CN102817716B - Binary mixed pressure intake duct applied to supersonic solid ramjet - Google Patents
Binary mixed pressure intake duct applied to supersonic solid ramjet Download PDFInfo
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- CN102817716B CN102817716B CN201210293527.9A CN201210293527A CN102817716B CN 102817716 B CN102817716 B CN 102817716B CN 201210293527 A CN201210293527 A CN 201210293527A CN 102817716 B CN102817716 B CN 102817716B
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Abstract
A binary mixed pressure intake duct applied to supersonic solid ramjet comprises an upper part outer cover and a lower part containing a front body, a baffle plate and a back body. A ventilation channel is between the upper part and the lower part; and a section with equivalent height of the ventilation channel is a throat, which is arranged at the back of a leading edge of the outer cover; the baffle plate is clamped between the front body and the back body; a boundary layer auxiliary suction channel communicating with the ventilation channel of the binary mixed pressure intake duct is arranged between the front body and the baffle plate, and a communicating position is an inlet of the boundary layer auxiliary suction channel; a boundary layer suction cavity is between the baffle plate and the back body and communicates with the throat, and a communicating position is an inlet of the boundary layer suction cavity; the outlet of the boundary layer auxiliary suction channel enters into the boundary layer suction cavity; and the boundary layer suction cavity outlet is arranged between the front body and the back body. The invention has simple and convenient structure, does not occupy space in the intake duct, and can fully eliminate influences of the boundary layer on the intake duct and effectively improve the performance of the intake duct at a low suction flow.
Description
Technical field
The present invention relates to a kind of binary mixed pressure intake duct that is applied to ultrasound velocity Ducted rocket, belong to the Design of Inlet field of supersonic speed Ducted rocket.
Background technique
The quality of intake duct service behaviour is directly connected to the size of Ducted rocket thrust, and then affects the overall operational performance of supersonic aircraft.Along with day by day distinct to supersonic vehicle mission requirements of future war, a kind of demand in wider range of Mach numbers with the intake duct of good self-starting characteristic, higher total pressure recovery coefficient and high flow coefficient is also become increasingly conspicuous.
When Mach number reaches 2.5 when above, in intake duct, boundary layer is larger on the impact of its performance, and it is more serious that the interference of shock wave and boundary layer also becomes.For obtaining better performance, it has been the common recognition of industry that intake duct is adopted to boundary layer absorption device.All have at present the research of the boundary layer absorption of pair binary mixed pressure intake duct both at home and abroad, it concentrates at precursor or outer cover leading edge place slots separately or boundary layer absorption is carried out in perforate.Research shows, these measures all can effectively reduce the phase mutual interference of shock wave and boundary layer, to improving inlet characteristic, have obtained certain achievement.But the mode of its cross-notching, perforate and absorption chamber design etc. are not all mentioned.
Summary of the invention
Technology of the present invention is dealt with problems: overcome the deficiencies in the prior art, a kind of binary mixed pressure intake duct that is applied to ultrasound velocity Ducted rocket is provided, its boundary layer absorption device is simple for structure, under lower absorption flow, can fully eliminate the impact of boundary layer on intake duct, effectively improve inlet characteristic.
Technological scheme of the present invention:
A binary mixed pressure intake duct that is applied to ultrasound velocity Ducted rocket, comprises upper half part and lower half portion, and upper half part is outer cover, and lower half portion comprises precursor, dividing plate and rear body; Between upper half part and lower half portion, be the venting channels of described binary mixed pressure intake duct, and in this venting channels highly equivalent one section be venturi, venturi is positioned at the rear of outer cover leading edge;
Lower half portion central diaphragm is clipped in the centre of precursor and rear body, between precursor and dividing plate, there is the auxiliary passage of absorbing of a boundary layer, the auxiliary passage of absorbing of this boundary layer is communicated with the venting channels of described binary mixed pressure intake duct, is communicated with position and is the auxiliary feeder connection of absorbing of boundary layer; Between dividing plate and rear body, there is a boundary layer to absorb chamber, boundary layer is absorbed chamber and is communicated with venturi, be communicated with position and be boundary layer absorption chamber entrance, it is inner that the auxiliary outlet of absorbing passage of described boundary layer enters into boundary layer absorption chamber, and boundary layer absorption chamber outlet is between precursor and rear body; The auxiliary absorption of boundary layer feeder connection, boundary layer absorb chamber entrance and boundary layer absorption chamber outlet is communicated with.
The auxiliary position of absorbing feeder connection of described boundary layer is the 2-3mm place, the place ahead of intersection point of the venting channels lower wall surface of the binary mixed pressure intake duct leading edge of outer cover forms while reaching Start mach number one oblique shock wave and described binary mixed pressure intake duct.
The position that described boundary layer is absorbed chamber entrance is the 2-3mm place, intersection point the place ahead of the binary mixed pressure intake duct leading edge of outer cover forms while reaching design Mach number one oblique shock wave and venturi lower wall surface.
The auxiliary feeder connection width of absorbing of boundary layer is between 2-4mm, and boundary layer is absorbed chamber throat width between 7-9mm, and boundary layer is absorbed the width of chamber outlet between 8-10mm.
The auxiliary passage of absorbing of described boundary layer tilts to binary mixed pressure intake duct front end, and itself and horizontal plane angle are 20.5 °;
The line that boundary layer is absorbed between the central point of chamber entrance and central point that boundary layer is absorbed chamber outlet tilts to binary mixed pressure intake duct front end, and the angle of itself and horizontal plane is 30 °.
The height of the auxiliary absorption of described boundary layer passage is even, and the distance between precursor and dividing plate is even.
The present invention's advantage is compared with prior art as follows:
(1), when incoming flow Mach number is lower, the auxiliary feeder connection of absorbing of boundary layer can effectively be absorbed the boundary layer producing on precursor, reduces the interference of outer cover leading edge lip shock and precursor boundary layer, thereby reduces Start mach number; Boundary layer is absorbed chamber entrance can effectively absorb the boundary layer that venturi place produces, and stablize the normal shock wave at venturi place, reduces the phase mutual interference of shock wave and boundary layer, thus the service behaviour of raising intake duct under flight Mach number.Boundary layer is absorbed simple in structure, is easy to processing, and does not destroy the structure of original intake duct and additionally do not take intake duct space.
(2) the auxiliary passage of absorbing of boundary layer of the present invention tilts to binary mixed pressure intake duct front end, is conducive to the absorption of boundary layer; The line of absorbing between the central point of chamber entrance and the central point of boundary layer absorption chamber outlet tilts to binary mixed pressure intake duct front end, absorbs chamber and exports also forward end inclination, effectively reduces like this impact of exit gas on intake duct outfield flow characteristic.
(3) boundary layer absorption flow of the present invention is lower, less on Flow coefficient of inlet impact.
(4) technological scheme of the present invention is compared with not adopting the intake duct of boundary layer removal techniques scheme, improved the flow field structure of intake duct precursor and venturi, expanded intake duct stable operation range, effectively improved the total pressure recovery coefficient of air intake port and reduce flow distortion.
(5) boundary layer removal techniques of the present invention is through wind tunnel test checking, can start compared with under low mach, largely, reduce the shock wave and the mutual interference of boundary layer phase of Flow Field In An Inlet, reduce intake duct pitot loss, effectively improve intake duct overall performance.
Accompanying drawing explanation
Fig. 1 is intake duct structural representation of the present invention;
Embodiment
The invention provides a kind of binary mixed pressure intake duct that is applied to ultrasound velocity Ducted rocket, as shown in Figure 1, comprise upper half part and lower half portion, upper half part is outer cover 2, and lower half portion comprises precursor 1, dividing plate 3 and rear body 4; Between upper half part and lower half portion, be the venting channels of described binary mixed pressure intake duct, and in this venting channels highly equivalent one section be venturi 9, venturi 9 is positioned at the rear of outer cover 2 leading edges;
Lower half portion central diaphragm 3 is clipped in the centre of precursor 1 and rear body 4, between precursor 1 and dividing plate 3, there is the auxiliary passage of absorbing of a boundary layer, the auxiliary passage of absorbing of this boundary layer is communicated with the venting channels of described binary mixed pressure intake duct, be communicated with position and be the auxiliary feeder connection 5 of absorbing of boundary layer, the height of the auxiliary absorption of boundary layer passage is even, and the distance between precursor 1 and dividing plate 3 is even; Between dividing plate 3 and rear body 4, there is a boundary layer to absorb chamber 7, boundary layer is absorbed chamber 7 and is communicated with venturi 9, be communicated with position and be boundary layer absorption chamber entrance 6, the auxiliary outlet of absorbing passage of described boundary layer enters into boundary layer and absorbs 7 inside, chamber, and boundary layer is absorbed chamber outlet 8 between precursor 1 and rear body 4; The auxiliary absorption of boundary layer feeder connection 5, boundary layer absorb chamber entrance 6 and boundary layer absorption chamber outlet 8 is communicated with.
The auxiliary position of absorbing feeder connection 5 of boundary layer is the 2-3mm place, the place ahead of intersection point of the venting channels lower wall surface of the binary mixed pressure intake duct leading edge of outer cover 2 forms while reaching Start mach number one oblique shock wave and described binary mixed pressure intake duct.The position that boundary layer is absorbed chamber entrance 6 is the 2-3mm place, intersection point the place ahead of the binary mixed pressure intake duct leading edge of outer cover 2 forms while reaching design Mach number one oblique shock wave and venturi 9 lower wall surfaces.Auxiliary feeder connection 5 width of absorbing of boundary layer are between 2-4mm, and boundary layer is absorbed chamber entrance 6 width between 7-9mm, and boundary layer is absorbed the width of chamber outlet 8 between 8-10mm.
The auxiliary passage of absorbing of boundary layer tilts to binary mixed pressure intake duct front end, and itself and horizontal plane angle are 20.5 °; The line that boundary layer is absorbed between the central point of chamber entrance 6 and central point that boundary layer is absorbed chamber outlet 8 tilts to binary mixed pressure intake duct front end, and the angle of itself and horizontal plane is 30 °.
The supercharging of slowing down of 1 pair of incoming flow of precursor, air-flow is before entering the venting channels of binary mixed pressure intake duct, on precursor 1, formed certain thickness boundary layer, and the leading edge of outer cover 2 also to be compressed and form one oblique shock wave to incoming flow and incides in the venting channels of binary mixed pressure intake duct.Near Start mach number, this oblique shock wave is forward at the drop point of the venting channels lower wall surface of binary mixed pressure intake duct, with the Boundary Layer Interaction forming on precursor 1 and produce separate bubble, separate bubble can produce the effect of the venting channels area that reduces binary mixed pressure intake duct, causes the intake duct cannot normal starting.At drop point the place ahead 2-3mm, the auxiliary feeder connection 5 of absorbing of narrower boundary layer is set, utilize the poor of the inner static pressure with external environment of intake duct, the boundary layer forming on a part of precursor 1 is sucked and absorbs chamber 7 by boundary layer enter the external world, thereby the effect of reduction Start mach number is also finally played in the interaction that reduces oblique shock wave and boundary layer.On the other hand, under design Mach number, the oblique shock wave that the leading edge of outer cover 2 produces is after the drop point of venturi 9 lower wall surfaces leans on, and now shock strength is larger, strong with the Boundary Layer Interaction at venturi 9 lower wall surface places.At this place ahead 2-3mm, wider boundary layer is set and absorbs chamber entrance 6, the boundary layer of a part of venturi 9 lower wall surfaces is sucked and by boundary layer, absorbs chamber 7 equally and enter the external world, reduce interaction the stable ending normal shock wave of oblique shock wave and boundary layer, finally improve the overall performance of intake duct.Auxiliary feeder connection 5, boundary layer absorption chamber entrance 6, boundary layer absorption chamber 7 and the boundary layer absorbed of boundary layer absorbed chamber outlet 8 all to intake duct front end inclination several angle, to be conducive to the absorption of boundary layer and to reduce the impact on intake duct Flow Field outside.
Embodiment:
Ultrasound velocity Ducted rocket binary mixed pressure intake duct, two wedge three wave systems.Start mach number 2.5, design Mach number 3.0.According to intake duct structure of the present invention, through numerical simulation and engineering calculation, determine auxiliary position and the width of absorbing feeder connection 5 and boundary layer absorption chamber entrance 6 of boundary layer.Wherein, boundary layer is auxiliary absorbs leading edge lip that feeder connection 5 the is positioned at outer cover 2 about 42mm of horizontal equivalent backward, and boundary layer is absorbed leading edge lip that chamber entrance 6 the is positioned at outer cover 2 about 81mm of horizontal equivalent backward.
Said structure is carried out to wind tunnel test.Results of property is as shown in the table.At design Mach number 3.0, under the inlet flow conditions of zero-incidence zero angle of sideslip, total pressure recovery coefficient σ has reached 0.598, compares (under equal design condition and test conditions with the conventional intake duct with absorption not, σ is about 0.45), its total pressure recovery coefficient has improved approximately 30%; Compare (under equal design condition and test conditions, σ is about 0.5) with the intake duct that common band is absorbed, its total pressure recovery coefficient has improved approximately 20%.The flow coefficient of the design's structure when design Mach number is 0.976, shows to absorb flow lower.
In sum, the present invention can effectively absorb the boundary layer in intake duct, can effectively suppress boundary layer separation in intake duct, reduces the phase mutual interference of shock wave/boundary layer, promotes to a great extent inlet characteristic.Preparation process is simple, does not destroy the structure of original intake duct, has scientific and technological purposes widely.
The unspecified part of the present invention belongs to general knowledge as well known to those skilled in the art.
Claims (6)
1. a binary mixed pressure intake duct that is applied to ultrasound velocity Ducted rocket, is characterized in that: comprise upper half part and lower half portion, upper half part is outer cover (2), and lower half portion comprises precursor (1), dividing plate (3) and rear body (4); Between upper half part and lower half portion, be the venting channels of described binary mixed pressure intake duct, and in this venting channels highly equivalent one section be venturi (9), venturi (9) is positioned at the rear of outer cover (2) leading edge;
Lower half portion central diaphragm (3) is clipped in the centre of precursor (1) and rear body (4), between precursor (1) and dividing plate (3), there is the auxiliary passage of absorbing of a boundary layer, the auxiliary passage of absorbing of this boundary layer is communicated with the venting channels of described binary mixed pressure intake duct, is communicated with position and is the auxiliary feeder connection (5) of absorbing of boundary layer; Between dividing plate (3) and rear body (4), there is a boundary layer to absorb chamber (7), boundary layer is absorbed chamber (7) and is communicated with venturi (9), be communicated with position and be boundary layer absorption chamber entrance (6), the auxiliary outlet of absorbing passage of described boundary layer enters into boundary layer and absorbs inside, chamber (7), and boundary layer is absorbed chamber outlet (8) and is positioned between precursor (1) and rear body (4); The auxiliary absorption of boundary layer feeder connection (5), boundary layer absorption chamber entrance (6) and boundary layer are absorbed chamber outlet (8) and are communicated with;
The auxiliary position of absorbing feeder connection (5) of described boundary layer is the 2-3mm place, the place ahead of intersection point of the venting channels lower wall surface of one oblique shock wave forming of the leading edge of binary mixed pressure intake duct outer cover (2) while reaching Start mach number and described binary mixed pressure intake duct.
2. a kind of binary mixed pressure intake duct that is applied to ultrasound velocity Ducted rocket according to claim 1, is characterized in that: the position that described boundary layer is absorbed chamber entrance (6) is one oblique shock wave forming of the leading edge of binary mixed pressure intake duct outer cover (2) while reaching design Mach number and the 2-3mm place, intersection point the place ahead of venturi (9) lower wall surface.
3. a kind of binary mixed pressure intake duct that is applied to ultrasound velocity Ducted rocket according to claim 1, it is characterized in that: auxiliary feeder connection (5) width of absorbing of boundary layer is between 2-4mm, boundary layer is absorbed chamber entrance (6) width between 7-9mm, and boundary layer is absorbed the width of chamber outlet (8) between 8-10mm.
4. a kind of binary mixed pressure intake duct that is applied to ultrasound velocity Ducted rocket according to claim 1, is characterized in that: the auxiliary passage of absorbing of described boundary layer tilts to binary mixed pressure intake duct front end, and itself and horizontal plane angle are 20.5 °.
5. a kind of binary mixed pressure intake duct that is applied to ultrasound velocity Ducted rocket according to claim 1, it is characterized in that: the line that boundary layer is absorbed between the central point of chamber entrance (6) and central point that boundary layer is absorbed chamber outlet (8) tilts to binary mixed pressure intake duct front end, and the angle of itself and horizontal plane is 30 °.
6. a kind of binary mixed pressure intake duct that is applied to ultrasound velocity Ducted rocket according to claim 1, is characterized in that: the height of the auxiliary absorption of described boundary layer passage is even, and the distance between precursor (1) and dividing plate (3) is even.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210293527.9A CN102817716B (en) | 2012-08-17 | 2012-08-17 | Binary mixed pressure intake duct applied to supersonic solid ramjet |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201210293527.9A CN102817716B (en) | 2012-08-17 | 2012-08-17 | Binary mixed pressure intake duct applied to supersonic solid ramjet |
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| CN102817716A CN102817716A (en) | 2012-12-12 |
| CN102817716B true CN102817716B (en) | 2014-09-10 |
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Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| GB201518573D0 (en) | 2015-10-20 | 2015-12-02 | Rolls Royce Plc | Fluid system |
| CN105221266B (en) * | 2015-10-29 | 2017-08-29 | 西北工业大学 | A kind of rocket based combined cycle engine, which becomes, absorbs control air intake duct |
| CN106989891B (en) * | 2017-03-30 | 2020-01-10 | 南京航空航天大学 | Acceleration self-starting experimental method for hypersonic air inlet |
| CN107061011B (en) * | 2017-06-02 | 2019-01-04 | 南京航空航天大学 | Low extrernal resistance hypersonic inlet |
| CN110805695B (en) * | 2019-11-11 | 2021-10-12 | 北京动力机械研究所 | Movable sealing structure of adjustable flow passage rotating shaft |
| CN112392600B (en) * | 2020-11-17 | 2023-10-13 | 北京动力机械研究所 | Axisymmetric adjustable intake passage center cone boundary layer sucking structure |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| NL243195A (en) * | 1958-09-10 | 1900-01-01 | ||
| DE2801119C2 (en) * | 1978-01-12 | 1982-12-02 | Deutsche Forschungs- und Versuchsanstalt für Luft- und Raumfahrt e.V., 5000 Köln | Supersonic air inlet of fixed geometry for air-breathing recoil engines of steerable missiles or aircraft, in particular for stagnation drives operated with solid fuels |
| US4611616A (en) * | 1984-01-10 | 1986-09-16 | Messerschmitt-Bolkow-Blohm Gmbh | Axially semisymmetrical supersonic air intake for reaction engines, particularly solid fuel ram jet rocket engines |
| CN100430584C (en) * | 2007-03-22 | 2008-11-05 | 南京航空航天大学 | Fixed geometrical supersonic-speed and high supersonic-speed adjusting air inlet |
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