Fixing clamp for welding maintenance of low-pressure turbine protective cover of aero-engine

Abstract

The utility model discloses an aero-engine low-pressure turbine protective cover welding maintenance fixing clamp which is characterized by comprising a supporting seat, a clamp mechanism and a spot welding box. Wherein a plurality of supporting columns are vertically arranged on the lower surface of the supporting seat at equal intervals in the circumferential direction of the supporting seat, the outer edge part of the upper surface of the supporting seat is sunken downwards to form an annular assembling groove matched with the protective cover, the spot welding box is assembled on the upper surface of the supporting seat in an embedded mode, and the bottom of the spot welding box is provided with an air pipe connector in a communicating mode. A plurality of clamp mechanisms used for limiting and fixing the protective cover are arranged on the outer side of the bottom of the supporting base at intervals. When the fixing clamp is used, the defects that in the prior art, no special clamp is used for fixing the low-pressure turbine protective cover of the aero-engine, so that damage and deformation are extremely prone to occurring due to manual work in the disassembling, assembling and repairing processes, welding is not facilitated when an operator fixes a ring body with hands in the welding process, the operator is prone to being scalded due to high temperature, and the working efficiency is high are overcome. And aerial materials or personnel are easy to damage.

Description

Technical Field

[0001] The utility model relates to the field of aircraft engine maintenance or repair, in particular to a welding maintenance and fixing fixture for an aircraft engine low-pressure turbine protective cover. Background Art

[0002] The low-pressure turbine is one of the keys to the safe operation of the engine, and the radiation shield of the low-pressure turbine 4th stage guide vane is a key implementation component. The quality of the repair work is more important with the improvement of modern manufacturing technology. The existing repair of the radiation shield hole of the low-pressure turbine 4th stage guide vane has the following problems.

[0003] 1. The CF34-8C5 engine low-pressure turbine stage 4 guide vane is equipped with a radiation shield made of nickel-based alloy, less than 4mm wide, and has a ring-shaped shape without effective stress points. The disassembly and repair process is done manually, which is very easy to be damaged and deformed.

[0004] 2. Repairing the radiation shield hole of the low-pressure turbine stage 4 guide blade involves grinding and welding. During grinding, the shield is large and difficult to operate, and the shield body is easily distorted. During welding, due to the high welding temperature, when the operator fixes the ring body by hand, it is not only not conducive to welding, but also causes high temperature and easy burns to personnel.

[0005] 3. The radiation shield of the 4th stage guide vane of the low-pressure turbine is the main part of the CF34-8C5 engine. It has the functions of radiation shielding, thermal protection, prevention of foreign matter intrusion, and structural reinforcement, and has the characteristics of high value and high precision. Falling or collision will cause surface damage, hidden cracks or failure of the shield. When the CF34-8C5 engine is running, the shield may break and fall off, which will cause damage to the turbine blades and the surrounding structural parts to be affected by high temperature. There are many risk points in the repair work, which is easy to cause damage to aviation materials or personnel.

[0006] Therefore, it is an urgent problem to be solved by the present invention to provide an aircraft engine low-pressure turbine shield welding and maintenance fixing fixture which can overcome the above technical problems during use, stably fix the aircraft engine low-pressure turbine shield, greatly protect the welding materials, and facilitate the staff to perform welding and maintenance operations. Utility Model Content

[0007] In view of the above-mentioned technical problems, the purpose of the present utility model is to overcome the problem that there is no special clamp in the prior art to fix the low-pressure turbine protective cover of an aircraft engine, so that the low-pressure turbine protective cover of an aircraft engine is easily damaged and deformed due to manual work during the disassembly and maintenance process. During welding, due to the high welding temperature, when the operator uses his hands to fix the ring body, it is not only not conducive to welding, but also causes high temperature to easily burn people, and it is also easy to cause problems of damage to aviation materials or personnel. Therefore, a welding, maintenance and fixing clamp for the low-pressure turbine protective cover of an aircraft engine is provided, which can overcome the above-mentioned technical problems during use, stably fix the low-pressure turbine protective cover of an aircraft engine, greatly protect the welding materials, and facilitate the staff to perform welding and maintenance operations.

[0008] In order to achieve the above-mentioned purpose, the utility model provides a welding maintenance and fixing fixture for a low-pressure turbine shield of an aircraft engine, the fixture comprising: a support seat, a clamp mechanism and a spot welding box; wherein,

[0009] The lower surface of the support seat is vertically provided with a plurality of support columns at equal intervals along its circumferential direction, and the outer edge portion of the upper surface is recessed downward to form an annular assembly groove adapted to the protective cover. The spot welding box is embedded in the upper surface of the support seat, and an air pipe joint is connected to the bottom thereof. A plurality of clamping mechanisms for limiting and fixing the protective cover are also spaced apart on the outer side of the bottom of the support seat.

[0010] Preferably, the clamp mechanism comprises: a mounting block and a quick clamp;

[0011] A plurality of mounting blocks are arranged at intervals on the outer side of the bottom of the support seat, and each mounting block is provided with a quick clamp. The clamping head of each quick clamp can be abutted and limited from the side of the protective cover.

[0012] Preferably, the clamping head of each quick clamp is wrapped with a rubber sleeve.

[0013] Preferably, the upper surface portion of the support seat is recessed downward to form a box fixing groove with an outer opening for assembling a spot welding box, the upper end of the air pipe joint is connected to the box fixing groove, and the spot welding box is detachably assembled in the box fixing groove, and a plurality of through holes are provided on the side of the spot welding box facing the outer opening of the box fixing groove.

[0014] Preferably, the upper surface of the support seat is provided with fixing holes around the box fixing groove, and the top of the box fixing groove is covered by a box sealing plate to limit and fix the spot welding box.

[0015] Preferably, a screw hole is provided through the position of the support seat where the support column is installed, and the support column is fixed to the support seat by a screw, and the top of the screw is lower than the upper surface of the support seat.

[0016] Preferably, an anti-slip pad is provided at the bottom of the support column.

[0017] According to the above technical scheme, the beneficial effects of the welding, repair and fixing fixture of the low-pressure turbine protective cover of an aircraft engine provided by the utility model when in use are as follows: a support seat is used to support the protective cover to be repaired and processed, and it is sleeved on the support seat so that it is located in the annular assembly groove, and then a number of clamping mechanisms are used to abut and limit it from the protective cover to ensure its stability. The fixture of this structure can greatly protect the protective cover and prevent it from being damaged and deformed, and it is convenient for the staff to perform welding and repair operations, and it can also prevent the problem of high temperature easily scalding the staff.

[0018] Other features and advantages of the utility model will be described in detail in the subsequent specific implementation mode; and the parts not involved in the utility model are the same as the prior art or can be implemented by using the prior art. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] The accompanying drawings are used to provide a further understanding of the present invention and constitute a part of the specification. Together with the following specific embodiments, they are used to explain the present invention, but do not constitute a limitation to the present invention. In the accompanying drawings:

[0020] Figure 1 It is a structural schematic diagram of a welding maintenance fixture for a low-pressure turbine shield of an aircraft engine provided in a preferred embodiment of the utility model;

[0021] Figure 2 It is a top view schematic diagram of a welding maintenance fixture for a low-pressure turbine shield of an aircraft engine provided in a preferred embodiment of the utility model;

[0022] Figure 3 It is a structural schematic diagram of a box fixing groove of an aircraft engine low-pressure turbine shield welding maintenance fixing fixture provided in a preferred embodiment of the utility model.

[0023] Description of Reference Numerals

[0024] 1Support seat 2Annular assembly groove

[0025] 3 support columns 4 spot welding box

[0026] 5 air pipe joint 6 mounting block

[0027] 7 Quick clamp 8 Box fixing slot

[0028] 9 box cover 10 anti-slip pad DETAILED DESCRIPTION

[0029] The specific implementation of the present invention is described in detail below in conjunction with the accompanying drawings. It should be understood that the specific implementation described here is only used to illustrate and explain the present invention, and is not used to limit the present invention.

[0030] In the present utility model, unless otherwise stated, directional words such as "upper, lower, inside, outside" contained in a term merely represent the orientation of the term in normal use, or are common names understood by those skilled in the art, and should not be regarded as limitations on the term.

[0031] like Figure 1-3 As shown, the utility model provides a welding maintenance and fixing fixture for a low-pressure turbine shield of an aircraft engine, characterized in that the fixture comprises: a support seat 1, a clamp mechanism and a spot welding box 4; wherein,

[0032] The lower surface of the support seat 1 is vertically provided with a plurality of support columns 3 at equal intervals along its circumferential direction, and the outer edge portion of the upper surface is recessed downward to form an annular assembly groove 2 adapted to the protective cover, the spot welding box 4 is embedded in the upper surface of the support seat 1, and an air pipe joint 5 is connected to the bottom thereof, and a plurality of clamping mechanisms for limiting and fixing the protective cover are also spaced apart on the outer side of the bottom of the support seat 1.

[0033] In the above scheme, when the fixing clamp is in use, the support base 1 is used to support the protective cover to be repaired and processed, and it is put on the support base 1 so that it is located in the annular assembly groove 2, and then a number of clamping mechanisms are used to limit the protective cover from the protective cover to ensure its stability. The clamp of this structure can greatly protect the protective cover and prevent it from being damaged and deformed. It is also convenient for the staff to perform welding and maintenance operations, and can also prevent the problem of high temperature easily scalding the staff.

[0034] In a preferred embodiment of the utility model, the clamping mechanism includes: a mounting block 6 and a quick clamp 7; a plurality of mounting blocks 6 are spaced apart on the outer side of the bottom of the support seat 1, and a quick clamp 7 is provided on each of the mounting blocks 6, and the clamping head of each quick clamp 7 can be abutted and limited from the side of the protective cover.

[0035] In the above scheme, the quick clamp 7 is installed on the mounting block 6, and is assembled on the bottom of the support seat 1 by bolts and other parts. This mechanism is also convenient for disassembly and assembly. The quick clamp 7 is an existing device. When in use, the operating rod is rotated, and the position of the clamping head will rotate to abut against the side of the protective cover for abutment and limitation. Its specific structure will not be repeated.

[0036] In a preferred embodiment of the present invention, the clamping head of each quick clamp 7 is wrapped with a rubber sleeve.

[0037] In the above solution, the rubber sleeve can not only protect the protective cover, but also increase the friction force to ensure the stability of the fixation.

[0038] like Figure 3 As shown, in a preferred embodiment of the utility model, the upper surface of the support seat 1 is partially recessed downward to form a box fixing groove 8 with an outer opening for assembling the spot welding box 4, the upper end of the air pipe joint 5 is connected to the box fixing groove 8, and the spot welding box 4 is detachably assembled in the box fixing groove 8, and the spot welding box 4 is provided with a plurality of through holes on the side of the spot welding box 4 facing the outer opening of the box fixing groove 8. The upper surface of the support seat 1 is provided with fixing holes around the box fixing groove 8, and the top of the box fixing groove 8 is covered by a box sealing plate 9 to limit and fix the spot welding box 4.

[0039] In the above scheme, the spot welding box 4 is placed in the box fixing groove 8, and then the box sealing plate 9 is covered on its open opening and fixed to the support seat 1 with screws, so as to limit and fix the spot welding box 4. The spot welding box is located at the hole exploration mouth of the protective cover. The spot welding box 4 should be filled with metal velvet first and then coated with sealant for assembly.

[0040] In a preferred embodiment of the present invention, a screw hole is provided through the position where the support column 3 is installed on the support seat 1, and the support column 3 is fixed to the support seat 1 by screws, and the top of the screw is lower than the upper surface of the support seat 1.

[0041] In the above scheme, the mechanism can ensure the stability of the support column 3 on the one hand, and can also facilitate the disassembly and assembly of the support column 3 on the other hand, and the top of the screw is lower than the upper surface of the support seat 1 to prevent the top of the screw from protruding and easily damaging the material. The support column 3 is generally provided with 4, which can ensure stability and facilitate the assembly of the clamp mechanism.

[0042] In a preferred embodiment of the present invention, an anti-slip pad 10 is provided at the bottom of the support column 3 .

[0043] In the above solution, the anti-skid pad 10 can increase the friction between the support seat and the workbench, thereby achieving an anti-skid effect.

[0044] To sum up, the welding, maintenance and fixing fixture for the low-pressure turbine shield of an aircraft engine provided by the utility model overcomes the problem that there is no special fixture to fix the low-pressure turbine shield of an aircraft engine in the prior art, so that the shield is easily damaged and deformed during the disassembly and repair process, and the welding temperature is relatively high when the operator fixes the ring body by hand, which is not only not conducive to welding, but also causes high temperature to easily burn people, and is also prone to damage to aviation materials or personnel.

[0045] The preferred embodiments of the present invention are described in detail above in conjunction with the accompanying drawings. However, the present invention is not limited to the specific details in the above embodiments. Within the technical concept of the present invention, the technical solution of the present invention can be subjected to a variety of simple modifications, and these simple modifications all belong to the protection scope of the present invention.

[0046] It should also be noted that the various specific technical features described in the above specific embodiments can be combined in any suitable manner without contradiction. In order to avoid unnecessary repetition, the present utility model will not further describe various possible combinations.

[0047] In addition, various embodiments of the present invention may be arbitrarily combined, and as long as they do not violate the concept of the present invention, they should also be regarded as the contents disclosed by the present invention.

Claims

1. A welding and repair fixture for a low-pressure turbine shield of an aircraft engine, characterized in that: The clamp comprises: a support seat (1), a clamp mechanism and a spot welding box (4); wherein: The lower surface of the support seat (1) is provided with a plurality of support columns (3) at equal intervals in a circumferential direction thereof, and the outer edge portion of the upper surface thereof is recessed downward to form an annular assembly groove (2) adapted to the protective cover. The spot welding box (4) is embedded and assembled on the upper surface of the support seat (1), and a trachea joint (5) is provided at the bottom thereof in communication therewith. A plurality of clamping mechanisms for limiting and fixing the protective cover are also provided at intervals on the outer side of the bottom of the support seat (1).

2. The welding, repair and fixing fixture for the low-pressure turbine shield of an aircraft engine according to claim 1 is characterized in that: The clamp mechanism comprises: a mounting block (6) and a quick clamp (7); A plurality of mounting blocks (6) are arranged at intervals on the outer side of the bottom of the support seat (1), and each mounting block (6) is provided with a quick clamp (7), and the clamping head of each quick clamp (7) can be abutted and limited from the side of the protective cover.

3. The welding, repair and fixing fixture for the low-pressure turbine shield of an aircraft engine according to claim 2 is characterized in that: The clamping head of each quick clamp (7) is wrapped with a rubber sleeve.

4. The welding, repair and fixing fixture for the low-pressure turbine shield of an aircraft engine according to claim 1, characterized in that: The upper surface portion of the support seat (1) is recessed downward to form a box fixing groove (8) which is open on the outside and is used to assemble the spot welding box (4); the upper end of the air pipe joint (5) is connected to the box fixing groove (8), and the spot welding box (4) is detachably assembled in the box fixing groove (8); and a plurality of through holes are provided on the side of the spot welding box (4) which is open on the outside of the box fixing groove (8).

5. The welding, repair and fixing fixture for the low-pressure turbine shield of an aircraft engine according to claim 4 is characterized in that: The upper surface of the support seat (1) is provided with fixing holes around the box fixing groove (8), and the top of the box fixing groove (8) is covered by a box sealing plate (9) to limit and fix the spot welding box (4).

6. The welding, repair and fixing fixture for the low-pressure turbine shield of an aircraft engine according to claim 1, characterized in that: A screw hole is provided through the position on the support seat (1) where the support column (3) is installed, and the support column (3) is fixed to the support seat (1) by means of screws, and the top of the screw is lower than the upper surface of the support seat (1).

7. The welding, repair and fixing fixture for the low-pressure turbine shield of an aircraft engine according to claim 6, characterized in that: An anti-slip pad (10) is provided at the bottom of the support column (3).

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