Aero turbine engine clamp mounting tool

Abstract

The utility model discloses a kind of aviation turbojet engine hoop installation tool, belong to the technical field of aero-engine installation tool.The tool includes bottom plate, two vertical support plates, hand presser, guide column and nut placing groove.Vertical support plate is fixed on bottom plate, guide column is positioned on vertical support plate for a part of positioning mount, and nut placing groove is used for preset nut.When installing, part of engine mount is positioned by guide column, after engine waist is aligned, press the other part of mount to make mounting hole plate coincide, and screw is fixed after hand presser is pressed tightly.The utility model realizes one person operation, reduces labor intensity, improves installation efficiency, avoids that mount and engine body surface are scratched.

Description

Technical Field

[0001] This utility model relates to the field of aircraft engine installation tools, and in particular to an aircraft turbojet engine clamp installation fixture. Background Technology

[0002] Aero-engine turbojet engine mounting brackets typically consist of two bent plates connected by screws, bent into a semi-circle, and then wound and secured within the engine's body groove. In existing installation methods, for high-thrust engines, the high rigidity of the bent plates necessitates two workers: one holds the engine and bracket, forcefully pressing the mounting plates towards alignment, while the other uses pliers to clamp the mounting plates, ensuring they align before tightening the bolts. This method has the following drawbacks: it requires a large workforce, is labor-intensive, has low installation efficiency, and the manual pressing process can easily cause the mounting bracket to rotate and rub against the engine fuselage, resulting in surface scratches and increasing production costs. Utility Model Content

[0003] The purpose of this utility model is to provide an installation fixture for aero-turbojet engine clamps to overcome the shortcomings of the prior art, enable one-person operation, reduce labor intensity, improve installation efficiency, and avoid scratches on the mounting bracket and engine fuselage surface.

[0004] To achieve the above objectives, this utility model provides a clamping fixture for aircraft turbojet engines, comprising:

[0005] Base plate;

[0006] Two vertical support plates are vertically fixed to the base plate, and the distance between them matches the outer diameter of the fixing frame after it is bent into a semicircle.

[0007] A positioning component is disposed on the vertical support plate and is used to position the mounting hole plate at the end of the fixing frame;

[0008] A manual clamping device is provided on one side of the vertical support plate and is used to clamp the mounting holes on both sides of the fixing frame so that they overlap.

[0009] Preferably, the positioning component includes:

[0010] A guide post is disposed at the top of the vertical support plate and is used to position the mounting hole plate at the end of the fixing frame;

[0011] Preferably, the positioning component further includes:

[0012] A nut placement slot is provided at the top of the vertical support plate for pre-positioning nuts.

[0013] Preferably, there are four guide columns, which are respectively located at the top of the two vertical support plates.

[0014] Preferably, the manual clamping device is a manual mechanical clamping device.

[0015] Compared with the prior art, the present invention has the following advantages and technical effects:

[0016] 1. The aviation turbojet engine clamp installation fixture provided by this utility model can be operated by one person through guide column positioning and manual clamping, reducing the number of personnel and labor intensity.

[0017] 2. The aviation turbojet engine clamp installation fixture provided by this utility model has high installation accuracy and avoids scratches on the fixing frame and engine fuselage surface caused by manual pressing.

[0018] 3. Improve installation efficiency and shorten installation time. Attached Figure Description

[0019] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0020] Figure 1 This is a schematic diagram of the installation fixture of this utility model;

[0021] Figure 2 This is a schematic diagram showing the usage state of the installation tooling of this utility model;

[0022] In the diagram: 1. Base plate; 2. Vertical support plate; 3. Manual clamp; 4. Guide column; 5. Nut placement slot; 6. Fixing bracket; 7. Engine; 8. Mounting hole plate. Detailed Implementation

[0023] It should be noted that, unless otherwise specified, the embodiments and features described in this utility model can be combined with each other. The described embodiments are merely some, not all, of the embodiments of this utility model. All other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this utility model. The present utility model will now be described in detail with reference to the accompanying drawings and embodiments.

[0024] like Figures 1 to 2 As shown, this utility model provides a clamping fixture for an aircraft turbojet engine, comprising:

[0025] Base plate 1;

[0026] Two vertical support plates 2 are vertically fixed to the base plate 1, and the distance between them matches the outer diameter of the fixed frame 6 after it is bent into a semicircle.

[0027] A positioning component is provided on the vertical support plate 2 and is used to position the mounting hole plate 8 at the end of the fixing frame 6.

[0028] Manual clamping device 3 is located on one side of the vertical support plate 2 and is used to clamp the mounting holes 8 on both sides of the fixing frame 6 so that they overlap.

[0029] Further optimization of the solution, including the positioning components:

[0030] Guide post 4 is located at the top of the vertical support plate 2 and is used to position the mounting hole plate 8 at the end of the fixing frame 6.

[0031] Further optimizations to the solution include the following positioning components:

[0032] Nut placement groove 5 is located at the top of the vertical support plate 2 and is used to pre-place nuts.

[0033] The design was further optimized so that there are four guide columns 4, which are respectively set at the top of the two vertical support plates 2.

[0034] Further optimizing the design, the manual clamping device 3 is a manual mechanical clamping device. Manually pulling the handle upwards loosens the clamping jaws, while pulling the handle downwards to the position of the vertical support plate 2 tightens them. This principle is similar to the function of pliers; fixing one handle of a pliers and pulling the other handle achieves the function of loosening the clamp. The manual mechanical clamping device is a commercially available component, and its working principle and usage are known existing technologies, which will not be elaborated here.

[0035] This utility model provides an aviation turbojet engine clamp installation fixture, including a base plate 1, two vertical support plates 2, a manual clamping device 3, four guide posts 4, and two nut placement slots 5. The vertical support plates 2 are vertically fixed to the base plate 1, with the distance between them being the same as the outer diameter of the semi-circularly bent mounting bracket 6, ensuring that the mounting bracket 6 accurately fits the body of the engine 7. The guide posts 4 are located on the surface of the vertical support plates 2 and are used to pass through the mounting hole plates 8 on one side of the mounting bracket 6 for positioning. The through holes on the mounting hole plates 8 are elongated holes to allow the mounting bracket 6 some room to move. The nut placement slots 5 are located on the base plate 1 for pre-positioning nuts.

[0036] During installation, first fix one side of the lower clamp of the mounting bracket 6 to the vertical support plate 2 using the guide post 4. The other side of the lower clamp is also fixed to another vertical support plate 2 using the guide post 4. The side of the upper clamp away from the manual clamping device 3 is connected to the lower clamp with screws. At this point, the connection between the upper and lower clamps is not fully tightened. The side of the upper clamp closest to the manual clamping device 3 can be lifted. Align the engine 7's body groove with the semicircular part of the mounting bracket 6 and press the engine 7 to ensure its body is in close contact with the mounting bracket 6. Then press the lifted upper clamp of the mounting bracket 6 to align its mounting hole plate 8 with the lower clamp's mounting hole plate 8. Activate the manual clamping device 3 to tighten the mounting hole plate 8 on the side where the nut is to be placed. Finally, use screws and the pre-placed nut to tighten the mounting bracket 6, completing the installation of the mounting bracket 6.

[0037] This invention simplifies the installation process by using guide posts for positioning and manual clamping, effectively solving the problems caused by manual operation in the prior art.

[0038] The above are merely preferred embodiments of this utility model, but the scope of protection of this utility model is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this utility model should be included within the scope of protection of this utility model.

Claims

1. A clamping fixture for an aircraft turbojet engine, characterized in that, include: Base plate (1); Two vertical support plates (2) are vertically fixed on the base plate (1), and the distance between them matches the outer diameter of the fixing frame (6) after it is bent into a semicircle; A positioning component is disposed on the vertical support plate (2) and is used to position the mounting hole plate (8) at the end of the fixing frame (6). Manual clamping device (3) is located on one side of the vertical support plate (2) and is used to clamp the mounting holes (8) on both sides of the fixing frame (6) so that they overlap.

2. The mounting fixture for aero-turbojet engines according to claim 1, characterized in that, The positioning component includes: Guide post (4), the guide post (4) is set at the top of the vertical support plate (2) and is used to position the mounting hole plate (8) at the end of the fixing frame (6).

3. The mounting fixture for aero-turbojet engines according to claim 2, characterized in that, The positioning component also includes: Nut placement groove (5) is provided at the top of the vertical support plate (2) for pre-positioning nuts.

4. The mounting fixture for aero-turbojet engines according to claim 2, characterized in that, The number of guide columns (4) is four, which are respectively located at the top of the two vertical support plates (2).

5. The mounting fixture for aero-turbojet engines according to claim 1, characterized in that, The manual clamp (3) is a manual mechanical clamping device.

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