CN104963787A - Binary spraying pipe with reverse thrusting function - Google Patents
Binary spraying pipe with reverse thrusting function Download PDFInfo
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- CN104963787A CN104963787A CN201510401053.9A CN201510401053A CN104963787A CN 104963787 A CN104963787 A CN 104963787A CN 201510401053 A CN201510401053 A CN 201510401053A CN 104963787 A CN104963787 A CN 104963787A
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- convergence plate
- side panel
- circle
- pushing away
- dimensional nozzle
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Abstract
The invention relates to the field of aero-engine designing, in particular to a binary spraying pipe with the reverse thrusting function. The problems that an existing reverse thrusting device is complex in structure, and air flow is prone to leakage are solved. The binary spraying pipe with the reverse thrusting function is mainly composed of a circle-to-square cylinder body, a reduction plate, a grid, movable outer covers, connecting rod mechanisms, actuating cylinders and side wall plates. The front end of the circle-to-square cylinder body is connected with an engine. In the normal air exhausting state, an in-spraying-pipe flow passage is composed of the reduction plate and the side wall plates; the actuating cylinders drive the middle section of the reduction plate through the connecting rod mechanisms to rotate to achieve the reverse thrusting function. On the premise that the reverse thrusting function is achieved, the binary spraying pipe guarantees the structural form and the functions of a conventional binary spraying pipe, the overall size is small, the structure is simple, reliability is high, convenience is brought to integration of a machine body, and the defects of a conventional spraying pipe reverse thrusting device are overcome.
Description
Technical field
The present invention relates to Aeroengine Design field, be specifically related to a kind of to there is the anti-two-dimensional nozzle pushing away function.
Background technique
The raising of air speed and the increase of wing loads, must make to take off and distance of landing run increases, and in order to shorten aircraft ground run distance and do necessary maneuvering flight action, just needs instead to push away speed reducer.Traditional grab bucket shape deflection plate THR REV, heavier, the reaction thrust load of bearing is large; Deflecting fence THR REV, mechanical coordination part is many, complex structure, and air-flow is easily revealed and caused engine performance to reduce.So the shortcoming in order to make up traditional THR REV, needing to design a kind of structural type and performance not affecting the routine of jet pipe, and there is the anti-two-dimensional nozzle pushing away function.
Summary of the invention
The object of this invention is to provide and a kind of there is the anti-two-dimensional nozzle pushing away function, solve existing THR REV complex structure and the problem easily revealed of air-flow.
Technological scheme of the present invention is: provide a kind of and have the anti-two-dimensional nozzle pushing away function, includes circle and turns square tube body 1, grid 3, movable outer cover 5, converging portion, linkage mechanism 8, pressurized strut 9 and rolling disc 10, it is characterized in that:
Described circle turns square tube body 1 one end and is set to circle, and is fastenedly connected with motor, and the other end is set to square, and centre seamlessly transits.
Described converging portion comprises two vertical and symmetrically arranged side panel 7 and two convergence plates be symmetricly set between described two side panels 7, and described side panel 7 and described convergence plate form the inner chamber of converging portion.
Described convergence plate comprises convergence plate leading portion 2, convergence plate stage casing 6 and convergence plate back segment 4, one end away from motor that one end and the described circle of described convergence plate leading portion 2 turn square tube body 1 is connected, the other end and described convergence plate stage casing 6 are overlapped by arc surface, and described convergence plate stage casing 6 is overlapped by arc surface with described convergence plate back segment 4 again.
Described convergence plate stage casing 6 is connected on described side panel 7 by described rolling disc 10, and described rolling disc 10 is connected on described side panel 7 by rotating shaft.
Described grid 3 is arranged in the space that described convergence plate leading portion 2, described convergence plate back segment 4 and described side panel 7 surround.
Described linkage mechanism 8, is connected with one end of described pressurized strut 9, and the roller end of described linkage mechanism 8 also rolling disc 10 described with two is connected.
The other end and the described circle of described pressurized strut 9 turn square tube body 1 and are connected.
Described movable outer cover 5 is symmetricly set on the outside of convergence plate, and two ends are fixedly connected in the rotating shaft of described rolling disc 10.
Alternatively, described movable outer cover 5, convergence plate stage casing 6 and rolling disc 10 synchronous axial system.
Alternatively, described pressurized strut 9 is provided with 2, the symmetrical both sides being distributed in side panel 7.
Alternatively, described side panel 7 has a long strip chute along jet pipe is axial arranged, and chute central plane crosses the axis of jet pipe, long strip chute can be set to rectangle chute, also can connect the above and below of chute with arc surface in two ends.
Alternatively, the long strip chute on described 2 side panels 7 is symmetrical arranged.
Alternatively, described grid 3 is set to the quadrilateral grid that transverse slat and riser intersect to form and fills.
Beneficial effect of the present invention: provide and a kind of there is the anti-two-dimensional nozzle pushing away function, this two-dimensional nozzle have counter push away the prerequisite of function under, ensure structural type and the function of conventional two-dimensional nozzle, overall sizes is little, structure is simple, reliability is high, be convenient to fuselage integration, compensate for the defect of conventional THR REV.
Accompanying drawing explanation
Fig. 1 is that the present invention has the anti-two-dimensional nozzle stereogram pushing away function;
Fig. 2 is the side view of the present invention when having that the anti-two-dimensional nozzle pushing away function is counter pushes away working state;
Fig. 3 is the sectional view of the present invention when having that the anti-two-dimensional nozzle pushing away function is counter pushes away working state;
Fig. 4 is that the present invention has anti-side view when pushing away the two-dimensional nozzle normal working of function;
Fig. 5 is that the present invention has anti-sectional view when pushing away the two-dimensional nozzle normal working of function;
Fig. 6 is that the present invention has the anti-stereogram pushing away the grid 3 of the two-dimensional nozzle of function.
Wherein: 1-circle turns square tube body, 2-convergence plate leading portion, 3-grid, 4-convergence plate back segment, 5-movable outer cover, 6-convergence plate stage casing, 7-side panel, 8-linkage mechanism, 9-pressurized strut, 10-rolling disc
Embodiment
Here will be described exemplary embodiment in detail, its sample table shows in the accompanying drawings.When description below relates to accompanying drawing, unless otherwise indicated, the same numbers in different accompanying drawing represents identical key element.
As shown in drawings, the invention provides and a kind of there is the anti-two-dimensional nozzle pushing away function, include circle and turn square tube body 1, grid 3, movable outer cover 5, converging portion, linkage mechanism 8, pressurized strut 9 and rolling disc 10.
Described circle turns square tube body 1 one end and is set to circle, and is fastenedly connected with motor, and the other end is set to square, and centre seamlessly transits, and circle turns the supporting member that square tube body 1 is whole two-dimensional nozzle.
Described converging portion comprises two vertical and symmetrically arranged side panel 7 and two convergence plates be symmetricly set between described two side panels 7, described side panel 7 and described convergence plate form convergent passage, justify to turn the air-flow that square tube body 1 enters from engine end and can flow out from convergent passage.
Described convergence plate comprises convergence plate leading portion 2, convergence plate stage casing 6 and convergence plate back segment 4, one end away from motor that one end and the described circle of described convergence plate leading portion 2 turn square tube body 1 is connected, the other end and described convergence plate stage casing 6 are overlapped by arc surface, and described convergence plate stage casing 6 is overlapped by arc surface with described convergence plate back segment 4 again.
Described convergence plate stage casing 6 is connected on described side panel 7 by described rolling disc 10, described rolling disc 10 is connected on described side panel 7 by rotating shaft, rotating shaft is through after side panel 7, with be symmetricly set on the movable outer cover 5 of restraining outside plate and be fixedly connected with, movable outer cover 5, convergence plate stage casing 6 and rolling disc 10 can synchronous axial system around the shaft.
Described grid 3 is arranged in the space that described convergence plate leading portion 2, described convergence plate back segment 4 and described side panel 7 surround, air ventilation passage when pushing away work as two-dimensional nozzle is counter.
Described linkage mechanism 8, be connected with one end of described pressurized strut 9, the roller end of described linkage mechanism 8 also rolling disc 10 described with two is connected, the linkage mechanism 8 of the same side is connected with the roller end of two rolling discs 10 of homonymy, to drive axis of rotation in linkage mechanism 8 movement process, thus drive movable outer cover 5, convergence plate stage casing 6 and rolling disc 10 synchronous axial system.
Linkage mechanism 8 is driven by pressurized strut 9.Particularly, pressurized strut 9 is along the axial horizontal arrangement of two-dimensional nozzle, and one end turns square tube body 1 with circle and is fixedly connected with, and the other end is connected with linkage mechanism 8.When two-dimensional nozzle need perform counter push away order time, as shown in Figure 2 and Figure 3, pressurized strut 9 drives convergence plate stage casing 6 to rotate, when turning to respective precalculated position to make upper and lower convergence plate stage casing 6 by linkage mechanism 8, make it mutual overlap joint, convergent passage is blocked; Meanwhile, movable outer cover 5 also synchronous axial system, the anti-inlet, outlet pushing away passage is opened simultaneously, and gas is discharged through grid, thus realizes instead pushing away function.On the contrary, as shown in Figure 4, Figure 5, when jet pipe is in normal exhaust state, movable outer cover 5 is positioned at grid 3 exhaust outlet position, restrain plate stage casing 6 and convergence plate leading portion 2 and restrain plate back segment 4 and mutually overlap, form complete convergence plate, air-flow is discharged backward from convergent passage.
Described pressurized strut 9 is provided with 2, the symmetrical both sides being distributed in side panel 7.
Described side panel 7 has a long strip chute along jet pipe is axial arranged, and chute central plane crosses the axis of jet pipe, long strip chute is set to rectangle chute.
Long strip chute on described 2 side panels 7 is symmetrical arranged.
Described grid 3 is set to the quadrilateral grid that transverse slat and riser intersect to form and fills.
The above; be only the specific embodiment of the present invention, but protection scope of the present invention is not limited thereto, is anyly familiar with those skilled in the art in the technical scope that the present invention discloses; the change that can expect easily or replacement, all should be encompassed within protection scope of the present invention.Therefore, protection scope of the present invention should be as the criterion with the protection domain of described claim.
Claims (6)
1. one kind has the anti-two-dimensional nozzle pushing away function, include circle and turn square tube body (1), grid (3), movable outer cover (5), converging portion, linkage mechanism (8), pressurized strut (9) and rolling disc (10), it is characterized in that:
Described circle turns square tube body (1) one end and is set to circle, and is fastenedly connected with motor, and the other end is set to square, and centre seamlessly transits;
Described converging portion comprises two vertical and symmetrically arranged side panel (7) and two convergence plates be symmetricly set between described two side panels (7), and described side panel (7) and described convergence plate form the inner chamber of converging portion;
Described convergence plate comprises convergence plate leading portion (2), convergence plate stage casing (6) and convergence plate back segment (4), one end away from motor that one end and the described circle of described convergence plate leading portion (2) turn square tube body (1) is connected, the other end and described convergence plate stage casing (6) are overlapped by arc surface, and described convergence plate stage casing (6) is overlapped by arc surface with described convergence plate back segment (4) again;
Described convergence plate stage casing (6) is connected on described side panel (7) by described rolling disc (10), and described rolling disc (10) is connected on described side panel (7) by rotating shaft;
Described grid (3) is arranged in the space that described convergence plate leading portion (2), described convergence plate back segment (4) and described side panel (7) surround;
Described linkage mechanism (8), is connected with one end of described pressurized strut (9), and described linkage mechanism (8) is also connected with the roller end of two described rolling discs (10);
The other end and the described circle of described pressurized strut (9) turn square tube body (1) and are connected;
Described movable outer cover (5) is symmetricly set on the outside of convergence plate, and two ends are fixedly connected in the rotating shaft of described rolling disc (10).
2. according to claim 1 a kind ofly have the anti-two-dimensional nozzle pushing away function, it is characterized in that: described movable outer cover (5), convergence plate stage casing (6) and rolling disc (10) synchronous axial system.
3. according to claim 1 a kind ofly have the anti-two-dimensional nozzle pushing away function, it is characterized in that: described pressurized strut (9) is provided with 2, the symmetrical both sides being distributed in side panel (7).
4. according to claim 1 a kind ofly have the anti-two-dimensional nozzle pushing away function, it is characterized in that: described side panel (7) has a long strip chute along jet pipe is axial arranged, and chute central plane crosses the axis of jet pipe, long strip chute is set to rectangle chute.
5. a kind of according to claim 1 and 4 has the anti-two-dimensional nozzle pushing away function, it is characterized in that: the long strip chute on described 2 side panels (7) is symmetrical arranged.
6. according to claim 1 a kind ofly have the anti-two-dimensional nozzle pushing away function, it is characterized in that: described grid (3) is set to the grid that transverse slat and riser intersect to form and fills.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510401053.9A CN104963787B (en) | 2015-07-09 | 2015-07-09 | Binary spraying pipe with reverse thrusting function |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510401053.9A CN104963787B (en) | 2015-07-09 | 2015-07-09 | Binary spraying pipe with reverse thrusting function |
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| Publication Number | Publication Date |
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| CN104963787A true CN104963787A (en) | 2015-10-07 |
| CN104963787B CN104963787B (en) | 2017-04-19 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201510401053.9A Active CN104963787B (en) | 2015-07-09 | 2015-07-09 | Binary spraying pipe with reverse thrusting function |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106021749A (en) * | 2016-05-25 | 2016-10-12 | 上海交通大学 | Realization method for consistency optimization of reaction thrust two-dimensional grilles |
| CN113107707A (en) * | 2021-04-28 | 2021-07-13 | 中国航发沈阳发动机研究所 | Engine spray pipe structure |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5174502A (en) * | 1991-05-10 | 1992-12-29 | General Electric Company | Support for a translating nozzle vectoring ring |
| WO2001004484A1 (en) * | 1999-07-12 | 2001-01-18 | Snecma Moteurs | Convergent-divergent axisymmetric turbojet exhaust nozzle |
| CN101652556A (en) * | 2007-04-04 | 2010-02-17 | 埃尔塞乐公司 | Thrust reverser for a jet engine |
| CN102877982A (en) * | 2012-07-24 | 2013-01-16 | 中国航空工业集团公司沈阳发动机设计研究所 | Thrust reverser of aero-engine |
| CN103696877A (en) * | 2013-12-05 | 2014-04-02 | 中国航空工业集团公司沈阳发动机设计研究所 | Reverse thrusting device with capacity of adjusting area of spray pipe |
| CN104033282A (en) * | 2014-06-09 | 2014-09-10 | 中国航空工业集团公司沈阳发动机设计研究所 | Binary convergent nozzle with reverse thrust function |
-
2015
- 2015-07-09 CN CN201510401053.9A patent/CN104963787B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5174502A (en) * | 1991-05-10 | 1992-12-29 | General Electric Company | Support for a translating nozzle vectoring ring |
| WO2001004484A1 (en) * | 1999-07-12 | 2001-01-18 | Snecma Moteurs | Convergent-divergent axisymmetric turbojet exhaust nozzle |
| CN101652556A (en) * | 2007-04-04 | 2010-02-17 | 埃尔塞乐公司 | Thrust reverser for a jet engine |
| CN102877982A (en) * | 2012-07-24 | 2013-01-16 | 中国航空工业集团公司沈阳发动机设计研究所 | Thrust reverser of aero-engine |
| CN103696877A (en) * | 2013-12-05 | 2014-04-02 | 中国航空工业集团公司沈阳发动机设计研究所 | Reverse thrusting device with capacity of adjusting area of spray pipe |
| CN104033282A (en) * | 2014-06-09 | 2014-09-10 | 中国航空工业集团公司沈阳发动机设计研究所 | Binary convergent nozzle with reverse thrust function |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106021749A (en) * | 2016-05-25 | 2016-10-12 | 上海交通大学 | Realization method for consistency optimization of reaction thrust two-dimensional grilles |
| CN106021749B (en) * | 2016-05-25 | 2019-03-05 | 上海交通大学 | The anti-consistency optimization implementation method for pushing away two-dimensional grid |
| CN113107707A (en) * | 2021-04-28 | 2021-07-13 | 中国航发沈阳发动机研究所 | Engine spray pipe structure |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104963787B (en) | 2017-04-19 |
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