CN112213069B - Flow field calibration and measurement bent frame with cooling structure for hypersonic high-temperature wind tunnel - Google Patents
Flow field calibration and measurement bent frame with cooling structure for hypersonic high-temperature wind tunnel Download PDFInfo
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- CN112213069B CN112213069B CN202011081758.4A CN202011081758A CN112213069B CN 112213069 B CN112213069 B CN 112213069B CN 202011081758 A CN202011081758 A CN 202011081758A CN 112213069 B CN112213069 B CN 112213069B
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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
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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
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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
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
- G01M9/065—Measuring arrangements specially adapted for aerodynamic testing dealing with flow
Abstract
The invention discloses a flow field calibration bent frame with a cooling structure for a hypersonic high-temperature wind tunnel. The flow field calibration bent frame comprises a bent frame front edge and a bent frame rear beam which are sequentially connected from front to back, wherein the bent frame front edge is a wedge, and the bent frame rear beam is a cuboid; the test probe is positioned on the symmetrical central plane and is inserted into and fixed with the rear beam of the bent from the front edge of the bent; and a cooling channel is arranged in the front edge of the bent frame, and cooling water flows into the other side surface from one side of the front edge of the bent frame and flows out of the other side surface to cool the front edge of the bent frame, the test probe and the rear beam of the bent frame. The front edge of the bent frame is provided with a conical through hole, the front end of the test probe is provided with a spherical bulge, and the front end sealing mode is linear sealing. The symmetrical center plane of the bent frame back beam is provided with a step through hole, and the back end sealing mode of the step through hole is surface sealing. The flow field calibration rack can simultaneously realize cooling of the test probes and the flow field calibration rack, meets the requirement of calibrating the flow field of the hypersonic high-temperature wind tunnel, and ensures the calibration safety.
Description
Technical Field
The invention belongs to the technical field of hypersonic wind tunnels, and particularly relates to a flow field calibration and measurement bent frame with a cooling structure for a hypersonic high-temperature wind tunnel.
Background
A hypersonic high-temperature wind tunnel is one of important ground test devices for developing key technical researches of hypersonic aircrafts, and the wind tunnel can simulate parameters such as Mach number, total enthalpy and dynamic pressure of a flight trajectory.
Wind tunnel flow field calibration is a basic work for ensuring the correctness and reliability of wind tunnel test data, fully and correctly reads the performance parameters of the wind tunnel flow field, relates to correct recognition of the uncertainty of the wind tunnel test data, and finally influences the application of the wind tunnel test data in terminal products such as aircraft design and the like.
When the hypersonic speed high-temperature wind tunnel is used for flow field calibration, a flow field calibration rack is usually arranged in a test flow field at the outlet of a spray pipe, and test flow field data are obtained through a test probe arranged on the flow field calibration rack. Because the total temperature of the airflow of the hypersonic high-temperature wind tunnel is higher and exceeds the melting point of conventional materials such as stainless steel used by the test probe, if no cooling measure is taken, both the test probe and the flow field calibration and measurement frame are possibly burnt.
In order to avoid the test probes and the flow field calibration rack from being burnt in the high supersonic speed high temperature wind tunnel calibration, a flow field calibration rack which is specially used for the high supersonic speed high temperature wind tunnel and is provided with a cooling structure needs to be developed urgently.
Disclosure of Invention
The invention aims to solve the technical problem of providing a flow field calibration bent frame with a cooling structure for a hypersonic high-temperature wind tunnel.
The invention discloses a flow field calibration bent frame with a cooling structure for a hypersonic high-temperature wind tunnel, which is characterized in that: the flow field calibration bent frame comprises a bent frame front edge and a bent frame rear beam which are sequentially connected from front to back, the bent frame front edge is wedge-shaped, the bent frame rear beam is a cuboid, the wedge back of the wedge is in smooth transition with the front end face of the cuboid, and the bent frame front edge and the bent frame rear beam share a symmetrical central plane; the test probe is positioned on the symmetrical central plane, the test probe is inserted into the bent back beam from the front edge of the bent, and the test probe is respectively fixed with the front edge of the bent and the bent back beam in a sealing way; and a cavity is arranged in the front edge of the bent frame, the cavity forms a cooling channel, cooling water flows into the cooling channel from one side surface of the front edge of the bent frame and flows out of the cooling channel from the other side surface of the front edge of the bent frame, and the front edge of the bent frame, the test probe and the bent frame rear beam are cooled.
Furthermore, the front edge of the bent frame is provided with a conical through hole, the front end of the test probe is provided with a spherical protrusion, the spherical protrusion is clamped in the conical through hole in the process that the test probe is inserted into the front edge of the bent frame, and the contact surface forms a front end sealing surface.
Furthermore, the symmetrical center plane of the bent frame back beam is provided with a step through hole, the inner diameter of the through hole I is R1, the inner diameter of the through hole II is R2, R1 is smaller than R2, the test probe is in clearance fit with the through hole I, the test probe is in clearance fit with the through hole II through a compression sealing block, and the tail end of the test probe is connected with a pressure measuring hose through a connecting joint.
Furthermore, the front end of the compression sealing block is also provided with an O-shaped sealing ring, and the position of the O-shaped sealing ring is a rear end sealing surface.
Furthermore, the material of the bent front edge is high-temperature alloy or stainless steel, the material of the bent back beam is stainless steel, and the material of the test probe is copper alloy.
The front end sealing mode of the flow field calibration and measurement bent frame with the cooling structure for the hypersonic high-temperature wind tunnel is linear sealing, the spherical protrusion at the front end of the test probe is in linear contact in the process of being inserted into the tapered through hole at the front edge of the bent frame, and then the linear sealing is realized through locking of the connecting joint at the rear end of the test probe, and the linear sealing does not need a sealing ring or sealant for auxiliary sealing, so that the sealing device is particularly suitable for being applied to the special environment of the test flow field of the hypersonic high-temperature wind tunnel.
The front end sealing mode of the flow field calibration and measurement frame with the cooling structure for the hypersonic high-temperature wind tunnel is surface sealing, the temperature of the rear end of the test probe is reduced after cooling water, the temperature use requirement of an O-shaped sealing ring is met, the O-shaped sealing ring is tightly pressed on the sealing surface of the rear end of the test probe by the pressing sealing block, and the sealing in the axial direction and the radial direction of the test probe can be realized.
The flow field calibration rack with the cooling structure for the hypersonic high-temperature wind tunnel can simultaneously realize cooling of the test probe and the flow field calibration rack, meets the requirement of the hypersonic high-temperature wind tunnel on flow field calibration and measurement, and ensures the calibration and measurement safety.
Drawings
Fig. 1 is a schematic structural diagram of a flow field calibration and measurement bent frame with a cooling structure for a hypersonic high-temperature wind tunnel according to the invention.
FIG. 2 is a sectional view of the mounting section of the front edge and the rear beam of the bent frame in the flow field calibration bent frame with a cooling structure for the hypersonic-speed high-temperature wind tunnel according to the invention;
FIG. 3 is a cross-sectional view of a test probe used in a flow field calibration bent with a cooling structure for a hypersonic high-temperature wind tunnel according to the present invention;
FIG. 4 is a cross sectional view of a front end sealing surface in a flow field calibration bent frame with a cooling structure for a hypersonic high-temperature wind tunnel according to the invention;
FIG. 5 is a cross-sectional view of a rear end sealing surface in a flow field calibration bent frame with a cooling structure for a hypersonic high-temperature wind tunnel according to the invention.
In the figure, 1, a bent front edge 2, a bent rear beam 3, a test probe 4, a cooling channel 5, an O-shaped sealing ring 6, a compression sealing block 7 and a connecting joint are arranged;
301. a front end sealing surface 302, a rear end sealing surface.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings and examples.
As shown in fig. 1 to 3, the flow field calibration bent frame with a cooling structure for a hypersonic high-temperature wind tunnel according to the invention comprises a bent frame front edge 1 and a bent frame rear beam 2 which are sequentially connected from front to back, wherein the bent frame front edge 1 is a wedge, the bent frame rear beam 2 is a cuboid, the back of the wedge is in smooth transition with the front end surface of the cuboid, and the bent frame front edge 1 and the bent frame rear beam 2 share a symmetrical central plane; the test probe 3 is positioned on the symmetrical central plane, the test probe 3 is inserted into the bent back beam 2 from the bent front edge 1, and the test probe 3 is respectively fixed with the bent front edge 1 and the bent back beam 2 in a sealing way; the cavity is arranged in the bent front edge 1, the cavity forms a cooling channel 4, cooling water flows into the cooling channel 4 from one side surface of the bent front edge 1 and flows out of the cooling channel 4 from the other side surface of the bent front edge 1, and the bent front edge 1, the test probe 3 and the bent back beam 2 are cooled.
Further, as shown in fig. 2, the front edge 1 of the bent frame is provided with a tapered through hole, the front end of the test probe 3 is provided with a spherical protrusion, and in the process of inserting the test probe 3 into the front edge 1 of the bent frame, the spherical protrusion is fitted and clamped in the tapered through hole, and the contact surface forms a front end sealing surface 301 as shown in fig. 4.
Furthermore, as shown in fig. 3, a stepped through hole is formed in the symmetrical center plane of the bent back beam 2, the inner diameter of the through hole i is R1, the inner diameter of the through hole ii is R2, R1 is smaller than R2, the test probe 3 is in clearance fit with the through hole i, the test probe 3 is in clearance fit with the through hole ii through a compression sealing block 6, and the tail end of the test probe 3 is connected with a pressure measuring hose through a connecting joint 7.
Furthermore, the front end of the compression seal block 6 is also provided with an O-ring 5, and the position of the O-ring 5 is a rear end seal surface 302 as shown in fig. 5.
Furthermore, the bent front edge 1 is made of high-temperature alloy or stainless steel, the bent back beam 2 is made of stainless steel, and the test probe 3 is made of copper alloy.
The following examples are intended to illustrate the invention but are not intended to limit the scope of the invention.
Example 1
The wedge apex angle of the bent front edge 1 of the bent frame is 40 degrees, the wall thickness is 3mm, and the arc radius R6 is formed; the arc radius R4 of the cooling channel 4 in the inner cavity of the bent front edge 1; the flow rate of the cooling water in the cooling passage 4 was about 10m/s, and the pressure of the cooling water was 1.0 MPa.
The bent front edge 1 of the embodiment is made of high-temperature alloy, the bent back beam 2 is made of stainless steel, and the test probe 3 is made of copper alloy with good heat conductivity.
Although the embodiments of the present invention have been disclosed above, it is not limited to the applications listed in the description and the embodiments, but it can be applied to various fields suitable for the present invention. Additional modifications and refinements of the present invention will readily occur to those skilled in the art without departing from the principles of the present invention, and therefore the present invention is not limited to the specific details and illustrations shown and described herein without departing from the general concept defined by the claims and their equivalents.
Claims (4)
1. The utility model provides a flow field calibration and measurement framed bent that is used for hypersonic high temperature wind-tunnel to have cooling structure which characterized in that: the flow field calibration bent frame comprises a bent frame front edge (1) and a bent frame rear beam (2) which are sequentially connected from front to back, wherein the bent frame front edge (1) is a wedge, the bent frame rear beam (2) is a cuboid, the wedge back of the wedge is in smooth transition with the front end surface of the cuboid, and the bent frame front edge (1) and the bent frame rear beam (2) share a symmetrical central plane; the test probe (3) is positioned on the symmetrical central plane, the test probe (3) is inserted into the bent back beam (2) from the bent front edge (1), and the test probe (3) is respectively fixed with the bent front edge (1) and the bent back beam (2) in a sealing way; a cavity is arranged in the bent front edge (1), the cavity forms a cooling channel (4), cooling water flows into the cooling channel (4) from one side surface of the bent front edge (1) and flows out of the cooling channel (4) from the other side surface of the bent front edge (1) to cool the bent front edge (1), the test probe (3) and the bent rear beam (2);
the bent frame rear beam (2) symmetry central plane on open and to have the step through-hole, the internal diameter of through-hole I is R1, the internal diameter of through-hole II is R2, R1 < R2, clearance fit between test probe (3) and the through-hole I, test probe (3) and through-hole II through compressing tightly sealed piece (6) clearance fit, the end of test probe (3) is through attach fitting (7) connection pressure measurement hose.
2. The flow field calibration bent frame with the cooling structure for the hypersonic high-temperature wind tunnel according to claim 1, wherein: the bent frame is characterized in that the bent frame front edge (1) is provided with a conical through hole, the front end of the test probe (3) is provided with a spherical protrusion, the spherical protrusion is clamped in the conical through hole in the process that the test probe (3) is inserted into the bent frame front edge (1), and a front end sealing surface (301) is formed on a contact surface.
3. The flow field calibration bent frame with the cooling structure for the hypersonic high-temperature wind tunnel according to claim 1, wherein: the front end of the compression sealing block (6) is also provided with an O-shaped sealing ring (5), and the position of the O-shaped sealing ring (5) is a rear end sealing surface (302).
4. The flow field calibration bent frame with the cooling structure for the hypersonic high-temperature wind tunnel according to claim 1, wherein: the bent front edge (1) is made of high-temperature alloy or stainless steel, the bent back beam (2) is made of stainless steel, and the test probe (3) is made of copper alloy.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011081758.4A CN112213069B (en) | 2020-10-12 | 2020-10-12 | Flow field calibration and measurement bent frame with cooling structure for hypersonic high-temperature wind tunnel |
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| CN202011081758.4A CN112213069B (en) | 2020-10-12 | 2020-10-12 | Flow field calibration and measurement bent frame with cooling structure for hypersonic high-temperature wind tunnel |
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| CN112213069A CN112213069A (en) | 2021-01-12 |
| CN112213069B true CN112213069B (en) | 2022-06-10 |
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| CN112985751B (en) * | 2021-02-01 | 2022-09-23 | 中国空气动力研究与发展中心超高速空气动力研究所 | Hypersonic wind tunnel stable section total temperature and total pressure test bent frame structure and manufacturing method |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN107014582A (en) * | 2017-05-18 | 2017-08-04 | 西北工业大学 | A kind of stagnation temperature framed bent for continuous high-speed wind-tunnel hydrojet nitrogen cooling system |
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| US6904799B2 (en) * | 2002-06-12 | 2005-06-14 | Polar Controls, Inc. | Fluid velocity sensor with heated element kept at a differential temperature above the temperature of a fluid |
| DE102008010477A1 (en) * | 2008-02-21 | 2009-09-03 | Erbe Elektromedizin Gmbh | Cryosurgical instrument |
| EP3112819B1 (en) * | 2015-06-30 | 2020-03-11 | Commissariat A L'energie Atomique Et Aux Energies Alternatives | Miniature differential pressure flow sensor |
| CN106482923B (en) * | 2016-10-28 | 2019-09-06 | 北京航天长征飞行器研究所 | A kind of flow field calibration test device suitable under hot environment |
| KR101869648B1 (en) * | 2017-03-23 | 2018-06-21 | 국방과학연구소 | Flow rate calibration device for wind tunnel model and method thereof |
| CN208156052U (en) * | 2018-05-21 | 2018-11-27 | 中国空气动力研究与发展中心超高速空气动力研究所 | A kind of electron number densitiy measurement two-probe arrangement |
| CN208887888U (en) * | 2018-11-22 | 2019-05-21 | 中国空气动力研究与发展中心高速空气动力研究所 | Driving device is surveyed in supersonic wind tunnel flow field school |
| CN110715789A (en) * | 2019-11-15 | 2020-01-21 | 中国空气动力研究与发展中心超高速空气动力研究所 | Water-cooling light-gathering optical fiber probe for hypersonic-velocity low-density wind tunnel stable section |
| CN110823502B (en) * | 2019-11-20 | 2020-06-02 | 中国空气动力研究与发展中心超高速空气动力研究所 | Whole water-cooling bent in high temperature flow field |
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| CN107014582A (en) * | 2017-05-18 | 2017-08-04 | 西北工业大学 | A kind of stagnation temperature framed bent for continuous high-speed wind-tunnel hydrojet nitrogen cooling system |
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Inventor after: Zeng Lingguo Inventor after: Ren Hu Inventor after: Zhou Xin Inventor after: Wu Jinshui Inventor after: Wu Jun Inventor after: Li Xiangdong Inventor after: Bu Qing Qing Inventor after: Xing Yanchang Inventor after: Zhang Lin Inventor after: Pu Xuyang Inventor after: Li Hongbin Inventor before: Zeng Lingguo Inventor before: Wu Jun Inventor before: Li Xiangdong Inventor before: Bu Qing Qing Inventor before: Zhang Lin Inventor before: Pu Xuyang Inventor before: Li Hongbin Inventor before: Ren Hu Inventor before: Zhou Xin |
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