CN103899433A - Novel thrust vectoring nozzle structure adopting shock vectoring controlling - Google Patents
Novel thrust vectoring nozzle structure adopting shock vectoring controlling Download PDFInfo
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- CN103899433A CN103899433A CN201410123384.6A CN201410123384A CN103899433A CN 103899433 A CN103899433 A CN 103899433A CN 201410123384 A CN201410123384 A CN 201410123384A CN 103899433 A CN103899433 A CN 103899433A
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Abstract
The invention provides a novel thrust vectoring nozzle structure adopting shock vectoring controlling in order to overcome defects of the prior art and improve performance of a thrust vectoring nozzle. The novel thrust vectoring nozzle structure comprises a plug plate system capable of vertically moving, a secondary flow injection system with flow adjustable, and a sealing system, a plug plate is arranged at an expansion section of the nozzle and is grooved for guiding secondary flow, and the secondary flow can guide air from an air compressor of an engine through a pipeline and is injected to a primary flow through a grooved passage in the plug plate; the sealing system is used for preventing air leak during moving of the plug plate; the plug plate can vertically move under control of a mechanical system; a valve is mounted on a secondary flow air guide pipeline so as to adjust injection capacity of the secondary flow.
Description
Technical field:
The present invention relates to technical field of engines, especially one is applied to the military thrust vectoring nozzle of the little duct of high thrust weight ratio, specifically a kind of novel shock wave control Thrust-vectoring Nozzle structure.
Background technique:
The application of Thrust Vectoring Technology can improve flexibility, mobility, fighting efficiency and the vital capacity of rocket, guided missile, fighter greatly, Thrust Vectoring Technology often relies on Thrust-vectoring Nozzle and realizes, and Thrust-vectoring Nozzle can be divided into two classes conventionally: mechanical conditioning type Thrust-vectoring Nozzle; Fixing how much pneumatic thrust vector sprays.
Mechanical conditioning type vector spray, need mobilizable flap or complicated actuating system to realize vector control, this nozzle structure has increased weight and the cost of push system greatly, and the movement parts under hot environment is increased, cooling requirement improves, reliability decrease, cost increases, and is unfavorable for the development of high-performance enginer technology.In recent years, external numerous research institution absorbs the achievement in research of the control field that flows consciously, propose to utilize fluid injection method to realize the method for thrust vectoring, be the concept of fluid thrust vectoring FTV (Fluidic Thrust Vectoring), its effective object, for fixing how much jet pipes, has simple in structure, lightweight, be easy to safeguard faster system response, the feature such as Stealth Fighter is good.Spray and realize fluid thrust vectoring and mainly concentrate in three kinds of controlling methods based on Secondary Flow at present, be i.e. shock wave vector control SVC (Shock Vectoring Controlling) method, nozzle throat skew TS (Throat Shift) method, adverse current CF (Counter Flow) method.Although each method realizes the mode difference of thrust vectoring, its control principle is all to utilize Secondary Flow to form thrust vectoring to the interference of main flow.Wherein SVC thrust technology receives much concern because of the superiority that it shows on high Design compression ratio jet pipe, since the nineties in last century, SVC method starts the fluidic vectoring nozzle for aeroengine vent systems, applicable object comprises that binary and axisymmetric receipts expand jet pipe, the main means that adopt model test and numerical simulation of research, research contents relates to aerodynamic parameter and (comprises blow down ratio, secondary pressure ratio and jet pipe stagnation temperature etc.), geometric parameter (comprises single spraying hole, many spray orifices, eject position and nozzle hole area etc.), and some key technologies of this kind of thrust vectoring are proposed.But conventional SVC Thrust-vectoring Nozzle exists the problems such as amount of air entrainment is large, and the performance to aeroengine is had a strong impact on generation, even can make engine intake flow reduce by 10%, motor power 20% left and right that declines.Therefore the present invention is directed to conventional this defect of SVC Thrust-vectoring Nozzle, a kind of shock wave control vector spray structure one plate/pneumatic combination SVC Thrust-vectoring Nozzle is proposed, thereby this jet pipe feature is to insert plate or inject Secondary Flow at nozzle divergence cone the flow direction that produces air-flow in oblique shock wave change jet pipe, this technology only produces vectored thrust, and does not change throat area.In this technology, the geometrical shape of plate, plate relative height and Secondary Flow injection amount, all can affect Thrust vector angle and thrust vectoring efficiency to a great extent.
Summary of the invention:
In order to overcome the deficiency in background technique, improve the performance of Thrust-vectoring Nozzle, the invention provides a kind of novel shock wave control Thrust-vectoring Nozzle structure; This structure comprises the plate system that can move up and down, Secondary Flow ejection system and sealing system that flow is adjustable.Plate is positioned at the extending section of jet pipe, and plate internal recessing is to introduce Secondary Flow; Second-circulation piping is from engine compressor bleed, and the slotted channels in plate is ejected in main flow; Sealing system is for preventing the gas leakage that plate moving process produces; Plate can move up and down by mechanical system control; On Secondary Flow bleed pipeline, mounted valve is to regulate Secondary Flow injection volume.
In shock wave control vector spray when work,, plate can move up and down by mechanical system control, and plate relative height can change to maximum value from 0, thereby produces from zero Thrust vector angle to a certain angle; By introducing Secondary Flow at plate internal recessing, Secondary Flow injection volume is by valve regulated, and Secondary Flow pressure ratio can from 0 to 1.5 variation, thereby can obtain from zero Thrust vector angle to a certain angle; Sharpest edges of the present invention show in the work in combination mode of the two, plate is adjusted to certain altitude, then spray the Secondary Flow of a small amount of (being not more than 5%) and can obtain desirable thrust vectoring angle, simultaneously because the amount of air entrainment of Secondary Flow flow is less, performance impact degree to aeroengine is also accordingly less, thus the baneful influence to aero-engine performance when having alleviated simple employing Secondary Flow and spraying to obtain large Thrust vector angle.Sealing system is used in the time regulating plate height, preventing gas leakage and design.
Brief description of the drawings:
Fig. 1 is structural representation of the present invention.
1-plate system in figure; 2-Secondary Flow ejection system; 3-sealing system; '
Embodiment:
With reference to each figure, this comprises the plate system 1 that can move up and down, Secondary Flow ejection system 2 and sealing system 3 that flow is adjustable.Plate 1 is positioned at the extending section of jet pipe, and plate internal recessing is to introduce Secondary Flow; Second-circulation piping is from engine compressor bleed, and the slotted channels in plate is ejected in main flow; The gas leakage of sealing system 3 for preventing that plate moving process from producing; Plate 1 can move up and down by mechanical system control; On Secondary Flow bleed pipeline, mounted valve is to regulate Secondary Flow injection volume.
In shock wave control vector spray when work,, plate 1 can move up and down by mechanical system control, and plate relative height can change to maximum value from 0, thereby produces from zero Thrust vector angle to a certain angle; By introducing Secondary Flow at plate internal recessing, Secondary Flow injection volume is by valve regulated, and Secondary Flow pressure ratio can from 0 to 1.5 variation, thereby can obtain from zero Thrust vector angle to a certain angle; Sharpest edges of the present invention show in the work in combination mode of the two, plate 1 is adjusted to certain altitude, then spray the Secondary Flow of a small amount of (being not more than 5%) and can obtain desirable thrust vectoring angle, simultaneously because the amount of air entrainment of Secondary Flow flow is less, performance impact degree to aeroengine is also accordingly less, thus the baneful influence to aero-engine performance when having alleviated simple employing Secondary Flow and spraying to obtain large Thrust vector angle.Sealing system 3 is used in the time regulating plate height, preventing gas leakage and design.
Below in conjunction with the drawings and specific embodiments, the invention will be further described, but the invention is not restricted to this embodiment.
Mode of execution as shown in Figure 1, plate 1 can move up and down by mechanical system control system in the extending section of jet pipe, induce together shock wave inner generation of jet pipe, air-flow in jet pipe is deflected, thereby generation thrust vectoring, plate relative height can change to maximum value (be no more than nozzle throat height 0.2) from 0, thereby produce from zero Thrust vector angle to a certain angle, owing to being subject to the effect of jet pipe pressurized gas, plate inserts height in jet pipe can not be too large, otherwise can move inefficacy or start are ineffective, therefore only can produce the Thrust vector angle of smaller angle (0-6 degree) by the insertion of plate, in the time only needing small angle thrust vectoring, can adopt which.In the time that plate does not insert jet pipe, make air flow deflector in jet pipe by also forming shock wave at plate internal recessing introducing Secondary Flow in jet pipe, thereby formation thrust vectoring, can control the size of thrust vectoring angle by the size of valve regulated secondary flow, but only in the time of the little thrust vectoring angle of needs, adopt, because the thrust vectoring angle that method produces thus needs a large amount of high-voltage secondary stream, will make aero-engine performance worsen.In demand during compared with high thrust vector angle, first plate is inserted to jet pipe certain altitude, then open plate internal recessing and introduce the valve of Secondary Flow, under the disturbance of plate and high-voltage secondary stream, the larger induction shock wave of intensity will be formed one in jet pipe, thereby produce larger thrust vectoring angle, in the time which is worked, can and regulate the flow of Secondary Flow to realize the control of the thrust vectoring angle of (higher Thrust vector angle) in certain limit by the height of up-down adjustment plate.
The present invention can pass through existing techniques in realizing without the technical characteristics of describing, and does not repeat them here.Certainly, above-mentioned explanation is not limitation of the present invention, and the present invention is also not limited in above-mentioned giving an example.Variation, remodeling, interpolation or replacement that those skilled in the art make in essential scope of the present invention, also should belong to protection scope of the present invention.
Claims (1)
1. a novel shock wave control Thrust-vectoring Nozzle structure, is characterized in that: this structure comprises the plate system that can move up and down, Secondary Flow ejection system and sealing system that flow is adjustable.Plate is positioned at the extending section of jet pipe, and plate internal recessing is to introduce Secondary Flow; Second-circulation piping is from engine compressor bleed, and the slotted channels in plate is ejected in main flow; Sealing system is for preventing the gas leakage that plate moving process produces; Plate can move up and down by mechanical system control; On Secondary Flow bleed pipeline, mounted valve is to regulate Secondary Flow injection volume.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201410123384.6A CN103899433A (en) | 2014-03-31 | 2014-03-31 | Novel thrust vectoring nozzle structure adopting shock vectoring controlling |
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| CN201410123384.6A CN103899433A (en) | 2014-03-31 | 2014-03-31 | Novel thrust vectoring nozzle structure adopting shock vectoring controlling |
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104712460A (en) * | 2015-01-14 | 2015-06-17 | 北京理工大学 | Solid rocket engine with controllable thrust |
| CN106014683A (en) * | 2016-05-30 | 2016-10-12 | 西北工业大学 | Pressurization flow control device-containing SERN structure for TBCC |
| CN106014684A (en) * | 2016-05-30 | 2016-10-12 | 西北工业大学 | Combined flow control method and structure for improving SERN for TBCC |
| CN106089488A (en) * | 2016-05-30 | 2016-11-09 | 西北工业大学 | A kind of engine jet pipe structure of band flow separation active control function |
| CN106762218A (en) * | 2017-01-05 | 2017-05-31 | 南京工业职业技术学院 | A kind of method and jet pipe for improving pulse detonation engine thrust coefficient |
| CN107235133A (en) * | 2017-05-08 | 2017-10-10 | 哈尔滨工程大学 | A kind of secondary water spray thruster vector control device |
| CN107655694A (en) * | 2017-08-24 | 2018-02-02 | 南京理工大学 | A kind of supersonic nozzle jet blends experimental provision |
| CN110529284A (en) * | 2019-08-01 | 2019-12-03 | 南京理工大学 | Thrust vector control system and method based on plasma synthesis jet-flow excitor |
| CN111594340A (en) * | 2020-04-30 | 2020-08-28 | 南京理工大学 | Wedge surface structure for controlling oblique detonation wave initiation by utilizing hot jet |
| CN112065603A (en) * | 2020-08-31 | 2020-12-11 | 南京航空航天大学 | Adopt receipts of shock wave bypass structure to expand spray tube |
| CN113550839A (en) * | 2021-08-11 | 2021-10-26 | 南京航空航天大学 | Thrust vector turbofan engine model and vector deflection stabilization control device |
| CN116822395A (en) * | 2023-05-04 | 2023-09-29 | 中国航发沈阳发动机研究所 | Engine design method integrating main flow thermodynamic cycle and secondary flow |
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| US3038305A (en) * | 1953-01-23 | 1962-06-12 | Lockheed Aircraft Corp | Subsonic, supersonic propulsive nozzle |
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Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104712460A (en) * | 2015-01-14 | 2015-06-17 | 北京理工大学 | Solid rocket engine with controllable thrust |
| CN106014683A (en) * | 2016-05-30 | 2016-10-12 | 西北工业大学 | Pressurization flow control device-containing SERN structure for TBCC |
| CN106014684A (en) * | 2016-05-30 | 2016-10-12 | 西北工业大学 | Combined flow control method and structure for improving SERN for TBCC |
| CN106089488A (en) * | 2016-05-30 | 2016-11-09 | 西北工业大学 | A kind of engine jet pipe structure of band flow separation active control function |
| CN106014683B (en) * | 2016-05-30 | 2018-04-06 | 西北工业大学 | A kind of TBCC SERN structures of band supercharging flow control apparatus |
| CN106762218A (en) * | 2017-01-05 | 2017-05-31 | 南京工业职业技术学院 | A kind of method and jet pipe for improving pulse detonation engine thrust coefficient |
| CN107235133A (en) * | 2017-05-08 | 2017-10-10 | 哈尔滨工程大学 | A kind of secondary water spray thruster vector control device |
| CN107655694A (en) * | 2017-08-24 | 2018-02-02 | 南京理工大学 | A kind of supersonic nozzle jet blends experimental provision |
| CN110529284A (en) * | 2019-08-01 | 2019-12-03 | 南京理工大学 | Thrust vector control system and method based on plasma synthesis jet-flow excitor |
| CN111594340A (en) * | 2020-04-30 | 2020-08-28 | 南京理工大学 | Wedge surface structure for controlling oblique detonation wave initiation by utilizing hot jet |
| CN111594340B (en) * | 2020-04-30 | 2022-01-11 | 南京理工大学 | Wedge surface structure for controlling oblique detonation wave initiation by utilizing hot jet |
| CN112065603A (en) * | 2020-08-31 | 2020-12-11 | 南京航空航天大学 | Adopt receipts of shock wave bypass structure to expand spray tube |
| CN112065603B (en) * | 2020-08-31 | 2021-11-23 | 南京航空航天大学 | Adopt receipts of shock wave bypass structure to expand spray tube |
| CN113550839A (en) * | 2021-08-11 | 2021-10-26 | 南京航空航天大学 | Thrust vector turbofan engine model and vector deflection stabilization control device |
| CN113550839B (en) * | 2021-08-11 | 2022-05-03 | 南京航空航天大学 | Thrust vector turbofan engine model and vector deflection stabilization control device |
| CN116822395A (en) * | 2023-05-04 | 2023-09-29 | 中国航发沈阳发动机研究所 | Engine design method integrating main flow thermodynamic cycle and secondary flow |
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Application publication date: 20140702 |