Aero-engine blade maintenance fixing clamp

Abstract

The utility model discloses an aero-engine blade maintenance fixing clamp which comprises a base, a first pressing assembly, a jacking assembly and a limiting assembly, and a first limiting groove matched with an engine blade disc base is formed in the base in a sunken mode. A first limiting groove is formed in one side of the base, a first pressing assembly and a jacking assembly are arranged on the two opposite sides of the first limiting groove correspondingly, the first pressing assembly is used for pressing the edge of the engine blade, the jacking assembly is used for limiting the side wall of the engine blade, and a limiting assembly is further arranged on one side of the base; the limiting assembly is used for preventing engine blades from rotating. The problem that when the aero-engine blade is maintained, multiple positions of the aero-engine blade need to be limited and fixed is solved, and the stability is improved. Therefore, the aero-engine blade maintenance fixing clamp can limit and fix multiple positions of the aero-engine blade.

Description

Technical Field

[0001] This utility model relates to the field of aviation technology, specifically to a fixing fixture for the maintenance of aircraft engine blades. Background Technology

[0002] An aircraft engine is a highly complex and precise thermodynamic machine. As the heart of an aircraft, it not only powers the aircraft's flight but also serves as a vital driving force for the development of the aviation industry. Every major transformation in the history of human aviation has been inseparable from the technological advancements in aircraft engines.

[0003] When repairing aero-engine blades, it is necessary to limit and fix the blades at multiple positions to improve stability.

[0004] Therefore, providing a maintenance and fixing fixture for aero-engine blades that can limit and fix them at multiple positions is a problem that this utility model urgently needs to solve. Utility Model Content

[0005] To address the aforementioned technical problems, the purpose of this invention is to overcome the need for multi-position limiting and fixing of aero-engine blades during maintenance to improve stability. Therefore, this invention provides an aero-engine blade maintenance fixing fixture capable of multi-position limiting and fixing of aero-engine blades.

[0006] To achieve the above objectives, this utility model provides a maintenance and fixing fixture for aero-engine blades. The fixing fixture includes a base, a first clamping component, a tightening component, and an anti-slip component. The base has a recessed first limiting groove adapted to the engine blade disk base. The first clamping component and the tightening component are respectively provided on opposite sides of the first limiting groove. The first clamping component is used to clamp the edge of the engine blade, and the tightening component is used to limit the sidewall of the engine blade. A limiting component is also provided on one side of the base to prevent the engine blade from rotating.

[0007] Preferably, the first clamping assembly includes: a first pressure plate, a first fixing nut, and a second fixing nut. One side of the first pressure plate is fixed to the base by the first fixing nut, and the other side is detachably fixed to the base by the second fixing nut.

[0008] Preferably, the base is provided with a first groove adapted to the first fixing nut, the first fixing nut is movably disposed in the first groove, and the first pressure plate is recessed with a second groove adapted to the second fixing nut.

[0009] Preferably, the first fixing nut has a threaded mounting block on its shaft, and a second limiting groove adapted to the moving block is provided in the first strip groove, wherein the moving block is movably disposed in the second limiting groove.

[0010] Preferably, the clamping assembly includes a clamping screw and a second clamping assembly. The clamping screw is horizontally threaded onto the base, and the second clamping assembly is used to clamp the edge of the engine blade. The clamping screw can clamp against the sidewall of the engine blade.

[0011] Preferably, the second clamping assembly includes a second pressure plate and a third fixing nut, wherein the clamping screw is detachably provided with a second pressure plate on each of its opposite sides via the third fixing nut.

[0012] Preferably, the limiting component includes: a locking block and a fourth fixing nut, the fourth fixing nut being inserted into one side of the base with an inclined thread, the locking block being adapted to the gap between the engine blades and being threaded onto the fourth fixing screw, and a locking block abutting against the side wall of the locking block being provided on one side of the base.

[0013] According to the above technical solution, the beneficial effects of this utility model compared with the prior art are as follows: This application achieves initial fixation by clamping the aero-engine bladed disk in the first limiting groove, then pressing the edge of any blade of the engine with the first clamping component, then limiting the side wall of the blade on the other side with the tightening component, and finally adjusting the limiting component to clamp between any two adjacent blades to prevent the engine blades from rotating, thereby limiting and fixing the aero-engine at multiple positions, so as to facilitate the maintenance of the aero-engine blades and improve stability.

[0014] Other features and advantages of this utility model will be described in detail in the following detailed description section; and all parts not covered in this utility model are the same as or can be implemented using existing technology. Attached Figure Description

[0015] The accompanying drawings are provided to further illustrate the present invention and form part of the specification. They are used together with the following detailed description to explain the present invention, but do not constitute a limitation thereof. In the drawings:

[0016] Figure 1 This is a three-dimensional model of an aero-engine blade maintenance and fixing fixture provided in a preferred embodiment of the present invention. Figure 1 .

[0017] Figure 2 This is a three-dimensional model of an aero-engine blade maintenance and fixing fixture provided in a preferred embodiment of the present invention. Figure 2 .

[0018] Figure 3 This is a planar sectional view of an aero-engine blade maintenance and fixing fixture provided in a preferred embodiment of the present invention.

[0019] Figure 4 This is a partial three-dimensional representation of an aero-engine blade maintenance and fixing fixture provided in a preferred embodiment of the present invention. Figure 1 .

[0020] Figure 5 This is a partial three-dimensional representation of an aero-engine blade maintenance and fixing fixture provided in a preferred embodiment of the present invention. Figure 2 .

[0021] Figure 6 This is a partial three-dimensional representation of an aero-engine blade maintenance and fixing fixture provided in a preferred embodiment of the present invention. Figure 3 .

[0022] Explanation of reference numerals in the attached drawings: 1-Base; 101-First limiting groove; 102-First strip groove; 10201-Second limiting groove; 103-Clocking block; 2-First pressing assembly; 201-First pressure plate; 20101-Second strip groove; 202-First fixing nut; 203-Second fixing nut; 204-Moving block; 3-Tightening assembly; 301-Tightening screw; 302-Second pressing assembly; 30201-Second pressure plate; 30202-Third fixing nut; 4-Limiting assembly; 401-Clocking block; 402-Fourth fixing nut. Detailed Implementation

[0023] The specific embodiments of this utility model will be described in detail below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are for illustration and explanation only and are not intended to limit the scope of this utility model.

[0024] In the description of the embodiments of this utility model, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," indicating orientation or positional relationships, are based on the orientation or positional relationships shown in the accompanying drawings, or the orientation or positional relationships commonly used when the utility model product is in use. These are merely for the convenience of describing the utility model and simplifying the description, and do not indicate or imply that the device or component referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the utility model. Furthermore, the terms "first," "second," and "third," etc., are only used for distinguishing descriptions and should not be construed as indicating or implying relative importance. Additionally, the terms "horizontal," "vertical," and "suspended," etc., do not indicate that the component is required to be absolutely horizontal or suspended, but rather that it can be slightly tilted. For example, "horizontal" simply means that its direction is more horizontal than "vertical," and does not mean that the structure must be completely horizontal, but can be slightly tilted.

[0025] In the description of the embodiments of this utility model, it should also be noted that, unless otherwise explicitly specified and limited, the terms "set," "install," "connect," and "link" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0026] To further understand the features, technical means, and specific objectives and functions achieved by this utility model, the following detailed description of this utility model is provided in conjunction with the accompanying drawings and specific embodiments.

[0027] Reference Figure 1 and Figure 2 A blade maintenance fixture for an aero-engine includes a base 1, a first clamping component 2, a tightening component 3, and a limiting component 4. The base 1 has a recessed first limiting groove 101 adapted to the base of the engine blade disk. The first clamping component 2 and the tightening component 3 are respectively provided on opposite sides of the first limiting groove 101. The first clamping component 2 is used to clamp the edge of the engine blade, and the tightening component 3 is used to limit the sidewall of the engine blade. The limiting component 4 is also provided on one side of the base 1 to prevent the engine blade from rotating.

[0028] This application achieves initial fixation by clamping the aero-engine bladed disk into the first limiting groove 101, then pressing the edge of any blade of the engine with the first clamping component 2, then limiting the sidewall of the blade on the other side with the tightening component 3, and finally adjusting the limiting component 4 to clamp between any two adjacent blades to prevent the engine blades from rotating. This multi-position limiting and fixing of the aero-engine facilitates the maintenance of the aero-engine blades and improves stability.

[0029] Reference Figure 2 The first clamping assembly 2 includes a first pressure plate 201, a first fixing nut 202 and a second fixing nut 203. One side of the first pressure plate 201 is fixed to the base 1 by the first fixing nut 202, and the other side is detachably fixed to the base 1 by the second fixing nut 203.

[0030] This application achieves fixation by tightening the second fixing nut 203 to drive the first pressure plate 201 to press against the engine blade.

[0031] Reference Figure 3 and Figure 4 The base 1 is provided with a first strip groove 102 that is adapted to the first fixing nut 202. The first fixing nut 202 is movably disposed in the first strip groove 102. The first pressure plate 201 is recessed with a second strip groove 20101 that is adapted to the second fixing nut 203.

[0032] When it is necessary to remove the engine blades, this application only requires loosening the second fixing nut 203 and the first fixing nut 202, and then moving the first pressure plate 201 along the length of the strip groove to release the limit.

[0033] Reference Figure 3 and Figure 4 The first fixing nut 202 has a threaded rod body fitted with a moving block 204. The first strip groove 102 is provided with a second limiting groove 10201 that is adapted to the moving block 204. The moving block 204 is movably disposed in the second limiting groove 10201.

[0034] This application uses a design that allows the first fixing nut 202 to move along the length of the slot and to fix the first pressure plate 201. In use, the movement and fixation of the first pressure plate 201 can be achieved simply by tightening and loosening the first fixing nut 202.

[0035] Reference Figure 2The clamping assembly 3 includes a clamping screw 301 and a second clamping assembly 302. The clamping screw 301 is horizontally threaded onto the base 1. The second clamping assembly 302 is used to clamp the edge of the engine blade. The clamping screw 301 can clamp against the side wall of the engine blade.

[0036] This application uses the second clamping assembly 302 to clamp the edge of the engine blade, and then rotates the clamping screw 301 to clamp the clamping screw 301 against the side wall of the engine blade.

[0037] Reference Figure 3 and Figure 5 The second clamping assembly 302 includes a second pressure plate 30201 and a third fixing nut 30202. The clamping screw 301 is detachably provided with the second pressure plate 30201 on both sides by the third fixing nut 30202.

[0038] This application uses the third fixing nut 30202 to tighten the second pressure plate 30201, thereby pressing it against the edge of the engine blade.

[0039] Reference Figure 2 and Figure 6 The limiting component 4 includes a locking block 401 and a fourth fixing nut 402. The fourth fixing nut 402 is inserted into one side of the base 1 by an inclined thread. The shape of the locking block 401 is adapted to the gap between the engine blades and is threaded onto the fourth fixing screw. A locking block 103 that abuts against the side wall of the locking block 401 is also provided on one side of the base 1.

[0040] This application prevents the engine blades from rotating by locking the locking block 401 between any two adjacent engine blades. With the design of the locking block 103, the user only needs to hold one side of the locking block 401 to remove the locking block 401 by rotating the fourth fixing nut 402.

[0041] When in use, the device provided by this utility model is initially fixed by clamping the aero-engine bladed disk into the first limiting groove 101, then pressing the edge of any blade of the engine with the first pressing component 2, then limiting the side wall of the blade on the other side with the pressing component 3, and finally adjusting the limiting component 4 to clamp between any two adjacent blades to prevent the engine blades from rotating. This device limits and fixes the aero-engine at multiple positions, which facilitates the maintenance of the aero-engine blades and improves stability.

[0042] The preferred embodiments of the present invention have been described in detail above with reference to the accompanying drawings. However, the present invention is not limited to the specific details of the above embodiments. Within the scope of the technical concept of the present invention, various simple modifications can be made to the technical solution of the present invention, and these simple modifications all fall within the protection scope of the present invention.

[0043] It should also be noted that the various specific technical features described in the above specific embodiments can be combined in any suitable way without contradiction. In order to avoid unnecessary repetition, this utility model will not describe the various possible combinations separately.

[0044] Furthermore, various different embodiments of this utility model can be combined in any way, as long as they do not violate the spirit of this utility model, they should also be regarded as the content disclosed by this utility model.

Claims

1. A blade maintenance and fixing fixture for aero-engines, characterized in that, The fixing fixture includes: a base (1), a first clamping component (2), a top clamping component (3), and a limiting component (4). The base (1) is recessed and has a first limiting groove (101) adapted to the engine blade base. The first limiting groove (101) is provided with a first clamping component (2) and a top clamping component (3) on opposite sides. The first clamping component (2) is used to clamp the edge of the engine blade, and the top clamping component (3) is used to limit the sidewall of the engine blade. The base (1) is also provided with a limiting component (4) on one side. The limiting component (4) is used to prevent the engine blade from rotating.

2. The aircraft engine blade maintenance and fixing fixture according to claim 1, characterized in that, The first clamping assembly (2) includes: a first pressure plate (201), a first fixing nut (202) and a second fixing nut (203). One side of the first pressure plate (201) is fixed to the base (1) by the first fixing nut (202), and the other side is detachably fixed to the base (1) by the second fixing nut (203).

3. The aircraft engine blade maintenance fixing fixture according to claim 2, characterized in that, The base (1) is provided with a first strip groove (102) adapted to the first fixing nut (202), the first fixing nut (202) is movably disposed in the first strip groove (102), and the first pressure plate (201) is recessed with a second strip groove (20101) adapted to the second fixing nut (203).

4. The aircraft engine blade maintenance and fixing fixture according to claim 3, characterized in that, The first fixing nut (202) has a threaded rod body fitted with a movable block (204), and the first strip groove (102) is provided with a second limiting groove (10201) that is adapted to the movable block (204). The movable block (204) is movably disposed in the second limiting groove (10201).

5. The aircraft engine blade maintenance and fixing fixture according to claim 1, characterized in that, The clamping assembly (3) includes a clamping screw (301) and a second clamping assembly (302). The clamping screw (301) is horizontally threaded onto the base (1). The second clamping assembly (302) is used to clamp the edge of the engine blade. The clamping screw (301) can clamp against the side wall of the engine blade.

6. The aircraft engine blade maintenance and fixing fixture according to claim 5, characterized in that, The second clamping assembly (302) includes a second pressure plate (30201) and a third fixing nut (30202). The clamping screw (301) is detachably provided with the second pressure plate (30201) on both sides by the third fixing nut (30202).

7. The aircraft engine blade maintenance fixing fixture according to claim 1, characterized in that, The limiting component (4) includes: a locking block (401) and a fourth fixing nut (402). The fourth fixing nut (402) is inserted into one side of the base (1) with an inclined thread. The shape of the locking block (401) is adapted to the gap between the engine blades and is threaded onto the fourth fixing screw. A locking block (103) that abuts against the side wall of the locking block (401) is also provided on one side of the base (1).

Images