Connecting structure of turbine rotor, turbine engine and aircraft

Abstract

The invention relates to the technical field of aero-engines, in particular to a connecting structure of a turbine rotor, a turbine engine and an aircraft, and the connecting structure of the turbine rotor comprises a shaft body and a turbine disc; the shaft body is provided with a connecting section and a shaft neck section used for assembling a bearing matched with a turbine rotor. A connecting surface is arranged on one side of the turbine disc and is connected with the connecting section; a first deformation structure is arranged between the connecting section and the journal section, and the vibration load of the turbine rotor drives the first deformation structure to deform to absorb strain energy. The vibration load generated by the turbine rotor is prevented from influencing the contact state between the shaft body and the turbine disc, reliable torque transmission is ensured, the vibration load generated by the turbine rotor is prevented from being completely borne by the assembled bearing fulcrum, and the service life of the bearing is prolonged. Meanwhile, the contact state between the shaft body and the turbine disc is prevented from being affected by scraping and abrasion loads of the sealing labyrinth, and torque transmission reliability is further guaranteed.

Description

Technical Field

[0001] The invention belongs to the technical field of aviation engines, and in particular relates to a connection structure of a turbine rotor, a turbine engine and an aircraft. Background Art

[0002] Turbine engines are widely used in the fields of aviation and aerospace, in which the turbine rotor is connected to the turbine disk via a turbine stub shaft, so that the bearing assembled on the turbine stub shaft serves as the fulcrum of the turbine rotor to achieve the installation of the turbine rotor.

[0003] The existing turbine stub shaft and turbine disk are used as a connection structure connected to the turbine rotor, referring to Figure 1 The turbine stub shaft and the turbine disk are usually directly connected by a flange bolt connection, wherein the upper part of the flange bolt connection is provided with a sealing grate structure that cooperates with the honeycomb on the bearing seat for sealing, while the lower part of the flange bolt connection is provided with a conical shell structure to reduce the diameter of the turbine stub shaft, so that the diameter of the bearing assembled at the shaft neck can also be reduced accordingly. However, as the turbine engine is put into operation, the sealing grate structure will be scraped and worn, which will easily cause vibration load eccentricity to the connection between the turbine stub shaft and the turbine disk. At the same time, directly connecting the shaft neck through the conical shell structure will also make the cone shell part more rigid, which will not only make the vibration load generated by the turbine rotor easily affect the contact state between the turbine stub shaft and the turbine disk, causing the connection to fail, but also cause the assembled bearing to bear a large load, greatly reducing the bearing life.

[0004] Therefore, the connection effect between the existing turbine stub shaft and the turbine disk is easily affected by vibration. Summary of the invention

[0005] In view of the above problems, the present invention provides a connection structure of a turbine rotor, a turbine engine and an aircraft, wherein a connection structure of a turbine rotor comprises:

[0006] A shaft body, on which a connecting section and a journal section are arranged, wherein the journal section is used to assemble a bearing matched with a turbine rotor;

[0007] A turbine disk, one side of which is provided with a connection surface, the connection surface being connected to the connection section;

[0008] A first deformation structure is provided between the connecting section and the journal section, and the vibration load of the turbine rotor drives the first deformation structure to deform and absorb strain energy.

[0009] In some specific embodiments, a sealing comb tooth is provided on a side of the connecting section away from the first deformation structure;

[0010] The size of the sealing grate teeth is matched with the size of the honeycomb on the bearing seat.

[0011] In some specific embodiments, a second deformation structure is provided between the connecting section and the sealing grate teeth, and the scraping load of the sealing grate teeth drives the second deformation structure to deform and absorb strain energy.

[0012] In some specific embodiments, the first deformation structure includes:

[0013] A first turning section and a first cone shell;

[0014] One side of the first turning section is connected to the connecting section;

[0015] The side of the first turning section away from the connecting section first extends toward the turbine disk, then bends and extends away from the turbine disk and is connected to the journal section through the first cone shell;

[0016] The thickness of the first cone shell is smaller than a first preset value.

[0017] In some specific embodiments, the second deformation structure includes:

[0018] a second turning section and a second cone shell;

[0019] One side of the second turning section is connected to the connecting section via the second cone shell;

[0020] A side of the second turning section away from the connecting section first extends in a direction away from the turbine disk, then bends and extends in a direction close to the turbine disk and is connected to the sealing grate teeth;

[0021] The thickness of the second cone shell is smaller than a second preset value.

[0022] In some specific embodiments, a sealing section is provided between the second deformation structure and the connecting section, and a brush sealing surface is provided on the outer wall of the sealing section;

[0023] The size of the brush sealing surface is matched with the size of the brush structure on the bearing seat.

[0024] In some specific embodiments, the inner wall of the sealing section and the inner wall of the first deformation structure are combined to form a limiting groove;

[0025] The width dimension of the limiting groove is matched with the width dimension of the connecting surface of the turbine disk.

[0026] In some specific embodiments, the rigidity strength of the first cone shell is lower than the rigidity strength of the first turning section;

[0027] The rigidity strength of the second cone shell is lower than the rigidity strength of the second turning section.

[0028] A turbine engine based on the same concept includes: a connection structure of a turbine rotor as described in any of the above specific embodiments.

[0029] An aircraft based on the same concept includes: a turbine engine as described in the above specific embodiment.

[0030] Compared with the prior art, the connection structure of the turbine rotor of the present invention has at least the following advantages: by arranging a first deformation structure on one side of the shaft body to connect the connection section and the journal section of the shaft body, when put into operation, the load generated by the vibration of the turbine rotor can be deformed by the first deformation structure to absorb the corresponding strain energy, which not only avoids the vibration load generated by the turbine rotor from affecting the contact state between the shaft body and the turbine disk and ensures reliable torque transmission, but also avoids the vibration load generated by the turbine rotor being completely borne by the assembled bearing fulcrum, thereby improving the service life of the bearing.

[0031] At the same time, by arranging sealing grate teeth and brush wire sealing surfaces that are respectively matched with the honeycomb and brush wire structures on the bearing seat on the other side of the shaft body, a double seal is formed to improve the sealing effect. In addition, the connecting section is connected to the sealing grate teeth through the second deformation structure, so that when it is put into operation, the load generated by the scraping of the sealing grate teeth can be deformed by the second deformation structure to absorb the corresponding strain energy, thereby avoiding the contact state between the shaft body and the turbine disc being affected by the scraping load of the sealing grate teeth, further ensuring reliable torque transmission.

[0032] Compared with the prior art, the turbine engine of the present invention has at least the following advantages: since it includes the connection structure of the turbine rotor described above, it has the same beneficial effects as the connection structure of the turbine rotor described above, and therefore, it will not be described in detail here.

[0033] Compared with the prior art, the aircraft of the present invention has at least the following advantages: since it includes the turbine engine described above, and the turbine engine includes the connection structure of the turbine rotor described above, it also has the same beneficial effects as the connection structure of the turbine rotor described above, so it will not be repeated here.

[0034] Other features and advantages of the present invention will be described in the following description, and partly become obvious from the description, or be understood by implementing the present invention. The purpose and other advantages of the present invention can be realized and obtained by the structures pointed out in the description and the drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0036] Figure 1 A schematic diagram showing a connection structure between an existing turbine stub shaft and a turbine disk is shown;

[0037] Figure 2 A schematic diagram showing a connection structure of a turbine rotor in an embodiment of the present invention is shown;

[0038] Figure 3 A schematic diagram of a shaft body in an embodiment of the present invention is shown.

[0039] In the figure, 100, shaft body; 110, connecting section; 120, journal section; 130, first deformation structure; 131, first turning section; 132, first cone shell; 140, sealing comb teeth; 150, second deformation structure; 151, second turning section; 152, second cone shell; 160, sealing section; 161, brush sealing surface; 200, turbine disk; 300, bolts. DETAILED DESCRIPTION

[0040] In order to make the purpose, technical solution and advantages of the embodiments of the present invention clearer, the technical solution in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0041] Reference Figure 2 The present invention provides a connection structure of a turbine rotor, comprising: a shaft body 100 and a turbine disc 200. The shaft body 100 is provided with a connection section 110 and a shaft neck section 120 for assembling a bearing matched with the turbine rotor. A connection surface is provided on one side of the turbine disc 200, and the connection surface is connected to the connection section 110. A first deformation structure 130 is provided between the connection section 110 and the shaft neck section 120, and the vibration load of the turbine rotor drives the first deformation structure 130 to deform and absorb strain energy.

[0042] Specifically, the shaft body 100 is provided with a connecting section 110, and a connecting surface is provided on one side of the turbine disk 200. The dimensions of the connecting surface and the inner wall of the connecting section 110 are adapted to each other. The connecting surface abuts against the inner wall of the connecting section 110 and is passed through by bolts 300 in sequence, thereby realizing the connection between the shaft body 100 and the turbine disk 200. Figure 3 A first deformation structure 130 is provided between the connecting section 110 and the journal section 120 of the shaft body 100. The first deformation structure 130 has a low rigidity, so that it can be deformed under the action of an external force. Then, when the connecting structure of the turbine rotor is put into operation, the load generated by the vibration of the turbine rotor can be deformed by the first deformation structure 130 to absorb the corresponding strain energy. This not only avoids the vibration load generated by the turbine rotor from affecting the contact state between the shaft body 100 and the turbine disk 200, thereby ensuring reliable torque transmission, but also avoids the vibration load generated by the turbine rotor being completely borne by the assembled bearing fulcrum, thereby improving the service life of the bearing.

[0043] At the same time, the connecting surface and the connecting section 110 may also be connected by riveting.

[0044] In some specific embodiments of the present invention, referring to Figure 3 A sealing grate 140 is provided on the side of the connection section 110 away from the first deformation structure 130. The size of the sealing grate 140 matches the size of the honeycomb on the bearing seat. Specifically, the sealing grate 140 is provided on the side of the connection section 110 away from the first deformation structure 130, and the sealing grate 140 also matches the size of the honeycomb on the bearing seat that matches the bearing, so that the sealing grate 140 and the honeycomb form a sealing structure to ensure the sealing effect when the connection structure of the turbine rotor is put into operation.

[0045] It should be noted that the matching relationship between the honeycomb and the sealing comb teeth 140 is the existing technology. Specifically, a shaft sleeve is arranged on the bearing seat, and the inner ring surface of the shaft sleeve is composed of a plurality of honeycomb cavities. There are a plurality of sealing comb teeth 140, and the plurality of sealing comb teeth 140 are arranged along the axial direction of the shaft sleeve. The plurality of sealing comb teeth 140 are matched with the inner ring surface clearance of the honeycomb sleeve, and the inlets of the plurality of honeycomb cavities are all inclined toward the direction of the airflow, thereby increasing the ability of the airflow to invade the honeycomb cavity, so that a vortex can be generated inside the honeycomb, thereby forming damping for the airflow, thereby sealing and reducing leakage.

[0046] In some specific embodiments of the present invention, referring to Figure 3 A second deformation structure 150 is provided between the connecting section 110 and the sealing grate teeth 140 , and the scraping load of the sealing grate teeth 140 drives the second deformation structure 150 to deform and absorb strain energy.

[0047] Specifically, a second deformation structure 150 is provided between the connecting section 110 and the sealing grate teeth 140, and the rigidity strength of the second deformation structure 150 is also relatively low, so that it can be deformed under the action of external force. When the connecting structure of the turbine rotor is put into operation, the sealing grate teeth 140 and the honeycomb on the bearing seat will continuously be scraped. Under the action of the second deformation structure 150, the load generated by the scraping of the sealing grate teeth 140 can be deformed by the second deformation structure 150 to absorb the corresponding strain energy, thereby avoiding the contact state between the shaft body 100 and the turbine disk 200 being affected by the scraping load of the sealing grate teeth 140, further ensuring the reliable torque transmission, and avoiding the scraping load generated by the sealing grate teeth 140 affecting the contact state between the shaft body 100 and the turbine disk 200.

[0048] In some specific embodiments of the present invention, referring to Figure 3 The first deformation structure 130 includes: a first turning section 131 and a first cone shell 132. One side of the first turning section 131 is connected to the connecting section 110. The side of the first turning section 131 away from the connecting section 110 first extends toward the turbine disk 200, then bends and extends away from the turbine disk 200 and is connected to the journal section 120 through the first cone shell 132. The thickness of the first cone shell 132 is less than the first preset value.

[0049] Specifically, the connecting section 110 is connected to the journal section 120 through the first turning section 131 and the first cone shell 132 in sequence, wherein one side of the first turning section 131 is connected to the side of the connecting section 110 away from the journal section 120, and the other side of the first turning section 131 first extends in the axial direction of the shaft body 100 toward the turbine disk 200, and then extends toward the axis of the shaft body 100 along the axis perpendicular to the shaft body 100 through a bending arrangement and is connected to the first cone shell 132. The side of the first cone shell 132 away from the first turning section 131 is connected to the side of the journal section 120 close to the connecting section 110, and the direction of the first cone shell 132 is arranged along the outer wall direction of the turbine disk 200, so as to minimize the diameter size of the journal section 120 connected to the first cone shell 132. At the same time, the thickness size of the first cone shell 132 is also less than the first preset value, so that the rigidity strength of the first cone shell 132 is reduced. When the connection structure of the turbine rotor is put into operation, the load generated by the vibration of the turbine rotor can be deformed by the first cone shell 132 to absorb the corresponding strain energy, thereby greatly reducing the transmission of the vibration load. Combined with the first cone shell 132 and the first turning section 131 between the connecting section 110, it can further prevent the vibration load generated by the turbine rotor from being transmitted to the connecting section 110, thereby ensuring that the contact state between the shaft body 100 and the turbine disk 200 can remain normal.

[0050] In some specific embodiments of the present invention, referring to Figure 3The second deformation structure 150 includes: a second turning section 151 and a second cone shell 152. One side of the second turning section 151 is connected to the connecting section 110 through the second cone shell 152. The side of the second turning section 151 away from the connecting section 110 first extends away from the turbine disk 200, then bends and extends toward the turbine disk 200 and is connected to the sealing comb teeth 140. The thickness of the second cone shell 152 is less than the second preset value.

[0051] Specifically, the connecting section 110 is connected to the journal section 120 through the second cone shell 152 and the second turning section 151 in sequence, wherein one side of the second cone shell 152 is connected to the side of the connecting section 110 away from the first turning section 131, and one side of the second turning section 151 is connected to the side of the second cone shell 152 away from the connecting section 110, and the other side of the second turning section 151 first extends in a direction perpendicular to the axial direction of the shaft body 100 in a direction away from the axis of the shaft body 100. Because the outer wall of the turbine disk 200 is inclined, when the side of the second turning section 151 away from the second cone shell 152 extends in a direction perpendicular to the axial direction of the shaft body 100 in a direction away from the axis of the shaft body 100, 0, the side of the second turning section 151 away from the second cone shell 152 is also gradually away from the outer wall of the turbine disk 200, thereby driving the second turning section 151 away from the side of the second cone shell 152, and then extending in the direction close to the turbine disk 200 through the bending setting until the shape and size of the outer wall of the second turning section 151 forms a platform structure that is compatible with the shape and size of the honeycomb of the bearing seat, thereby facilitating the setting of the sealing grate teeth 140 on the outer wall of the second turning section 151, completing the connection between the second turning section 151 and the sealing grate teeth 140, and also facilitating the setting of the sealing grate teeth 140 to be compatible with the size of the honeycomb of the bearing seat. When the connection structure of the turbine rotor is put into operation, the load generated by the scraping of the sealing grate teeth 140 can be transmitted to the second cone shell 152 by the second turning section 151, and then the second cone shell 152 is deformed to absorb the corresponding strain energy, thereby greatly reducing the transmission of the scraping load. In conjunction with the second turning section 151, it can also reduce in advance the scraping load generated by the sealing grate teeth 140 that is transmitted to the second cone shell 152, thereby ensuring that the contact state between the shaft body 100 and the turbine disc 200 can remain normal.

[0052] Furthermore, the side of the second conical shell 152 close to the connecting section 110 is arranged close to the outer wall of the turbine disk 200, and the side of the second conical shell 152 away from the connecting section 110 is arranged away from the outer wall of the turbine disk 200, so that the second conical shell 152 is arranged as a whole at an angle, so that there is a gap between the side of the second conical shell 152 away from the connecting section 110 and the outer wall of the turbine disk 200, which facilitates the second turning section 151 to form a platform structure that is compatible with the size of the honeycomb of the bearing seat.

[0053] In some specific embodiments of the present invention, referring to Figure 3A sealing section 160 is provided between the second deformation structure 150 and the connecting section 110, and a brush sealing surface 161 is provided on the outer wall of the sealing section 160. The brush sealing surface 161 is adapted to the size of the brush structure on the bearing seat. Specifically, the sealing section 160 is provided between the second cone shell 152 and the connecting section 110 and is connected to the second cone shell 152 and the connecting section 110 respectively. The setting direction of the sealing section 160 is adapted to the size of the setting direction of the brush structure on the bearing seat, so that a brush sealing surface 161 that can cooperate with the brush structure on the bearing seat is provided on the outer wall of the sealing section 160, thereby forming a sealing structure through the brush sealing surface 161 and the brush structure, and the matching relationship between the sealing comb teeth 140 and the honeycomb, and then the two sealing methods are combined to further improve the sealing effect.

[0054] It should be noted that the matching relationship between the brush wire sealing surface 161 and the brush wire structure is the prior art, specifically, a ring sleeve is provided on the bearing seat, the ring sleeve is provided on the brush wire sealing surface 161, and a brush wire bundle with a high density and inclined arrangement is provided on the brush wire sealing surface 161. When rotating, the brush wire sealing surface 161 contacts and rubs with the inner ring surface of the ring sleeve through the brush wires of the brush wire bundle. When the airflow passes through the brush wire bundle, due to the unevenness of the gaps between the brush wires of the brush wire bundle, the uniform airflow becomes uneven in the brush wire bundle, thereby forming bias flow, co-directional flow, jet flow, and random secondary flow and vortex flow. By forming the above-mentioned complex fluid flows, it helps to enhance the sealing effect and prevent leakage. At the same time, the brush wires of the brush wire bundle also play the role of countless small springs, thereby avoiding the increase of the gap between the two due to direct, long-term, high-frequency contact and friction with the inner ring surface of the ring sleeve, thereby ensuring the sealing effect.

[0055] In some specific embodiments of the present invention, referring to Figure 3 The inner wall of the sealing section 160 and the inner wall of the first deformation structure 130 together form a limiting groove. The width dimension of the limiting groove is adapted to the width dimension of the connecting surface of the turbine disk 200. Specifically, one side of the sealing section 160 is connected to the connecting section 110 away from the first turning section 131, and the other side of the sealing section 160 extends along the axial direction of the shaft body 100 toward the turbine disk 200 and is connected to the side of the second cone shell 152 close to the connecting section 110, so that the inner wall of the sealing section 160 and the inner wall of the bending part of the first turning section 131 together form a limiting groove, and the width dimension of the limiting groove is adapted to the width dimension of the connecting surface of the turbine disk 200. Refer to Figure 2When the connecting surface is connected to the connecting section 110, the sides of the connecting surface can respectively abut against the inner wall of the sealing section 160 and the inner wall of the bend of the first turning section 131, and after the connecting surface is connected to the connecting section 110, the connecting surface can be clamped in the limiting groove by the inner wall of the sealing section 160 and the inner wall of the bend of the first turning section 131, so as to limit the position between the connecting surface and the connecting section 110, thereby ensuring the connection stability between the turbine disk 200 and the shaft body 100, and avoiding relative movement between the turbine disk 200 and the shaft body 100 even if some vibration load or scraping load is transmitted to the connecting section 110.

[0056] In some specific embodiments of the present invention, the rigidity of the first cone shell 132 is lower than the rigidity of the first transition section 131, so that when the vibration load generated by the turbine rotor is transmitted, the first cone shell 132 can be deformed smoothly and absorb the corresponding strain energy. At the same time, the rigidity of the second cone shell 152 is also lower than the rigidity of the second transition section 151, so that when the scraping load generated by the sealing grate teeth 140 is transmitted, the second cone shell 152 can be deformed smoothly and absorb the corresponding strain energy.

[0057] The present invention also provides a turbine engine, comprising: a connection structure of a turbine rotor as in any of the above-mentioned specific embodiments. Specifically, when the turbine engine is put into operation, the connection structure of the turbine rotor therein can be deformed by the first cone shell 132 to absorb the corresponding strain energy in response to the load generated by the vibration of the turbine rotor, thereby greatly reducing the transmission of the vibration load, ensuring reliable torque transmission, and avoiding the vibration load generated by the turbine rotor being completely borne by the assembled bearing fulcrum, thereby improving the service life of the bearing. The connection structure of the turbine rotor therein can be transmitted from the second turning section 151 to the second cone shell 152 in response to the load generated by the scraping of the sealing comb teeth 140, and then the second cone shell 152 can be deformed to absorb the corresponding strain energy, thereby greatly reducing the transmission of the scraping load, further ensuring reliable torque transmission. The turbine engine can operate normally and stably for a long time.

[0058] The present invention also provides an aircraft, comprising: the turbine engine as described above. Specifically, when the aircraft is put into operation, the turbine engine arranged therein can operate normally and stably for a long time, thereby greatly improving the operational safety of the aircraft.

[0059] Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent substitutions for some of the technical features therein; and these modifications or substitutions do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A connection structure of a turbine rotor, characterized in that: include: A shaft body (100) is provided with a connecting section (110) and a journal section (120), wherein the journal section (120) is used to assemble a bearing matched with a turbine rotor; A turbine disk (200) having a connection surface disposed on one side thereof, the connection surface being connected to the connection section (110); A first deformation structure (130) is provided between the connecting section (110) and the journal section (120), and the vibration load of the turbine rotor drives the first deformation structure (130) to deform and absorb strain energy.

2. The connection structure of the turbine rotor according to claim 1, characterized in that: A sealing comb tooth (140) is provided on a side of the connecting section (110) away from the first deformation structure (130); The size of the sealing comb teeth (140) is matched with the size of the honeycomb on the bearing seat.

3. The connection structure of the turbine rotor according to claim 2, characterized in that: A second deformation structure (150) is provided between the connecting section (110) and the sealing grate teeth (140), and the scraping load of the sealing grate teeth (140) drives the second deformation structure (150) to deform and absorb strain energy.

4. The connection structure of the turbine rotor according to claim 3, characterized in that: The first deformation structure (130) comprises: A first turning section (131) and a first cone shell (132); One side of the first turning section (131) is connected to the connecting section (110); The side of the first turning section (131) away from the connecting section (110) first extends in a direction close to the turbine disk (200), then bends and extends in a direction away from the turbine disk (200), and is connected to the journal section (120) through the first cone shell (132); The thickness of the first cone shell (132) is smaller than a first preset value.

5. The connection structure of the turbine rotor according to claim 4, characterized in that: The second deformation structure (150) comprises: A second turning section (151) and a second cone shell (152); One side of the second turning section (151) is connected to the connecting section (110) via the second cone shell (152); The side of the second turning section (151) away from the connecting section (110) first extends in a direction away from the turbine disc (200), then bends and extends in a direction close to the turbine disc (200) and is connected to the sealing comb teeth (140); The thickness of the second cone shell (152) is smaller than a second preset value.

6. The connection structure of the turbine rotor according to claim 4, characterized in that: A sealing section (160) is provided between the second deformation structure (150) and the connecting section (110), and a brush sealing surface (161) is provided on the outer wall of the sealing section (160); The size of the brush sealing surface (161) is compatible with the size of the brush structure on the bearing seat.

7. The connection structure of the turbine rotor according to claim 6, characterized in that: The inner wall of the sealing section (160) and the inner wall of the first deformation structure (130) are combined to form a limiting groove; The width dimension of the limiting groove is matched with the width dimension of the connecting surface of the turbine disc (200).

8. The connection structure of the turbine rotor according to claim 5, characterized in that: The rigidity strength of the first cone shell (132) is lower than the rigidity strength of the first turning section (131); The rigidity strength of the second cone shell (152) is lower than the rigidity strength of the second turning section (151).

9. A turbine engine, characterized in that: include: A turbine rotor connection structure as claimed in any one of claims 1 to 8.

10. An aircraft, characterized in that: include: The turbine engine as claimed in claim 9.

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