CN101029597A - Fixed geometrical supersonic-speed and high supersonic-speed adjusting air inlet - Google Patents
Fixed geometrical supersonic-speed and high supersonic-speed adjusting air inlet Download PDFInfo
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- CN101029597A CN101029597A CN 200710021005 CN200710021005A CN101029597A CN 101029597 A CN101029597 A CN 101029597A CN 200710021005 CN200710021005 CN 200710021005 CN 200710021005 A CN200710021005 A CN 200710021005A CN 101029597 A CN101029597 A CN 101029597A
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- intake duct
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- 230000006835 compression Effects 0.000 claims description 20
- 238000007906 compression Methods 0.000 claims description 20
- 238000002604 ultrasonography Methods 0.000 claims description 13
- 230000000087 stabilizing effect Effects 0.000 claims description 6
- 239000012530 fluid Substances 0.000 abstract description 5
- 239000000284 extract Substances 0.000 abstract description 3
- 230000001105 regulatory effect Effects 0.000 description 6
- 230000007423 decrease Effects 0.000 description 2
- 230000008676 import Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000011084 recovery Methods 0.000 description 2
- 230000035939 shock Effects 0.000 description 2
- 238000013459 approach Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 230000001276 controlling effect Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005672 electromagnetic field Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000005284 excitation Effects 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 238000004064 recycling Methods 0.000 description 1
- 239000004576 sand Substances 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 239000004577 thatch Substances 0.000 description 1
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Abstract
This invention provides a constant geometrical supersonic and hypersonic speed adjustable inlet channel which has fixed geometrical shape and simple structure and can adjust the wave system and the effective passage throat area in the inlet channel. Its features lie in that it includes the inlet channel subject, liplike cap, pipeline, valve, porous or multi-crevicel plate, stabilized voltage tune, water-spreading plate and tune. It extracts a small quantity of relatively high pressure secondary fluid through the water-spreading plate and tune fixed in the high-pressure area of the inner inlet channel. The fluid is then carried through the pipe to the stabilized voltage tune fixed in the all-level constricted sloping plate of the inlet channel subject. After that it pours along the distribution and preinstalled way in the flow field of the inlet channel through the porous or multi-crevice plate which achieves the real-time adjustment of the wave system and the effective passage throat area in the trophy of the inlet channel. The merits of this invention are not only the high resistance value in the wide Mach number, the low coefficient of drag relative to the conventional inlet channel, but also the fixed geometrical shape, simple structure and being apt to achieve.
Description
Technical field
The present invention relates to a kind of ultrasound velocity, hypersonic inlet, but particularly a kind of to import wave system, the effective equal real-time regulated of throat area, and geometrical shape is fixed, fixed how much ultrasound velocitys simple in structure, hypersonic variable geometry inlet.
Background technique
As one of three big parts of pressed engine, ultrasound velocity, hypersonic inlet are directly towards the firing chamber, bearing catch incoming flow and to incoming flow slow down, multinomial function such as supercharging, rectification, thereby its design is quite crucial, and its traffic capture characteristic, total static pressure recovery characteristics and drag characteristic etc. directly affect the working efficiency and the service requirement of propulsion system.At present, it is generally acknowledged that the flow coefficient of intake duct is the most direct to the influence of pressed engine thrust, the increase of flow coefficient promptly corresponding the increase in proportion of motor power.Yet unfortunately, for deciding for the wide Mach of geometry ultrasound velocity, the hypersonic inlet of conventional design, when being operated in the decline highly significant that wave system seals Mach number its flow coefficient when following, and be accompanied by insufferable spillage drag, binary hypersonic inlet flow coefficient when Mach 5 is worked as certain Mach 6 design has just dropped to 0.73, obviously this is seriously restricting the performance of propulsion system performance, and is particularly totally unfavorable to the accelerating process of the low Mach of aircraft.For this reason, the flow coefficient of raising intake duct is very crucial.
For the import wave system of intake duct is controlled to improve its flow coefficient, adopting more technological approaches at present is specialized agency to be set make the geometrical shape of intake duct adjustable, as ATREX center cone adjustable positions intake duct, HYPR umbrella intake duct and the axial variable geometry inlet of compressing surface, the adjustable axialsymmetrical inlet of multistage disk of Japan, how much intake ducts of the GTK semicircle deformation of the U.S. etc.It is long-pending to control object plane geometric parameter and throatpiston mechanically, become how much intake ducts and can carry out real-time regulated oral area wave system and contraction ratio, so can in comparatively broad range of Mach numbers, obtain higher flows coefficient and total pressure recovery performance, but its cost of paying also is quite expensive: weight increases, complex structure, the useful space descends, and reliability reduces, and has a series of problems such as control, obturage.
The magnetic control intake duct that people such as Russia scholar Fraishtadt, Kuranov propose is the hypersonic variable geometry inlet of studying at present of class new ideas, its thought is to utilize the existing or made plasma ambient of incoming flow, in the additional magnetic field of intake duct oral area, change airflow direction by long-range navigation thatch power, thereby realize control intake duct oral area wave system.The great advantage of magnetic control intake duct is that the geometrical shape of intake duct fixes.Yet, because isolated plants such as excitation of plasma device, controllable electromagnetic field generator, energy accumulator, enegrgy converter need be set, adopt after this technology the obtainable net profit of institute on earth how, be still a query at present.In addition, the stack of high magnetic fields brings immeasurable negative effect may for the aspects such as guidance, communication of aircraft.
Summary of the invention
1, goal of the invention: need to dispose the deficiency that complicated supporting facility maybe needs to rotate the compressing surface swash plate in the existing variable geometry inlet in order to solve, the invention provides a kind of fixed how much ultrasound velocitys, hypersonic variable geometry inlet, this variable geometry inlet geometrical shape is fixed, simple in structure, need not any actuator, also need not the high-pressure air source of adding, only the aperture that is arranged on valve in the intake duct main body by change can realize the intake duct oral area wave system and the effective real-time regulated of throat area, make intake duct oral area wave system under different Mach number, all keep sealing, thereby obtain high flow coefficient.
2, technological scheme: a kind of fixed how much ultrasound velocitys of the present invention, hypersonic variable geometry inlet, it comprises intake duct main body and intake duct lip cover, it is characterized in that: be installed in the porous on the intake duct main body external compression inclined-plane or stitch plate more and link to each other by an end that is arranged on the pipeline in pressure stabilizing cavity and the intake duct main body in the external compression inclined-plane, the valve of adjusting the secondary flow flow is installed on the pipeline, and the pipeline the other end links to each other with dumping-guiding plate in being installed in the intake duct zone of high pressure by drainage lumens.
According to different design needs, external compression inclined-plane that can the intake duct main body is set to 1～4 grade, and promptly the external compression inclined-plane is that an inclined-plane constitutes or constantly increases the inclined-plane by 2～4 continuous and inclination angles and constitutes.
In order to obtain regulating effect preferably and to reduce the pitot loss of intake duct, with porous or stitch the front end that plate is installed in intake duct main body external compression at different levels inclined-plane more.
Working principle of the present invention is: by being arranged on dumping-guiding plate and the drainage lumens in the intake duct internal high pressure district, in intake duct, extract the higher relatively a secondary fluid of a spot of pressure, and through line transportation to the pressure stabilizing cavity that is arranged in the intake duct main body slant compression plates at different levels, then by porous or stitch plate more and distribute in default mode with along journey and inject in the intake duct flow field.Because the injection of secondary flow has brought associated mass and turbulence loss, make near the negotiability of the main flow of intake duct flow field internal face constantly weaken, main flow is forced to toward the direction deflection of leaving wall, produce the shock wave that a branch of weak compressional wave and victim compression face send, make it outwardly-bent, so can control the relative position of oral area multishock and inlet lip.In addition, because the secondary flow of extracting from the intake duct zone of high pressure has been injected in the intake duct flow field again at the front end of compressing surfaces at different levels, that is to say that this part fluid is to recycle, but occupied certain venturi circulation area, the flow of therefore controlling secondary flow is effective venturi circulation area of may command intake duct also.
3, beneficial effect: fixed how much ultrasound velocitys, hypersonic variable geometry inlets of the present invention not only have high flow coefficient in the range of Mach numbers of broad, the forebody drag coefficient also significantly is lower than conventional intake duct, and have geometrical shape fix, simple in structure, be easy to advantages such as realization.
Description of drawings
Accompanying drawing is the structural representation that the present invention has 2 grades of external compression face intake ducts.
Embodiment
The invention will be further described below in conjunction with accompanying drawing.
As Fig. 1, these fixed how much ultrasound velocitys, the involved component names of hypersonic variable geometry inlet comprise intake duct main body 1, intake duct lip cover 2, pipeline 3, valve 4, porous or stitch plate 5, pressure stabilizing cavity 6, dumping-guiding plate 7 and drainage lumens 8 more; Intake duct main body 1 is 2 grades of external compression inclined-planes, and promptly the external compression inclined-plane constitutes by two sections inclined-planes are continuous.With two porous or stitch the front end that plate 5 is installed in two external compression inclined-planes more, and the pressure stabilizing cavity 6 by separately and pipeline 3 link to each other with drainage lumens 8 with dumping-guiding plate 7 in being arranged on the intake duct zone of high pressure respectively, and the valve 4 of regulating the secondary flow flow all is installed on pipeline 3 separately.By being arranged on dumping-guiding plate 7 and the drainage lumens 8 in the intake duct internal high pressure district, in intake duct, extract the higher relatively a secondary fluid of a spot of pressure, and in pipeline 3 is delivered to the pressure stabilizing cavity 6 that is arranged in the intake duct main body slant compression plates at different levels, then by porous or stitch plate 5 more and distribute in default mode with along journey and inject in the intake duct flow field, thus to the oral area wave system of intake duct and effectively throat area regulate.
The mode of operation of this variable geometry inlet under different Mach number is as follows: if the required work range of Mach numbers of intake duct is M
1～M
2(M
1＜M
2), then select M
s(M
1＜M
s＜M
2) for wave system seals the profile design that Mach number carries out intake duct, when intake duct is operated in M
sAnd when following, need not shock wave is controlled, valve 4 is closed fully, is operated in M and work as intake duct
sWhen above, cause the performance of intake duct to decline to a great extent in order to prevent the external compression wave system from squeezing into internal channel even unstable operation occurs, Open valve 4 and was regulated its aperture as required and was just pasted mouth with the external compression wave system that keeps intake duct this moment.Therefore, this variable geometry inlet is at M
sReach above flow coefficient and can reach 1 in theory, at M
sThe following also more conventional intake duct of flow coefficient is improved largely.
The external compression face of ultrasound velocity, hypersonic inlet generally can have 1～4 grade, and all need arrange pipeline 3, valve 4 and porous or stitch plate 5 each cover more each grade compressing surface.
Embodiment:
Under the design condition of work range of Mach numbers 4～6, designed the hypersonic variable geometry inlet of certain geometry.This variable geometry inlet is that wave system seals Mach number and carries out profile design with Mach number 5, has two-stage external compression inclined-plane, in Mach number 5～6 scopes, keep the oral area wave system to paste mouth by injecting an amount of secondary flow always, the inferior flow that consumed this moment is 0.0～1.5% (the recycling) that intake duct is caught flow, and the adjusting range of during Mach number 6 effective passage throat being amassed is more than 15%.Contrasted in the table 1 and decided hypersonic variable geometry inlet of geometry and the conventional Specifeca tion speeification of deciding how much intake ducts, the starting Mach number of two schemes is 4.0, and the difference of outlet Mach number is in 2.0%.As can be seen, fixed how much hypersonic variable geometry inlets have significant advantage at aspects such as flow coefficient, forebody drag coefficients.
Fixed how much hypersonic variable geometry inlets of table 1 and the conventional performance parameter contrast of deciding how much intake ducts
Claims (3)
1, a kind of fixed how much ultrasound velocitys, hypersonic variable geometry inlet, it comprises intake duct main body (1) and intake duct lip cover (2), it is characterized in that: be installed in the porous on intake duct main body (1) the external compression inclined-plane or stitch plate (5) more and link to each other by an end that is arranged on the pipeline (3) in pressure stabilizing cavity (6) and the intake duct main body (1) in the external compression inclined-plane, the valve (4) of adjusting the secondary flow flow is installed on the pipeline (3), and pipeline (3) the other end links to each other with dumping-guiding plate (7) in being installed in the intake duct zone of high pressure by drainage lumens (8).
2, fixed how much ultrasound velocitys according to claim 1, hypersonic variable geometry inlet is characterized in that: the external compression inclined-plane is that an inclined-plane constitutes or is made of 2～4 sections continuous inclined-planes.
3, fixed how much ultrasound velocitys according to claim 1 and 2, hypersonic variable geometry inlet is characterized in that: porous or stitch the front end that plate (5) is installed in intake duct main body (1) external compression at different levels inclined-plane more.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2007100210052A CN100430584C (en) | 2007-03-22 | 2007-03-22 | Fixed geometrical supersonic-speed and high supersonic-speed adjusting air inlet |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2007100210052A CN100430584C (en) | 2007-03-22 | 2007-03-22 | Fixed geometrical supersonic-speed and high supersonic-speed adjusting air inlet |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101029597A true CN101029597A (en) | 2007-09-05 |
| CN100430584C CN100430584C (en) | 2008-11-05 |
Family
ID=38715122
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|---|---|---|---|
| CNB2007100210052A Expired - Fee Related CN100430584C (en) | 2007-03-22 | 2007-03-22 | Fixed geometrical supersonic-speed and high supersonic-speed adjusting air inlet |
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| CN101994570A (en) * | 2010-11-19 | 2011-03-30 | 南京航空航天大学 | Embedded air inlet based on vortex excretion and aircraft using embedded air inlet |
| CN101575012B (en) * | 2009-06-04 | 2012-09-05 | 南京航空航天大学 | Power switching method for hypersonic lifting body aircraft and aircraft |
| CN102817716A (en) * | 2012-08-17 | 2012-12-12 | 中国航天空气动力技术研究院 | Binary mixed pressure intake duct applied to supersonic solid ramjet |
| CN102828832A (en) * | 2012-08-14 | 2012-12-19 | 西北工业大学 | Method for improving starting capability of fixed-geometry two-dimensional mixed-compression inlet |
| CN102953826A (en) * | 2012-11-22 | 2013-03-06 | 南京航空航天大学 | Pneumatic supersonic velocity/hypersonic velocity adjustable air inlet passage for forebody-inner passage circulation |
| CN102953825A (en) * | 2012-11-22 | 2013-03-06 | 南京航空航天大学 | Pneumatic supersonic velocity/hypersonic velocity adjustable air inlet passage for self-circulation of forebody |
| CN103748337A (en) * | 2011-04-29 | 2014-04-23 | 航空集团联合控股公司 | Adjustable supersonic air inlet |
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| CN103797229A (en) * | 2011-04-29 | 2014-05-14 | 航空集团联合控股公司 | Method for adjusting a supersonic air inlet |
| CN103953448A (en) * | 2014-04-15 | 2014-07-30 | 南京航空航天大学 | Hypersonic air inlet channel |
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