Turbine disk shaft connection structure and aeroengine

Abstract

The present invention discloses a turbine disk shaft connection structure and an aeroengine. The aeroengine includes a turbine shaft, a turbine stator, a first-stage turbine rotor, and a second-stage turbine rotor. The turbine disk shaft connection structure includes a flexible connection structure formed on the inner ring of the first-stage turbine rotor. The flexible connection structure is configured to have a cross-section in a bent-back structure 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 greater than a preset size. A clearance space is formed on the side where the second-stage turbine rotor is connected to the first-stage turbine rotor and where the flexible connection structure faces the turbine stator, so that the turbine stator has a space for layout within the disk centers of the first-stage turbine rotor and the second-stage turbine rotor. The energy generated during the operation of the disk is stored and released in the form of elastic potential energy, thereby reducing the displacement deformation caused by the centrifugal force at the mating part of the two-stage turbine disks and ensuring the coaxiality requirement between the disk and the shaft during the high-speed operation of the turbine.

Description

Technical Field

[0001] The present invention relates to the technical field of aeroengines, and in particular, to a turbine disk shaft connection structure. In addition, the present invention also relates to an aeroengine including the above turbine disk shaft connection structure. Background Art

[0002] The power turbines of high-performance and low fuel consumption rate turbine engines in the prior art often have multiple turbine disks. In order to facilitate the machining of the turbine disks and the assembly of the engine, the turbine disks usually do not have complex structural configurations. The disks are connected by short journal shafts extending from the wheel center and fixed by large bolts. The disks and the turbine shaft are also connected by a spigot flange and bolts. Refer to Figure 1 , the entire rotor has a large cantilever configuration, resulting in at least the following problems:

[0003] 1) Since the distance between the turbine disk and the No. 1 bearing is too large, the bearing bears an excessive load.

[0004] 2) Since the turbine disk and the turbine shaft are connected by bolts, the installation is complex during the mating process, the reliability is low during the working process, and the low cycle fatigue life of the turbine disk is reduced due to the bolt holes being opened near the wheel center.

[0005] 3) The turbine disk structure adopts a rigid design. The displacement deformation caused by centrifugal force at the disk shaft mating part easily causes the disk and the shaft to fail to meet the coaxiality requirements; precise bolts are used for centering between the disks and between the disk and the shaft, and the deformation mismatch between the parts will generate additional shear force on the bolts.

[0006] 4) The turbine disk adopts a rigid structure, which cannot buffer the applied load, easily causes stress concentration locally, resulting in damage. In addition, under the rigid connection structure, the deformation generated by the gyroscopic moment and the load directly act on the bearing, and the bearing bears an excessive load. Summary of the Invention

[0007] The present invention provides a turbine disk shaft connection structure and an aeroengine to solve the technical problem that the support bearing of the engine power turbine rotor bears an excessive load due to the too long cantilever.

[0008] According to one aspect of the present invention, a turbine disk - shaft connection structure is provided, which is applied to a turbine engine. The turbine engine includes a turbine shaft, a turbine stator, a first - stage turbine rotor, and a second - stage turbine rotor. The turbine disk - shaft connection structure includes a flexible connection structure formed on the inner ring of the first - stage turbine rotor. The flexible connection structure is configured to have a cross - section in a bent - back structure 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 greater than a preset size. A clearance space is formed on the side where the second - stage turbine rotor is connected to the first - stage turbine rotor and the flexible connection structure faces the turbine stator, so that the turbine stator has a space to be arranged within the disk centers of the first - stage turbine rotor and the second - stage turbine rotor.

[0009] As a further improvement of the above - mentioned technical solution, the flexible connection structure includes a first wall surface facing the second - stage turbine rotor. The first wall surface of the turbine disk - shaft connection structure is configured with one or more arc - shaped transition structures from the outer - ring root to the inner - ring root. The arc - shaped transition structure is used to optimize the stress distribution and to make the maximum stress position of the first - stage turbine rotor located on the arc - shaped transition structure.

[0010] As a further improvement of the above - mentioned technical solution, the thickness distribution of the flexible connection structure is matched and allocated based on the load - bearing force distribution obtained from simulation analysis.

[0011] As a further improvement of the above - mentioned technical solution, the turbine disk - shaft connection structure further includes a spline - tooth connection structure. The spline - tooth connection structure includes splines respectively arranged on the inner ring of the first - stage turbine rotor and the outer wall of the turbine shaft, a first shoulder formed on the turbine shaft, and a stop member threadedly connected to the turbine shaft. The spline on the inner ring of the first - stage turbine rotor is engaged with the spline on the turbine shaft. The first end of the inner ring of the first - stage turbine rotor abuts against the first shoulder of the turbine shaft. The stop member is used to be threadedly connected to the turbine shaft to abut against the second end of the inner ring of the first - stage turbine rotor.

[0012] As a further improvement of the above - mentioned technical solution, the turbine disk - shaft connection structure further includes a wheel - disk stop provided on the turbine shaft. The inner ring of the first - stage turbine rotor is in interference fit with the wheel - disk stop.

[0013] As a further improvement of the above - mentioned technical solution, a mating bushing is sleeved on the turbine shaft. The two ends of the mating bushing are respectively used to abut against the first shoulder and the first - stage turbine rotor.

[0014] 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 connecting structure, and the surface of the second-stage turbine rotor toward the first-stage turbine rotor extends axially to form a second connecting structure, and the first connecting structure and the second connecting structure are connected by a bolt connection structure.

[0015] As a further improvement of the above technical solution, the plurality of bolt connection structures are evenly distributed along the circumferential direction.

[0016] 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.

[0017] According to another aspect of the present invention, an aircraft engine is provided, which includes the turbine disk-shaft connection structure described above.

[0018] The present invention has the following beneficial effects:

[0019] The flexible connection structure of this turbine disk-shaft connection structure is formed on the inner ring of the first-stage turbine rotor and its cross-section is an approximately C-shaped bend structure, thereby reducing the connection stiffness between the first-stage turbine rotor and the turbine shaft. The energy generated by the wheel disc working process can be stored and released 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 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 concentration at the connection point of the two-stage turbine disk and the bearing position, thereby further improving the working reliability of the turbine disk. When the engine attitude changes, the load generated by the gyroscopic torque can be dissipated 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, the bending structure based on the flexible connection structure enables the turbine stator to be arranged in the space within the disk centers of the turbine first-stage rotor and the turbine second-stage rotor and can further adjust the layout position axially in the direction of the turbine first-stage rotor bending structure. Compared with the traditional structure, the distance between the overall center of gravity load of the turbine disk and the bearing is shortened, 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.

[0020] In addition to the above-described objects, features and advantages, the present invention has other objects, features and advantages. The present invention will be further described in detail below with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] The accompanying drawings, which form 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 of the present invention. In the drawings:

[0022] Figure 1 is a schematic diagram of the connection between a traditional power turbine disk and shaft in the prior art;

[0023] Figure 2 is a schematic diagram of the load on a traditional power turbine shaft in the prior art;

[0024] Figure 3 is a simplified layout diagram of a traditional power turbine disk and shaft in the prior art;

[0025] Figure 4 is a schematic structural diagram of the turbine disk and shaft connection structure of the preferred embodiment of the present invention;

[0026] Figure 5 is a simplified layout diagram of the preferred embodiment of the present invention;

[0027] Figure 6 is a schematic diagram of the load on the center of a traditional power turbine disk in the prior art;

[0028] Figure 7 is a schematic diagram of the load on the center of the turbine first-stage rotor of the preferred embodiment of the present invention;

[0029] Figure 8 is a schematic diagram of the thickness distribution of the flexible connection structure of the preferred embodiment of the present invention;

[0030] Figure 9 is a simplified diagram of the low-pressure turbine disk - shaft bolt connection structure in the prior art;

[0031] Figure 10 is a schematic diagram of the load environment of the spline connection structure of the preferred embodiment of the present invention;

[0032] Figure 11 is a schematic diagram of the load-bearing situation of the spline connection structure under the bending load of the preferred embodiment of the present invention;

[0033] Figure 12 is a schematic structural diagram of Comparative Example 1.

[0034] Legend:

[0035] 100, turbine stator; 200, turbine second-stage rotor; 300, turbine first-stage rotor; 400, first bearing; 500, second bearing; 600, bearing seal structure; 700, flexible connection structure; 701, spline; 702, spigot; 703, stop; 704, arc transition structure; 800, turbine shaft; 900, bolt connection structure. Detailed implementation manners

[0036] 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.

[0037] Figure 1 is a schematic diagram of the connection between a traditional power turbine disk and shaft in the prior art; Figure 2 is a schematic diagram of the load on a traditional power turbine shaft in the prior art; Figure 3 is a simplified layout diagram of a traditional power turbine disk and shaft in the prior art; Figure 4 is a schematic structural diagram of the turbine disk and shaft connection structure of the preferred embodiment of the present invention; Figure 5 is a simplified layout diagram of the preferred embodiment of the present invention; Figure 6 is a schematic diagram of the load on the center of the disk of a traditional power turbine in the prior art; Figure 7 is a schematic diagram of the load on the center of the disk of the turbine first-stage rotor of the preferred embodiment of the present invention; Figure 8 is a schematic diagram of the thickness distribution of the flexible connection structure of the preferred embodiment of the present invention; Figure 9 is a simplified diagram of the low-pressure turbine disk - shaft bolt connection structure in the prior art; Figure 10 is a schematic diagram of the load environment of the spline connection structure of the preferred embodiment of the present invention; Figure 11 is a schematic diagram of the load-bearing situation of the spline connection structure under bending load of the preferred embodiment of the present invention; Figure 12 is a schematic structural diagram of Comparative Example 1.

[0038] As Figures 1 to 11 shown, the turbine disk and shaft connection structure of this embodiment is applied to a turbine engine. The turbine engine 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 and 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 configured to have a reverse-bending cross-section to reduce the connection stiffness between the turbine first-stage rotor 300 and the turbine shaft 800. The centers of the disks of the turbine first-stage rotor 300 and the turbine second-stage rotor 200 are respectively set to be greater than a preset size. The turbine second-stage rotor 200 is connected to the turbine first-stage rotor 300, and a clearance space is formed on the side of the flexible connection structure 700 facing the turbine stator 100, so that the turbine stator 100 has a space for layout within the centers of the disks of the turbine first-stage rotor 300 and the turbine second-stage rotor 200.

[0039] Among them, a bearing seal structure 600 is provided between the inner wall of the end of the turbine stator 100 and the turbine shaft 800. A first bearing 400 and a second bearing 500 are respectively provided between the turbine stator 100 and the turbine shaft 800. The first bearing 400 is located at one end close to the turbine first-stage rotor 300;

[0040] 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 turbine first-stage rotor 300 and its cross-section is approximately a C-shaped bend structure, thereby reducing the connection stiffness between the turbine first-stage rotor 300 and the turbine shaft 800. The energy generated by the wheel disk working process can be stored and released 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 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 concentration at the connection point of the two-stage turbine disk and the bearing position, thereby further improving the working reliability of the turbine disk. When the engine attitude changes, the load generated by the gyroscopic torque can be dissipated through the flexible connection structure 700. deformation, 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 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 bending structure of the turbine first-stage rotor 300. Compared with the traditional structure, the distance between the 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.

[0041] 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 a 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 improving 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 to avoid waste of material strength performance, reduce the overall weight of the wheel, and improve 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.

[0042] In some embodiments, the turbine disk shaft connection structure further includes a spline connection structure. The spline connection structure includes splines 701 respectively disposed on the inner ring of the first-stage turbine 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 splines 701 on the inner ring of the first-stage turbine rotor 300 cooperate with the splines 701 on the turbine shaft 800. The first end of the inner ring of the first-stage turbine rotor 300 abuts against the first shoulder of the turbine shaft 800. The stopper 703 is used to be threadedly 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 stop bolt / nut threadedly connected to the turbine shaft 800. Further, the turbine disk shaft connection structure further includes a wheel disk stop 702 disposed on the turbine shaft 800. The inner ring of the first-stage turbine rotor 300 is in interference fit with the wheel disk stop 702, ensuring the coaxiality of the turbine disk and the turbine shaft 800, reducing the runout generated during the high-speed operation of the turbine disk. Compared with the traditional bolt connection, the installation is more convenient and the working reliability is higher.

[0043] It should be noted that referring to Figure 9 , in the traditional high-power turboshaft engine, the low-pressure rotor 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 adopts a stop 702-bolt connection, with the stop 702 for centering, torque transmission through the end face, and axial force transmission through the bolts. The trailing edge of the wheel disk extends out of the shaft neck and is connected to the shaft. Due to the large mass and moment of inertia of the low-pressure turbine disk, when the low-pressure rotor system undergoes bending deformation, the gyroscopic moment acting on the low-pressure turbine disk will cause a bending load on the low-pressure turbine disk-shaft connection structure, deteriorating the contact state of the bolt connection structure 900, resulting in problems such as loss of connection stiffness and reduction of rotor coaxiality. In this embodiment, through the splines 701 respectively on the inner ring of the first-stage turbine rotor 300 and the outer wall of the turbine shaft 800, spline torque transmission is adopted. Referring to Figure 10 , during the operation of the rotor, the spline connection structure will bear assembly pre-tightening compression / tension loads , torque T, centrifugal loads and bending loads and other complex loadings. Among them, the bending load is the main reason for the non-deterministic stiffness characteristics of the connection structure. Figure 11 shows the load-bearing conditions of each interface of the spline connection structure under bending. Figure 11 In , respectively represent the normal and tangential loads received by the front / rear centering surfaces. are the normal loads received by the upper / lower parts of the positioning end face. are the pre-tightening pressure received by the outer shaft of the spline and the pre-tightening tension received by the inner shaft of the spline respectively. The rotational speed is ω.It is a bending load. The bending load on the sleeve gear 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 uncoordinated deformation of the inner and outer shaft segments 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 problem of connection stiffness loss and reduced rotor coaxiality, the disk-shaft connection structure adopts a sleeve gear connection structure, and the turbine rotor adopts a cantilever structure. Under the action of bending load, the change in radial contact stiffness and the increase in axial slip may This leads to an increase in angular deformation, thereby causing a loss of bending stiffness and affecting 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 more 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.

[0044] In some embodiments, the turbine shaft 800 is further provided with a mating bushing, the two ends of which 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 mating bushing is first installed into the turbine shaft 800 so that it abuts against the first shaft shoulder, and the length of the mating 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 mated with the spline 701 of the turbine shaft 800, and is moved axially to abut against the mating bushing. The mating area with the turbine shaft 800 can be increased through the mating bushing, and it is convenient for disassembly and replacement.

[0045] In some embodiments, a first connection structure is formed by axially extending the surface of the first-stage turbine rotor 300 facing the second-stage turbine rotor 200, and a second connection structure is formed by axially extending the surface of the second-stage turbine rotor 200 facing the first-stage turbine rotor 300. The first connection structure and the second connection structure are connected by a bolt connection structure 900. Among them, the first connection structure is arranged near the outer ring of the first-stage turbine rotor 300. Similarly, the second connection structure is arranged near the second-stage turbine rotor 200. When connecting the first connection structure and the second connection structure through the bolt connection structure 900, there is more space and the operation is more convenient; further, a plurality of bolt connection structures 900 are evenly distributed in the circumferential direction to make the connection between the first-stage turbine rotor 300 and the second-stage turbine rotor 200 stable and the operation stable.

[0046] On the other hand, a preferred embodiment of the present invention further provides an aeroengine, which applies the above-mentioned turbine disk shaft connection structure.

[0047] Comparative Example 1

[0048] Reference Figure 12 , this comparative example is the preliminary design scheme of the preferred embodiment. The flexible connection structure 700 is only arranged in the center of the first-stage turbine rotor 300 where there is a layout space for the turbine stator 100. However, the disk shaft connection structure is still relatively rigid and is likely to quickly transfer the bending moment of the rotor to the turbine shaft 800, bringing adverse effects such as vibration to the engine; in a specific embodiment, the center of the first-stage turbine rotor 300 is further increased to leave more space for the bending structure of the flexible connection structure 700, and it is beneficial for adjusting the axial layout positions of the bearing and the turbine stator 100, increasing the bending angle of the bending structure at the connection of the turbine disk and the shaft, and optimizing the stress distribution by optimizing the thickness distribution and changing the straight transition to an arc transition, so as to weaken the vibration of the power turbine rotor and thus reduce the bearing load.

[0049] In the description of the present invention, it should be noted that the orientation or positional relationship indicated by the terms "upper", "lower", "front", "rear", etc. is based on the orientation or positional relationship shown in the drawings, and is 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 orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the present invention.

[0050] In the description of the present invention, it should be noted that, unless otherwise clearly defined and limited, the terms "installed", "connected", and "coupled" 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 directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two components. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific situations.

[0051] 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 modifications and changes. 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 is applied to a turbine engine. The turbine engine includes a turbine shaft (800), a turbine stator (100), a first-stage turbine rotor (300), and a second-stage turbine rotor (200), and is characterized in that, The turbine disk shaft connection structure includes a flexible connection structure (700), which is formed on the inner ring of the first-stage turbine rotor (300). The flexible connection structure (700) is configured with a cross-section in a bent-back structure to reduce the connection stiffness between the first-stage turbine rotor (300) and the turbine shaft (800). The centers of the disks of the first-stage turbine rotor (300) and the second-stage turbine rotor (200) are respectively set to be larger than a preset size. A clearance space is formed on the side where the second-stage turbine rotor (200) is connected to the first-stage turbine rotor (300) and where the flexible connection structure (700) faces the turbine stator component (100), so that the turbine stator component (100) has a space for layout within the centers of the disks of the first-stage turbine rotor (300) and the second-stage turbine rotor (200). The flexible connection structure (700) includes a first wall surface facing the second-stage turbine rotor (200). The first wall surface of the turbine disk shaft connection structure is configured with one or more arc transition structures (704) from the outer ring root to the inner ring root. The arc transition structures (704) are used to optimize the stress distribution and to make the position of the maximum stress of the first-stage turbine rotor (300) located on the arc transition structures (704). The thickness distribution of the flexible connection structure (700) is matched and allocated based on the load-bearing force distribution obtained from simulation analysis, forming a thin-thick-thin transition structure from the outer ring root to the inner ring root.

2. The turbine disk shaft connection structure according to claim 1, characterized in that, The turbine disk shaft connection structure further includes a spline connection structure. The spline connection structure includes splines (701) respectively provided on the inner ring of the first-stage turbine rotor (300) and the outer wall of the turbine shaft (800), a first shoulder formed on the turbine shaft (800), and a stop member (703) threadedly connected to the turbine shaft (800). The splines (701) on the inner ring of the first-stage turbine rotor (300) cooperate with the splines (701) on the turbine shaft (800). The first end of the inner ring of the first-stage turbine rotor (300) abuts against the first shoulder of the turbine shaft (800). The stop member (703) is used to be threadedly connected to the turbine shaft (800) to abut against the second end of the inner ring of the first-stage turbine rotor (300).

3. The turbine disk shaft connection structure according to claim 2, characterized in that, The turbine disk shaft connection structure further includes a wheel disk stop (702) provided on the turbine shaft (800). The inner ring of the first-stage turbine rotor (300) is in interference fit with the wheel disk stop (702).

4. The turbine disk shaft connection structure according to claim 2, characterized in that, A mating bushing is sleeved on the turbine shaft (800). The two ends of the mating bushing are respectively used to abut against the first shoulder and the first-stage turbine rotor (300).

5. The turbine disk shaft connection structure according to claim 1, characterized in that, A first connection structure extends axially on the surface of the first-stage turbine rotor (300) facing the second-stage turbine rotor (200). A second connection structure extends axially on the surface of the second-stage turbine rotor (200) facing the first-stage turbine rotor (300). The first connection structure and the second connection structure are connected by a bolt connection structure (900).

6. The turbine disk shaft connection structure according to claim 5, characterized in that A plurality of the bolt connection structures (900) are evenly distributed in the circumferential direction.

7. The turbine disk shaft connection structure according to any one of claims 1-6, characterized in that, A bearing seal structure (600) is arranged between the inner wall of the end of the turbine stator part (100) and the turbine shaft (800). A first bearing (400) and a second bearing (500) are respectively arranged between the turbine stator part (100) and the turbine shaft (800), and the first bearing (400) is located at one end close to the first-stage turbine rotor (300).

8. An aeroengine, characterized in that, The turbine disk shaft connection structure according to any one of claims 1-7 is applied.

Images