CN216841941U - Sealing structure of turbojet engine casing and guider sleeve - Google Patents
Sealing structure of turbojet engine casing and guider sleeve Download PDFInfo
- Publication number
- CN216841941U CN216841941U CN202122358261.9U CN202122358261U CN216841941U CN 216841941 U CN216841941 U CN 216841941U CN 202122358261 U CN202122358261 U CN 202122358261U CN 216841941 U CN216841941 U CN 216841941U
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- sealing
- turbojet engine
- sealing ring
- gaskets
- wall
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- 238000007789 sealing Methods 0.000 title claims abstract description 65
- 230000000694 effects Effects 0.000 abstract description 9
- 238000003825 pressing Methods 0.000 abstract description 8
- 238000005457 optimization Methods 0.000 description 4
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000005489 elastic deformation Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
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Abstract
The utility model discloses a sealing structure of a turbojet engine casing and a guider sleeve, which belongs to the technical field of turbojet engines, and the technical scheme is characterized in that the sealing structure comprises a casing body, a first sealing ring can extrude a fixed plate when a first connecting end and a second connecting end are inserted into the casing body, so that the fixed plate extrudes a movable plate and moves towards the direction close to the casing body, the fixed plate is arranged at the left side and the right side of a spring through gaskets, the pressing force of the pressing force can be more uniformly applied to the end surface of the spring to prevent the spring from generating unstable deformation, the sealing ring can be pressed by the movable plate and the fixed plate to play a sealing role, thereby preventing oil leakage of a gap between the casing body and the guider sleeve, sealing between the guider sleeve and the casing movable plate can be realized through the first sealing ring and the second sealing ring, the spring can transmit pretightening force to the sealing ring through the gaskets and the gaskets, meanwhile, the spring in a compressed state is in pressing contact with the gaskets on the left end face and the right end face, so that a good sealing effect can be achieved.
Description
Technical Field
The utility model relates to a turbojet engine technical field, in particular to turbojet engine casket and seal structure of director cover.
Background
The turbojet engine is a turbine engine and is characterized in that the turbojet engine completely depends on gas flow to generate thrust, the turbojet engine is usually used as the power of a high-speed airplane, but the oil consumption is higher than that of a turbofan engine, the turbojet engine is divided into a centrifugal type and an axial type, compared with the centrifugal turbojet engine, the axial type has the advantages of small cross section and high compression ratio, most of the conventional turbojet engines are axial type, and a sealing structure of a casing and a guide sleeve of the turbojet engine is required in the production process of the turbojet engine.
However, the sealing effect between the conventional turbojet engine casing and the guider sleeve is poor, and the sealing ring cannot be well compressed, so that the sealing element is loosened, and the problem of oil leakage is caused.
SUMMERY OF THE UTILITY MODEL
The utility model discloses to above problem, provide a seal structure of turbojet engine machine casket and director cover and solve above-mentioned problem.
The utility model discloses a realize like this, a seal structure of turbojet engine machine casket and director cover, including casket body and director cover, the right side of director cover fixedly connected with is located the inside first link and the second link of casket body in proper order, the fixed plate, two are all installed to the upper and lower both sides between the outer wall of second link and the inner wall of casket body the equal butt of one end of fixed plate has the movable plate, two the one end that the movable plate is relative all contacts with the outer wall of second link, two gaskets, per two are all installed to the inside of movable plate all install two springs between the gasket, two the sealing ring is installed on the right side of fixed plate and movable plate.
In order to further seal between director cover and the machine casket body, the utility model discloses a seal structure of turbojet engine machine casket and director cover is preferred, install first sealing washer and second sealing washer between the outer wall of second link and the inner wall of machine casket body, first sealing washer and second sealing washer are located the left and right sides of two fixed plates respectively.
In order to realize the friction seal between sealing ring and the second sealing washer, the utility model discloses a seal structure of turbojet engine machine casket and director cover is preferred, install the friction ring between sealing ring and the second sealing washer.
In order to improve the sealing effect, the utility model discloses a seal structure of turbojet engine machine casket and director cover is preferred, four the gasket is flexible gasket.
In order to make director cover and this body coupling of machine casket stable, the utility model discloses a seal structure of turbojet engine machine casket and director cover is preferred, be threaded connection between the outer wall of first link and the inner wall of machine casket body.
Compared with the prior art, the beneficial effects of the utility model are that:
1. according to the sealing structure of the turbojet engine casing and the guider sleeve, when the first connecting end and the second connecting end are inserted into the casing body, the fixed plate can be extruded through the first sealing ring, the fixed plate is enabled to extrude the movable plate and move towards the direction close to the casing body, the fixed plate is correspondingly arranged at the left side and the right side of the spring through the gaskets, pressing force applied by the gaskets can be more uniformly applied to the end face of the spring to prevent the spring from generating unstable deformation, the sealing ring can be compressed by the movable plate and the fixed plate to play a role in sealing, and oil leakage of a gap between the casing body and the guider sleeve is further prevented;
2. according to the sealing structure of the turbojet engine casing and the guider sleeve, the right gasket and the moving plate can transmit the pretightening force to the sealing ring through the spring, and the spring in a compressed state is in compression contact with the gaskets on the left end face and the right end face, so that a good sealing effect can be achieved.
Drawings
FIG. 1 is an overall structure diagram of a sealing structure of a turbojet engine casing and a guide sleeve according to the present invention;
FIG. 2 is a cross-sectional structural view of the sealing structure of the turbojet engine casing and the guide sleeve of the present invention;
fig. 3 is an enlarged structural view of a portion a of fig. 2 according to the present invention.
In the figure, 1, a casing body; 2. a guide sleeve; 201. a first connection end; 202. a second connection end; 3. A first seal ring; 301. a second seal ring; 4. a fixing plate; 401. moving the plate; 402. a gasket; 403. a spring; 404. a seal ring; 405. a friction ring.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
In the description of the present invention, it is to be understood that the terms "length", "width", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are merely for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention. In addition, in the description of the present invention, "a plurality" means two or more unless specifically limited otherwise.
Referring to fig. 1-3, the present invention provides a technical solution: the utility model provides a seal structure of turbojet engine machine casket and director cover, including casket body 1 and director cover 2, the right side of director cover 2 fixedly connected with in proper order is located first link 201 and the second link 202 of casket body 1 inside, fixed plate 4 is all installed to the upper and lower both sides between the outer wall of second link 202 and the inner wall of casket body 1, the equal butt of one end of two fixed plates 4 has movable plate 401, the relative one end of two movable plates 401 all contacts with the outer wall of second link 202, two gaskets 402 are all installed to the inside of two movable plates 401, all install two springs 403 between per two gaskets 402, sealing ring 404 is installed on the right side of two fixed plates 4 and movable plate 401.
In this embodiment: when the first connecting end 201 and the second connecting end are inserted into the casing body 1, the first sealing ring 3 can press the fixed plate 4 to enable the fixed plate 4 to press the moving plate 401 and move towards the direction close to the casing body 1, the gaskets 402 are correspondingly arranged at the left side and the right side of the spring 403, pressing force of the gaskets 402 can be more uniformly applied to the end face of the spring 403 to prevent the springs from generating unstable deformation, the right gasket 402 and the moving plate 401 can transmit pretightening force to the sealing ring 404 through the spring 403, and the spring 403 in a compressed state is in pressing contact with the gaskets 402 at the left end face and the right end face, so that a good sealing effect can be achieved, the sealing ring 404 can be pressed through the moving plate 401 and the fixed plate 4 to achieve a sealing effect, and oil leakage of a gap between the casing body 1 and the guider sleeve 2 is further prevented.
As a technical optimization scheme of the utility model, install first sealing washer 3 and second sealing washer 301 between the outer wall of second link 202 and the inner wall of receiver body 1, first sealing washer 3 and second sealing washer 301 are located the left and right sides of two fixed plates 4 respectively.
In this embodiment: further sealing between the guider sleeve 2 and the casing body 1 can be realized through the first sealing ring 3 and the second sealing ring 301, so that the problem of oil leakage is avoided.
As a technical optimization scheme of the utility model, install friction ring 405 between sealing ring 404 and the second sealing washer 301.
In this embodiment: the friction seal between the sealing ring 404 and the second sealing ring 301 can be realized by the friction ring 405, so that oil leakage is avoided.
As a technical optimization scheme of the utility model, four gaskets 402 are flexible gaskets.
In this embodiment: the gasket 402 is a flexible gasket having elastic deformation, so that the sealing effect can be improved.
As a technical optimization scheme of the present invention, a threaded connection is formed between the outer wall of the first connection end 201 and the inner wall of the casing body 1.
In this embodiment: the first connecting end 201 is connected with the casing body 1 in a threaded manner, so that the guide sleeve 2 can be stably connected with the casing body 1.
The utility model discloses a theory of operation and use flow: firstly, the guider sleeve 2 is connected with the casing body 1, specifically, the second connecting end 202 is inserted into the casing body 1, meanwhile, the first connecting end 201 is in threaded connection with the casing body 1, meanwhile, the first sealing ring 3 can extrude the fixing plate 4 to enable the fixing plate 4 to be stressed to extrude the moving plate 401, the moving plate 401 is stressed to extrude the gasket 402 to enable the gasket 402 to extrude the spring 403 through pressing force, the spring 403 is compressed, meanwhile, the spring 403 in a compressed state is in pressing contact with the left end face and the right end face, a good sealing effect can be achieved, and pretightening force is transmitted to the sealing ring 404 and the friction ring 405 through the right gasket 402 and the moving plate 401, and the sealing effect can be improved.
The present invention is not limited to the above preferred embodiments, and any modifications, equivalent replacements, and improvements made within the spirit and principle of the present invention should be included within the protection scope of the present invention.
Claims (5)
1. The utility model provides a seal structure of turbojet engine machine casket and director cover, includes casket body (1) and director cover (2), its characterized in that: the right side of the guider sleeve (2) is fixedly connected with a first connecting end (201) and a second connecting end (202) which are located inside a casing body (1) in sequence, fixing plates (4) are installed on the upper side and the lower side between the outer wall of the second connecting end (202) and the inner wall of the casing body (1), one end of each fixing plate (4) is abutted to a moving plate (401), one end, opposite to the moving plate (401), of each moving plate is contacted with the outer wall of the second connecting end (202), two gaskets (402) are installed inside the moving plates (401), every two springs (403) are installed between the gaskets (402), and a moving plate sealing ring (404) is installed on the right sides of the fixing plates (4) and the moving plates (401).
2. The seal structure of the turbojet engine casing and the guide sleeve according to claim 1, wherein: install first sealing washer (3) and second sealing washer (301) between the outer wall of second link (202) and the inner wall of machine casket body (1), first sealing washer (3) and second sealing washer (301) are located the left and right sides of two fixed plates (4) respectively.
3. The seal structure of the turbojet engine casing and the guide sleeve according to claim 1, wherein: a friction ring (405) is arranged between the sealing ring (404) and the second sealing ring (301).
4. The seal structure of the turbojet engine casing and the guide sleeve according to claim 1, wherein: four of the shims (402) are all flexible shims.
5. The sealing structure for the turbojet engine case and the guide sleeve as recited in claim 1, wherein: the outer wall of the first connecting end (201) is in threaded connection with the inner wall of the casing body (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122358261.9U CN216841941U (en) | 2021-09-28 | 2021-09-28 | Sealing structure of turbojet engine casing and guider sleeve |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122358261.9U CN216841941U (en) | 2021-09-28 | 2021-09-28 | Sealing structure of turbojet engine casing and guider sleeve |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216841941U true CN216841941U (en) | 2022-06-28 |
Family
ID=82083202
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202122358261.9U Expired - Fee Related CN216841941U (en) | 2021-09-28 | 2021-09-28 | Sealing structure of turbojet engine casing and guider sleeve |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216841941U (en) |
-
2021
- 2021-09-28 CN CN202122358261.9U patent/CN216841941U/en not_active Expired - Fee Related
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20220628 |