CN110043367A - A kind of super/hypersonic inlet of side plate openings - Google Patents
A kind of super/hypersonic inlet of side plate openings Download PDFInfo
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- CN110043367A CN110043367A CN201910323643.2A CN201910323643A CN110043367A CN 110043367 A CN110043367 A CN 110043367A CN 201910323643 A CN201910323643 A CN 201910323643A CN 110043367 A CN110043367 A CN 110043367A
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- internal channel
- side plate
- air intake
- channel inner
- intake duct
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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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Characterised By The Charging Evacuation (AREA)
Abstract
The invention discloses a kind of super/hypersonic inlets of side plate openings, including first order external compression face, second level external compression face, lower wall surface, air intake duct pedestal, aerial drainage chamber on the opening side plate, air intake duct internal channel, air intake duct internal channel of external compression section.The working principle of the invention is: conventional binary is super/hypersonic inlet at work, often there is strong swept shock-boundary layer interactions phenomenon on external compression section side plate, this phenomenon can deteriorate air intake duct flow field quality, reduce air intake duct aeroperformance, the present invention on external pressure side plate by cutting off an open area, on the one hand it can be reduced the low energy stream ratio in internal channel, on the other hand the strong Features of Interaction Between Swept Shock of external compression section/boundary layer interference appearance is inhibited, the generation of whirlpool is prevented to flow to, to greatly improve flow field quality, improve the total pressure recovery coefficient and anti-reflective pressure energy power of air intake duct.
Description
Technical field
The invention belongs to aircraft air intake duct technical fields.
Background technique
Punching engine is mainly made of Supersonic Inlet, combustion chamber, the big core component of jet pipe three, air intake duct conduct
One of critical component of punching engine, performance directly affect the comprehensive performance of propulsion system or even entire aircraft.
At work, due to the effect of gas viscosity, air intake duct wall surface can have boundary layer to super/hypersonic inlet,
Interfering with each other for shock wave-boundary layer is phenomenon common in air intake duct flow field, and this Shock/Boundary-Layer interference can not only deteriorate
Flow field quality and its pitot loss and anti-reflective pressure energy power are also affected, even causes surge when serious, engine is caused to put out
Fire.Therefore, inhibit even to be eliminated counter productive brought by this Shock/Boundary-Layer interference, for improving inlet characteristic, reality
Existing hypersonic efficient flight is of great significance.
According to incident shock/sides in super/hypersonic inlet are mainly studied in open source literature, most of work at present
The mechanism and control means of interlayer interference, and to binary it is super/hypersonic inlet in the Features of Interaction Between Swept Shock boundary layer that is widely present
Interference phenomenon is then studied less.Binary it is super/hypersonic inlet in, since the entrance in side plate boundary layer is so that in air intake duct
Low energy stream ratio increases in runner, in addition, external compression section can have serious Features of Interaction Between Swept Shock/boundary layer interference phenomenon, and generates
Whirlpool is flowed to, exacerbates low energy stream in the accumulation of angular region, this not only seriously affects the uniformity coefficient of air-flow, even more weakens boundary
The resistance back-pressure ability of layer.For this problem, at present it can be seen that way be cancel external compression section partition, while in order to avoid
Two sides expansion flowing forms interference to air intake duct traffic capture and internal channel entrance flow parameter, and external compression section is straight along two sides etc.
Extend.Although this method can significantly improve the negative effect of side plate boundary layer bring, there is also many drawbacks.Firstly,
Although also external compression section is widened while cancelling external compression section partition, but still can have that flow loss is more serious to ask
Topic；Secondly, in practical projects, valuable aircraft space can be occupied by widening external compression section not only, and its brought volume
Outer weight and extrernal resistance can also weaken the thrust ratio of entire propulsion device, this should be to try to keep away for super/hypersonic flight
Exempt from.
Therefore, explore a kind of new flow field control method inhibit binary it is super/hypersonic inlet China and foreign countries compression section
Swept shock-boundary layer interactions phenomenon is of great importance for promoting the aeroperformance of punching engine propulsion system.
Summary of the invention
Goal of the invention: the present invention provides a kind of super/hypersonic inlet of side plate openings, in order to inhibit binary
The swept shock-boundary layer interactions of super/hypersonic inlet China and foreign countries compression section, the aeroperformance for improving propulsion device.
Technical solution: following technical scheme can be used in the present invention:
A kind of super/hypersonic inlet of side plate openings, including internal channel inner surface, be located on the outside of internal channel inner surface
Lip cover, on the outside of internal channel inner surface and connect the internal channel side plate of internal channel inner surface outer rim Yu lip cover outer rim；It is described
Internal channel inner surface, lip cover and internal channel side plate surround the internal channel of air intake duct；Internal channel inner surface front end is connected with two
Grade compressing surface, wherein second level compressing surface is connected between first order compressing surface and internal channel inner surface；
It further include the outer panel for being connected to two stages of compression face lateral border, which connect with internal channel side plate, and this is outer
It is additionally provided on side plate by the opening of outside connection in outer panel；The opening tilts labiad from outer panel and two stages of compression face junction
Cover direction is extended up to through outer panel.
Further, it is equipped with several aerial drainage chambers below internal channel inner surface, and is offered on internal channel inner surface and aerial drainage
The aerial drainage air cleft of chamber connection.
Further, open area leading edge and the angle of second external pressure oblique shock wave under low mach are θ4, external compression section
The open area rear of opening side plate and the angle of the second external pressure oblique shock wave under design Mach number are θ3；θ3And θ4Value
Range meets: 2 °≤θ3≤ 8 °, 2 °≤θ4≤8°。
The present invention can also use following technical scheme:
A kind of super/hypersonic inlet of side plate openings, including internal channel inner surface, be located on the outside of internal channel inner surface
Lip cover, on the outside of internal channel inner surface and connect the internal channel side plate of internal channel inner surface outer rim Yu lip cover outer rim；It is described
Internal channel inner surface, lip cover and internal channel side plate surround the internal channel of air intake duct；Internal channel inner surface front end is connected with two
Grade compressing surface, wherein second level compressing surface is connected between first order compressing surface and internal channel inner surface；It further include being connected to
First outer panel of one stage of compression face lateral border, the second outer panel for being connected to second level compressing surface lateral border, the second outer panel
It is connect with internal channel side plate, there is opening, and first order compressing surface and the second level are pressed between the first outer panel and the second outer panel
The junction lateral margin in contracting face is in the range of the opening.
Compared with the existing technology, the present invention by excision air intake duct external compression section side plate on Features of Interaction Between Swept Shock interference range, one
Aspect reduces the low energy stream ratio in internal channel, and another program inhibits the strong Features of Interaction Between Swept Shock of external compression section/boundary layer interference
Occur, while also having prevented to flow to the generation of whirlpool, to greatly improve flow field quality, improves the total pressure recovery of air intake duct
Coefficient and anti-reflective pressure energy power.
Detailed description of the invention
Fig. 1 is hypersonic inlet three dimensional structure diagram of the present invention；
Fig. 2 is hypersonic inlet two-dimensional structure schematic diagram of the present invention；
Fig. 3 is Fig. 1 split shed plate region partial schematic diagram；
Fig. 4 is free stream Mach number Ma∞When=5.0, prototype solution Flow Field In An Inlet streamline and external compression face vertical plane Mach
Number isopleth map；
Fig. 5 is free stream Mach number Ma∞When=5.0, be open side plate scheme Flow Field In An Inlet streamline and external compression face vertical plane
Mach number isopleth map；
Fig. 6 is free stream Mach number Ma∞When=5.0, the prototype solution air intake duct wall friction line of force；
Fig. 7 is free stream Mach number Ma∞When=5.0, be open the side plate scheme air intake duct wall friction line of force；
Fig. 8 is free stream Mach number Ma∞When=5.0, prototype solution inlet throat section Mach number isopleth map；
Fig. 9 is free stream Mach number Ma∞When=5.0, be open side plate scheme inlet throat section Mach number isopleth map.
Specific embodiment
The following further describes the present invention in detail with reference to the accompanying drawings and specific embodiments.
Referring to FIG. 1 to 3, a kind of super/hypersonic inlet of side plate openings of the present invention includes: table in internal channel
Face 4, positioned at the lip cover 5 in the outside of internal channel inner surface 4, positioned at 4 outside of internal channel inner surface and connect 4 outer rim of internal channel inner surface
With the internal channel side plate 101 of 5 outer rim of lip cover.The internal channel inner surface 4, lip cover 5 and internal channel side plate 101 surround air intake duct
Internal channel 9.The depths of internal channel 9 is venturi 7.The lower section of the lip cover 5 is the upper surface 6 of internal channel.Table in the internal channel
4 front end of face is connected with two stages of compression face, wherein second level compressing surface 2 be connected to first order compressing surface 1 and internal channel inner surface 4 it
Between.The air intake duct further includes the outer panel 3 for being connected to two stages of compression face lateral border, and the outer panel 3 and internal channel side plate 101 connect
It connects, and is additionally provided on the outer panel 101 by the opening 102 of outside connection in outer panel；The opening 102 is from outer panel 101 and two
Grade compressing surface junction is tilted towards 5 direction of lip cover and extends up to through outer panel.Such as Fig. 1, opening 102 is substantially by outer panel 101
The first outer panel and the second outer panel have been divided into it, the second outer panel is connect with internal channel side plate.
Wherein, it is equipped with several aerial drainage chambers 8 below internal channel inner surface 4, and is offered on internal channel inner surface 4 and aerial drainage chamber
The aerial drainage air cleft of 8 connections.The purpose that aerial drainage chamber is arranged is to arrange shift-in air flue shoulder low energy stream, weaken lip shock and air inlet
The interference strength of road shoulder boundary-layer, widens the stable operation range of air intake duct.The design method of aerial drainage chamber is referring to a kind of high property
It can dual rectangular channels loong shunt TBCC air intake duct and design method (ZL201710664795.X).
Referring to Fig. 3, according to the fast domain of air intake duct work and acquiring second under design Mach number in conjunction with oblique shock wave relational expression
The Angle of Shock Waves θ of road external pressure oblique shock wave 151And under low mach second external pressure oblique shock wave 14 Angle of Shock Waves θ2.Open area leading edge
11 with low mach under the angle of second external pressure oblique shock wave 15 be θ4, the open area rear 12 of external compression section opening side plate 3
Angle with the second external pressure oblique shock wave 15 under design Mach number is θ3.To prevent second external pressure oblique shock wave 14,15 and opening
The relevant whirlpool generated in mouth 3 boundary layer of side plate enters inner flow passage 9 and avoids the capture flow of air intake duct internal channel entrance 10 too low,
θ3And θ4Value range should meet: 2 °≤θ3≤ 8 °, 2 °≤θ4≤8°.In addition, guaranteeing that second external pressure tiltedly swashs under low mach
Wave 14 intersects with the top endpoint of open area leading edge 11 just.
The folder of second external pressure oblique shock wave 14 under the open area leading edge 11 and low mach of the compression section opening side plate 3
Angle θ4=6.5 °, the open area rear 12 and the second external pressure under design Mach number of the external compression section opening side plate 3 are oblique
The angle theta of shock wave 153=7 °.Under low mach second external pressure oblique shock wave 14 just with the top endpoint of open area leading edge 11
Just intersection.As can be seen that this hatch method completely avoids interfering with each other for second external pressure shock wave and side plate boundary-layer
Phenomenon.
Referring to Fig. 3, being so that the low energy stream of 1,2 top of compressing surface and opening 3 inner surface of side plate is easier to exclude, to open
Mouth region domain leading edge 11 is dihedral angle crest line, using 3 outer surface of side plate that is open as half-plane, does one 15 ° to being open on the inside of side plate 3
Dihedral angle, and complete to cut along another half-plane opposite side plate of the dihedral angle；With open area rear 12 for dihedral angle crest line, with
Opening 3 inner surface of side plate is half-plane, to opening side plate 3 on the outside of do one 15 ° of dihedral angle, and along the dihedral angle the other half
Plane is completed to cut to side plate.
Application example
Scheme introduction:
A binary hypersonic inlet is designed, height 200mm is captured, designs Mach 2 ship 5.0, work fast domain
Ma4.0-5.0.Second level external compression angle is respectively 9.0 °, and 11.6 °, contract ratio is 2.60, and air intake duct the ratio of width to height is 0.9, θ1=
23.4 °, θ2=26.6 °, θ3=7.0 °, θ4=6.5 °.
As shown in Fig. 4, Fig. 6, Fig. 8, when air intake duct is using side plate is blocked entirely, the captured air-flow of main flow area flows into interior logical substantially
In road, the boundary layer developed by side plate starting point has had larger thickness (Fig. 4) before interior feeder connection, works as Ma∞=5.0
When, since shock strength is stronger at this time, external pressure oblique shock wave and side plate boundary-layer are relevant violent, it can be seen that wall friction power at this time
Clearly main convergence line, i.e. defiber (Fig. 6) have been formd in line, show that side wall surface has already appeared separation, in Disengagement zone
Vortex can aggravate low energy and flow to angular region accumulation, so that air-flow degree of irregularity is further exacerbated by when along flow direction development.In venturi
(Fig. 8) is as can be seen that the Low Energy Region of large area all occur in side plate and upper lower wall surface angular region, at this time in the Mach number isopleth map of section
The ability that negative sequence harmonic is resisted in boundary layer is weaker, therefore the three-dimensional aeroperformance for becoming geometry air intake duct is bigger than occurring compared with two-dimensional phase
Width decline.
As shown in Fig. 5, Fig. 7, Fig. 9, after side plate openings, at this time under the driving of pressure difference, external compression section proximal panel wall surface
A large amount of low energy streams in area are outwardly flowed out by side plate seam, and this aspect significantly reduces low energy in internal channel entrance section air-flow
Flowing accounting improves the air-flow uniformity, Features of Interaction Between Swept Shock/boundary layer interference generation is on the other hand in turn avoided, to inhibit high horse
Conspicuous several lower side panels flow to the appearance of vortex.The side plate boundary layer thickness of air intake duct internal channel entrance is obviously reduced, and venturi is cut
Face lower wall surface to the low energy stream region near side plate angular region is also corresponding reduces.It can be with by the wall friction line of force of opening side plate scheme
Find out, converging phenomenon, strong Features of Interaction Between Swept Shock/boundary layer of the prototype solution in High Mach number does not occur in the wall friction line of force at this time
Interference is inhibited.In addition, improving the venturi of side plate scheme in the Mach number isopleth map of throatpiston by comparison two schemes
Section flow field uniformity is significantly improved, and angular region low energy stream packing phenomenon is eased.
As shown in table 1, the aeroperformance for the side plate scheme that is open has a distinct increment compared with prototype solution.Wherein, discharge coefficient is only
Decline 2.3%, and critical pressure ratio promotes 29.8%, total pressure recovery coefficient promotes 28.5%.
1 prototype air intake duct of table and opening side plate inlet characteristic main performance list
| Scheme | Discharge coefficient | Total pressure recovery coefficient | Critical pressure ratio |
| Prototype solution | 0.938 | 0.274 | 141 |
| Be open side plate scheme | 0.918 | 0.352 | 183 |
There are many concrete application approach of the present invention, the above is only a preferred embodiment of the present invention, it is noted that for
For those skilled in the art, without departing from the principle of the present invention, several improvement can also be made, this
A little improve also should be regarded as protection scope of the present invention.
Claims (6)
1. super/hypersonic inlet of a kind of side plate openings, including internal channel inner surface, on the outside of internal channel inner surface
Lip cover on the outside of internal channel inner surface and connects the internal channel side plate of internal channel inner surface outer rim Yu lip cover outer rim；In described
Channel inner surface, lip cover and internal channel side plate surround the internal channel of air intake duct；Internal channel inner surface front end is connected with two-stage
Compressing surface, wherein second level compressing surface is connected between first order compressing surface and internal channel inner surface；
It is characterized in that, further including the outer panel for being connected to two stages of compression face lateral border, which connect with internal channel side plate,
And it is additionally provided on the outer panel by the opening of outside connection in outer panel；The opening is inclined from outer panel and two stages of compression face junction
Oblique lip cover direction is extended up to through outer panel.
2. air intake duct according to claim 1, it is characterised in that: several aerial drainage chambers are equipped with below internal channel inner surface, and
The aerial drainage air cleft being connected to aerial drainage chamber is offered on internal channel inner surface.
3. air intake duct according to claim 1 or 2, it is characterised in that: second under open area leading edge and low mach
The angle of external pressure oblique shock wave is θ4, open area rear and the second external pressure under design Mach number of external compression section opening side plate
The angle of oblique shock wave is θ3；θ3And θ4Value range meet: 2 °≤θ3≤ 8 °, 2 °≤θ4≤8°。
4. super/hypersonic inlet of a kind of side plate openings, including internal channel inner surface, on the outside of internal channel inner surface
Lip cover on the outside of internal channel inner surface and connects the internal channel side plate of internal channel inner surface outer rim Yu lip cover outer rim；In described
Channel inner surface, lip cover and internal channel side plate surround the internal channel of air intake duct；Internal channel inner surface front end is connected with two-stage
Compressing surface, wherein second level compressing surface is connected between first order compressing surface and internal channel inner surface；
It is characterized in that, further including the first outer panel for being connected to first order compressing surface lateral border, being connected to second level compressing surface
Second outer panel of lateral border, the second outer panel are connect with internal channel side plate, are had between the first outer panel and the second outer panel
Opening, and the junction lateral margin of first order compressing surface and second level compressing surface is in the range of the opening.
5. air intake duct according to claim 4, it is characterised in that: several aerial drainage chambers are equipped with below internal channel inner surface, and
The aerial drainage air cleft being connected to aerial drainage chamber is offered on internal channel inner surface.
6. air intake duct according to claim 4 or 5, it is characterised in that: second under open area leading edge and low mach
The angle of external pressure oblique shock wave is θ4, open area rear and the second external pressure under design Mach number of external compression section opening side plate
The angle of oblique shock wave is θ3；θ3And θ4Value range meet: 2 °≤θ3≤ 8 °, 2 °≤θ4≤8°。
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910323643.2A CN110043367A (en) | 2019-04-22 | 2019-04-22 | A kind of super/hypersonic inlet of side plate openings |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910323643.2A CN110043367A (en) | 2019-04-22 | 2019-04-22 | A kind of super/hypersonic inlet of side plate openings |
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ID=67278394
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110630382A (en) * | 2019-09-27 | 2019-12-31 | 南京航空航天大学 | Internal/external compression integrated adjustable variable-geometry air inlet and design method |
| CN111173618A (en) * | 2020-01-08 | 2020-05-19 | 南京航空航天大学 | Embedded air inlet channel with mouth surface vortex releasing groove |
| CN111797477A (en) * | 2020-07-10 | 2020-10-20 | 南京航空航天大学 | Sweepforward front edge type side plate structure matched with binary supersonic air inlet channel |
| CN112319827A (en) * | 2020-11-20 | 2021-02-05 | 江西洪都航空工业集团有限责任公司 | Embedded air inlet channel and aircraft |
| CN114248936A (en) * | 2021-11-23 | 2022-03-29 | 南京航空航天大学 | Air inlet with spanwise sweepback structural characteristic and design method |
| CN114458448A (en) * | 2022-01-26 | 2022-05-10 | 南京航空航天大学 | Self-adaptive suction orifice plate for inhibiting shock wave boundary layer interference |
| CN115585063A (en) * | 2022-12-12 | 2023-01-10 | 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 |
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| GB2070139B (en) * | 1980-02-26 | 1983-06-22 | Gen Electric | Inlet cowl for supersonic aircraft engine |
| CN107298180A (en) * | 2017-06-09 | 2017-10-27 | 南京航空航天大学 | A kind of aircraft and pneumatic adaptation design method for possessing one flowing control |
| CN107575309A (en) * | 2017-08-07 | 2018-01-12 | 南京航空航天大学 | A kind of high-performance dual rectangular channels loong shunt TBCC air intake ducts and design method |
| CN108533405A (en) * | 2018-03-19 | 2018-09-14 | 南京航空航天大学 | Two-dimensional supersonic inlet with aerial drainage air cleft |
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2019
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| Publication number | Priority date | Publication date | Assignee | Title |
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| GB2070139B (en) * | 1980-02-26 | 1983-06-22 | Gen Electric | Inlet cowl for supersonic aircraft engine |
| CN107298180A (en) * | 2017-06-09 | 2017-10-27 | 南京航空航天大学 | A kind of aircraft and pneumatic adaptation design method for possessing one flowing control |
| CN107575309A (en) * | 2017-08-07 | 2018-01-12 | 南京航空航天大学 | A kind of high-performance dual rectangular channels loong shunt TBCC air intake ducts and design method |
| CN108533405A (en) * | 2018-03-19 | 2018-09-14 | 南京航空航天大学 | Two-dimensional supersonic inlet with aerial drainage air cleft |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110630382A (en) * | 2019-09-27 | 2019-12-31 | 南京航空航天大学 | Internal/external compression integrated adjustable variable-geometry air inlet and design method |
| CN111173618A (en) * | 2020-01-08 | 2020-05-19 | 南京航空航天大学 | Embedded air inlet channel with mouth surface vortex releasing groove |
| 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 |
| CN111797477A (en) * | 2020-07-10 | 2020-10-20 | 南京航空航天大学 | Sweepforward front edge type side plate structure matched with binary supersonic air inlet channel |
| CN111797477B (en) * | 2020-07-10 | 2023-05-23 | 南京航空航天大学 | Forward-swept front edge type side plate structure matched with binary supersonic air inlet channel |
| CN112319827A (en) * | 2020-11-20 | 2021-02-05 | 江西洪都航空工业集团有限责任公司 | Embedded air inlet channel and aircraft |
| CN114248936A (en) * | 2021-11-23 | 2022-03-29 | 南京航空航天大学 | Air inlet with spanwise sweepback structural characteristic and design method |
| CN114458448A (en) * | 2022-01-26 | 2022-05-10 | 南京航空航天大学 | Self-adaptive suction orifice plate for inhibiting shock wave boundary layer interference |
| CN115585063A (en) * | 2022-12-12 | 2023-01-10 | 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 |
| 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 |
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