CN108412617B - A kind of air intake duct and widen the design method that air intake duct excess determines free stream Mach number range - Google Patents
A kind of air intake duct and widen the design method that air intake duct excess determines free stream Mach number range Download PDFInfo
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- CN108412617B CN108412617B CN201810229568.9A CN201810229568A CN108412617B CN 108412617 B CN108412617 B CN 108412617B CN 201810229568 A CN201810229568 A CN 201810229568A CN 108412617 B CN108412617 B CN 108412617B
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- air intake
- intake duct
- lip cover
- mach number
- lip
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- 238000000034 method Methods 0.000 title claims abstract description 12
- 230000035939 shock Effects 0.000 claims description 17
- 239000002243 precursor Substances 0.000 claims description 12
- CNKHSLKYRMDDNQ-UHFFFAOYSA-N halofenozide Chemical compound C=1C=CC=CC=1C(=O)N(C(C)(C)C)NC(=O)C1=CC=C(Cl)C=C1 CNKHSLKYRMDDNQ-UHFFFAOYSA-N 0.000 claims description 7
- 238000005452 bending Methods 0.000 claims description 5
- 230000006835 compression Effects 0.000 claims description 5
- 238000007906 compression Methods 0.000 claims description 5
- 238000000926 separation method Methods 0.000 abstract description 11
- 230000003068 static effect Effects 0.000 abstract description 2
- 230000003993 interaction Effects 0.000 description 4
- 230000007812 deficiency Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 210000000867 larynx Anatomy 0.000 description 1
- 230000007257 malfunction Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The present invention provides a kind of air intake duct, dredging flow groove is opened up on the lip cover wall surface of the air intake duct, using wall surface static pressure difference inside and outside air intake duct lip cover, the separation packet under super rated condition in air intake duct lip cover is drawn into internal channel.The flow field control method can significantly widen normal work Mach number of the air intake duct under super rated condition.The configuration of the present invention is simple, it is easy to accomplish.Invention also provides the above-mentioned design methods widened air intake duct excess and determine free stream Mach number range.
Description
Technical field
The present invention relates to field of flight vehicle design, and in particular to the air intake duct used on a kind of aircraft.
The invention further relates to a kind of design methods widened air intake duct excess and determine free stream Mach number range.
Background technique
Air intake duct is that the component of air mass flow is provided for airbreathing motor, it must be supplied in entire working range
The quality of flow needed for engine and flow field, performance and delivery quality, to the overall performance of engine and entire aircraft
With important influence.In the air suction type supersonic aircraft design of wide Mach number work, Flight Vehicle Design horse is generallyd use
Conspicuous number is the sealing Mach number of air intake duct, i.e., the shock wave of air intake duct external compression section is before intersecting at lip cover just under designing Mach number
Edge.Therefore when aircraft free stream Mach number is higher than design Mach number, air intake duct is in super rated operation, precursor compressing surface
Shock wave intersect in advance and squeeze into inside lip cover, be easy to make lip cover under the Boundary Layer Interaction that intense shock wave and lip cover develop
Neighbouring boundary-layer separation, causes inlet total pressure loss to increase, can even deteriorate the stream for destroying entire air intake duct when serious
, it causes inoperative under air intake duct High Mach number.
The research discovery of German aerospace research center by using the mode of active suction can effectively reduce lip oblique shock wave with
The separation that the effect of precursor boundary-layer generates；Australian scholar has found in the works in HyShot, by opening up in air intake duct shoulder
The low energy fluid in precursor boundary-layer can be discharged for dredging flow groove, while can weaken lip using the dilatational wave at dredging flow groove turning and tiltedly swash
The intensity of wave can effectively reduce the size of separation packet, to improve the performance of air intake duct and engine；U.S. NASA etc. is directed to
Influence of the aerial drainage to shockwave boundary layer interaction has been carried out compared with in-depth study discovery, and aerial drainage can be effectively improved shock-boundary
Interference can reduce separation packet and even be eliminated.
Shockwave boundary layer interaction can be effectively improved really by studying the flow field controls such as discovery aerial drainage, suction from these, and be dropped
The self-starting Mach number of low air intake duct.But these methods have no for surpassing under rated condition before air intake duct precursor shock wave and lip cover
The separation of Shock Wave Boundary Layer produced by edge intersects and its research of caused inoperative problem.
Therefore the technical solution for needing one kind new is to solve the above problems.
Summary of the invention
To solve the above problems, the present invention provides a kind of rectangle single channel Supersonic Inlet.Air intake duct can be widened
Range of Mach numbers is flowed, and solves the problems, such as that slow channels starting performance is bad.
In order to achieve the above objectives, following technical solution can be used in air intake duct of the present invention:
A kind of air intake duct, including air intake duct main body, the air intake duct lip cover being mounted on the outside of air intake duct main body；The air intake duct
It is air intake duct internal channel between main body and air intake duct lip cover, offers dredging flow groove in the air intake duct lip cover, dredging flow groove connection
On the outside of lip cover and air intake duct internal channel, the air intake duct main body are equipped with connection air intake duct internal channel and prolong into air intake duct main body
The aerial drainage chamber stretched；The aerial drainage chamber is located at the venturi rear of air intake duct internal channel, and dredging flow groove is located at the larynx of air intake duct internal channel
In front of road.
The utility model has the advantages that air intake duct of the invention is using wall surface static pressure difference inside and outside air intake duct lip cover, by under super rated condition into
Air-flow separation packet in air flue lip cover draws internal channel by dredging flow groove.The flow field control method can significantly widen air intake duct super
Normal free stream Mach number under rated condition.The configuration of the present invention is simple, it is easy to accomplish.
The present invention also provides the design method that above-mentioned air intake duct excess determines free stream Mach number range, technical solutions are as follows:
The aerial drainage groove center is to the up-front distance of lip and precursor shock wave under super rated operation away to lip cover leading edge
The ratio of distance isIn super rated operation, makeMeanwhile making the width 1mm or more of dredging flow groove.
The utility model has the advantages that being under excess determines free stream Mach number state in the air intake duct, the setting of single dredging flow groove is existedPosition vent flow can be made to reach minimum.And the air intake duct is in excess and determines under free stream Mach number state, dredging flow groove
Width be 1mm or more when, air intake duct lip cover improvement isolated greatly, air intake duct can work normally.
Further, make the air intake duct that there is three stage compression face, when free stream Mach number is 3.5, venturi Mach 2 ship
1.689；When free stream Mach number is 4.5, venturi Mach 2 ship 1.849.
Detailed description of the invention
Fig. 1 is a kind of flow field control technical pattern schematic diagram for widening the super nominal working range of air intake duct.
Fig. 2 is the perspective view that lip cover opens up dredging flow groove.
Precursor shock wave structure figure when Fig. 3 is super rated operation.
Fig. 4 is the aerial drainage hundred that air intake duct dredging flow groove when free stream Mach number is respectively Ma3.5 and Ma4.5 is located at different location
Divide and compares statistical chart.
Fig. 5 is aerial drainage percentage of the air intake duct when free stream Mach number is respectively Ma3.5 and Ma4.5 under different in width dredging flow groove
Compare statistical chart.
The vent flow change curve statistics of Fig. 6 is free stream Mach number when being respectively Ma3.5 and Ma4.5 different angle dredging flow groove
Figure.
Specific embodiment
The present invention is described in further detail below in conjunction with the accompanying drawings.
As shown in Figs.1 and 2, the invention discloses a kind of air intake duct, including air intake duct main body 1, it is mounted on air inlet
The air intake duct lip cover 2 in 1 outside of road main body；It is air intake duct internal channel between the air intake duct main body 1 and air intake duct lip cover 2.It is described
Dredging flow groove 3 is offered in air intake duct lip cover 2, which is connected on the outside of lip cover and air intake duct internal channel.The air intake duct main body
The 1 aerial drainage chamber 5 for being equipped with connection air intake duct internal channel and extending into air intake duct main body.The aerial drainage chamber 5 is located in air intake duct
The venturi rear in channel, and dredging flow groove is located in front of the venturi of air intake duct internal channel.Wherein venturi be inlet passageway in most
Small flow area.
The air intake duct lip cover 2 includes continuing the lip cover main body 21 that extends forward and from 21 front end of lip cover main body to air intake duct
The bending part 22 of body side bending, the dredging flow groove are located on the bending part 22.
Wherein, carrying out widening air intake duct excess to determine the design method of free stream Mach number range for above-mentioned air intake duct is root
Free stream Mach number range, which is determined, according to the excess widened required for air intake duct determines aerial drainage groove location, aerial drainage groove width, dredging flow groove inclination
Three parameters of angle, as shown in fig.2, dredging flow groove is opened up with determining parameter at air intake duct lip cover corresponding position.Institute
State aerial drainage groove center to the up-front distance of lip with precursor shock wave under super rated operation away from the ratio to lip cover leading edge distance
ForIn super rated operation, makeMeanwhile making the width 1mm or more of dredging flow groove.
As shown in fig.3, air intake duct is fixed in excess when aircraft air intake duct free stream Mach number is higher than design Mach number
The oblique shock wave 7 of working condition, precursor compressing surface intersects in advance and squeezes into inside lip cover, has an intersection point 6 with lip cover.In intense shock wave
It separating with easily occurring boundary-layer under lip cover Boundary Layer Interaction in lip cover, pressure is larger after lip cover internal channel shock wave at this time, and
Pressure is smaller after shock wave outside lip cover, and there are pressure differences for the inlet and outlet in dredging flow groove channel, by internal channel low energy under the driving of pressure difference
Gas is discharged outside air intake duct, so that the separated region near lip cover reduces.When dredging flow groove channel, inlet outlet pressure differential deficiency causes to let out
When flow is inadequate, separation packet cannot be eliminated；But the separation packet after lip cover is once eliminate, in newly-established normal stream dredging flow groove off field
Less, the vent flow of lip cover dredging flow groove is smaller at this time for the inlet and outlet pressure difference in channel.
Application example
(1) technical indicator:
The flight Mach number for designing inlet operating condition is Ma3.5, and the flight Mach number of super rated operation is extremely
Ma4.5
(2) scheme introduction:
The two-dimensional supersonic inlet with three stage compression face is devised, when free stream Mach number is 3.5, three compressions
Wedge surface angle [alpha]1、α2、α3Respectively 4 °, 12 ° and 9 °, venturi Mach 2 ship 1.689；Precursor shock wave just seals at this time.Refering to figure
Shown in 3.When free stream Mach number is 4.5, venturi Mach 2 ship 1.849, precursor shock wave intersects and is incident in advance the air intake duct
Inside lip cover, with lip cover leading edge at a distance of l1At=11.5mm.Dredging flow groove is opened up in lip cover, can be compared point by numerical simulation
The aerodynamic characteristic of prototype air intake duct with the air intake duct for being equipped with dredging flow groove is analysed, and considers aerial drainage groove width, dredging flow groove tilt angle, lip
Influence of the cover outside angle to super rated operation air intake duct flow field.
(3) it is compared under super rated operation:
The design Mach 2 ship 3.5 of prototype air intake duct, when free stream Mach number is higher than 3.5, precursor shock wave intersects in advance and beats
Enter in lip cover.When free stream Mach number is 4.5, nearby there is large stretch of separated region in prototype air intake duct lip cover leading edge, destroys
The proper flow of air intake duct interior air-flow, flow field at this time are unstable.And the air intake duct of dredging flow groove is opened up in lip cover, incoming flow Mach
When number is 4.5, the separation at air intake duct lip cover disappears substantially.Illustrate to open up dredging flow groove in lip cover that can be effectively improved air intake duct super
Flow field under rated operation, air intake duct excess are determined free stream Mach number range and are significantly widened.
(4) lip cover aerial drainage groove location stream field influences comparison:
Aerial drainage groove width 3mm, perpendicular to inner wall, the dredging flow groove arrangement studied can make the separation near air intake duct lip cover
Region reduces, and air intake duct can work normally.Under the super rated condition of Ma0=4.5, the setting of single dredging flow groove is existed's
Position can make vent flow reach minimum.And when designing Mach number, vent flow increases with the up-front distance of dredging flow groove and lip cover
And it is increased slightly.
(5) lip cover aerial drainage groove width stream field influences comparison
The aerial drainage angle of the v-groove is vertical with air intake duct inner wall, and position is located atPlace, as shown in fig.4, in Ma0=4.5
Under the conditions of, vent flow is not obvious with the change width of dredging flow groove, and under the conditions of Ma0=3.5 dredging flow groove vent flow with
The increase of width and increase.As shown in fig.5, when aerial drainage groove width is 0.5mm, air intake duct is big under conditions of Ma0=4.5
Separating flowing field does not improve, air intake duct still cisco unity malfunction, and the width of dredging flow groove be 1mm or more when, air intake duct lip cover is big
Isolated improvement, air intake duct can work normally, and interior flow field is almost the same.
(6) lip cover dredging flow groove tilt angle stream field influences comparison
As shown in fig. 6, dredging flow groove is located atPosition, aerial drainage groove width be 3mm.When Ma0=4.5, it can be seen that
Influence of the aerial drainage angle of the v-groove to air intake duct flow field is smaller, and the dredging flow groove of each angle can make the normal work of air intake duct in research range
Make.The angle of dredging flow groove is affected to vent flow when designing Mach number, as the increase vent flow of γ reduces, when γ reaches
Vent flow is 0.39% at 135 °.
Claims (5)
1. a kind of air intake duct, including air intake duct main body, the air intake duct lip cover being mounted on the outside of air intake duct main body；The air intake duct master
It is air intake duct internal channel between body and air intake duct lip cover, which is characterized in that offer dredging flow groove in the air intake duct lip cover, this is let out
Chute is connected on the outside of lip cover and air intake duct internal channel, and the air intake duct main body is equipped with connection air intake duct internal channel and to air intake duct
The aerial drainage chamber extended in main body；
The aerial drainage chamber is located at the venturi rear of air intake duct internal channel, and dredging flow groove is located in front of the venturi of air intake duct internal channel.
2. air intake duct according to claim 1, it is characterised in that: the air intake duct lip cover includes the lip for continuing to extend forward
Cover main body and the bending part bent from lip cover body front end to air intake duct body side, the dredging flow groove are located on the bending part.
3. air intake duct according to claim 1, it is characterised in that: the aerial drainage chamber from air intake duct internal channel intersection to
Interior is in infundibulate.
4. a kind of air intake duct excess as described in claims 1 or 2 or 3 determines the design method of free stream Mach number range, feature exists
In: the aerial drainage groove center to the up-front distance of lip and precursor shock wave under super rated operation away to lip cover leading edge distance
Ratio isIn super rated operation, makeMeanwhile making the width 1mm or more of dredging flow groove.
5. design method according to claim 4, it is characterised in that: make the air intake duct that there is three stage compression face, incoming flow horse
When conspicuous number is 3.5, venturi Mach 2 ship 1.689；When free stream Mach number is 4.5, venturi Mach 2 ship 1.849.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810229568.9A CN108412617B (en) | 2018-03-20 | 2018-03-20 | A kind of air intake duct and widen the design method that air intake duct excess determines free stream Mach number range |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810229568.9A CN108412617B (en) | 2018-03-20 | 2018-03-20 | A kind of air intake duct and widen the design method that air intake duct excess determines free stream Mach number range |
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| Publication Number | Publication Date |
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| CN108412617A CN108412617A (en) | 2018-08-17 |
| CN108412617B true CN108412617B (en) | 2019-03-29 |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110486168B (en) * | 2019-09-18 | 2020-07-28 | 南京航空航天大学 | Binary supersonic inlet duct with step type side plate |
| CN111173618B (en) * | 2020-01-08 | 2022-06-10 | 南京航空航天大学 | Embedded air inlet channel with mouth surface vortex releasing groove |
| CN113464280B (en) * | 2021-07-29 | 2022-05-24 | 南京航空航天大学 | Controllable air inlet channel based on leakage gap switch and method |
| CN115585063B (en) * | 2022-12-12 | 2023-03-10 | 中国航空工业集团公司沈阳空气动力研究所 | Control system and method for stabilizing lip shock waves of supersonic air inlet channel |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101029597A (en) * | 2007-03-22 | 2007-09-05 | 南京航空航天大学 | Fixed geometrical supersonic-speed and high supersonic-speed adjusting air inlet |
| CN104863715A (en) * | 2015-04-16 | 2015-08-26 | 南京航空航天大学 | Binary hypersonic-velocity variable-geometry air inlet way with rectangular inlet, design method thereof and working method thereof |
| US9429071B2 (en) * | 2011-06-23 | 2016-08-30 | Continuum Dynamics, Inc. | Supersonic engine inlet diffuser with deployable vortex generators |
| CN106996334A (en) * | 2017-05-08 | 2017-08-01 | 北京航空航天大学 | Hypersonic gill formula becomes the multistage oblique shock wave system compression air intake duct of geometry |
| CN107191273A (en) * | 2017-06-15 | 2017-09-22 | 南京航空航天大学 | The continuously adjustabe air intake duct and control method of a kind of rigid/flexible combination regulation |
-
2018
- 2018-03-20 CN CN201810229568.9A patent/CN108412617B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101029597A (en) * | 2007-03-22 | 2007-09-05 | 南京航空航天大学 | Fixed geometrical supersonic-speed and high supersonic-speed adjusting air inlet |
| US9429071B2 (en) * | 2011-06-23 | 2016-08-30 | Continuum Dynamics, Inc. | Supersonic engine inlet diffuser with deployable vortex generators |
| CN104863715A (en) * | 2015-04-16 | 2015-08-26 | 南京航空航天大学 | Binary hypersonic-velocity variable-geometry air inlet way with rectangular inlet, design method thereof and working method thereof |
| CN106996334A (en) * | 2017-05-08 | 2017-08-01 | 北京航空航天大学 | Hypersonic gill formula becomes the multistage oblique shock wave system compression air intake duct of geometry |
| CN107191273A (en) * | 2017-06-15 | 2017-09-22 | 南京航空航天大学 | The continuously adjustabe air intake duct and control method of a kind of rigid/flexible combination regulation |
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Inventor after: Xie Lvrong Inventor after: Duan Xu Inventor after: Li Chenglong Inventor after: Wang Weixing Inventor after: Wang Kun Inventor after: Li Bo Inventor after: Liu Yu Inventor before: Xie Lvrong Inventor before: Li Chenglong Inventor before: Duan Xu Inventor before: Wang Weixing Inventor before: Wang Kun Inventor before: Li Bo Inventor before: Liu Yu |
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Granted publication date: 20190329 Termination date: 20210320 |