CN219197496U - Inner cone structure of sectional jet engine exhaust device - Google Patents
Inner cone structure of sectional jet engine exhaust device Download PDFInfo
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- CN219197496U CN219197496U CN202320167660.3U CN202320167660U CN219197496U CN 219197496 U CN219197496 U CN 219197496U CN 202320167660 U CN202320167660 U CN 202320167660U CN 219197496 U CN219197496 U CN 219197496U
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- cone
- inner cone
- jet engine
- engine exhaust
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Abstract
The utility model provides an inner cone structure of a sectional jet engine exhaust device, which comprises an inner cone front section and an inner cone rear section connected with the inner cone front section; the bottom end face of the front section of the inner cone is connected with a mounting edge, and the top end face of the rear section of the inner cone is connected with a cone bottom; the surface circumference of interior awl anterior segment has seted up a plurality of equalizing holes, has seted up the mounting hole on the lateral wall that interior awl anterior segment is close to the top. The utility model is simple and reliable, has better strength and rigidity, better manufacturability, easy assembly, low cost and strong practicability, and can obtain the inner cone with better structural strength and performance by a simple processing mode.
Description
Technical Field
The utility model relates to an inner cone structure of a sectional jet engine exhaust device, and belongs to the field of structural design of aeroengine exhaust devices.
Background
The inner cone is an integral part of the exhaust device of the jet engine, and has the functions of rectifying, diffusing and decelerating the flow of the gas after the turbine. The existing inner cone can be divided into a sectional type and an integral type, and the sectional type inner cone is axially backwards divided into a plurality of sections from the rear mounting edge of the turbine support and is connected in a welding mode; the integral inner cone integrally forms the mounting edge and the rear cone portion into a single inner cone.
According to the design requirement of the exhaust device, the inner cone body is designed longer under partial conditions, and the structural weight is required to be lighter, so that the strength and thickness control of the inner cone body are required to be more severely; meanwhile, the integral inner cone has higher requirements on the processing and forming process method, and the one-step forming quality is lower.
Disclosure of Invention
In order to solve the technical problems, the utility model provides an inner cone structure of a sectional type jet engine exhaust device, which has simple and reliable structure, simple component parts and wide application, and is particularly suitable for the exhaust device with the inner cone with a larger axial length.
The utility model is realized by the following technical scheme.
The utility model provides an inner cone structure of a sectional jet engine exhaust device, which comprises an inner cone front section and an inner cone rear section connected with the inner cone front section; the bottom end face of the front section of the inner cone is connected with a mounting edge, and the top end face of the rear section of the inner cone is connected with a cone bottom; the surface circumference of interior awl anterior segment has seted up a plurality of equalizing holes, has seted up the mounting hole on the lateral wall that interior awl anterior segment is close to the top.
The front section of the inner cone is connected with the rear section of the inner cone into a whole through a strap and a bolt.
A plurality of mounting holes are axially distributed on the mounting edge, and screws are arranged in the mounting holes.
The cone bottom is connected with the rear section of the inner cone through welding, and the installation edge is connected with the front section of the inner cone through welding.
The cone bottom is one of a pointed cone, a cone and a truncated cone.
The front hoop is shaped like a Chinese character 'ji', and the front end of the rear hoop is provided with a seat; the front strap is welded on the inner wall of the front section of the inner cone, and the rear strap is welded on the inner wall of the rear section of the inner cone.
The surface of front strap has all been seted up the connecting hole, and the connecting hole has all been seted up on the surface of seat.
The connecting hole of the front strap is matched with the connecting hole of the seat to jointly form a bolt hole for placing a bolt.
The utility model has the beneficial effects that: the inner cone is simple and reliable, good in strength and rigidity, good in manufacturability, easy to assemble, low in cost and high in practicability, and the inner cone with excellent structural strength and performance can be obtained through a simple processing mode.
Drawings
FIG. 1 is a schematic diagram of the structure of the present utility model;
FIG. 2 is an enlarged view at A in FIG. 1;
FIG. 3 is an enlarged view at B in FIG. 1;
in the figure: 1-mounting edge, 2-inner cone front section, 3-equalizing hole, 4-mounting hole, 5-inner cone rear section, 6-cone bottom, 7-screw, 8-front strap, 9-back strap, 10-bolt and 11-seat.
Detailed Description
The technical solution of the present utility model is further described below, but the scope of the claimed utility model is not limited to the above.
An inner cone structure of a sectional jet engine exhaust device as shown in fig. 1-3 comprises an inner cone front section 2 and an inner cone rear section 5 connected with the inner cone front section 2; the bottom end face of the inner cone front section 2 is connected with a mounting edge 1, and the top end face of the inner cone rear section 5 is connected with a cone bottom 6; the surface circumference of the inner cone front section 2 is provided with a plurality of pressure equalizing holes 3, and the side wall of the inner cone front section 2 close to the top is provided with a mounting hole 4.
The front section 2 of the inner cone and the rear section 5 of the inner cone are connected into a whole through a strap and a bolt 10.
A plurality of mounting holes 4 are axially distributed on the mounting edge 1, and screws 7 are arranged in the mounting holes 4.
The cone bottom 6 is connected with the inner cone rear section 5 through welding, and the installation edge 1 is connected with the inner cone front section 2 through welding.
The cone bottom 6 is one of a pointed cone, a cone and a truncated cone.
The band is divided into a front band 8 and a rear band 9, the front band 8 is shaped like a Chinese character 'ji', and the front end of the rear band 9 is provided with a seat 11; the front strap 8 is welded on the inner wall of the front section 2 of the inner cone, and the rear strap 9 is welded on the inner wall of the rear section 5 of the inner cone.
The surface of the front strap 8 is provided with connecting holes, and the surface of the seat 11 is provided with connecting holes.
The connecting holes of the front strap 8 are matched with the connecting holes of the seat 11 to jointly form a bolt hole for placing the bolt 10.
Furthermore, the pressure equalizing hole 3 is communicated with the inner cavity of the cone and the turbine after-combustion gas flow passage, so that the adverse effect on the strength of the inner cone caused by dead space formed in the inner cavity of the inner cone is avoided
Further, the front band 8 and the rear band 9 are connected by bolts 10, thereby achieving the purpose of connecting the inner cone front section 2 and the inner cone rear section 5.
Further, the mounting edge 1 is connected to the turbine support by means of screws 7, forming an inner cone of the installed state of the engine.
The utility model comprises the following steps:
1. the parts and the connecting pieces are processed by adopting the traditional machining, sheet metal machining, additive manufacturing or composite material and forming technologies according to the design requirements, and the mounting holes 4 and the connecting holes are processed in advance.
2. The front section 2 of the inner cone is respectively welded and connected with the mounting edge 1 and the front strap 8, the rear section 5 of the inner cone is respectively welded and connected with the rear strap 9 and the cone bottom 6, and the front section and the rear section of the inner cone are connected into a whole through the bolts 10.
3. The inner cone connected into a whole is assembled to the turbine support through the screw 7 to form the inner cone in the installed state of the engine.
Claims (8)
1. The utility model provides a sectional type jet engine exhaust's interior cone structure, includes interior cone anterior segment (2) and interior cone back end (5) of being connected with interior cone anterior segment (2), its characterized in that: the bottom end face of the inner cone front section (2) is connected with a mounting edge (1), and the top end face of the inner cone rear section (5) is connected with a cone bottom (6); the surface circumference of the inner cone front section (2) is provided with a plurality of pressure equalizing holes (3), and the side wall of the inner cone front section (2) close to the top is provided with a mounting hole (4).
2. The internal cone structure of a segmented jet engine exhaust as set forth in claim 1, wherein: the front section (2) of the inner cone is connected with the rear section (5) of the inner cone into a whole through a strap and a bolt (10).
3. The internal cone structure of a segmented jet engine exhaust as set forth in claim 1, wherein: a plurality of mounting holes (4) are axially distributed on the mounting edge (1), and screws (7) are arranged in the mounting holes (4).
4. The internal cone structure of a segmented jet engine exhaust as set forth in claim 1, wherein: the cone bottom (6) is connected with the rear section (5) of the inner cone through welding, and the mounting edge (1) is connected with the front section (2) of the inner cone through welding.
5. The internal cone structure of a segmented jet engine exhaust as set forth in claim 1, wherein: the cone bottom (6) is one of a pointed cone, a cone and a truncated cone.
6. The internal cone structure of a segmented jet engine exhaust as set forth in claim 2, wherein: the band is divided into a front band (8) and a rear band (9), the front band (8) is shaped like a Chinese character 'ji', and the front end of the rear band (9) is provided with a seat (11); the front hoop (8) is welded on the inner wall of the front section (2) of the inner cone, and the rear hoop (9) is welded on the inner wall of the rear section (5) of the inner cone.
7. The internal cone structure of a segmented jet engine exhaust as set forth in claim 6, wherein: the surface of the front strap (8) is provided with connecting holes, and the surface of the seat (11) is provided with connecting holes.
8. The internal cone structure of a segmented jet engine exhaust as set forth in claim 7, wherein: the connecting holes of the front strap (8) are matched with the connecting holes of the seat (11) to jointly form a bolt hole for placing a bolt (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320167660.3U CN219197496U (en) | 2023-02-09 | 2023-02-09 | Inner cone structure of sectional jet engine exhaust device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320167660.3U CN219197496U (en) | 2023-02-09 | 2023-02-09 | Inner cone structure of sectional jet engine exhaust device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN219197496U true CN219197496U (en) | 2023-06-16 |
Family
ID=86703768
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202320167660.3U Active CN219197496U (en) | 2023-02-09 | 2023-02-09 | Inner cone structure of sectional jet engine exhaust device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN219197496U (en) |
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2023
- 2023-02-09 CN CN202320167660.3U patent/CN219197496U/en active Active
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