CN115290291A - Experimental device for simulating boundary layer leakage flow and subsonic velocity outflow coupling effect - Google Patents
Experimental device for simulating boundary layer leakage flow and subsonic velocity outflow coupling effect Download PDFInfo
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- 230000001808 coupling effect Effects 0.000 title claims abstract description 14
- 238000012360 testing method Methods 0.000 claims abstract description 39
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- 230000008602 contraction Effects 0.000 claims description 34
- 230000003068 static effect Effects 0.000 claims description 29
- 238000006073 displacement reaction Methods 0.000 claims description 21
- 238000007599 discharging Methods 0.000 claims description 10
- 230000008719 thickening Effects 0.000 claims description 8
- 238000011144 upstream manufacturing Methods 0.000 claims description 8
- 239000000654 additive Substances 0.000 claims description 5
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- 238000003556 assay Methods 0.000 claims 6
- 238000002474 experimental method Methods 0.000 abstract description 18
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- 230000008569 process Effects 0.000 abstract description 4
- 230000008878 coupling Effects 0.000 abstract description 3
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- 238000005859 coupling reaction Methods 0.000 abstract description 3
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- 238000013461 design Methods 0.000 description 6
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- 238000010521 absorption reaction Methods 0.000 description 1
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Abstract
The invention provides an experimental device capable of simulating the coupling effect of boundary layer leakage flow and subsonic velocity outflow flow. The main pipeline and the auxiliary pipeline suck air from the atmospheric environment, outlets of the main pipeline and the auxiliary pipeline are connected with a low-pressure air source through valves, and the Mach number of a test section required by an experiment can be matched by adjusting the opening degree of a downstream ball valve of the experiment table in the experiment process. The subsonic velocity experiment table device is simple in pneumatic principle, easy to realize in structure, wide in range of simulating incoming flow Mach number, low in requirements on experiment sites and air sources, and capable of greatly reducing experiment cost. Therefore, on the premise of ensuring the economy, the invention can accurately simulate the subsonic flow field, and provides a feasible experimental device for researching the boundary layer leakage flow and subsonic outflow coupling mechanism.
Description
Technical Field
The invention relates to the field of subsonic flow experiments, in particular to an experiment table device capable of simulating the coupling effect of boundary layer leakage flow and subsonic outflow flow.
Background
The air intake duct is located at the most front end of the air-breathing propulsion system and is mainly responsible for capturing, compressing and adjusting free incoming flow to provide air flow with sufficient flow, pressure and uniformity for the engine, and is called as the throat main duct of the engine. Also, the inlet duct is also an aerodynamic link coupling the engine and the aircraft, and a strong source of scattering of radar waves. Therefore, the air inlet channel has important influences on the working efficiency, the working envelope and the working safety of the engine, as well as the aerodynamic characteristics and the stealth performance of the aircraft, and the design of the air inlet channel becomes one of the key problems which must be firstly broken through in the process of developing various advanced aviation weaponry in China.
The air inlet has the characteristics of complex internal flow mechanism, variable upstream and downstream working conditions, high pneumatic performance requirement (low loss, low distortion) and the like, and the pneumatic design challenge is large, so that the flow control measure is widely used in the pneumatic design of the air inlet. The common air inlet channel flow control measures comprise boundary layer suction, boundary layer partitions, inlet bulges, vortex generators and the like, and for the boundary layer suction flow control measures, the factors influencing the control effect of the boundary layer suction flow control measures comprise the air inlet efficiency, the flow resistance of an inner channel and the air discharge resistance of a boundary layer suction device. Wherein, the air bleeding resistance generally relates to the coupling effect of the boundary layer leakage flow and the aircraft outflow, therefore, compared with the air intake efficiency and the inner channel circulation resistance, the air bleeding resistance is the main factor influencing the working efficiency of the boundary layer suction flow control device. In addition, because the air discharge resistance is influenced by the coupling effect of the inner flow and the outer flow, the air discharge resistance cannot be reasonably estimated in the design stage of the boundary layer suction flow control device, so that the optimal aerodynamic performance cannot be obtained in the design of the boundary layer suction flow control device. Meanwhile, in the conventional wind tunnel at present, the coupling effect of boundary layer leakage flow and outflow flow cannot be simulated finely.
Therefore, on the premise of guaranteeing accurate simulation of boundary layer leakage flow and outflow, an experimental device convenient for observing a flow field structure of the coupling action of the boundary layer leakage flow and the outflow is required to be designed, and meanwhile, the experimental device is simple in structure as much as possible and easy to operate and maintain.
Disclosure of Invention
In order to solve the above problems, the present invention provides an experimental apparatus for simulating the coupling effect of boundary layer leakage flow and subsonic outflow, which can simultaneously simulate boundary layer leakage flow and subsonic outflow, and is convenient for studying the coupling effect of boundary layer leakage flow and outflow under different inflow conditions. Meanwhile, the device has the advantages of simple structure, small size, low requirements on an experimental site and air source capacity and convenience in operation and maintenance.
In order to achieve the purpose, the technical scheme adopted by the invention is as follows:
an experimental device capable of simulating the coupling effect of boundary layer leakage flow and subsonic velocity outflow comprises a main pipeline, an auxiliary pipeline and an embedded boundary layer displacement device; the main pipeline comprises a first inlet section, a first rectifying section, a first contraction section, a first boundary layer development section, a first test section and a first switching section which are connected in sequence; the auxiliary pipeline comprises a second inlet section, a second rectifying section, a second contraction section, a second boundary layer development section, a second test section and a second switching section which are connected in sequence; boundary layer thickening devices are mounted on the outer side surfaces of the first boundary layer development section and the second boundary layer development section; the embedded boundary layer displacement device is arranged on the first wall surface of the first test section, the embedded boundary layer displacement device is arranged on the second wall surface of the second test section, and the embedded boundary layer displacement device is used for communicating the main pipeline with the auxiliary pipeline; a first boundary layer measuring device is arranged at an outlet of the first boundary layer development section; a second boundary layer measuring device is arranged at the upstream of the outlet of the embedded boundary layer displacement device; the first test section is provided with a third boundary layer measuring device; the main pipeline is provided with a first static pressure hole extending along the symmetric center on the wall surface where the inlet of the embedded boundary layer discharging and moving device is located and the opposite side wall surface back to the wall surface, and the auxiliary pipeline is provided with a second static pressure hole extending along the symmetric center on the wall surface where the outlet of the embedded boundary layer discharging and moving device is located and the opposite side wall surface back to the wall surface; the first static pressure hole and the second static pressure hole are used for installing static pressure probes.
Further, the inlet of the main pipeline and the inlet of the auxiliary pipeline are not coherent with each other.
Further, the first inlet section, the first rectifying section and the first contraction section are integrally processed by adopting an additive manufacturing technology; the second inlet section, the second rectifying section and the second contraction section are integrally processed by adopting an additive manufacturing technology.
Further, the first inlet section and the second inlet section are consistent in pipeline configuration; the first rectifying section and the second rectifying section have the same pipeline configuration; the first contraction section and the second contraction section have the same pipeline configuration; the first boundary layer development section and the second boundary layer development section have the same pipeline configuration.
Further, the length of the first rectifying section is not less than 2 times of the height of the outlet of the first contraction section; the second fairing section has a length no less than 2 times the second constrictor outlet height.
Furthermore, the contraction ratio of the first contraction section to the second contraction section is not less than 5.
Furthermore, the first boundary layer development section and the second boundary layer development section have single-side expansion of the upper wall surface, and the expansion angle is 0.3 degrees.
Furthermore, the thickness of the boundary layer at the outlet of the first boundary layer development section and the thickness of the boundary layer at the outlet of the second boundary layer development section are both controlled by the boundary layer thickening device.
Further, the outlet of the embedded boundary layer displacement device is installed on the wall surface of the second test section through an outlet installation plate of the embedded boundary layer displacement device.
Furthermore, the first static pressure holes positioned in the first contraction section, the first boundary layer development section and the first test section part are arranged at equal intervals of 10mm, and the first static pressure holes positioned in the first inlet section, the first rectifying section and the first switching section part are arranged at equal intervals of 25mm; the second static holes positioned in the second contraction section, the second boundary layer development section and the second test section are arranged at equal intervals of 10mm, and the second static holes positioned in the second inlet section, the second rectifying section and the second switching section are arranged at equal intervals of 25 mm.
Has the advantages that: compared with the conventional subsonic wind tunnel, the experimental bench device realized by the invention can simulate boundary layer leakage flow and subsonic outflow in a refined manner, and further can study the coupling effect of the boundary layer leakage flow and the subsonic outflow in a detailed manner, so that experimental data support can be provided for the design of flow control devices such as boundary layer absorption and removal. In addition, the experiment table device is simple in structure, small in size, low in maintenance cost and experiment cost, wide in range of simulated incoming flow Mach number, low in requirements on an experiment field and an air source, and capable of providing a practical experiment device for researching boundary layer leakage flow and subsonic velocity outflow coupling mechanism.
Drawings
FIG. 1 is a perspective view of a boundary layer measuring device provided by the present invention;
FIG. 2 is a view showing the construction of a main pipe according to the present invention;
FIG. 3 is a view showing the construction of a secondary duct according to the present invention;
FIG. 4 is a schematic view of a boundary layer thickening apparatus;
FIG. 5 is a schematic view of a boundary layer measurement apparatus;
FIG. 6 is the distribution of the flow direction Mach numbers at the positions where the symmetric planes of the main/auxiliary ducts are 0.26H, 0.50H and 0.74H degrees away from the lower wall surface under the condition that the test section inlet airflow Mach number is 0.54;
FIG. 7 shows the distribution of Mach number of the flow direction at the positions where the symmetry plane of the main/sub duct is 0.26H, 0.50H and 0.74H away from the lower wall surface under the condition of the test section inlet flow Mach number of 0.75.
Detailed Description
The invention discloses an experimental device for simulating the coupling effect of boundary layer leakage flow and subsonic velocity outflow. The experimental device designed by the method of the invention and having the test section Mach number of 0.50-0.75 and the maximum sum of the two channel flow rates of 1.5kg/s is described below. Referring to fig. 1 to 5, the experimental apparatus includes a main pipe, a sub-pipe, and a buried boundary layer displacement apparatus 11. The main pipeline comprises a first inlet section 1, a first rectifying section 2, a first contraction section 3, a first boundary layer development section 4, a first test section 5 and a first switching section 6 which are connected in sequence. The secondary pipeline comprises a second inlet section 1', a second rectifying section 2', a second contraction section 3', a second boundary layer development section 4', a second test section 5 'and a second switching section 6' which are connected in sequence. And boundary layer thickening devices are arranged on the outer side surfaces of the first boundary layer development section 4 and the second boundary layer development section 4'. The inlet of the embedded boundary layer displacement device 11 is installed on one wall surface of the first test section 5, the outlet of the embedded boundary layer displacement device 11 is installed on one wall surface of the second test section 5', and the embedded boundary layer displacement device 11 communicates the main pipeline with the secondary pipeline.
A first boundary layer measuring device 8 is arranged at the outlet of the first boundary layer development section 4. And a second boundary layer measuring device 9 is arranged at the upstream of the outlet of the embedded boundary layer displacement device 11. The first test section 5 is equipped with a third boundary layer measuring device 10.
The main pipeline is provided with a first static pressure hole 21 extending along the symmetry center on the wall surface where the inlet of the embedded boundary layer discharging device 11 is located and the opposite side wall surface back to the wall surface, and the auxiliary pipeline is provided with a second static pressure hole 22 extending along the symmetry center on the wall surface where the outlet of the embedded boundary layer discharging device 11 is located and the opposite side wall surface back to the wall surface; the first static pressure hole 21 and the second static pressure hole 22 are used for installing a static pressure probe, and the diameter of the static pressure hole is 1.1mm.
The inlet sections 1/1', the rectifying sections 2/2' and the contraction sections 3/3' of the main pipeline and the auxiliary pipeline are manufactured by an additive manufacturing method, so that the number of connecting pieces is reduced, and the interference on a downstream flow field is reduced. In addition, in order to reduce the influence of the airflow at the inlet of the channel on the other channel in the experimental process, the center distance between the inlet sections of the two channels of pipelines is more than 8 times of the height of the outlet of the contraction section of the experimental table; in order to improve the uniformity of the airflow at the inlet of the test section 5/5', the length of the rectifying section 2/2' is not less than 2 times of the outlet height of the contraction section of the test table, and the contraction ratio of the contraction section 3/3' is not less than 5.
The outlet of the contraction section 3/3' is connected with a boundary layer development section 4/4', the upstream lower wall surface side of the boundary layer development section 4/4' is provided with a replaceable boundary layer thickening device 7/7', and the characteristic parameter (the height (h) of a first row of cylinders) of the boundary layer thickening device 7/7' is changed 1 ) Center distance of first row of cylinders(l 1 ) Second row of cylinder height (h) 2 ) The center distance of the second row of cylinders 2 ) The central distance between the first row of cylinders and the second row of cylinders 3 ) Control of the boundary layer thickness at the exit of the boundary layer development section may be achieved. Meanwhile, the thickness of the boundary layer at the outlet of the boundary layer development section of the main pipe can be measured by a boundary layer measuring device 8 installed at the outlet of the boundary layer development section 4 on the lower wall surface side. The boundary layer growth rate of the wall surface of the boundary layer development section is high, the influence of the wall surface boundary layer on the Mach number of the main flow is weakened, the flowing speed of the air flow in the downstream main flow region of the boundary layer development section is constant, the pipeline profile of the boundary layer development section has unilateral expansion (upper wall surface expansion), the pipeline expansion angle is generally not larger than 0.5 degrees according to the related engineering experience, and the upper wall surface has 0.3 degree unilateral expansion in the present case.
The outlet of the boundary layer development section 4/4 'is connected with the test section 5/5', the inlet of the embedded boundary layer discharging device 11 is installed on the lower wall surface of the main pipeline test section 5, the outlet of the embedded boundary layer discharging device 11 is installed on the lower wall surface of the auxiliary pipeline test section 5 'through an embedded boundary layer discharging device outlet installation plate 12, and the boundary layer parameters of the incoming flow at the upstream of the outlet of the embedded boundary layer discharging device can be measured by a boundary layer measuring device 9 installed on the lower wall surface side of the test section 5'. Boundary layer parameters downstream of the submerged boundary layer displacement device inlet can be measured by boundary layer measuring devices 10 mounted on the lower wall side of the test section 5.
The 5/5 'outlet of the test section is connected with the 6/6' of the switching section, the switching section is used for connecting the experiment table with a downstream vacuum air source, and in order to avoid local separation of air flow caused by transitional expansion, the expansion angle of the expansion section is generally not more than 8 degrees. In addition, in order to monitor the flow field structure in the experiment table pipeline, static pressure holes for mounting static pressure probes are designed on the symmetrical surfaces of the upper wall surface and the lower wall surface of the experiment table pipeline, and because the change rules of flow field parameters at different positions are different, the distance between the static pressure holes at different positions is different, the distance between the static pressure holes from the inlet of the contraction section 3/3' to the outlet of the test section 5/5' is 10mm, and the distance between the static pressure holes of the inlet section 1/1', the rectifying section 2/2' and the switching section 6/6' is 25mm; meanwhile, the upper side of the test section 5/5' is made of transparent optical materials, and the test section can be used for observing flow field structures near the inlet and the outlet of the boundary layer displacement device in the experimental process.
Aiming at the invention, the effect of the technical scheme is verified by adopting a numerical simulation method, the flow field quality of the experiment table under the condition that the Mach number of the inlet of the test section is 0.54 and 0.75 is simulated, and the distribution of the flow direction Mach numbers at the heights of 0.26H, 0.50H and 0.74H of the distance between the symmetrical plane of the main/auxiliary pipeline and the lower wall surface is given in the figures 2 and 3 (note: the upstream flow field of the experiment model is mainly concerned in the experiment). As can be seen from the figure, the Mach number of the air flow in the main flow area at the upstream of the inlet of the test section is basically kept unchanged, and the quality of the flow field at the inlet of the test section meets the experimental requirements.
In addition, there are many ways to implement the invention, and the above description is only a preferred embodiment of the invention. It should be noted that, for those skilled in the art, without departing from the principle of the present invention, several improvements and modifications can be made, and these improvements and modifications should also be construed as the protection scope of the present invention.
Claims (10)
1. The utility model provides a can simulate experimental apparatus of boundary layer earial drainage and subsonic velocity outflow coupling effect which characterized in that: comprises a main pipeline, an auxiliary pipeline and an embedded boundary layer displacement device (11); the main pipeline comprises a first inlet section (1), a first rectifying section (2), a first contraction section (3), a first boundary layer development section (4), a first test section (5) and a first switching section (6) which are connected in sequence; the auxiliary pipeline comprises a second inlet section (1 '), a second rectifying section (2'), a second contraction section (3 '), a second boundary layer development section (4'), a second test section (5 ') and a second switching section (6') which are connected in sequence; boundary layer thickening devices are mounted on the outer side surfaces of the first boundary layer development section (4) and the second boundary layer development section (4'); an inlet of the embedded boundary layer displacement device (11) is arranged on one wall surface of the first test section (5), an outlet of the embedded boundary layer displacement device (11) is arranged on one wall surface of the second test section (5'), and the embedded boundary layer displacement device (11) is used for communicating the main pipeline with the auxiliary pipeline;
a first boundary layer measuring device (8) is arranged at the outlet of the first boundary layer development section (4); a second boundary layer measuring device (9) is arranged at the upstream of the outlet of the embedded boundary layer displacement device (11); the first test section (5) is provided with a third boundary layer measuring device (10);
the main pipeline is provided with a first static pressure hole (21) extending along the symmetric center on the wall surface where the inlet of the embedded boundary layer discharging device (11) is located and the opposite side wall surface back to the wall surface, and the auxiliary pipeline is provided with a second static pressure hole (22) extending along the symmetric center on the wall surface where the outlet of the embedded boundary layer discharging device (11) is located and the opposite side wall surface back to the wall surface; the first static pressure hole (21) and the second static pressure hole (22) are used for installing a static pressure probe.
2. The assay device of claim 1, wherein: the inlet of the main pipeline and the inlet of the auxiliary pipeline are not coherent with each other.
3. The assay device of claim 1, wherein: the first inlet section (1), the first rectifying section (2) and the first contraction section (3) are integrally processed by an additive manufacturing technology; the second inlet section (1 '), the second rectifying section (2 ') and the second contraction section (3 ') are integrally processed by adopting an additive manufacturing technology.
4. The assay device according to claim 1 or 3, wherein: the first inlet section (1) and the second inlet section (1') are in the same pipeline configuration; the first rectifying section (2) and the second rectifying section (2') are consistent in pipeline configuration; the first contraction section (3) and the second contraction section (3') are consistent in pipeline configuration; the first boundary layer development section (4) and the second boundary layer development section (4') are identical in pipe configuration.
5. The assay device according to claim 1, wherein: the length of the first rectifying section (2) is not less than 2 times of the outlet height of the first contraction section (3); the length of the second rectifying section (2 ') is not less than 2 times of the outlet height of the second contraction section (3').
6. The assay device of claim 1, wherein: the contraction ratio of the first contraction section (3) to the second contraction section (3') is not less than 5.
7. The assay device of claim 1, wherein: the first boundary layer development section (4) and the second boundary layer development section (4') both have unilateral expansion of the upper wall surface, and the expansion angle is 0.3 degrees.
8. The aspiration laboratory bench device according to claim 7, wherein: the thickness of the boundary layer at the outlet of the first boundary layer development section (4) and the thickness of the boundary layer at the outlet of the second boundary layer development section (4') are both controlled by the boundary layer thickening device.
9. The suction bench device of claim 8 wherein: the outlet of the embedded boundary layer displacement device (11) is arranged on the wall surface of the second test section (5') through an outlet mounting plate (12) of the embedded boundary layer displacement device.
10. The suction bench device of claim 9 wherein: the first static holes at the first contraction section (3), the first boundary layer development section (4) and the first test section (5) are arranged at equal intervals of 10mm, and the first static holes at the first inlet section (1), the first rectification section (2) and the first switching section (6) are arranged at equal intervals of 25mm; the second static holes positioned at the parts of the second contraction section (3 '), the second boundary layer development section (4') and the second test section (5 ') are arranged at equal intervals of 10mm, and the second static holes positioned at the parts of the second inlet section (1'), the second rectifying section (2 ') and the second switching section (6') are arranged at equal intervals of 25 mm.
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| CN115950493A (en) * | 2022-12-21 | 2023-04-11 | 南京航空航天大学 | Flow testing system and method suitable for subsonic flow channel |
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