Dismounting device for air inlet cone of aero-engine

Abstract

The invention provides an aero-engine air inlet cone dismounting device, and relates to the technical field of aero-engine part dismounting equipment, and the aero-engine air inlet cone dismounting device comprises a hooking assembly, a clamping assembly, a clamping assembly and a clamping assembly, and the hooking assembly comprises a flexible fixed pulling claw, a centering expansion sleeve and a contraction sleeve; the telescopic sleeve is movably arranged outside the pipe wall of the flexible fixed pulling claw in a sleeving mode so as to extrude and contract the flexible fixed pulling claw, and the centering expansion sleeve is arranged in the pipe wall of the flexible fixed pulling claw in a sleeving mode and used for expanding the contracted flexible fixed pulling claw so that the flexible fixed pulling claw can be stably fixed to the air inlet cone. The supporting assembly comprises a supporting end cover and a force application rod, the supporting end cover is fixed to the top end of the flexible fixed pulling claw, and the force application rod penetrates through the supporting end cover and the interior of the centering expansion sleeve; a threaded section is arranged on the force application rod, and the supporting end cover is in threaded connection with the force application rod on the threaded section, so that the supporting end cover and the flexible fixed pulling claw are driven to move upwards by rotating the force application rod, and the air inlet cone of the engine is pulled out. The disassembly efficiency of the air inlet cone is improved, and the disassembly risk is reduced.

Description

Technical Field

[0001] The present invention relates to the technical field of aero-engine component disassembly equipment, and particularly relates to a disassembly device for an aero-engine intake cone. Background Art

[0002] As one of the key links in the manufacturing process of engine products, assembly is the core hub of aero-engine manufacturing. Product R & D, mass production, and maintenance all converge on assembly, and are closely related to operations such as design, part manufacturing, testing, and operation and maintenance. The trial production of aero-engines is even more inseparable from the assembly link. The efficiency and quality of the assembly process can directly affect the R & D cycle and performance of the entire product. As an inlet flow guiding structure of an aero-engine, the intake cone plays a crucial role in guiding the intake air of the engine. Ensuring the flatness and smoothness of the intake cone surface is very important for the integration of the engine inlet air flow. This results in the inability of ordinary devices to take root on the intake cone during the disassembly process, making the disassembly process of the intake cone very difficult.

[0003] Therefore, proposing a disassembly device for an aero-engine intake cone is of great significance for the rapid assembly of aero-engines. Summary of the Invention

[0004] In view of this, the embodiments of the present application provide a disassembly device for an aero-engine intake cone, aiming to solve the problem of disassembly of the aero-engine intake cone, so as to achieve the purpose of improving the disassembly efficiency of the intake cone and reducing the disassembly risk.

[0005] The embodiments of the present application provide the following technical solutions: A disassembly device for an aero-engine intake cone, comprising:

[0006] A hook component, the hook component includes a flexible fixed claw, a centering expansion sleeve, and a contraction sleeve; the flexible fixed claw is tubular in its natural state, the flexible fixed claw includes a flexible tubular outer wall and a plurality of flexible hook teeth uniformly arranged circumferentially on the tubular outer wall, the cross-section of the flexible hook teeth is a tooth-like structure extending outward from the tube wall, for hooking the engine intake cone; the contraction sleeve is movably sleeved outside the tube wall of the flexible fixed claw, and the diameter of the contraction sleeve is smaller than the diameter of the flexible fixed claw in its natural state, so as to squeeze and contract the tube wall of the flexible fixed claw through the contraction sleeve, for inserting the bottom end of the contracted flexible fixed claw into the inner hole of the engine intake cone, and after pushing the contraction sleeve back in the reverse direction, enabling the flexible fixed claw to hook the engine intake cone through the flexible hook teeth after natural rebound; the centering expansion sleeve is sleeved inside the tube wall of the flexible fixed claw, for expanding the flexible fixed claw squeezed and contracted by the contraction sleeve inside the tube wall, so as to radially position the flexible fixed claw and stably fix the flexible fixed claw on the engine intake cone;

[0007] The supporting assembly includes a supporting end cover and a force applying rod, wherein the supporting end cover is fixedly connected to the top end of the flexible fixed claw, and the force applying rod passes through the interior of the supporting end cover and the centering expansion sleeve and extends from the bottom end of the flexible fixed claw; a threaded section is provided on the force applying rod, and the supporting end cover is threadedly connected to the force applying rod on the threaded section, so that by rotating the force applying rod, the supporting end cover is driven to move upward on the force applying rod, thereby driving the flexible fixed claw to move upward to pull out the engine intake cone.

[0008] According to one embodiment of the present application, the support assembly further includes a force extension rod, which is fixedly disposed at the top end of the force rod, and the axis of the force extension rod is perpendicular to the axis of the force rod.

[0009] According to one embodiment of the present application, the support assembly further includes a fixing rod, which is fixedly connected to the support end cover, and the axis of the fixing rod is perpendicular to the axis of the force applying rod.

[0010] According to one embodiment of the present application, the support assembly further includes a transfer spherical structure for providing a support point, wherein the transfer spherical structure is fixedly disposed at the bottom end of the force rod and is used to press the transfer spherical structure against the engine to provide a force support point.

[0011] According to one embodiment of the present application, the cross-section of the support end cover is a stepped surface, and a plurality of slots are circumferentially provided on the bottom edge of the support end cover. A plurality of protrusions adapted to the slots are circumferentially provided on the top edge of the flexible fixing claw. The protrusions are inserted into the slots and fixed by screws to fix the support end cover to the flexible fixing claw.

[0012] According to an embodiment of the present application, a length ratio of the shrinking sleeve to the flexible fixing claw is 1:3.

[0013] According to an embodiment of the present application, the flexible fixing claw is made of rubber.

[0014] According to an embodiment of the present application, the tubular outer wall of the flexible fixed claw and the flexible hook tooth are integrally formed.

[0015] Compared with the prior art, the at least one technical solution adopted in the embodiments of this specification can achieve the following beneficial effects:

[0016] (1) The air intake cone disassembly device provided by the embodiment of the present invention uses the flexible hook teeth of the flexible fixing claw to fix the air intake cone, and uses a threaded structure for disassembly. A shrinkage and expansion anti - detachment structure is added, and the force - applying and guiding structures are organically integrated, greatly improving the disassembly efficiency of the air intake cone and reducing the disassembly risk.

[0017] (2) Through this air intake cone disassembly device of the aero - engine, the problem that the air intake cone is difficult to disassemble due to its smooth surface is perfectly solved.

[0018] (3) The structure of the device has clear logic, and each part cooperates with each other, and it is easy to use. In addition, different engine air intake cones can be disassembled by modifying the adapter size. Brief Description of the Drawings

[0019] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings in the following description are only some embodiments of the present application. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0020] Figure 1 It is a schematic diagram of the overall disassembly device in the embodiment of the present invention;

[0021] Figure 2 It is a schematic cross - sectional structure diagram of the disassembly device in the embodiment of the present invention;

[0022] Figure 3 It is a schematic diagram of the flexible fixing claw in the embodiment of the present invention;

[0023] Figure 4 It is a schematic diagram of the shrinkage sleeve in the embodiment of the present invention;

[0024] Figure 5 It is a schematic diagram of the support end cover in the embodiment of the present invention;

[0025] Figure 6 It is a schematic diagram of the centering expansion sleeve in the embodiment of the present invention;

[0026] Among them, 1 - flexible fixing claw, 2 - centering expansion sleeve, 3 - shrinkage sleeve, 4 - support end cover, 5 - force - applying rod, 6 - force - applying extension rod, 7 - fixing rod, 8 - adapter spherical structure. Detailed Embodiments

[0027] The embodiments of the present application will be described in detail below with reference to the drawings.

[0028] The following describes the implementation manners of the present application through specific examples. Those skilled in the art can easily understand other advantages and effects of the present application from the content disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. The present application can also be implemented or applied through other different specific implementation manners. Various details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that, without conflict, the following embodiments and the features in the embodiments can be combined with each other. All other embodiments obtained by those of ordinary skill in the art based on the embodiments in the present application without creative efforts belong to the scope of protection of the present application.

[0029] As Figures 1-6 shown, an embodiment of the present invention provides a disassembly device for an aero-engine intake cone, including:

[0030] A hook component, the hook component includes a flexible fixed claw 1, a centering expansion sleeve 2 and a contraction sleeve 3; the flexible fixed claw 1 is tubular in its natural state, the flexible fixed claw 1 includes a flexible tubular outer wall and a plurality of flexible hook teeth circumferentially and evenly arranged on the tubular outer wall, and the cross-section of the flexible hook teeth is a tooth-like structure extending outward from the tube wall, for hooking the engine intake cone; the contraction sleeve 3 is movably sleeved outside the tube wall of the flexible fixed claw 1, and the diameter of the contraction sleeve 3 is smaller than the diameter of the flexible fixed claw 1 in its natural state, so as to squeeze and contract the tube wall of the flexible fixed claw 1 through the contraction sleeve 3, for inserting the bottom end of the contracted flexible fixed claw 1 into the inner hole of the engine intake cone, and after pushing the contraction sleeve 3 back in the reverse direction, the flexible fixed claw 1 rebounds naturally and hooks the engine intake cone through the flexible hook teeth; the centering expansion sleeve 2 is sleeved inside the tube wall of the flexible fixed claw 1, for expanding the flexible fixed claw 1 squeezed and contracted by the contraction sleeve 3 inside the tube wall, so as to radially position the flexible fixed claw 1 and make the flexible fixed claw 1 stably fixed on the engine intake cone;

[0031] A support component, the support component includes a support end cover 4 and a force application rod 5, the support end cover 4 is fixedly connected to the top end of the flexible fixed claw 1, and the force application rod 5 penetrates through the inside of the support end cover 4 and the centering expansion sleeve 2 and extends out from the bottom end of the flexible fixed claw 1; a threaded section is provided on the force application rod 5, and the support end cover 4 is threadedly connected to the force application rod 5 on the threaded section, so as to drive the support end cover 4 to move upward on the force application rod 5 by rotating the force application rod 5, thereby driving the flexible fixed claw 1 to move upward to pull out the engine intake cone.

[0032] The aircraft engine intake cone removal device according to the present invention maintains the intake opening in any aircraft engine posture. Flexible hooks on a flexible retaining claw 1 are used to position the intake cone's inner bore. A centering expansion sleeve 2 is used to radially position the intake cone, and finally, the cone is disassembled using a threaded structure. The characteristics of the threaded structure are utilized to disassemble the cone. Furthermore, a retracting sleeve 3 is added to the entire mechanism. This retracting sleeve 3 retracts the flexible hooks, effectively placing them inside the cone. Reversing the retracting sleeve 3 allows the hooks to rebound and engage the cone, simplifying operation and enhancing convenience.

[0033] In specific implementation, the flexible fixing claw 1 is a retractable cylindrical elastic structure. The elastic hook teeth are retracted inward to fix the disassembly device and the air intake cone, and the centering expansion sleeve 2 is expanded outward to stably fix the air intake cone. The two cooperate with each other to connect the flexible fixing claw 1 and the air intake cone as one.

[0034] In some embodiments of the present invention, the support assembly further includes a force extension rod 6, which is fixedly disposed at the top end of the force application rod 5, and the axis of the force extension rod 6 is perpendicular to the axis of the force application rod 5. The provision of the force extension rod 6 facilitates the rotation of the force application rod 5 by the force extension rod 6 when using the disassembly device, thereby facilitating manual operation and reducing manual effort.

[0035] In some embodiments of the present invention, the support assembly further includes a fixing rod 7, which is fixedly connected to the support end cap 4, and the axis of the fixing rod 7 is perpendicular to the axis of the force-applying rod 5. In specific implementations, the fixing rod 7 is used in conjunction with the force-applying extension rod 6. While the operator rotates the force-applying extension rod 6 with one hand, the operator holds the fixing rod 7 with the other hand, facilitating the exertion of force.

[0036] In some embodiments of the present invention, the support assembly further includes a spherical adapter structure 8 for providing a support point. This spherical adapter structure 8 is fixedly mounted at the bottom end of the force-applying rod 5 and is used to press the spherical adapter structure 8 against the engine, providing a support point for applying force. The bottom end of the force-applying rod 5 is the spherical adapter structure 8, which provides support during disassembly. Furthermore, the spherical adapter structure 8 prevents relative sliding during use of the intake cone disassembly device, making disassembly more convenient.

[0037] In some embodiments of the present invention, the cross-section of the supporting end cover 4 is a stepped surface. A plurality of clamping grooves are circumferentially formed at the bottom edge of the supporting end cover 4. A plurality of convex columns adapted to the clamping grooves are circumferentially arranged at the top edge of the flexible fixing claw 1. The convex columns are snapped into the clamping grooves and are limited and fixed by screws, so as to fixedly connect the supporting end cover 4 and the flexible fixing claw 1. Specifically in implementation, the force application structure is the internal thread of the bearing end cover. The bearing end cover and the flexible fixing claw 1 are fixed in a clamping groove form. After the clamping groove is embedded, it is limited and fixed by screws, thereby realizing axial fixation.

[0038] In some embodiments of the present invention, the length ratio of the shrinkage sleeve 3 to the flexible fixing claw 1 is 1:3. This length ratio is the preferred length ratio between the shrinkage sleeve 3 and the flexible fixing claw 1. The setting of this length dimension facilitates the shrinkage sleeve 3 to push outside the flexible fixing claw 1 to realize the shrinkage and expansion of the flexible fixing claw 1.

[0039] In some embodiments of the present invention, the flexible fixing claw 1 is made of rubber material; the tubular outer wall of the flexible fixing claw 1 and the flexible hook teeth are integrally formed.

[0040] The use process of the aero-engine intake cone disassembly device according to the embodiment of the present invention is specifically as follows:

[0041] 1. First, disassemble the compression nut for fixing the intake cone, so that the intake cone is in a free state, ensuring that there are no interfering components on the disassembly path.

[0042] 2. Use the shrinkage sleeve 3 to cover and approach the bottom end of the flexible fixing claw 1, so that the flexible fixing claw 1 contracts inward, and then the flexible fixing claw 1 is placed at the intake cone compression nut. Then, the shrinkage sleeve 3 is toggled in the reverse direction, and the flexible fixing claw 1 naturally expands outward, thereby hooking the intake cone.

[0043] 3. Install the centering expansion sleeve 2 into the flexible fixing claw 1, so that the flexible fixing claw 1 is stably fixed on the intake cone. After fixing, it is necessary to drag the flexible fixing claw 1 by hand to ensure that the flexible hook teeth of the flexible fixing claw 1 stably hook the intake cone.

[0044] 4. Install the supporting end cover 4 on the end face of the flexible fixing claw 1, and rotate the supporting end cover 4 so that the clamping groove of the supporting end cover 4 is engaged with the flexible fixing claw 1. Then, use bolts to radially limit the supporting end cover 4. It should be noted in this step that the force application rod 5 is installed together when installing the supporting end cover 4.

[0045] 5. Fix the fixing rod 7 by hand, and rotate the force application extension rod 6 with the other hand. The force application rod 5 rotates, and slowly drives the intake cone to be disassembled from the engine.

[0046] 6. After removing the intake cone, remove the intake cone disassembly device from the intake cone along the reverse steps, and then assemble the intake cone disassembly device into a whole.

[0047] The aviation engine intake cone disassembly device provided by the embodiment of the present invention uses the flexible hook teeth of the flexible fixing claw to fix the intake cone, uses the threaded structure for disassembly, adds the shrinkage and expansion anti-disconnection structure, and organically integrates the force application and guiding structure, greatly improving the intake cone disassembly efficiency and reducing the disassembly risk.

[0048] The above is only the specific implementation manner of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by those skilled in the art within the technical scope disclosed by the present application should be covered within the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. An air intake cone disassembly device for an aeroengine, characterized in that, include: The hooking assembly comprises a flexible fixed claw, a centering expansion sleeve and a shrinking sleeve; the flexible fixed claw is tubular in its natural state, and comprises a flexible tubular outer wall and a plurality of flexible hook teeth uniformly arranged on the tubular outer wall in a circumferential direction, the cross section of the flexible hook teeth being a tooth-like structure extending outward from the tube wall, for hooking the engine intake cone; the shrinking sleeve is movably sleeved outside the tube wall of the flexible fixed claw, and the diameter of the shrinking sleeve is smaller than the tube diameter of the flexible fixed claw in its natural state, so as to adjust the flexible claw to the centering expansion sleeve. The flexible fixing claw is squeezed and contracted to extend the bottom end of the contracted flexible fixing claw into the inner hole of the engine intake cone, and after the shrinking sleeve is pushed back in the reverse direction, the flexible fixing claw is hooked on the engine intake cone through the flexible hook teeth after natural rebound; the centering expansion sleeve is sleeved inside the tube wall of the flexible fixing claw, and is used to expand the flexible fixing claw squeezed and contracted by the shrinking sleeve inside the tube wall, so as to radially position the flexible fixing claw and stably fix the flexible fixing claw on the engine intake cone; The supporting assembly includes a supporting end cover and a force applying rod, wherein the supporting end cover is fixedly connected to the top end of the flexible fixed claw, and the force applying rod passes through the interior of the supporting end cover and the centering expansion sleeve and extends from the bottom end of the flexible fixed claw; a threaded section is provided on the force applying rod, and the supporting end cover is threadedly connected to the force applying rod on the threaded section, so that by rotating the force applying rod, the supporting end cover is driven to move upward on the force applying rod, thereby driving the flexible fixed claw to move upward to pull out the engine intake cone.

2. The aircraft engine intake cone disassembly device according to claim 1, characterized in that: The support assembly further includes a force extension rod, which is fixedly arranged on the top end of the force rod, and the axis of the force extension rod is perpendicular to the axis of the force rod.

3. The aircraft engine intake cone disassembly device according to claim 1, characterized in that: The support assembly further includes a fixing rod, which is fixedly connected to the support end cover, and an axis of the fixing rod is perpendicular to an axis of the force applying rod.

4. The aircraft engine intake cone disassembly device according to claim 1, characterized in that: The support assembly further includes a transfer spherical structure for providing a support point. The transfer spherical structure is fixedly arranged at the bottom end of the force application rod and is used to press the transfer spherical structure against the engine to provide a force application support point.

5. The air intake cone disassembly device for an aeroengine according to claim 1, wherein, The cross-section of the support end cover is a stepped surface, and a plurality of slots are circumferentially provided on the bottom edge of the support end cover. A plurality of bosses adapted to the slots are circumferentially provided on the top edge of the flexible fixing claw. The bosses are inserted into the slots and fixed by screws to fix the support end cover to the flexible fixing claw.

6. The air intake cone disassembly device for an aeroengine according to claim 1, characterized in that, The length ratio of the shrink sleeve to the flexible fixing claw is 1:

3.

7. The air intake cone disassembly device of an aero-engine according to claim 1, characterized in that, The flexible fixing claws are made of rubber material.

8. The air intake cone disassembly device of an aeroengine according to claim 1, characterized in that, The tubular outer wall of the flexible fixed claw and the flexible hook tooth are integrally formed.

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