CN210860194U - Water-cooling test flange for hypersonic-velocity low-density wind tunnel stabilization section - Google Patents
Water-cooling test flange for hypersonic-velocity low-density wind tunnel stabilization section Download PDFInfo
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- CN210860194U CN210860194U CN201921978729.0U CN201921978729U CN210860194U CN 210860194 U CN210860194 U CN 210860194U CN 201921978729 U CN201921978729 U CN 201921978729U CN 210860194 U CN210860194 U CN 210860194U
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Abstract
The utility model discloses a water-cooling test flange for hypersonic low density wind-tunnel stable section. The water-cooling test flange is a circular ring, a cavity in the center of the circular ring is used for passing through hypersonic low-density wind tunnel airflow, an annular water channel is arranged in the circular wall of the circular ring, straight water channels which are uniformly distributed and perpendicular to the annular water channel are formed in the annular water channel, water-cooling joints are connected to the straight water channels, one part of the water-cooling joints are externally connected with a cooling water inlet pipeline, and the other part of the corresponding water-cooling joints are externally connected with a cooling water outlet pipeline; through holes which are uniformly distributed and perpendicular to the annular water channel are further formed in the annular water channel, test joints are connected to the through holes, one part of the test joints are used for installing a total pressure sensor for measuring the total pressure of the hypersonic low-density wind tunnel airflow, and the other part of the test joints are used for installing a temperature sensor for measuring the total temperature of the hypersonic low-density wind tunnel airflow. The water-cooling test flange is simple in structure and strong in reliability, and can measure high-temperature and high-pressure gas with the pressure of 10MPa and the temperature of 9000K.
Description
Technical Field
The utility model belongs to the technical field of the hypersonic wind tunnel test, concretely relates to water-cooling test flange for hypersonic low density wind tunnel stable section.
Background
In a hypersonic wind tunnel, particularly in high-temperature and high-pressure wind tunnel equipment such as a hypersonic low-density wind tunnel, an electric arc wind tunnel and the like, gas in a stable section is high-temperature and high-pressure gas, a testing instrument is required to be connected to a water-cooling testing flange when the pressure and the temperature of the gas in the stable section are measured, and the water-cooling testing flange is located between the stable section and an inlet of a spray pipe, so that the influence of the water-cooling testing flange on the parameters of the high-temperature and high-pressure gas is reduced as much as possible on the basis of meeting. The existing water-cooling test flange is convenient for installing a test instrument, a water-cooling channel is not usually arranged at a test port, and due to the fact that the structural design is unreasonable, high-temperature and high-pressure gas in a stable section often causes burning loss of the test port and the test instrument of the water-cooling test flange.
At present, a water-cooling test flange special for a hypersonic speed low-density wind tunnel stabilizing section needs to be developed.
SUMMERY OF THE UTILITY MODEL
The utility model aims to solve the technical problem that a water-cooling test flange for hypersonic low density wind tunnel stable section is provided.
The utility model discloses a water-cooling test flange for hypersonic low density wind tunnel stable section, its characteristics are, water-cooling test flange include water-cooling joint, flange, straight water course, annular water course and test connector;
the flange is a circular ring, a cavity in the center of the circular ring is used for passing through hypersonic low-density wind tunnel airflow, an annular water channel is arranged in the ring wall of the circular ring, 2m straight water channels which are perpendicular to the annular water channel and are uniformly distributed are formed in the annular water channel, m is larger than or equal to 1, water cooling joints are connected to the straight water channels, m water cooling joints are externally connected with cooling water inlet pipelines, and the other m symmetrical water cooling joints which correspond to the cooling water inlet pipelines one by one are externally connected with cooling water outlet pipelines;
2n through holes perpendicular to the annular water channel are uniformly distributed on the annular water channel, n is more than or equal to 1, the through holes are connected with test connectors, one part of the test connectors are provided with total pressure sensors for measuring the total pressure of the hypersonic low-density wind tunnel airflow, and the other part of the test connectors are provided with temperature sensors for measuring the total temperature of the hypersonic low-density wind tunnel airflow;
bolt holes for connecting and fixing the hypersonic speed low-density wind tunnel stabilizing section are uniformly distributed in the ring wall of the ring, a boss is arranged on one side of the outer surface of the ring wall of the ring, a corresponding concave platform is arranged on the other side of the outer surface of the ring wall of the ring, an annular sealing groove is formed in the boss, a sealing ring is arranged in the annular sealing groove, and the boss and the concave platform are used for positioning and sealing when the water-cooling test flange is connected with the hypersonic speed low-density wind tunnel stabilizing section;
the thickness range of the circular ring of the flange is 20 mm-50 mm.
The temperature sensor is a thermocouple.
The total pressure sensor is a solid piezoresistive sensor.
The water inlet pressure range of the water-cooling joint is 1 MPa-5 MPa.
The number of the flanges is N, and N is more than or equal to 1.
The water-cooling joint, the flange and the test joint are made of stainless steel.
The utility model discloses a water-cooling test flange for hypersonic low density wind tunnel stable section adopts intermediate layer water-cooling mode, test tube in the test joint arranges in between the water-cooling intermediate layer, test tube symmetrical arrangement has guaranteed that the rivers in the annular water course are even, the problem of the test socket and the test instrument burnout of water-cooling test flange has been solved, the demand of installing test instrument on hypersonic low density wind tunnel stable section has been satisfied, the measurement of hypersonic low density wind tunnel stable section total pressure and total temperature has been realized.
The utility model discloses a water-cooling test flange for hypersonic low density wind tunnel stable section simple structure, the good reliability can measure the high temperature high-pressure gas of hypersonic low density wind tunnel stable section that pressure is up to 10MPa, temperature up to 9000K.
The utility model discloses a water-cooling test flange for hypersonic low density wind tunnel stable section can extend the temperature and the pressure measurement of being applied to other high temperature high-pressure pipelines.
Drawings
Fig. 1 is a schematic structural view (front view) of a water-cooling test flange for a hypersonic low-density wind tunnel stabilizing section according to the present invention;
fig. 2 is a schematic structural diagram (side view) of the water-cooling test flange for the hypersonic low-density wind tunnel stabilizing section of the present invention.
In the figure, 1, a water-cooling connector 2, a flange 3, a straight water channel 4, an annular water channel 5 and a test connector.
Detailed description of the preferred embodiments
The present invention will be described in detail with reference to the accompanying drawings.
Example 1
In this embodiment, m is 1, N is 1, and N is 1, that is, the number of the water cooling joints 1 is 2, the number of the test joints 5 is 2, and the number of the flanges 2 is 1.
As shown in fig. 1 and fig. 2, the water-cooling test flange for the hypersonic low-density wind tunnel stabilization section of the present embodiment includes a water-cooling joint 1, a flange 2, a straight water channel 3, an annular water channel 4 and a test joint 5;
the flange 2 is a circular ring, a cavity in the center of the circular ring is used for passing through hypersonic low-density wind tunnel airflow, an annular water channel 4 is arranged in the ring wall of the circular ring, two uniformly distributed straight water channels 3 perpendicular to the annular water channel 4 are arranged on the annular water channel 4, 2 water-cooling joints 1 are connected to the straight water channels 3, one water-cooling joint 1 is externally connected with a cooling water inlet pipeline, and the other water-cooling joint 1 is externally connected with a cooling water outlet pipeline;
two through holes which are uniformly distributed and vertical to the annular water channel 4 are also formed in the annular water channel 4, 2 test joints 5 are connected to the through holes, one test joint 5 is provided with a total pressure sensor for measuring the total pressure of the hypersonic low-density wind tunnel airflow, and the other test joint 5 is provided with a temperature sensor for measuring the total temperature of the hypersonic low-density wind tunnel airflow;
bolt holes for connecting and fixing the hypersonic speed low-density wind tunnel stabilizing section are uniformly distributed in the ring wall of the ring, a boss is arranged on one side of the outer surface of the ring wall of the ring, a corresponding concave platform is arranged on the other side of the outer surface of the ring wall of the ring, an annular sealing groove is formed in the boss, a sealing ring is arranged in the annular sealing groove, and the boss and the concave platform are used for positioning and sealing when the water-cooling test flange is connected with the hypersonic speed low-density wind tunnel stabilizing section;
the thickness range of the circular ring of the flange 2 is 20 mm-50 mm.
The temperature sensor is a thermocouple.
The total pressure sensor is a solid piezoresistive sensor.
The water inlet pressure range of the water-cooling joint 1 is 1 MPa-5 MPa.
The water-cooling joint 1, the flange 2 and the test joint 5 are made of stainless steel.
According to the test requirements, more than 2 flanges 2 can be assembled and overlapped through a boss and a concave table for use, so that N is more than 1; a water-cooling joint 1 can also be added on each flange 2, so that m is more than 1; it is also possible to add a test connection 5 to each flange 2, and to install a plurality of total pressure sensors and temperature sensors so that n > 1.
Claims (6)
1. A water-cooling test flange for a hypersonic low-density wind tunnel stabilization section is characterized by comprising a water-cooling joint (1), a flange (2), a straight water channel (3), an annular water channel (4) and a test joint (5);
the flange (2) is a circular ring, a cavity in the center of the circular ring is used for passing through hypersonic low-density wind tunnel airflow, an annular water channel (4) is arranged in the ring wall of the circular ring, 2m straight water channels (3) perpendicular to the annular water channel (4) are uniformly distributed on the annular water channel (4), m is larger than or equal to 1, the straight water channels (3) are connected with water-cooling joints (1), the m water-cooling joints (1) are externally connected with cooling water inlet pipelines, and the other m symmetrical water-cooling joints (1) which are in one-to-one correspondence with the cooling water inlet pipelines are externally connected with cooling water outlet pipelines;
2n uniformly distributed through holes perpendicular to the annular water channel (4) are further formed in the annular water channel (4), n is larger than or equal to 1, a test connector (5) is connected to each through hole, a part of the test connectors (5) are provided with total pressure sensors for measuring the total pressure of the hypersonic-velocity low-density wind tunnel airflow, and the other part of the test connectors (5) are provided with temperature sensors for measuring the total temperature of the hypersonic-velocity low-density wind tunnel airflow;
bolt holes for connecting and fixing the hypersonic speed low-density wind tunnel stabilizing section are uniformly distributed in the ring wall of the ring, a boss is arranged on one side of the outer surface of the ring wall of the ring, a corresponding concave platform is arranged on the other side of the outer surface of the ring wall of the ring, an annular sealing groove is formed in the boss, a sealing ring is arranged in the annular sealing groove, and the boss and the concave platform are used for positioning and sealing when the water-cooling test flange is connected with the hypersonic speed low-density wind tunnel stabilizing section;
the thickness range of the circular ring of the flange (2) is 20 mm-50 mm.
2. The water-cooling test flange for the stabilizing section of the hypersonic low-density wind tunnel according to claim 1, wherein the temperature sensor is a thermocouple.
3. The water-cooled test flange for the hypersonic speed low-density wind tunnel stabilizing section according to claim 1, wherein the total pressure sensor is a solid piezoresistive sensor.
4. The water-cooling test flange for the hypersonic-velocity low-density wind tunnel stabilizing section according to claim 1, wherein the water-cooling connector (1) has a water inlet pressure ranging from 1MPa to 5 MPa.
5. The water-cooling test flange for the hypersonic-speed low-density wind tunnel stabilizing section according to claim 1, wherein the number of the flanges (2) is N, and N is more than or equal to 1.
6. The water-cooling test flange for the hypersonic low-density wind tunnel stabilizing section according to claim 1, wherein the water-cooling joint (1), the flange (2) and the test joint (5) are made of stainless steel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921978729.0U CN210860194U (en) | 2019-11-15 | 2019-11-15 | Water-cooling test flange for hypersonic-velocity low-density wind tunnel stabilization section |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921978729.0U CN210860194U (en) | 2019-11-15 | 2019-11-15 | Water-cooling test flange for hypersonic-velocity low-density wind tunnel stabilization section |
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| Publication Number | Publication Date |
|---|---|
| CN210860194U true CN210860194U (en) | 2020-06-26 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201921978729.0U Active CN210860194U (en) | 2019-11-15 | 2019-11-15 | Water-cooling test flange for hypersonic-velocity low-density wind tunnel stabilization section |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110762305A (en) * | 2019-11-15 | 2020-02-07 | 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 test flange for hypersonic-velocity low-density wind tunnel stabilization section |
| CN116810151A (en) * | 2023-08-30 | 2023-09-29 | 靖江佳晟真空技术有限公司 | Water-cooling flange structure, welding device and welding method of water-cooling flange |
-
2019
- 2019-11-15 CN CN201921978729.0U patent/CN210860194U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110762305A (en) * | 2019-11-15 | 2020-02-07 | 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 test flange for hypersonic-velocity low-density wind tunnel stabilization section |
| CN116810151A (en) * | 2023-08-30 | 2023-09-29 | 靖江佳晟真空技术有限公司 | Water-cooling flange structure, welding device and welding method of water-cooling flange |
| CN116810151B (en) * | 2023-08-30 | 2023-12-22 | 靖江佳晟真空技术有限公司 | Water-cooling flange structure |
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