Hanging tool for disc-shaped piece of aero-engine

Abstract

The invention discloses an aero-engine disc-shaped piece hanging tool. The aero-engine disc-shaped piece hanging tool comprises a center rod (7), a lifting device (8) and a lifting device (9), the multiple supporting rods (5) are arranged in the circumferential direction of the center rod (7), one ends of the supporting rods (5) are hinged to the center rod (7), and the supporting rods (5) are configured to swing in the plane passing through the axis of the center rod (7) relative to the center rod (7) so that the other ends of the supporting rods (5) can be switched between the folding position and the unfolding position; the unfolded position is farther from the central rod (7) than the folded position; and the positioning mechanism is configured to position the supporting rod (5) at the opening position.

Description

Technical Field

[0001] This invention relates to the field of aircraft engine disc component inspection technology, and more specifically, to an aircraft engine disc component lifting fixture. Background Technology

[0002] Penetrant testing is a commonly used non-destructive testing method for inspecting surface defects on components. Disc-shaped parts in aero-engines are key rotating components; even minor defects or impacts can affect the engine's safe operation. Therefore, penetrant testing of aero-engine disc-shaped parts often requires several people working together to carefully move the disc into the penetrant testing frame before testing begins. Because most disc-shaped parts are heavy, and some integral bladed disks have sharp edges, there is still a significant risk of personnel being struck by objects or cut by sharp edges during manual handling. Furthermore, manual handling of disc-shaped parts is inherently unsafe.

[0003] Currently, eye bolts are commonly used as lifting tools for disc-shaped components. During and after lifting, three to four eye bolts need to be secured to the upper mounting edge of the disc-shaped component with nuts before lifting. The installation and disassembly process is quite cumbersome, and lifting is impossible if the disc-shaped component cannot be secured with eye bolts and nuts at the mounting edge. Summary of the Invention

[0004] The present invention aims to provide a hoisting fixture for disc-shaped components of aircraft engines, so as to improve the problem of cumbersome installation and disassembly processes of existing hoisting tools.

[0005] According to one aspect of the present invention, the present invention provides a mounting fixture for an aircraft engine disc-shaped component, the mounting fixture comprising:

[0006] Center rod;

[0007] Multiple support rods are arranged circumferentially along the central rod. One end of each support rod is hinged to the central rod and configured to swing relative to the central rod in a plane passing through the axis of the central rod, so that the other end of the support rod switches between a retracted position and an extended position, the extended position being farther away from the central rod than the retracted position.

[0008] A positioning mechanism is configured to position the support rod in the extended position.

[0009] In some embodiments, the positioning mechanism includes:

[0010] A sliding sleeve is movably fitted onto the central rod;

[0011] Multiple connecting rods are provided in a one-to-one correspondence with multiple support rods, one end of each connecting rod is hinged to the sliding sleeve, and the other end is hinged to the corresponding support rod;

[0012] A positioning element is configured to restrict the movement of the sleeve along the central rod toward the end where the central rod is hinged to the support rod, so as to position the support rod in the open position.

[0013] In some embodiments, at least one segment of the center rod is provided with external threads, and the positioning element includes a threaded sleeve adapted to the external threads.

[0014] In some embodiments, the outer diameter of the threaded sleeve is larger than the outer diameter of the sliding sleeve.

[0015] In some embodiments, the aircraft engine disc-shaped component lifting fixture further includes a support plate, one side of which is hinged to the end of the support rod away from the central rod, and the other side of which is used to contact the disc surface of the disc-shaped component.

[0016] In some embodiments, the pallet swings relative to the support rod in a plane passing through the axis of the central rod and the support rod.

[0017] In some embodiments, the side of the tray away from the support rod is provided with an elastic pad.

[0018] In some embodiments, the hinge axes of the plurality of support rods are flush with the length direction of the central rod.

[0019] In some embodiments, the aircraft engine disc-shaped component lifting fixture further includes a first hinge mechanism, the first hinge mechanism including a first connecting structure, a second connecting structure and a first pin, the first connecting structure including a first notch extending inward from its end and a first pin hole communicating with and intersecting the first notch, the second connecting structure being configured to be inserted into the first notch from the end of the first connecting structure and having a second pin hole, the first pin being configured to be able to pass through the first pin hole and the second pin hole;

[0020] The support rod and the center rod are connected by the first hinge mechanism, wherein one of the first connecting structure and the second connecting structure is disposed on the support rod, and the other is disposed on the center rod; and / or

[0021] The connecting rod and the sliding sleeve are connected by the first hinge mechanism, wherein one of the first connecting structure and the second connecting structure is disposed on the connecting rod, and the other is disposed on the sliding sleeve; and / or

[0022] The tray and the support rod are connected by a first hinge mechanism, wherein one of the first connection structure and the second connection structure is disposed on the tray and the other is disposed on the support rod.

[0023] In some embodiments, the aircraft engine disc-shaped component lifting fixture further includes a second hinge mechanism, the second hinge mechanism including a third connecting structure, a fourth connecting structure and a second pin, the third connecting structure including a second notch extending inward from its circumference and a third pin hole communicating with and intersecting the second notch, the fourth connecting structure being configured to be insertable into the second notch from its circumference and having a fourth pin hole, the second pin being configured to be insertable into the third pin hole and the fourth pin hole.

[0024] In some embodiments, the aircraft engine disc-shaped component lifting fixture further includes an annular component connected to one end of the central rod away from the support rod, the annular component being used to connect to crane jaws.

[0025] By applying the technical solution of this application, when the other end of the support rod is in the retracted position, multiple support rods are attached to the periphery of the central rod 7, so that the overall outer diameter of the lifting fixture is reduced so that the support rod of the lifting fixture can pass through the central hole of the disc-shaped part. After the support rod passes through the central hole of the disc-shaped part, the support rod moves to the open position away from the central rod so that the support rod supports the disc surface of the disc-shaped part, thereby enabling the crane connected to the central rod to lift the disc-shaped part, which improves the problem of cumbersome installation and disassembly process of the lifting tools in the prior art.

[0026] Other features and advantages of the invention will become clear from the following detailed description of exemplary embodiments of the invention with reference to the accompanying drawings. Attached Figure Description

[0027] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0028] Figure 1 A schematic diagram of the structure of the aircraft engine disc-shaped component lifting fixture according to an embodiment of the present invention is shown;

[0029] Figure 2 A schematic diagram of the first hinge mechanism of the aircraft engine disc-shaped component lifting fixture according to an embodiment of the present invention is shown.

[0030] Figure 3 A schematic diagram of the second hinge mechanism of the aircraft engine disc-shaped component lifting fixture according to an embodiment of the present invention is shown.

[0031] In the diagram: 1. Annular component; 2. Sliding sleeve; 3. Positioning component; 4. Connecting rod; 5. Support rod; 6. Support plate; 7. Center rod; 8. First pin; 9. Second pin; A. First connecting structure; B. Second connecting structure; C. Third connecting structure; D. Fourth connecting structure. Detailed Implementation

[0032] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. The following description of at least one exemplary embodiment is merely illustrative and is in no way intended to limit the present invention or its application or use. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0033] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application pertains; the terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the application; the terms “comprising” and “having”, and any variations thereof, in the specification, claims, and foregoing description of the drawings are intended to cover non-exclusive inclusion.

[0034] In this document, the term "embodiment" means that a particular feature, structure, or characteristic described in connection with an embodiment may be included in at least one embodiment of this application. The appearance of this phrase in various places throughout the specification does not necessarily refer to the same embodiment, nor is it a separate or alternative embodiment mutually exclusive with other embodiments. It will be explicitly and implicitly understood by those skilled in the art that the embodiments described herein can be combined with other embodiments.

[0035] In the description of this application, it should be noted that, unless otherwise stated, "a plurality of" means two or more; the terms "upper," "lower," "left," "right," "inner," and "outer," etc., indicating orientation or positional relationships, are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation on this application. Furthermore, the terms "first," "second," and "third," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance. "Vertical" is not vertical in the strict sense, but within the allowable tolerance range. "Parallel" is not parallel in the strict sense, but within the allowable tolerance range.

[0036] The directional terms used in the following description refer to the directions shown in the figures and are not intended to limit the specific structure of this application. It should also be noted in the description of this application that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.

[0037] Unless otherwise specified, the terms "comprising" and "including" as used in this application can be open-ended or closed-ended. For example, "comprising" and "including" can mean that other components not listed may also be included, or that only the listed components may be included.

[0038] Unless otherwise specified, the term "or" is inclusive in this application. For example, the phrase "A or B" means "A, B, or both A and B". More specifically, the condition "A or B" is satisfied by any of the following conditions: A is true or exists and B is false or does not exist; A is false or does not exist and B is true or exists; or both A and B are true or exist.

[0039] See Figure 1 The aircraft engine disc-shaped component lifting fixture of this embodiment includes a central rod 7, multiple support rods 5, and a positioning mechanism.

[0040] Multiple support rods 5 are arranged circumferentially along a central rod 7. One end of each support rod 5 is hinged to the central rod 7 and configured to swing relative to the central rod 7 in a plane passing through the axis of the central rod 7, so that the other end of the support rod 5 switches between a retracted position and an extended position, with the extended position being farther from the central rod 7 than the retracted position. A positioning mechanism is configured to position the support rod 5 in the extended position.

[0041] In the technical solution of this application, when the other end of the support rod 5 is in the retracted position, multiple support rods 5 are attached to the periphery of the central rod 7, so that the overall outer diameter of the lifting fixture is reduced so that the support rods 5 of the lifting fixture can pass through the central hole of the disc-shaped part. After the support rods 5 pass through the central hole of the disc-shaped part, the support rods 5 move toward the open position away from the central rod 7 so that the support rods 5 support the disc surface of the disc-shaped part, thereby enabling the crane connected to the central rod 7 to lift the disc-shaped part, which improves the problem of cumbersome installation and disassembly process of the lifting tools in the prior art.

[0042] In some embodiments, the positioning mechanism includes a sliding sleeve 2, a plurality of connecting rods 4, and a positioning element 3. The sliding sleeve 2 is movably fitted onto the central rod 7. The plurality of connecting rods 4 are arranged in a one-to-one correspondence with the plurality of support rods 5, with one end of the connecting rod 4 hinged to the sliding sleeve 2 and the other end hinged to the corresponding support rod 5.

[0043] As the sliding sleeve 2 moves along the central rod 7, it causes the support rods 5 to switch between a retracted position and an extended position. Specifically, when the sliding sleeve 2 moves upward along the central rod 7, it causes multiple support rods 5 to move towards a retracted position closer to the central rod 7; when the sliding sleeve 2 moves downward, it causes multiple support rods 5 to move towards an extended position farther away from the support rods 5. When the hanging fixture needs to pass through the central hole of the disc-shaped component, the sliding sleeve 2 causes the support rods 5 to move to the retracted position. After the hanging fixture passes through the central hole of the disc-shaped component, the sliding sleeve 2 causes the support rods 5 to move towards the extended position so that the support rods 5 can support the disc-shaped component to be hung.

[0044] Positioning element 3 is configured to restrict the movement of sliding sleeve 2 along the central rod 7 toward the end of the central rod 7 that is hinged to the support rod 5, thereby positioning the support rod 5 in the open position. Positioning element 3 fixes the support rod 5 in the open position to restrict the swing of the support rod 5 relative to the central rod 7, thereby allowing the hanging fixture to hang disc-shaped parts.

[0045] At least one section of the center rod 7 is provided with external threads, and the positioning element 3 includes a threaded sleeve adapted to the external threads. Utilizing the self-locking function of the threads, the sliding sleeve 2 can be restricted to any position. The rotation of the threaded sleeve can drive the sliding sleeve 2 to move along the center rod 7, thereby causing the support to switch between the retracted position and the extended position.

[0046] The outer diameter of the threaded sleeve is larger than the outer diameter of the sliding sleeve 2, so that the threaded sleeve can support the sliding sleeve 2 and move it upward along the central rod. Furthermore, it also helps the threaded sleeve to support the sliding sleeve 2.

[0047] The aircraft engine disc-shaped component lifting fixture also includes a support plate 6. One side of the support plate 6 is hinged to the end of the support rod 5 away from the center rod 7, and the other side of the support plate 6 is used to contact the disc surface of the disc-shaped component.

[0048] The pallet 6 swings relative to the support rod 5 in the plane passing through the axis of the central rod 7 and the support rod 6, so that the pallet can contact the disc surface of the disc-shaped component at different angles when the support rod 5 is fixed relative to the central rod 7.

[0049] An elastic pad is provided on the side of the support plate 6 away from the support rod 5. Optionally, the elastic pad is a high-temperature resistant rubber sleeve to prevent scratching the parts when lifting them.

[0050] The hinge axes of the multiple support rods 5 and the central rod 7 are flush with the length of the central rod 7.

[0051] See Figure 2The aircraft engine disc-shaped component lifting fixture also includes a first hinge mechanism. The first hinge mechanism includes a first connecting structure A, a second connecting structure B, and a first pin 8. The first connecting structure A includes a first notch extending inward from its end and a first pin hole communicating with and intersecting the first notch. The second connecting structure B is configured to be inserted into the first notch from the end of the first connecting structure A and is provided with a second pin hole. The first pin 8 is configured to be able to pass through the first pin hole and the second pin hole.

[0052] Support rod 5 and center rod 7 are connected by a first hinge mechanism, wherein one of the first connecting structure A and the second connecting structure B is disposed on support rod 5 and the other is disposed on center rod 7; and / or

[0053] Link 4 and sliding sleeve 2 are connected by a first hinge mechanism, wherein one of the first connecting structure A and the second connecting structure B is disposed on link 4 and the other is disposed on sliding sleeve 2; and / or

[0054] The tray 6 and the support rod 5 are connected by a first hinge mechanism. One of the first connecting structure A and the second connecting structure B is set on the tray 6, and the other is set on the support rod 5.

[0055] See Figure 3 The aircraft engine disc-shaped component lifting fixture also includes a second hinge mechanism. The second hinge mechanism includes a third connecting structure C, a fourth connecting structure D, and a second pin 9. The third connecting structure C includes a second notch extending inward from its circumference and a third pin hole communicating with and intersecting the second notch. The fourth connecting structure D is configured to be inserted into the second notch from its circumference and is provided with a fourth pin hole. The second pin 9 is configured to be inserted into the third pin hole and the fourth pin hole.

[0056] The aircraft engine disc-shaped component lifting fixture also includes an annular component 1, which is connected to the end of the central rod 7 away from the support rod 5. The annular component 1 is used to connect the crane claw.

[0057] The upper ring component 1 of the hoisting fixture is made of high-quality steel reinforcement. The inner side of the ring component 1 is connected to the upper end of the central rod 7, and the outer ring can be picked up by the crane's claws for hoisting.

[0058] The upper cylindrical part of the center rod 7 is threaded. The positioning part 3 (sleeve) is a nut that can move up and down at the thread of the center rod 7. The sleeve 2 is a metal sleeve that fits directly onto the center rod 7. The outer diameter of the sleeve 2 is slightly smaller than the outer diameter of the positioning part 3 (sleeve) so that it can be supported by the positioning part 3 (sleeve). When the positioning part 3 (sleeve) moves up and down, it drags the sleeve 2 up and down with it. The connecting rod 4 and the support rod 5 are metal support rods. The connecting rod 4 and the support rod pass through... Figure 2 The form is connected to the 2-sleeve sleeve, and the 4-bracket link is connected via... Figure 3The form is connected to the support rod 5, and the support rod 5 is connected by... Figure 2 It is connected to the bottom of the center rod 7 in the form of a rod.

[0059] The working process of the penetrant testing fixture for aero-engine discs is as follows: The lifting support rod 5 is tightened inward to bring the pallet 6 closer to the center rod 7. During lifting, the entire fixture passes through the inner ring of the aero-engine disc, so that the pallet 6 is lower than the lower surface of the aero-engine disc. Then, the nut of the positioning part 3 (sleeve) is rotated and moved downward. At the same time, the sleeve 2 also moves downward with the positioning part 3 (sleeve). The connecting rod 4 gradually lowers the support rod 5. The pallets 6 move downward and outward with the support rod 5 until all four pallets 6 are in complete contact with the lower surface of the aero-engine disc. The crane's claws grab the ring component 1 for lifting.

[0060] The above are merely exemplary embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A hoisting fixture for a disc-shaped component of an aircraft engine, characterized in that, include: Center rod (7); Multiple support rods (5) are arranged circumferentially along the central rod (7), one end of each support rod (5) is hinged to the central rod (7) and configured to swing relative to the central rod (7) in a plane passing through the axis of the central rod (7) so that the other end of the support rod (5) switches between a retracted position and an extended position, the extended position being farther away from the central rod (7) than the retracted position. The positioning mechanism is configured to position the support rod (5) in the open position.

2. The aero-engine disc-shaped component lifting fixture according to claim 1, characterized in that, The positioning mechanism includes: The sliding sleeve (2) is movably fitted onto the central rod (7); Multiple connecting rods (4) are arranged one-to-one with multiple support rods (5). One end of each connecting rod (4) is hinged to the sliding sleeve (2), and the other end is hinged to the corresponding support rod (5). The positioning element (3) is configured to restrict the movement of the sliding sleeve (2) along the center rod (7) toward the end of the center rod (7) that is hinged to the support rod (5) to position the support rod (5) in the open position.

3. The aero-engine disc-shaped component lifting fixture according to claim 2, characterized in that, At least one section of the central rod (7) is provided with an external thread, and the positioning member (3) includes a threaded sleeve adapted to the external thread.

4. The aero-engine disc-shaped component lifting fixture according to claim 3, characterized in that, The outer diameter of the threaded sleeve is larger than the outer diameter of the sliding sleeve (2).

5. The aircraft engine disc-shaped component lifting fixture according to any one of claims 1 to 4, characterized in that, It also includes a tray (6), one side of which is hinged to the end of the support rod (5) away from the central rod (7), and the other side of the tray (6) is used to contact the disc surface of the disc-shaped component.

6. The aero-engine disc-shaped component lifting fixture according to claim 5, characterized in that, The pallet (6) swings relative to the support rod (5) in a plane passing through the axis of the central rod (7) and the support rod (6).

7. The aero-engine disc-shaped component lifting fixture according to claim 5, characterized in that, An elastic pad is provided on the side of the tray (6) away from the support rod (5).

8. The aero-engine disc-shaped component lifting fixture according to claim 1, characterized in that, The hinge axes of the plurality of support rods (5) and the central rod (7) are flush with the length direction of the central rod (7).

9. The aero-engine disc-shaped component lifting fixture according to claim 5, characterized in that, It also includes a first hinge mechanism, which includes a first connecting structure (A), a second connecting structure (B) and a first pin (8). The first connecting structure (A) includes a first notch extending inward from its end and a first pin hole communicating with and intersecting the first notch. The second connecting structure (B) is configured to be inserted into the first notch from the end of the first connecting structure (A) and is provided with a second pin hole. The first pin (8) is configured to be able to pass through the first pin hole and the second pin hole. The support rod (5) and the center rod (7) are connected by the first hinge mechanism, and one of the first connecting structure (A) and the second connecting structure (B) is disposed on the support rod (5) and the other is disposed on the center rod (7); and / or The connecting rod (4) is connected to the sliding sleeve (2) via the first hinge mechanism, wherein one of the first connecting structure (A) and the second connecting structure (B) is disposed on the connecting rod (4) and the other is disposed on the sliding sleeve (2); and / or The pallet (6) and the support rod (5) are connected by a first hinge mechanism. One of the first connecting structure (A) and the second connecting structure (B) is disposed on the pallet (6) and the other is disposed on the support rod (5).

10. The aero-engine disc-shaped component lifting fixture according to claim 2, characterized in that, It also includes a second hinge mechanism, which includes a third connecting structure (C), a fourth connecting structure (D), and a second pin (9). The third connecting structure (C) includes a second notch extending inward from its circumference and a third pin hole communicating with and intersecting the second notch. The fourth connecting structure (D) is configured to be inserted into the second notch from its circumference and is provided with a fourth pin hole. The second pin (9) is configured to be inserted into the third pin hole and the fourth pin hole.

11. The aero-engine disc-shaped component lifting fixture according to claim 1, characterized in that, It also includes an annular component (1) connected to the end of the central rod (7) away from the support rod (5), the annular component (1) being used to connect the crane claw.

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