A puller for disassembling an aircraft engine oil distributor sleeve assembly

Abstract

A disassembly tool for an aero-engine oil distributor sleeve assembly includes an outer support frame, an inner puller plate, a pawl, a pawl limiting ring, a limiting ring position adjusting rod, and a force-applying stud. The outer support frame is engaged with a rotor balancing assembly, and a force-applying stud through hole is provided at the center of the outer support frame. The force-applying stud has an annular limiting boss and a force-applying handle at its outermost end. The inner puller plate is located inside the outer support frame, and a threaded hole is provided at its center, with the force-applying stud threaded into the threaded hole. The root end of the pawl is hinged to the inner puller plate, and the outer side of the pawl finger tip is engaged with the oil distributor sleeve assembly. The pawl limiting ring is engaged with the inner side of the pawl finger tip. The outer support frame and the inner puller plate have a limiting ring position adjusting rod through hole, the inner end of the adjusting rod is threaded and fixed to the pawl limiting ring, and the outer end of the adjusting rod is located outside the outer support frame. A friction-reducing component is fitted onto the force-applying stud between the annular limiting boss and the outer support frame. An adjusting rod limiting component is provided between the limiting ring position adjusting rod and the inner puller plate.

Description

Technical Field

[0001] This invention belongs to the field of aircraft engine maintenance technology, and in particular relates to a puller for disassembling an aircraft engine oil distributor sleeve assembly. Background Technology

[0002] Currently, during the maintenance of aircraft engines, it is necessary to disassemble the parts of the aircraft engine from the overall structure, which includes the situation where the oil distributor assembly is disassembled from the rotor balancing assembly.

[0003] When the parts to be disassembled are located outside the overall structure, existing disassembly pullers generally adopt an internal clamping and external hooking structure, which can easily disassemble and pull out parts located outside the overall structure.

[0004] However, the oil distribution sleeve assembly is located in the innermost core of the rotor balancing assembly, which has the characteristics of poor visibility and small force point. Traditional pullers are no longer applicable, and it can only be disassembled manually by relying on a leather hammer. This makes the disassembly of the oil distribution sleeve assembly very difficult and can easily lead to damage to the parts. The qualified rate of the disassembled parts is low, and the disassembly process takes a long time. Summary of the Invention

[0005] To address the problems existing in the prior art, this invention provides a puller for disassembling the oil jacket assembly of an aero-engine. It features a simple structure, easy operation, flexibility, and labor-saving characteristics. Compared with traditional disassembly methods, it effectively reduces damage to parts, increases the pass rate of disassembled parts by about 50%, and reduces the time required for the disassembly process to only half of the original, thus effectively improving the work efficiency of the disassembly process.

[0006] To achieve the above objectives, the present invention adopts the following technical solution: a puller for disassembling an aero-engine oil separator assembly, comprising an outer support frame, an inner puller plate, a hook, a hook limit ring, a limit ring position adjustment rod, and a force-applying stud; the outer support frame is fitted with a rotor balancing assembly, and a through hole for the force-applying stud is provided at the center of the outer support frame; an annular limit boss is fixed on the stud body on the outer side of the outer support frame, and a force-applying handle is provided at the outermost end of the force-applying stud; the inner puller plate is located inside the outer support frame, and a threaded hole is provided at the center of the inner puller plate. The force-applying stud is screwed into the central threaded hole of the inner pull plate; the hooks are evenly distributed around the circumference of the inner pull plate, and the root end of the hook is hinged to the inner pull plate through a cylindrical pin. The outer side of the finger tip of the hook is engaged with the oil distribution sleeve assembly. The hook limit ring is engaged with the inner side of the finger tip of the hook. The outer support frame and the inner pull plate are both provided with limit ring position adjustment rod through holes. The inner end of the limit ring position adjustment rod is screwed and fixed to the hook limit ring. The outer end of the limit ring position adjustment rod is located outside the outer support frame. The limit ring position adjustment rod is evenly distributed along the hook limit ring.

[0007] A rubber pad is installed between the outer support frame and the rotor balancing assembly.

[0008] A friction-reducing component is fitted onto the force-applying stud between the annular limiting boss and the outer support frame.

[0009] The friction-reducing component includes a spherical convex washer and a conical concave washer. The convex surface of the spherical convex washer and the concave surface of the concave concave washer are engaged together, and the contact surface between the two serves as a sliding friction-reducing surface.

[0010] An adjusting rod limiting component is provided between the position adjusting rod of the limiting ring and the inner pull plate.

[0011] The adjusting rod limiting component includes a screw plug, a thrust spring, and a round-headed pin; the inner pull plate has an adjusting rod limiting hole, and the adjusting rod body at the limiting ring position has an annular groove, which is directly opposite to the adjusting rod limiting hole on the inner pull plate; the round-headed pin is located at the innermost side of the adjusting rod limiting hole, and the round-headed pin is engaged with the annular groove; the screw plug is screwed and fixed at the outermost side of the adjusting rod limiting hole, and the thrust spring is disposed between the screw plug and the round-headed pin.

[0012] The beneficial effects of this invention are:

[0013] The extractor for disassembling the oil jacket assembly of an aero-engine of the present invention has the characteristics of simple structure, easy operation, flexibility and labor saving. Compared with the traditional disassembly method, it effectively reduces the damage to parts, the qualified rate of disassembled parts can be increased by about 50%, and the time required for the disassembly process is only half of the original, thus effectively improving the work efficiency of the disassembly process. Attached Figure Description

[0014] Figure 1 This is a schematic diagram (section view) of a disassembly tool for an aero-engine oil separator assembly according to the present invention;

[0015] Figure 2 for Figure 1 Sectional view of AA;

[0016] Figure 3 This is a schematic diagram (view 2) of the structure of a disassembly tool for an aero-engine oil separator sleeve assembly (the entire assembly and oil separator sleeve assembly are not shown).

[0017] Figure 4 This is a schematic diagram (view 2) of the structure of a puller for disassembling an aero-engine oil separator assembly according to the present invention (sectional view, oil separator assembly not shown);

[0018] In the diagram, 1—outer support frame, 2—inner pull plate, 3—hook, 4—hook limit ring, 5—limit ring position adjustment rod, 6—force application stud, 7—annular limit boss, 8—force application handle, 9—cylindrical pin, 10—oil distributor sleeve assembly, 11—rotor balance assembly, 12—rubber pad, 13—spherical convex washer, 14—conical concave washer, 15—screw plug, 16—thrust spring, 17—round head pin, 18—adjustment rod limit hole, 19—annular groove. Detailed Implementation

[0019] The present invention will now be described in further detail with reference to the accompanying drawings and specific embodiments.

[0020] like Figures 1-4 As shown, a disassembly tool for an aero-engine oil jacket assembly includes an outer support frame 1, an inner puller plate 2, a hook 3, a hook 3, a hook limiting ring 4, a limiting ring position adjusting rod 5, and a force-applying stud 6. The outer support frame 1 is engaged with a rotor balancing assembly 11. A through hole for the force-applying stud 6 is provided at the center of the outer support frame 1. An annular limiting boss 7 is fixed on the column of the force-applying stud 6 on the outer side of the outer support frame 1. A force-applying handle 8 is provided at the outermost end of the force-applying stud 6. The inner puller plate 2 is located inside the outer support frame 1. A threaded hole is provided at the center of the inner puller plate 2. The force-applying stud 6 and the inner puller plate 1 are connected by a threaded hole. The center threaded hole of the inner pull plate 2 is screwed into place; the hooks 3 are evenly distributed around the inner pull plate 2, and the root end of the hooks 3 is hinged to the inner pull plate 2 through the cylindrical pin 9. The outer side of the finger tip of the hooks 3 is engaged with the oil distribution sleeve assembly 10. The hook limit ring 4 is engaged with the inner side of the finger tip of the hooks 3. The outer support frame 1 and the inner pull plate 2 are both provided with through holes for the limit ring position adjustment rod 5. The inner end of the limit ring position adjustment rod 5 is screwed and fixed to the hook limit ring 4. The outer end of the limit ring position adjustment rod 5 is located outside the outer support frame 1. The limit ring position adjustment rod 5 is evenly distributed along the hook limit ring 4.

[0021] A rubber pad 12 is installed between the outer support frame 1 and the rotor balancing assembly 11.

[0022] A friction-reducing component is fitted onto the force-applying stud 6 between the annular limiting boss 7 and the outer support frame 1.

[0023] The friction-reducing component includes a spherical convex washer 13 and a conical concave washer 14. The convex surface of the spherical convex washer 13 and the concave surface of the concave concave washer 14 are engaged together, and the contact surface between the two serves as a sliding friction-reducing surface.

[0024] An adjusting rod limiting component is provided between the limiting ring position adjusting rod 5 and the inner pull plate 2.

[0025] The adjusting rod limiting component includes a screw plug 15, a thrust spring 16, and a round-headed pin 17; an adjusting rod limiting circular hole 18 is provided on the inner pull plate 2, and an annular groove 19 is provided on the rod body of the adjusting rod 5 at the limiting ring position, the annular groove 19 being directly opposite the adjusting rod limiting circular hole 18 on the inner pull plate 2; the round-headed pin 17 is located at the innermost side of the adjusting rod limiting circular hole 18, and the round-headed pin 17 is engaged with the annular groove 19; the screw plug 15 is screwed and fixed at the outermost side of the adjusting rod limiting circular hole 18, and the thrust spring 16 is disposed between the screw plug 15 and the round-headed pin 17.

[0026] The following describes a single use of the present invention with reference to the accompanying drawings:

[0027] In this embodiment, the outer support frame 1 includes four circumferentially distributed legs, the number of hooks 3 is set to four, and the number of limit ring position adjustment rods 5 is set to four.

[0028] Before disassembly, first place the four legs of the outer support frame 1 against the outer end face of the rotor balancing assembly 11, and install a rubber pad 12 between the legs of the outer support frame 1 and the outer end face of the rotor balancing assembly 11. At the same time, extend the four claws 3 into the interior of the oil distribution sleeve assembly 10. Then, manually turn the claws 3 outward so that the outer side of the fingertip of the claw 3 forms a blocking and limiting engagement with the inner boss of the outer circle of the oil distribution sleeve assembly 10. At the same time, press down on the position adjustment rod 5 of the limiting ring to drive the claw limiting ring 4 to move downward until the claw limiting ring 4 and the claw are engaged. When the inner side of the fingertip of hook 3 is accurately fitted, the fingertip of hook 3 is restricted between the oil distribution sleeve assembly 10 and the hook 3 limiting ring 4 and cannot move freely. At the same time that the hook 3 limiting ring 4 is fitted with the inner side of the fingertip of hook 3, the annular groove 19 on the rod body of the limiting ring position adjustment rod 5 just moves to the adjusting rod limiting round hole 18 of the inner pull plate 2. Under the action of the thrust spring 16, the front end of the round head pin 17 is pushed into the annular groove 19, thereby limiting the axial degree of freedom of the limiting ring position adjustment rod 5, and thus locking the position of the hook 3 limiting ring 4.

[0029] After the above preparations are completed, hold the force application handle 8 and apply torque to the force application stud 6 to make the force application stud 6 rotate. At this time, the rotational motion of the force application stud 6 will be synchronously converted into the translational motion of the inner pull plate 2. With the help of the reverse support force generated by the outer support frame 1 pressing against the outer end face of the rotor balance assembly 11, the inner pull plate 2 will move outward along the axis and apply an axial outward pulling force to the hook 3. This pulling force will directly act on the oil distribution sleeve assembly 10. As the force application stud 6 continues to rotate, the inner pull plate 2 gradually moves outward, and the oil distribution sleeve assembly 10 will gradually be pulled out of the rotor balance assembly 11 until it is completely separated from the rotor balance assembly 11.

[0030] After the oil distribution sleeve assembly 10 is separated from the rotor balancing assembly 11, the oil distribution sleeve assembly 10 can be detached from the rotor balancing assembly 11 along with the puller of the present invention. Then, the position adjusting rod 5 of the limiting ring is pulled outward by force to overcome the pushing force of the thrust spring 16, so that the round pin 17 is disengaged from the annular groove 19. The position adjusting rod 5 of the limiting ring can then be pulled out smoothly. As the position adjusting rod 5 of the limiting ring is pulled out, the inner side of the fingertip of the hook claw 3 is disengaged from the hook claw 3, and the hook claw 3 is released from the limiting position. Then, the hook claw 3 is turned inward so that the outer side of the fingertip of the hook claw 3 is disengaged from the oil distribution sleeve assembly 10. Finally, the oil distribution sleeve assembly 10 is removed from the puller of the present invention, and the disassembly work is completed.

[0031] The solutions described in the embodiments are not intended to limit the scope of patent protection of this invention. All equivalent implementations or modifications that do not depart from the scope of this invention are included in the patent scope of this case.

Claims

1. A puller for disassembling an aero-engine oil separator sleeve assembly, characterized in that: The system includes an outer support frame, an inner pull plate, hooks, hook limit rings, limit ring position adjustment rods, and force-applying studs. The outer support frame is fitted with the rotor balancing assembly. A through hole for the force-applying stud is located at the center of the outer support frame. An annular limiting boss is fixed to the stud on the outer side of the outer support frame, and a force-applying handle is located at the outermost end of the stud. The inner pull plate is located inside the outer support frame and has a threaded hole at its center. The force-applying stud is screwed into the threaded hole at the center of the inner pull plate. The hooks are evenly distributed around the circumference of the inner pull plate. The root end of the hook is hinged to the inner pull plate via a cylindrical pin. The outer side of the hook's fingertip is fitted with the oil distribution sleeve assembly. The hook limit ring is fitted with the inner side of the hook's fingertip. Limiting rings are provided on both the outer support frame and the inner pull plate. A ring position adjusting rod passes through a hole. The inner end of the ring position adjusting rod is screwed and fixed to the hook claw limiting ring. The outer end of the ring position adjusting rod is located outside the outer support frame. The ring position adjusting rods are evenly distributed along the hook claw limiting ring. An adjusting rod limiting component is provided between the ring position adjusting rod and the inner pull plate. The adjusting rod limiting component includes a screw plug, a thrust spring, and a round-headed pin. An adjusting rod limiting circular hole is provided on the inner pull plate. An annular groove is provided on the rod body of the ring position adjusting rod, and the annular groove is directly opposite the adjusting rod limiting circular hole on the inner pull plate. The round-headed pin is located at the innermost side of the adjusting rod limiting circular hole and is engaged with the annular groove. The screw plug is screwed and fixed at the outermost side of the adjusting rod limiting circular hole, and the thrust spring is located between the screw plug and the round-headed pin.

2. The puller for disassembling an aero-engine oil separator sleeve assembly according to claim 1, characterized in that: A rubber pad is installed between the outer support frame and the rotor balancing assembly.

3. The puller for disassembling an aero-engine oil separator sleeve assembly according to claim 1, characterized in that: A friction-reducing component is fitted onto the force-applying stud between the annular limiting boss and the outer support frame.

4. The puller for disassembling an aero-engine oil separator sleeve assembly according to claim 3, characterized in that: The friction-reducing component includes a spherical convex washer and a conical concave washer. The convex surface of the spherical convex washer and the concave surface of the concave concave washer are engaged together, and the contact surface between the two serves as a sliding friction-reducing surface.

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