A multi-model aero-engine spring assembly auxiliary assembly device and method

Abstract

The application discloses a kind of multi-model aero-engine spring assembly auxiliary assembly devices, including spring assembly main body assembly rack and cable tensioning assembly;Spring assembly main body assembly rack includes assembly base;Multi-angle adjustable sliding block, fixed support and stop boss are provided on the assembly base;Multi-angle adjustable sliding block, fixed support and stop boss form the installation space of spring assembly between them.The application also provides a kind of multi-model aero-engine spring assembly auxiliary assembly method.Through the cooperation of spring assembly main body assembly rack and cable tensioning assembly, the assembly of multi-model spring assembly can be effectively assisted, single-person operation is always guaranteed in the assembly process that spring torque is in qualified range, while the assembly efficiency is improved, the safety hazard in the assembly process is reduced.

Description

Technical Field

[0001] This invention belongs to the field of engine spring assembly technology, specifically relating to an auxiliary assembly device and method for spring assemblies of multiple types of aero engines. Background Technology

[0002] The assembly of the spring assembly for an aircraft engine is a crucial step in ensuring the adjustability of the engine's adjustable nozzle. The assembly process involves screwing the flat spiral spring into the disc-shaped component assembly, using a pin to position the spiral spring's tail hole, and then installing the bracket after adjusting the spring to the required torque.

[0003] Currently, there are many difficulties in assembling spring assemblies: (1) Due to the irregular bottom of the disc-shaped part of the spring assembly, it is difficult to stop during assembly; (2) Due to the large torque of the spiral spring and the lack of gap in the spring contact surface wound into the disc-shaped part, it is difficult for the positioning pin to pass through the spring positioning hole for positioning; (3) Before assembling the bracket, it is necessary to keep the spring within the required torque range by pulling the steel cable, but there is no special steel cable pulling tool, which makes it difficult to ensure that the torque of the spring does not change during the assembly of the bracket. Summary of the Invention

[0004] To address the aforementioned problems, this invention aims to provide an auxiliary assembly device and method for spring assemblies of various types of aero engines.

[0005] To achieve the above objectives, the present invention adopts the following technical solution:

[0006] A multi-model aero-engine spring assembly auxiliary assembly device includes a spring assembly main assembly stand and a steel cable tensioning assembly.

[0007] The main assembly stand for the spring assembly includes an assembly base; a multi-angle adjustable slider, a fixed bracket, and a stop boss are provided on the assembly base; the multi-angle adjustable slider, the fixed bracket, and the stop boss form an installation space for the spring assembly.

[0008] Preferably, a stop bolt is provided on the multi-angle adjustable slider; the stop bolt is vertically disposed on the upper part of the multi-angle adjustable slider and penetrates the side wall of the multi-angle adjustable slider.

[0009] Preferably, an arc-shaped groove is provided on the mounting base, and a multi-angle adjustable slider is installed in the arc-shaped groove.

[0010] Preferably, the fixing bracket is U-shaped and detachably connected to the mounting base; a bracket mounting hole is provided on the top of the fixing bracket.

[0011] Preferably, the retaining boss is provided with multiple boss bolt holes for mounting the spring assembly.

[0012] Preferably, the cable tensioning assembly includes a screw anti-rotation bracket; an anti-rotation tension screw is provided on the top of the screw anti-rotation bracket, and the screw anti-rotation bracket is arranged perpendicularly to the anti-rotation tension screw.

[0013] Preferably, a screw drive nut is provided on the outer wall of the anti-rotation tension screw.

[0014] Preferably, the anti-rotation tensioning screw is positioned facing the spring assembly body assembly stand; a screw thread hole is provided along the length of the anti-rotation tensioning screw.

[0015] Preferably, the spring assembly main assembly frame and the steel cable tensioning assembly are detachably mounted on the worktable.

[0016] A method for assisted assembly of spring assemblies for multiple types of aircraft engines includes the following steps:

[0017] S1. Assemble the spring assembly in the mounting space formed between the multi-angle adjustable slider, the fixed bracket, and the stop boss, and wind the spring into the housing of the spring assembly;

[0018] S2. Adjust the multi-angle adjustable slider and use the stop bolt to hold the spring assembly in place; rotate the spring to lock it into the positioning groove inside the spring assembly;

[0019] S3. Attach one end of the steel cable to the spring assembly, screw the other end of the steel cable into the threaded hole of the anti-rotation tensioning screw, and install the anti-rotation tensioning screw on the anti-rotation bracket;

[0020] S4. When the spring is tightened to the required torque, adjust the screw drive nut to tighten the steel cable, and install the spring assembly bracket.

[0021] Compared with the prior art, the present invention has the following advantages:

[0022] The present invention discloses an auxiliary assembly device and method for multiple types of aero-engine spring assemblies. By cooperating with the main assembly stand of the spring assembly and the steel cable tensioning assembly, the assembly of multiple types of spring assemblies can be effectively assisted. During the assembly process, a single person can operate the assembly and the spring torque is always kept within the qualified range. The assembly efficiency is improved while reducing safety hazards during the assembly process. Attached Figure Description

[0023] To more clearly illustrate the technical solutions in the specific embodiments of the present invention, the drawings used in the description of the embodiments 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.

[0024] Figure 1This is a schematic diagram of the structure of an auxiliary assembly device for spring assemblies of multiple types of aero engines according to the present invention;

[0025] Figure 2 This is a schematic diagram of the main assembly stand for the spring assembly in this invention;

[0026] Figure 3 for Figure 2 Top view;

[0027] Figure 4 This is a schematic diagram of the assembly of the spring assembly main body assembly stand and the spring assembly in this invention;

[0028] Figure 5 for Figure 4 The front view;

[0029] Figure 6 This is a schematic diagram of the steel cable tensioning assembly in this invention;

[0030] Reference numerals: 1-Spring assembly main assembly stand, 10-Assembly base, 100-Arc-shaped slide, 11-Multi-angle adjustable slider, 110-Stop bolt, 12-Fixed bracket, 120-Bracket mounting hole, 13-Stop boss, 130-Boss bolt hole, 2-Steel cable tensioning assembly, 20-Screw anti-rotation bracket, 21-Anti-rotation tension screw, 210-Screw threaded hole, 22-Screw drive nut, 3-Spring assembly, 4-Worktable. Detailed Implementation

[0031] The present invention will be further described below with reference to the accompanying drawings and specific embodiments. However, it should not be construed that the scope of the subject matter of the present invention is limited to the following embodiments. All modifications, substitutions and alterations made based on ordinary technical knowledge and common practices in the art without departing from the above-described technical concept of the present invention are included within the scope of the present invention.

[0032] Combined with reference Figures 1 to 6 This invention discloses an auxiliary assembly device for spring assemblies of various types of aero-engines, comprising a spring assembly main body assembly stand 1 and a steel cable tensioning assembly 2; the spring assembly main body assembly stand 1 and the steel cable tensioning assembly 2 are detachably mounted on a workbench 4. Specifically, in this embodiment, the spring assembly main body assembly stand 1 and the steel cable tensioning assembly 2 are spaced apart on the workbench 4 and are respectively fixedly connected to the workbench 4 using M5 fixing bolts.

[0033] The main assembly frame of the spring assembly includes an assembly base 10, and M5 fixing bolts are provided at the four corners of the assembly base 10 for detachable connection with the worktable 4.

[0034] A multi-angle adjustable slider 11, a fixed bracket 12, and a stop boss 13 are provided on the mounting base 10; the multi-angle adjustable slider 11, the fixed bracket 12, and the stop boss 13 form an installation space for the spring assembly 3.

[0035] A stop bolt 110 is provided on the multi-angle adjustable slider 11. The stop bolt 110 is vertically provided on the upper part of the multi-angle adjustable slider 11 and passes through the side wall of the multi-angle adjustable slider 11. When the spring assembly 3 is placed in the installation space, it can be held in place by rotating the stop bolt 110.

[0036] An arc-shaped groove 100 is provided on the mounting base 10, and a multi-angle adjustable slider 11 is installed in the arc-shaped groove 100. Specifically, in this embodiment, the arc direction of the arc-shaped groove 100 is oriented towards the direction of the fixed bracket 12 and the stop boss 13. The bottom of the multi-angle adjustable slider 11 has protruding edges on both sides, and M2 fixing bolts and M5 hexagonal fixing nuts are provided on the protruding edges. When the multi-angle adjustable slider 11 moves to the desired position in the arc-shaped groove 100, the position of the multi-angle adjustable slider 11 can be fixed by the M2 fixing bolts and M5 hexagonal fixing nuts.

[0037] The fixed bracket 12 is U-shaped and detachably connected to the mounting base 10; a bracket mounting hole 120 is provided on the top of the fixed bracket 12. Specifically, the U-shaped opening of the fixed bracket 12 is oriented towards the multi-angle adjustable slider 11 and the stop boss 13; the bottom of the fixed bracket 12 is fixedly connected to the mounting base 10 by an M5 hexagonal bolt; the bracket mounting hole 120 on the top of the fixed bracket 12 is used to install the spring assembly 3.

[0038] The stop boss 13 is provided with a plurality of boss bolt holes 130 for mounting the spring assembly 3. In this embodiment, the boss bolt holes 130 are located at the four corners of the stop boss 13. To better mount the spring assembly 3, the top end face of the stop boss 13 is inclined, with the inclination direction facing the multi-angle adjustable slider 11.

[0039] The steel cable tensioning assembly 2 includes a lead screw anti-rotation bracket 20; the lead screw anti-rotation bracket 20 is detachably connected to the worktable 4 by an M5 fixing bolt located at the bottom.

[0040] An anti-rotation tension screw 21 is provided at the top of the anti-rotation bracket 20, and the anti-rotation bracket 20 and the anti-rotation tension screw 21 are arranged perpendicularly. Specifically, an opening is provided at the top of the anti-rotation bracket 20, the anti-rotation tension screw 21 is installed in the opening, and is arranged perpendicularly to the anti-rotation bracket 20.

[0041] A screw drive nut 22 is provided on the outer wall of the anti-rotation tension screw 21. The screw drive nut 22 is installed on the side of the anti-rotation tension screw 21 away from the spring assembly main body assembly stand 1.

[0042] The anti-rotation tension screw 21 is positioned facing the spring assembly main body assembly stand 1; a screw thread hole 210 is provided in the length direction of the anti-rotation tension screw 21.

[0043] This invention also provides an auxiliary assembly method for spring assemblies of multiple types of aero engines, comprising the following steps:

[0044] S1. Assemble the spring assembly 3 in the mounting space formed between the multi-angle adjustable slider 11, the fixed bracket 12 and the stop boss 13, and roll the spring assembly 3 cover into the housing of the spring assembly.

[0045] S2. Adjust the multi-angle adjustable slider 11 and use the stop bolt 110 to hold the spring assembly 3 in place; rotate the spring clockwise to insert the spring into the positioning groove inside the spring assembly 3;

[0046] S3. Attach one end of the steel cable to the spring assembly 3, and screw the other end of the steel cable into the threaded hole 210 of the anti-rotation tensioning screw 21, and attach the anti-rotation tensioning screw 21 to the anti-rotation bracket 20;

[0047] S4. When the spring is tightened to the required torque, adjust the screw drive nut 22 to tighten the steel cable and install the spring assembly bracket.

[0048] The present invention provides an auxiliary assembly device and method for multiple types of aero-engine spring assemblies. By cooperating with the spring assembly main assembly stand 1 and the steel cable tensioning assembly 2, the assembly of multiple types of spring assemblies 3 can be effectively assisted. During the assembly process, a single person can operate the assembly and the spring torque is always kept within the qualified range. The assembly efficiency is improved while reducing safety hazards during the assembly process.

[0049] The foregoing has provided a detailed description of the auxiliary assembly device and method for spring assemblies of multiple types of aero-engines provided by the present invention. Specific examples have been used to illustrate the structure and working principle of the invention. The descriptions of the embodiments above are merely for the purpose of helping to understand the method and core ideas of the present invention. It should be noted that those skilled in the art can make various improvements and modifications to the present invention without departing from its principles, and these improvements and modifications also fall within the scope of protection of the claims of the present invention.

Claims

1. An auxiliary assembly device for spring assemblies of multiple types of aircraft engines, characterized in that: It includes a spring assembly main assembly stand (1) and a steel cable tensioning assembly (2); The spring assembly main assembly stand (1) includes an assembly base (10); a multi-angle adjustable slider (11), a fixed bracket (12) and a stop boss (13) are provided on the assembly base (10); the multi-angle adjustable slider (11), the fixed bracket (12) and the stop boss (13) form an installation space for the spring assembly (3); A stop bolt (110) is provided on the multi-angle adjustable slider (11); the stop bolt (110) is vertically provided on the upper part of the multi-angle adjustable slider (11) and passes through the side wall of the multi-angle adjustable slider (11); An arc-shaped slide groove (100) is provided on the mounting base (10), and a multi-angle adjustable slider (11) is installed in the arc-shaped slide groove (100); The stop boss (13) is provided with multiple boss bolt holes (130) for mounting the spring assembly (3).

2. The auxiliary assembly device for spring assemblies of multiple types of aero-engines according to claim 1, characterized in that: The fixed bracket (12) is U-shaped and can be detachably connected to the mounting base (10); a bracket mounting hole (120) is provided on the top of the fixed bracket (12).

3. The auxiliary assembly device for spring assemblies of multiple types of aircraft engines according to claim 2, characterized in that: The cable tensioning assembly (2) includes a screw anti-rotation bracket (20); an anti-rotation tension screw (21) is provided on the top of the screw anti-rotation bracket (20), and the screw anti-rotation bracket (20) and the anti-rotation tension screw (21) are arranged perpendicularly.

4. The auxiliary assembly device for spring assemblies of multiple types of aircraft engines according to claim 3, characterized in that: A screw drive nut (22) is provided on the outer wall of the anti-rotation tension screw (21).

5. The auxiliary assembly device for spring assemblies of multiple types of aero-engines according to claim 4, characterized in that: The anti-rotation tension screw (21) is positioned toward the spring assembly main body assembly stand (1); a screw thread hole (210) is provided in the length direction of the anti-rotation tension screw (21).

6. The auxiliary assembly device for spring assemblies of multiple types of aero-engines according to claim 5, characterized in that: The spring assembly main assembly frame (1) and the steel cable tensioning assembly (2) are detachably installed on the workbench (4).

7. An assembly method for an auxiliary assembly device for spring assemblies of multiple types of aero-engines according to claim 6, characterized in that: Includes the following steps: S1. Assemble the spring assembly (3) in the mounting space formed between the multi-angle adjustable slider (11), the fixed bracket (12) and the stop boss (13), and wind the spring into the housing of the spring assembly (3); S2. Adjust the multi-angle adjustable slider (11) and use the stop bolt (110) to hold the spring assembly (3) in place; rotate the spring to insert it into the positioning groove inside the spring assembly (3); S3. Attach one end of the steel cable to the spring assembly (3), screw the other end of the steel cable into the threaded hole (210) of the anti-rotation tensioning screw (21), and attach the anti-rotation tensioning screw (21) to the anti-rotation bracket (20); S4. When the spring is tightened to the required torque, adjust the screw drive nut (22) to tighten the steel cable and install the spring assembly bracket.

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