CN115493793B - 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
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- CN115493793B CN115493793B CN202211219165.9A CN202211219165A CN115493793B CN 115493793 B CN115493793 B CN 115493793B CN 202211219165 A CN202211219165 A CN 202211219165A CN 115493793 B CN115493793 B CN 115493793B
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- 230000010349 pulsation Effects 0.000 title claims abstract description 38
- 238000005245 sintering Methods 0.000 claims abstract description 79
- 230000000087 stabilizing effect Effects 0.000 claims abstract description 34
- 238000009792 diffusion process Methods 0.000 claims abstract description 25
- 238000009530 blood pressure measurement Methods 0.000 claims abstract description 10
- 238000005056 compaction Methods 0.000 claims abstract description 5
- 239000010985 leather Substances 0.000 claims abstract description 4
- 238000003825 pressing Methods 0.000 claims description 23
- 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 9
- 238000003466 welding Methods 0.000 claims description 9
- 238000009423 ventilation Methods 0.000 claims description 7
- 238000005242 forging Methods 0.000 claims description 6
- 239000007921 spray Substances 0.000 claims description 6
- 229910000831 Steel Inorganic materials 0.000 claims description 3
- 239000007787 solid Substances 0.000 claims description 3
- 239000010959 steel Substances 0.000 claims description 3
- 238000005520 cutting process Methods 0.000 claims description 2
- 238000004804 winding Methods 0.000 claims 1
- 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 4
- 241000264877 Hippospongia communis Species 0.000 description 35
- 230000000694 effects Effects 0.000 description 5
- 238000010586 diagram Methods 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 230000006835 compression Effects 0.000 description 3
- 238000007906 compression Methods 0.000 description 3
- 238000011161 development Methods 0.000 description 3
- 230000000149 penetrating effect Effects 0.000 description 2
- 238000011144 upstream manufacturing Methods 0.000 description 2
- 238000009826 distribution Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
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- 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
Abstract
The invention belongs to the technical field of hypersonic wind tunnel equipment design, and particularly relates to a device for reducing low Mach number 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 taper hole diffusion section, a honeycomb device, a sintering net section and a compaction section which are sequentially arranged from front to back, wherein the taper hole diffusion section is arranged in an inner cavity of a stabilizing section shell; a leather pressure measurement interface and a pulsating pressure measurement interface are arranged on the shell of the stabilizing section; and a replacement section for replacing the sintering net section. The device for reducing the low Mach number airflow pulsation of the large-caliber hypersonic wind tunnel can improve the flow separation phenomenon of test airflow in a stable section when the hypersonic wind tunnel runs at the low Mach number, reduce the airflow pulsation of the test airflow and improve the accuracy of a force measurement test of an aircraft model.
Description
Technical Field
The invention belongs to the technical field of hypersonic wind tunnel equipment design, and particularly relates to a device for reducing low Mach number airflow pulsation of a large-caliber hypersonic wind tunnel.
Background
Hypersonic wind tunnel testing is one of the main means of acquiring aerodynamic performance of an aircraft. The data obtained by hypersonic wind tunnel test is directly applied to aerodynamic design and shaping of the aircraft, so that the accuracy and data quality of the test data are particularly important in the whole development process of the aircraft. In recent years, with the continuous development and upgrading of aircrafts, the development department of aircrafts puts higher and higher demands on the quality of wind tunnel test data.
The non-uniformity and unsteady flow of the hypersonic wind tunnel flow field have a significant effect on the aircraft test data. Therefore, from the viewpoint of improving the accuracy of wind tunnel test data, it is always desirable that hypersonic wind tunnels have as good a flow field quality as possible. For the large-caliber hypersonic wind tunnel, when the hypersonic wind tunnel runs in a low Mach number state, the flow of the test airflow is large, and meanwhile, the diameter of the stable section is large in order to meet the design requirement that the flow in the stable section is smaller than 30 m/s. The large-caliber stabilizing section can bring about flow separation of the air flow in the stabilizing section, and the flow separation can lead to pulsation of the air flow in the stabilizing section, so that the flow field quality of the outlet of the spray pipe is directly affected.
In order to obtain uniform flow with low turbulence at the outlet of the hypersonic wind tunnel jet pipe, reduce the running airflow pulsation of the wind tunnel and improve the quality of the wind tunnel flow field, a series of devices for eliminating airflow pulsation are required to be arranged in a stable section shell with large upstream area, so that large-scale and non-isotropic vortex generated at the upstream of the wind tunnel is converted into small-scale vortex under the action of inertia force, and the small-scale vortex forms fully developed turbulence under the action of viscous dissipation.
Currently, there is a need to develop a device for reducing the low mach number airflow pulsation of a large-caliber hypersonic wind tunnel.
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 relates to a device for reducing the low Mach number airflow pulsation of a large-caliber hypersonic wind tunnel, which is characterized by comprising a taper hole diffusion section, a honeycomb device, a sintering net section and a compression section which are arranged in sequence from front to back, wherein the taper hole diffusion section is arranged in an inner cavity of a shell of a stabilizing section; a leather pressure measurement interface and a pulsating pressure measurement interface are arranged on the shell of the stabilizing section; the device also comprises a replacing section for replacing the sintering net section;
the inner cavity of the stabilizing section shell is sequentially provided with a step hole I, a step hole II, a stabilizing section inner hole, a step hole III and a step Kong from front to back along the forward air flow direction, wherein the corresponding inner diameters are D1, D2, D, D and D4 respectively, D1 is more than D2 and D is less than D3 and D4; a step end face I of the reverse air flow is arranged between the step hole I and the step hole II, a step end face II of the reverse air flow is arranged between the step hole II and the inner hole of the stable section, a step end face III of the forward air flow is arranged between the inner hole of the stable section and the step hole III, and a step end face IV of the forward air flow is arranged between the step hole III and the step Kong;
the inner diameter of the step hole I is D1, and the depth is t1; the rear end of the taper hole diffusion section is provided with a flange ring I, 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 stepped hole I from front to back, countersunk through holes I are uniformly distributed on the flange ring I, screw holes I which are in one-to-one correspondence with the countersunk through holes I are uniformly distributed on the end face I of the step, and the taper hole diffusion section is fixed on the end face I of the step through countersunk screws I penetrating through the countersunk through holes I and the screw holes I;
the inner diameter of the step hole II is D2, and the depth is t2; the outer diameter of the honeycomb device is D2, the thickness of the honeycomb device is t2, the honeycomb device is arranged in the step hole II, the front end face of the honeycomb device is tightly propped against the rear end face of the taper hole diffusion section, and the rear end face of the honeycomb device is tightly propped against the step end face II;
the inner diameter of the 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 running state; screw holes III are formed in the corresponding shell wall surfaces of the stabilizing sections, and Pi Tuoya force measuring interfaces are connected with the screw holes III through threads;
the inner diameter of the step hole III is D3, and the depth is t3; the outer diameter of the sintering net section is D3, the thickness of the sintering net section is t3, the sintering net section is arranged in the step hole III, the front end face of the sintering net section is propped against the step end face III, and the rear end face of the sintering net section is propped against the front end face of the compacting section;
the step Kong has an inner diameter D4 and a depth 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 is t4, the flange ring II is inserted into the step Kong from back to front, countersunk through holes II are uniformly distributed on the flange ring II, screw holes II which are in one-to-one correspondence with the countersunk through holes II are uniformly distributed on the end face IV of the step, and the compression section is fixed on the end face IV of the step through countersunk screws II penetrating through the countersunk through holes II and the screw holes II.
Further, the replacing section is a cylinder and is made of stainless steel plates, and the length, the outer diameter and the inner diameter of the replacing section are respectively the same as the length, the outer diameter and the inner diameter of the corresponding sintering net section.
Further, the front end of the taper hole diffusion section is a nose 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 processed by a stainless steel forging piece, is of a solid structure, is provided with a ball head at the top, has a vertex angle range of 45-70 degrees, and is welded with the skirt section; the skirt section is made of stainless steel plates, and the wall thickness meets the structural stability in the low Mach number maximum flow running state; the skirt section is provided with vent holes which are arrayed, the central axis of each vent hole is perpendicular to the generatrix of the head cone, the three adjacent vent holes are in a regular triangle, the effective flow area of all vent holes is more than 60%, and the skirt section is connected with the flange ring I by welding; the flange ring I is matched with the step hole I by H8/H7.
Further, the honeycomb device is disc-shaped and is integrally manufactured by adopting a stainless steel forging piece; 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 honeycombs Kong Chengzheng are triangular; the honeycomb device is matched with the step hole II by H8/H7.
Further, the effective ventilation diameter of the sintering net section is the same as the inner diameter D of the shell of the stabilizing section, and the sintering net section is of a multi-layer net structure and comprises a pressing plate, a sintering net and a supporting ring; the pressing plate and the supporting ring are both circular, a well-shaped framework is arranged in the pressing plate and the supporting ring, and the pressing plate and the supporting ring are integrally formed by cutting steel plates or assembling and welding parts; the windward side of the well-shaped framework of the pressing plate is provided with a pointed cone; the sintering net is formed by sintering a plurality of layers of silk screens 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 supporting ring are fixedly connected by adopting welding or countersunk screws.
Further, setting a plurality of sintering net sections according to the requirement, wherein the sintering net sections are separated by a spacing ring, and the sum of the thicknesses of the plurality of sintering net sections and the matched spacing ring is t3; screw holes IV are respectively formed in the wall surface of the stabilizing section shell corresponding to each spacer ring, and the pulsating pressure measurement interface is connected with the screw holes IV through threads; the mesh numbers of the sintering meshes in each sintering mesh section are the same or different.
Further, the spacer ring is a cylinder, is made of stainless steel plates, and has a thickness which meets the structural stability in the low Mach number maximum flow running state; the outer diameter of the spacing ring is the same as the inner diameter D3 of the step hole III, and the inner diameter of the spacing ring is the same as the inner diameter D of the shell of the stabilizing section; the length of the spacing ring is more than 100 times of the nominal diameter of a single hole of the sintering net.
Further, the front end of the compaction section is a cylinder, the rear end of the compaction section is a flange ring II, and the compaction section is rolled by stainless steel plates; the inner hole of the compacting 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 stabilizing section, and the diameter D5 of the inlet of the connected hypersonic wind tunnel axisymmetric molded surface spray pipe is the same as the diameter D5 of the inlet of the connected hypersonic wind tunnel axisymmetric molded surface spray pipe; the outer diameter of the cylinder at the front end of the compacting section is the same as that of the sintering net section; the flange ring II is matched with the step Kong by 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 accuracy of the force measurement test of the aircraft model is improved.
2. The adjustable sintering net sections are adopted, and the number of the sintering net sections, the mesh number of the sintering net and the layer number can be adjusted according to different test requirements so as to achieve the optimal effect and the maximum efficiency.
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 air flow channel in the shell of the stable section is ensured to have no steps, and air flow disturbance is reduced.
4. The taper hole diffusion section and the honeycomb device play a good role in reducing speed and guiding flow, the axis of the vent hole of the taper hole diffusion section is perpendicular to the taper bus, the purpose of reducing speed of air flow is achieved, and the air flow is uniformly guided by the honeycomb device to run along the downstream field direction, so that the interference of transverse noise waves is reduced.
5. The ventilation holes of the taper 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 air flow is reduced; the honeycomb Kong Caiyong regular hexagon structure of the honeycomb device is easy to typeset during processing, reduces gaps among honeycomb holes and increases ventilation rate, and round ventilation holes are adopted because the taper hole diffusion section is an inclined plane and is difficult to process.
6. The windward side of the cross-shaped framework of the supporting ring of the sintering net section adopts a pointed cone form, so that on one hand, the resistance and pressure drop of air flow are reduced, and on the other hand, the rectifying effect is also realized, so that the air flow flows along the axial direction more smoothly.
7. The distance between the sintering net sections can be adjusted according to the requirements, and the distance between the sintering net sections can be adjusted according to different test requirements, different sintering net meshes and different layers of the sintering net sections, so that the best rectifying effect can be achieved.
8. The compacting section can enable the whole device to be firmly and stably fixed in the stabilizing section body, reduce airflow pulsation caused by vibration and improve the rectifying effect of the device.
The device for reducing the low Mach number airflow pulsation of the large-caliber hypersonic wind tunnel can improve the flow separation phenomenon of test airflow in a stable section when the hypersonic wind tunnel runs at the low Mach number, reduce the airflow pulsation of the test airflow and improve the accuracy of a force measurement test of an aircraft model.
Drawings
FIG. 1 is a schematic structural diagram of a device for reducing the low Mach number airflow pulsation of a large-caliber hypersonic wind tunnel according to the invention;
FIG. 2 is a schematic diagram of a stable section shell structure in the device for reducing the low Mach number airflow pulsation of the large-caliber hypersonic wind tunnel;
FIG. 3 is a schematic diagram of a cone hole diffuser section in the device for reducing the low Mach number airflow pulsation of the large-caliber hypersonic wind tunnel;
FIG. 4 is a front view of a honeycomb 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 partial enlarged view of the honeycomb cell distribution in the device for reducing the low Mach number airflow pulsation of the large-caliber hypersonic wind tunnel;
FIG. 6 is a side view of a sintered mesh segment in the apparatus for reducing the low Mach number airflow pulsations of a large caliber hypersonic wind tunnel of the present invention;
FIG. 7 is a front view of a sintered mesh segment in the apparatus for reducing the low Mach number airflow pulsations of a large caliber hypersonic wind tunnel of the present invention;
FIG. 8 is a diagram of a support ring configuration in the device for reducing the low Mach number airflow pulsations of a large-caliber hypersonic wind tunnel according to the present invention;
FIG. 9 is a front view of a compacting section in the device for reducing the pulsation of the low Mach number air flow of the large-caliber hypersonic wind tunnel.
In the figure, 1. A taper hole diffusion section; 2. countersunk head screw I; 3. a honeycomb device; 4. a stabilizing section housing; 5. sintering the net section; 6. a spacer ring; 7. a compacting section; 8. countersunk head screw II; 9. pi Tuoya force measurement interface; 10. a pulsating pressure measurement interface; 11. step hole I; 12. screw hole I; 13. step hole II; 14. step hole III; 15. a step Kong; 16. 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. honeycomb holes; 25. a pressing 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 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 comprises a taper hole diffusion section 1, a honeycomb device 3, a sintering net section 5 and a compacting section 7 which are arranged in sequence from front to back, wherein the taper hole diffusion section is arranged in the inner cavity of a stabilizing section shell 4; the stabilizing section shell 4 is provided with a leather pressure measuring interface 9 and a pulsating pressure measuring interface 10; also comprises a replacing section for replacing the sintering net section 5;
as shown in fig. 2, in the inner cavity of the stabilizing section shell 4, a step hole i 11, a step hole ii 13, a stabilizing section inner hole, a step hole iii 14 and a step Kong are sequentially arranged from front to back along the forward airflow direction, and the corresponding inner diameters are D1, D2, D, D and D4 respectively, wherein D1 is greater than D2 and D is less than D3 and D4; a step end face I of reverse air flow is arranged between the step hole I11 and the step hole II 13, a step end face II of reverse air flow is arranged between the step hole II 13 and the inner hole of the stable section, a step end face III of forward air flow is arranged between the inner hole of the stable section and the step hole III 14, and a step end face IV of forward air flow is arranged between the step hole III 14 and the step Kong;
the inner diameter of the step hole I11 is D1, and the depth is t1; the rear end of the taper hole diffusion section 1 is provided with a flange ring I22, the outer diameter of the flange ring I22 is D1, and the thickness 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 are in one-to-one correspondence with the countersunk through holes I23 are uniformly distributed on the stepped end face I, and the taper hole diffusion section 1 is fixed on the stepped end face I through countersunk screws I2 which pass through the countersunk through holes I23 and the screw holes I12;
the inner diameter of the step 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 3 is t2, the honeycomb device 3 is arranged in the step hole II 13, the front end face of the honeycomb device 3 abuts against the rear end face of the taper hole diffusion section 1, and the rear end face of the honeycomb device 3 abuts against the step end face II;
the inner diameter of the 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 running state; screw holes III 17 and Pi Tuoya are formed in the wall surface of the corresponding stabilizing section shell 4, and the force measuring interfaces 9 are connected with the screw holes III 17 through threads;
the inner diameter of the step hole III 14 is D3, and the depth is t3; the outer diameter of the sintering net section 5 is D3, the thickness is t3, the sintering net section 5 is arranged in the step hole III 14, the front end face of the sintering net section 5 is propped against the step end face III, and the rear end face of the sintering net section 5 is propped against the front end face of the compacting section 7;
the step Kong has an inner diameter D4 and a depth t4; the rear end of the pressing 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 Kong from back to front, countersunk through holes II 29 are uniformly distributed on the flange ring II 30, screw holes II 16 which are in one-to-one correspondence with the countersunk through holes II 29 are uniformly distributed on the step end face IV, and the pressing section 7 is fixed on the step end face IV through countersunk screws II 8 which penetrate through the countersunk through holes II 29 and the screw holes II 16.
Further, the replacing section is a cylinder and is made of stainless steel plates, and the length, the outer diameter and the inner diameter of the replacing section are respectively the same as the length, the outer diameter and the inner diameter of the corresponding sintering net section 5.
Further, as shown in fig. 3, the front end of the taper hole diffusion 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 processed by a stainless steel forging, is of a solid structure, is provided with a ball head at the top, has a vertex angle range of 45-70 degrees, and is welded and connected with the skirt section 20; the skirt section 20 is made of stainless steel plates, and the wall thickness meets the structural stability under the low Mach number maximum flow running 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 bus of the nose cone 19, the three adjacent vent holes 21 are in a regular triangle shape, the effective flow area of all vent holes 21 is more than 60%, and the skirt section 20 is connected with the flange ring I22 by welding; the flange ring I22 is matched with the stepped hole I11 by H8/H7.
Further, as shown in fig. 4 and 5, the honeycomb device 3 is a disc type, and is integrally manufactured by adopting a stainless steel forging 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 regular triangles; the honeycomb device 3 is matched with the step hole II 13 by H8/H7.
Further, as shown in fig. 6 and 7, the effective ventilation diameter of the sintering net section 5 is the same as the inner diameter D of the stabilizing section shell 4, and the sintering net section 5 has a multi-layer net structure, including 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, a well-shaped framework is arranged in the pressing plate, and the pressing plate and the supporting ring are integrally cut and formed by steel plates or formed by assembling and welding parts; the windward side of the well-shaped framework of the pressing plate 25 is provided with a pointed cone 26; the sintering net 27 is formed by sintering a plurality of layers of silk screens with the same specification, and the mesh number of the sintering net 27 ranges from 20 meshes to 120 meshes; the pressing plate 25, the sintering net 27 and the supporting ring 28 are fixedly connected by adopting welding connection or countersunk screws.
Further, a plurality of sintering net sections 5 are arranged according to the requirement, the sintering net sections 5 are separated by a spacing ring 6, and the sum of the thicknesses of the plurality of sintering net sections 5 and the matched spacing ring 6 is t3; screw holes IV 18 are respectively formed in the wall surface of the stabilizing section shell 4 corresponding to each spacer ring 6, and the pulsating pressure measurement interface 10 is connected with the screw holes IV 18 through threads; the mesh numbers of the sintering meshes 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 stainless steel plate, and the thickness of the spacer ring 6 satisfies the structural stability in the low mach number maximum flow running state; the outer diameter of the spacing ring 6 is the same as the inner diameter D3 of the step hole III 14, and the inner diameter of the spacing 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 sintering net 27.
Further, as shown in fig. 9, the front end of the compacting section 7 is a cylinder, the rear end is a flange ring ii 30, and the compacting section is made of stainless steel plate; the inner hole of the compacting 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 inlet of the connected hypersonic wind tunnel axisymmetric molded surface spray pipe is the same as the outlet of the cone hole; the outer diameter of the cylinder at the front end of the compacting section 7 is the same as the outer diameter of the sintering net section 5; the flange ring II 30 is matched with the step Kong by H8/H7.
Although embodiments of the invention have been disclosed in the foregoing description and illustrated in the drawings, it will be understood by those skilled in the art that the present invention is not limited to the specific details and illustrations of features and steps set forth herein, and that all features of the invention disclosed, or steps of the method or process, except for mutually exclusive features and/or steps, may be combined in any manner without departing from the principles of the invention.
Claims (8)
1. The device for reducing the low Mach number airflow pulsation of the large-caliber hypersonic wind tunnel is characterized by comprising a taper hole diffusion section (1), a honeycomb device (3), a sintering net section (5) and a compacting section (7) which are arranged in sequence from front to back, wherein the taper hole diffusion section is arranged in an inner cavity of a stabilizing section shell (4); a leather pressure measurement interface (9) and a pulsation pressure measurement interface (10) are arranged on the stabilizing section shell (4); the device also comprises a replacing section for replacing the sintering net section (5);
the inner cavity of the stabilizing section shell (4) is sequentially provided with a step hole I (11), a step hole II (13), a stabilizing section inner hole, a step hole III (14) and a step Kong (15) from front to back along the forward airflow direction, wherein the corresponding inner diameters are D1, D2, D, D and D4 respectively, D1 is more than D2 and D is less than D3 and less than D4; a step end face I of reverse air flow is arranged between the step hole I (11) and the step hole II (13), a step end face II of reverse air flow is arranged between the step hole II (13) and the inner hole of the stable section, a step end face III of forward air flow is arranged between the inner hole of the stable section and the step hole III (14), and a step end face IV of forward air flow is arranged between the step hole III (14) and the step Kong (15);
the inner diameter of the step hole I (11) is D1, and the depth is t1; the rear end of the taper hole diffusion section (1) is provided with a flange ring I (22), the outer diameter of the flange ring I (22) is D1, and the thickness 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 are in one-to-one correspondence with the countersunk through holes I (23) are uniformly distributed on the step end face I, and the taper 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 step 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 arranged in the step hole II (13), the front end face of the honeycomb device (3) abuts against the rear end face of the taper hole diffusion section (1), and the rear end face of the honeycomb device (3) abuts against the step end face II;
the inner diameter of the 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 running state; screw holes III (17) are formed in the wall surface of the corresponding stabilizing section shell (4), and Pi Tuoya force measuring interfaces (9) are connected with the screw holes III (17) through threads;
the inner diameter of the step hole III (14) is D3, and the depth is t3; the outer diameter of the sintering net section (5) is D3, the thickness of the sintering net section is t3, the sintering net section (5) is arranged in the step hole III (14), the front end face of the sintering net section (5) is propped against the step end face III, and the rear end face of the sintering net section (5) is propped against the front end face of the compacting section (7);
the step Kong (15) has an inner diameter D4 and a depth t4; the rear end of the pressing 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 Kong (15) from back to front, countersunk head through holes II (29) are uniformly distributed on the flange ring II (30), screw holes II (16) which are in one-to-one correspondence with the countersunk head through holes II (29) are uniformly distributed on the step end face IV, and the pressing section (7) is fixed on the step end face IV through countersunk head screws II (8) which penetrate through the countersunk head through holes II (29) and the screw holes 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 stainless steel plates, and the length, the outer diameter and the inner diameter of the replacing section are respectively the same as the length, the outer diameter and the inner diameter of the corresponding sintering net section (5).
3. The device for reducing the low Mach number airflow pulsation of the large-caliber hypersonic wind tunnel according to claim 1 is characterized in that the front end of the taper hole diffusion 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 processed by adopting a stainless steel forging piece, is of a solid structure, is provided with a ball head at the top, has a vertex angle range of 45-70 degrees, and is welded and connected with the skirt section (20); the skirt section (20) is formed by adopting stainless steel plates, and the wall thickness meets the structural stability under the low Mach number maximum flow running 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 bus of the nose cone (19), the three adjacent vent holes (21) are in a regular triangle, 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) by welding; the flange ring I (22) is matched with the step hole I (11) by 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 honeycomb device (3) is a disc type and is integrally manufactured by adopting a stainless steel forging 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 regular triangles; the honeycomb device (3) is matched with the step hole II (13) by adopting H8/H7.
5. The device for reducing the low Mach number airflow pulsation of the large-caliber hypersonic wind tunnel according to claim 1 is characterized in that the effective ventilation diameter of the sintering net section (5) is the same as the inner diameter D of the stabilizing section shell (4), and the sintering net 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 annular, a well-shaped framework is arranged in the pressing plate, and the pressing plate is formed by integrally cutting steel plates or assembling and welding parts; the windward side of the well-shaped framework of the pressing plate (25) is provided with a pointed cone (26); the sintering net (27) is formed by sintering a plurality of layers of silk screens with the same specification, and the mesh number of the sintering net (27) ranges from 20 meshes to 120 meshes; the pressing plate (25), the sintering net (27) and the supporting ring (28) are fixedly connected by adopting welding or countersunk screws.
6. The device for reducing the low Mach number airflow pulsation of the large-caliber hypersonic wind tunnel according to claim 5 is characterized in that a plurality of sintering network segments (5) are arranged according to requirements, the sintering network segments (5) are 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 stabilizing section shell (4) corresponding to each spacer ring (6), and the pulsation pressure measurement interface (10) is connected with the screw holes IV (18) through threads; the mesh numbers of the sintering screens (27) in the sintering screen sections (5) are the same or different.
7. The device for reducing the low Mach number airflow pulsation of the large-caliber hypersonic wind tunnel according to claim 6, wherein the spacer ring (6) is a cylinder, is made of stainless steel plates, and has a thickness which meets the structural stability in the low Mach number maximum flow running state; the outer diameter of the spacing ring (6) is the same as the inner diameter D3 of the step hole III (14), and the inner diameter of the spacing ring (6) is the same as the inner diameter D of the stabilizing section shell (4); the length of the spacing ring (6) is more than 100 times of the nominal diameter of a single hole of the sintering net (27).
8. The device for reducing the low Mach number airflow pulsation of the large-caliber hypersonic wind tunnel according to claim 1 is characterized in that the front end of the compressing section (7) is a cylinder, the rear end is a flange ring II (30), and a stainless steel plate is adopted for winding; the inner hole of the compacting 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 inlet of the connected hypersonic wind tunnel axisymmetric molded surface spray pipe is the same as the diameter D5 of the outlet of the connected hypersonic wind tunnel axisymmetric molded surface spray pipe; the outer diameter of the cylinder at the front end of the compaction section (7) is the same as the outer diameter of the sintering net section (5); the flange ring II (30) is matched with the step Kong (15) by adopting H8/H7.
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