CN108301926A - A kind of hypersonic convex turns round contract air intake duct and its design method - Google Patents
A kind of hypersonic convex turns round contract air intake duct and its design method Download PDFInfo
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- CN108301926A CN108301926A CN201810018510.XA CN201810018510A CN108301926A CN 108301926 A CN108301926 A CN 108301926A CN 201810018510 A CN201810018510 A CN 201810018510A CN 108301926 A CN108301926 A CN 108301926A
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- convex
- intake duct
- air intake
- round
- inlet
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- 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
- F02C7/042—Air intakes for gas-turbine plants or jet-propulsion plants having variable geometry
Abstract
The invention discloses a kind of hypersonic convexs to turn round contract air intake duct and its design method, including：The lip plate middle part that the convex turns round air intake duct is provided with convex part, and entrance shape is in convex, and is shunk to exit and fade to circle, is then connected with the circular section isolator of homalographic；By the method for characteristic curves obtain the controllable inner conical surface of compressing surface Mach number, etc. flow angles variable cross-section centerbody and benchmark flow field, reverse streamlined impeller is carried out according to air intake duct round exit；Convex part is added on the basis of original rectangle and extends at centerbody for inlet, and then is matched to the natural outlet area that male inlet streamlined impeller goes out, and obtains the round exit of homalographic；After carrying out streamline fitting, boundary layer correction, obtains final convex and turn round air intake duct.The present invention significantly improves contract intake duct starting problem under the premise of ensureing the sealing of design point shock wave by the convex-shaped overflow means of streamlined impeller Technology design.
Description
Technical field
The present invention relates to a kind of hypersonic convexs to turn round contract air intake duct and its design method, belongs to hypersonic
Air intake duct technical field.
Background technology
Scramjet engine technology is the third in mankind's aviation history after the aircraft of Lai Te brothers, jet-propulsion
Secondary revolution.It is empty that this propulsion device or the combined type propulsion device based on this propulsion device utilize air intake duct to compress
Gas, the flow field that enough air and qualification are provided for engine combustion.
The good and bad normal work for scramjet engine and entire aircraft of hypersonic inlet performance is all
It is vital.Lightweight construction, compression efficiency are high, hinder in addition to that should have for one good hypersonic inlet of design
Power is small, the air-flow of combustion chamber is supplied to have outside the requirements such as high-quality, and also requirement can be started reliably.Once air intake duct cannot rise
Dynamic, engine will lose thrust, and even result in aircraft therefore and crash.Therefore, starting performance is that hypersonic inlet is
To entire engine health, the premise and basis of reliably working.
Hypersonic inlet includes binary plane compression air intake duct, binary axialsymmetrical inlet, three-dimensional side pressure air intake duct
Type, wherein inside rotating into the compression efficiency of air flue, to be recognized be highest.However, currently, interior rotate into air flue because of starting performance
It is poor and influence it and go further to apply.
In order to solve the starting problem of air intake duct, multiple technologies scheme is explored both at home and abroad and is asked to solve the starting of air intake duct
Topic.
(1) geometry regulation technology
Geometry regulation technology can be main to ask by changing contract than realizing the starting of air intake duct and restarting
Topic is that geometry regulating mechanism is excessively complicated, heavy.Increase the deadweight of aircraft.For hypersonic aircraft, also relate to
The problems such as thermal protection of regulating mechanism and geometry seal.
(2) flowing control
Flowing control includes the passive removal in boundary layer, actively the methods of blowing, absorption and jet vectoring.Wherein, air blowing class
Flowing control needs special high pressure compressing device and control piper, boundary-layer that class control method is sucked out and loses flow.This two class
The maximum problem of flowing control is that the position of flowing control is fixed, once air intake duct be absorbed in it is inoperative after, the position of flowing control
Setting may be extremely inefficient.
(3) geometry designs
The inoperative basic reason of supersonic speed/hypersonic inlet is the flow and air intake duct larynx that air intake duct capture is come in
Contradiction between the negotiability in road.Therefore, it is cleverly designed by some, both can guarantee stream of the air intake duct under High Mach number
Amount is captured and compressed performance, and can improve the starting characteristic of air intake duct on the basis of reasonable overflow.The pass of this design philosophy
Key is that overflow falls into air flue theoretically and cannot circulate " extra " flow, scientifically and rationally coordinates the capture and circulation of air intake duct
Ability.For opposite geometry is adjustable, this mode does not need any regulating mechanism.
Invention content
Goal of the invention：In order to overcome the deficiencies in the prior art, the present invention to provide a kind of hypersonic convex turn circle
Shape contract air intake duct and its design method pass through streamlined impeller Technology design under the premise of ensureing the sealing of design point shock wave
Convex-shaped overflow means significantly improve contract intake duct starting problem, realizing also can self-starting in more low mach
Target.
Technical solution：To achieve the above object, the technical solution adopted by the present invention is：
A kind of round contract air intake duct of hypersonic convex turn, including convex turn the directly isolation of round air intake duct and circle etc.
Section；
Wherein, it includes inlet lip plate, air intake duct side plate and air intake duct top plate that the convex, which turns round air intake duct, and into
It is provided with convex part in the middle part of air flue lip plate；The convex turns the entrance shape of round air intake duct similar to convex, and to outlet
Place, which is shunk, fades to circle, then connects with the round isolator of homalographic.
A kind of round contract Design of Inlet method of hypersonic convex turn, including：It can obtaining compressing surface Mach number
Behind the inner conical surface of control, the centerbody configuration of variable cross section and benchmark flow field, reverse streamline is carried out according to air intake duct round exit and is chased after
Track；Then convex part is added on the basis of original rectangle capture face in inlet, and it is made to extend at centerbody, constitutes convex
Import, and then streamlined impeller acquisition nature discharge area is carried out to male inlet and is matched, obtain the round conduct of homalographic
Final outlet shapes；After carrying out streamline fitting, boundary layer correction, obtains final convex and turn round air intake duct air-driven type face.
Further, by the method for characteristic curves obtain the controllable inner conical surface of the compressing surface Mach number, etc. flow angles variable cross-section
The centerbody configuration of design and benchmark flow field.Wherein, etc. flow angles, which become centerbody design, so that incident shock is beaten after lip
Realize reflected shock wave disperse, to improve shock loss caused by total pressure recovery.
Due to being the contract air intake duct directly tracked out in benchmark flow field, present invention incident shock under design point
It can realize that sealing, incident shock are just beaten at the lip of convex operative tip, be not in discharge coefficient loss, then carry out
Normal shock wave reflection, and off design point is due to the presence of the convex shape of entrance, effect, which is equal to, carries out lip fluting, increases
Degree of overflow achievees the effect that reduce self-starting Mach number.
Advantageous effect：A kind of hypersonic convex provided by the invention turns round contract air intake duct and its design method,
Compared with the existing technology, it has the following advantages：Improve contract intake duct starting problem based on geometry designs means, in high Mach
Shock wave realizes sealing under number design point, and increasing degree of overflow under low mach off design point prevents venturi to be jammed, that is, is protecting
Under the premise of demonstrate,proving the sealing of design point shock wave, by the convex-shaped overflow means of streamlined impeller Technology design, interior receipts are reduced
It is retracted the self-starting Mach number of air flue, while ensure that discharge coefficient meets the requirements, has reached solution contract intake duct starting
The target of problem.
Description of the drawings
Fig. 1 is the structural schematic diagram that a kind of hypersonic convex of the present invention turns round contract air intake duct；
Fig. 2 is the front view that a kind of hypersonic convex of the present invention turns round contract air intake duct；
Fig. 3 is the vertical view that a kind of hypersonic convex of the present invention turns round contract air intake duct；
Fig. 4 is the side view that a kind of hypersonic convex of the present invention turns round contract air intake duct；
Fig. 5 is the left view that inlet and outlet convex turns circular cross-section gradual change benchmark flow field in the present invention；
Fig. 6 is the perspective view that inlet and outlet convex turns circular cross-section gradual change benchmark flow field in the present invention；
Figure includes：1, convex turns round air intake duct, 2, round isolator, 3, male inlet, 4, air intake duct it is round
Outlet, 5, inlet lip plate, 6, air intake duct side plate, 7, air intake duct top plate, 8, benchmark flow field centerbody, 9, benchmark flow field inlet
Locate centerbody cross-section, 10, benchmark flow field exit centerbody cross-section, 11, benchmark flow field inlet section, 12, benchmark flow field exits
Section, 13, distance piece round exit, 14, benchmark flow field incident shock face, 15, benchmark flow field reflected shock wave face.
Specific implementation mode
The present invention is further described below in conjunction with the accompanying drawings.
Be as shown in Figure 1,2,3, 4 that a kind of hypersonic convex turns round contract air intake duct, including convex turn it is round into
Air flue 1 and round isolator 2；
Wherein, the round air intake duct 1 of the convex turn includes inlet lip plate 5, air intake duct side plate 6 and air intake duct top plate 7,
And 5 middle part of inlet lip plate is provided with convex part；The convex turns the entrance shape of round air intake duct 1 similar to convex, and
It is shunk to exit and fades to circle, then connected with the round isolator 2 of homalographic.
It is that a kind of hypersonic convex turns round contract Design of Inlet method as shown in Figure 5,6, air intake duct captures face
The convex shape constituted for " rectangle+convex slit ".From fig. 5, it can be seen that entrance male inlet 3 extends at centerbody 9.
The convex shape that " rectangle+convex slit " is constituted intersects along flow direction projection with the curved shock face in benchmark flow field, including
The male inlet molded line of air intake duct including male inlet 3；
A series of streamline races that streamlined impeller acquisition is carried out to male inlet 3, carry out inverse further according to air intake duct round exit 4
Another streamline race is obtained to streamlined impeller.Using section transition techniques, using transition function f (x)=x by Liang Zu streamlines race again
Fitting, obtains that import section is convex, outlet is circular contract hypersonic inlet without viscous configuration.Due to boundary
Layer presence, need carry out boundary layer viscous correction, by without glue type face on the basis of, retire outward boundary layer thickness away from
From, finally obtain convex turn circular hypersonic inlet air-driven type face 1.
Wherein, the streams such as inner conical surface can be used to design along the controllable method of characteristic curves of journey Mach Number Distribution and obtain, and centerbody uses
Dynamic angle mimetic design obtains.Inner conical surface and centerbody configuration are not only obtained by the method for characteristic curves, while obtaining benchmark flow field result.Institute
The convex part wall for stating convex capture cross section gradually turns round along flow direction development, finally develops into the top circle of round exit
Arc shape realizes that convex turns circular section progressive formation.
The male inlet 3 of the air intake duct and the shape of round exit 4 are fully controllable, including male inlet area, convex
Partial width and height and discharge area, these parameters can be according to the specific traffic capture demands of specific air intake duct come really
It is fixed.Disengaging mouth-shaped can be adjusted flexibly as needed, minimize the error that type face gradation zone comes, met the requirements
Male inlet and round exit size.By the cleverly design to convex overflow window, may be implemented in wide operating range
Minimum flow loss cost is paid, realizes that air intake duct starts reliable and securely under low mach.
Due to the sealing design used in design point design time-histories sequence, thus the present invention may be implemented under design point
Shock wave seals, i.e., incident shock is just beaten at the lip on convex shape top, to ensure that air intake duct exists to the maximum extent
The traffic capture special efficacy of design point.In low mach off design point, since Angle of Shock Waves increases, convex as Mach number reduces
The intersection part (overflow launder in Fig. 1 and Fig. 3 after lip) of the convex part of capture cross section and benchmark flow shock wave, effect etc.
It is same as carrying out lip fluting, has rationally overflowed the intransitable excess traffic of inlet throat, reach and reduce self-starting Mach number,
Improve the effect of starting performance.
The above is only a preferred embodiment of the present invention, it should be pointed out that：For the ordinary skill people of the art
For member, various improvements and modifications may be made without departing from the principle of the present invention, these improvements and modifications are also answered
It is considered as protection scope of the present invention.
Claims (3)
1. a kind of hypersonic convex turns round contract air intake duct, which is characterized in that including convex turn round air intake duct (1) and
Round isolator (2)；
Wherein, it includes inlet lip plate (5), air intake duct side plate (6) and air intake duct top plate that the convex, which turns round air intake duct (1),
(7), and in the middle part of inlet lip plate (5) it is provided with convex part；The convex turns the entrance shape of round air intake duct (1) in convex
Shape, and shunk to exit and fade to circle, then connect with the round isolator of homalographic (2).
2. a kind of hypersonic convex turns round contract Design of Inlet method, which is characterized in that obtaining compressing surface Mach
Behind the controllable inner conical surface of number, the centerbody configuration of variable cross section and benchmark flow field, carried out according to air intake duct round exit (4) reverse
Streamlined impeller；Convex part is then added on the basis of rectangle capture face and it is made to extend at centerbody for inlet, constitutes convex
Shape import (3), and then streamlined impeller acquisition nature discharge area is carried out to male inlet (3) and is matched, obtain homalographic
Circle is as final outlet shapes；After carrying out streamline fitting, boundary layer correction, obtains final convex and turn round air intake duct
(1) air-driven type face.
3. a kind of hypersonic convex according to claim 2 turns round contract Design of Inlet method, feature exists
In, by the method for characteristic curves obtain the controllable inner conical surface of the compressing surface Mach number, etc. flow angles variable cross-section design centerbody structure
Type and benchmark flow field.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810018510.XA CN108301926B (en) | 2018-01-09 | 2018-01-09 | Hypersonic convex-to-circular inner contraction air inlet channel and design method thereof |
Applications Claiming Priority (1)
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|---|---|---|---|
| CN201810018510.XA CN108301926B (en) | 2018-01-09 | 2018-01-09 | Hypersonic convex-to-circular inner contraction air inlet channel and design method thereof |
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| CN108301926A true CN108301926A (en) | 2018-07-20 |
| CN108301926B CN108301926B (en) | 2020-06-09 |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108999704A (en) * | 2018-08-17 | 2018-12-14 | 中国人民解放军国防科技大学 | Hypersonic air inlet starting method and starting device |
| CN109214061A (en) * | 2018-08-10 | 2019-01-15 | 西安理工大学 | A kind of scramjet engine distance piece section gradual change optimum design method |
| CN109488459A (en) * | 2018-09-29 | 2019-03-19 | 南京航空航天大学 | Rotatable air intake duct and aircraft in the hypersonic three-dimensional of one kind |
| CN110925091A (en) * | 2019-11-07 | 2020-03-27 | 南京航空航天大学 | Design method of non-axisymmetric generalized inner cone reference flow field for high-super internal rotation type air inlet |
| CN110985208A (en) * | 2019-12-16 | 2020-04-10 | 南京航空航天大学 | Internal rotation type air inlet channel assembly based on plasma vortex generator and control method |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB885661A (en) * | 1959-06-19 | 1961-12-28 | Power Jets Res & Dev Ltd | Intakes for supersonic flow |
| CN102518517A (en) * | 2011-12-08 | 2012-06-27 | 南京航空航天大学 | Bistable air inlet, its application as aircraft air inlet and design method of bistable air inlet |
| CN104895676A (en) * | 2015-04-14 | 2015-09-09 | 中国科学院力学研究所 | High supersonic speed variable cross section air intake duct and design method thereof |
| CN105151306A (en) * | 2015-09-29 | 2015-12-16 | 厦门大学 | Method of integrally designing forebody and air intake duct of cone configuration hypersonic flight vehicle |
| CN105667811A (en) * | 2016-01-27 | 2016-06-15 | 南京航空航天大学 | Design method for multi-stage coupling integrated structure of front body and air inflow channel of hypersonic aircraft |
-
2018
- 2018-01-09 CN CN201810018510.XA patent/CN108301926B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB885661A (en) * | 1959-06-19 | 1961-12-28 | Power Jets Res & Dev Ltd | Intakes for supersonic flow |
| CN102518517A (en) * | 2011-12-08 | 2012-06-27 | 南京航空航天大学 | Bistable air inlet, its application as aircraft air inlet and design method of bistable air inlet |
| CN104895676A (en) * | 2015-04-14 | 2015-09-09 | 中国科学院力学研究所 | High supersonic speed variable cross section air intake duct and design method thereof |
| CN105151306A (en) * | 2015-09-29 | 2015-12-16 | 厦门大学 | Method of integrally designing forebody and air intake duct of cone configuration hypersonic flight vehicle |
| CN105667811A (en) * | 2016-01-27 | 2016-06-15 | 南京航空航天大学 | Design method for multi-stage coupling integrated structure of front body and air inflow channel of hypersonic aircraft |
Non-Patent Citations (1)
| Title |
|---|
| 王扬，杨立军: "《飞行器制造工艺与装备》", 30 June 2015, 哈尔滨工业大学出版社 * |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109214061A (en) * | 2018-08-10 | 2019-01-15 | 西安理工大学 | A kind of scramjet engine distance piece section gradual change optimum design method |
| CN109214061B (en) * | 2018-08-10 | 2019-08-16 | 西安理工大学 | A kind of scramjet engine distance piece section gradual change optimum design method |
| CN108999704A (en) * | 2018-08-17 | 2018-12-14 | 中国人民解放军国防科技大学 | Hypersonic air inlet starting method and starting device |
| CN109488459A (en) * | 2018-09-29 | 2019-03-19 | 南京航空航天大学 | Rotatable air intake duct and aircraft in the hypersonic three-dimensional of one kind |
| CN110925091A (en) * | 2019-11-07 | 2020-03-27 | 南京航空航天大学 | Design method of non-axisymmetric generalized inner cone reference flow field for high-super internal rotation type air inlet |
| CN110925091B (en) * | 2019-11-07 | 2021-06-22 | 南京航空航天大学 | Design method of non-axisymmetric generalized inner cone reference flow field for high-super internal rotation type air inlet |
| CN110985208A (en) * | 2019-12-16 | 2020-04-10 | 南京航空航天大学 | Internal rotation type air inlet channel assembly based on plasma vortex generator and control method |
| CN110985208B (en) * | 2019-12-16 | 2021-09-24 | 南京航空航天大学 | Internal rotation type air inlet channel assembly based on plasma vortex generator and control method |
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| CN108301926B (en) | 2020-06-09 |
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