CN106762219B - A kind of new-type binary plug nozzle - Google Patents
A kind of new-type binary plug nozzle Download PDFInfo
- Publication number
- CN106762219B CN106762219B CN201710051008.4A CN201710051008A CN106762219B CN 106762219 B CN106762219 B CN 106762219B CN 201710051008 A CN201710051008 A CN 201710051008A CN 106762219 B CN106762219 B CN 106762219B
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- Prior art keywords
- cone
- center
- plug
- new
- type binary
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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
- F02K1/82—Jet pipe walls, e.g. liners
-
- 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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Disintegrating Or Milling (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The present invention provides a kind of new-type binary plug nozzle, including supporting member, cone, mixer (5), supporting member is by cylinder (1), circle turns square changeover portion (2), jet area contraction section (3) import that successively head and the tail docking is constituted is the cylindrical member that round exit is rectangle, mixer (5) is the annular component being socketed on the axis of supporting member inner cavity, cone is the double-layer thin wall component being socketed on mixer (5) inner ring axis, cone is bored by wedge plug, and the section docked with wedge plug cone is the center cone composition of circular ring shape, support construction is provided between two thin-walled of center cone.New-type binary plug nozzle provided by the present invention, center cone and plug cone integrated design, entire aerodynamic flow path transition is smooth, aerodynamic loss is small, blocking completely for engine interior high-temperature component may be implemented, with good stealth capabilities, while having both the advantage that structure is simple, length is short, light-weight.
Description
Technical field
The invention belongs to aero-engine fields, and in particular to a kind of new-type binary plug nozzle.
Background technique
Traditional binary plug nozzle design is not able to achieve stream in entire jet pipe using inner cone and plug cone independent design technology
Field continuous uniform distribution, aeroperformance is poor, while bad to the occlusion effect of engine interior high-temperature component, so that infrared hidden
Body and radar invisible effect are poor.There is certain difference in height, tools for the fixed and unadjustable curved two-dimensional nozzle inlet and outlet axis of S
There is good Stealth Fighter, but there is a problem of that length is long, weight is big.
Summary of the invention
The purpose of the present invention is to provide a kind of new-type binary plug nozzles, overcome or alleviated by least one of the prior art
Drawbacks described above.
The purpose of the present invention is achieved through the following technical solutions: a kind of new-type binary plug nozzle, including supporting member, cone
Body, mixer,
The supporting member is successively to be docked the import constituted from beginning to end by cylinder, the square changeover portion of circle turn, jet area contraction section and be
Round exit is the cylindrical member of rectangle, wherein cylinder one end is connected with engine, and the cylinder other end turns square changeover portion by circle
Prismatic table shape jet area contraction section is connected, circle, which turns square changeover portion, becomes rectangle from circle for the cross sectional shape of supporting member；
The mixer is the annular component being socketed on the axis of supporting member inner cavity, and one end face of annular component with
Turbine rear casing frame is connected；
The cone is the double-layer thin wall component being socketed on mixer inner ring axis, the cone bored by wedge plug and
One end is bored the center cone that the section that the docking other end is connected with turbine rear casing frame is circular ring shape with the wedge plug and is constituted,
In, cavity one end which bores between two thin-walleds comes together at one and is closed, the cavity phase between the other end and two thin-walled of center cone
Perforation, wherein be provided with support construction between two thin-walled of center cone.
Preferably, the center cone in the cone and the wedge plug bore integrated molding.
Preferably, the center cone is connected by changeover portion with wedge plug cone, the section transitions shape of the changeover portion
Formula is round, rectangle or ellipse.
Preferably, the center cone includes the center cone outer wall being connected with turbine rear casing frame and is socketed in this
The center conical inner surface of center cone outer wall inner cavity, wherein the center conical inner surface is connected by supporting plate with the center cone outer wall；The wedge
Shape plug cone includes the plug conical inner surface that the plug docked with center cone outer wall is bored outer wall and docked with center conical inner surface.
Preferably, the quantity of the supporting plate is 2~18, and multiple supporting plate is circumferentially evenly arranged in the center cone
In cavity between wall and the center cone outer wall.
Preferably, the supporting plate is entity or hollow structure.
Preferably, the center conical inner surface and the center cone outer wall pass through welding or bolt and the supporting plate phase
Even.
Preferably, the jet area contraction section outlet is zigzag.
Preferably, the ratio of width to height of jet area contraction section rectangular section is 2~12.
Preferably, the mixer is lobed mixer, zigzag mixer or adjustability mixer.
A kind of beneficial effect of new-type binary plug nozzle provided by the present invention is that inner cone and plug cone integration are set
Meter, entire aerodynamic flow path transition is smooth, and aerodynamic loss is small, and blocking completely for engine interior high-temperature component may be implemented, have
Good stealth capabilities, while having both the advantage that structure is simple, length is short, light-weight.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of the new-type binary plug nozzle of the present invention；
Fig. 2 is the cross-sectional view of the new-type binary plug nozzle of the present invention；
Fig. 3 is the front view of the new-type binary plug nozzle of the present invention；
Fig. 4 is the structural schematic diagram that cone is filled in the new-type binary plug nozzle of the present invention；
Fig. 5 is the structural schematic diagram of center cone in the new-type binary plug nozzle of the present invention；
Fig. 6 is the structural schematic diagram of mixer in the new-type binary plug nozzle of the present invention.
Appended drawing reference:
1- cylinder, 2- circle turn square changeover portion, 3- jet area contraction section, 4- plug cone outer wall, 5- mixer, 6- supporting plate, the center 7-
Conical inner surface, 8- center cone outer wall, 9- fill in conical inner surface.
Specific embodiment
To keep the purposes, technical schemes and advantages of the invention implemented clearer, below in conjunction in the embodiment of the present invention
Attached drawing, 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 indicate same or similar element or element with the same or similar functions.Described embodiment is the present invention
A 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 every other embodiment obtained without creative efforts, shall fall within the protection scope of the present invention.
New-type binary plug nozzle of the invention is described in further details with reference to the accompanying drawing.
As depicted in figs. 1 and 2, a kind of new-type binary plug nozzle, including supporting member, cone, mixer 5 support structure
Part be a square changeover portion 2 is turned by cylinder 1, circle, successively to dock the import constituted from beginning to end be round exit to jet area contraction section 3 is rectangle
Cylindrical member, 1 one end of cylinder are connected with engine, and as the supporting member of entire jet pipe, 1 other end of cylinder turns square mistake by circle
It crossing section 2 and connects prismatic table shape jet area contraction section 3, circle, which turns square changeover portion 2, becomes rectangle from circle for the cross sectional shape of supporting member,
In, 3 rectangular section area of jet area contraction section gradually becomes smaller along the direction far from cylinder 1, the ratio of width to height selection of the rectangular section
It is 2~12, and 3 exit end of jet area contraction section selects zigzag.
As shown in figures 1 to 6, mixer 5 is the annular component being socketed on the axis of supporting member inner cavity, and the ring-type
Component is connected by the installation side on an end face with turbine rear casing frame, which can enhance outer culvert and intension is cold and hot
The blending of air-flow, mixer 5 can select according to specific needs lobed mixer, zigzag mixer, annular mixer and
The mixer of the forms such as adjustability mixer.
As shown in Figures 2 and 3, cone is the double-layer thin wall component being socketed on 5 inner ring axis of mixer, and the cone is by wedge
Shape plug cone and one end bore the center that the section that the docking other end is connected with turbine rear casing frame is circular ring shape with the wedge plug
Cone is constituted.Center cone and wedge plug cone in the present embodiment are formed using integrated design, and are bored in center cone and wedge plug
Between be provided with changeover portion so that the cone of integrated design is transitioned into other shapes section by circular cross-section, the changeover portion
Section transitions form can choose the shapes such as circle, rectangle, ellipse, and the cone of such form can make entire nozzle interior field
It is evenly distributed continuous, while jet pipe length can be shortened again, mitigate weight.
The center cone of double-layer structure includes the center cone outer wall 8 being connected with turbine rear casing frame and is socketed in this
The heart bores the center conical inner surface 7 of 8 inner cavity of outer wall, which is connected by supporting plate 6 with the center cone outer wall 8, wherein branch
Type of attachment between plate 6 and center conical inner surface 7 and center cone outer wall 8, which can choose, to be bolted or welds, the supporting plate 6
Quantity can select 2~18, and the circumferential sky being evenly arranged between center conical inner surface 7 and center cone outer wall 8 of multiple supporting plate 6
Intracavitary (see shown in Fig. 3 and Fig. 5), while supporting plate 6 can according to need selection entity or hollow structure.Wedge plug cone include with
The plug conical inner surface 9 (see shown in Fig. 2 and Fig. 4) that the plug that center cone outer wall 8 docks is bored outer wall 4 and docked with center conical inner surface 7,
In, plug cone outer wall 4 can realize the high-temperature component of engine interior to be blocked completely.The wedge plug bores the sky between inside and outside two thin-walleds
Chamber one end comes together at one and is closed, and the cavity inside and outside the other end and center cone between two thin-walleds connects, as shown in Figure 2, center cone
Cavity between cavity, plug conical inner surface 9 between inner wall 7 and center cone outer wall 8 and plug cone outer wall 4 forms air collecting chamber, by drawing
It is cooling to center cone and plug coning row to enter cold airflow, reduces its surface temperature, there is preferable infrared stealth effect.
The above description is merely a specific embodiment, but scope of protection of the present invention is not limited thereto, any
In the technical scope disclosed by the present invention, any changes or substitutions that can be easily thought of by those familiar with the art, all answers
It is included within the scope of the present invention.Therefore, protection scope of the present invention should be with the scope of protection of the claims
It is quasi-.
Claims (10)
1. a kind of new-type binary plug nozzle, which is characterized in that including supporting member, cone, mixer (5),
The supporting member be by cylinder (1), circle turn square changeover portion (2), jet area contraction section (3) successively head and the tail docking constitute into
Mouth is the cylindrical member that round exit is rectangle, wherein cylinder (1) one end is connected with engine, and cylinder (1) other end passes through circle
Turn square changeover portion (2) and connect prismatic table shape jet area contraction section (3), circle turns square changeover portion (2) for the cross sectional shape of supporting member by justifying
Shape becomes rectangle；
The mixer (5) is the annular component being socketed on the axis of supporting member inner cavity, and one end face of annular component with
Turbine rear casing frame is connected；
The cone is the double-layer thin wall component being socketed on mixer (5) inner ring axis, and the cone is by wedge plug cone, Yi Jiyi
It holds and bores the center cone composition that the section that the docking other end is connected with turbine rear casing frame is circular ring shape with the wedge plug, wherein
Cavity one end that the wedge plug bores between two thin-walleds comes together at one and is closed, and the cavity between the other end and two thin-walled of center cone mutually passes through
It is logical, wherein to be provided with support construction between two thin-walled of center cone.
2. new-type binary plug nozzle according to claim 1, which is characterized in that the center cone in the cone and
The wedge plug bores integrated molding.
3. new-type binary plug nozzle according to claim 1, which is characterized in that the center cone passes through changeover portion and institute
It states wedge plug cone to be connected, the section transitions form of the changeover portion is round, rectangle or ellipse.
4. new-type binary plug nozzle according to claim 1, which is characterized in that the center cone includes and machine after turbine
The connected center cone outer wall (8) of casket frame and the center conical inner surface (7) for being socketed in center cone outer wall (8) inner cavity, wherein
The center conical inner surface (7) is connected by supporting plate (6) with the center cone outer wall (8)；The wedge plug is bored
(8) plug cone outer wall (4) docked and the plug conical inner surface (9) docked with center conical inner surface (7).
5. new-type binary plug nozzle according to claim 4, which is characterized in that the quantity of the supporting plate (6) is 2~18
It is a, and multiple supporting plate (6) is circumferentially evenly arranged on the cavity between the center conical inner surface (7) and the center cone outer wall (8)
It is interior.
6. new-type binary plug nozzle according to claim 4, which is characterized in that the supporting plate (6) be entity or in
Hollow structure.
7. new-type binary plug nozzle according to claim 4, which is characterized in that the center conical inner surface (7) and institute
Center cone outer wall (8) are stated to be connected by welding or bolt with the supporting plate (6).
8. new-type binary plug nozzle according to claim 1, which is characterized in that jet area contraction section (3) outlet is
Zigzag.
9. new-type binary plug nozzle according to claim 1, which is characterized in that jet area contraction section (3) rectangle is cut
The ratio of width to height in face is 2~12.
10. new-type binary plug nozzle according to claim 1, which is characterized in that the mixer (5) is lobe mixing
Device, zigzag mixer or adjustability mixer.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710051008.4A CN106762219B (en) | 2017-01-23 | 2017-01-23 | A kind of new-type binary plug nozzle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710051008.4A CN106762219B (en) | 2017-01-23 | 2017-01-23 | A kind of new-type binary plug nozzle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106762219A CN106762219A (en) | 2017-05-31 |
| CN106762219B true CN106762219B (en) | 2019-03-22 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710051008.4A Active CN106762219B (en) | 2017-01-23 | 2017-01-23 | A kind of new-type binary plug nozzle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106762219B (en) |
Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108757216A (en) * | 2018-07-10 | 2018-11-06 | 西北工业大学 | A kind of petal-shaped noise reduction D-shaped vector spray |
| CN108894891A (en) * | 2018-07-10 | 2018-11-27 | 西北工业大学 | A kind of deformable noise reduction D-shaped vector spray |
| CN109339975B (en) * | 2018-11-02 | 2020-09-22 | 中国航空工业集团公司西安飞机设计研究所 | Stealth exhaust pipe with adjustable conical cavity |
| CN109372653A (en) * | 2018-12-13 | 2019-02-22 | 中国航发沈阳发动机研究所 | A kind of fanjet noise-reducing exhaust component |
| CN110805501B (en) * | 2019-10-16 | 2021-09-17 | 南京航空航天大学 | Throat offset type pneumatic thrust vectoring nozzle with inner S-shaped bend |
| CN113339156A (en) * | 2021-06-28 | 2021-09-03 | 西北工业大学 | Dual-bearing binary plug type thrust vectoring nozzle |
| CN114017202B (en) * | 2021-11-12 | 2023-04-18 | 中国航发沈阳发动机研究所 | Spray tube composite center cone connecting structure |
| CN115614177B (en) * | 2022-08-29 | 2024-04-16 | 中国航发四川燃气涡轮研究院 | Full shielding blending integrated casing |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3710890A (en) * | 1971-09-27 | 1973-01-16 | Boeing Co | Aircraft engine noise suppression |
| US4137992A (en) * | 1976-12-30 | 1979-02-06 | The Boeing Company | Turbojet engine nozzle for attenuating core and turbine noise |
| US4240519A (en) * | 1979-07-02 | 1980-12-23 | United Technologies Corporation | Acoustical turbine engine tail pipe plug |
| CN203214189U (en) * | 2013-04-03 | 2013-09-25 | 中国航空工业集团公司沈阳发动机设计研究所 | Plug type axial symmetry spray pipe central cone circulation adjustable cooling structure |
| CN104271894A (en) * | 2012-03-29 | 2015-01-07 | 赫拉克勒斯公司 | Integration of parts of an afterbody of an aircraft engine |
| CN104948343A (en) * | 2015-07-09 | 2015-09-30 | 中国航空工业集团公司沈阳发动机设计研究所 | Two-dimensional plug nozzle |
-
2017
- 2017-01-23 CN CN201710051008.4A patent/CN106762219B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3710890A (en) * | 1971-09-27 | 1973-01-16 | Boeing Co | Aircraft engine noise suppression |
| US4137992A (en) * | 1976-12-30 | 1979-02-06 | The Boeing Company | Turbojet engine nozzle for attenuating core and turbine noise |
| US4240519A (en) * | 1979-07-02 | 1980-12-23 | United Technologies Corporation | Acoustical turbine engine tail pipe plug |
| CN104271894A (en) * | 2012-03-29 | 2015-01-07 | 赫拉克勒斯公司 | Integration of parts of an afterbody of an aircraft engine |
| CN203214189U (en) * | 2013-04-03 | 2013-09-25 | 中国航空工业集团公司沈阳发动机设计研究所 | Plug type axial symmetry spray pipe central cone circulation adjustable cooling structure |
| CN104948343A (en) * | 2015-07-09 | 2015-09-30 | 中国航空工业集团公司沈阳发动机设计研究所 | Two-dimensional plug nozzle |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106762219A (en) | 2017-05-31 |
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