CN208416743U - It is a kind of that injection device is shifted to an earlier date based on the fuel for rotating into air flue in three-dimensional - Google Patents
It is a kind of that injection device is shifted to an earlier date based on the fuel for rotating into air flue in three-dimensional Download PDFInfo
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- CN208416743U CN208416743U CN201821090546.0U CN201821090546U CN208416743U CN 208416743 U CN208416743 U CN 208416743U CN 201821090546 U CN201821090546 U CN 201821090546U CN 208416743 U CN208416743 U CN 208416743U
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- spray mouth
- air flue
- fuel injection
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- 239000000446 fuel Substances 0.000 title claims abstract description 55
- 238000002347 injection Methods 0.000 title claims abstract description 20
- 239000007924 injection Substances 0.000 title claims abstract description 20
- 238000011144 upstream manufacturing Methods 0.000 claims abstract description 4
- 239000007921 spray Substances 0.000 claims description 54
- 239000003380 propellant Substances 0.000 claims description 36
- 230000003134 recirculating effect Effects 0.000 claims description 4
- 238000002485 combustion reaction Methods 0.000 abstract description 11
- 238000002156 mixing Methods 0.000 abstract description 8
- 230000006835 compression Effects 0.000 abstract description 5
- 238000007906 compression Methods 0.000 abstract description 5
- 238000000926 separation method Methods 0.000 abstract 1
- 230000035939 shock Effects 0.000 description 14
- 238000013461 design Methods 0.000 description 6
- 238000010586 diagram Methods 0.000 description 4
- 238000000034 method Methods 0.000 description 3
- 238000011160 research Methods 0.000 description 3
- 238000004088 simulation Methods 0.000 description 2
- 241001640558 Cotoneaster horizontalis Species 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000000593 degrading effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000284 extract Substances 0.000 description 1
- 238000013213 extrapolation Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000035515 penetration Effects 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 239000004575 stone Substances 0.000 description 1
- 230000000007 visual effect Effects 0.000 description 1
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- Combustion Methods Of Internal-Combustion Engines (AREA)
Abstract
一种基于三维内转进气道的燃料提前喷注装置，涉及近空间高超声速飞行器。设有三维内转进气道和进气道内收缩段；在进气道内收缩段的型面上设有燃料喷注口和燃料喷嘴，所述燃料喷嘴设在燃料喷注口两侧；所述三维内转进气道设有三维内转进气道压缩型面和燃料喷注口；在燃料喷注口上设有喷注口上游分离区和喷注口下游回流区，在燃料喷注口下游形成低速区。通过在三维内转进气道压缩面上按指定空间分布布置细长形燃料喷注口和圆形燃料喷嘴，有效地利用了进气道提供给燃料的预掺混长度，弥补了常规冲压发动机燃料的喷注和掺混仅在燃烧室内完成而造成的燃料实际驻留时间过短的不足，有助于实现充分燃烧，提升下游燃烧室性能。
A fuel advance injection device based on a three-dimensional internal rotation intake port relates to a near-space hypersonic vehicle. A three-dimensional inwardly rotating air inlet and a constricted section in the air inlet are provided; a fuel injection port and a fuel nozzle are arranged on the profile of the constricted section in the air inlet, and the fuel nozzles are arranged on both sides of the fuel injection port; the The three-dimensional internal rotation intake port is provided with a three-dimensional internal rotation intake port compression profile and a fuel injection port; the fuel injection port is provided with an upstream separation area of the injection port and a downstream recirculation area of the injection port, which is located downstream of the fuel injection port. A low velocity zone is formed. By arranging slender fuel injection ports and circular fuel nozzles according to a specified spatial distribution on the three-dimensional inner-turning intake port compression surface, the pre-blending length of the fuel provided by the intake port is effectively utilized, which makes up for the conventional ramjet engine. The fact that the fuel injection and blending are only completed in the combustion chamber causes the short actual residence time of the fuel, which helps to achieve full combustion and improve the performance of the downstream combustion chamber.
Description
Technical field
The utility model relates near space hypersonic aircraft, more particularly, to a kind of based on rotating into air flue in three-dimensional
Fuel shifts to an earlier date injection device.
Background technique
To the hypersonic aircraft of near space, international is already especially become to the research of its propulsion system and is competitively striven
One of hard-core technology commanding elevation taken by force, wherein scramjet engine is become and is promoted with the advantage of its high specific impulse and big thrust loading
The primary study object of system.But hypersonic aircraft operates mainly in the environment of high Mach incoming flow, fuel is burning
Effective Mixed length of indoor residence time and fuel and air is all extremely short, and the efficiency of combustion that this allows for fuel is low,
And then cause aircraft thrust insufficient, therefore how to be improved by improving the efficiency of combustion of scramjet engine thrust by
Pay attention to.Domestic and foreign scholars have done a lot of research work on improving burning, including rectangular standing vortex, sweepback standing vortex, fuel vertically spray
Note, side wall spray etc..However, the propellant spray blending research of the overwhelming majority is carried out in combustion chamber and distance piece at present
, seldom leave for considering directly to advance to the spray of fuel in air intake duct completing from integrated angle.Furthermore it is being higher than
It designs under Mach number operating condition, external compression wave system and strong slip-stream layer easily enter under the total pressure recovery coefficient that internal channel causes air intake duct
The unstable operation of drop and engine.It can be seen that in hypersonic aircraft field, design a kind of can be in air intake duct
Spray in advance with this come enhance fuel blending and can using fuel carry out multishock control device it is most important.
Summary of the invention
Injection device is shifted to an earlier date based on the fuel for rotating into air flue in three-dimensional the purpose of the utility model is to provide a kind of.
The utility model is equipped in three-dimensional and rotates into air flue and air intake duct contract section；On the type face of air intake duct contract section
Equipped with propellant spray mouth and fuel nozzle, the fuel nozzle is located at propellant spray mouth two sides；Air flue is rotated into the three-dimensional to set
Have and rotates into air flue compression-type face and propellant spray mouth in three-dimensional；Spray mouth upstream Disengagement zone and spray are equipped on propellant spray mouth
Mouth downstream recirculating zone forms low regime in propellant spray mouth downstream.
Elongated shape propellant spray mouth can be used in the propellant spray mouth.
Circular fuel nozzle can be used in the fuel nozzle.
The utility model has the advantage that
Arrangement elongated shape propellant spray mouth and circle are distributed by designated space on air flue compressing surface by rotating into three-dimensional
Fuel nozzle efficiently utilizes the pre-blended length that air intake duct is supplied to fuel, compensates for conventional punch engine fuel
Spray and blending only complete in the combustion chamber and caused by the too short deficiency of the practical residence time of fuel, help to realize abundant combustion
It burns, promotes downstream combustion chamber performance.In addition, changing the bending journey of incident shock by fuel jet under the conditions of becoming Mach number
Degree makes it keep lip cover sealing, improves air intake duct traffic capture to effectively increase engine net thrust.Therefore, this is practical new
Blending dexterously is planned as a whole to combine by type with shock wave control, is to kill two birds with one stone.
Detailed description of the invention
Fig. 1 is to rotate into air flue schematic diagram in the hypersonic three-dimensional of one kind；
Fig. 2 is to rotate into air flue schematic diagram in a kind of three-dimensional provided with elongated shape propellant spray mouth and fuel nozzle；
Fig. 3 is that the flow field on the plane of symmetry of three-dimensional contract air intake duct near the elongated shape propellant spray mouth that intercepts is special
Levy schematic diagram；
Fig. 4 is that fuel shifts to an earlier date spray schematic diagram on the plane of symmetry of three-dimensional contract air intake duct.
Specific embodiment
As shown in figures 1-4, the utility model embodiment is equipped in three-dimensional based on rotating into air flue in typical three-dimensional
Rotate into air flue 2 and air intake duct contract section 3；Elongated shape propellant spray mouth 4 and circle are equipped on the type face of air intake duct contract section 3
Shape fuel nozzle 5, the circular fuel nozzle 5 are located at 4 two sides of elongated shape propellant spray mouth；Air flue 2 is rotated into the three-dimensional to set
Have and rotates into air flue compression-type face and elongated shape propellant spray mouth 4 in three-dimensional；It is equipped on spray mouth on elongated shape propellant spray mouth 4
Disengagement zone 7 and spray mouth downstream recirculating zone 11 are swum, forms low regime 12 in 4 downstream of elongated shape propellant spray mouth.
The main implementation steps of the utility model include:
(1) three-dimensional contract air intake duct geometrical model is obtained according to design requirement.It is solved with the method for characteristic curves related basic
Then flow field is generated in three-dimensional using the method for streamlined impeller and rotates into air flue compression-type face 3, finally obtain a kind of as shown in Figure 1
Rectangular entrance turn the air intake duct of round exit.
(2) three-dimensional contract inlet duct flow field structure is obtained.Numerical simulation is carried out to air intake duct model, and extracts its three-dimensional
Flow field structure is obtained in design Mach number and the shock wave wave system figure being higher than under design two kinds of operating conditions of Mach number.
(3) the inlet duct flow field structure and feature obtained according to step (2) arranges that the 1st elongated shape fires on its contract face
Expect spray mouth 4.Increase the thinking of effectively blending duration using spray fuel is shifted to an earlier date in air intake duct, it is true according to fuel flow demand
Determine the width and length of elongated shape propellant spray mouth 4.By fuel from elongated shape propellant spray mouth 4 vertically spray into air intake duct after
Cause bowshock 8 in free incoming flow, bowshock 8 and negative sequence harmonic act on 4 upstream of elongated shape propellant spray mouth together
Carry out laminar boundary layer, promote it to separate before elongated shape propellant spray mouth 4, set as shown in Figure 2 on this basis thin
Elongated propellant spray mouth 4 makes jet stream can make full use of the upper of elongated shape propellant spray mouth 4 along the spacing and quantity of flow direction distribution
Swim the blending of recirculating zone 11 reinforcement and incoming flow in Disengagement zone 7 and downstream.
(4) circular fuel nozzle 5 is arranged in 4 two sides of elongated shape propellant spray mouth.Arrangement are as follows: the base in step (3)
Simulation calculation is carried out to the example with the elongated shape propellant spray mouth on plinth, intercepts the stream near elongated shape propellant spray mouth 4
Field feature and the contraction front boundary-layer rule of development.As shown in figure 3, fuel forms tubbiness in the outlet of elongated shape propellant spray mouth 4
Shock wave 10 forms mainstream and hinders, and forms low regime 12 in 4 downstream of elongated shape propellant spray mouth, thus sprays in elongated shape fuel
Geat 4 arranges the circular fuel nozzle 5 installed according to certain space angle perpendicular to the two sides of direction of flow, spray angle and
In spray stagnation pressure visual flow field depending on the distributed areas in the leeward low flow velocity area 12 of tubbiness shock wave 10.By adjusting circular fuel nozzle
5 jet angle can also change the penetration depth of jet stream, to adapt to the Field Characteristics under air intake duct difference operating condition.
(5) by rationally adjusting the injection pressure of elongated shape propellant spray mouth 4 and two sides circular fuel nozzle 5, with combustion
Expect the extrapolation effect that spray is formed, in conjunction with step (2) wave system action rule obtained, controls air intake duct incident shock 14 and combustion
The interference and shock wave offset that material jet stream 15 is formed after colliding, realize that curved shock 18 pastes mouth.As shown in figure 4, when air intake duct works
Under the operating condition for being higher than design Mach number, since the corresponding Angle of Shock Waves of High Mach number reduces, external compression shock wave is caused to squeeze into lip cover
Within form strong reflection and be degrading the working environment of air intake duct, for this problem, the utility model, which can pass through, adjusts fuel
Injection pressure, which to be formed, induces shock wave 16 that compression shock is extrapolated to patch mouth, and can be by changing air intake duct contract section 3 not
With the injection pressure of the elongated shape propellant spray mouth 4 on position, the shape modification to curved shock 18 is dexterously realized, according to not
With the relative position of demand flexible modulation incident shock and lip.
In fig 1 and 2, label 1 indicates hypersonic incoming flow.
In Fig. 3, label 6 indicates free incoming flow, and 9 indicate fuel jet boundary.
In Fig. 4, label 13 indicates free incoming flow, and 17 indicate air intake duct wall surface.
Claims (3)
1. a kind of shift to an earlier date injection device based on the fuel for rotating into air flue in three-dimensional, it is characterised in that equipped with rotated into three-dimensional air flue and
Air intake duct contract section；Propellant spray mouth and fuel nozzle, the fuel nozzle are equipped on the type face of air intake duct contract section
It is located at propellant spray mouth two sides；It is described three-dimensional in rotate into air flue be equipped with three-dimensional in rotate into air flue compression-type face and propellant spray mouth；
It is equipped with spray mouth upstream Disengagement zone and spray mouth downstream recirculating zone on propellant spray mouth, forms low speed in propellant spray mouth downstream
Area.
2. a kind of as described in claim 1 shift to an earlier date injection device based on the fuel for rotating into air flue in three-dimensional, it is characterised in that described
Propellant spray mouth uses elongated shape propellant spray mouth.
3. a kind of as described in claim 1 shift to an earlier date injection device based on the fuel for rotating into air flue in three-dimensional, it is characterised in that described
Fuel nozzle uses circular fuel nozzle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821090546.0U CN208416743U (en) | 2018-07-11 | 2018-07-11 | It is a kind of that injection device is shifted to an earlier date based on the fuel for rotating into air flue in three-dimensional |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821090546.0U CN208416743U (en) | 2018-07-11 | 2018-07-11 | It is a kind of that injection device is shifted to an earlier date based on the fuel for rotating into air flue in three-dimensional |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208416743U true CN208416743U (en) | 2019-01-22 |
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|---|---|---|---|
| CN201821090546.0U Active CN208416743U (en) | 2018-07-11 | 2018-07-11 | It is a kind of that injection device is shifted to an earlier date based on the fuel for rotating into air flue in three-dimensional |
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| Country | Link |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111120108A (en) * | 2019-12-16 | 2020-05-08 | 南京航空航天大学 | Internally rotating inlet port assembly based on momentum injected plasma synthetic jet and its control method |
| CN115556945A (en) * | 2022-10-14 | 2023-01-03 | 西安近代化学研究所 | Aircraft with scramjet engine based on polyborane compound fuel |
-
2018
- 2018-07-11 CN CN201821090546.0U patent/CN208416743U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111120108A (en) * | 2019-12-16 | 2020-05-08 | 南京航空航天大学 | Internally rotating inlet port assembly based on momentum injected plasma synthetic jet and its control method |
| CN115556945A (en) * | 2022-10-14 | 2023-01-03 | 西安近代化学研究所 | Aircraft with scramjet engine based on polyborane compound fuel |
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