CN108087148A - A kind of infrared stealth jet pipe and with its aircraft - Google Patents
A kind of infrared stealth jet pipe and with its aircraft Download PDFInfo
- Publication number
- CN108087148A CN108087148A CN201711309973.3A CN201711309973A CN108087148A CN 108087148 A CN108087148 A CN 108087148A CN 201711309973 A CN201711309973 A CN 201711309973A CN 108087148 A CN108087148 A CN 108087148A
- Authority
- CN
- China
- Prior art keywords
- wall
- jet pipe
- section
- raised
- infrared stealth
- 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.)
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
Abstract
The invention discloses a kind of infrared stealth jet pipe and with its aircraft.The infrared stealth jet pipe includes first segment and the rectification section being connected with the first segment；Wherein, the first segment includes the first wall, second wall opposite with first wall, the 3rd wall and fourth wall opposite with the 3rd wall；Second wall is to the first wall direction protrusion, so as to form raised section；First is formed between the raised section and the 3rd wall and expands passage；Second is formed between the raised section and the 4th wall and expands passage.The aeroperformance of the infrared stealth jet pipe jet pipe of the application is better than S bending nozzles, and on the premise of can ensureing that hot-end component effectively blocks, reduces jet pipe offset distance, be conducive to body integrated design after aircraft.It can reduce jet pipe offset distance while ensureing that hot-end component effectively blocks, be conducive to body integrated design after aircraft, and improve jet pipe aeroperformance.
Description
Technical field
The present invention relates to spray bar technology field, more particularly to a kind of infrared stealth jet pipe and with its aircraft.
Background technology
Exhaust system is the most important source of infrared radiation of aircraft, and infra-red radiation is mainly derived from tail jet and jet pipe heat
Cavity, generally can be by blocking to reduce its infrared intensity to exhaust system high-temperature component, and S bending nozzles are typically to spray
The hot cavity of pipe blocks technology, and jet pipe center line is double S type curves, and center line, there are certain offset distance, passes through the 1st with turbine axis
A curved passages of S make the off-center axis of combustion gas, using the 2nd curved passage of S combustion gas are made to return to axial location, and then by turbine leaf
The high-temperature components such as piece and center cone are effectively blocked, so as to reduce infra-red radiation.
But the elastic line feature of jet pipe causes jet pipe offset distance larger, and body integrated design is difficult after increasing aircraft
Degree, and elastic line feature can increase the performance loss of jet pipe.
Thus, it is desirable to have a kind of technical solution is come at least one drawbacks described above for overcoming or at least mitigating the prior art.
The content of the invention
It is an object of the invention to provide a kind of infrared stealth jet pipe come overcome or at least mitigate the prior art at least one
A drawbacks described above.
To achieve the above object, the present invention provides a kind of infrared stealth jet pipe, and the infrared stealth jet pipe includes first segment 6
And the rectification section being connected with the first segment；Wherein,
The first segment include the first wall, second wall opposite with first wall, the 3rd wall and with the 3rd wall
The 4th opposite wall；
Second wall is to the first wall direction protrusion, so as to form raised section；
First is formed between the raised section and the 3rd wall and expands passage；Between the raised section and the 4th wall
It forms second and expands passage.
Preferably, one end of the rectification section is connected with one end of the first segment；
The end face of the other end of the rectification section is nozzle exit section.
Preferably, the raised maximum position of the raised section to the wall surface space of the first wall is known as raised pole space, institute
State the inlet diameter that the distance of raised pole space in a first direction is not less than jet pipe.
Preferably, the raised maximum position of the raised section is the maximum position of the raised section in a first direction.
Present invention also provides a kind of aircraft, the aircraft includes infrared stealth jet pipe as described above.
The aeroperformance of the infrared stealth jet pipe jet pipe of the application is better than S bending nozzles, and can ensure that hot-end component effectively hides
On the premise of gear, reduce jet pipe offset distance, be conducive to body integrated design after aircraft.It can ensure what hot-end component effectively blocked
Meanwhile reduce jet pipe offset distance, be conducive to body integrated design after aircraft, and improve jet pipe aeroperformance.
Description of the drawings
Fig. 1 is the structure diagram of the infrared stealth jet pipe of the application first embodiment.
Fig. 2 is another structure diagram of infrared stealth jet pipe shown in FIG. 1.
Fig. 3 is another structure diagram of infrared stealth jet pipe shown in FIG. 1.
Fig. 4 is another structure diagram of infrared stealth jet pipe shown in FIG. 1.
Fig. 5 is another structure diagram of infrared stealth jet pipe shown in FIG. 1.
Reference numeral：
| 1 | First segment | 13 | 3rd wall |
| 2 | Rectification section | 14 | 4th wall |
| 11 | First wall | 121 | Raised section |
| 12 | Second wall | 141 | Second expands passage |
| 131 | First expands passage | 21 | Nozzle exit section |
| 3 | Raised pole space |
Specific embodiment
To make the purpose, technical scheme and advantage that the present invention is implemented clearer, below in conjunction in the embodiment of the present invention
Attached drawing, the technical solution in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label represent same or similar element or there is same or like element.Described embodiment is the present invention
Part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to use
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiments of the present invention, ordinary skill people
Member's all other embodiments obtained without creative efforts, belong to the scope of protection of the invention.Under
Face is described in detail the embodiment of the present invention with reference to attached drawing.
In the description of the present invention, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instructions such as "left", "right", " vertical ", " level ", " top ", " bottom " " interior ", " outer " is based on attached drawing institutes
The orientation or position relationship shown is for only for ease of the description present invention and simplifies description rather than instruction or imply signified dress
It puts or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that the present invention is protected
The limitation of scope.
Fig. 1 is the structure diagram of the infrared stealth jet pipe of the application first embodiment.Fig. 2 is shown in FIG. 1 infrared hidden
Another structure diagram of body jet pipe.Fig. 3 is another structure diagram of infrared stealth jet pipe shown in FIG. 1.Fig. 4 is Fig. 1 institutes
Another structure diagram of the infrared stealth jet pipe shown.
In the present embodiment, first direction is the B directions shown in Fig. 4.
Infrared stealth jet pipe as shown in Figures 1 to 4 includes first segment 1 and the rectification section 2 being connected with first segment 1；Its
In,
First segment 1 include the first wall 11, second wall 12 opposite with first wall 11, the 3rd wall 13 and with the 3rd wall
13 the 4th opposite walls 14；
Second wall 12 is to the first wall direction protrusion, so as to form raised section 121；
First is formed between 121 and the 3rd wall 13 of raised section and expands passage 131；Shape between 121 and the 4th wall 14 of raised section
Expand passage 141 into second.
The aeroperformance of the infrared stealth jet pipe jet pipe of the application is better than S bending nozzles, and can ensure that hot-end component effectively hides
On the premise of gear, reduce jet pipe offset distance, be conducive to body integrated design after aircraft.It can ensure what hot-end component effectively blocked
Meanwhile reduce jet pipe offset distance, be conducive to body integrated design after aircraft, and improve jet pipe aeroperformance.
Referring to Fig. 3, in the present embodiment, one end of rectification section 2 is connected with one end of first segment 1；
The end face of the other end of rectification section 2 is nozzle exit section 21.
Referring to Fig. 3, in the present embodiment, raised maximum position to the wall surface space of the first wall of raised section is known as raised pole
The space of points 3, the distance of raised pole space 3 in a first direction are not less than the inlet diameter of jet pipe.
Referring to Fig. 3, in the present embodiment, the raised maximum position of the raised section for the raised section in a first direction
Maximum position.
Referring to Fig. 1 to Fig. 4,121 length of raised section is L1, jet pipe width be more than raised section width, that is, W >=B (B in Fig. 4,
W in Fig. 5)；
The height and width of raised section at raised pole space 3 reach maximum, and the raised section maximum width at this is not small
In nozzle inlet diameter, i.e. B >=D (D in the B in Fig. 4, Fig. 2), the area of raised pole space 3 is about nozzle inlet area
80~90%；
Referring to Fig. 3, raised section 121 is tilted to rectification section direction to be extended, and the part of the extension becomes descending branch, the length of this section
It spends for L2, the height and width of this section of raised section are gradually decrease to 0 vertically, and aisle spare is gradually reduced vertically；
Referring to Fig. 3, the axis of rectification section 2 is parallel with turbine outlet axis, length L3；
Referring to Fig. 4, the first wall surface of raised pole space is arch, and the second wall surface is in same with nozzle inlet minimum point
Horizontal line, nozzle exit section 21 has larger the ratio of width to height, to increase the shielding rate of the hot cavity of jet pipe.
The infrared stealth jet pipe of the application is compared with S bending nozzles, it is ensured that while hot-end component effectively blocks, reduces spray
Pipe offset distance, and improve jet pipe aeroperformance.Gradually increase forms convex closure to the lower wall surface height and width of raised section vertically
Raised pole space, the convex closure maximum width of raised pole space are more than nozzle inlet diameter, to ensure to have hot-end component
Effect is blocked, and the first wall surface of raised pole space is close with the convex hull shape of raised pole space, and nozzle exit section 21 has
There is larger the ratio of width to height, raised pole space can increase shielding rate with 21 collective effect of nozzle exit section, so as to ensure hot junction
While component occlusion effect, the nozzle structure design of big offset distance is avoided.Jet pipe both sides outside wall surface wraps up convex closure, a part
Air-flow can expand passage by the second of convex closure both sides and the first expansion passage flows to nozzle exit, increases section type face 2
Circulation area, so as to reducing flowing velocity of the air-flow in raised section, relative reduction flow losses of the air-flow in raised section 1,
Rectification section 2 adjusts the flow direction of air-flow to close to axially, reduces the performance loss of jet pipe as far as possible.
Present invention also provides a kind of aircraft, the aircraft includes infrared stealth jet pipe as described above.
It is last it is to be noted that：The above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations.To the greatest extent
Pipe is with reference to the foregoing embodiments described in detail the present invention, it will be understood by those of ordinary skill in the art that：It is still
It can modify to the technical solution recorded in foregoing embodiments or which part technical characteristic is equally replaced
It changes；And these modifications or replacement, the essence of appropriate technical solution is not made to depart from the essence of various embodiments of the present invention technical solution
God and scope.
Claims (5)
1. a kind of infrared stealth jet pipe, which is characterized in that the infrared stealth jet pipe includes first segment (1) and with described first
The rectification section (2) of section (1) connection；Wherein,
The first segment (1) include the first wall (11), with opposite the second wall (12) of first wall (11), the 3rd wall (13) with
And fourth wall (14) opposite with the 3rd wall (13)；
Second wall (12) is to the first wall direction protrusion, so as to form raised section (121)；
First is formed between the raised section (121) and the 3rd wall (13) and expands passage (131)；The raised section (121)
Second is formed between the 4th wall (14) and expands passage (141).
2. infrared stealth jet pipe as described in claim 1, which is characterized in that one end and described first of the rectification section (2)
One end connection of section (1)；
The end face of the other end of the rectification section (2) is nozzle exit section (21).
3. infrared stealth jet pipe as claimed in claim 2, which is characterized in that the raised maximum position of the raised section to first
The wall surface space of wall is known as raised pole space (3), and the distance of the protrusion pole space (3) in a first direction is not less than jet pipe
Inlet diameter.
4. infrared stealth jet pipe as claimed in claim 3, which is characterized in that the raised maximum position of the raised section is described
The maximum position of raised section in a first direction.
5. a kind of aircraft, which is characterized in that the aircraft includes the infrared stealth as described in any one in Claims 1-4
Jet pipe.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711309973.3A CN108087148A (en) | 2017-12-11 | 2017-12-11 | A kind of infrared stealth jet pipe and with its aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711309973.3A CN108087148A (en) | 2017-12-11 | 2017-12-11 | A kind of infrared stealth jet pipe and with its aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108087148A true CN108087148A (en) | 2018-05-29 |
Family
ID=62174653
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711309973.3A Pending CN108087148A (en) | 2017-12-11 | 2017-12-11 | A kind of infrared stealth jet pipe and with its aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108087148A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112455699A (en) * | 2020-11-13 | 2021-03-09 | 中国航空工业集团公司沈阳飞机设计研究所 | High fusion aircraft afterbody |
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| US4018046A (en) * | 1975-07-17 | 1977-04-19 | Avco Corporation | Infrared radiation suppressor for gas turbine engine |
| US4864819A (en) * | 1985-06-03 | 1989-09-12 | General Electric Company | Exhaust system including protective arrangements |
| US5483793A (en) * | 1970-09-02 | 1996-01-16 | General Electric Company | Infrared radiation suppression device |
| EP1849983A1 (en) * | 2006-04-28 | 2007-10-31 | Snecma | Elbow-shaped propelling gas exhaust assembly in an aircraft |
| EP1849985A1 (en) * | 2006-04-28 | 2007-10-31 | Snecma | Twisted elbow-shaped propelling gas exhaust assembly in an aircraft |
| CN102926888A (en) * | 2012-11-16 | 2013-02-13 | 中国航空工业集团公司西安飞机设计研究所 | Stealth exhaust system |
| US20130104557A1 (en) * | 2011-10-28 | 2013-05-02 | Shawn M. McMahon | Gas turbine engine cooling valve |
| CN104033280A (en) * | 2014-06-06 | 2014-09-10 | 中国航空工业集团公司沈阳发动机设计研究所 | Binary vector spraying pipe capable of realizing S-bent shading function |
| CN105114206A (en) * | 2015-09-18 | 2015-12-02 | 中国航空工业集团公司沈阳发动机设计研究所 | Jet pipe capable of reducing features of infrared signals and radar signals |
| CN105370437A (en) * | 2014-08-25 | 2016-03-02 | 中国航空工业集团公司沈阳发动机设计研究所 | Contracting nozzle with excellent invisibility function |
| CN106014686A (en) * | 2016-05-30 | 2016-10-12 | 西北工业大学 | S-shaped spray pipe structure for turbofan engine |
| CN106894917A (en) * | 2017-02-17 | 2017-06-27 | 南京航空航天大学 | Double outlet S bending nozzles and its control method of a kind of low-infrared radiation signal |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US5483793A (en) * | 1970-09-02 | 1996-01-16 | General Electric Company | Infrared radiation suppression device |
| US4018046A (en) * | 1975-07-17 | 1977-04-19 | Avco Corporation | Infrared radiation suppressor for gas turbine engine |
| US4864819A (en) * | 1985-06-03 | 1989-09-12 | General Electric Company | Exhaust system including protective arrangements |
| EP1849983A1 (en) * | 2006-04-28 | 2007-10-31 | Snecma | Elbow-shaped propelling gas exhaust assembly in an aircraft |
| EP1849985A1 (en) * | 2006-04-28 | 2007-10-31 | Snecma | Twisted elbow-shaped propelling gas exhaust assembly in an aircraft |
| US20130104557A1 (en) * | 2011-10-28 | 2013-05-02 | Shawn M. McMahon | Gas turbine engine cooling valve |
| CN102926888A (en) * | 2012-11-16 | 2013-02-13 | 中国航空工业集团公司西安飞机设计研究所 | Stealth exhaust system |
| CN104033280A (en) * | 2014-06-06 | 2014-09-10 | 中国航空工业集团公司沈阳发动机设计研究所 | Binary vector spraying pipe capable of realizing S-bent shading function |
| CN105370437A (en) * | 2014-08-25 | 2016-03-02 | 中国航空工业集团公司沈阳发动机设计研究所 | Contracting nozzle with excellent invisibility function |
| CN105114206A (en) * | 2015-09-18 | 2015-12-02 | 中国航空工业集团公司沈阳发动机设计研究所 | Jet pipe capable of reducing features of infrared signals and radar signals |
| CN106014686A (en) * | 2016-05-30 | 2016-10-12 | 西北工业大学 | S-shaped spray pipe structure for turbofan engine |
| CN106894917A (en) * | 2017-02-17 | 2017-06-27 | 南京航空航天大学 | Double outlet S bending nozzles and its control method of a kind of low-infrared radiation signal |
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| 中国人民解放军总装备部均是训练教材编辑工作委员会: "《高低速风洞气动与结构设计》", 30 April 2003, 国防工业出版社 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112455699A (en) * | 2020-11-13 | 2021-03-09 | 中国航空工业集团公司沈阳飞机设计研究所 | High fusion aircraft afterbody |
| CN112455699B (en) * | 2020-11-13 | 2024-01-02 | 中国航空工业集团公司沈阳飞机设计研究所 | High-fusion aircraft rear body |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20180529 |
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| RJ01 | Rejection of invention patent application after publication |