Turbine disc shaft connecting structure and aero-engine

Abstract

The invention discloses a turbine disc shaft connecting structure and an aero-engine, the engine comprises a turbine shaft, a turbine stator part, a turbine first-stage rotor and a turbine second-stage rotor, the turbine disc shaft connecting structure comprises a flexible connecting structure, and the flexible connecting structure is formed on an inner ring of the turbine first-stage rotor; the cross section of the flexible connecting structure is of a back-bending structure so that the connecting rigidity of the turbine first-stage rotor and the turbine shaft can be reduced. The disc center of the turbine first-stage rotor and the disc center of the turbine second-stage rotor are arranged to be larger than the preset size, the turbine second-stage rotor is connected with the turbine first-stage rotor, and an avoiding space is formed in the side, facing the turbine stator piece, of the flexible connecting structure, so that the turbine stator piece is provided with the turbine first-stage rotor. And the space is arranged in the disc center of the secondary rotor of the turbine. Energy generated in the working process of the wheel disc is stored and released in an elastic potential energy mode, so that displacement deformation generated at the matching position of the two-stage turbine disc due to the centrifugal force effect is reduced, and the disc and shaft coaxiality matching requirement during high-speed operation of the turbine is met.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft engines, and in particular, to a turbine disk-shaft connection structure. In addition, the present invention also relates to an aircraft engine comprising the turbine disk-shaft connection structure. Background Art

[0002] The power turbine of a high-performance, low-fuel-consumption turbine engine in the prior art often has a multi-stage turbine disk. In order to facilitate the processing of the turbine disk and the assembly of the engine, the turbine disk is usually not designed with a complex structure. The disks are connected by short shaft necks extending from the wheel center and fixed by large bolts. The disks are also connected to the turbine shaft by stop flanges and bolts. Figure 1 The entire rotor has a large cantilever configuration, which leads to at least the following problems: 1) The distance between the turbine disk and bearing No. 1 is too large, causing the bearing to bear too much load; 2) Since the turbine disk and the turbine shaft are connected by bolts, the installation process is complicated and the reliability is low during operation. In addition, the bolt holes near the wheel center will reduce the low-cycle fatigue life of the turbine disk. 3) The turbine disc structure adopts a rigid design. The displacement deformation caused by centrifugal force at the disc-shaft joint causes the disc and shaft to fail to meet the coaxiality requirements. Precision bolts are used for centering between the discs and the disc shaft, and the mismatch in deformation between parts will generate additional shear force on the bolts. 4) The turbine disk adopts a rigid structure and cannot buffer the load. It is easy to cause stress concentration in the local area, leading to damage. In addition, the deformation and load caused by the gyroscopic torque under the rigid connection structure directly act on the bearing, causing the bearing to bear too much load. Summary of the invention

[0003] The present invention provides a turbine disk-shaft connection structure and an aircraft engine, so as to solve the technical problem that the supporting bearing of the engine power turbine rotor bears too much load due to the excessively long cantilever.

[0004] According to one aspect of the present invention, there is provided a turbine disk-shaft connection structure, which is applied to a turbine engine. The turbine engine comprises a turbine shaft, a turbine stator, a first-stage turbine rotor and a second-stage turbine rotor. The turbine disk-shaft connection structure comprises a flexible connection structure, which is formed on the inner ring of the first-stage turbine rotor. The flexible connection structure is constructed as a structure with a bent cross section to reduce the connection stiffness between the first-stage turbine rotor and the turbine shaft. The disk centers of the first-stage turbine rotor and the second-stage turbine rotor are respectively set to be larger than a preset size, the second-stage turbine rotor is connected to the first-stage turbine rotor, and an avoidance space is formed on one side of the flexible connection structure toward the turbine stator so that the turbine stator has space for being arranged within the disk centers of the first-stage turbine rotor and the second-stage turbine rotor.

[0005] As a further improvement of the above technical solution, the flexible connection structure includes a first wall surface facing the second-stage rotor of the turbine, and the first wall surface of the turbine disk-shaft connection structure is constructed from the root of the outer ring to the root of the inner ring to form one or more arc-shaped transition structures, and the arc-shaped transition structure is used to optimize the stress distribution and to make the maximum stress position of the first-stage rotor of the turbine be located on the arc-shaped transition structure.

[0006] As a further improvement of the above technical solution, the thickness distribution of the flexible connection structure is matched and allocated based on the distribution of the load force obtained through simulation analysis.

[0007] As a further improvement of the above technical solution, the turbine disk shaft connection structure also includes a sleeve tooth connection structure, which includes splines respectively arranged on the inner ring of the turbine first-stage rotor and the outer wall of the turbine shaft, a first shoulder formed on the turbine shaft, and a stopper threadedly connected to the turbine shaft, the splines of the inner ring of the turbine first-stage rotor cooperate with the splines of the turbine shaft, the first end of the inner ring of the turbine first-stage rotor abuts against the first shoulder of the turbine shaft, and the stopper is used to be threadedly connected to the turbine shaft to abut against the second end of the inner ring of the turbine first-stage rotor.

[0008] As a further improvement of the above technical solution, the turbine disk-shaft connection structure also includes a wheel disk stop provided on the turbine shaft, and the inner ring of the first-stage turbine rotor is interference fit with the wheel disk stop.

[0009] As a further improvement of the above technical solution, the turbine sleeve is provided with a matching bushing, and the two ends of the matching bushing are used to respectively abut against the first shaft shoulder and the turbine first-stage rotor.

[0010] As a further improvement of the above technical solution, the surface of the first-stage turbine rotor toward the second-stage turbine rotor extends axially to form a first connection structure, and the surface of the second-stage turbine rotor toward the first-stage turbine rotor extends axially to form a second connection structure, and the first connection structure and the second connection structure are connected by a bolt connection structure.

[0011] As a further improvement of the above technical solution, the plurality of bolt connection structures are evenly distributed along the circumferential direction.

[0012] As a further improvement of the above technical solution, a bearing sealing structure is arranged between the inner wall of the end of the turbine stator and the turbine shaft, and a first bearing and a second bearing are respectively arranged between the turbine stator and the turbine shaft, and the first bearing is located at one end close to the first-stage rotor of the turbine.

[0013] According to another aspect of the present invention, there is also provided an aircraft engine, which comprises the above-mentioned turbine disk-shaft connection structure.

[0014] The present invention has the following beneficial effects: The flexible connection structure of the turbine disk-shaft connection structure is formed on the inner ring of the first-stage turbine rotor, and its cross-section is approximately a C-shaped bend structure, thereby reducing the connection stiffness between the first-stage turbine rotor and the turbine shaft, and can store and release the energy generated by the working process of the wheel disk in the form of elastic potential energy, thereby reducing the displacement deformation caused by the centrifugal force at the matching point of the two-stage turbine disk, ensuring the coaxiality matching requirements of the disk and the shaft when the turbine is running at high speed, and the flexible connection structure can buffer the load on the turbine disk, avoiding the load from being concentrated at the connection point of the two-stage turbine disk and the bearing position, thereby further improving the working reliability of the turbine disk, and when the engine attitude changes, the load generated by the gyroscopic torque can be transferred through the flexible connection structure The deformation of the structure is borne, thereby reducing the bearing support load and further improving the bearing life; the turbine first-stage rotor and the turbine second-stage rotor are connected, and the disk centers of the turbine first-stage rotor and the turbine second-stage rotor are respectively set to be larger than the preset size. At the same time, based on the return bending structure of the flexible connection structure, the turbine stator can be arranged in the space within the disk centers of the turbine first-stage rotor and the turbine second-stage rotor, and the layout position can be further axially adjusted in the direction of the return bending structure of the turbine first-stage rotor. Compared with the traditional structure, the distance between the overall center of gravity load of the turbine disk and the bearing is shortened, thereby avoiding excessive vibration of the power turbine rotor when the engine is working, effectively reducing the vibration of the power turbine rotor and thus reducing the bearing load.

[0015] In addition to the above-described purposes, features and advantages, the present invention has other purposes, features and advantages. The present invention will be further described in detail with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] The drawings constituting a part of this application are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the drawings: Figure 1 It is a schematic diagram of the connection between the disk and shaft of a conventional power turbine in the prior art; Figure 2 It is a schematic diagram of the load on the conventional power turbine shaft in the prior art; Figure 3 It is a simplified diagram of the disk-shaft layout of a conventional power turbine in the prior art; Figure 4 is a structural schematic diagram of a turbine disk-shaft connection structure according to a preferred embodiment of the present invention; Figure 5 is a simplified layout diagram of a preferred embodiment of the present invention; Figure 6It is a schematic diagram of the load on the disk center of a conventional power turbine in the prior art; Figure 7 Schematic diagram of the load on the disk center of the first-stage turbine rotor in the preferred embodiment of the present invention; Figure 8 is a schematic diagram of thickness distribution of a flexible connection structure of a preferred embodiment of the present invention; Fig. 9 It is a schematic diagram of the low-pressure turbine disk-shaft bolt connection structure in the prior art; Fig.10 Schematic diagram of the load environment of the sleeve-tooth connection structure of the preferred embodiment of the present invention; Fig.11 Schematic diagram of the loading condition of the sleeve tooth connection structure under bending load in the preferred embodiment of the present invention; Fig.12 It is a structural schematic diagram of comparative example 1.

[0017] Legend: 100, turbine stator; 200, turbine second-stage rotor; 300, turbine first-stage rotor; 400, first bearing; 500, second bearing; 600, bearing sealing structure; 700, flexible connection structure; 701, spline; 702, stopper; 703, stopper; 704, arc-shaped transition structure; 800, turbine shaft; 900, bolt connection structure. DETAILED DESCRIPTION

[0018] The embodiments of the present invention are described in detail below with reference to the accompanying drawings. However, the present invention can be implemented in many different ways as defined and covered below.

[0019] Figure 1 It is a schematic diagram of the connection between the disk and shaft of a conventional power turbine in the prior art; Figure 2 It is a schematic diagram of the load on the conventional power turbine shaft in the prior art; Figure 3 It is a simplified diagram of the disk-shaft layout of a conventional power turbine in the prior art; Figure 4 is a structural schematic diagram of a turbine disk-shaft connection structure according to a preferred embodiment of the present invention; Figure 5 is a simplified layout diagram of a preferred embodiment of the present invention; Figure 6 It is a schematic diagram of the load on the disk center of a conventional power turbine in the prior art; Figure 7 Schematic diagram of the load on the disk center of the first-stage turbine rotor in the preferred embodiment of the present invention; Figure 8 is a schematic diagram of thickness distribution of a flexible connection structure of a preferred embodiment of the present invention; Fig. 9 It is a schematic diagram of the low-pressure turbine disk-shaft bolt connection structure in the prior art; Fig.10 Schematic diagram of the load environment of the sleeve-tooth connection structure of the preferred embodiment of the present invention; Fig.11 Schematic diagram of the loading condition of the sleeve tooth connection structure under bending load in the preferred embodiment of the present invention; Fig.12 It is a structural schematic diagram of comparative example 1.

[0020] like Figures 1 to 11 As shown, the turbine disk-shaft connection structure of this embodiment is applied to a turbine engine, which includes a turbine shaft 800, a turbine stator 100, a turbine first-stage rotor 300 and a turbine second-stage rotor 200. The turbine disk-shaft connection structure includes a flexible connection structure 700. The flexible connection structure 700 is formed on the inner ring of the turbine first-stage rotor 300. The flexible connection structure 700 is constructed with a cross-section having a return-bend structure to reduce the connection stiffness between the turbine first-stage rotor 300 and the turbine shaft 800. The disk centers of the turbine first-stage rotor 300 and the turbine second-stage rotor 200 are respectively set to be larger than a preset size, the turbine second-stage rotor 200 is connected to the turbine first-stage rotor 300, and an avoidance space is formed on the side of the flexible connection structure 700 toward the turbine stator 100, so that the turbine stator 100 has space for being arranged within the disk centers of the turbine first-stage rotor 300 and the turbine second-stage rotor 200.

[0021] A bearing sealing structure 600 is provided between the inner wall of the end of the turbine stator 100 and the turbine shaft 800, and a first bearing 400 and a second bearing 500 are provided between the turbine stator 100 and the turbine shaft 800, respectively. The first bearing 400 is located at one end close to the turbine first-stage rotor 300; It can be understood that the flexible connection structure 700 of the turbine disk-shaft connection structure is formed on the inner ring of the first-stage turbine rotor 300 and its cross-sectional structure is approximately a C-shaped bend structure, thereby reducing the connection stiffness between the first-stage turbine rotor 300 and the turbine shaft 800, and can store and release the energy generated by the working process of the wheel disk in the form of elastic potential energy, thereby reducing the displacement deformation caused by the centrifugal force at the matching point of the two-stage turbine disk, ensuring the coaxiality matching requirements of the disk and the shaft when the turbine is running at high speed, and the flexible connection structure 700 can buffer the load on the turbine disk, avoiding the load from being concentrated at the connection point of the two-stage turbine disk and the bearing position, thereby further improving the working reliability of the turbine disk, and when the engine attitude changes, the load generated by the gyroscopic torque can be dissipated through the flexible connection structure 700 The deformation is borne, thereby reducing the bearing support load and further improving the bearing life; the turbine first-stage rotor 300 and the turbine second-stage rotor 200 are connected and the disk centers of the turbine first-stage rotor 300 and the turbine second-stage rotor 200 are respectively set to be larger than the preset size. At the same time, based on the return bending structure of the flexible connection structure 700, the turbine stator 100 can be arranged in the space within the disk centers of the turbine first-stage rotor 300 and the turbine second-stage rotor 200 and can further adjust the layout position axially in the direction of the return bending structure of the turbine first-stage rotor 300. Compared with the traditional structure, the distance between the overall center of gravity load of the turbine disk and the bearing can be reduced, thereby avoiding excessive vibration of the power turbine rotor when the engine is working, effectively reducing the vibration of the power turbine rotor and thus reducing the bearing load.

[0022] In some embodiments, the flexible connection structure 700 includes a first wall facing the turbine secondary rotor 200, and the first wall of the turbine disk-shaft connection structure is constructed from the outer ring root to the inner ring root to form one or more arc-shaped transition structures 704. The arc-shaped transition structure 704 is used to optimize the stress distribution and to make the maximum stress position of the turbine primary rotor 300 located on the arc-shaped transition structure 704. It should be noted that the arc-shaped transition structure 704 is obtained based on the simulation calculation method of the aircraft engine in the prior art. The outer ring root position of the turbine disk-shaft connection structure is constructed in an approximately "human" shaped structure, and the outer ring root position is optimized from a straight structure to an arc-shaped transition structure 704, so that the maximum The stress position is closer to the geometric center of the wheel structure, making the stress distribution more uniform, thereby increasing the service life of the turbine disk; further, the thickness distribution of the flexible connection structure 700 is matched and distributed based on the load force distribution of the simulation analysis, forming a "thin-thick-thin" transition structure from the root of the outer ring to the root of the inner ring, which maximizes the use of material strength. According to the simulation analysis, the parts with large loads are thickened and strengthened, and the parts with small loads are weakened and thinned, thereby avoiding waste of material strength performance, reducing the overall weight of the wheel, and improving turbine performance. On the other hand, this structural form can further effectively improve the flexibility of the flexible connection structure 700 and buffer the load.

[0023] In some embodiments, the turbine disk-shaft connection structure further includes a sleeve tooth connection structure, which includes a spline 701 respectively arranged on the inner ring of the turbine first-stage rotor 300 and the outer wall of the turbine shaft 800, a first shoulder formed on the turbine shaft 800, and a stopper 703 threadedly connected to the turbine shaft 800, the spline 701 of the inner ring of the turbine first-stage rotor 300 cooperates with the spline 701 of the turbine shaft 800, the first end of the inner ring of the turbine first-stage rotor 300 abuts against the first shoulder of the turbine shaft 800, and the stopper 703 is used for threaded connection. Connected to the turbine shaft 800 to abut against the second end of the inner ring of the first-stage turbine rotor 300; it can be understood that the stopper 703 is a stopper bolt / nut threadedly connected to the turbine shaft 800; further, the turbine disk-shaft connection structure also includes a wheel disk stopper 702 provided on the turbine shaft 800, and the inner ring of the first-stage turbine rotor 300 and the wheel disk stopper 702 are interference-fitted to ensure that the turbine disk and the turbine shaft 800 are coaxial and concentric, and reduce the movement of the turbine disk when it runs at high speed. Compared with the traditional bolt fit, the installation is more convenient and the working reliability is higher; It should be noted that the reference Fig. 9The low-pressure rotor of a conventional high-power turboshaft engine adopts a single-stage low-pressure turbine disk, and the turbine disk, turbine shaft 800, and turbine short shaft are connected together by short bolts. The low-pressure turbine disk-shaft is connected by a stopper 702-bolt connection. The stopper 702 is used for centering, the end face transmits torque, the bolt transmits axial force, and the rear edge of the wheel extends out of the shaft neck to connect with the shaft. Due to the large mass and moment of inertia of the low-pressure turbine disk, when the low-pressure rotor system is bent and deformed, the gyroscopic torque exerted on the low-pressure turbine disk will cause a bending load on the low-pressure turbine disk-shaft connection structure, causing the contact state of the bolt connection structure 900 to deteriorate, resulting in problems such as loss of connection stiffness and reduced rotor coaxiality. This embodiment uses a spline 701 on the inner ring of the first-stage turbine rotor 300 and the outer wall of the turbine shaft 800, respectively, to transmit torque using a sleeve tooth. Fig.10 During the operation of the rotor, the sleeve gear connection structure will be subjected to the assembly pre-tightening compression / tension load , torque T, centrifugal load and bending load Complex loads such as bending load This is the main reason for the uncertainty of the stiffness characteristics of the connection structure. Fig.11 The load conditions of each interface of the sleeve-tooth connection structure under bending; Fig.11 middle, Respectively represent the normal load and tangential load on the front / rear centering surface; To locate the normal load on the upper / lower part of the end surface; are the preload pressure on the outer shaft of the sleeve gear and the preload tension on the inner shaft of the sleeve gear respectively; the speed is ω, It is a bending load. The bending load on the sleeve-tooth connection structure is balanced by the bending moment formed by the unevenly distributed normal load on the upper and lower parts of the positioning end face and the bending moment formed by the normal load and tangential load on the front and rear positioning end faces, that is, the bending load is borne jointly by the positioning end face and the front and rear centering faces; under the above joint action, the connection structure has a certain degree of bending deformation, the separation of each contact interface, especially the slip of the front and rear centering cylindrical surfaces, which will lead to the incoordination of the deformation of the inner and outer shaft sections at the contact interface, thereby causing the angular constraint ability of the inner shaft of the connection structure to the outer shaft to decrease, resulting in stiffness loss; in order to suppress the loss of connection stiffness and the reduction of rotor coaxiality, the disk-shaft connection structure adopts a sleeve-tooth connection structure, and the turbine rotor adopts a cantilever structure. Under the action of bending load, the change of radial contact stiffness and the increase of axial slip may This leads to an increase in angular deformation, which in turn causes a loss in bending stiffness and affects the dynamic characteristics of the rotor system. In this embodiment, the axial position of the bearing of the turbine stator 100 is optimized through the flexible connection structure 700, which can effectively increase the bending stiffness of the turbine rotor and make the stiffness loss of the sleeve gear connection structure relatively stable. The first shoulder is used to axially position the end face that is abutted against it, and the front and rear ends form cylindrical centering respectively. A stopper 703 is provided to lock the inner and outer shafts of the sleeve gear and related structures such as the bearing, and bear the axial force, so that the working reliability is strong. At the same time, the flexible connection structure 700 can cause the deformation caused by the centrifugal force of the turbine disk to act on the flexible connection structure 700, thereby avoiding the influence of the deformation of the turbine disk on the stop 702, further ensuring the coaxiality of the rotor connection, and making the operation more reliable.

[0024] In some embodiments, the turbine shaft 800 is also provided with a matching bushing, and the two ends of the matching bushing are used to respectively abut against the first shaft shoulder and the turbine first-stage rotor 300. It can be understood that during assembly, the matching bushing is first installed into the turbine shaft 800 to make it abut against the first shaft shoulder, and the length of the matching bushing is slightly longer than the length of the shaft section in which it is located; when the turbine first-stage rotor 300 is installed, its spline 701 is matched with the spline 701 of the turbine shaft 800, and it moves axially to abut against the matching bushing. The matching bushing can increase the matching area with the turbine shaft 800, and it is convenient for disassembly and replacement.

[0025] In some embodiments, the surface of the turbine first-stage rotor 300 facing the turbine second-stage rotor 200 extends axially to form a first connection structure, and the surface of the turbine second-stage rotor 200 facing the turbine first-stage rotor 300 extends axially to form a second connection structure. The first connection structure and the second connection structure are connected by a bolt connection structure 900, wherein the first connection structure is arranged at a position close to the outer ring of the turbine first-stage rotor 300, and similarly, the second connection structure is arranged at a position close to the turbine second-stage rotor 200. When the first connection structure and the second connection structure are connected by the bolt connection structure 900, there is more space and the operation is more convenient; furthermore, a plurality of bolt connection structures 900 are evenly distributed along the circumference so that the turbine first-stage rotor 300 and the turbine second-stage rotor 200 are firmly connected and operate stably.

[0026] On the other hand, a preferred embodiment of the present invention further provides an aircraft engine, which is applied with the above-mentioned turbine disk-shaft connection structure.

[0027] Comparative Example 1 refer to Fig.12 This comparative example is a preliminary design scheme of a preferred embodiment. The flexible connection structure 700 is only provided with a space for arranging the turbine stator 100 in the disk center of the turbine first-stage rotor 300. However, the disk-shaft connection structure is still relatively rigid, and it is easy to quickly transmit the bending moment of the rotor to the turbine shaft 800, which brings adverse effects such as vibration to the engine. In a specific embodiment, the disk center of the turbine first-stage rotor 300 is further increased to leave a larger space for the return bending structure of the flexible connection structure 700, and facilitate the adjustment of the axial layout position of the bearing and the turbine stator 100, increase the return bending angle of the return bending structure at the connection between the turbine disk and the shaft, and reduce the stiffness of the connection structure based on the thickness distribution optimization, and optimize the straight transition to an arc transition to optimize the stress distribution, so as to reduce the vibration of the power turbine rotor and reduce the bearing load.

[0028] In the description of the present invention, it should be noted that the directions or positional relationships indicated by the terms "upper", "lower", "front", "rear", etc. are based on the directions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore cannot be understood as a limitation on the present invention.

[0029] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0030] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A turbine disk-shaft connection structure, applied to a turbine engine, the turbine engine comprising a turbine shaft (800), a turbine stator (100), a turbine first-stage rotor (300) and a turbine second-stage rotor (200), characterized in that: The turbine disk-shaft connection structure comprises a flexible connection structure (700), the flexible connection structure (700) is formed on the inner ring of the turbine first-stage rotor (300), the flexible connection structure (700) is constructed as a cross-section with a bent structure to reduce the connection rigidity between the turbine first-stage rotor (300) and the turbine shaft (800), the disk centers of the turbine first-stage rotor (300) and the turbine second-stage rotor (200) are respectively set to be larger than a preset size, the turbine second-stage rotor (200) is connected to the turbine first-stage rotor (300), and a side of the flexible connection structure (700) facing the turbine stator (100) is formed with an avoidance space, so that the turbine stator (100) has a space for being arranged within the disk centers of the turbine first-stage rotor (300) and the turbine second-stage rotor (200).

2. The turbine disk-shaft connection structure according to claim 1, characterized in that: The flexible connection structure (700) comprises a first wall surface facing the turbine secondary rotor (200), and the first wall surface of the turbine disk-shaft connection structure is constructed from the outer ring root to the inner ring root to form one or more arc-shaped transition structures (704), and the arc-shaped transition structure (704) is used to optimize stress distribution and to make the maximum stress position of the turbine primary rotor (300) located on the arc-shaped transition structure (704).

3. The turbine disk-shaft connection structure according to claim 1, characterized in that: The thickness distribution of the flexible connection structure (700) is matched and distributed based on the load force distribution obtained through simulation analysis.

4. The turbine disk-shaft connection structure according to claim 1, characterized in that: The turbine disk-shaft connection structure also includes a sleeve tooth connection structure, which includes splines (701) respectively arranged on the inner ring of the turbine first-stage rotor (300) and the outer wall of the turbine shaft (800), a first shaft shoulder formed on the turbine shaft (800), and a stopper (703) threadedly connected to the turbine shaft (800), the splines (701) of the inner ring of the turbine first-stage rotor (300) cooperate with the splines (701) of the turbine shaft (800), the first end of the inner ring of the turbine first-stage rotor (300) abuts against the first shaft shoulder of the turbine shaft (800), and the stopper (703) is used to be threadedly connected to the turbine shaft (800) so as to abut against the second end of the inner ring of the turbine first-stage rotor (300).

5. The turbine disk-shaft connection structure according to claim 4, characterized in that: The turbine disk-shaft connection structure also includes a wheel disk stop (702) arranged on the turbine shaft (800), and the inner ring of the turbine first-stage rotor (300) is interference-fitted with the wheel disk stop (702).

6. The turbine disk-shaft connection structure according to claim 4, characterized in that: The turbine shaft (800) is sleeved with a matching bushing, and two ends of the matching bushing are used to respectively abut against the first shaft shoulder and the turbine first-stage rotor (300).

7. The turbine disk-shaft connection structure according to claim 1, characterized in that: The surface of the first-stage turbine rotor (300) extending axially toward the surface of the second-stage turbine rotor (200) forms a first connection structure, and the surface of the second-stage turbine rotor (200) extending axially toward the surface of the first-stage turbine rotor (300) forms a second connection structure, and the first connection structure and the second connection structure are connected by a bolt connection structure (900).

8. The turbine disk-shaft connection structure according to claim 7, characterized in that: The plurality of bolt connection structures (900) are evenly distributed along the circumferential direction.

9. The turbine disk-shaft connection structure according to any one of claims 1 to 8, characterized in that: A bearing sealing structure (600) is arranged between the inner wall of the end of the turbine stator (100) and the turbine shaft (800), and a first bearing (400) and a second bearing (500) are arranged between the turbine stator (100) and the turbine shaft (800), respectively, and the first bearing (400) is located at one end close to the first-stage rotor (300) of the turbine.

10. An aircraft engine, characterized in that: The turbine disk-shaft connection structure according to any one of claims 1 to 9 is applied.

Images