CN204511701U - A kind of aeroengine flap - Google Patents
A kind of aeroengine flap Download PDFInfo
- Publication number
- CN204511701U CN204511701U CN201520023187.7U CN201520023187U CN204511701U CN 204511701 U CN204511701 U CN 204511701U CN 201520023187 U CN201520023187 U CN 201520023187U CN 204511701 U CN204511701 U CN 204511701U
- Authority
- CN
- China
- Prior art keywords
- rotating shaft
- aeroengine
- flap
- horizontal baffle
- jet pipe
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Abstract
A kind of aeroengine flap, is characterized in that: described aeroengine flap, comprises lateral retaining plate, horizontal baffle, rotating shaft; Wherein: rotating shaft is arranged on the outlet port of jet pipe; Horizontal baffle and rotating shaft weld together; The global shape of lateral retaining plate is approximately sector structure, is connected, mutually in vertical direction by welding with horizontal baffle.Advantage of the present utility model: aeroengine flap described in the utility model, practical, of many uses, Be very effective, when ensureing jet pipe deflection vector and receiving expansion, realizes the raising to space availability ratio.
Description
Technical field
The utility model relates to aeroengine Nozzle Design field, particularly a kind of aeroengine flap.
Background technique
The receipts that engine jet pipe not only will realize jet pipe expand, and also will realize deflection vector.And typical dual vector jet pipe is when realizing these functions, in the adjustable offset rotation mechanism utilized, adjustment sheet is separated with baffle plate, and wherein adjustment sheet motion, baffle plate is fixed, and occupies unnecessary space.
Model utility content
The purpose of this utility model is mainly for dual vector jet pipe, and when ensureing jet pipe deflection vector and receiving expansion, realize the raising to space availability ratio, spy provides a kind of aeroengine flap.
The utility model provides a kind of aeroengine flap, it is characterized in that: described aeroengine flap, comprises lateral retaining plate 1, horizontal baffle 2, rotating shaft 3;
Wherein: rotating shaft 3 is arranged on the outlet port of jet pipe; Horizontal baffle 2 and rotating shaft weld together; The global shape of lateral retaining plate 1 is approximately sector structure, is connected, mutually in vertical direction by welding with horizontal baffle.
Described rotating shaft 3 is arranged on outside nozzle, and the length of rotating shaft 3 is equal to the long edge lengths of jet pipe rectangular outlet.
The long limit of described horizontal baffle 2 is identical with rotating shaft 3 length.
For a jet pipe, the rotating shaft quantity of needs is 2, and the quantity of horizontal baffle is 2, and the quantity of lateral retaining plate is 4
Receive at guarantee jet pipe and expand and in deflection vector merit can completely situation, adjustment sheet and baffle plate can be moved in jet pipe, fully improves space availability ratio.
Adjustment sheet is arranged on the outlet of two-dimensional nozzle, and the pressurized strut of jet pipe, by the rotating shaft of rocking bar regulating and controlling sheet, makes adjustment sheet can move around the shaft under the effect of pressurized strut.Because lateral retaining plate is welded on horizontal baffle, therefore both can move together.When pressurized strut regulating and controlling sheet moves, horizontal baffle moves together with lateral retaining plate, completes contraction, expansion, yaw motion.When adjustment sheet inwardly shrinks, due to two dislocation of lateral retaining plate on horizontal baffle, two lateral retaining plates are different to the distance at horizontal baffle edge, the lateral retaining plate of two adjustment sheets can be hung together, achieve the raising of space availability ratio.
Advantage of the present utility model:
Aeroengine flap described in the utility model, practical, of many uses, Be very effective, when ensureing jet pipe deflection vector and receiving expansion, realizes the raising to space availability ratio.
Accompanying drawing explanation
Below in conjunction with drawings and the embodiments, the utility model is described in further detail:
Fig. 1 is aeroengine flap structural representation;
Fig. 2 is the scheme of installation of aeroengine flap adjustment sheet on jet pipe;
In figure, 1 is lateral retaining plate, and 2 is horizontal baffle, and 3 is rotating shaft, and 4 is rocking bar, and 5 is flat segments, and 6 is mounting edge, and 7 is fitting seat, and 8 is pressurized strut, and 9 is baffle plate.
Embodiment
Embodiment 1
Present embodiments provide a kind of aeroengine flap, it is characterized in that: described aeroengine flap, comprise lateral retaining plate 1, horizontal baffle 2, rotating shaft 3;
Wherein: rotating shaft 3 is arranged on the outlet port of jet pipe; Horizontal baffle 2 and rotating shaft weld together; The global shape of lateral retaining plate 1 is approximately sector structure, is connected, mutually in vertical direction by welding with horizontal baffle.
Described rotating shaft 3 is arranged on outside nozzle, and the length of rotating shaft 3 is equal to the long edge lengths of jet pipe rectangular outlet.
The long limit of described horizontal baffle 2 is identical with rotating shaft 3 length.
For a jet pipe, the rotating shaft quantity of needs is 2, and the quantity of horizontal baffle is 2, and the quantity of lateral retaining plate is 4
Receive at guarantee jet pipe and expand and in deflection vector merit can completely situation, adjustment sheet and baffle plate can be moved in jet pipe, fully improves space availability ratio.
Adjustment sheet is arranged on the outlet of two-dimensional nozzle, and the pressurized strut of jet pipe, by the rotating shaft of rocking bar regulating and controlling sheet, makes adjustment sheet can move around the shaft under the effect of pressurized strut.Because lateral retaining plate is welded on horizontal baffle, therefore both can move together.When pressurized strut regulating and controlling sheet moves, horizontal baffle moves together with lateral retaining plate, completes contraction, expansion, yaw motion.When adjustment sheet inwardly shrinks, due to two dislocation of lateral retaining plate on horizontal baffle, two lateral retaining plates are different to the distance at horizontal baffle edge, the lateral retaining plate of two adjustment sheets can be hung together, achieve the raising of space availability ratio.
Claims (3)
1. an aeroengine flap, is characterized in that: described aeroengine flap, comprises lateral retaining plate (1), horizontal baffle (2), rotating shaft (3);
Wherein: rotating shaft (3) is arranged on the outlet port of jet pipe; Horizontal baffle (2) and rotating shaft weld together; The global shape of lateral retaining plate (1) is approximately sector structure, is connected, mutually in vertical direction by welding with horizontal baffle.
2. according to aeroengine flap according to claim 1, it is characterized in that: described rotating shaft (3) is arranged on outside nozzle, the length of rotating shaft (3) is equal to the long edge lengths of jet pipe rectangular outlet.
3. according to aeroengine flap according to claim 1, it is characterized in that: the long limit of described horizontal baffle (2) is identical with rotating shaft (3) length.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520023187.7U CN204511701U (en) | 2015-01-13 | 2015-01-13 | A kind of aeroengine flap |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520023187.7U CN204511701U (en) | 2015-01-13 | 2015-01-13 | A kind of aeroengine flap |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204511701U true CN204511701U (en) | 2015-07-29 |
Family
ID=53709687
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520023187.7U Expired - Fee Related CN204511701U (en) | 2015-01-13 | 2015-01-13 | A kind of aeroengine flap |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204511701U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112943481A (en) * | 2021-02-11 | 2021-06-11 | 西北工业大学 | Mechanical adjustable S-shaped spray pipe nozzle structure |
-
2015
- 2015-01-13 CN CN201520023187.7U patent/CN204511701U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112943481A (en) * | 2021-02-11 | 2021-06-11 | 西北工业大学 | Mechanical adjustable S-shaped spray pipe nozzle structure |
| CN112943481B (en) * | 2021-02-11 | 2022-08-05 | 西北工业大学 | Mechanical adjustable S-shaped spray pipe nozzle structure |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150729 Termination date: 20220113 |