CN115493793A - Device for reducing low Mach number airflow pulsation of large-caliber hypersonic wind tunnel - Google Patents
Device for reducing low Mach number airflow pulsation of large-caliber hypersonic wind tunnel Download PDFInfo
- Publication number
- CN115493793A CN115493793A CN202211219165.9A CN202211219165A CN115493793A CN 115493793 A CN115493793 A CN 115493793A CN 202211219165 A CN202211219165 A CN 202211219165A CN 115493793 A CN115493793 A CN 115493793A
- Authority
- CN
- China
- Prior art keywords
- section
- hole
- sintering
- wind tunnel
- face
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 230000010349 pulsation Effects 0.000 title claims abstract description 36
- 238000005245 sintering Methods 0.000 claims abstract description 77
- 238000009792 diffusion process Methods 0.000 claims abstract description 20
- 238000005056 compaction Methods 0.000 claims abstract description 11
- 230000000087 stabilizing effect Effects 0.000 claims description 22
- 238000003825 pressing Methods 0.000 claims description 20
- 229910001220 stainless steel Inorganic materials 0.000 claims description 18
- 239000010935 stainless steel Substances 0.000 claims description 18
- 125000006850 spacer group Chemical group 0.000 claims description 16
- 238000003466 welding Methods 0.000 claims description 12
- 238000005242 forging Methods 0.000 claims description 5
- 238000009423 ventilation Methods 0.000 claims description 5
- 238000009530 blood pressure measurement Methods 0.000 claims description 4
- 239000007921 spray Substances 0.000 claims description 4
- 229910000831 Steel Inorganic materials 0.000 claims description 3
- 238000005520 cutting process Methods 0.000 claims description 3
- 239000007787 solid Substances 0.000 claims description 3
- 239000010959 steel Substances 0.000 claims description 3
- 238000012360 testing method Methods 0.000 abstract description 16
- 238000000926 separation method Methods 0.000 abstract description 5
- 238000013461 design Methods 0.000 abstract description 4
- 238000005259 measurement Methods 0.000 abstract description 3
- 230000006835 compression Effects 0.000 description 8
- 238000007906 compression Methods 0.000 description 8
- 238000010586 diagram Methods 0.000 description 4
- 238000011161 development Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000000149 penetrating effect Effects 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 230000006641 stabilisation Effects 0.000 description 2
- 238000011105 stabilization Methods 0.000 description 2
- 238000011144 upstream manufacturing Methods 0.000 description 2
- 238000009826 distribution Methods 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
- 238000004804 winding Methods 0.000 description 1
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
- G01M9/04—Details
Landscapes
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention belongs to the technical field of design of hypersonic wind tunnel equipment, and particularly relates to a device for reducing low-Mach airflow pulsation of a large-caliber hypersonic wind tunnel. The device for reducing the low Mach number airflow pulsation of the large-caliber hypersonic wind tunnel comprises a conical hole diffusion section, a honeycomb device, a sintering network section and a compaction section which are arranged in the inner cavity of a stable section shell from front to back in sequence; a pitot pressure measuring interface and a pulsating pressure measuring interface are arranged on the stable section shell; a replacement segment for replacing the sintered segment is also included. The device for reducing the low Mach number airflow pulsation of the large-caliber hypersonic wind tunnel can improve the flow separation phenomenon of the test airflow in the stable section when the hypersonic wind tunnel operates at the low Mach number, reduce the airflow pulsation of the test airflow and improve the force measurement test precision of an aircraft model.
Description
Technical Field
The invention belongs to the technical field of design of hypersonic wind tunnel equipment, and particularly relates to a device for reducing low-Mach airflow pulsation of a large-caliber hypersonic wind tunnel.
Background
The hypersonic wind tunnel test is one of the main means for acquiring the aerodynamic performance of an aircraft. Data obtained by hypersonic wind tunnel test are directly applied to aerodynamic design and shaping of the aircraft, so the precision and the data quality of the test data are particularly important in the whole aircraft development process. In recent years, with the continuous development and upgrading of aircrafts, the development department of aircrafts puts forward higher and higher requirements on the quality of wind tunnel test data.
The unevenness and unsteady flow of the hypersonic wind tunnel flow field have great influence on aircraft test data. Therefore, from the viewpoint of improving the accuracy of the test data of the wind tunnel, it is always desirable that the hypersonic wind tunnel has the best possible flow field quality. When the large-caliber hypersonic wind tunnel operates in a low Mach number state, the diameter of the stabilizing section is larger for meeting the design requirement that the flow velocity in the stabilizing section is less than 30 m/s because the flow of the test air flow is large. The stable section with the large caliber inevitably brings about flow separation of the airflow in the stable section, and the flow separation can cause pulsation of the airflow in the stable section, thereby directly influencing the flow field quality of the outlet of the spray pipe.
In order to obtain uniform flow with low turbulence at the nozzle outlet of the hypersonic wind tunnel, reduce the running airflow pulsation of the wind tunnel and improve the flow field quality of the wind tunnel, a series of devices for eliminating the airflow pulsation are required to be arranged in a stable section shell with a large upstream area, so that large-scale and non-isotropic vortexes generated at the upstream of the wind tunnel are converted into small-scale vortexes under the action of inertia force, and the small-scale vortexes form fully developed turbulence under the action of viscous dissipation.
At present, a device for reducing the low mach number airflow pulsation of the large-caliber hypersonic wind tunnel is urgently needed to be developed.
Disclosure of Invention
The invention aims to solve the technical problem of providing a device for reducing the low-Mach number airflow pulsation of a large-caliber hypersonic wind tunnel.
The invention discloses a device for reducing low-Mach number airflow pulsation of a large-caliber hypersonic wind tunnel, which is characterized by comprising a conical hole diffusion section, a honeycomb device, a sintering network section and a compaction section, wherein the conical hole diffusion section, the honeycomb device, the sintering network section and the compaction section are arranged in the inner cavity of a shell of a stable section in sequence from front to back; a pitot pressure measuring interface and a pulsating pressure measuring interface are arranged on the stable section shell; the device also comprises a replacing section for replacing the sintering section;
a step hole I, a step hole II, a stabilizing section inner hole, a step hole III and a step hole IV are sequentially arranged in the inner cavity of the stabilizing section shell along the airflow direction from front to back, the corresponding inner diameters are D1, D2, D3 and D4 respectively, D1 is more than D2 and more than D, D is more than D3 and less than D4; a step end face I with counter airflow is arranged between the step hole I and the step hole II, a step end face II with counter airflow is arranged between the step hole II and the inner hole of the stabilizing section, a step end face III with forward airflow is arranged between the inner hole of the stabilizing section and the step hole III, and a step end face IV with forward airflow is arranged between the step hole III and the step hole IV;
the inner diameter of the stepped hole I is D1, and the depth is t1; a flange ring I is arranged at the rear end of the conical hole diffusion section, the outer diameter of the flange ring I is D1, and the thickness of the flange ring I is t1; the flange ring I is inserted into the step hole I from front to back, countersunk through holes I are uniformly distributed on the flange ring I, screw holes I which correspond to the countersunk through holes I in a one-to-one mode are uniformly distributed on the step end face I, and the conical hole diffusion section is fixed on the step end face I through countersunk screws I which penetrate through the countersunk through holes I and the screw holes I;
the inner diameter of the stepped hole II is D2, and the depth is t2; the outer diameter of the honeycombed device is D2, the thickness of the honeycombed device is t2, the honeycombed device is installed in the step hole II, the front end face of the honeycombed device abuts against the rear end face of the conical hole diffusion section, and the rear end face of the honeycombed device abuts against the step end face II;
the inner diameter of an inner hole of the stabilizing section is D, and the value of D meets the condition that the flow velocity in the stabilizing section is less than 30 m/s under the maximum flow operation state with low Mach number; a screw hole III is formed in the wall surface of the corresponding stable section shell, and the pitot pressure measuring interface is connected with the screw hole III through threads;
the inner diameter of the stepped hole III is D3, and the depth is t3; the outer diameter of the sintering network section is D3, the thickness of the sintering network section is t3, the sintering network section is installed in the step hole III, the front end face of the sintering network section tightly props against the step end face III, and the rear end face of the sintering network section tightly props against the front end face of the pressing section;
the inner diameter of the step hole IV is D4, and the depth is t4; the rear end of the compression section is provided with a flange ring II, the outer diameter of the flange ring II is D4, the thickness of the flange ring II is t4, the flange ring II is inserted into a step hole IV from the rear to the front, countersunk through holes II are uniformly distributed on the flange ring II, screw holes II which correspond to the countersunk through holes II one to one are uniformly distributed on the step end face IV, and the compression section is fixed on the step end face IV through countersunk screws II penetrating through the countersunk through holes II and the screw holes II.
Furthermore, the replacement section is a cylinder and is rolled by a stainless steel plate, and the length, the outer diameter and the inner diameter of the replacement section are respectively the same as those of the corresponding sintering network section.
Furthermore, the front end of the conical hole diffusion section is a head cone facing the incoming flow, the middle section is a skirt section, and the rear end is a flange ring I; the nose cone is machined by a stainless steel forging and is of a solid structure, the top of the nose cone is a ball head, the vertex angle of the nose cone ranges from 45 degrees to 70 degrees, and the nose cone is connected with the skirt section in a welding mode; the skirt section is made of stainless steel sheet coils, and the wall thickness meets the structural stability in a low Mach number maximum flow operation state; the skirt section is provided with vent holes which are arranged in an array mode, the central axis of each vent hole is perpendicular to a generatrix of the head cone, three adjacent vent holes are in a regular triangle shape, the effective flow area of all the vent holes is larger than 60%, and the skirt section is connected with the flange ring I in a welding mode; the flange ring I and the stepped hole I are matched by H8/H7.
Furthermore, the honeycomb device is of a disc shape and is integrally processed and manufactured by adopting a stainless steel forging; the thickness range of the honeycomb device is 80 mm-120 mm; the honeycomb holes on the honeycomb device are regular hexagons, and three adjacent honeycomb holes are in regular triangles; the honeycomb device is matched with the stepped hole II by adopting H8/H7.
Furthermore, the effective ventilation diameter of the sintering network section is the same as the inner diameter D of the stable section shell, and the sintering network section is of a multilayer network structure and comprises a pressing plate, a sintering network and a support ring; the pressing plate and the supporting ring are both circular, the insides of the pressing plate and the supporting ring are provided with a # -shaped framework, and the pressing plate and the supporting ring are integrally formed by cutting a steel plate or formed by assembling and welding parts; a pointed cone is arranged on the windward side of the well-shaped framework of the pressing plate; the sintering net is formed by sintering a plurality of layers of wire nets with the same specification, and the mesh number of the sintering net ranges from 20 meshes to 120 meshes; the pressing plate, the sintering net and the support ring are fixedly connected by welding or countersunk head screws.
Furthermore, a plurality of sintering network segments are arranged according to the requirement, each sintering network segment is separated through a spacing ring, and the sum of the thicknesses of the sintering network segments and the matched spacing rings is t3; screw holes IV are respectively formed in the wall surface of the stable section shell corresponding to each spacing ring, and the pulsating pressure measuring interface is connected with the screw holes IV through threads; the mesh number of the sintering nets in each sintering net section is the same or different.
Furthermore, the spacer ring is a cylinder and is wound by a stainless steel plate, and the thickness of the spacer ring meets the structural stability in a low Mach number maximum flow operation state; the outer diameter of the spacer ring is the same as the inner diameter D3 of the step hole III, and the inner diameter of the spacer ring is the same as the inner diameter D of the stable section shell; the spacer ring length is greater than 100 times the nominal diameter of a single hole of the sintered mesh.
Furthermore, the front end of the compression section is a cylinder, the rear end of the compression section is a flange ring II, and the compression section is rolled by a stainless steel plate material; the inner hole of the compaction section is a taper hole, the inner diameter of the inlet of the taper hole is the same as the inner diameter D of the shell of the stabilization section, and the diameter D5 of the outlet of the taper hole is the same as the diameter D5 of the inlet of the connected axisymmetric profile spray pipe of the hypersonic wind tunnel; the outer diameter of the cylinder at the front end of the compaction section is the same as that of the sintering network section; the flange ring II is matched with the stepped hole IV by adopting H8/H7.
The device for reducing the low Mach number airflow pulsation of the large-caliber hypersonic wind tunnel has the following advantages:
1. the flow separation of the low-Mach number airflow of the large-caliber hypersonic wind tunnel in the stable section can be greatly improved, the airflow pulsation phenomenon is reduced, and the force measurement test precision of the aircraft model is improved.
2. The adjustable sintering network segments are adopted, and the number of the sintering network segments, the mesh number of the sintering networks and the layer number can be adjusted according to different test requirements, so that the optimal effect and the maximum efficiency are achieved.
3. The replacement section is adopted to replace the sintering network sections, the distance between the sintering network sections can be adjusted according to actual needs, the airflow channel in the stable section shell is ensured to have no steps, and airflow disturbance is reduced.
4. The conical hole diffusion section and the honeycomb device play good roles in speed reduction and flow guiding, the axis of an air vent of the conical hole diffusion section is perpendicular to the pointed cone bus, the purpose of air flow speed reduction is achieved, air flows are guided by the honeycomb device to move along the direction of a downstream field uniformly, and interference of transverse foreign waves is reduced.
5. The vent holes of the conical hole diffusion section and the honeycomb holes of the honeycomb device are distributed in a regular triangle, so that the ventilation rate is increased to the maximum extent and the pressure loss of airflow is reduced; the honeycomb holes of the honeycomb device adopt a regular hexagon structure, are easy to type during processing, reduce the clearance between the honeycomb holes, increase the ventilation rate, and consider that the taper hole diffusion section is an inclined plane, and difficult processing adopts a circular air vent.
6. The wind-facing side of the # -shaped framework of the support ring of the sintering network section adopts a pointed cone form, so that on one hand, the resistance and the pressure drop of the airflow are reduced, and on the other hand, the airflow also plays a role in rectification, so that the airflow flows more smoothly along the axis direction.
7. The distance between the sintering net sections can be adjusted by the spacing ring according to needs, and the distance can be adjusted according to different test requirements, different sintering net mesh numbers and different layer numbers, so that the best rectification effect is achieved.
8. The pressing section enables the whole device to be fixed in the stabilizing section more firmly and stably, airflow pulsation caused by vibration is reduced, and the rectification effect of the device is improved.
The device for reducing the low-Mach airflow pulsation of the large-caliber hypersonic wind tunnel can improve the flow separation phenomenon of the test airflow in the stable section when the hypersonic wind tunnel runs at the low Mach number, reduce the airflow pulsation of the test airflow and improve the force measurement test precision of the aircraft model.
Drawings
FIG. 1 is a schematic structural diagram of a device for reducing low Mach number airflow pulsation in a large-caliber hypersonic wind tunnel according to the present invention;
FIG. 2 is a schematic structural diagram of a stable section shell in the device for reducing the low Mach number airflow pulsation of the large-caliber hypersonic wind tunnel according to the invention;
FIG. 3 is a schematic structural diagram of a cone hole diffuser in the device for reducing the low Mach number airflow pulsation of a large-caliber hypersonic wind tunnel according to the present invention;
FIG. 4 is a front view of a honeycomb device in the device for reducing the low Mach number airflow pulsation of a large-caliber hypersonic wind tunnel according to the present invention;
FIG. 5 is a partially enlarged view of the honeycomb hole distribution of the honeycomb device in the device for reducing the low Mach number airflow pulsation of the large-caliber hypersonic wind tunnel according to the present invention;
FIG. 6 is a side view of a sintering network segment in the device for reducing the low Mach number airflow pulsation of a large-caliber hypersonic wind tunnel according to the invention;
FIG. 7 is a front view of a sintering network segment in the device for reducing the low Mach number airflow pulsation of the large-caliber hypersonic wind tunnel according to the invention;
FIG. 8 is a structural diagram of a support ring in the device for reducing the low Mach number airflow pulsation of the large-caliber hypersonic wind tunnel according to the invention;
FIG. 9 is a front view of a compacting section in the device for reducing the low Mach number airflow pulsation of the large-caliber hypersonic wind tunnel according to the invention.
In the figure, 1, a taper hole diffusion section; 2. a countersunk head screw I; 3. a honeycombing device; 4. a stabilization section housing; 5. sintering the network segment; 6. a spacer ring; 7. a compression section; 8. a countersunk head screw II; 9. a pitot pressure measurement interface; 10. a pulsating pressure measurement interface; 11. a stepped hole I; 12. a screw hole I; 13. a step hole II; 14. a step hole III; 15. a step hole IV; 16. a screw hole II; 17. screw hole III; 18. screw holes IV; 19. a nose cone; 20. a skirt section; 21. a vent hole; 22. a flange ring I; 23. a countersunk through hole I; 24. a honeycomb hole; 25. pressing a plate; 26. a pointed cone; 27. sintering the net; 28. a support ring; 29. a countersunk through hole II; 30. and a flange ring II.
Detailed Description
The present invention is described in detail below with reference to the drawings and examples.
Example 1
As shown in fig. 1, the device for reducing the low mach number airflow pulsation of the large-caliber hypersonic wind tunnel in the embodiment includes a conical hole diffuser section 1, a honeycomb device 3, a sintering network section 5 and a compacting section 7 which are arranged in the inner cavity of a stable section shell 4 in sequence from front to back; a pitot pressure measuring interface 9 and a pulsating pressure measuring interface 10 are arranged on the stable section shell 4; also comprises a replacing segment for replacing the sintering segment 5;
as shown in fig. 2, a step hole i 11, a step hole ii 13, a stabilizing section inner hole, a step hole iii 14 and a step hole iv 15 are sequentially arranged in the inner cavity of the stabilizing section shell 4 from front to back along the downdraft direction, the corresponding inner diameters are D1, D2, D3 and D4, D1 > D2 > D, D < D3 < D4; a step end face I with counter airflow is arranged between the step hole I11 and the step hole II 13, a step end face II with counter airflow is arranged between the step hole II 13 and the inner hole of the stabilizing section, a step end face III with airflow is arranged between the inner hole of the stabilizing section and the step hole III 14, and a step end face IV with airflow is arranged between the step hole III 14 and the step hole IV 15;
the inner diameter of the stepped hole I11 is D1, and the depth is t1; a flange ring I22 is arranged at the rear end of the taper hole diffusion section 1, the outer diameter of the flange ring I22 is D1, and the thickness of the flange ring is t1; the flange ring I22 is inserted into the stepped hole I11 from front to back, countersunk through holes I23 are uniformly distributed on the flange ring I22, screw holes I12 which correspond to the countersunk through holes I23 in a one-to-one mode are uniformly distributed on the stepped end face I, and the conical hole diffusion section 1 is fixed on the stepped end face I through countersunk screws I2 which penetrate through the countersunk through holes I23 and the screw holes I12;
the inner diameter of the stepped hole II 13 is D2, and the depth is t2; the outer diameter of the honeycombed device 3 is D2, the thickness is t2, the honeycombed device 3 is installed in the step hole II 13, the front end face of the honeycombed device 3 abuts against the rear end face of the conical hole diffusion section 1, and the rear end face of the honeycombed device 3 abuts against the step end face II;
the inner diameter of an inner hole of the stable section is D, and the value of D meets the condition that the flow velocity in the stable section is less than 30 m/s in the low Mach number maximum flow operation state; a screw hole III 17 is formed in the wall surface of the corresponding stable section shell 4, and the pitot pressure measuring interface 9 is connected with the screw hole III 17 through threads;
the inner diameter of the stepped hole III 14 is D3, and the depth is t3; the outer diameter of the sintering network section 5 is D3, the thickness is t3, the sintering network section 5 is installed in the step hole III 14, the front end face of the sintering network section 5 tightly abuts against the step end face III, and the rear end face of the sintering network section 5 tightly abuts against the front end face of the pressing section 7;
the inner diameter of the step hole IV 15 is D4, and the depth is t4; the rear end of the compression section 7 is provided with a flange ring II 30, the outer diameter of the flange ring II 30 is D4, the thickness of the flange ring II 30 is t4, the flange ring II 30 is inserted into the step hole IV 15 from back to front, countersunk through holes II 29 are uniformly distributed on the flange ring II 30, screw holes II 16 corresponding to the countersunk through holes II 29 one to one are uniformly distributed on the step end face IV, and the compression section 7 is fixed on the step end face IV through countersunk screws II 8 penetrating through the countersunk through holes II 29 and the screw holes II 16.
Furthermore, the replacement section is a cylinder and is made by winding a stainless steel plate, and the length, the outer diameter and the inner diameter of the replacement section are respectively the same as those of the corresponding sintering network section 5.
Further, as shown in fig. 3, the front end of the conical hole diffuser section 1 is a nose cone 19 facing the incoming flow, the middle section is a skirt section 20, and the rear end is a flange ring i 22; the nose cone 19 is machined by a stainless steel forging and is of a solid structure, the top of the nose cone 19 is a ball head, the vertex angle of the nose cone 19 ranges from 45 degrees to 70 degrees, and the nose cone 19 is connected with the skirt section 20 in a welding mode; the skirt section 20 is made of stainless steel sheet coils, and the wall thickness meets the structural stability in a low Mach number maximum flow operation state; the skirt section 20 is provided with vent holes 21 which are arrayed, the central axis of each vent hole 21 is perpendicular to the generatrix of the nose cone 19, three adjacent vent holes 21 are in a regular triangle shape, the effective flow area of all the vent holes 21 is larger than 60%, and the skirt section 20 is connected with the flange ring I22 in a welding manner; the flange ring I22 is matched with the stepped hole I11 in an H8/H7 mode.
Further, as shown in fig. 4 and 5, the honeycomb device 3 is a disk type and is integrally machined and manufactured by a stainless steel forging; the thickness range of the honeycomb device 3 is 80 mm-120 mm; the honeycomb holes 24 on the honeycomb device 3 are regular hexagons, and three adjacent honeycomb holes 24 are regular triangles; H8/H7 matching is adopted between the honeycombed device 3 and the stepped hole II 13.
Further, as shown in fig. 6 and 7, the effective ventilation diameter of the sintering section 5 is the same as the inner diameter D of the stabilizing section shell 4, and the sintering section 5 is of a multi-layer net structure and comprises a pressing plate 25, a sintering net 27 and a supporting ring 28; the pressing plate 25 and the supporting ring 28 are both circular, the insides of the pressing plate and the supporting ring are provided with framework shaped like a Chinese character 'jing', and the pressing plate and the supporting ring are integrally formed by cutting steel plates or formed by assembling and welding parts; a pointed cone 26 is arranged on the windward side of the # -shaped framework of the pressing plate 25; the sintering net 27 is formed by sintering a plurality of layers of wire nets with the same specification, and the mesh range of the sintering net 27 is 20-120 meshes; the pressure plate 25, the sintering net 27 and the supporting ring 28 are fixedly connected by welding or countersunk screws.
Furthermore, a plurality of sintering network segments 5 are arranged according to the requirement, each sintering network segment 5 is separated by a spacing ring 6, and the sum of the thicknesses of the plurality of sintering network segments 5 and the matched spacing rings 6 is t3; the wall surface of the stable section shell 4 corresponding to each spacing ring 6 is respectively provided with a screw hole IV 18, and the pulsating pressure measurement interface 10 is connected with the screw hole IV 18 through threads; the mesh numbers of the sintering mesh 27 in the respective sintering segments 5 are the same or different.
Further, as shown in fig. 8, the spacer ring 6 is a cylinder and is made of a stainless steel sheet material, and the thickness of the spacer ring 6 satisfies the structural stability in the low mach number maximum flow operation state; the outer diameter of the spacer ring 6 is the same as the inner diameter D3 of the stepped hole III 14, and the inner diameter of the spacer ring 6 is the same as the inner diameter D of the stabilizing section shell 4; the spacer ring 6 has a length greater than 100 times the nominal diameter of a single hole of the sintered mesh 27.
Further, as shown in fig. 9, the front end of the compressing section 7 is a cylinder, and the rear end is a flange ring ii 30, which is made of stainless steel sheet material coil; the inner hole of the compaction section 7 is a taper hole, the inner diameter of the inlet of the taper hole is the same as the inner diameter D of the stabilizing section shell 4, and the diameter D5 of the outlet of the taper hole is the same as the diameter D5 of the inlet of the connected hypersonic wind tunnel axisymmetric profile spray pipe; the outer diameter of the cylinder at the front end of the compaction section 7 is the same as that of the sintering network section 5; the flange ring II 30 is matched with the stepped hole IV 15 by adopting H8/H7.
Although embodiments of the invention have been described above, it is not intended to be limited to the specific details set forth in the description or the embodiments, but rather, to one skilled in the art, that all of the features of the invention disclosed, or all of the steps of any method or process disclosed, may be combined in any suitable manner, except for mutually exclusive features and/or steps, without departing from the principles of the invention, and that the invention is not limited to the specific details set forth and illustrated in the drawings described herein.
Claims (8)
1. A device for reducing the low Mach number airflow pulsation of a large-caliber hypersonic wind tunnel is characterized by comprising a conical hole diffusion section (1), a honeycomb device (3), a sintering network section (5) and a compaction section (7), wherein the conical hole diffusion section, the honeycomb device, the sintering network section and the compaction section are arranged in the inner cavity of a stable section shell (4) in sequence from front to back; a pitot pressure measuring interface (9) and a pulsating pressure measuring interface (10) are arranged on the stable section shell (4); also comprises a replacing segment for replacing the sintering segment (5);
a step hole I (11), a step hole II (13), a stabilizing section inner hole, a step hole III (14) and a step hole IV (15) are sequentially arranged in the inner cavity of the stabilizing section shell (4) from front to back along the airflow direction, the corresponding inner diameters are D1, D2, D3 and D4 respectively, D1 is more than D2 and more than D, D is more than D3 and less than D4; a step end face I with reverse airflow is arranged between the step hole I (11) and the step hole II (13), a step end face II with reverse airflow is arranged between the step hole II (13) and the inner hole of the stabilizing section, a step end face III with forward airflow is arranged between the inner hole of the stabilizing section and the step hole III (14), and a step end face IV with forward airflow is arranged between the step hole III (14) and the step hole IV (15);
the inner diameter of the stepped hole I (11) is D1, and the depth is t1; a flange ring I (22) is arranged at the rear end of the conical hole diffusion section (1), the outer diameter of the flange ring I (22) is D1, and the thickness of the flange ring I is t1; the flange ring I (22) is inserted into the step hole I (11) from front to back, countersunk through holes I (23) are uniformly distributed on the flange ring I (22), screw holes I (12) which correspond to the countersunk through holes I (23) one by one are uniformly distributed on the step end face I, and the conical hole diffusion section (1) is fixed on the step end face I through countersunk screws I (2) which penetrate through the countersunk through holes I (23) and the screw holes I (12);
the inner diameter of the stepped hole II (13) is D2, and the depth is t2; the outer diameter of the honeycomb device (3) is D2, the thickness of the honeycomb device is t2, the honeycomb device (3) is installed in the step hole II (13), the front end face of the honeycomb device (3) tightly props against the rear end face of the conical hole diffusion section (1), and the rear end face of the honeycomb device (3) tightly props against the step end face II;
the inner diameter of an inner hole of the stable section is D, and the value of D meets the condition that the flow velocity in the stable section is less than 30 m/s in the low Mach number maximum flow operation state; a screw hole III (17) is formed in the wall surface of the corresponding stabilizing section shell (4), and the pitot pressure measuring interface (9) is connected with the screw hole III (17) through threads;
the inner diameter of the stepped hole III (14) is D3, and the depth is t3; the outer diameter of the sintering network section (5) is D3, the thickness of the sintering network section is t3, the sintering network section (5) is installed in the step hole III (14), the front end face of the sintering network section (5) is tightly propped against the step end face III, and the rear end face of the sintering network section (5) is tightly propped against the front end face of the pressing section (7);
the inner diameter of the stepped hole IV (15) is D4, and the depth is t4; compress tightly section (7) rear end and be provided with flange ring II (30), the external diameter of flange ring II (30) is D4, thickness is t4, insert in step hole IV (15) behind to preceding flange ring II (30), equipartition countersunk head through-hole II (29) on the flange ring II (30), equipartition and countersunk head through-hole II (29) one-to-one screw hole II (16) on the step terminal surface IV, compress tightly section (7) and fix on step terminal surface IV through countersunk head screw II (8) that pass countersunk head through-hole II (29) and screw hole II (16).
2. The device for reducing the low mach number airflow pulsation of the large-caliber hypersonic wind tunnel according to claim 1, wherein the replacing section is a cylinder and is made of a stainless steel plate coil, and the length, the outer diameter and the inner diameter of the replacing section are respectively the same as those of the corresponding sintering network section (5).
3. The device for reducing the low Mach number airflow pulsation of the large-caliber hypersonic wind tunnel according to claim 1, characterized in that the front end of the conical hole diffuser section (1) is a nose cone (19) facing the incoming flow, the middle section is a skirt section (20), and the rear end is a flange ring I (22); the nose cone (19) is machined by a stainless steel forging and is of a solid structure, the top of the nose cone is a ball head, the vertex angle of the nose cone (19) ranges from 45 degrees to 70 degrees, and the nose cone (19) is connected with the skirt section (20) in a welding mode; the skirt section (20) is rolled by adopting a stainless steel plate, and the wall thickness meets the structural stability in a low Mach number maximum flow operation state; the skirt section (20) is provided with vent holes (21) which are arrayed, the central axis of each vent hole (21) is perpendicular to the generatrix of the nose cone (19), three adjacent vent holes (21) are in a regular triangle shape, the effective flow area of all vent holes (21) is larger than 60%, and the skirt section (20) is connected with the flange ring I (22) in a welding manner; the flange ring I (22) is matched with the stepped hole I (11) by adopting H8/H7.
4. The device for reducing the low Mach number airflow pulsation of the large-caliber hypersonic wind tunnel according to claim 1, wherein the honeycombed device (3) is in a disc shape and is integrally machined and manufactured by a stainless steel forged piece; the thickness range of the honeycomb device (3) is 80 mm-120 mm; the honeycomb holes (24) on the honeycomb device (3) are regular hexagons, and three adjacent honeycomb holes (24) are in regular triangles; H8/H7 matching is adopted between the honeycombing device (3) and the stepped hole II (13).
5. The device for reducing the low Mach number airflow pulsation of the large-caliber hypersonic wind tunnel according to claim 1, characterized in that the effective ventilation diameter of the sintering segment (5) is the same as the inner diameter D of the stable segment shell (4), and the sintering segment (5) is of a multilayer net structure and comprises a pressing plate (25), a sintering net (27) and a support ring (28); the pressing plate (25) and the supporting ring (28) are both circular, the insides of the pressing plate and the supporting ring are provided with # -shaped frameworks, and the pressing plate and the supporting ring are integrally formed by cutting steel plates or formed by assembling and welding parts; a pointed cone (26) is arranged on the windward side of the # -shaped framework of the pressure plate (25); the sintering net (27) is formed by sintering a plurality of layers of wire nets with the same specification, and the mesh range of the sintering net (27) is 20-120 meshes; the pressure plate (25), the sintering net (27) and the support ring (28) are fixedly connected by adopting welding connection or countersunk head screws.
6. The device for reducing the low Mach number airflow pulsation of the large-caliber hypersonic wind tunnel according to claim 5, wherein a plurality of sintering network segments (5) are arranged as required, each sintering network segment (5) is separated by a spacing ring (6), and the sum of the thicknesses of the plurality of sintering network segments (5) and the matched spacing ring (6) is t3; screw holes IV (18) are respectively formed in the wall surface of the stable section shell (4) corresponding to each spacing ring (6), and the pulsating pressure measurement interface (10) is connected with the screw holes IV (18) through threads; the mesh number of the sintering mesh (27) in each sintering mesh segment (5) is the same or different.
7. The device for reducing the low-Mach airflow pulsation of the large-caliber hypersonic wind tunnel according to claim 6, wherein the spacer ring (6) is a cylinder and is wound by a stainless steel plate, and the thickness of the spacer ring (6) meets the structural stability in the low-Mach maximum flow operation state; the outer diameter of the spacer ring (6) is the same as the inner diameter D3 of the stepped hole III (14), and the inner diameter of the spacer ring (6) is the same as the inner diameter D of the stabilizing section shell (4); the spacer ring (6) has a length greater than 100 times the nominal diameter of a single hole of the sintered mesh (27).
8. The device for reducing the low Mach number airflow pulsation of the large-caliber hypersonic wind tunnel according to claim 1, characterized in that the front end of the compressing section (7) is a cylinder, the rear end is a flange ring II (30) and is made of stainless steel sheet coil; the inner hole of the compaction section (7) is a taper hole, the inner diameter of the inlet of the taper hole is the same as the inner diameter D of the stable section shell (4), and the diameter D5 of the outlet of the taper hole is the same as the diameter D5 of the inlet of the connected axisymmetric profile spray pipe of the hypersonic wind tunnel; the outer diameter of the front end cylinder of the compaction section (7) is the same as that of the sintering network section (5); the flange ring II (30) is matched with the stepped hole IV (15) by adopting H8/H7.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211219165.9A CN115493793B (en) | 2022-10-08 | 2022-10-08 | Device for reducing low Mach number airflow pulsation of large-caliber hypersonic wind tunnel |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211219165.9A CN115493793B (en) | 2022-10-08 | 2022-10-08 | Device for reducing low Mach number airflow pulsation of large-caliber hypersonic wind tunnel |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115493793A true CN115493793A (en) | 2022-12-20 |
| CN115493793B CN115493793B (en) | 2024-03-29 |
Family
ID=84472589
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211219165.9A Active CN115493793B (en) | 2022-10-08 | 2022-10-08 | Device for reducing low Mach number airflow pulsation of large-caliber hypersonic wind tunnel |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115493793B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117686177A (en) * | 2024-02-04 | 2024-03-12 | 中国航空工业集团公司沈阳空气动力研究所 | Hypersonic wind tunnel stabilizing section rectifying device |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2007046924A (en) * | 2005-08-08 | 2007-02-22 | Hitachi Ltd | Wind tunnel system and pulsation flow producing device |
| CN102252818A (en) * | 2011-06-23 | 2011-11-23 | 中国人民解放军国防科学技术大学 | Supersonic wind tunnel with variable quality of flow field |
| CN102680201A (en) * | 2012-05-15 | 2012-09-19 | 空气动力学国家重点实验室 | Buffeting wind tunnel testing method based on video measurement |
| CN111272376A (en) * | 2020-03-16 | 2020-06-12 | 中国科学院工程热物理研究所 | Wind tunnel boundary layer control mechanism and supersonic wind tunnel |
| CN114279671A (en) * | 2022-03-03 | 2022-04-05 | 中国空气动力研究与发展中心超高速空气动力研究所 | Method for designing low-Mach-number total-enthalpy flight platform based on existing hypersonic wind tunnel |
| CN114813096A (en) * | 2022-06-29 | 2022-07-29 | 中国空气动力研究与发展中心超高速空气动力研究所 | Multi-layer sintering net test model selection method for hypersonic wind tunnel |
-
2022
- 2022-10-08 CN CN202211219165.9A patent/CN115493793B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2007046924A (en) * | 2005-08-08 | 2007-02-22 | Hitachi Ltd | Wind tunnel system and pulsation flow producing device |
| CN102252818A (en) * | 2011-06-23 | 2011-11-23 | 中国人民解放军国防科学技术大学 | Supersonic wind tunnel with variable quality of flow field |
| CN102680201A (en) * | 2012-05-15 | 2012-09-19 | 空气动力学国家重点实验室 | Buffeting wind tunnel testing method based on video measurement |
| CN111272376A (en) * | 2020-03-16 | 2020-06-12 | 中国科学院工程热物理研究所 | Wind tunnel boundary layer control mechanism and supersonic wind tunnel |
| CN114279671A (en) * | 2022-03-03 | 2022-04-05 | 中国空气动力研究与发展中心超高速空气动力研究所 | Method for designing low-Mach-number total-enthalpy flight platform based on existing hypersonic wind tunnel |
| CN114813096A (en) * | 2022-06-29 | 2022-07-29 | 中国空气动力研究与发展中心超高速空气动力研究所 | Multi-layer sintering net test model selection method for hypersonic wind tunnel |
Non-Patent Citations (1)
| Title |
|---|
| 周勇为;: "超声速静风洞设计和流场校侧", 国防科技大学学报, no. 06, 25 December 2005 (2005-12-25) * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117686177A (en) * | 2024-02-04 | 2024-03-12 | 中国航空工业集团公司沈阳空气动力研究所 | Hypersonic wind tunnel stabilizing section rectifying device |
Also Published As
| Publication number | Publication date |
|---|---|
| CN115493793B (en) | 2024-03-29 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN115493793B (en) | Device for reducing low Mach number airflow pulsation of large-caliber hypersonic wind tunnel | |
| JP6174655B2 (en) | Ducted heat exchanger system for gas turbine engine and method for manufacturing heat exchanger for gas turbine engine | |
| CN111649005B (en) | Axial-flow fan and dryer of air conditioner | |
| US9175577B2 (en) | Quiet bleed valve for gas turbine engine | |
| CN112229639B (en) | Design method of aero-engine intake total pressure distortion generation device | |
| CN212903808U (en) | Ejector and wind tunnel test device with same | |
| CN112727860B (en) | Structure for high-Mach-number molded surface spray pipe water-cooling throat of hypersonic wind tunnel | |
| CN111578310A (en) | Air film cooling hole structure for turboshaft engine | |
| CN212624783U (en) | Silencing sheet, silencing device and acoustic wind tunnel device | |
| CN114282326A (en) | Structural design method for axisymmetric nozzle of hypersonic wind tunnel | |
| CN111912596B (en) | Small-sized straight-flow wind tunnel diffusion section with ultra-long fairing and annular separation-preventing net | |
| CN113324261B (en) | Diffuser with rectifying plate and application thereof | |
| CN112113241B (en) | Rectifying grid of stamping combustion chamber | |
| CN111272376B (en) | Wind tunnel boundary layer control mechanism and supersonic wind tunnel | |
| CN115560357B (en) | Rectifying device for combustion chamber air inlet test | |
| CN114198324B (en) | Multi-element coupling centrifugal fan collector, centrifugal fan and preparation method of centrifugal fan collector | |
| CN210014130U (en) | Ventilation end silencer | |
| CN111828387A (en) | Fan blade of large-flow low-speed fan | |
| CN114912196B (en) | Design method of aeroengine intake total pressure distortion generator based on stacked grids | |
| CN116537950A (en) | Ventilation cooling air inlet device for turbofan engine core cabin | |
| CN109289373B (en) | Filter device and manufacturing method thereof | |
| CN111609243B (en) | Manufacturing method of large equivalent diameter conical tandem type noise elimination channel | |
| CN212508975U (en) | Fan blade of large-flow low-speed fan | |
| CN217032623U (en) | External rectifier | |
| CN221046822U (en) | Stator dust removal workbench |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |