CN102817716A - 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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- CN102817716A CN102817716A CN2012102935279A CN201210293527A CN102817716A CN 102817716 A CN102817716 A CN 102817716A CN 2012102935279 A CN2012102935279 A CN 2012102935279A CN 201210293527 A CN201210293527 A CN 201210293527A CN 102817716 A CN102817716 A CN 102817716A
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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 ultrasonic tachy steroling that be applied to, belong to Supersonic and tachy sterol towards the intake duct design field of motor towards the binary mixed pressure intake duct of motor.
Background technique
The quality of intake duct service behaviour is directly connected to solid size towards motor power, and then influences the overall operational performance of supersonic aircraft.Along with future war distinct day by day to the supersonic vehicle mission requirements, a kind of demand that in the broad range of Mach numbers, has 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, boundary layer is bigger to its Effect on Performance in the intake duct, and it is more serious that the interference of shock wave and boundary layer also becomes.For obtaining more performance, adopting boundary layer to absorb device to intake duct has been the common recognition of industry.The present research that the boundary layer absorption of pair binary mixed pressure intake duct is all arranged both at home and abroad, it concentrates at precursor or outer cover leading edge place slots separately or the boundary layer absorption is carried out in perforate.Research shows, these measures all can effectively reduce the mutual interference mutually of shock wave and boundary layer, have obtained certain achievement to improving inlet characteristic.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: the deficiency that overcomes existing technology; A kind of ultrasonic tachy steroling towards the binary mixed pressure intake duct of motor that be applied to is provided; It is simple that its boundary layer is absorbed apparatus structure; Under lower absorption flow, can fully eliminate the influence of boundary layer to intake duct, effectively improve inlet characteristic.
Technological scheme of the present invention:
A kind ofly be applied to ultrasonic tachy steroling towards the binary mixed pressure intake duct of motor, comprise upper half part and lower half portion, upper half part is an outer cover, and lower half portion comprises precursor, dividing plate and back body; Be the venting channels of said binary mixed pressure intake duct between upper half part and lower half portion, 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 back body; The auxiliary passage of absorbing of one boundary layer is arranged between precursor and the dividing plate; The auxiliary passage of absorbing of this boundary layer is communicated with the venting channels of said binary mixed pressure intake duct, is communicated with the position and is the auxiliary feeder connection of absorbing of boundary layer; There is a boundary layer to absorb the chamber between dividing plate and the back body; Boundary layer is absorbed the chamber and is communicated with venturi; Be communicated with the position and be boundary layer absorption chamber inlet, the auxiliary outlet of absorbing passage of said boundary layer enters into boundary layer and absorbs inside, chamber, and boundary layer is absorbed the chamber outlet between precursor and back body; The auxiliary absorption of boundary layer feeder connection, boundary layer absorb the chamber inlet and boundary layer is absorbed chamber outlet connection.
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 when reaching the starting Mach number one oblique shock wave and said binary mixed pressure intake duct.
The position that described boundary layer is absorbed the chamber inlet is the 2-3mm place, intersection point the place ahead of the binary mixed pressure intake duct leading edge of outer cover forms when reaching the 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 the 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 said 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 inlet and the central point that boundary layer is absorbed the 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 said boundary layer passage is even, and promptly the distance between precursor and the dividing plate is even.
The present invention's advantage compared with prior art is following:
(1) when the incoming flow Mach number is low, the auxiliary feeder connection of absorbing of boundary layer can effectively be absorbed the boundary layer that produces on the precursor, reduces the interference of outer cover leading edge lip shock and precursor boundary layer, thereby reduces the starting Mach number; Boundary layer is absorbed the chamber inlet can effectively absorb the boundary layer that the venturi place produces, and stablize the normal shock wave at venturi place, reduces the mutual interference mutually 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 the not extra intake duct space that takies.
(2) the auxiliary passage of absorbing of boundary layer of the present invention tilts to binary mixed pressure intake duct front end, helps the absorption of boundary layer; Line between the central point that the central point of absorption chamber inlet and boundary layer are absorbed the chamber outlet tilts to binary mixed pressure intake duct front end, promptly absorbs the chamber and exports also forward end inclination, effectively reduces the influence of exit gas to intake duct outfield flow characteristic like this.
(3) boundary layer absorption flow of the present invention is lower, and is less to the influence of inlet duct flow flow coefficient.
(4) technological scheme of the present invention is compared with the intake duct that does not adopt boundary layer removal techniques scheme; Improved the flow field structure of intake duct precursor and venturi; Enlarged the intake duct stable operation range, effectively improved the total pressure recovery coefficient of intake duct outlet and reduce flow distortion.
(5) boundary layer removal techniques of the present invention is through the wind tunnel test checking, can be than starting low mach under, reduce the shock wave and boundary layer mutual interference mutually of intake duct flow field on largely, and reduction intake duct pitot loss effectively improves the intake duct overall performance.
Description of drawings
Fig. 1 is an intake duct structural representation of the present invention;
Embodiment
The invention provides a kind of ultrasonic tachy steroling that be applied to towards the binary mixed pressure intake duct of motor, as shown in Figure 1, comprise upper half part and lower half portion, upper half part is an outer cover 2, lower half portion comprises precursor 1, dividing plate 3 and back body 4; Be the venting channels of said binary mixed pressure intake duct between upper half part and lower half portion, 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 back body 4; The auxiliary passage of absorbing of one boundary layer is arranged between precursor 1 and the dividing plate 3; The auxiliary passage of absorbing of this boundary layer is communicated with the venting channels of said binary mixed pressure intake duct; Be communicated with the 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 promptly the distance between precursor 1 and the dividing plate 3 is even; There is a boundary layer to absorb chamber 7 between dividing plate 3 and the back body 4; Boundary layer is absorbed chamber 7 and is communicated with venturi 9; Be communicated with the position and be boundary layer absorption chamber inlet 6; The auxiliary outlet of absorbing passage of said boundary layer enters into boundary layer and absorbs 7 inside, chamber, and boundary layer is absorbed chamber outlet 8 between precursor 1 and back body 4; The auxiliary absorption of boundary layer feeder connection 5, boundary layer absorb chamber inlet 6 and boundary layer is absorbed chamber outlet 8 connections.
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 when reaching the starting Mach number one oblique shock wave and said binary mixed pressure intake duct.The position that boundary layer is absorbed chamber inlet 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 when reaching the 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 the chamber and entered the mouth 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 inlet 6 and the 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 the venting channels that gets into binary mixed pressure intake duct; The certain thickness boundary layer of formation on precursor 1, and the leading edge of outer cover 2 also will compress and form one oblique shock wave to incoming flow and incide in the venting channels of binary mixed pressure intake duct.Near the starting 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; Interact and the generation separate bubble with the boundary layer that forms on the precursor 1; Separate bubble can produce the effect of the venting channels area that reduces binary mixed pressure intake duct, causes the intake duct can't normal starting.2-3mm is provided with the auxiliary feeder connection 5 of absorbing of narrower boundary layer in drop point the place ahead; Utilize the poor of the inner static pressure with external environment of intake duct; Enter the external world with the boundary layer suction that forms on a part of precursor 1 and through boundary layer absorption chamber 7, thereby reduce the interaction of oblique shock wave and boundary layer and finally play the effect that reduces the starting Mach number.On the other hand, under the 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 this moment, shock strength was bigger, and is strong with the boundary layer interaction at venturi 9 lower wall surface places.2-3mm is provided with the boundary layer absorption chamber inlet 6 of broad in this place ahead; The boundary layer suction of a part of venturi 9 lower wall surfaces is also absorbed chamber 7 through boundary layer equally enter the external world; Reduce the interaction and the stable ending normal shock wave of oblique shock wave and boundary layer, finally improve the overall performance of intake duct.Boundary layer is auxiliary absorbs that feeder connection 5, boundary layer are absorbed chamber inlet 6, boundary layer absorbs chamber 7 and boundary layer is absorbed chamber outlet 8 all to intake duct front end inclination several angle, with the absorption that helps boundary layer and reduce the outer influence on flow field of intake duct.
Embodiment:
Ultrasonicly tachy sterol towards motor binary mixed pressure intake duct two wedges, three wave systems.Starting Mach number 2.5, design Mach number 3.0.According to intake duct structure of the present invention,, confirm auxiliary position and the width of absorbing feeder connection 5 and boundary layer absorption chamber inlet 6 of boundary layer through numerical simulation and engineering calculation.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, boundary layer absorb the chamber enter the mouth 6 be positioned at outer cover 2 the leading edge lip about 81mm of horizontal equivalent backward.
Said structure is carried out 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, and does not compare (under equal design condition and test conditions with the conventional intake duct of absorption; σ is about 0.45), its total pressure recovery coefficient has improved about 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 about 20%.The flow coefficient of the design's structure when the design Mach number is 0.976, shows that the absorption flow is lower.
In sum, the present invention can effectively absorb the boundary layer in the intake duct, can effectively suppress boundary layer separation in the intake duct, reduces the phase mutual interference of shock wave/boundary layer, promotes inlet characteristic to a great extent.Preparation process is simple, does not destroy the structure of original intake duct, has scientific and technological widely purposes.
The unspecified part of the present invention belongs to general knowledge as well known to those skilled in the art.
Claims (7)
1. one kind is applied to ultrasonic tachy steroling towards the binary mixed pressure intake duct of motor, it 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 back body (4); Be the venting channels of said binary mixed pressure intake duct between upper half part and lower half portion, 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 back body (4); The auxiliary passage of absorbing of one boundary layer is arranged between precursor (1) and the dividing plate (3); The auxiliary passage of absorbing of this boundary layer is communicated with the venting channels of said binary mixed pressure intake duct, is communicated with the position and is the auxiliary feeder connection (5) of absorbing of boundary layer; There is a boundary layer to absorb chamber (7) between dividing plate (3) and the back body (4); Boundary layer is absorbed chamber (7) and is communicated with venturi (9); Be communicated with the position and be boundary layer absorption chamber inlet (6); The auxiliary outlet of absorbing passage of said 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 the back body (4); The auxiliary absorption of boundary layer feeder connection (5), boundary layer absorb chamber inlet (6) and boundary layer is absorbed chamber outlet (8) connection.
2. a kind of ultrasonic tachy steroling towards the binary mixed pressure intake duct of motor that be applied to according to claim 1 is characterized in that: 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) when reaching the starting Mach number and said binary mixed pressure intake duct.
3. a kind of ultrasonic tachy steroling towards the binary mixed pressure intake duct of motor that be applied to according to claim 1 is characterized in that: the position that described boundary layer is absorbed chamber inlet (6) is one oblique shock wave forming of the leading edge of binary mixed pressure intake duct outer cover (2) when reaching the design Mach number and the 2-3mm place, intersection point the place ahead of venturi (9) lower wall surface.
4. a kind of ultrasonic tachy steroling that be applied to according to claim 1 towards the binary mixed pressure intake duct of motor; It is characterized in that: auxiliary feeder connection (5) width of absorbing of boundary layer is between 2-4mm; Boundary layer is absorbed chamber inlet (6) width between 7-9mm, and boundary layer is absorbed the width of chamber outlet (8) between 8-10mm.
5. a kind of ultrasonic tachy steroling towards the binary mixed pressure intake duct of motor that be applied to according to claim 1 is characterized in that: the auxiliary passage of absorbing of said boundary layer tilts to binary mixed pressure intake duct front end, and itself and horizontal plane angle are 20.5 °.
6. a kind of ultrasonic tachy steroling that be applied to according to claim 1 towards the binary mixed pressure intake duct of motor; It is characterized in that: the central point that boundary layer is absorbed chamber inlet (6) and boundary layer are absorbed line between the central point of chamber outlet (8) to the inclination of binary mixed pressure intake duct front end, and the angle of itself and horizontal plane is 30 °.
7. a kind of ultrasonic tachy steroling towards the binary mixed pressure intake duct of motor that be applied to according to claim 1 is characterized in that: the height of the auxiliary absorption of said boundary layer passage is even, and promptly the distance between precursor (1) and the dividing plate (3) is even.
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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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| CN201210293527.9A CN102817716B (en) | 2012-08-17 | 2012-08-17 | Binary mixed pressure intake duct applied to supersonic solid ramjet |
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| CN102817716B CN102817716B (en) | 2014-09-10 |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105221266A (en) * | 2015-10-29 | 2016-01-06 | 西北工业大学 | A kind of rocket based combined cycle motor becomes absorbs control intake duct |
| CN106989891A (en) * | 2017-03-30 | 2017-07-28 | 南京航空航天大学 | Hypersonic inlet accelerates self-starting experimental method |
| CN107061011A (en) * | 2017-06-02 | 2017-08-18 | 南京航空航天大学 | Low extrernal resistance hypersonic inlet |
| US10077675B2 (en) | 2015-10-20 | 2018-09-18 | Rolls-Royce Plc | Fluid system |
| CN110805695A (en) * | 2019-11-11 | 2020-02-18 | 北京动力机械研究所 | Movable sealing structure of adjustable flow passage rotating shaft |
| CN112392600A (en) * | 2020-11-17 | 2021-02-23 | 北京动力机械研究所 | Absorbing and removing structure for central cone boundary layer of axisymmetric adjustable air inlet |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10077675B2 (en) | 2015-10-20 | 2018-09-18 | Rolls-Royce Plc | Fluid system |
| CN105221266A (en) * | 2015-10-29 | 2016-01-06 | 西北工业大学 | A kind of rocket based combined cycle motor becomes absorbs control intake duct |
| CN106989891A (en) * | 2017-03-30 | 2017-07-28 | 南京航空航天大学 | Hypersonic inlet accelerates self-starting experimental method |
| 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 |
| CN107061011A (en) * | 2017-06-02 | 2017-08-18 | 南京航空航天大学 | Low extrernal resistance hypersonic inlet |
| CN110805695A (en) * | 2019-11-11 | 2020-02-18 | 北京动力机械研究所 | Movable sealing structure of adjustable flow passage rotating shaft |
| 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 |
| CN112392600A (en) * | 2020-11-17 | 2021-02-23 | 北京动力机械研究所 | Absorbing and removing structure for central cone boundary layer of axisymmetric adjustable air inlet |
| 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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| CN102817716B (en) | 2014-09-10 |
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