replace the bearing support structure at the lower end of the combustion chamber, an inter-stage support system is usually arranged between the high-pressure turbine and the low-pressure turbine. This inter-stage support structure needs to simultaneously meet multiple functions such as flow guiding, load bearing, and sealing, and its design directly affects the structural integrity and operation reliability of the engine.

[0003] Currently, for this inter-stage support area, there are mainly the following two technical paths:

[0004] One is the integrated design of the load-bearing support plate and the bearing seat, and the split structure of the guide vanes before and after. In this scheme, the upper and lower flange plates of the front and rear split guide vanes extend out the mounting edges. The upper and lower mounting edges of the front half guide vanes are respectively aligned with and connected by bolts to the upper and lower mounting edges of the rear half guide vanes to form an integral guide vane. The integral guide vane is hung on the integrated load-bearing structure. This structure separates the flow guiding and load-bearing functions, which is beneficial to the development of large engines. However, the number of scattered parts of the split guide vanes increases, there are many connection interfaces, the assembly process is cumbersome, and there is a difficulty in gas sealing in the split area of the vanes.

[0005] The other is that the flow guiding part and the load-bearing part are designed as one body, and the guide vane not only undertakes the flow guiding function but also is a load-bearing structure. The usual support scheme is: one side of the upper flange plate of the guide vane extends out the mounting edge, and the mounting edge is rigidly connected to the casing mounting edge by bolts to transfer the load, and the other side is flexibly connected so that the guide vane can expand freely. The guide vane and the bearing seat are rigidly connected by bolts through the lower mounting edge. With the continuous increase of the temperature of the high-temperature gas in front of the turbine, the strength and stiffness of the load-bearing turbine guide vanes continue to decline, and at the same time, the manufacturing and processing of the integral ring guide vanes are difficult, which brings size limitations to the development of the engine.

[0006] Therefore, the existing schemes are difficult to balance the comprehensive requirements of high-temperature adaptability and structural simplicity. Summary of the Invention

[0007] The present invention provides a load-bearing casing structure to solve the technical problem that the existing schemes are difficult to balance the comprehensive requirements of high-temperature adaptability and structural simplicity.

[0008] According to one aspect of the present invention, a load-bearing casing structure is provided, which includes an integral bearing housing integrated with a plurality of load-bearing support plates evenly distributed in the circumferential direction; a turbine casing surrounding the integral bearing housing, and the turbine casing is connected to one end of the load-bearing support plate away from the integral bearing housing to form a static load transfer path along the integral bearing housing, the load-bearing support plate and the turbine casing; a guide vane unit, with one guide vane unit provided on each load-bearing support plate, and all the guide vane units jointly form an annular integral ring of guide vanes, and a connection structure allowing axial and / or radial thermal expansion of the guide vanes is provided between the guide vane unit and the bearing housing.

[0009] Optionally, the connection structure includes a support seat provided on the integral bearing housing, a groove is radially formed on the support seat, a boss is provided on the guide vane unit and is in clearance fit with the groove of the support seat.

[0010] Optionally, the support seat includes a front support and a rear support located on different sides of the load-bearing support plate respectively, the groove includes a front groove formed on the front support and a rear groove formed on the rear support, and the boss includes a front boss cooperating with the front groove and a rear boss cooperating with the rear groove.

[0011] Optionally, the front support is in sliding fit with the integral bearing housing axially, and a pin is passed through between the front support and the integral bearing housing to limit the circumferential rotation of the front support.

[0012] Optionally, a hook seat is provided on the turbine casing, a hook body is provided on the guide vane unit, and the hook body is axially snapped into the hook seat.

[0013] Optionally, the hook seat includes a front hook seat and a rear hook seat located on different sides of the load-bearing support plate respectively, and the hook body includes a front hook body cooperating with the front hook seat and a rear hook body cooperating with the rear hook seat.

[0014] Optionally, a metal sealing wire is provided between the front hook body and the front hook seat, and the metal sealing wire is used to seal the circumferential surfaces of the front hook body and the front hook seat.

[0015] Optionally, a retaining ring is provided on the rear hook seat, and the retaining ring cooperates with the axial end face of the rear hook body to limit the axial displacement of the guide vane unit.

[0016] Optionally, a convex ring for cooperating with the rear hook seat of the casing is provided on the rear hook body.

[0017] Optionally, a channel for connecting an air or lubricating oil pipeline is provided on the guide vane unit.

[0018] In summary, the present application includes at least one of the following beneficial technical effects:

[0019] First, through the integrated design of the load-bearing support plate and the bearing seat, the bolts or welded connections between the support plate and the bearing seat in the traditional structure are eliminated, significantly reducing the number of components, reducing the assembly workload, enhancing the structural stiffness and integrity, and solving the problems of difficult centering and unstable load-bearing caused by multiple connection points in the traditional split structure. Secondly, by designing the guide vane structure as a modular segmented unit, each vane unit is independently installed on the load-bearing support plate, avoiding the complex assembly of split guide vanes and the problem of gas sealing at the separation of split guide vanes, and significantly enhancing the flexibility of local manufacturing, quality control, and later replacement. Thirdly, by setting a connection structure between the guide vane and the bearing seat, the guide vane can freely expand axially and radially in the high-temperature gas environment, thereby effectively releasing the stress concentration caused by thermal expansion, avoiding structural deformation, fatigue cracks, or seal failure problems caused by limited thermal strain, and achieving a significant improvement in high-temperature adaptability. In summary, while meeting the thermal strain absorption requirements under the high-temperature working conditions of the gas turbine, this structure realizes the convenience of assembly and maintenance of the load-bearing structure and the flow guiding structure through integrated design and modular guide vane configuration, and solves the contradictory technical problems in the prior art that it is difficult to balance the structural simplicity and thermal adaptation ability.

[0020] In addition to the purposes, features, and advantages described above, the present invention has other purposes, features, and advantages. The following will refer to the drawings for a further detailed description of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] The drawings forming a part of this application are used to provide a further understanding of the present invention. The schematic embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation to the present invention. In the drawings:

[0022] Figure 1 is the front view of the load-bearing casing structure of the present invention;

[0023] Figure 2 is the structural schematic diagram of the integral bearing seat of the present invention;

[0024] Figure 3 is the cross-sectional view of the load-bearing casing structure of the present invention;

[0025] Figure 4 is the structural schematic diagram of the guide vane unit of the present invention;

[0026] Figure 5 is the schematic diagram of the full-circle guide vane composed of the guide vane units of the present invention;

[0027] Figure 6 is the installation schematic diagram of the guide vane unit of the present invention.

[0028] LEGEND DESCRIPTION:

[0029] 1. Integral bearing housing; 2. Guide vane unit; 3. Turbine casing; 4. Load-bearing support plate; 5. Connecting bolt; 6. Support bolt; 7. Front support; 8. Rear support; 9. Metal sealing wire; 10. Retaining ring; 21. Front hook body; 22. Rear hook body; 31. Front hook seat; 32. Rear hook seat; 23. Front boss; 24. Rear boss; 71. Front groove; 72. Slide groove; 73. Pin; 81. Rear groove; 12. Passageway. Detailed implementation manners

[0030] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings. However, the present invention can be implemented in many different ways defined and covered by the following.

[0031] The following will be further described in detail with reference to the attached Figures 1-6 This application will be further described in detail.

[0032] The embodiments of this application disclose a load-bearing casing structure.

[0033] Referring to Figure 1 , a load-bearing casing structure provided by the present invention includes an integral bearing housing 1, a load-bearing support plate 4, a turbine casing 3, and a plurality of guide vane units 2. Referring to Figure 2 , the integral bearing housing 1 is an integral structure, and a bearing cavity is provided inside it for installing a rotor bearing, which is the core load-bearing component of the entire inter-stage structure. To meet the requirements of structural stiffness and load transfer, a plurality of load-bearing support plates 4 are integrally formed along the circumferential direction on the outer periphery of the integral bearing housing 1. Each load-bearing support plate 4 extends radially outward and is evenly distributed along the circumferential direction.

[0034] The turbine casing 3 is arranged outside the integral bearing housing 1 and is fixedly connected to one end of each load-bearing support plate 4 away from the bearing cavity through a connecting bolt 5. This connection method enables the axial and radial static loads from the rotating shaft to be sequentially transmitted from the bearing housing to the load-bearing support plate 4 and then to the turbine casing 3, forming a complete and continuous static load transfer path. Since the load-bearing support plate 4 is an integrally formed part of the bearing housing, it can avoid the assembly deviation, connection looseness, or positioning error caused by multi-segment connection in the traditional structure, and improve the strength and installation accuracy of the overall structure.

[0035] Referring to Figure 3, each load-bearing support plate 4 is provided with a guide blade unit 2, and the guide blade unit 2 adopts a segmented design, and each unit includes two adjacent fixed guide blades to form a double structure. Multiple guide blade units 2 are installed on each load-bearing support plate 4 in sequence, and are combined along the circumferential direction to form a full circle of guide blades arranged in an annular manner, taking into account both manufacturing feasibility and assembly flexibility. The segmented blade structure is not only convenient for unit processing and independent quality control, but also convenient for replacing local components during assembly or maintenance, avoiding the complicated operation of replacing the entire ring of guide blades due to local damage in the full ring guide vane solution.

[0036] In order to meet the thermal deformation requirements under the high-temperature gas flow environment of the turbine section, a connection structure is provided between the guide vane unit 2 and the bearing seat, which allows the guide vanes to produce corresponding thermal expansion displacements in the axial and / or radial directions. By reasonably setting the installation gap, flexible matching parts, etc., the thermal stress of the guide vanes in high-temperature operation can be effectively released, and expansion blockage, instability or fatigue damage caused by structural limitations can be prevented, further improving the reliability and service life of the overall assembly structure in a thermal environment.

[0037] Specifically, the connection structure includes a support seat arranged on the integrated bearing seat 1, and a plurality of grooves are provided on the support seat in the radial direction. The guide blade unit 2 is provided with a boss structure that matches the groove of the support seat. During assembly, the boss of the guide blade unit 2 is inserted into the groove of the support seat from the radial direction to form a concave-convex fitting connection. A clearance fit is provided between the groove and the boss, and the clearance value is designed based on the operating temperature, the linear expansion coefficient of the material and the structural dimensions, so that the guide blade can achieve controllable free expansion under the action of thermal load, avoiding local stress concentration due to rigid constraints.

[0038] The support seat includes a front support 7 and a rear support 8 respectively located on different sides of the load-bearing support plate 4. The front support 7 is arranged on the side of the load-bearing support plate 4 close to the front edge of the guide blade unit 2, and the rear support 8 is arranged on the side close to the rear edge of the guide blade unit 2. The two together constitute a double-sided support structure for the front and rear ends of the guide blade unit 2. A front groove 71 is provided on the front support 7 for plugging and positioning with the front boss 23 on the guide blade unit 2; a rear groove 81 is provided on the rear support 8 for plugging and positioning with the rear boss 24 on the guide blade unit 2. The front boss 23 and the front groove 71, and the rear boss 24 and the rear groove 81 all adopt a clearance fit structure to avoid the rigid bite from limiting the thermal deformation of the guide blade. The concave and convex fitting section is generally a rectangular, trapezoidal or dovetail-shaped groove body, which can not only ensure the insertion and positioning strength, but also reserve sufficient thermal deformation stroke space.

[0039] The front support 7 is connected to the integral bearing housing 1 through a sliding fit, and the installation direction is axial insertion. A rigid axial fixing structure is not provided, enabling the front support 7 to have floating ability in the axial direction, thereby giving the entire guide vane unit 2 an expansion allowance space in the axial direction. Specifically, the front support 7 is provided with a chute 72 that cooperates with the chute 72 of the integral bearing housing 1. A pin 73 limiting structure is provided between the front support 7 and the bearing housing to limit the rotation of the front support 7 in the circumferential direction. The pin 73 is inserted into the mating hole to achieve reliable circumferential positioning, but does not limit its axial floating.

[0040] The rear support 8 is fixed to the bearing housing through the support bolts 6, enabling it to maintain stable positioning during operation without axial or circumferential displacement, thereby providing a reliable rear support surface for the guide vane unit 2. This bolt connection method has a simple structure and is firmly installed, ensuring that the support structure does not loosen or fall off in a high-temperature and high-load environment, and enhancing the connection rigidity and operation reliability of the entire guide assembly.

[0041] To further improve the connection stability between the guide vane unit 2 and the turbine casing 3 and prevent the guide vanes from being displaced or misaligned due to air flow impact or vibration during operation, a hook connection structure is provided between the guide vane unit 2 and the turbine casing 3. This hook structure not only ensures assembly reliability but also takes into account assembly simplicity and thermal expansion adaptability.

[0042] Multiple hook seats are provided on the turbine casing 3, located at the corresponding positions at the front and rear ends of the guide vane unit 2, including a front hook seat 31 and a rear hook seat 32. The front hook seat 31 is located on the turbine casing 3 near the inlet side of the guide vane for clamping and supporting the front end of the guide vane; the rear hook seat 32 is provided on the outlet side of the guide vane for limiting and fixing the rear end of the guide vane. The hook seats are arranged at intervals along the circumferential direction of the turbine casing 3, matching the arrangement pitch of the entire ring of guide vanes, forming an annular surrounding structure.

[0043] Hook bodies that cooperate with the hook seats are provided on the guide vane unit 2, including a front hook body 21 provided at the front end of the vane unit and a rear hook body 22 at the rear end. The front hook body 21 is formed as a hook-shaped protrusion with a locking section at the end that can be inserted into the front hook seat 31; the rear hook body 22 is relatively simplified and mainly serves as a limiting structure, forming a lapping fit with the rear hook seat 32. Both hook body structures extend along the axial direction, facilitating positioning during assembly through axial insertion.

[0044] During the assembly process, first insert the front boss 23 and the rear boss 24 of the guide vane unit 2 into the front support 7 and the rear support 8 grooves on the bearing housing in sequence to complete the plug-in fit between the guide vane and the integral bearing housing 1. Subsequently, push the guide vane inward from the outside so that the front hook body 21 aligns with the front hook seat 31 and snaps in along the axial direction to form a front-end snap-in positioning. Continue to push the guide vane until it is in the fully installed state, so that the rear hook body 22 overlaps and cooperates with the rear hook seat 32 to complete the structural limit of the entire guide vane unit 2. The assembly sequence is clear and the operation is simple, which is suitable for on-site rapid assembly. In terms of the structural coordination relationship, the basic support and thermal deformation release functions are realized between the guide vane unit 2 and the support seat through concave-convex plug-in, while the hook structure between the guide vane unit 2 and the turbine casing 3 further provides external locking and axial limit functions. This double-layer support structure not only ensures the stable positioning of the guide vane, but also provides a thermal strain compensation channel for it, avoiding deformation or wear caused by rigid constraints, and effectively improving the service life and reliability of the overall guide structure.

[0045] To ensure the sealing effect between the guide vane unit 2 and the turbine casing 3 and effectively control the axial and circumferential thermal displacements of the guide vane in a high-temperature environment, a sealing and limiting structure is further provided on the basis of the hook connection structure. This structure not only improves the tightness of the gas passage, but also enhances the thermal adaptability through a flexible positioning method.

[0046] A metal sealing wire 9 is provided between the hook body at the front end of the guide vane unit 2 and the front hook seat 31, and the sealing wire is arranged on the circumferential mating surface between the hook body and the hook seat. The metal sealing wire 9 usually adopts a corrugated wire, a braided sealing strip or a flexible metal strip structure, which can adapt to the circumferential thermal expansion of the blade at high temperature while ensuring sealing. After the assembly is completed, the sealing wire adheres to the hook body and the hook seat in a compressed state, and can automatically adjust its shape with the thermal deformation of the blade during the operation of the engine to ensure that the sealing surface is continuously fitted, thereby suppressing the leakage of high-temperature and high-pressure gas and improving the turbine thermal efficiency and operation safety.

[0047] A limiting retaining ring 10 is provided between the hook body at the rear end of the guide vane unit 2 and the rear hook seat 32 to limit the free movement of the guide vane in the axial direction. The retaining ring 10 is fixed to the rear hook seat 32 by snap connection or screw installation, and its front end face forms an axial stop fit with the rear end face of the hook body. In the assembled state, the guide vane is inserted forward to a preset position, and the rear hook body 22 finally abuts against the retaining ring 10 to form a clear axial positioning surface, preventing the blade from moving backward due to heat flow impact, vibration or centrifugal force during operation.

[0048] To further enhance the positioning effect of the retaining ring 10, a locally protruding ring structure protruding radially outward is also provided at the rear end of the rear hook body 22, and the ring forms a socket fitting relationship with a local groove on the inner wall of the casing. This structure provides a mechanical stop function for axial limit on the one hand, and realizes two-way constraint and improves the installation accuracy and connection stability of the guide vane through the circumferential locking assistance of the ring and the groove on the other hand. Through the sealing and limiting structure formed by the metal sealing wire 9 and the retaining ring 10, the guide vane unit 2 can not only maintain good sealing performance under high-temperature, high-speed, and high-pressure gas conditions, but also has the ability to adapt to thermal expansion and structural integrity, significantly improving the thermal reliability and long-term service performance of the turbine guide system.

[0049] To achieve the cooling and lubrication functions of the bearing cavity, the guide vane is designed to be hollow, facilitating the threading of the cooling air pipeline and the lubricating oil pipeline 12, and forming a complete fluid path through system with the bearing housing and the turbine casing 3.

[0050] The passage 12 is arranged inside the body of the guide vane unit 2 and is distributed in a ring shape, consistent with the circumferential layout of the entire guide system. Each pipeline is evenly distributed in the circumferential direction, and the layout pitch is coordinated with the spacing of the guide vanes to avoid problems such as uneven flow distribution or concentrated thermal load.

[0051] The air pipeline and the lubricating oil pipeline are end-connected between the guide vane unit 2, the bearing housing, and the turbine casing 3 through methods such as threaded interfaces, dovetail groove clamping, and sealing ring docking, and auxiliary structures such as metal bellows, flexible connection segments, or limit sheaths are used to compensate for the interface deviation caused by thermal expansion or assembly errors, improving the overall sealing performance and adaptability of the system. By setting the air pipeline and the lubricating oil pipeline, not only the temperature control ability and the structural lubrication effect in the area around the guide vane are improved, but also the long-term operation reliability of the overall support system under high-temperature and high-speed conditions is enhanced, reducing risks such as local thermal instability, dry friction wear, or lubrication failure, and effectively extending the service life and maintenance cycle of the components.

[0052] During the assembly process, first install the integrated bearing housing 1 on the intermediate casing or frame structure of the engine, ensure that the bearing cavity is coaxial with the rotating shaft, and complete the installation and positioning of the bearing components. Each load-bearing support plate 4 is provided with an installation reference area for inserting the guide vane unit 2, forming the basic interface for subsequent assembly.

[0053] Refer to Figure 4 and Figure 5 In a specific implementation manner, the entire circle of guide vanes is divided into seven segments, each segment is a guide vane unit 2, and each guide vane unit 2 includes two adjacent integrated guide vanes forming a double-link structure, which are respectively installed on the corresponding load-bearing support plates 4 on the outer periphery of the integrated bearing housing 1. The seven guide vane units 2 form a complete annular guide structure.

[0054] Reference Figure 6 Figure 6 , the installation of the guide vane unit 2 is carried out sequentially in the circumferential direction, generally starting from the top of the casing or a specific numbered reference position, and inserted one by one in a predetermined order. Each guide vane unit 2 is inserted from the outside towards the axial center direction, and its front boss 23 and rear boss 24 are respectively aligned with the front groove 71 and rear groove 81 on the front support 7 and rear support 8. During the insertion process, ensure that the insertion depth and angle are consistent to avoid jamming or offset. After completing the assembly of all guide vane units 2 in sequence, an integral closed annular guide structure is formed overall.

[0055] The front and rear supports 8 are respectively assembled on the front and rear sides of the load-bearing support plate 4. The front support 7 is inserted into the opening part of the load-bearing support plate 4 by means of axial sliding and is in floating fit with the bearing housing. The rear support 8 is fixedly connected to the integrated bearing housing 1 by bolts and serves as the structural support for the rear end of the guide vane. A pin 73 is inserted between the front support 7 and the bearing housing for circumferential position limitation to prevent rotational offset during operation, and at the same time, it allows a small movement in the axial direction to adapt to the thermal expansion stroke of the guide vane.

[0056] Subsequently, the guide vane unit 2 is pushed inward so that the front hook body 21 is aligned with and snapped into the front hook seat 31 on the turbine casing 3 to form a snap-fit. Continue to insert the guide vane until the rear hook body 22 is lapped with the rear hook seat 32 to complete the circumferential installation of the entire section of the guide vane. To enhance the sealing performance, a metal sealing wire 9 is inserted between the front hook body 21 and the hook seat to achieve gas sealing in an elastic fitting manner and allow circumferential thermal expansion compensation. After the rear hook body 22 is positioned, a limit retaining ring 10 is sleeved on its end. The retaining ring 10 cooperates with the convex ring structure on the hook body to form an axial limit stop to prevent the blade from moving backward or loosening due to vibration or thermal drift.

[0057] Compared with the traditional structure, the present invention has achieved significant optimization in aspects such as the guide vane support method, load-bearing structure layout, thermal deformation release mechanism, and assembly process adaptability, and has the following comprehensive technical advantages and engineering application values:

[0058] Compared with the traditional integral ring guide vane structure, the integral ring guide vane usually adopts the integral casting method. Although it has advantages in terms of aerodynamic continuity, the manufacturing difficulty increases significantly after the structural size increases, especially when there is a design requirement for a cooling inner cavity, and the integral forming has approached the limit. However, this structure divides the guide vane into multiple double-link units and realizes the whole-circle arrangement through modular insertion, significantly reducing the manufacturing difficulty and defective rate, and at the same time avoiding the problems of circumferential jamming or fracture of the integral ring guide vane due to uneven thermal expansion in a high-temperature environment.

[0059] Compared with the existing split load-bearing structures, in the traditional solution, the load-bearing support plate and the bearing seat are connected by welding or bolts to form an assembly, which has problems such as a large number of parts, many connection interfaces, high requirements for assembly accuracy, and large error accumulation. Through the integrated structural design of the bearing seat and the load-bearing support plate, the present invention fundamentally eliminates the key connection interfaces, simplifies the load-bearing path, and improves the overall structural stiffness and operating stability.

[0060] In terms of the assembly process, this structure constructs a complete modular blade assembly process through methods such as concave-convex fitting and insertion, hook positioning, flexible sealing with sealing wires, and snap ring limiting. Each unit blade is assembled independently without interference, facilitating quick installation, position reproduction, and local replacement. Compared with the traditional structure that requires whole-ring disassembly and unified positioning, it significantly improves the assembly simplicity and the later maintenance efficiency.

[0061] In terms of thermal environment adaptability, the structure is provided with clearance fit structures, sliding connection structures for front and rear supports, and circumferential release structures for sealing wires, realizing thermal expansion compensation of the guide vane in three directions: axial, radial, and circumferential. This thermal deformation coordination mechanism effectively avoids problems such as stress concentration, jamming, or thermal fatigue failure commonly existing in traditional rigid connection structures, and improves the service life of the structure under high-temperature conditions.

[0062] While reducing the number of parts, simplifying the assembly steps, and improving the maintenance efficiency, the structure of the present invention reduces structural redundancy, increases the power-to-weight ratio, and is conducive to the lightweight design and high-performance development of the engine. At the same time, the modular segmented solution reduces the manufacturing difficulty and quality control difficulty of single components, is applicable to various engine size levels, and has good versatility and engineering promotion value.

[0063] The above are only the preferred embodiments of the present invention and are not intended to limit the present invention. For those skilled in the art, the present invention can have various changes and modifications. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.

Claims

1. The structure of the load-bearing casing, characterized in that: including, an integral bearing housing (1) with a plurality of load-bearing support plates (4) integrally formed on its outer periphery and evenly distributed circumferentially; a turbine casing (3) surrounding the integral bearing housing (1), and the turbine casing (3) is connected to one end of the load-bearing support plate (4) away from the integral bearing housing (1) to form a static load transfer path along the integral bearing housing (1), the load-bearing support plate (4) and the turbine casing (3); a guide vane unit (2) provided on the load-bearing support plate (4), and the guide vane units (2) on the plurality of load-bearing support plates (4) jointly form an annular integral circle of guide vanes, and a connection structure allowing axial and / or radial thermal expansion of the guide vanes is provided between the guide vane unit (2) and the integral bearing housing (1).

2. The load-bearing casing structure according to claim 1, wherein: The connection structure includes a support seat provided on the integral bearing housing (1), a groove is radially formed on the support seat, a boss is provided on the guide vane unit (2) and is matched with the groove of the support seat, and a clearance fit is provided between the boss and the groove.

3. The load-bearing casing structure according to claim 2, wherein: The support seat includes a front support (7) and a rear support (8) respectively located on different sides of the load-bearing support plate (4), the groove includes a front groove (71) formed on the front support (7) and a rear groove (81) formed on the rear support (8), and the boss includes a front boss (23) matched with the front groove (71) and a rear boss (24) matched with the rear groove (81).

4. The load-bearing casing structure according to claim 3, wherein: The front support (7) is slidably matched with the integral bearing housing (1) axially, and a pin (73) is inserted between the front support (7) and the integral bearing housing (1) to limit the circumferential rotation of the front support (7).

5. The load-bearing casing structure according to claim 1, wherein: A hook seat is provided on the turbine casing (3), and a hook body is provided on the guide vane unit (2), and the hook body is axially clamped into the hook seat.

6. The load-bearing casing structure according to claim 5, wherein: The hook seat includes a front hook seat (31) and a rear hook seat (32) respectively located on different sides of the load-bearing support plate (4), and the hook body includes a front hook body (21) matched with the front hook seat (31) and a rear hook body (22) matched with the rear hook seat (32).

7. The load-bearing casing structure according to claim 6, wherein: A metal sealing wire (9) is provided between the front hook body (21) and the front hook seat (31), and the metal sealing wire (9) is used to seal the circumferential surfaces of the front hook body (21) and the front hook seat (31).

8. The load-bearing casing structure according to claim 6, wherein: A retaining ring (10) is provided on the rear hook seat (32), and the retaining ring (10) is matched with the axial end face of the rear hook body (22) to limit the axial displacement of the guide vane unit (2).

9. The load-bearing casing structure according to claim 8, wherein: A convex ring for cooperating with the inner wall of the casing rear hook seat (32) is provided on the rear hook body (22).

10. The load-bearing casing structure according to claim 1, wherein: The guide vane unit (2) is provided with a passage (12) for connecting an air pipeline or a lubricating oil pipeline.

Images