Precise sealing assembly of aviation engine

Abstract

The utility model relates to the technical field of aviation engine sealing, in particular to a precise sealing assembly of an aviation engine. The device comprises a lifting assembly, the lifting assembly comprises a lead screw, a sliding block is slidably inserted in the middle of the lead screw in a penetrating mode, the sliding block is fixedly connected with a second connecting pipe, a fixing block is rotatably arranged on one side of the sliding block, and a clamping block corresponding to the fixing block is slidably arranged in a first connecting pipe. And a pressure spring is fixedly arranged between the sliding block and the fixed block. The lead screw is driven by the limiting rod to rotate, meanwhile, the lead screw drives the second connecting pipe to slide up and down in the first connecting pipe to adjust the length of the device, and the distance between the first connecting pipe and the second connecting pipe can be freely adjusted according to needs to adjust the length of the device. And the situation that the pipeline needs to be cut when the pipeline in the engine is connected due to the improper length of the device is prevented, and the practicability of the device is improved.

Description

Technical Field

[0001] The utility model relates to the technical field of aviation engine sealing, and particularly to a precision sealing component for an aviation engine. Background Art

[0002] An aeroengine is a device that provides flight power for an aircraft. The sealing components of an aviation engine are key components to ensure the sealing between different components inside the aeroengine. They are crucial for maintaining the internal pressure of the engine, preventing gas leakage, and protecting the internal structure of the engine. When manufacturing an aviation engine, multiple internal pipelines need to be connected using sealing components. Since the length of the existing sealing components for connecting the internal pipelines is fixed, sealing components with different lengths are required to connect pipelines with different spacings. When there is no sealing component with a suitable length, a part of the pipeline needs to be cut off, which is very troublesome to operate. In view of this, we propose a precision sealing component for an aviation engine. Content of the Utility Model

[0003] The purpose of the utility model is to provide a precision sealing component for an aviation engine to solve the problems raised in the above background art.

[0004] To achieve the above purpose, the utility model provides a precision sealing component for an aviation engine, including a first connecting pipe. An elevating component is arranged inside the first connecting pipe. A second connecting pipe is slidably arranged on the lower side of the first connecting pipe. The elevating component includes a lead screw rotatably arranged inside the first connecting pipe. A slider is slidably inserted through the middle of the lead screw. The slider is fixedly connected to the second connecting pipe. A fixed block is rotatably arranged on one side of the slider. A clamping block corresponding to the fixed block is slidably arranged inside the first connecting pipe. A pressure spring is fixedly arranged between the slider and the fixed block. Both the slider and the fixed block are arranged inside the first connecting pipe.

[0005] As a further improvement of this technical solution, a first bevel gear is fixedly arranged on the upper side of the lead screw. A second bevel gear is meshed and connected to the upper side of the first bevel gear. A limiting rod is fixedly arranged in the middle of the second bevel gear. One end of the limiting rod close to the second bevel gear is rotatably arranged inside the first connecting pipe. The other end of the limiting rod far from the second bevel gear is fixedly provided with a knob. The knob is arranged outside the first connecting pipe.

[0006] As a further improvement of this technical solution, a first sealing strip is fixedly arranged on the upper side of the second connecting pipe. A second sealing strip corresponding to the first sealing strip is fixedly arranged on the lower side of the first connecting pipe. Both the second connecting pipe and the first sealing strip are made of rubber.

[0007] As a further improvement of the present technical solution, a first connector is provided on the upper side of the first connecting pipe. One side of the first connector is threadedly connected to a second connector corresponding to the first connector, and both the first connector and the second connector are threadedly connected to the upper side of the first connecting pipe.

[0008] As a further improvement of the present technical solution, two sealing rings are symmetrically and fixedly arranged up and down in the middle of the first connector and the second connector, and notch openings corresponding to the sealing rings are provided inside both the first connector and the second connector.

[0009] As a further improvement of the present technical solution, the lower side of the second connecting pipe is threadedly connected to the first connector and the second connector. Two sealing rings are symmetrically and fixedly arranged up and down in the middle of the first connector and the second connector, and notch openings corresponding to the two sealing rings are provided inside the first connector and the second connector.

[0010] Compared with the prior art, the beneficial effects of the present utility model are as follows:

[0011] In this precision sealing assembly for an aeroengine, the limiting rod drives the lead screw to rotate. At the same time, the lead screw drives the second connecting pipe to slide up and down inside the first connecting pipe to adjust the length of the device. Subsequently, the first connecting pipe and the second connecting pipe are fixed by connecting the fixing block and the clamping block. This device can freely adjust the distance between the first connecting pipe and the second connecting pipe according to needs to adjust the length of the device, preventing the need to cut the pipeline when connecting the internal pipelines of the engine due to inappropriate device length, and improving the practicability of the device. Description of the Drawings

[0012] Figure 1 It is a schematic diagram of the overall structure of the present utility model;

[0013] Figure 2 It is an exploded schematic diagram of the overall structure of the utility model;

[0014] Figure 3 It is a cross-sectional view of the structure of the first connecting pipe of the utility model;

[0015] Figure 4 It is a schematic diagram of the structure of the lifting assembly of the utility model.

[0016] The meanings of each label in the figure are as follows:

[0017] 1. First connecting pipe; 2. Lifting assembly; 21. Lead screw; 22. Slide block; 23. Fixing block; 24. Pressure spring; 25. First bevel gear; 26. Second bevel gear; 27. Limiting rod; 28. Knob.

[0018] 3. Second connecting pipe; 4. First sealing strip; 5. Second sealing strip; 6. First connector; 7. Second connector; 8. Sealing ring. Detailed implementation mode

[0019] The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0020] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", etc. indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the present invention.

[0021] Embodiment 1

[0022] Please refer to Figures 1 - 2As shown in the figure, this embodiment provides a precision sealing component for an aeroengine, including a first connecting pipe 1. A first connecting head 6 is arranged on the upper side of the first connecting pipe 1. One side of the first connecting head 6 is threadedly connected to a second connecting head 7 corresponding to the first connecting head 6. Both the first connecting head 6 and the second connecting head 7 are threadedly connected to the upper side of the first connecting pipe 1. Two sealing rings 8 are symmetrically and fixedly arranged up and down in the middle of the first connecting head 6 and the second connecting head 7. Notches corresponding to the sealing rings 8 are formed inside the first connecting head 6 and the second connecting head 7. A second connecting pipe 3 is slidably arranged on the lower side of the first connecting pipe 1. A first sealing strip 4 is fixedly arranged on the upper side of the second connecting pipe 3. A second sealing strip 5 corresponding to the first sealing strip 4 is fixedly arranged on the lower side of the first connecting pipe 1. To ensure a tight connection between the first connecting pipe 1 and the second connecting pipe 3, both the second connecting pipe 3 and the first sealing strip 4 are made of rubber. The lower side of the second connecting pipe 3 is threadedly connected to the first connecting head 6 and the second connecting head 7. Two sealing rings 8 are symmetrically and fixedly arranged up and down in the middle of the first connecting head 6 and the second connecting head 7. Notches corresponding to the two sealing rings 8 are formed inside the first connecting head 6 and the second connecting head 7. When using this device, the user first inserts one end of the two pipes into the inside of the sealing ring 8, and then connects the first connecting head 6 and the second connecting head 7. After connecting the first connecting head 6 and the second connecting head 7, the user connects the first connecting pipe 1 to the corresponding first connecting head 6 and second connecting head 7.

[0023] Please refer to Figures 2 - 4As shown in the figure, a lifting component 2 is arranged inside the first connecting pipe 1. The lifting component 2 includes a lead screw 21 which is rotatably arranged inside the first connecting pipe 1. A first bevel gear 25 is fixedly arranged on the upper side of the lead screw 21. A second bevel gear 26 is meshed and connected to the upper side of the first bevel gear 25. A limiting rod 27 is fixedly arranged in the middle of the second bevel gear 26. One end of the limiting rod 27 close to the second bevel gear 26 is rotatably arranged inside the first connecting pipe 1. A knob 28 is fixedly arranged at the end of the limiting rod 27 far from the second bevel gear 26. The knob 28 is arranged outside the first connecting pipe 1. After connecting the first connecting pipe 1 with the corresponding first connector 6 and second connector 7, the user drives the second bevel gear 26 to rotate by rotating the knob 28 outside the first connecting pipe 1. Subsequently, the second bevel gear 26 drives the first bevel gear 25 and the lead screw 21 below it to rotate. A slider 22 is slidably inserted through the middle of the lead screw 21. The slider 22 is fixedly connected to the second connecting pipe 3. The lead screw 21 drives the slider 22 and the second connecting pipe 3 to slide inside the first connecting pipe 1 to adjust the distance between the first connecting pipe 1 and the second connecting pipe 3. A fixing block 23 is rotatably arranged on one side of the slider 22. A clamping block corresponding to the fixing block 23 is slidably arranged inside the first connecting pipe 1. A compression spring 24 is fixedly arranged between the slider 22 and the fixing block 23. Both the slider 22 and the fixing block 23 are arranged inside the first connecting pipe 1. After adjusting the distance between the first connecting pipe 1 and the second connecting pipe 3, the user slides the clamping block to make it clamped with the fixing block 23. After connecting the fixing block 23 with the clamping block, the compression spring 24 presses the fixing block 23 to prevent the connection between the fixing block 23 and the clamping block from loosening. Subsequently, the user can connect the second connecting pipe 3 with the corresponding first connector 6 and second connector 7.

[0024] When the precision sealing component of the aero-engine in this embodiment is specifically used, the user first passes the pipeline through the middle of the two sealing rings 8, and then connects the first connector 6 and the corresponding second connector 7. After connecting the first connecting pipe 1 with the corresponding first connector 6 and second connector 7, the user drives the lead screw 21 to rotate by rotating the knob 28. At the same time, the lead screw 21 drives the second connecting pipe 3 to slide up and down inside the first connecting pipe 1 to adjust the length of the device. Subsequently, the first connecting pipe 1 and the second connecting pipe 3 are fixed by connecting the fixing block 23 with the clamping block. The device can freely adjust the distance between the first connecting pipe 1 and the second connecting pipe 3 according to needs to adjust the length of the device, preventing the pipeline inside the engine from being cut when connecting due to the inappropriate length of the device, and improving the practicability of the device.

[0025] The foregoing has shown and described the basic principles, main features and advantages of the present utility model. Those skilled in the art should understand that the present utility model is not limited by the above embodiments, and the above embodiments and the descriptions in the specification are only preferred examples of the present utility model, and are not used to limit the present utility model. Without departing from the spirit and scope of the present utility model, the present utility model will have various changes and improvements, and these changes and improvements all fall within the scope of the present utility model claimed. The scope of protection claimed by the present utility model is defined by the appended claims and their equivalents.

Claims

1. An aircraft engine precision sealing assembly, comprising a No. 1 connecting pipe (1), wherein a lifting assembly (2) is arranged inside the No. 1 connecting pipe (1), and a No. 2 connecting pipe (3) is slidably arranged under the No. 1 connecting pipe (1), characterized in that: The lifting assembly (2) comprises a screw rod (21), the screw rod (21) is rotatably arranged inside the No. 1 connecting tube (1), a slider (22) is slidably inserted in the middle of the screw rod (21), the slider (22) is fixedly connected to the No. 2 connecting tube (3), a fixed block (23) is rotatably arranged on one side of the slider (22), a clamping block corresponding to the fixed block (23) is slidably arranged inside the No. 1 connecting tube (1), a pressure spring (24) is fixedly arranged between the slider (22) and the fixed block (23), and the slider (22) and the fixed block (23) are both arranged inside the No. 1 connecting tube (1).

2. The aircraft engine precision sealing assembly according to claim 1, characterized in that: A first bevel gear (25) is fixedly arranged on the upper side of the screw rod (21), a second bevel gear (26) is meshedly connected to the upper side of the first bevel gear (25), a limit rod (27) is fixedly arranged in the middle of the second bevel gear (26), one end of the limit rod (27) close to the second bevel gear (26) is rotatably arranged inside the first connecting tube (1), and one end of the limit rod (27) away from the second bevel gear (26) is fixedly arranged with a knob (28), and the knob (28) is arranged on the outer side of the first connecting tube (1).

3. The aircraft engine precision sealing assembly according to claim 1, characterized in that: A No. 1 sealing strip (4) is fixedly arranged on the upper side of the No. 2 connecting pipe (3), and a No. 2 sealing strip (5) corresponding to the No. 1 sealing strip (4) is fixedly arranged on the lower side of the No. 1 connecting pipe (1), and the No. 2 connecting pipe (3) and the No. 1 sealing strip (4) are both made of rubber material.

4. The aircraft engine precision sealing assembly according to claim 1, characterized in that: A No. 1 connecting head (6) is arranged on the upper side of the No. 1 connecting pipe (1), and a No. 2 connecting head (7) corresponding to the No. 1 connecting head (6) is threadedly connected to one side of the No. 1 connecting head (6), and the No. 1 connecting head (6) and the No. 2 connecting head (7) are both threadedly connected to the upper side of the No. 1 connecting pipe (1).

5. The aircraft engine precision sealing assembly according to claim 4, characterized in that: Two sealing rings (8) are symmetrically fixedly arranged in the middle of the No. 1 connector (6) and the No. 2 connector (7) in an upper and lower manner, and notches corresponding to the sealing rings (8) are opened inside the No. 1 connector (6) and the No. 2 connector (7).

6. The aircraft engine precision sealing assembly according to claim 1, characterized in that: The lower side of the No. 2 connecting pipe (3) is threadedly connected to a No. 1 connecting head (6) and a No. 2 connecting head (7); two sealing rings (8) are symmetrically fixedly arranged in the middle of the No. 1 connecting head (6) and the No. 2 connecting head (7); and notches corresponding to the two sealing rings (8) are provided inside the No. 1 connecting head (6) and the No. 2 connecting head (7).

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