CN219866230U - Aeroengine metal sealing gasket - Google Patents
Aeroengine metal sealing gasket Download PDFInfo
- Publication number
- CN219866230U CN219866230U CN202321349038.0U CN202321349038U CN219866230U CN 219866230 U CN219866230 U CN 219866230U CN 202321349038 U CN202321349038 U CN 202321349038U CN 219866230 U CN219866230 U CN 219866230U
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- CN
- China
- Prior art keywords
- sealing
- sealing strip
- strip
- aeroengine
- aircraft engine
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- 238000007789 sealing Methods 0.000 title claims abstract description 152
- 239000002184 metal Substances 0.000 title claims abstract description 21
- 230000000694 effects Effects 0.000 abstract description 7
- 210000003205 muscle Anatomy 0.000 description 6
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000009423 ventilation Methods 0.000 description 1
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- Gasket Seals (AREA)
Abstract
The utility model relates to the technical field of aero accessories, and discloses a metal sealing gasket of an aero engine, which comprises an upper sealing ring and a lower sealing ring, wherein a first sealing strip and a second sealing strip are respectively and fixedly arranged at the bottom of the upper sealing ring, a third sealing strip is fixedly arranged at the top of the lower sealing ring, and the third sealing strip is inserted and arranged between the first sealing strip and the second sealing strip. The utility model discloses a dual-seal's structure for sealing connection between upper seal circle and the lower seal circle, thereby improved the sealed effect to aeroengine.
Description
Technical Field
The utility model relates to the technical field of aero accessories, in particular to a metal sealing gasket for an aero-engine.
Background
The metal sealing gasket is an important sealing element of an aeroengine ventilation pipeline and is formed by processing a metal plate with a flat surface.
Wherein the patent number is CN214887403U, discloses an aeroengine cylinder end sealing gasket, including being annular first sealing piece and second sealing piece, one side of first sealing piece is provided with elastic first protruding muscle, the length direction of first sealing piece is followed to first protruding muscle extends, the second sealing piece is located one side that first sealing piece set up first protruding muscle to the second sealing piece is located one side that first protruding muscle is close to the inner edge of first sealing piece.
In the above scheme, the sealing effect is mainly achieved by propping up the protruding parts of the first sealing piece and the second sealing piece, and once looseness occurs between the first sealing piece and the second sealing piece, the sealing effect is greatly reduced. For this purpose, a metal gasket for an aircraft engine is proposed.
Disclosure of Invention
The utility model aims to solve the problem of poor sealing effect of a metal sealing gasket of an aero-engine in the prior art, and provides the metal sealing gasket of the aero-engine.
In order to achieve the above purpose, the present utility model adopts the following technical scheme:
the utility model provides an aeroengine metal seal pad, includes sealing washer and lower sealing washer, the bottom of last sealing washer is fixed respectively and is equipped with first sealing strip and second sealing strip, the fixed third sealing strip that is equipped with in top of lower sealing washer, the third sealing strip peg graft and set up between first sealing strip and second sealing strip.
Preferably, the opposite sides of the first sealing strip and the second sealing strip are fixedly provided with sealing convex ribs, and the two sides of the third sealing strip are provided with sealing grooves matched with the sealing convex ribs.
Preferably, the cross section of the sealing convex rib and the cross section of the sealing groove are both semicircular structures.
Preferably, a relief groove is formed in the top of the third sealing strip.
Preferably, the side of the first sealing strip, which is away from the second sealing strip, is provided with an arc-shaped surface.
Preferably, an integrated forming device is adopted between the upper sealing ring and the first sealing strip and between the upper sealing ring and the second sealing strip, and an integrated forming device is adopted between the lower sealing ring and the third sealing strip.
Compared with the prior art, the utility model provides the metal sealing gasket of the aero-engine, which has the following beneficial effects:
1. this aeroengine metal seal fills up, through first sealing strip, second sealing strip and the third sealing strip that is equipped with, the third sealing strip can insert between first sealing strip and second sealing strip, can play sealed effect between upper seal circle and the lower sealing circle.
2. This aeroengine metal seal fills up, through the sealed protruding muscle that is equipped with, seal groove and the groove of yielding, when the third sealing strip inserts in the inside of first sealing strip and second sealing strip for the both sides of third sealing strip are through yielding groove extrusion deformation, thereby make sealed protruding muscle and seal groove cooperate, increase the leakproofness between first sealing strip, second sealing strip and the third sealing strip.
The device does not involve the part and all is the same with prior art or can adopt prior art to realize, the utility model discloses a dual seal's structure for sealing connection between upper seal circle and the lower seal circle, thereby improved the sealed effect to aeroengine.
Drawings
FIG. 1 is a schematic structural view of an aircraft engine metal gasket according to the present utility model;
FIG. 2 is an enlarged view of the portion A of FIG. 1;
fig. 3 is a top view of the third sealing strip of fig. 2.
In the figure: 1. an upper sealing ring; 2. a lower sealing ring; 3. a first sealing strip; 4. a second sealing strip; 5. a third sealing strip; 6. sealing the convex ribs; 7. sealing the groove; 8. a back-off groove.
Detailed Description
The following description of the embodiments of the present utility model will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present utility model, but not all embodiments.
Example 1
Referring to fig. 1-2, an aeroengine metal gasket comprises an upper sealing ring 1 and a lower sealing ring 2, wherein a first sealing strip 3 and a second sealing strip 4 are respectively and fixedly arranged at the bottom of the upper sealing ring 1, one sides, deviating from each other, of the first sealing strip 3 and the second sealing strip 4 are all provided with arc surfaces, a third sealing strip 5 is fixedly arranged at the top of the lower sealing ring 2, the third sealing strip 5 is inserted and arranged between the first sealing strip 3 and the second sealing strip 4, and an integrated forming arrangement is adopted between the upper sealing ring 1 and the first sealing strip 3 and the second sealing strip 4.
Adopt integrated into one piece to set up between lower sealing washer 2 and the third sealing strip 5, third sealing strip 5 can insert between first sealing strip 3 and second sealing strip 4, can play sealed effect between upper sealing washer 1 and lower sealing washer 2.
Example 2
Referring to fig. 2-3, a sealing convex rib 6 is fixedly arranged on one side of the first sealing strip 3 opposite to the second sealing strip 4, sealing grooves 7 matched with the sealing convex rib 6 are formed on two sides of the third sealing strip 5, the cross section of the sealing convex rib 6 and the cross section of the sealing grooves 7 are of semicircular structures, and a relief groove 8 is formed in the top of the third sealing strip 5.
When the third sealing strip is inserted 5 into the first sealing strip 3 and the second sealing strip 4, the two sides of the third sealing strip 5 are extruded and deformed through the yielding grooves 8, so that the sealing convex ribs 6 are matched with the sealing grooves 7, and the tightness among the first sealing strip 3, the second sealing strip 4 and the third sealing strip 5 is improved.
The foregoing is only a preferred embodiment of the present utility model, but the scope of the present utility model is not limited thereto, and any person skilled in the art, who is within the scope of the present utility model, should make equivalent substitutions or modifications according to the technical scheme of the present utility model and the inventive concept thereof, and should be covered by the scope of the present utility model.
Claims (6)
1. The utility model provides an aeroengine metal seal fills up, includes upper seal circle (1) and lower sealing circle (2), its characterized in that: the bottom of last sealing washer (1) is fixed respectively and is equipped with first sealing strip (3) and second sealing strip (4), the top of lower sealing washer (2) is fixed and is equipped with third sealing strip (5), third sealing strip (5) peg graft and set up between first sealing strip (3) and second sealing strip (4).
2. An aircraft engine metal gasket according to claim 1, wherein: sealing convex ribs (6) are fixedly arranged on one side, opposite to the first sealing strip (3) and the second sealing strip (4), of each of the two sides of the third sealing strip (5), and sealing grooves (7) matched with the sealing convex ribs (6) are formed in the two sides of the third sealing strip.
3. An aircraft engine metal gasket according to claim 2, wherein: the cross section of the sealing convex rib (6) and the cross section of the sealing groove (7) are both semicircular structures.
4. An aircraft engine metal gasket according to claim 1, wherein: and a back-off groove (8) is formed in the top of the third sealing strip (5).
5. An aircraft engine metal gasket according to claim 1, wherein: one side, which is away from the first sealing strip (3) and the second sealing strip (4), is provided with an arc-shaped surface.
6. An aircraft engine metal gasket according to claim 1, wherein: the upper sealing ring (1) is integrally formed with the first sealing strip (3) and the second sealing strip (4), and the lower sealing ring (2) is integrally formed with the third sealing strip (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321349038.0U CN219866230U (en) | 2023-05-31 | 2023-05-31 | Aeroengine metal sealing gasket |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321349038.0U CN219866230U (en) | 2023-05-31 | 2023-05-31 | Aeroengine metal sealing gasket |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN219866230U true CN219866230U (en) | 2023-10-20 |
Family
ID=88331373
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202321349038.0U Active CN219866230U (en) | 2023-05-31 | 2023-05-31 | Aeroengine metal sealing gasket |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN219866230U (en) |
-
2023
- 2023-05-31 CN CN202321349038.0U patent/CN219866230U/en active Active
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |