CN110486168B - Binary supersonic inlet duct with step type side plate - Google Patents
Binary supersonic inlet duct with step type side plate Download PDFInfo
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- CN110486168B CN110486168B CN201910880002.7A CN201910880002A CN110486168B CN 110486168 B CN110486168 B CN 110486168B CN 201910880002 A CN201910880002 A CN 201910880002A CN 110486168 B CN110486168 B CN 110486168B
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- 230000006835 compression Effects 0.000 claims abstract description 42
- 238000007906 compression Methods 0.000 claims abstract description 42
- 230000035939 shock Effects 0.000 abstract description 20
- 238000011084 recovery Methods 0.000 abstract description 12
- 238000000926 separation method Methods 0.000 abstract description 7
- 238000010408 sweeping Methods 0.000 abstract 1
- 230000000694 effects Effects 0.000 description 3
- 239000000446 fuel Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 230000002411 adverse Effects 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 238000007664 blowing Methods 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012418 validation experiment Methods 0.000 description 1
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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)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a binary supersonic air inlet channel with a step type side plate, which comprises an inner compression surface, an outer compression surface, a lip cover and a side plate, wherein the inner compression surface is provided with a plurality of convex ribs; the side plates comprise a first side plate positioned on the outer sides of the lip cover and the inner compression surface and a second side plate positioned on the outer side of the outer compression surface; the intersection of the second side plate and the first side plate forms a step fall, and the step fall forms a certain overflow port near the lip of the air inlet channel. The overflow port dredges and eliminates part of the side plate boundary layer, and can effectively weaken the interference of the sweeping shock wave of the outer compression surface and the lip cover and the side plate boundary layer, thereby reducing the air flow separation at the inlet of the air inlet channel and improving the flow coefficient and the total pressure recovery coefficient of the air inlet channel.
Description
Technical Field
The invention relates to the field of design of air-breathing supersonic aircrafts, in particular to a binary supersonic air inlet channel.
Background
The air inlet channel is used as a key pneumatic component of the air-breathing supersonic propulsion system, and bears the tasks of capturing high-speed airflow and compressing air to enable the outlet airflow to meet the requirements of an air compressor or a combustion chamber, and the design form and the working characteristics of the air inlet channel directly influence the overall efficiency performance of the propulsion system. And (3) judging the performance of the supersonic air inlet channel, and evaluating the performance of the supersonic air inlet channel mainly from parameters such as total pressure recovery coefficient, flow coefficient and the like.
The flow loss in the supersonic air inlet channel mainly comprises total pressure loss of a shock wave system, total pressure loss in a channel behind a throat channel, friction loss caused by gas viscosity and viscous interference loss. Wherein viscous disturbance loss is generated by the separation of air flow in the presence of an inverse pressure gradient, and occupies a considerable proportion of the total loss, typically represented by the separation phenomenon caused by shock wave/boundary layer disturbance. According to research, the thrust loss exceeds 1 percent and is generally about 1.25 percent when the total pressure recovery coefficient of the air inlet is reduced by 1 percent, and the unit fuel consumption rate is increased by 2.5 percent. The thrust loss and the specific fuel consumption increase more significantly with increasing flying speed. Therefore, reducing the problem of shock boundary layer interference becomes one of the research focuses on supersonic flow.
At present, the study on the shock wave/boundary layer interference control of a binary supersonic air inlet channel mainly focuses on the improvement of the adverse resistance pressure gradient characteristic of the boundary layer, such as the arrangement of a blowing groove, an air release groove, the installation of a vortex generator and the like. The existing research results show that the control method has an obvious control effect on flow separation caused by shock wave/boundary layer interference. Among various interference phenomena, lip shroud shock waves/boundary layer interference is often strong and directly affects the working performance of the air inlet channel. At present, the improvement measures for the interference of the lip cover shock wave and the side plate boundary layer are less, and in actual work, under the influence of the inverse pressure gradient of the external compression surface and the lip cover oblique shock wave, the boundary layer of the side wall surface is easy to separate, and the flow field of the compression surface near the side wall surface is directly influenced, so that the total pressure recovery coefficient and the flow coefficient of the air inlet channel are reduced.
Disclosure of Invention
The purpose of the invention is as follows: in order to weaken the total pressure loss and flow loss caused by the interference of the external compression surface of the binary supersonic air inlet, the oblique shock wave of the lip cover and the boundary layer of the side plate, the invention provides the binary supersonic air inlet with the stepped side plate so as to improve the flow and the total pressure recovery coefficient of the air inlet.
The technical scheme is as follows: in order to achieve the above object, the present invention provides the following technical solutions.
A binary supersonic air inlet channel with a step type side plate comprises an inner compression surface, an outer compression surface, a lip cover positioned above the inner compression surface and the side plate; an inner channel of the air inlet channel is formed between the inner compression surface and the lip cover, the inner compression surface is positioned inside an inlet of the inner channel, and the outer compression surface is positioned outside the inlet of the inner channel; the side plates comprise a first side plate positioned on the outer sides of the lip cover and the inner compression surface and a second side plate positioned on the outer side of the outer compression surface; the first side plate forms a side wall of the inner channel; the intersection of the second side plate and the first side plate forms a step fall, the height of the second side plate is lower than that of the first side plate, and the upper edge of the second side plate forms a continuous bevel edge extending from high to low.
Has the advantages that: the stepped side plate is arranged, namely the second side plate does not completely shield the outer side of the inlet of the air inlet, but the outer side of the inlet of the air inlet is exposed out of a part of the overflow port in a stepped drop manner. The method simultaneously weakens the negative effects of the three aspects; firstly, the boundary layer of the inlet of the air inlet channel is re-developed, and the influence of the angular region vortex of the channel in the binary air inlet channel on the total pressure loss is weakened; secondly, the interference of the oblique shock wave of the outer compression surface and the boundary layer near the lip side plate is weakened; thirdly, the interference of the lip oblique shock wave and the boundary layer of the side plate of the channel in the air inlet channel is weakened. The separation bag at the inlet of the air inlet channel is obviously reduced, and the effective flow area of the air inlet channel is increased. Compared with the existing control scheme and the base profile without control, the air inlet with the step type side plate can effectively improve the total pressure recovery coefficient of the air inlet without sacrificing flow and under the condition that the flow is improved to a certain extent, and the performance of the air inlet is improved.
Drawings
Fig. 1 is a three-dimensional structure diagram of the interior of a binary supersonic air inlet having stepped side plates according to the present invention.
Fig. 2 is a three-dimensional structure view of the exterior of a two-dimensional supersonic air inlet having stepped side plates according to the present invention.
Fig. 3 is a front view of the stepped side plate.
Fig. 4(a) is a mach number cloud plot of a sideplate-free chamfered inlet duct x-370 mm cross-section.
Figure 4(b) is a mach number cloud with a chamfer height of 8mm and a cross-section of x 370 mm.
Figure 4(c) is a mach number cloud with a chamfer height of 16mm and a cross-section of x 370 mm.
Figure 4(d) is a mach number cloud with a chamfer height of 24mm and a cross-section of x 370 mm.
Figure 4(e) is a mach number cloud with a chamfer height of 32mm and a cross-section of x 370 mm.
Fig. 5(a) is a mach number cloud plot of a 16mm and 32mm cutoff z-inlet port without a side panel chamfer.
Figure 5(b) is a mach number cloud with a chamfer of 8mm height, z 16mm and z 32 mm.
Figure 5(c) is a mach number cloud with a chamfer of 16mm height, z 16mm and z 32 mm.
Figure 5(d) is a mach number cloud with a chamfer of 24mm height, z 16mm and z 32 mm.
Figure 5(e) is a mach number cloud with a chamfer of 32mm height, z 16mm and z 32 mm.
FIG. 6 is a graph of inlet flow versus side plate chamfer height.
FIG. 7 is a graph of total pressure recovery coefficient of an inlet throat as a function of side plate chamfer height.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings.
Referring to fig. 1 to 3, the present invention provides a two-dimensional supersonic inlet with a stepped side plate, which includes an inner compression surface 2, an outer compression surface 1, a lip cover 3 located above the inner compression surface 2, and a side plate 4. An inner channel 6 of the air inlet channel is formed between the inner compression surface 2 and the lip cover 3. The inner compression surface 2 is located inside the inlet 7 of the inner channel 6 and the outer compression surface 1 is located outside the inlet 7 of the inner channel. The side plates 4 comprise a first side plate 8 positioned outside the lip cover 3 and the inner compression surface 2 and a second side plate 9 positioned outside the outer compression surface 1; the first side plate 8 forms the side wall of the inner channel. The second side plate 9 and the first side plate 8 meet to form a step head 10. The step 10 forms an overflow 11 between the leading edge of the lip 3 and the upper edge of the second side plate 9. The height of the second side panel 9 is lower than the height of the first side panel 8. The inlet front edge part of the channel in the air inlet channel is a lip 12, the height of the second side plate 9 (the beveling height in fig. 3) is the distance from the lip 12 downwards to the lip cover 3, and the height of the second side plate 9 is less than one third of the vertical distance between the lip of the air inlet channel and the outer compression surface. The upper edge of the second side plate 9 forms a continuous high-to-low extending bevelled edge. Meanwhile, the inner compression surface is provided with a drainage groove 5 communicated with the inner channel. In the embodiment, the supersonic air inlet channel is 35mm wide, and the incoming flow mach number in the designed working state is 3.2.
In the present embodiment, the step 10 between the second side plate 9 and the first side plate 8 can be considered to be formed by chamfering the upper edge of the second side plate 9. In order to reduce the influence of the boundary layer of the two-dimensional supersonic inlet side plate on the flow field and the performance of the inlet at the inlet of the inlet, the original fully-closed second side plate (the fully-closed second side plate which is not obliquely cut completely shields the side edge of the lip) is symmetrically and obliquely cut off a side plate body with a certain depth. Under the premise of ensuring the structural strength of the side plates, the second side plate 9 can be inclined at any angle (inclined angle in fig. 3) and inclined at any height to achieve the purpose of eliminating the low-energy flow of the boundary layer on the side plate of the air inlet channel.
Furthermore, the starting point of beveling is arranged at the intersection point 13 of the inlet lip cover 3 and the original closed side plate, namely the inlet corner area of the air inlet channel and two oblique shock wave interference areas, so that the influence of a thicker boundary layer developed by the second side plate 9 on the performance of the inner channel flow field and the air inlet channel can be effectively weakened, and therefore the second side plate 9 is arranged below the inlet lip cover 3. The cut side plate part is a right-angled triangle, the short side of the right angle is vertical to the outer wall surface of the inlet lip cover 3, and the included angle between the long side of the right angle and the bevel edge of the original side plate is a beveling angle. Still further, in order to remove the side plate boundary layer without causing excessive overflow, the height of the second side plate 9 should be less than one third of the vertical distance between the inlet lip 3 and the outer compression surface 1.
Examples of the applications
(1) The technical indexes are as follows:
the designed supersonic air inlet channel has the working range of Ma2.45-3.8, the flying height of 10-24km and the incoming flow Mach number of 3.2 in the designed working state.
(2) Introduction of the scheme:
to validate the invention, the following validation experiments were designed. In the experiment, the prototype binary supersonic inlet adopts a binary four-wave system supersonic inlet with the design working state of Ma3.2 and the attack angle of 4 degrees. And (3) performing beveling treatment on the side plate of the air inlet, wherein the beveling angle is 6.4 degrees, and the beveling height is set to be 8, 16, 24 and 32 mm.
(3) The oblique cutting of the side plate has the influence on the flow field structure:
fig. 4(a) - (e) show the mach number clouds of the air inlet channels with different side plate beveling heights at the cross section of x ═ 370mm respectively. It can be seen that the last oblique shock wave on the compression surface 1 of the inlet duct presents different shapes for different side plate bevelling heights. For the inlet duct without a side panel chamfer, fig. 4(a), the oblique shock wave near the side panel is lifted and appears concave. The oblique shock wave generated by the outer compression surface is separated from the air flow formed by the interference of a thicker boundary layer on a side plate below the inlet of the air inlet, a larger separation area exists in a corner area at the inlet of the air inlet, and the oblique shock wave is lifted. After a certain amount of beveling is carried out on the side plate, as shown in fig. 4(b) to (e), the bending oblique shock wave near the side plate is gradually leveled, and the shock wave/boundary layer interference phenomenon near the lip cover is relieved to a certain extent. Fig. 5(a) - (e) show the mach number clouds at inlet cross-sections z 16mm and z 32mm at different side panel chamfer heights. Comparing the figures, it is obvious that the oblique shock wave of the outer compression surface is gradually sealed along with the increase of the oblique cutting height, so that the overflow at the position of the air inlet lip cover is reduced. This explains to some extent the phenomenon of increased inlet flow due to the bevelling of the side plates.
(4) The oblique cutting of the side plate has influence on the performance of the air inlet:
the bevelling of the side plates has a large impact on the performance of the air intake duct. FIGS. 6 and 7 are graphs of inlet flow and total pressure recovery coefficient at the throat as a function of side plate chamfer angle height. It can be seen that when the chamfering height is 8mm, the flow and total pressure recovery coefficient of the air inlet channel are not greatly improved, the chamfering height is small, and the effect of controlling flow field separation is not achieved; when the beveling height is increased to 16mm and 24mm, the flow rate and the total pressure recovery coefficient of the air inlet channel are both obviously improved; the flow is improved by 1% to the maximum, and the total pressure recovery coefficient is improved by 2.3% to the maximum; when the chamfer height is increased to 32mm, the total pressure recovery coefficient is highest, but the flow rate of the air inlet channel is greatly reduced, which is mainly caused by the fact that the chamfer side plate area is too large and the overflow amount is increased. In practical application, the beveling height of the air inlet channel is selected between 16mm and 24mm, so that the performance of the air inlet channel can be effectively improved.
In conclusion, the supersonic air inlet channel can not only improve the working performance of the air inlet channel, but also improve the flow capture of the air inlet channel, so that the design scheme is feasible.
The foregoing is only a preferred embodiment of the present invention, and it should be noted that several deductions or substitutions can be made without departing from the spirit of the present invention, and all such deductions or substitutions should be considered as the protection scope of the present invention.
Claims (5)
1. A binary supersonic air inlet channel with a step type side plate comprises an inner compression surface, an outer compression surface, a lip cover positioned above the inner compression surface and the side plate; an inner channel of the air inlet channel is formed between the inner compression surface and the lip cover, the inner compression surface is positioned inside an inlet of the inner channel, and the outer compression surface is positioned outside the inlet of the inner channel; the side plates comprise a first side plate positioned on the outer sides of the lip cover and the inner compression surface and a second side plate positioned on the outer side of the outer compression surface; the first side plate forms a side wall of the inner channel; the height of the second side plate is lower than that of the first side plate, and the upper edge of the second side plate forms a continuous bevel edge extending from high to low; the step fall between the second side plate and the first side plate is formed by beveling the upper edge of the second side plate at a beveling angle; the beveling height of the air inlet channel is selected to be between 16mm and 24 mm; the incoming flow Mach number of the supersonic air inlet channel in the working state is 3.2.
2. The binary supersonic air inlet according to claim 1, characterized in that: the inlet front edge part of passageway is the lip in the intake duct, the second curb plate height is for following the distance of lip downward and perpendicular to lip cover, and the second curb plate height is less than intake duct lip and the one third of external compression face vertical distance.
3. The binary supersonic air inlet according to claim 2, characterized in that: and the inner compression surface is provided with a drainage groove communicated with the inner channel.
4. The binary supersonic air inlet according to claim 3, characterized in that: the second side plate is in the shape of a right triangle.
5. The binary supersonic air inlet according to claim 3, characterized in that: the joint of the bottom of the step fall and the second side plate is a right-angle radius with the radius of 8 mm.
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| CN201910880002.7A CN110486168B (en) | 2019-09-18 | 2019-09-18 | Binary supersonic inlet duct with step type side plate |
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| CN201910880002.7A CN110486168B (en) | 2019-09-18 | 2019-09-18 | Binary supersonic inlet duct with step type side plate |
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| CN110486168B true CN110486168B (en) | 2020-07-28 |
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Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1055607A (en) * | 1965-10-11 | 1967-01-18 | Rolls Royce | Supersonic intake for a jet engine |
| IL62132A0 (en) * | 1980-02-26 | 1981-03-31 | Gen Electric | Inlet cowl for a two-dimensional inlet |
| US9447731B1 (en) * | 2012-08-15 | 2016-09-20 | The Boeing Company | Supersonic elliptical ramp inlet |
| CN107089341B (en) * | 2017-06-05 | 2018-07-27 | 南京航空航天大学 | With aircraft integrated hypersonic inlet external compression face design method |
| CN108412617B (en) * | 2018-03-20 | 2019-03-29 | 南京航空航天大学 | A kind of air intake duct and widen the design method that air intake duct excess determines free stream Mach number range |
| CN108412620B (en) * | 2018-03-20 | 2019-03-29 | 南京航空航天大学 | A kind of adjustable air intake duct of capture area and traffic capture rea adjusting method |
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