A self-locking device structure for preventing loosening of a bolt

Abstract

The utility model discloses a bolt's anti -loose self -locking device structure relates to bolt self -locking technical field, including a plurality of connecting components for installing tail nozzle on turbojet engine body, and connecting component includes first connecting part or second connecting part, first connecting part includes the special screw of passing through tail nozzle and with turbojet engine body screw connection, and the special screw is detachably connected with the stop piece for preventing special screw loosening, and the stop piece is fixedly connected with tail nozzle, and second connecting part includes the outside hexagonal screw of passing through tail nozzle and with turbojet engine body screw connection, and the outside hexagonal screw is detachably connected with the holding piece for preventing outside hexagonal screw loosening, and the holding piece sets up on tail nozzle, the utility model discloses the rotation of special screw is restricted through stop piece, and the rotation of outside hexagonal screw is restricted through holding piece, makes special screw and outside hexagonal screw not because of thermal expansion and cold shrink from the loosening and falling off of turbojet engine body.

Description

Technical Field

[0001] This utility model relates to the field of bolt self-locking technology, and in particular to a bolt anti-loosening self-locking device structure. Background Technology

[0002] Turbojet engines rely entirely on the flow of exhaust gases to generate thrust and are typically used to power high-speed aircraft. Currently, the exhaust nozzles of turbojet engines require the use of screws for connection and fastening. The screws commonly used are hexagonal socket head cap screws to mount the exhaust nozzles onto the turbojet engine body. However, due to the high temperature at the exhaust nozzle location of a turbojet engine, thermal expansion and contraction at the screw connection points during engine shutdown and startup can cause the screws to loosen. Therefore, it is necessary to frequently check the looseness of the screws after shutdown and before startup.

[0003] Currently, existing technologies typically use washers to prevent bolts from loosening. For example, Chinese Patent Publication No. CN208565205U discloses a pre-installed anti-loosening shock-absorbing bolt and engine cover. This design uses upper and lower shock-absorbing washers to separate the bolt sleeve from the engine cover, avoiding direct contact between the two and thus reducing noise generated by their collision. At the same time, the lower shock-absorbing washer holds the lower part of the bolt sleeve in place, making it less likely for the bolt sleeve to fall off during pre-installation. However, the elasticity of the washers decreases under high-temperature conditions, resulting in unstable anti-loosening effects.

[0004] Therefore, there is an urgent need for a bolt anti-loosening self-locking device structure that can effectively prevent the screws at the tail nozzle of the turbojet engine from loosening and falling off, so that the tail nozzle can be effectively installed on the turbojet engine body. Utility Model Content

[0005] The purpose of this invention is to provide a bolt anti-loosening self-locking device structure to solve the problems existing in the prior art.

[0006] To achieve the above objectives, this utility model provides the following solution: This utility model provides a bolt anti-loosening self-locking device structure, including multiple connecting components for mounting the tail nozzle to the turbojet engine body. The connecting components include a first connecting part or a second connecting part; the first connecting part includes a special-shaped screw that passes through the tail nozzle and is threadedly connected to the turbojet engine body, and the special-shaped screw is detachably connected to a stop plate for preventing the special-shaped screw from loosening, the stop plate being fixedly connected to the tail nozzle; the second connecting part includes an external hexagonal screw that passes through the tail nozzle and is threadedly connected to the turbojet engine body, the external hexagonal screw being detachably connected to a clamping member for preventing the external hexagonal screw from loosening, the clamping member being disposed on the tail nozzle.

[0007] Preferably, the screw cap of the irregular screw has multiple teeth on its circumference, and the groove between two adjacent teeth is adapted to the stop plate.

[0008] Preferably, the plurality of teeth are spaced at equal intervals.

[0009] Preferably, the stop plate is rectangular in shape, one end of the stop plate is detachably connected to the toothed groove, and the other end of the stop plate is fixedly connected to the tail nozzle.

[0010] Preferably, the screw shank of the irregular screw passes through the positioning hole of the tail nozzle and is threadedly connected to the turbojet engine body.

[0011] Preferably, the stop piece is arranged in an arc shape.

[0012] Preferably, the clamping component includes a ring fixedly connected to the tail nozzle, the ring having a through hole at its center, the through hole being detachably connected to the external hexagonal screw, the through hole communicating with a positioning hole on the tail nozzle, and multiple clamping plates fixedly connected to the ring in the circumferential direction.

[0013] Preferably, the external hexagonal screw passes through the through hole and the positioning hole of the tail nozzle in sequence and is threadedly connected to the turbojet engine body.

[0014] Preferably, the screw cap of the external hexagonal screw is detachably connected to the retaining plate.

[0015] Preferably, the plurality of the retaining pieces are arranged at equal intervals.

[0016] The present invention discloses the following technical effects:

[0017] This invention restricts the rotation of the irregular-shaped screws by using a stop plate and restricts the rotation of the external hexagonal screws by using a clamping member, so that the irregular-shaped screws and external hexagonal screws will not loosen or fall off the turbojet engine body due to thermal expansion and contraction, and the tail nozzle can be effectively installed on the turbojet engine body. Attached Figure Description

[0018] 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.

[0019] Figure 1 This is a schematic diagram of the overall structure of this utility model;

[0020] Figure 2This is a schematic diagram of the first connecting part of this utility model;

[0021] Figure 3 This is a top view of the second connecting part of this utility model;

[0022] Figure 4 This is a top view of the clamping component of this utility model;

[0023] Among them, 1. turbojet engine body; 2. tail nozzle; 3. special-shaped screw; 4. stop plate; 5. clamping plate; 31. tooth; 32. tooth groove; 51. ring; 52. through hole; 53. external hexagon screw. Detailed Implementation

[0024] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0025] To make the above-mentioned objectives, features and advantages of this utility model more apparent and understandable, the utility model will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0026] Reference Figures 1-4 This utility model discloses a bolt anti-loosening self-locking device structure, including multiple connecting components for mounting the tail nozzle 2 onto the turbojet engine body 1. Each connecting component includes a first connecting part or a second connecting part. The first connecting part includes a non-circular screw 3 that penetrates the tail nozzle 2 and is threadedly connected to the turbojet engine body 1. The non-circular screw 3 is detachably connected to a stop plate 4 for preventing loosening, and the stop plate 4 is fixedly connected to the tail nozzle 2. The second connecting part includes an external hexagonal screw 53 that penetrates the tail nozzle 2 and is threadedly connected to the turbojet engine body 1. The external hexagonal screw 53 is detachably connected to a clamping member for preventing loosening, and the clamping member is disposed on the tail nozzle 2. The stop plate 4 or the clamping member is respectively fixed to the tail nozzle 2 by welding.

[0027] This invention restricts the rotation of the irregular screw 3 by using a stop plate 4 and restricts the rotation of the external hexagonal screw 53 by using a clamping member, so that the irregular screw 3 and the external hexagonal screw 53 will not loosen or fall off the turbojet engine body 1 due to thermal expansion and contraction, and the tail nozzle 2 can be effectively installed on the turbojet engine body 1.

[0028] The irregular screw 3 is an internal hexagon screw, which facilitates the installation and removal of the irregular screw 3.

[0029] In a further optimized design, the screw head of the irregular screw 3 has multiple teeth 31 circumferentially oriented, and the groove 32 between two adjacent teeth 31 is adapted to the stop plate 4. By inserting the stop plate 4 into the groove 32 between two adjacent teeth 31, the tightened irregular screw 3 can be effectively prevented from loosening and falling off.

[0030] The tilt angle of tooth 31 is 60°, and the depth of the stop plate 4 inserted into tooth groove 32 is ≥2mm.

[0031] The stop plate 4 is made of elastic metal material, which allows the irregular screw 3 to move during the tightening process, so that the irregular screw 3 can be effectively tightened.

[0032] The material test data used for the stop plate 4: for example, the tensile strength retention rate of 304 stainless steel at 800℃ is ≥85%.

[0033] The design was further optimized by creating multiple teeth 31 at equal intervals. This allows the stop plate 4 to be effectively inserted into the groove 32 between two adjacent teeth 31.

[0034] The design is further optimized so that the stop plate 4 is rectangular in shape, with one end of the stop plate 4 detachably connected to the tooth groove 32 and the other end of the stop plate 4 fixedly connected to the tail nozzle 2. This allows the stop plate 4 to be effectively inserted into the tooth groove 32 between two adjacent teeth 31.

[0035] In a further optimized design, the screw shank of the irregular-shaped screw 3 passes through the positioning hole of the tail nozzle 2 and is threadedly connected to the turbojet engine body 1. The tail nozzle 2 can be mounted on the turbojet engine body 1 using the irregular-shaped screw 3.

[0036] The design was further optimized so that the stop piece 4 is arranged in an arc shape. That is, the end of the stop piece 4 facing the groove 32 between two adjacent teeth 31 can be effectively inserted into the groove 32.

[0037] Further optimizing the design, the clamping component includes a ring 51 fixedly connected to the tail nozzle 2. The ring 51 has a through hole 52 at its center, which is detachably connected to an external hexagonal screw 53. The through hole 52 communicates with a positioning hole on the tail nozzle 2. Multiple clamping plates 5 are fixedly connected to the circumference of the ring 51. When the external hexagonal screw 53 is tightened, bending the clamping plates 5 causes them to abut against the outer side of the external hexagonal screw 53, effectively preventing the tightened external hexagonal screw 53 from loosening.

[0038] The ring 51 of the clamping component is welded to the tail nozzle 2.

[0039] In a further optimized design, the external hexagonal screw 53 passes through the through hole 52 and the positioning hole of the tail nozzle 2 in sequence, and is threadedly connected to the turbojet engine body 1. The tail nozzle 2 can be installed on the turbojet engine body 1 using the external hexagonal screw 53.

[0040] In a further optimized design, the screw cap of the external hexagonal screw 53 is detachably connected to the retaining plate 5. When multiple retaining plates 5 cover the external hexagonal screw 53, the external hexagonal screw 53 cannot rotate; when multiple retaining plates 5 do not cover the external hexagonal screw 53, the external hexagonal screw 53 can rotate.

[0041] The design was further optimized by setting multiple retaining plates 5 at equal intervals. This ensures that the retaining plates 5 can effectively cover the external hexagonal screws 53, thus effectively preventing the tightened external hexagonal screws 53 from loosening.

[0042] The anti-loosening effect test of this utility model: After 100 cycles of 800℃-25℃ test, the loosening rate of the irregular screw 3 and the external hexagonal screw 53 was 0.

[0043] Work process:

[0044] Reference Figures 1-2 When it is necessary to use special-shaped screws 3 to install the tail nozzle 2 on the turbojet engine body 1, the special-shaped screws 3 are used in conjunction with the retaining plates 4. Multiple retaining plates 4 are welded to the tail nozzle 2 at equal intervals. During the tightening process of the special-shaped screws 3, the teeth 31 of the special-shaped screws 3 will move the retaining plates 4, so that the special-shaped screws 3 can be tightened. After the special-shaped screws 3 are tightened, the retaining plates 4 are inserted into the grooves 32 between two adjacent teeth 31. The retaining plates 4 limit the teeth 31, which can effectively prevent the tightened special-shaped screws 3 from loosening and falling off. This prevents the special-shaped screws 3 from being loosened and falling off due to thermal expansion and contraction.

[0045] When disassembling the irregular screw 3, simply separate the stop plate 4 from the tooth groove 32 to disassemble the irregular screw 3.

[0046] This utility model is easy to install. Operators can install it with the help of an electric screwdriver. When the irregular screw 3 is tightened, the stop plate 4 will automatically lock the irregular screw 3 to prevent the irregular screw 3 from loosening.

[0047] Reference Figures 3-4When the tail nozzle 2 needs to be installed on the turbojet engine body 1 using an external hexagonal screw 53, the ring 51 is welded to the positioning hole of the tail nozzle 2, so that the through hole 52 is connected to the positioning hole. The external hexagonal screw 53 is then passed through the through hole 52 and the positioning hole of the tail nozzle 2 in sequence and threadedly connected to the turbojet engine body 1. After the external hexagonal screw 53 is tightened, multiple retaining plates 5 are bent so that they abut against the outer side of the external hexagonal screw 53. This effectively prevents the tightened external hexagonal screw 53 from loosening and is prevented from being loosened or dislodged due to thermal expansion and contraction.

[0048] When it is necessary to disassemble the external hexagonal screw 53, simply bend the retaining plate 5 so that the multiple retaining plates 5 can no longer cover the external hexagonal screw 53, and then the external hexagonal screw 53 can be disassembled.

[0049] This utility model is easy to install; the operator can install it with an electric screwdriver. After the external hexagonal screw 53 is tightened, multiple retaining plates 5 abut against the outer side of the external hexagonal screw 53, which can prevent the external hexagonal screw 53 from loosening.

[0050] Currently, existing technologies typically use spring washers to prevent loosening. However, when applied to turbojet engines, the temperature at the exhaust nozzle 2 of the turbojet engine is ≥800℃, and thermal cycling is frequent. The spring washers in existing technologies will fail due to high temperature elasticity. This invention effectively avoids changes in thread clearance caused by thermal expansion and contraction by using the rigid limiting of the metal stop plate 4 and the plastic deformation of the retaining plate 5.

[0051] The stop plate 4 and the retaining plate 5 of this utility model are designed based on the environment of the tail nozzle 2 of the turbojet engine and are aimed at the technical field of turbojet engines, rather than conventional anti-loosening methods of general machinery.

[0052] In the description of this utility model, it should be understood that the terms "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this utility model and do not indicate or imply that the device or element 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 this utility model.

[0053] The embodiments described above are merely preferred embodiments of the present utility model and are not intended to limit the scope of the present utility model. Various modifications and improvements made to the technical solutions of the present utility model by those skilled in the art without departing from the spirit of the present utility model should fall within the protection scope defined by the claims of the present utility model.

Claims

1. A bolt anti-loosening self-locking device structure, characterized in that: It includes multiple connecting components for mounting the tail nozzle (2) on the turbojet engine body (1), the connecting components including a first connecting part or a second connecting part; The first connecting part includes a special-shaped screw (3) that passes through the tail nozzle (2) and is threaded to the turbojet engine body (1). The special-shaped screw (3) is detachably connected to a stop plate (4) for preventing the special-shaped screw (3) from loosening. The stop plate (4) is fixedly connected to the tail nozzle (2). The second connection part includes an external hexagonal screw (53) that passes through the tail nozzle (2) and is threaded to the turbojet engine body (1). The external hexagonal screw (53) is detachably connected to a clamping member for preventing the external hexagonal screw (53) from loosening. The clamping member is disposed on the tail nozzle (2).

2. The anti-loosening self-locking device structure for bolts according to claim 1, characterized in that: The screw cap of the irregular screw (3) has multiple teeth (31) on its circumference, and the groove (32) between two adjacent teeth (31) is adapted to the stop plate (4).

3. The anti-loosening self-locking device structure for bolts according to claim 2, characterized in that: Multiple teeth (31) are equally spaced.

4. The anti-loosening self-locking device structure for bolts according to claim 2, characterized in that: The stop plate (4) is rectangular in shape. One end of the stop plate (4) is detachably connected to the tooth groove (32), and the other end of the stop plate (4) is fixedly connected to the tail nozzle (2).

5. The anti-loosening self-locking device structure for bolts according to claim 2, characterized in that: The screw shank of the irregular screw (3) passes through the positioning hole of the tail nozzle (2) and is threadedly connected to the turbojet engine body (1).

6. The anti-loosening self-locking device structure for bolts according to claim 1, characterized in that: The stop piece (4) is arranged in an arc shape.

7. The anti-loosening self-locking device structure for bolts according to claim 1, characterized in that: The clamping component includes a ring (51) fixedly connected to the tail nozzle (2). The ring (51) has a through hole (52) at its center. The through hole (52) is detachably connected to the external hexagonal screw (53). The through hole (52) is connected to the positioning hole on the tail nozzle (2). Multiple clamping plates (5) are fixedly connected to the ring (51) in the circumferential direction.

8. The anti-loosening self-locking device structure for bolts according to claim 7, characterized in that: The external hexagonal screw (53) passes through the through hole (52) and the positioning hole of the tail nozzle (2) in sequence and is threadedly connected to the turbojet engine body (1).

9. The anti-loosening self-locking device structure for bolts according to claim 8, characterized in that: The screw cap of the external hexagonal screw (53) is detachably connected to the retaining plate (5).

10. The anti-loosening self-locking device structure for bolts according to claim 7, characterized in that: The multiple clamping pieces (5) are arranged at equal intervals.

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