CN105298683B - Venturi offset fluidic vectoring nozzle and control method with afterburning boosting function - Google Patents
Venturi offset fluidic vectoring nozzle and control method with afterburning boosting function Download PDFInfo
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- CN105298683B CN105298683B CN201510666593.XA CN201510666593A CN105298683B CN 105298683 B CN105298683 B CN 105298683B CN 201510666593 A CN201510666593 A CN 201510666593A CN 105298683 B CN105298683 B CN 105298683B
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- venturi
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- afterburning
- fuel oil
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- 238000000034 method Methods 0.000 title claims description 4
- 239000000446 fuel Substances 0.000 claims abstract description 26
- 239000000295 fuel oil Substances 0.000 claims abstract description 25
- 239000007921 spray Substances 0.000 claims abstract description 10
- 239000010761 intermediate fuel oil Substances 0.000 claims description 3
- 210000000867 larynx Anatomy 0.000 claims description 3
- 239000003921 oil Substances 0.000 claims description 3
- 238000002485 combustion reaction Methods 0.000 claims description 2
- 238000002156 mixing Methods 0.000 claims description 2
- 238000000926 separation method Methods 0.000 claims 2
- 239000000203 mixture Substances 0.000 abstract description 4
- 238000005516 engineering process Methods 0.000 description 9
- 239000003570 air Substances 0.000 description 6
- 238000013461 design Methods 0.000 description 6
- 238000002347 injection Methods 0.000 description 4
- 239000007924 injection Substances 0.000 description 4
- 230000003014 reinforcing effect Effects 0.000 description 4
- 230000008901 benefit Effects 0.000 description 2
- 238000010276 construction Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 239000012080 ambient air Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 238000007634 remodeling Methods 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
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Abstract
The invention discloses a kind of venturi offset fluidic vectoring nozzle with afterburning boosting function.The inner flow passage of the jet pipe includes the anterior converging portion of a venturi, a venturi, two venturis front portion expansion converging portion, two venturis successively.The body for realizing its afterburning boosting function is to rely on to be arranged in the fuel nozzle at a venturi cusp or mix fuel in the secondary stream that a venturi vicinity is injected and realize in a venturi fired downstream.By controlling fuel nozzle to spray into angle, speed, flow or the size for controlling the ratio and secondary flow of fuel and air in time stream of fuel oil, the control for jet pipe azimuth and throat area can be realized, and realize that afterburning is reinforced, accelerate flight significant in the air for the aircraft using venturi offset fluidic vectoring nozzle.
Description
Technical field
The present invention relates to aircraft propulsion design field, particularly a kind of venturi offset fluidic vectoring nozzle.
Background technology
With the development of science and technology, the aircraft of equipment thrust vectoring aero-engine is more and more.And for fight
It is not need afterburning reinforcing for machine and guided missile etc., during orthodox flight；When being evaded, return, pursue, maneuvering flight when,
Inevitably need to carry out afterburning reinforcing, improve engine jet pipe and export stagnation temperature stagnation pressure to improve motor power, added
Speed, while carrying out maneuvering flight using Thrust Vectoring Technology.Therefore, Thrust Vectoring Technology and afterburning reinforcing technology are provided simultaneously with
Effuser device has substantial worth for the realization of future aircraft.
Instantly, it is designed with a lot, but rarely has two individually for what Thrust-vectoring Nozzle and afterburning augmentor were carried out
The design that person is merged.Just not saying the difficulty and difficulty of the two Combined design, most merely for Thrust-vectoring Nozzle
Design seldom realizes engineer applied just as rest on paper the problems such as complicated in mechanical structure, heaviness, poor reliability, high cost.
Venturi offset fluidic vectoring nozzle is divided into active and passive type venturi offset fluidic vectoring nozzle, is in recent years
Come a kind of new Thrust Vectoring Technology risen, by simple in construction, lightweight feature, more and more favored.
The structure of typical venturi offset fluidic vectoring nozzle is double venturi formulas, and the gas flowed wherein is flowed successively through
One venturi front portion converging portion, a venturi, two venturis front portion expansion converging portion, finally flow out from two venturis.Certainly, also have some its
The venturi offset fluidic vectoring nozzle of his configuration, will not be described here.
Active venturi offset fluidic vectoring nozzle is more to be drawn from engine compressor, turbine, air intake duct or outside atmosphere
Gas, also there is the bleed mode such as gas cylinder, air pump, by its near a venturi at a particular angle, speed and flow inject
Main flow produces disturbance to realize the function of thrust vectoring.And passive type venturi offset fluidic vectoring nozzle is more from engine whirlpool
Wheel outlet bleed, if or the air-flow for entering jet pipe be divided into carried interest and produced with wherein one or several bursts injection main flows disturb,
So as to obtain vector effect.
The content of the invention
Goal of the invention：In order to overcome the deficiencies in the prior art, the present invention provides a kind of with afterburning boosting function
Venturi offset fluidic vectoring nozzle, there is no for solving existing aircraft and be provided simultaneously with pneumatic thrust vectoring technology and benefit
Fire the technical problem of the jet pipe of reinforcing technology.
Technical scheme：To achieve the above object, the technical solution adopted by the present invention is：
A kind of venturi offset fluidic vectoring nozzle with afterburning boosting function, in venturi offset fluidic vectoring nozzle
Inside it is provided with fuel inlet and igniter, before and after the venturi that the position of the fuel inlet is arranged on, is not more than away from a venturi
20% 1 venturi is highly located, and the igniter is arranged on a venturi downstream position.Fuel oil forms oil gas after being mixed with main flow and mixed
Compound, can improve the stagnation temperature and stagnation pressure of main flow after lighting, realize afterburning, and due to having sprayed into fuel oil into main flow, therefore
The pneumatic throat area of main flow can be changed, so as to improve motor power.
The concrete form of fuel inlet is referred to following 2 kinds of modes：
1st, the fuel inlet is fuel nozzle, and fuel nozzle is arranged at a venturi position of cusp, is met away from a larynx
Road is not more than the position of 20% 1 venturi height, and fuel nozzle sprays velocity direction and the mainstream speed direction vector of fuel oil
Angle be 0 ° -180 °.
2nd, the fuel inlet is time circulation road.Secondary circulation road in conventional venturi offset fluidic vectoring nozzle goes out
Mouth position meets the position for being not more than 20% 1 venturi height away from a venturi.
No matter which kind of mode above is applied in conventional venturi offset fluidic vectoring nozzle, sprayed all without changing
The inner mold face of pipe, so as to maintain the basic performance of jet pipe.
Further, in the present invention, mixed after fuel oil is sprayed by fuel nozzle with main flow, regulation as needed sprays
Angle, speed and the flow of fuel oil, so as to control the pneumatic throat area of nozzle thrust azimuth and main flow.
Further, in the present invention, fuel oil is sprayed by secondary circulation road, as needed regulation time stream intermediate fuel oil and air
Ratio and secondary flow size, so as to control the pneumatic throat area of nozzle thrust azimuth and main flow.
Beneficial effect：
A kind of venturi offset fluidic vectoring nozzle with afterburning boosting function that the present invention is provided, is offset using venturi
The characteristics of formula fluidic vectoring nozzle inner profile and the flow field structure of flow field, are dexterously disposed about fuel oil in a venturi cusp
Nozzle mixes fuel oil in the secondary stream that a venturi vicinity is injected, and has fully ensured that the blending of fuel oil and main flow, and pass through point
Firearm ignites gas mixture, is efficiently burnt in a venturi downstream, realizes afterburning boosting function, has widened its application
Occasion, specifically includes the advantage of the following aspects：
(1) Thrust-vectoring Nozzle is combined with afterburning augmentor, using the characteristics of its inner profile and flow field stream
Field structure, fuel oil is mixed in the secondary stream that the fuel nozzle oil spout that a venturi cusp is disposed about or a venturi vicinity are injected,
And by type of igniter pilot gas mixture, in a venturi fired downstream, realize that afterburning is reinforced, it is not necessary to vector spray in itself
Structure carries out larger change, so as to ensure that the performance of vector spray；
(2) can easily with body integrated design after aircraft, in spite of afterburning augmentor is used, jet pipe size do not have
Change, binary spout easily can carry out integrated design with aircraft rear fuselage, so that reduce afterbody drag,
Reduce body infra-red radiation；
(3) nozzle can be controlled to spray the secondary stream for injecting main flow at angle, flow and the speed of fuel oil, or one venturi of control
Flow, ratio and the speed of intermediate fuel oil, so as to control the Thrust vector angle of jet pipe, regulation throat area；
(4) the characteristics of making full use of venturi offset fluidic vectoring nozzle flow field, using its internal whirlpool, to fuel oil
Sufficiently blended with air, improve fuel efficiency and stable flame, cancel flameholder, mitigate construction weight；
(5) this jet pipe key technology can coordinate other larynxs including anti-push type, VTOL type, omnidirectional's vector type
The remodeling of road offset fluidic vectoring nozzle is used, using in extensive range.
Brief description of the drawings
Fig. 1 is jet pipe inner mold face structural side view of the invention.
Embodiment
The present invention is further described below in conjunction with the accompanying drawings.
The structure chart in conventional venturi offset fluidic vectoring nozzle inner mold face shown in Fig. 1, mainly by jet pipe upper wall surface 1,
The anterior converging portion 3 of jet pipe lower wall surface 2, a venturi, a venturi cusp 4, a venturi 5, two venturis front portion expansion converging portion 6, rear body
The parts such as cavity 7, two venturi cusps 8, two venturis 9 are constituted.
The present invention passes through on the basis of identical is kept with above-mentioned conventional venturi offset fluidic vectoring nozzle inner mold face
Fuel oil is injected near a venturi 5, the stagnation temperature and stagnation pressure of main flow is improved, and adds in main flow quality, it is achieved thereby that for
The regulation and control of jet pipe azimuth, realize afterburning boosting function.Therefore, jet pipe of the invention has 2 kinds of working conditions：Just
Normal state and afterburning Afterburning condition.
Normal condition is used as conventional venturi offset fluidic vectoring nozzle, afterburning Afterburning condition specifically include with
Lower 2 kinds of realization rates：
Realization rate 1：Using the technical scheme of fuel nozzle, fuel nozzle is arranged in the vicinity of a venturi cusp 4, its
The fuel oil velocity direction of injection and the angle of mainstream speed direction vector are 0 ° -180 °, can be by controlling fuel oil to spray
Angle, flow and speed, so as to realize the control for Thrust vector angle, it is possible to which venturi face is adjusted by identical method
Product.
Realization rate 2：Using the technical scheme that fuel oil is blended into secondary stream, secondary circulation road is then offset with conventional venturi
The secondary circulation road set in formula fluidic vectoring nozzle is consistent, i.e., near a venturi 5, and whether secondary circulation road blends fuel oil not
The arrangement form and position of influence time circulation road, with the performance for the thrust vectoring for maintaining jet pipe.Therefore, fuel oil injection main flow
Angle with time stream injection fuel oil angle it is consistent.Wherein, the secondary stream for injecting main flow in a venturi 5 can come from engine and calm the anger
Machine or combustion chamber, can be from jet pipe exit flow or aircraft air intake duct or ambient air, could also be from gas cylinder, pressure
The sources of the gas such as contracting machine, air pump.
Described above is only the preferred embodiment of the present invention, it should be pointed out that：For the ordinary skill people of the art
For member, under the premise without departing from the principles of the invention, some improvements and modifications can also be made, these improvements and modifications also should
It is considered as protection scope of the present invention.
Claims (3)
1. a kind of venturi offset fluidic vectoring nozzle with afterburning boosting function, it is characterised in that：The venturi offset gas
Dynamic vector jet pipe is double venturi formulas, and fuel inlet and igniter, the combustion are provided with venturi offset fluidic vectoring nozzle
The position of oil inlet is arranged on the venturi of a venturi longitudinal separation one and is not more than at the position of 20% 1 venturi height, the igniter
It is arranged on a venturi downstream position；Fuel inlet is fuel nozzle either time circulation road, when fuel inlet is fuel nozzle
When, fuel oil is mixed after being sprayed by fuel nozzle with main flow, and regulation sprays angle, speed and the flow of fuel oil, so as to control spray
The Thrust vector angle of pipe and the pneumatic throat area of main flow, when fuel inlet is secondary circulation road, fuel oil is sprayed by secondary circulation road
Go out, the ratio and the size of secondary flow of regulation time stream intermediate fuel oil and air, so as to control the gas of nozzle thrust azimuth and main flow
Dynamic throat area.
2. the venturi offset fluidic vectoring nozzle according to claim 1 with afterburning boosting function, it is characterised in that：
The fuel nozzle is arranged at a venturi position of cusp, and fuel nozzle sprays the velocity direction of fuel oil and mainstream speed is sweared
The angle for measuring direction is 0 ° -180 °.
3. a kind of controlling party of venturi offset fluidic vectoring nozzle with afterburning boosting function according to claim 1
Method, it is characterised in that：Fuel oil and master are injected in the range of the venturi of a venturi longitudinal separation one is not more than 20% 1 venturi height
Stream mixing, and lighted in a venturi downstream position, the stagnation temperature and stagnation pressure for improving main flow change the pneumatic larynx of main flow simultaneously
Road area.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510666593.XA CN105298683B (en) | 2015-10-15 | 2015-10-15 | Venturi offset fluidic vectoring nozzle and control method with afterburning boosting function |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510666593.XA CN105298683B (en) | 2015-10-15 | 2015-10-15 | Venturi offset fluidic vectoring nozzle and control method with afterburning boosting function |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105298683A CN105298683A (en) | 2016-02-03 |
| CN105298683B true CN105298683B (en) | 2017-09-15 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201510666593.XA Active CN105298683B (en) | 2015-10-15 | 2015-10-15 | Venturi offset fluidic vectoring nozzle and control method with afterburning boosting function |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109630312B (en) * | 2018-11-26 | 2021-02-09 | 中国航天空气动力技术研究院 | High-frequency response vectoring nozzle |
| CN110284994B (en) * | 2019-05-10 | 2021-08-06 | 南京航空航天大学 | Parallel thrust vector exhaust system based on throat offset type pneumatic vector spray pipe |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6679048B1 (en) * | 2000-10-24 | 2004-01-20 | Lockheed Martin Corporation | Apparatus and method for controlling primary fluid flow using secondary fluid flow injection |
| CN102536514A (en) * | 2012-01-17 | 2012-07-04 | 南京航空航天大学 | Binary plug nozzle of turbofan engine with afterburning |
| CN104847529A (en) * | 2015-03-27 | 2015-08-19 | 南京航空航天大学 | Three-degree of freedom vectored thrust system based on novel air-operated vectoring thrust nozzle |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7509797B2 (en) * | 2005-04-29 | 2009-03-31 | General Electric Company | Thrust vectoring missile turbojet |
| US7793504B2 (en) * | 2006-05-04 | 2010-09-14 | Rolls-Royce Corporation | Nozzle with an adjustable throat |
-
2015
- 2015-10-15 CN CN201510666593.XA patent/CN105298683B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6679048B1 (en) * | 2000-10-24 | 2004-01-20 | Lockheed Martin Corporation | Apparatus and method for controlling primary fluid flow using secondary fluid flow injection |
| CN102536514A (en) * | 2012-01-17 | 2012-07-04 | 南京航空航天大学 | Binary plug nozzle of turbofan engine with afterburning |
| CN104847529A (en) * | 2015-03-27 | 2015-08-19 | 南京航空航天大学 | Three-degree of freedom vectored thrust system based on novel air-operated vectoring thrust nozzle |
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|---|---|
| CN105298683A (en) | 2016-02-03 |
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