CN103899432A - Improved pneumatic vectoring nozzle structure with function of injecting double secondary flow branches - Google Patents
Improved pneumatic vectoring nozzle structure with function of injecting double secondary flow branches Download PDFInfo
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- CN103899432A CN103899432A CN201410123383.1A CN201410123383A CN103899432A CN 103899432 A CN103899432 A CN 103899432A CN 201410123383 A CN201410123383 A CN 201410123383A CN 103899432 A CN103899432 A CN 103899432A
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Abstract
The invention provides a pneumatic vectoring nozzle structure with a function of injecting double secondary flow branches. The pneumatic vectoring nozzle structure is characterized in that a pneumatic vectoring nozzle with the function of injecting the double secondary flow branches structurally comprises a secondary flow injection system I, a secondary flow injection system II and a closing and converging nozzle; the secondary flow injection system I comprises an air entrainment pipeline and a valve; the secondary flow injection system II comprises another air entrainment pipeline and another valve. The pneumatic vectoring nozzle structure has the advantage that shortcomings of decrease of flow of an engine and reduction of thrust due to the fact that air is entrained from a high-pressure component of the engine can be overcome.
Description
Technical field:
The present invention relates to aero engine technology field, especially one is applied to aeroengine novel exhaust system structure, specifically a kind of improved two bursts of Secondary Flows injection fluidic vectoring nozzle structures that have.
Background technique:
The application of Thrust Vectoring Technology can improve flexibility, mobility, fighting efficiency and the vital capacity of rocket, guided missile, fighter greatly, and the basis of this technology is Thrust-vectoring Nozzle technology.Shock wave vector control SVC since the nineties (Shock Vectoring Controlling) method starts the pneumatic thrust vector spray technical research for aeroengine vent systems, its principle is to spray into Secondary Flow at the extending section of jet pipe, utilize Secondary Flow to disturb and form shock wave generation thrust vectoring main flow, applicable object comprises that binary and axisymmetric receipts expand jet pipe.The people such as the Abeyounis in U.S. NASA Langley research center in 1987 have verified that on binary convergent diver gent nozzle employing shock wave method realizes binary convergent diver gent nozzle pitching thrust vectoring.1992, the people such as Wing, Chiarelli completed pitching, driftage vector functions by shock wave vector method in conjunction with attached wall (Coanda blowing) technology of blowing down.Nineteen ninety-five, Giuliano on NASA langley jet flow exhaust system test device specialize binary sphere based on shock wave vector control restrain/spread the test of adjustment sheet pitching Thrust-vectoring Nozzle, and in 1996, carried out based on shock wave vector control not only there is pitching thrust vectoring function, and there is the jet pipe test of driftage thrust vectoring ability.In recent years, the Thrust-vectoring Nozzle spraying based on Secondary Flow is simple in structure because of it, lightweight, be easy to safeguard, and faster system response, Stealth Fighter is good, can produce the advantage such as Thrust vector angle of 5 °-15 °, has become the hot issue of research.But, conventional SVC Thrust-vectoring Nozzle Secondary Flow is introduced from engine high pressure parts conventionally, there is the problem that amount of air entrainment is large, studies show that, draw 10% gas from high voltage component and be incorporated into nozzle divergence cone and can cause the thrust of motor to decline 20%, thrust loss is on the one hand because Secondary Flow is injected main flow and formed shock wave and produce; Be owing to from high voltage component bleed, motor common working point being moved to left on the other hand, the air flow rate that enters aeroengine reduces, and then causes the decline of gross thrust.Thereby Secondary Flow is injected the generation of main flow generation shock wave, thrust vectoring is the necessary means of shock wave vector control technology, thereby shock loss is not eliminable in the method.Therefore, in guaranteeing thrust vectoring, reduce the major issue that becomes the application of shock wave vector control technology engineering from the amount of air entrainment of high voltage component to reduce the thrust loss of motor.
Summary of the invention:
In order to overcome the deficiency in background technique, make motor flow reduce the defect that causes thrust to decline in order to solve from the bleed of engine high pressure parts, the invention provides a kind of fluidic vectoring nozzle structure that two strands of Secondary Flows spray that has.
A kind of fluidic vectoring nozzle structure with two bursts of Secondary Flows injections of the present invention, is characterized in that, its structure comprises: the fluidic vectoring nozzle of two bursts of Secondary Flow injections expands jet pipe by Secondary Flow ejecting system I, Secondary Flow ejecting system II and receipts and forms; Secondary Flow ejecting system I comprises bleed pipeline and valve; Secondary Flow ejecting system II comprises bleed pipeline and valve;
Secondary Flow ejecting system I is from the front end bleed of jet pipe converging portion; Secondary Flow ejecting system II is from the bleed of engine high pressure gas compressor; Secondary Flow ejecting system I and Secondary Flow ejecting system II are positioned at same plane, and Secondary Flow ejecting system II is positioned at the bottom of Secondary Flow ejecting system I, and the spout of bleed pipeline 1 is positioned at the spout front end of bleed pipeline; The spout of bleed pipeline is perpendicular to the wall of nozzle divergence cone; The spout of bleed pipeline is perpendicular to the wall of nozzle divergence cone; Valve and valve are adjustable, and valve and valve intercouple according to the state of jet pipe.
When two strands of Secondary Flows spray fluidic vectoring nozzle work, Secondary Flow ejecting system I introduces gas by bleed pipeline from the converging portion front end of jet pipe and is injected into the mainstream gas of nozzle divergence cone through the spout of bleed pipeline, in the time of Secondary Flow and main flow interference, produce oblique shock wave, thereby obtain certain thrust vectoring, the main effect of Secondary Flow ejecting system I has been to increase the throat opening area of jet pipe, strengthen the negotiability of jet pipe, valve is used for regulating amount of air entrainment size, in the time of jet pipe circulation scarce capacity, can tune up valve; Secondary Flow ejecting system II introduces gas and is injected in the mainstream gas of nozzle divergence cone through the spout of bleed pipeline from engine high pressure gas compressor by bleed pipeline, Secondary Flow and main flow form oblique shock wave while interference, produce Thrust vector angle, to realize the pitching movement of aircraft, valve is used for controlling amount of air entrainment, regulates the amount of incident of Secondary Flow can obtain thrust vectoring in various degree.The advantage of maximum of the present invention is, Secondary Flow ejecting system I has produced certain thrust vectoring, Secondary Flow ejecting system II can reduce relatively from engine high pressure gas compressor part amount of air entrainment, thereby the engine performance having reduced because causing from high-pressure compressor bleed declines, Secondary Flow ejecting system I has increased the negotiability of jet pipe simultaneously, thereby has promoted the performance of motor.
Accompanying drawing explanation:
Fig. 1 is structural representation of the present invention;
1-bleed pipeline in figure; 2-valve; 3-bleed pipeline; 4-valve; 5-receives and expands jet pipe.
Embodiment:
With reference to each figure, this kind of fluidic vectoring nozzle structure with two bursts of Secondary Flows injections, is characterized in that, its structure comprises: the fluidic vectoring nozzle of two bursts of Secondary Flow injections expands jet pipe 5 by Secondary Flow ejecting system I, Secondary Flow ejecting system II and receipts and forms; Secondary Flow ejecting system I comprises bleed pipeline 1 and valve 2; Secondary Flow ejecting system II comprises bleed pipeline 3 and valve 4;
Secondary Flow ejecting system I is from the front end bleed of jet pipe 5 converging portions; Secondary Flow ejecting system II is from the bleed of engine high pressure gas compressor; Secondary Flow ejecting system I and Secondary Flow ejecting system II are positioned at same plane, and Secondary Flow ejecting system II is positioned at the bottom of Secondary Flow ejecting system I, and the spout of bleed pipeline 1 is positioned at the spout front end of bleed pipeline 3; The spout of bleed pipeline 1 is perpendicular to the wall of jet pipe 5 extending sections; The spout of bleed pipeline 3 is perpendicular to the wall of jet pipe 5 extending sections; Valve 2 and valve 4 are adjustable, and valve 2 intercouples according to the state of jet pipe with valve 4.
When two strands of Secondary Flows spray fluidic vectoring nozzle work, Secondary Flow ejecting system I introduces gas by bleed pipeline 1 from the converging portion front end of jet pipe 5 and is injected into the mainstream gas of jet pipe 5 extending sections through the spout of bleed pipeline 1, in the time of Secondary Flow and main flow interference, produce oblique shock wave, thereby obtain certain thrust vectoring, the main effect of Secondary Flow ejecting system I has been to increase the throat opening area of jet pipe 5, strengthen the negotiability of jet pipe 5, valve 2 is for regulating amount of air entrainment size, in the time that jet pipe 5 negotiabilities are not enough, can tune up valve 2; Secondary Flow ejecting system II introduces gas and is injected in the mainstream gas of jet pipe 5 extending sections through the spout of bleed pipeline 3 from engine high pressure gas compressor by bleed pipeline 3, Secondary Flow and main flow form oblique shock wave while interference, produce Thrust vector angle, to realize the pitching movement of aircraft, valve 4, for controlling amount of air entrainment, regulates the amount of incident of Secondary Flow can obtain thrust vectoring in various degree.The advantage of maximum of the present invention is, Secondary Flow ejecting system I has produced certain thrust vectoring, Secondary Flow ejecting system II can reduce relatively from engine high pressure gas compressor part amount of air entrainment, thereby the engine performance having reduced because causing from high-pressure compressor bleed declines, Secondary Flow ejecting system I has increased the negotiability of jet pipe simultaneously, thereby has promoted the performance of motor.
In the time of the less Thrust vector angle of needs, valve 2 is in closed state, Secondary Flow ejecting system I does not work, Secondary Flow ejecting system II introduces gas and is injected in the mainstream gas of jet pipe 5 extending sections through the spout of bleed pipeline 3 from engine high pressure gas compressor by bleed pipeline 3, Secondary Flow and main flow are disturbed and are formed oblique shock wave, produce Thrust vector angle, valve 4, for controlling amount of air entrainment, regulates the amount of incident of Secondary Flow can obtain different small angle Thrust vector angles.But, in the time of the larger Thrust vector angle of needs, if just Secondary Flow ejecting system II work tunes up valve 4 and realizes, can cause the sharply decline of engine performance, now open valve 2, Secondary Flow ejecting system I introduces gas by bleed pipeline 1 from the converging portion front end of jet pipe 5 and is injected into the mainstream gas of jet pipe 5 extending sections through the spout of bleed pipeline 1, Secondary Flow and main flow are disturbed and are produced oblique shock wave, thereby obtain certain thrust vectoring, Secondary Flow ejecting system I plays the effect of the throat opening area that has increased jet pipe 5, strengthen the negotiability of jet pipe 5, again because Secondary Flow ejecting system I has produced certain thrust vectoring, valve 4 can be turned down, can reduce from the bleed of high-pressure section, thereby reduce the thrust loss of motor.
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. have the fluidic vectoring nozzle structure that two strands of Secondary Flows spray, it is characterized in that, its structure comprises: the fluidic vectoring nozzle of two bursts of Secondary Flow injections expands jet pipe by Secondary Flow ejecting system I, Secondary Flow ejecting system II and receipts and forms; Secondary Flow ejecting system I comprises bleed pipeline and valve; Secondary Flow ejecting system II comprises bleed pipeline and valve; Secondary Flow ejecting system I is from the front end bleed of jet pipe converging portion; Secondary Flow ejecting system II is from the bleed of engine high pressure gas compressor; Secondary Flow ejecting system I and Secondary Flow ejecting system II are positioned at same plane, and Secondary Flow ejecting system II is positioned at the bottom of Secondary Flow ejecting system I, and the spout of bleed pipeline 1 is positioned at the spout front end of bleed pipeline; The spout of bleed pipeline is perpendicular to the wall of nozzle divergence cone; The spout of bleed pipeline is perpendicular to the wall of nozzle divergence cone; Valve and valve are adjustable, and valve and valve intercouple according to the state of jet pipe.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201410123383.1A CN103899432A (en) | 2014-03-31 | 2014-03-31 | Improved pneumatic vectoring nozzle structure with function of injecting double secondary flow branches |
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| CN201410123383.1A CN103899432A (en) | 2014-03-31 | 2014-03-31 | Improved pneumatic vectoring nozzle structure with function of injecting double secondary flow branches |
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Cited By (10)
| 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 |
| CN105443268A (en) * | 2015-11-26 | 2016-03-30 | 南京航空航天大学 | Bypass type passive double-throat pneumatic vector spraying pipe with flow regulating function and control method |
| 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 |
| CN106523188A (en) * | 2016-10-10 | 2017-03-22 | 哈尔滨工程大学 | Distributed type air inlet channel solid rocket engine jet pipe divergent section afterflaming device |
| CN106545434A (en) * | 2016-10-10 | 2017-03-29 | 哈尔滨工程大学 | A kind of annular inlet Exit Cone of Solid Rocket Nozzle aftercombustion device |
| CN107642436A (en) * | 2017-08-11 | 2018-01-30 | 北京航空航天大学 | A kind of hybrid rocket engine thrust gas vector controlled structure and method |
| 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 |
| CN112160846A (en) * | 2020-09-18 | 2021-01-01 | 中国航发四川燃气涡轮研究院 | Self-air-entraining pneumatic thrust vectoring nozzle with S-shaped curved flow passage |
| CN115075981A (en) * | 2021-03-15 | 2022-09-20 | 中国科学院沈阳自动化研究所 | Thrust vectoring nozzle adopting flow control |
| 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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Cited By (15)
| 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 |
| CN105443268B (en) * | 2015-11-26 | 2017-07-18 | 南京航空航天大学 | Passive pair of venturi fluidic vectoring nozzle of bypass type with flow regulating function and control method |
| CN105443268A (en) * | 2015-11-26 | 2016-03-30 | 南京航空航天大学 | Bypass type passive double-throat pneumatic vector spraying pipe with flow regulating function and control method |
| 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 |
| CN106523188B (en) * | 2016-10-10 | 2018-01-19 | 哈尔滨工程大学 | A kind of distributed air intake duct Exit Cone of Solid Rocket Nozzle aftercombustion device |
| CN106545434A (en) * | 2016-10-10 | 2017-03-29 | 哈尔滨工程大学 | A kind of annular inlet Exit Cone of Solid Rocket Nozzle aftercombustion device |
| CN106523188A (en) * | 2016-10-10 | 2017-03-22 | 哈尔滨工程大学 | Distributed type air inlet channel solid rocket engine jet pipe divergent section afterflaming device |
| CN106545434B (en) * | 2016-10-10 | 2018-01-19 | 哈尔滨工程大学 | A kind of annular inlet Exit Cone of Solid Rocket Nozzle aftercombustion device |
| CN107642436A (en) * | 2017-08-11 | 2018-01-30 | 北京航空航天大学 | A kind of hybrid rocket engine thrust gas vector controlled structure and method |
| 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 |
| CN112160846A (en) * | 2020-09-18 | 2021-01-01 | 中国航发四川燃气涡轮研究院 | Self-air-entraining pneumatic thrust vectoring nozzle with S-shaped curved flow passage |
| CN112160846B (en) * | 2020-09-18 | 2022-02-01 | 中国航发四川燃气涡轮研究院 | Self-air-entraining pneumatic thrust vectoring nozzle with S-shaped curved flow passage |
| CN115075981A (en) * | 2021-03-15 | 2022-09-20 | 中国科学院沈阳自动化研究所 | Thrust vectoring nozzle adopting flow control |
| 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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