CN115026757B

CN115026757B - Disassembling tool for sealing runway

Info

Publication number: CN115026757B
Application number: CN202110244646.4A
Authority: CN
Inventors: 郑思凯; 胡一廷; 李明; 何玉峰
Original assignee: AECC Commercial Aircraft Engine Co Ltd
Current assignee: AECC Commercial Aircraft Engine Co Ltd
Priority date: 2021-03-05
Filing date: 2021-03-05
Publication date: 2024-02-27
Anticipated expiration: 2041-03-05
Also published as: CN115026757A

Abstract

The invention discloses a disassembly tool for a sealing runway. The disassembly tool of the sealing track includes a support ring assembly and a pullout disassembly structure. The support ring assembly comprises a support ring and a pulling claw. The fingers are rotatably coupled to the support ring and are configured to mate with the flange to hook the flange. The pull-out break-up structure is coupled to the support ring and is configured to apply a pulling force to the support ring to cause the sealing race to disengage from the low pressure turbine shaft support cone wall with the support ring when the pull-out fingers are rotated relative to the support ring such that the pull-out fingers catch the flange. The decomposition tool provided by the invention is rapid in decomposition, and the decomposition efficiency of the sealing runway is improved.

Description

Disassembling tool for sealing runway

Technical Field

The invention relates to a disassembly tool for a sealing runway.

Background

As shown in fig. 1, the rear supporting point sealing runway 20 of the aero-engine is placed in the shaft cavity of the low-pressure turbine shaft supporting conical wall 40, and after the sealing area 21 of the sealing runway 20 is matched with the graphite sealing device on the rear casing of the turbine, the sealing runway is used for sealing the rear supporting point bearing cavity to prevent bearing lubricating oil from leaking. The contact of the sealing runway 20 and the low pressure turbine shaft support cone wall 40 is sealed by a rubber ring 50. During disassembly or assembly of the sealing runway, a large external force is required to overcome the friction of the rubber ring 50 and the inner wall of the low pressure turbine shaft support cone wall 40 to pull out the sealing runway 20. As shown in fig. 1, the rear end of the sealing track 20 (the rear end refers to the portion of the shaft cavity exposing the low-pressure turbine shaft supporting conical wall 40) is slender, thin in wall, easy to deform and has other parts in the shaft hole, and if the sealing track 20 is broken down by repeatedly knocking the rear end of the sealing track 20 to make the rubber ring 50 fail, the sealing track 20 is easily damaged. If the sealing runway 20 is disassembled by ejecting the sealing runway 20 from the front end of the sealing runway 20, the low-pressure turbine shaft supporting conical wall 40 needs to be removed, the rear section of the exhaust pipe 30 is knocked from the front end, and the rear section of the exhaust pipe 30 and the sealing runway 20 are separated at the same time, so that the maintenance cost is greatly increased in this way.

It should be noted that the statements in this background section merely provide background information related to the present disclosure and may not necessarily constitute prior art.

Disclosure of Invention

The invention provides a disassembly tool for a sealing runway, which is used for improving the disassembly efficiency of the sealing runway.

The invention provides a disassembly tool of a sealing runway, wherein a flange of the sealing runway is positioned in an inner cavity of a low-pressure turbine shaft supporting conical wall, and the disassembly tool comprises the following components:

the support ring assembly comprises a support ring and a pulling claw, the pulling claw is rotatably connected to the support ring and is configured to be matched with the flange to hook the flange; and

and the drawing and decomposing structure is connected to the support ring, and when the drawing claw rotates relative to the support ring so that the drawing claw hooks the flange, the drawing and decomposing structure is configured to apply a pulling force to the sealing runway so as to enable the sealing runway to deviate from the support cone wall of the low-pressure turbine shaft.

In some embodiments, the finger includes an axially extending finger body and a boss disposed at a lower end of the finger body, the boss extending radially outward relative to the finger body and an upper surface of the boss configured to be in abutting engagement with a lower end face of the flange.

In some embodiments, the upper surface of the boss is an upwardly projecting arcuate surface.

In some embodiments, the pulling claw body is of a bent rod structure and comprises a first longitudinal section and a second longitudinal section distributed in the axial direction, the first longitudinal section and the second longitudinal section are at least partially overlapped, and a boss is arranged at the lower end of the second longitudinal section.

In some embodiments, the positioning ring further comprises a positioning ring, the positioning ring comprises a first cylindrical surface, a flange ring arranged at the upper end of the first cylindrical surface and a second cylindrical surface arranged at the lower end of the first cylindrical surface, the first cylindrical surface is matched with the inner hole of the supporting ring, the outer surface of the flange ring protrudes towards the radial outer side relative to the first cylindrical surface to be supported on the upper end surface of the supporting ring, the outer surface of the second cylindrical surface is recessed towards the radial inner side relative to the first cylindrical surface, and the second cylindrical surface is matched with the surface of the second longitudinal section, which is positioned on the radial inner side, to limit the pulling claw.

In some embodiments, the support ring includes lugs disposed on the underside, the lugs being provided with hinge holes, the fingers being hinged at the hinge holes of the lugs.

In some embodiments, the seal runway further comprises a tightening ring, the tightening ring is arranged on the lower side of the supporting ring, the tightening ring is configured to be sleeved on the outer side of the low-pressure turbine shaft supporting conical wall, the drawing decomposition structure comprises a jackscrew, the jackscrew is in threaded connection with the supporting ring, the lower end of the jackscrew is tightened with the upper end face of the tightening ring, and the jackscrew is configured to be screwed relative to the supporting ring to pull the seal runway out of the inner cavity.

In some embodiments, the draw-break structure includes at least two jackscrews disposed circumferentially.

Based on the technical scheme provided by the invention, the disassembly tool of the sealing runway comprises a support ring assembly and a drawing disassembly structure. The support ring assembly comprises a support ring and a pulling claw. The fingers are rotatably coupled to the support ring and are configured to mate with the flange to hook the flange. The pull-out break-up structure is coupled to the support ring and is configured to apply a pulling force to the support ring to cause the sealing race to disengage from the low pressure turbine shaft support cone wall with the support ring when the pull-out fingers are rotated relative to the support ring such that the pull-out fingers catch the flange. The decomposition tool provided by the embodiment of the invention is rapid to decompose, and the decomposition efficiency of the sealing runway is improved.

Other features of the present invention and its advantages will become apparent from the following detailed description of exemplary embodiments of the invention, which proceeds with reference to the accompanying drawings.

Drawings

The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this application, illustrate embodiments of the invention and together with the description serve to explain the invention and do not constitute a limitation on the invention. In the drawings:

FIG. 1 is a schematic view of a seal runway mounted on a low pressure turbine shaft support cone wall;

FIG. 2 is a schematic view of an assembled perspective between a break-up tool and a low pressure turbine shaft support cone wall of an embodiment of the present invention during break-up of a sealing runway;

FIG. 3 is a schematic view of an assembled cross-sectional structure between the break-up tool and the low pressure turbine shaft support cone wall shown in FIG. 2;

FIG. 4 is a schematic view of an exploded tool according to an embodiment of the present invention;

FIG. 5 is a schematic cross-sectional view of an exploded tool according to an embodiment of the present invention;

FIG. 6 is a schematic view of the support ring of FIG. 5;

fig. 7 is a schematic view of the structure of the pulling claw in fig. 5.

Detailed Description

The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. The following description of at least one exemplary embodiment is merely exemplary in nature and is in no way intended to limit the invention, its application, or uses. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.

The relative arrangement of the components and steps, numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present invention unless it is specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective parts shown in the drawings are not drawn in actual scale for convenience of description. Techniques, methods, and apparatus known to one of ordinary skill in the relevant art may not be discussed in detail, but should be considered part of the authorization specification where appropriate. In all examples shown and discussed herein, any specific values should be construed as merely illustrative, and not a limitation. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numerals and letters denote like items in the following figures, and thus once an item is defined in one figure, no further discussion thereof is necessary in subsequent figures.

Spatially relative terms, such as "above … …," "above … …," "upper surface at … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial location relative to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as "above" or "over" other devices or structures would then be oriented "below" or "beneath" the other devices or structures. Thus, the exemplary term "above … …" may include both orientations of "above … …" and "below … …". The device may also be positioned in other different ways and the spatially relative descriptions used herein are construed accordingly.

As shown in fig. 1, the sealing race 20 includes a flange 70 located within the interior cavity of the low pressure turbine shaft support cone wall 40. The compression nut 60 is mounted on the upper end surface of the flange 70.

Referring to fig. 2, the inventor of the present invention has proposed a disassembly tool 10 for a sealing runway, which is characterized in that the sealing runway 20 has a flange located in an inner cavity. In some embodiments, the break-up tool 10 of the sealing track includes a support ring assembly and a pull-out break-up structure. Wherein, referring to fig. 3 to 5, the support ring assembly comprises a support ring 11 and a pulling claw 13. The fingers 13 are rotatably connected to the support ring 11, and the fingers 13 are configured to cooperate with the flange 70 to hook the flange 70. The pull-out and break-up structure is coupled to the support ring 11 and is configured to apply a pulling force to the support ring 11 to disengage the seal runway 20 from the low pressure turbine shaft support cone wall with the support ring 11 when the pulling pawl 13 is rotated relative to the support ring 11 such that the pulling pawl 13 hooks the flange 70. The decomposition tool provided by the embodiment of the invention is rapid to decompose, and the decomposition efficiency of the sealing runway is improved. The disassembly tool realizes the nondestructive disassembly of the sealing runway in the low-pressure turbine shaft cavity of the aero-engine on the premise of not disassembling the low-pressure turbine shaft.

In some embodiments, referring to FIG. 7, the finger 13 includes an axially extending finger body and a boss 133 disposed at a lower end of the finger body. The boss 133 extends radially outward relative to the finger body and an upper surface of the boss 133 is configured to be in abutting engagement with a lower end surface of the flange 70. The boss 133 extending radially outward forms a hook structure with respect to the finger body, and the finger 13 is controlled to rotate outward so that the boss 133 moves to the lower side of the flange 70 and abuts against the lower end surface of the flange 70, thereby the finger 13 hooks the flange 70, and then an upward pulling force is applied to the finger 13 to pull out the sealing track 20.

In some embodiments, the upper surface of boss 133 is an upwardly projecting arcuate surface. Referring to fig. 3, the lower end surface of the flange 70 is an upwardly concave arc surface, so that the upper surface of the boss 133 is set to an upwardly convex arc surface so that the upper surface of the boss 133 is embedded into the lower end surface of the flange 70, thereby improving the hooking and fixing effect of the fingers 13 to the flange 70.

In some embodiments, referring to fig. 7, the collet body is a bent rod structure and includes first and second longitudinal sections distributed in an axial direction. The first longitudinal section and the second longitudinal section at least partially overlap, and the lower end of the second longitudinal section is provided with a boss 133. Referring to fig. 7, a hinge hole 132 is provided at an overlapping portion of the first and second longitudinal sections. The pin shaft passes through the hinge hole 132 and is hinged with the lug 112 at the lower side of the support ring 111.

The flange 70 of the sealing track 20 of some embodiments is narrower. To prevent the pulling claw 13 from unhooking, the disassembly tool positioning ring 15 of the present embodiment restricts the rotation of the pulling claw 13, preventing the pulling claw 13 from shrinking inward to cause unhooking of the pulling claw 13.

Referring to fig. 4 and 5, in some embodiments, the break-up tool 10 of the sealing track further includes a locating ring 15. The positioning ring 15 comprises a first cylindrical surface, a flange ring arranged at the upper end of the first cylindrical surface and a second cylindrical surface arranged at the lower end of the first cylindrical surface. The first cylindrical surface is matched with an inner hole of the supporting ring 11, the outer surface of the flange ring protrudes outwards in the radial direction relative to the first cylindrical surface to be supported on the upper end surface of the supporting ring 11, the outer surface of the second cylindrical surface is recessed inwards in the radial direction relative to the first cylindrical surface, and the second cylindrical surface is matched with the surface 131 of the radial inner side of the second longitudinal section to limit the pulling claw.

In some embodiments, referring to fig. 6, the support ring 11 includes a lug 112 provided at the lower side, the lug 112 is provided with a hinge hole, and the pulling claw 13 is hinged at the hinge hole of the lug 112.

In some embodiments, referring to fig. 4 and 5, the seal runway break-up tool 10 further includes a tightening ring 14. The tightening ring 14 is provided at the lower side of the support ring 11. The draw-off structure comprises a jackscrew 16, the jackscrew 16 being in threaded connection with the support ring 11 and the lower end being in abutment with the upper end face of the abutment ring 14, the jackscrew 14 being configured to be screwed against the support ring 11 to withdraw the sealing track 20 from the cavity.

Referring to fig. 6, the support ring 11 is provided with a screw hole 111, and the jackscrew 16 is threaded into the screw hole 111 and is screwed with the jackscrew 16.

In some embodiments, referring to fig. 4, the draw-break structure includes at least two jackscrews 16 disposed circumferentially. At least two jackscrews 16 simultaneously apply tension to the sealing race 20 to uniformly stress the sealing race 20 circumferentially, thereby avoiding damage to the sealing race during disassembly.

The construction and operation of the disassembly tool for a sealing runway according to an embodiment of the present invention will be described in detail with reference to fig. 2 to 7.

As shown in fig. 4 and 5, in the present embodiment, the disassembly tool 10 of the sealing runway includes a support ring 11, a pin 12, a pulling claw 13, a tightening ring 14, a positioning ring 15, and a jackscrew 16.

As shown in fig. 6, the support ring 11 has a circular ring structure. Threaded holes 111 are evenly distributed on the circumference for mounting the jackscrews 16. Three pairs of lugs 112 are uniformly arranged on the circumference of the lower end of the support ring 11, and through holes are formed in the lugs 112 and are used for installing the pin shafts 12. The gap between the pair of lugs 112 is used to mount the fingers 13, and the fingers 13 after mounting are rotatable about the pin 12.

The pin shaft 12 is of an optical axis structure, and is mounted on a lug 112 and a pulling claw 13 on the lower end surface of the support ring 11 to serve as a rotating shaft of the pulling claw 13.

As shown in fig. 7, the pulling claw 13 has a bent rod-shaped structure, a through hole is formed in the middle of the pulling claw for mounting the pin shaft 12, a boss 133 is formed on the radial outer side of the pulling claw, and the pulling claw is matched with the lower end face of the circular flange 70 at the rear end of the sealing runway 20 to apply a decomposing force to the sealing runway 20. As shown in fig. 7, the surface 131 of the finger 13 located radially inside is provided as an arc surface, and cooperates with the outer cylindrical surface of the positioning ring 15 to perform a limiting function.

As shown in fig. 4 and 5, the tightening ring 14 has a circular structure. The inner bore of the annular structure is threaded to mate with the outer threads of the journal of the low pressure turbine rotor support cone wall 40. The upper end surface of the tightening ring 14 is used to tighten the jack screw 16 and apply a decomposition reaction force.

As shown in fig. 4, the positioning ring 15 has a stepped ring structure, and the upper end ring flange is matched with the upper end surface of the supporting ring 11 to play a supporting role. The second column surface at the lower end is matched with the radial inner arc surface of the pulling claw 13, so that the pulling claw 13 is limited, and the pulling claw 13 is prevented from shrinking inwards to cause unhooking.

As shown in fig. 4, the jackscrew 16 is of a screw structure, is mounted in a threaded hole 111 of the support ring 11, and abuts against the upper end surface of the tightening ring 14 for exerting a resolving power.

The pulling claw 13 of the decomposing tool of the embodiment can rotate around the rotating shaft, the pulling claw 13 stretches into the sealing runway back hole after rotating inwards, then the pulling claw is rotated outwards to be attached to the back end face of the flange 70, and the pulling claw 13 is limited to rotate through the positioning ring 15 to be attached to the flange 70 of the sealing runway 20 to be integrated with the sealing runway 20. In order to generate the pulling force for overcoming the friction force of the rubber ring, a jackscrew 16 is designed, a jacking ring 14 is designed into a large nut structure, the jacking ring is screwed and fixed on the threads of the shaft neck of the low-vortex rotor supporting cone wall, and the supporting ring 11 of the connecting claw 13 is provided with threaded holes 111 which are uniformly distributed on the circumference

As shown in fig. 2 and 3, the disassembly process of the sealing track 20 is as follows:

the compression nut 60 is first unscrewed and then the jacking ring 14 is mounted on the threads of the journal of the low pressure turbine rotor support cone wall 40.

Pulling the fingers 13 to retract the lower ends of the fingers 13 inwardly, then mounting the support ring 11 and fingers 13 in the cone wall journal cavity, and pulling the fingers 13 to hook the flange 70 at the rear end of the sealing race 20.

The positioning ring 15 is installed in the supporting ring 11 to limit the rotation of the pulling claw 13 and prevent the pulling claw 13 from unhooking caused by the inward shrinkage of the pulling claw 13.

The jackscrews 16 are installed in threaded holes in the supporting ring 11, the jackscrews 16 are tightly propped against the upper end face of the jacking ring 14, the jackscrews 16 are continuously and uniformly screwed circumferentially, and the sealing runway 20 is pulled out of the conical wall.

Three lugs 112 are uniformly distributed on the circumference of the supporting ring 11 of the decomposing tool, and the lugs 112 are provided with pulling claws 13. The pulling claw 13 is connected with the lug 112 through the hinge pair so that the pulling claw 13 can rotate around the connecting shaft, when the pulling claw 112 rotates inwards to shrink, the pulling claw 112 can be placed below the flange 70 of the sealing runway 20, then the pulling claw 13 rotates outwards to hook the flange 70 of the sealing runway 20, and then the rotation of the pulling claw 13 is limited by the positioning ring 15. The sealing track 20 is broken down by applying a breaking force with the jackscrews 16 mounted on the support ring 11.

From the above, the invention fully utilizes the structure of the sealing runway, provides a special decomposition tool which can be clamped at the flange drawing table of the sealing runway, takes the flange of the sealing runway as an external force action point in the decomposition process, and further realizes the nondestructive decomposition of the sealing runway. And the low pressure turbine shaft support cone wall 40 need not be removed during the disassembly process.

Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present invention and not for limiting the same; while the invention has been described in detail with reference to the preferred embodiments, those skilled in the art will appreciate that: modifications may be made to the specific embodiments of the present invention or equivalents may be substituted for part of the technical features thereof; without departing from the spirit of the invention, it is intended to cover the scope of the invention as claimed.

Claims

1. A disassembly tool for a sealing runway, the flange (70) of the sealing runway (20) being located in an interior cavity of a low pressure turbine shaft support cone wall (40), comprising:

a support ring assembly comprising a support ring (11) and a pulling claw (13), the pulling claw (13) being rotatably connected to the support ring (11), and the pulling claw (13) being configured to cooperate with the flange (70) to hook the flange (70); and

a pull-out and break-out structure coupled to the support ring (11), the pull-out and break-out structure configured to apply a pulling force to the sealing track (20) to disengage the sealing track (20) from within the low pressure turbine shaft support cone wall (40) when the pull-out fingers (13) are rotated relative to the support ring (11) such that the pull-out fingers (13) hook over the flange (70);

the disassembly tool further comprises a tightening ring (14), the tightening ring (14) is arranged on the lower side of the supporting ring (11), the tightening ring (14) is configured to be sleeved on the outer side of the low-pressure turbine shaft supporting conical wall (40), the drawing disassembly structure comprises at least two jackscrews (16) which are arranged along the circumferential direction, the jackscrews (16) are in threaded connection with the supporting ring (11) and the lower ends of the jackscrews are in tightening connection with the upper end face of the tightening ring (14), the jackscrews are configured to be screwed up relative to the supporting ring, and other jackscrews are continuously and circumferentially uniformly screwed up to pull out the sealing runway from the inner cavity.

2. A disassembly tool for a sealing track according to claim 1, wherein the finger (13) comprises an axially extending finger body and a boss (133) provided at a lower end of the finger body, the boss (133) extending radially outwardly relative to the finger body and an upper surface of the boss (133) being configured for abutting engagement with a lower end face of the flange (70).

3. A sealing track break-up tool according to claim 2, characterized in that the upper surface of the boss (133) is an upwardly protruding cambered surface.

4. The sealing runway breaking-up tool of claim 2, wherein the pulling pawl body is of a bent rod structure and comprises a first longitudinal section and a second longitudinal section distributed in an axial direction, the first longitudinal section and the second longitudinal section at least partially overlap, and the lower end of the second longitudinal section is provided with the boss.

5. The tool for decomposing a sealing runway according to claim 4, further comprising a positioning ring (15), wherein the positioning ring (15) comprises a first cylindrical surface, a flange ring arranged at the upper end of the first cylindrical surface, and a second cylindrical surface arranged at the lower end of the first cylindrical surface, the first cylindrical surface is matched with the inner hole of the supporting ring (11), the outer surface of the flange ring protrudes outwards radially relative to the first cylindrical surface to be supported on the upper end surface of the supporting ring (11), the outer surface of the second cylindrical surface is recessed inwards radially relative to the first cylindrical surface, and the second cylindrical surface is matched with the surface (131) of the second longitudinal section, which is positioned on the inner radial side, to limit the pulling claw (13).

6. A break-up tool for a sealing track according to claim 1, characterized in that the support ring (11) comprises lugs (112) arranged on the underside, the lugs (112) being provided with hinge holes, the fingers (13) being hinged at the hinge holes of the lugs.