Fusing structure for necking bolt of aero-engine and aero-engine

Abstract

The invention provides a fusing structure for an aero-engine necking bolt and an aero-engine, the fusing structure for the aero-engine necking bolt comprises a first conical wall, a second conical wall, a plurality of protective shells, a first connecting piece and a connecting assembly, one end of the first conical wall is used for supporting a first bearing, and the other end of the first conical wall is used for supporting a second bearing; one end of the second conical wall is connected with the intermediate case frame through a first connecting piece, the other end of the first conical wall is connected with the other end of the second conical wall through a connecting assembly, the protective shells are installed at the other end of the first conical wall, a cavity is defined by each protective shell and the first conical wall, and the connecting assemblies are arranged in the cavities in a covering mode; wherein the connecting assembly comprises a fusing bolt assembly, and when the fusing bolt assembly is disconnected, the cavity is used for containing the disconnected part, close to one side of the first conical wall, of the fusing bolt assembly. Through the arrangement of the protective shell, after the fusing bolt is fractured, the fractured part is accommodated by the protective shell and does not cause impact damage to the rotor structure.

Description

Technical Field

[0001] The invention relates to the technical field of aeroengines, and in particular to a fusing structure for a necked bolt of an aeroengine and an aeroengine. Background Art

[0002] Aircraft engines need to ensure that a fan blade off (FBO) event does not lead to catastrophic consequences. For this reason, fuse design is applied to engine design to ensure the safety of aircraft engines when FBO events occur.

[0003] At present, the common fuse design scheme is to set a fuse component near the No. 1 bearing closest to the fan, such as a necked bolt, a cone wall with a thinned section, etc. The fuse structure used for the necked bolt of the aircraft engine fails under the action of a predetermined load, reducing the unbalanced load transmitted to the intermediate casing through the bearing and its support, etc., and avoiding damage to other key components of the engine.

[0004] The weak section of the cone wall will cause the front section of the cone wall to collide and rub against the fan shaft after the melting, increasing the risk of fire. It is also easy to damage the lubrication of the No. 1 bearing, causing dry grinding, overheating and jamming of the bearing, resulting in the engine not being able to rotate normally. As for the fuse bolt method, the fuse bolt will fall off after failure, causing impact damage to the rotor structure, and the cone wall also has the risk of collision and friction with the fan shaft. In order to reduce the risk of secondary collision after melting, some structures have added a second layer of cone wall and other devices, but this device increases the overall weight of the engine and increases operating costs.

[0005] Based on this, the inventor of the present application has designed a fuse structure for an aircraft engine necking bolt and an aircraft engine, in order to solve the above-mentioned technical problems. Summary of the invention

[0006] The technical problem to be solved by the present invention is to overcome the defects in the prior art that the bolts of the fuse structure used for the necking bolts of aircraft engines are easily collided with the fan blades or the front section of the cone wall after melting is easily rubbed with the fan shaft, and to provide a fuse structure for the necking bolts of aircraft engines and an aircraft engine.

[0007] The present invention solves the above technical problems through the following technical solutions:

[0008] The present invention provides a fusing structure for an aircraft engine neck bolt, which is characterized by comprising:

[0009] A first cone wall, a second cone wall, a plurality of protective shells, a first connecting member and a connecting assembly, wherein one end of the first cone wall is used to support a first bearing;

[0010] One end of the second cone wall is connected to the intermediate casing frame through the first connecting piece, the other end of the first cone wall is connected to the other end of the second cone wall through the connecting component, the protective shell is installed at the other end of the first cone wall, each of the protective shells and the first cone wall forms a chamber, and the connecting component cover is arranged in the chamber; wherein,

[0011] The connection assembly includes a fuse bolt assembly. When the fuse bolt assembly is disconnected, the chamber is used to receive a disconnected portion of the fuse bolt assembly close to the first cone wall.

[0012] According to one embodiment of the present invention, at least two installation plates are arranged at intervals at the other end of the first cone wall, and installation gaps are formed between adjacent installation plates. The protective shell is connected to the installation plates, and the first connecting member passes through the installation gap to connect to the second cone wall and the intermediate casing frame.

[0013] The second connecting member and the fuse bolt assembly pass through the mounting plate and are connected to the second cone wall.

[0014] According to one embodiment of the present invention, the fuse bolt assembly includes a bolt body and a bolt washer;

[0015] The bolt washer is located on the side of the first cone wall away from the second cone wall, and the bolt body is passed through the bolt washer and connected to the first cone wall and the second cone wall;

[0016] A limiting hole is provided in the middle of the bolt gasket, the hole wall of the limiting hole is arc-shaped, and an arc-shaped boss which is matched and installed with the arc-shaped hole wall of the limiting hole is provided on the bolt body.

[0017] According to an embodiment of the present invention, a first matching hole matching with the fuse bolt is formed on the first cone wall, and a second matching hole matching with the fuse bolt is formed on the second cone wall;

[0018] A contraction section is provided in the middle of the bolt body, and a rotation-stopping boss is also provided on the bolt body. When the bolt body is installed, the contraction section is located in the first matching hole, and the rotation-stopping boss is located in the second matching hole.

[0019] According to one embodiment of the present invention, the fuse bolt assembly further includes an elastic bushing and a mounting nut, wherein the elastic bushing is sleeved on the outside of the contraction section, and the mounting nut is disposed on a side of the second cone wall away from the first cone wall and is threadedly connected to the bolt body.

[0020] According to one embodiment of the present invention, the connection assembly further includes a second connection member, which is located in the protective shell and is used to connect the first cone wall and the second cone wall;

[0021] The second connecting member includes a connecting bolt, an elastic member and a connecting nut, and the elastic member is sleeved on the connecting bolt;

[0022] The elastic member is installed on a side of the mounting plate away from the second cone wall, and the connecting nut is located on a side of the second cone wall away from the mounting plate and is threadedly connected to the connecting bolt.

[0023] According to an embodiment of the present invention, a plurality of the protective shells are evenly spaced apart along the outer circumference of the first cone wall, and a plurality of the second connecting members are disposed between adjacent protective shells to connect the second cone wall and the intermediate casing.

[0024] According to one embodiment of the present invention, an oil supply pipeline is further provided on the outer side of the first cone wall, one end of the oil supply pipeline extends to the first bearing, and the other end extends to the intermediate casing frame;

[0025] The length of the oil supply pipeline is adjustable.

[0026] According to an embodiment of the present invention, the oil supply pipeline is connected to the first cone wall via a mounting frame, and a corrugated section is provided on a side of the oil supply pipeline close to the intermediate casing frame.

[0027] According to an embodiment of the present invention, a receiving groove is formed on the second cone wall facing the first cone wall, and the first cone wall is sleeved in the receiving groove and connected to the second cone wall;

[0028] The outer peripheral portion where the first cone wall and the second cone wall are connected is arranged in an arc shape.

[0029] The present invention also provides an aircraft engine, which is characterized in that it includes:

[0030] Intermediate casing frame;

[0031] First bearing;

[0032] As described above, the fuse structure for the aircraft engine neck bolt has one end connected to the first bearing, and the other end connected to the intermediate casing frame.

[0033] The positive and progressive effects of the present invention are:

[0034] The present invention is used for the fusing structure of the necked bolt of an aero-engine, and has the following advantages:

[0035] 1. The first cone wall and the second cone wall are connected by a fuse bolt assembly, and a protective shell is provided on the outside of the first cone wall on the fuse bolt assembly, so that when the fuse bolt breaks, the broken part is received by the protective shell and will not cause impact damage to the rotor structure.

[0036] 2. The contact surface between the bolt body and the bolt gasket is an arc surface, which ensures that the contraction section of the bolt body is not subjected to bending moment, and the bolt body only bears tension, which increases the accuracy of the design calculation results and the reliability of the structure.

[0037] 3. An elastic bushing is arranged outside the contraction section of the bolt body, so that the tightening torque during installation of the bolt body can be accurately controlled, the dispersion of the pre-tightening force is reduced, and the connection reliability of the bolt body to the first cone wall and the second cone wall is increased.

[0038] Fourth, a corrugated section is provided on the oil supply pipeline near the intermediate casing frame, so that the circular swinging motion of the first cone wall will not affect the integrity of the pipeline and will not damage the oil supply pipeline, thereby ensuring the function of the No. 1 bearing and its squeeze film damper. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] The above and other features, properties and advantages of the present invention will become more apparent through the following description in conjunction with the accompanying drawings and embodiments, in which:

[0040] Figure 1 It is a partial structural schematic diagram of the aircraft engine of the present invention;

[0041] Figure 2 It is a structural schematic diagram of a fusing structure for an aircraft engine necking bolt of the present invention;

[0042] Figure 3 for Figure 2 A partial cross-sectional view of a fuse structure for an aircraft engine neck bolt is shown;

[0043] Figure 4 for Figure 2 The exploded structural diagram of the fusing structure for the necked bolt of an aero-engine is shown;

[0044] Figure 5 It is a schematic diagram of the installation of the fuse bolt assembly of the present invention;

[0045] Figure 6 It is a structural schematic diagram of an embodiment of a fuse bolt assembly of the present invention;

[0046] Figure 7 This is a schematic diagram of the structure inside the protective shell of the present invention;

[0047] Figure 8 is a cross-sectional view at an angle of the second connecting member;

[0048] Fig. 9 A diagram showing a matching state of a first cone wall and a second cone wall in one embodiment of the prior art of the present invention;

[0049] Fig.10 for Figure 7 A schematic diagram of the enlarged structure at A in the middle;

[0050] Fig.11 The cross-sectional view is a sectional view of an embodiment of the fusing structure of the neck bolt for an aircraft engine according to the present invention. DETAILED DESCRIPTION

[0051] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the specific embodiments of the present invention are described in detail below with reference to the accompanying drawings.

[0052] Embodiments of the present invention will now be described in detail with reference to the accompanying drawings. Reference will now be made in detail to preferred embodiments of the present invention, examples of which are shown in the accompanying drawings. Wherever possible, the same reference numerals will be used in all drawings to represent the same or similar parts. In addition, although the terms used in the present invention are selected from well-known and commonly used terms, some of the terms mentioned in the specification of the present invention may be selected by the applicant at his or her discretion, and their detailed meanings are explained in the relevant parts of the description herein. In addition, it is required to understand the present invention not only by the actual terms used, but also by the meaning implied by each term.

[0053] Please refer to Figures 1 to 11 , describing the fusing structure for the aero-engine necking bolt and the aero-engine of the present invention.

[0054] Reference Figures 1 to 3 The present invention proposes a fuse structure for an aircraft engine necking bolt, comprising a first cone wall 10, a second cone wall 30, a plurality of protective shells 110, a first connecting member 310 and a connecting assembly 50, wherein one end of the first cone wall 10 is used to support a first bearing 20. One end of the second cone wall 30 is connected to an intermediate casing frame 40 through the first connecting member 310, and the other end of the first cone wall 10 is connected to the other end of the second cone wall 30 through the connecting assembly 50. The protective shell 110 is installed at the other end of the first cone wall 10, and a chamber is enclosed between each protective shell 110 and the first cone wall 10, and the connecting assembly 50 is covered in the chamber.

[0055] The connection assembly 50 includes a fuse bolt assembly 510 . When the fuse bolt assembly 510 is disconnected, the chamber is used to receive the disconnected portion of the fuse bolt assembly 510 close to the first cone wall 10 .

[0056] It should be noted that a protective shell 110 is provided on the first cone wall 10, and the fuse bolt assembly 510 is arranged in the protective shell 110. In this way, when the fuse bolt assembly 510 is disconnected, the disconnected part close to the side of the first cone wall 10 is received by the protective shell 110, and will not fly out and collide with rotor components such as fan blades, thereby reducing the serious impact of the fuse bolt assembly 510 on rotor components such as fan blades after it is melted.

[0057] The protective shell 110 and the first cone wall 10 may be connected by bonding or welding, and welding is preferred to improve the connection strength between the protective shell 110 and the first cone wall 10. In some other embodiments, the protective shell 110 and the first cone wall 10 may also be connected by bonding, which is not limited here.

[0058] In one embodiment, a hole is provided on the intermediate casing frame 40 to accommodate the other part of the disconnected fuse bolt assembly 510, so that when the fuse bolt assembly 510 is disconnected, the two disconnected sections are respectively collected by the hole on the intermediate casing side and the protective shell 110 provided on the first cone wall 10, thereby preventing the disconnected fuse bolt from flying around and impacting components such as rotor blades.

[0059] Please refer to Figures 4 to 6 In one embodiment, at least two mounting plates 120 are spaced apart from each other at the second end of the first cone wall 10 , and a mounting gap 121 is formed between adjacent mounting plates 120 . The protective shell 110 is connected to the mounting plates 120 , and the first connecting member 310 passes through the mounting gap 121 to connect to the second cone wall 30 and the intermediate casing.

[0060] The installation process of the first cone wall 10, the second cone wall 30 and the intermediate casing frame 40 is as follows:

[0061] First, the first cone wall 10 and the second cone wall 30 are installed by the fuse bolt assembly 510 . After the installation is completed, the second cone wall 30 and the intermediate casing frame 40 are installed by the second connecting member 520 .

[0062] In one embodiment, at least two mounting plates 120 are evenly spaced apart along the outer circumference of the first cone wall 10 , thereby improving the connection stability of the connecting assembly 50 to the first cone wall 10 and the second cone wall 30 .

[0063] Correspondingly, at least two protective shells 110 are evenly spaced apart along the outer circumference of the first cone wall 10 , and at least two second connecting members 520 connect the second cone wall 30 and the intermediate casing frame 40 between adjacent protective shells 110 .

[0064] In one embodiment, the number of protective shells 110 is more than 3, and the plurality of protective shells 110 are evenly spaced around the outer circumference of the first cone wall 10. It should be noted that the more protective shells 110 are provided, the higher the connection stability between the first cone wall 10 and the second cone wall 30 is under the connection of the connection assembly 50.

[0065] In one embodiment, the fuse bolt assembly 510 includes a bolt body 511 and a bolt washer 512, the bolt washer 512 is located on the side of the first cone wall 10 away from the second cone wall 30, the bolt body 511 is penetrated by the bolt washer 512 and connected to the first cone wall 10 and the second cone wall 30. A limiting hole 513 is provided in the middle of the bolt washer 512, the hole wall of the limiting hole 513 is arc-shaped, and an arc-shaped boss 514 is provided on the bolt body 511 to be matched with the arc-shaped hole wall of the limiting hole 513.

[0066] The contact surface between the arc-shaped boss 514 and the arc-shaped hole wall is an arc surface. When the first cone wall 10 is greatly deformed under the overturning moment (refer to Figure 6 The distance a) in the bolt body 511 can still make the contraction section 515 (see below) of the bolt body 511 mainly bear the tensile force through the sliding of the arc surface between the bolt body 511 and the bolt washer 512.

[0067] Furthermore, a first matching hole 130 matching with the fuse bolt assembly 510 is opened on the first cone wall 10, and a second matching hole 320 matching with the fuse bolt assembly 510 is opened on the second cone wall 30. A contraction section 515 is provided in the middle of the bolt body 511, and a stop-rotation boss 516 is also provided on the bolt body 511. When the bolt body 511 is in the installed state, the contraction section 515 is located in the first matching hole 130, and the stop-rotation boss 516 is located in the second matching hole 320.

[0068] That is, by providing the anti-rotation boss 516, the bolt body 511 only bears axial thrust, and the torque transmitted by the installation nut 518 (see below) only acts on the anti-rotation boss 516, thereby preventing the contraction section 515 of the bolt body 511 from being subjected to the torque of the nut during the installation process. The contraction section 515 only needs to bear axial load, thereby ensuring the accuracy of the design structure of the bolt body 511 and the reliability of the installation of the bolt body 511.

[0069] That is, by setting the installation contact surface between the bolt body 511 and the bolt gasket 512 as an arc surface, it can be ensured that the contraction section 515 of the bolt body 511 is not subjected to bending moment, and then under the action of the arc surface and the anti-rotation boss 516, the contraction section 515 of the bolt body 511 only bears tensile force, thereby increasing the accuracy of the calculation results during design and increasing the structural reliability.

[0070] In one embodiment, the fuse bolt assembly 510 also includes an elastic bushing 517 and a mounting nut 518. The elastic bushing 517 is sleeved on the outside of the contraction section 515. The mounting nut 518 is disposed on the side of the second cone wall 30 away from the first cone wall 10 and is threadedly connected to the bolt body 511.

[0071] An elastic bushing 517 is arranged outside the contraction section 515 of the bolt body 511. The elastic bushing 517 can measure the relationship between the tightening torque and the pre-tightening force, so as to accurately control the pre-tightening force of the bolt body 511 and avoid the bolt body 511 from breaking prematurely or not breaking due to the dispersion of the pre-tightening force.

[0072] Please refer to Figures 7 and 8 In one embodiment, the connecting assembly 50 further includes a second connecting member 520, which is located in the protective shell 110 and is used to connect the first cone wall 10 and the second cone wall 30. The second connecting member 520 includes a connecting bolt 521, an elastic member 522, and a connecting nut 523. The elastic member 522 is sleeved on the connecting bolt 521, and the elastic member 522 is installed on the side of the mounting plate 120 away from the second cone wall 30. The connecting nut 523 is located on the side of the second cone wall 30 away from the mounting plate 120 and is threadedly connected to the connecting bolt 521.

[0073] The second connecting member 520 is provided to continue connecting the first cone wall 10 and the second cone wall 30 after the fuse bolt assembly 510 is blown, so as to prevent the first cone wall 10 from moving forward and rubbing against the fan blades.

[0074] It should be noted that three types of holes are provided on the intermediate casing frame 40. The first type of hole is used to accommodate the protruding portion of the first connecting member 310. The second type of hole is used to accommodate the protruding portion of the fuse bolt assembly 510 and is also used to collect the fused portion after the fuse bolt is melted. The third type of hole is used to accommodate the protruding portion of the second connecting member 520.

[0075] Please refer to Figures 9 to 11 In one embodiment, an oil supply pipeline 140 is further provided on the outer side of the first cone wall 10 , one end of the oil supply pipeline 140 extends to the first bearing 20 , and the other end extends to the intermediate casing frame 40 ; the length of the oil supply pipeline 140 is adjustable.

[0076] Specifically, the oil supply pipeline 140 is connected to the first cone wall 10 through a mounting frame, and a corrugated section 141 is provided on a side of the oil supply pipeline 140 close to the intermediate casing frame 40 .

[0077] A corrugated section 141 with adjustable length is provided on the oil supply pipeline 140 installed on the outside of the first cone wall 10, so as to ensure that the oil supply pipeline 140 is not affected after the fuse bolt assembly 510 is melted, and its integrity and functionality can be maintained, and oil can continue to be supplied to the No. 1 bearing and the squeeze film damper.

[0078] After the fuse bolt assembly 510 is fused, the first cone wall 10 moves in a circular swing near the No. 1 bearing (refer to Fig. 9 ), a corrugated section 141 is provided on the oil supply pipeline 140, which is beneficial to not affecting the normal oil supply of the oil supply pipeline 140 when the first cone wall 10 makes a circular swinging motion, thereby ensuring the integrity and effectiveness of the oil supply pipeline 140 after the fuse bolt assembly 510 is melted, and at the same time ensuring that the oil supply pipeline 140 can still supply oil to the No. 1 bearing and its squeeze film damper after the fuse bolt assembly 510 is melted.

[0079] Reference Fig.10 In one embodiment, a receiving groove 330 is provided on the second cone wall 30 facing the first cone wall 10, the first cone wall 10 is sleeved in the receiving groove 330 and connected to the second cone wall 30, and the outer peripheral portion where the first cone wall 10 and the second cone wall 30 are connected is an arc-shaped setting.

[0080] That is, the outer peripheral surface of the first cone wall 10 is an arc-shaped stop structure. In the initial installation state, the stop has a centering and positioning function. After the fuse bolt assembly 510 is blown, the first cone wall 10 close to the No. 1 bearing has a larger displacement and performs a circular swinging motion. The first cone wall 10 close to the intermediate casing frame 40 is connected and limited by the second connecting piece 520, and the connecting surface with the second cone wall 30 is an arc surface. In this way, it is ensured that the first cone wall 10 will not have structural interference with the second cone wall 30 during the circular swinging motion, and will not get stuck.

[0081] The present invention also proposes an aircraft engine, comprising an intermediate casing frame 40, a first bearing 20 and the above-mentioned fuse structure for the aircraft engine necking bolt, wherein one end of the fuse structure for the aircraft engine necking bolt is connected to the first bearing 20, and the other end is connected to the intermediate casing frame 40.

[0082] The present application uses specific words to describe the embodiments of the present application. For example, "one embodiment", "an embodiment", and / or "some embodiments" refer to a certain feature, structure or characteristic related to at least one embodiment of the present application. Therefore, it should be emphasized and noted that "one embodiment" or "an embodiment" or "an alternative embodiment" mentioned twice or multiple times in different positions in this specification does not necessarily refer to the same embodiment. In addition, some features, structures or characteristics in one or more embodiments of the present application can be appropriately combined.

[0083] Although the present invention is disclosed as above with preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications without departing from the spirit and scope of the present invention. Therefore, any modification, equivalent change and modification made to the above embodiments according to the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope defined by the claims of the present invention.

Claims

1. A fusing structure for an aircraft engine neck bolt, characterized in that: include: A first cone wall, a second cone wall, a plurality of protective shells, a first connecting member and a connecting assembly, wherein one end of the first cone wall is used to support a first bearing; One end of the second cone wall is connected to the intermediate casing frame through the first connecting piece, the other end of the first cone wall is connected to the other end of the second cone wall through the connecting component, the protective shell is installed at the other end of the first cone wall, each of the protective shells and the first cone wall forms a chamber, and the connecting component cover is arranged in the chamber; wherein, The connection assembly includes a fuse bolt assembly. When the fuse bolt assembly is disconnected, the chamber is used to receive a disconnected portion of the fuse bolt assembly close to the first cone wall.

2. The fuse structure for an aircraft engine neck bolt according to claim 1, characterized in that: The other end of the first cone wall is provided with at least two installation plates spaced apart from each other, and an installation gap is formed between adjacent installation plates, the protective shell is connected to the installation plates, and the first connecting member passes through the installation gap to connect to the second cone wall and the intermediate casing frame; The fuse bolt assembly passes through the mounting plate and is connected to the second cone wall.

3. The fuse structure for the aircraft engine neck bolt according to claim 2, characterized in that: The fuse bolt assembly includes a bolt body and a bolt gasket; The bolt washer is located on the side of the first cone wall away from the second cone wall, and the bolt body is passed through the bolt washer and connected to the first cone wall and the second cone wall; A limiting hole is provided in the middle of the bolt gasket, the hole wall of the limiting hole is arc-shaped, and an arc-shaped boss which is matched and installed with the arc-shaped hole wall of the limiting hole is provided on the bolt body.

4. The fuse structure for an aircraft engine neck bolt according to claim 3, characterized in that: A first matching hole matching with the fuse bolt is formed on the first cone wall, and a second matching hole matching with the fuse bolt is formed on the second cone wall; A contraction section is provided in the middle of the bolt body, and a rotation-stopping boss is also provided on the bolt body. When the bolt body is installed, the contraction section is located in the first matching hole, and the rotation-stopping boss is located in the second matching hole.

5. The fuse structure for the aircraft engine neck bolt according to claim 4, characterized in that: The fuse bolt assembly also includes an elastic bushing and a mounting nut. The elastic bushing is sleeved on the outside of the contraction section. The mounting nut is arranged on a side of the second cone wall away from the first cone wall and is threadedly connected to the bolt body.

6. The fuse structure for the aircraft engine neck bolt according to claim 2, characterized in that: The connecting assembly further includes a second connecting member, which is located in the protective shell and is used to connect the first cone wall and the second cone wall; The second connecting member includes a connecting bolt, an elastic member and a connecting nut, and the elastic member is sleeved on the connecting bolt; The elastic member is installed on a side of the mounting plate away from the second cone wall, and the connecting nut is located on a side of the second cone wall away from the mounting plate and is threadedly connected to the connecting bolt.

7. The fuse structure for an aircraft engine neck bolt according to claim 6, characterized in that: The plurality of protective shells are evenly spaced and arranged along the outer circumference of the first cone wall, and the plurality of second connecting members are arranged between adjacent protective shells to connect the second cone wall and the intermediate casing.

8. The fusing structure for an aircraft engine neck bolt according to any one of claims 1 to 7, characterized in that: An oil supply pipeline is also provided on the outer side of the first cone wall, one end of the oil supply pipeline extends to the first bearing, and the other end extends to the intermediate casing frame; The length of the oil supply pipeline is adjustable.

9. The fuse structure for an aircraft engine neck bolt according to claim 8, characterized in that: The oil supply pipeline is connected to the first cone wall through a mounting frame, and a corrugated section is provided on a side of the oil supply pipeline close to the intermediate casing frame.

10. The fusing structure for an aircraft engine neck bolt according to any one of claims 1 to 7, characterized in that: A receiving groove (330) is formed on the second cone wall on one side facing the first cone wall, and the first cone wall is sleeved in the receiving groove (330) and connected to the second cone wall; The outer peripheral portion where the first cone wall and the second cone wall are connected is arranged in an arc shape.

11. An aircraft engine, characterized in that: include: Intermediate casing frame; First bearing; According to the fuse structure for an aircraft engine necking bolt as described in any one of claims 1 to 10, one end of the first cone wall is connected to the first bearing, and one end of the second cone wall is connected to the intermediate casing frame.

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