CN101392686A - Internal waverider hypersonic inlet and design method for giving attention to internal and external flow performance - Google Patents
Internal waverider hypersonic inlet and design method for giving attention to internal and external flow performance Download PDFInfo
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- CN101392686A CN101392686A CNA2008101558984A CN200810155898A CN101392686A CN 101392686 A CN101392686 A CN 101392686A CN A2008101558984 A CNA2008101558984 A CN A2008101558984A CN 200810155898 A CN200810155898 A CN 200810155898A CN 101392686 A CN101392686 A CN 101392686A
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Abstract
The invention provides an internal waverider-derived high speed inlet considering both internal flow performance and external flow performance and a design method thereof. The structure of the high speed inlet consists of a contraction section, an insulation section or an expansion section, wherein the contraction section of the high speed inlet is characterized by adopting three-dimensional inward contraction of a smooth curved surface. High speed incoming flow forms a curved surface shockwave at the inlet to close the inlet completely so as to realize that the inlet 'rides' on shockwave without overflow completely. The design method is to carry out flow line tracing by using a specific non-axisymmetric internally contracted basic flow field as a base to obtain downstream flow surface according to the given inlet shape, thereby obtaining a three-dimensional moulding surface of the internal waverider-derived high speed inlet. The non-axisymmetric internally contracted basic flow field can be obtained through performing gradual change based on the prior revolution surface along a circumferential contracting surface, and arranging a cylinder with specific radius on the axes. The internal waverider-derived high speed inlet and the method have the advantages that external flow resistance can be reduced more while ensuring high quality of internal flow, wide range of working mach number, strong counter pressure resistance and other performances of the internal flow.
Description
Technical field
What the present invention relates to is a kind of interior rider formula intake duct and design method thereof of taking into account inside and outside fluidity energy.Intake duct between flight Mach number 2.5～5 ultrasound velocity airbreathing propulsion system (inferior burning ramjet) and flight Mach number greater than the effect of the combination property that all improves a lot in 5 the hypersonic airbreathing propulsion system (scramjet engine).Rider formula intake duct design field in belonging to.
Background technique
The climax of pursuing two 3 (flying speed 3 overtone speed, flying height 3 myriametres) on the aeronautical technology development history is after period, and one period has been slowed down in the development of high-speed flight technology.Yet, high-speed flight becomes the emphasis of aeronautical technology development again over past ten years, especially independent pressed engine or comprise today of high speed power technology fast development of the combined engine of pressed engine, common ultrasound velocity (Supersonic) aircraft between the flight Mach number 2.5～5 and flight Mach number are greater than the representative of the advanced aeronautical technology of hypersonic (Hypersonic) aircraft appellation of 5, its development relates to national security and peaceful use space, is one of strategic emphasis of present international high technology competition.The high speed intake duct that is fit to these high-speed aircrafts is a key point of this class thrust power technology of development, and its effect improves and significantly strengthens with flying speed.Its design object is to be the high energy air-flow that the propulsion system parts in downstream provide coupling with less flow losses.From the technical standpoint analysis, the designing requirement of hypersonic inlet mainly contains following several respects: 1. inner flowing characteristic is good, when the air-flow that will be swallowed is compressed to required pressure ratio, should accomplish that efficient (outlet stagnation pressure) is high and the exit flow distortion is little; 2. outflow resistance is little, and this just requires, and inlet duct flow amount capture ability is strong, overflow is little; 3. the range of Mach numbers of working is wide, and inoperative phenomenon takes place because need prevent that intake duct venturi through-current capability when low mach is not enough, thus should be able to be under the situation of not using geometry deformation (can bring the complicated and weight increasing of mechanism) automatic overflow; 4. anti-back-pressure ability is good, can bear the force value that exceeds design back-pressure certain amplitude and be unlikely to take place inoperative phenomenon under the situation of generation pressure surges such as firing chamber, downstream.5. design proposal also should be structurally favourable to aircraft: size is as far as possible little, weight is light as far as possible, and this just requires geometrical construction to adopt simple fixed geometry as far as possible.
The hypersonic inlet form that has proposed at present mainly comprises: dualistic formula intake duct, axisymmetric intake duct, side pressure intake duct etc.Lot of domestic and foreign scholar has carried out extensive and deep research to their problem such as design method, flow performance, performance characteristic, Study on Engineering Design.In addition, over the past two years, the researcher had also proposed some novel advanced hypersonic inlet mentality of designing and schemes.As: the streamline traced hypersonic Busemann inlet that the Billig F.S of U.S. Johns Hopkins University etc. propose, adopt the streamline tracer technique, Busemann constant entropy intake duct is improved; " Funnel " type intake duct notion that the Ajay P.K. of U.S. Astrox company etc. propose is copied and is used conical flow to generate the thinking of rider body, uses the axisymmetric flow pattern of inside inflection to generate intake duct internal surface configuration.In the U.S.'s hypersonic propulsion system project of future generation, Hycause and FALCON aircraft also all intend adopting this type of to be called as three-dimensional interior intake duct form of shrinking.
Make a general survey of above all kinds of intake duct scheme, though they all have separately some advantages and characteristics, but still be faced with bigger technical difficulty, main problem is that 5 aspects of above-mentioned intake duct design usually require contradiction mutually, is difficult to satisfy simultaneously.Except that the anti-back-pressure ability of the 4th aspect the know-how guarantee is arranged and the contradictory relation that requires with other technologies relative simple, the requirement of several respects intricately weave in then in addition.Such as: to count ability to work be exactly a very serious contradiction with becoming M to decide geometry designs.In the existing typical intake duct, the side pressure intake duct can be realized under the situation of geometric fixation reducing with Mach number increases overflow automatically, can coordinate this contradiction (also therefore having obtained the attention of more domestic and international research) preferably.But this spillover very big (even design Mach number work also overflow 10～20%) will enlarge markedly the aircraft outflow resistance, and multishock complexity, shock wave/boundary layer are violent, so the exit flow quality is not high.In order to overcome these problems, the M.K.Smart in U.S. NASA Langley research center etc. has proposed the design concept of REST intake duct just, and the REST intake duct is actually the intake duct of contraction flow in a kind of the utilization.Its basic design philosophy is: in certain is specific in the compressional axis symmetric(al) flow, adopt the streamline tracing to make object plane according to the stream interface that needed intake duct import or export molded lines generates, and also can under fixed how much situations, possess wide preferably M and count ability to work, and exit flow performance and outflow resistance (design flight Mach number underflow stream 5%～10%) aspect all are better than the side pressure intake duct with the side pressure intake duct is the same.But the design method of this intake duct still can't realize not having fully overflow under design point.Because airflow kinetic energy is compared with other forms of energy (such as pressure potential) and is enlarged markedly during high-speed flight, so even the extrernal resistance increase that a spot of overflow causes also can be quite remarkable.
All kinds of high speed intake duct design proposals from present domestic and international other researchers' propositions of having reported, it is best relatively that the REST intake duct in U.S. NASA Langley research center can be taken into account the many-sided technical requirements of intake duct at last, but its technical order still also has improved necessity, is especially taking into account the high and little this respect of outflow resistance of intake duct flow field quality.
Summary of the invention
The present invention proposes to take into account the interior rider formula intake duct and the design method thereof of inside and outside fluidity energy, be intended to take into account better the many-sided technical requirements of intake duct, in guaranteeing intake duct in the performance such as strong, the geometric fixation of family status matter height, work range of Mach numbers wide, anti-back-pressure ability, reducing overflow as far as possible and being implemented in design point does not have overflow, reduces outflow resistance thereby take into account.
Technical solution of the present invention: the interior rider formula intake duct that can take into account inside and outside fluidity energy, its structure is to comprise that intake duct contraction section, distance piece are that hypersonic situation or extending section are common ultrasound velocity situation, and wherein the intake duct contraction section is characterized as and adopts the three-dimensional of smooth surface inwardly to shrink; The curved surface shock wave that the high speed incoming flow forms in inlet is three-dimensional inlet face complete closed, with realize import fully " taking " on shock wave and do not have an overflow.What realize that the raising of anti-back-pressure ability adopts is existing technology, and the air-flow after will compressing respectively by distance piece or extending section is sent into the firing chamber with ultrasound velocity or subsonic velocity.
Can take into account the interior rider formula intake duct design method of inside and outside fluidity energy, it is characterized in that by the streamline back tracking method one nonaxisymmetrical in contracted basic flow field cut out shock surface and the oral area molded lines that pastes mouthful by entry shape, and the stream interface that is developed downstream along this oral area molded lines; With the tube wall face of this stream interface as intake duct.
Advantage of the present invention: interior rider formula high speed intake duct is a kind of fixing how much intake ducts.The interior rider notion of using the present invention to propose designs, can guarantee that this intake duct catches the incoming flow flow fully and promptly do not have overflow under design point, thereby this just reduces to wind-exposuring area the minimum outflow resistance that reduces when guaranteeing to provide motor to need air-flow.Interior rider formula high speed intake duct can be adjusted overflow again automatically under the low mach situation, in the work range of Mach numbers of widening intake duct the overflow under these speed is significantly reduced.The moulding of intake duct contraction section is to be made of the smooth stream interface that is in the isentropic Compression part in the former basic flow field, inwardly shrinks compressed air stream by three-dimensional, can obtain higher compression efficiency and flow quality.Therefore, fluidity energy and reduce a plurality of technical requirementss such as outflow resistance in family status matter height in interior rider formula high speed intake duct can be taken into account well, work range of Mach numbers wide, anti-back-pressure ability are strong etc.
Description of drawings
Accompanying drawing 1 is a contracted basic flow field schematic representation in the axisymmetric.
Accompanying drawing 2 is contracted basic flow field schematic representation in the non-axisymmetric.
Accompanying drawing 3 is that the import windward side is trapezoidal interior rider formula high speed intake duct inlet/outlet shape schematic representation.
Accompanying drawing 4 is that the import windward side is trapezoidal interior rider formula high speed intake duct three-D profile schematic representation.
Among the figure 1 is expression ultrasound velocity incoming flow, the 2nd, represent to shrink in the specific non-axisymmetric revolution wall, the 3rd, expression axisymmetric centerbody (cylindrical body), the 4th, the pairing just round import molded lines of expression axisymmetric basic flow field, the 5th, the initial incident shock of expression basic flow field, the 6th, the reflected shock wave of expression basic flow field, the 7th, expression is flowed through certain point on the initial incident shock and is walked downstream streamline, the 8th, represent through the streamline that goes out after reflected shock wave and the turnover, the 9th, the non-circular import molded lines of constricting tube wall in the used axisymmetric of expression the present invention, the 10th, certain specific windward side profile of the intake duct import that design hope obtains, the intake duct import molded lines that 11 expressions intercept on the initial shock surface of basic flow field by the import profile, the 12nd, expression is followed the trail of the downstream stream interface that obtains along intake duct import molded lines with streamline, the 13rd, the expression windward side is trapezoidal interior rider formula high speed intake duct import ABCDE, the 14th, the expression windward side is trapezoidal interior rider formula high speed intake duct outlet abcde, the 15th, represent parabolical shoulder shape line a ' c ', the 16th, the flow-off DE of expression intake duct import bottom.
Embodiment
The contrast accompanying drawing, the interior rider formula intake duct of fluidity energy inside and outside can taking into account, its structure comprises intake duct contraction section, distance piece (hypersonic situation) or extending section (common ultrasound velocity situation).Wherein, emphasis of the present invention is the intake duct contraction section, and its three-dimensional of smooth surface formation that be shaped as inwardly shrinks.Compress in together on the curved surface shock wave by particular design technical guarantee intake duct under the design Mach number " taking ", shock wave pastes mouth and just can realize not having overflow like this.Inwardly shrinking the intake duct of design has higher efficient based on three-dimensional than the design proposal of conventionally form, and can reduce outlet distortion and ancient piece of jade, round, flat and with a hole in its centre face heat load.What realize that the raising of anti-back-pressure ability adopts is existing technology, and the air-flow after will compressing respectively by distance piece or extending section is sent into the firing chamber with ultrasound velocity or subsonic velocity.
The initial incident curved surface shock wave that described intake duct, high speed incoming flow form in inlet is three-dimensional inlet face complete closed, with realize import fully " taking " on shock wave and do not have an overflow.
Described intake duct, there is the overflow gap in its import Lower Half, this flow-off automatic overflow when flight Mach number is lower than the design Mach number, and the degree that reduces with flight Mach number is many more and overflow is big more, thereby solve the low mach lower inlet and catch the too much problem of flow, reach the purpose of widening intake duct work range of Mach numbers.
Can take into account the design method of the interior rider formula intake duct of inside and outside fluidity energy, be by the streamline back tracking method one nonaxisymmetrical in appropriate location in the contracted basic flow field by certain entry shape (windward side, be the dead ahead) cut out the shock surface and the oral area molded lines that paste mouthful, and the stream interface that is developed downstream along this oral area molded lines; With the tube wall face of this stream interface as intake duct.Nonaxisymmetrical interior contracted basic flow field used in the design is on the basis of contracted basic flow field in an axisymmetric, by on original turning surface basis, carrying out gradual change (radius increase or reduce) along circumferential contraction front, and arrange that at the place, axle center an adjustable cylinder of radius crosses strong problem in order to eliminate near place, axle center shock wave.Shrink wall in nonaxisymmetrical on the pairing section of each angle, except that inlet radius is variable, can also adjust the wall compression angle.Nonaxisymmetrical interior contracted basic flow field like this can provide than the more options space for the intake duct profile generates.Just form the lower wall surface of intake duct in the import molded lines near the stream interface that the bottom generated of this cylinder.
The supersonic speed incoming flow can form flow field structure as shown in Figure 1 in interior constricted channel, the together initial shock wave of formation also incides on the central cylinder, then forms reflected shock wave one.On initial shock wave, look for a bit all can following the trail of arbitrarily and obtain the streamline that this point sends downstream according to streamline.If the molded lines of a closure is set, then can follow the trail of a closed stream interface (promptly obtaining a stream pipe) that is sent downstream according to streamline on initial shock surface.The present invention adopts this basic fundamental in flow field shown in Figure 2, rider formula high speed intake duct in generating by certain technical requirements.
The basic flow field of designed use is to shrink flow field (shown in Figure 2) in the non-axisymmetric, forms by shrinking pipeline in axisymmetric cylindrical center and the non-axisymmetric.Constricting tube wall except that inlet radius is variable, can also be adjusted the wall compression angle in nonaxisymmetrical on the pairing section of each angle.What adopt the design of above Pneumatic method is interior rider formula intake duct under the no stick spare.On this basis, do not undertaken just having finished design work of the present invention after viscosity correction (biasing of boundary layer displacement thickness) and the shoulder fairing processing by intake duct there being the cementation wall.
Embodiment:
At the design flight Mach number is 5 situation, has designed contracted basic flow field in the non-axisymmetric as shown in Figure 2, and the section molded lines of interior contraction wall is a cubic curve, initial in angle of throat be 8 degree; Interior contraction conduit entrance is oval, and its semi-minor axis is littler by 15% than major semi axis size.The intake duct shaped design requires: the intake duct import is trapezoidal (see figure 3) in the windward side projection of shape, and trapezoidal two hypotenuses elongation line on the windward side is crossed the center of circle of cylindrical center's body.Accompanying drawing 4 is the three-D profiles that design this internal waverider hypersonic inlet that obtains.
Under the design point of incoming flow Mach number 5, the result of calculation of intake duct shows this routine design proposal when having obtained slightly above fluidity energy in other existing type intake ducts, and traffic capture coefficient 0.99 (being overflow about 1%) has greatly reduced outflow resistance.Formed one curved surface shock wave (see figure 4) of applying inlet side ABCDE in inlet, import is just taken advantage of on this curved surface shock wave; This shock wave forms one reflected shock wave and is positioned at DEa ' c ' in lower surface reflection back locates (see figure 4).Be lower than at 5 o'clock at supersonic speed incoming flow Mach number, the oral area shock wave breaks away from import, and unnecessary air-flow overflows (see figure 4) from the flow-off DE of intake duct import bottom, makes intake duct possess wide work range of Mach numbers.Generally speaking, this embodiment illustrates that designing technique of the present invention can reach the purpose of design of taking into account the inside and outside fluidity energy of intake duct.
In addition, the present invention also can be designed as other similar import and export shapes, and the foregoing description just is used for explanation of the invention, and can not be as limitation of the present invention.Therefore the mode of execution that mentality of designing every and of the present invention is identical is all in protection scope of the present invention.
Working principle of the present invention is: under design point, hypersonic air communication is crossed import and is entered intake duct.Interior rider formula intake duct generates these characteristics of moulding by the stream interface of basic flow field, the entry shape that can make air communication cross appointment generates specific oral area incident shock, in fact this shock wave is exactly to reappear the initial shock wave that generates in the used basic flow field of moulding, it can close three-dimensional inlet face just, has so just guaranteed that intake duct catches flow and all enter intake duct.The air-flow that enters intake duct converges to the center through the three-dimensional compression of interior contraction section, produces reflection at the intake duct lower surface.In fact reflected shock wave is exactly to reappear to generate the shock wave that reflects in the used basic flow field of moulding on central cylinder.The distance piece (or extending section) that air-flow behind the reflected shock wave enters the back again and connected.Be lower than under the design Mach number situation, intake duct oral area incident shock angle increases, and part is caught the automatic flow-off from the intake duct downside that fails to be convened for lack of a quorum and overflowed, and widens intake duct low mach ability to work.
Claims (4)
1, can take into account the interior rider formula intake duct of inside and outside fluidity energy, it is characterized in that comprising that intake duct contraction section, distance piece are that hypersonic situation or extending section are common ultrasound velocity situation, wherein the intake duct contraction section is characterized as and adopts the three-dimensional of smooth surface inwardly to shrink; The curved surface shock wave that the high speed incoming flow forms in inlet is three-dimensional inlet face complete closed, with realize import fully " taking " on shock wave and do not have an overflow;
2, the interior rider formula intake duct of taking into account inside and outside fluidity energy according to claim 1, it is characterized in that described three-dimensional inlet face: there is flow-off in its import Lower Half, function is an automatic overflow when flight Mach number is lower than the design Mach number, and overflow is big more with the degree that reduces is many more, thereby solve the low mach lower inlet and catch the too much problem of flow, reach the purpose of widening intake duct work range of Mach numbers.
3, the interior rider formula intake duct design method of taking into account inside and outside fluidity energy according to claim 1, it is characterized in that by the streamline back tracking method one nonaxisymmetrical in contracted basic flow field cut out shock surface and the oral area molded lines that pastes mouthful by entry shape, and the stream interface that is developed downstream along this oral area molded lines; Then with the tube wall face of this stream interface as intake duct.
4, the interior rider formula intake duct design method of taking into account inside and outside fluidity energy according to claim 3, it is characterized in that described nonaxisymmetrical interior contracted basic flow field is on the basis of contracted basic flow field in an axisymmetric, by contraction front circumferential in upper edge, original turning surface basis carry out gradual change, its radius, initial compression angle can be adjusted, and locate the adjustable cylinder of radius of layout to eliminate near the strong excessively problem of center shock wave in the axle center.
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| CNA2008101558984A CN101392686A (en) | 2008-10-15 | 2008-10-15 | Internal waverider hypersonic inlet and design method for giving attention to internal and external flow performance |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN102278232A (en) * | 2011-05-26 | 2011-12-14 | 南京航空航天大学 | Modified scramjet combustion chamber and design method of swirler thereof |
| CN103174520A (en) * | 2013-04-03 | 2013-06-26 | 南京航空航天大学 | Subsonic outflowing high external pressure internal waverider type air inlet and designing method thereof |
| CN103538727A (en) * | 2013-09-30 | 2014-01-29 | 中国人民解放军国防科学技术大学 | Method for designing pneumatic layout of axial-symmetry air-breathing hypersonic aircraft |
| CN104908957A (en) * | 2015-06-12 | 2015-09-16 | 南京航空航天大学 | Ridge type sweeping vortex generator and generation method |
| CN104912667A (en) * | 2015-06-10 | 2015-09-16 | 西北工业大学 | Design method of hypersonic speed internal-contraction air inlet channel carried out in steps |
| CN106741976A (en) * | 2017-01-11 | 2017-05-31 | 中国人民解放军63820部队吸气式高超声速技术研究中心 | A kind of mimetic design method of waverider forebody derived air intake duct integration configuration |
| CN109026442A (en) * | 2018-09-27 | 2018-12-18 | 北京理工大学 | Shock wave lures burning ramjet and shock wave to lure combustion punching press starting method |
| CN109455309A (en) * | 2018-11-19 | 2019-03-12 | 厦门大学 | Rider air intake duct integrated design method in sweepforward based on circular cone precursor shock wave |
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2008
- 2008-10-15 CN CNA2008101558984A patent/CN101392686A/en active Pending
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102278232A (en) * | 2011-05-26 | 2011-12-14 | 南京航空航天大学 | Modified scramjet combustion chamber and design method of swirler thereof |
| CN102278232B (en) * | 2011-05-26 | 2014-05-28 | 南京航空航天大学 | Modified scramjet combustion chamber and design method of swirler thereof |
| CN103174520A (en) * | 2013-04-03 | 2013-06-26 | 南京航空航天大学 | Subsonic outflowing high external pressure internal waverider type air inlet and designing method thereof |
| CN103538727A (en) * | 2013-09-30 | 2014-01-29 | 中国人民解放军国防科学技术大学 | Method for designing pneumatic layout of axial-symmetry air-breathing hypersonic aircraft |
| CN104912667A (en) * | 2015-06-10 | 2015-09-16 | 西北工业大学 | Design method of hypersonic speed internal-contraction air inlet channel carried out in steps |
| CN104908957A (en) * | 2015-06-12 | 2015-09-16 | 南京航空航天大学 | Ridge type sweeping vortex generator and generation method |
| CN106741976A (en) * | 2017-01-11 | 2017-05-31 | 中国人民解放军63820部队吸气式高超声速技术研究中心 | A kind of mimetic design method of waverider forebody derived air intake duct integration configuration |
| CN109026442A (en) * | 2018-09-27 | 2018-12-18 | 北京理工大学 | Shock wave lures burning ramjet and shock wave to lure combustion punching press starting method |
| CN109455309A (en) * | 2018-11-19 | 2019-03-12 | 厦门大学 | Rider air intake duct integrated design method in sweepforward based on circular cone precursor shock wave |
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