CN213874884U - Probe calibration wind tunnel test stand - Google Patents
Probe calibration wind tunnel test stand Download PDFInfo
- Publication number
- CN213874884U CN213874884U CN202120082694.3U CN202120082694U CN213874884U CN 213874884 U CN213874884 U CN 213874884U CN 202120082694 U CN202120082694 U CN 202120082694U CN 213874884 U CN213874884 U CN 213874884U
- Authority
- CN
- China
- Prior art keywords
- nozzle
- air inlet
- wind tunnel
- tunnel test
- probe calibration
- 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.)
- Active
Links
Images
Landscapes
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
An object of the utility model is to provide a probe calibration wind-tunnel test platform, it can be at the calibration scope of bigger calibrating to the probe. In order to realize the purpose, the probe calibration wind tunnel test bed comprises an air inlet pipeline, wherein the air inlet pipeline is provided with a regulating valve, the air inlet pipeline is arranged on the upstream side of the regulating valve, an air inlet switch valve is further arranged, and the opening degree of the air inlet switch valve is adjustable.
Description
Technical Field
The utility model relates to a probe calibrating device.
Background
The aerospace field has wide application to sensor technology, wherein the pressure sensing part is extremely important to the application of parts such as aircraft surfaces, airframes and aero-engines. Various probes are very important for the development of aerospace related technologies, and due to the particularity of the structure of the pressure sensing part, in order to ensure the measurement precision, a blowing test, namely probe calibration, needs to be completed in advance.
With the development of aerospace technology, the use environment of the probe sensor gradually crosses from subsonic speed to supersonic speed, and the precision requirement on probe calibration is higher and higher. The conventional probe calibration wind tunnel is mostly applied to the calibration of subsonic probes, and cannot obtain supersonic and even hypersonic probe calibration data. If the related calibration data is needed, a test bed is additionally arranged, and the equipment cost is increased. Chinese patent specification CN109186815A discloses a similar probe temperature calibration device for low-temperature high-mach-number test, which includes a continuous air source, an electric heater, an air inlet valve, a calibration wind tunnel, etc. The test part is positioned in a pressure stabilizing section and a convergence section of the calibration wind tunnel and comprises a movable upright post, a standard temperature probe, a temperature probe to be tested, a temperature probe with the same structure as the temperature probe to be tested, a data acquisition system and a computer. The air flow generated by the continuous air source is heated by the electric heater, and the required temperature is controlled by the temperature controller. After passing through the electric heater, the airflow passes through the air inlet valve through the pipeline, and the air inlet flow is controlled by changing the opening of the valve, so that the Mach number of the airflow at the nozzle is changed. Then the air flow respectively flows through the expansion section, the pressure stabilizing section and the convergence section of the calibration wind tunnel, and uniform air flow at the nozzle of the convergence section is provided. The standard temperature probe is placed in the voltage stabilization section, the temperature probe to be measured is placed at the nozzle of the convergence section, and the temperature probe which is completely the same as the temperature probe to be measured is placed in the voltage stabilization section.
In addition, the single valve adjustment mode causes the problems of relatively low adjustment precision and slow response of the flow Mach number at the outlet of the spray pipe.
In addition, when the high-Mach-number probe is calibrated, if no electric heater is arranged, due to the fact that the static temperature in the spray pipe is reduced, the phenomenon that frost and ice are formed inside the spray pipe can occur, the flowing state of gas flowing through the spray pipe can be changed, the Mach-number fluctuation situation occurs, and the calibration accuracy of the probe is affected.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide a probe calibration wind-tunnel test platform, it can be at the calibration scope of bigger calibrating to the probe.
In order to realize the purpose, the probe calibration wind tunnel test bed comprises an air inlet pipeline, wherein the air inlet pipeline is provided with a regulating valve, the air inlet pipeline is arranged on the upstream side of the regulating valve, an air inlet switch valve is further arranged, and the opening degree of the air inlet switch valve is adjustable.
In one embodiment, the intake line is further connected to a blow line, in which a blow valve is provided, on the upstream side of the intake switch valve.
In one embodiment, the intake line is further provided with a main line switching valve located on the upstream side of the connection location to the blowdown line.
In one embodiment, the regulator valve comprises a main regulator valve and an auxiliary regulator valve in parallel.
In one embodiment, the air inlet pipeline is further provided with a pressure stabilizing component and a spray pipe, the spray pipe is located on the downstream side of the pressure stabilizing component, the spray pipe is arranged to be replaceable, and the probe calibration wind tunnel test stand comprises a plurality of spray pipes, and the plurality of spray pipes correspond to different Mach number configurations.
In one embodiment, the nozzle includes a nozzle box and a nozzle block formed separately from the nozzle box, the nozzle block providing a flow path profile of the nozzle.
In one embodiment, the inlet line is further provided with a pressure-stabilizing part on the downstream side of the regulating valve and a nozzle, which comprises a nozzle box and a nozzle block that is formed separately from the nozzle box and provides the flow path profile of the nozzle.
In one embodiment, the nozzle box is configured with a plurality of nozzle blocks corresponding to different mach numbers, and one selected from the plurality of nozzle blocks is detachably mounted in the nozzle box.
In one embodiment, the air inlet line is provided with a standard interface for alternative connection to a plurality of nozzles.
In one embodiment, the intake line further comprises a test zone, an injection cylinder and an exhaust valve arranged downstream of the test zone in succession.
In one embodiment, the probe calibration wind tunnel test stand further comprises a drying device, and the drying device is arranged on the air inlet side of the air inlet pipeline, so that air entering the probe calibration wind tunnel test stand is dry air.
Besides the Mach number and the target Mach number are calculated through the adjusting valves, the air inlet switch valve is further arranged, and the Mach number and the target Mach number can be further adjusted and calculated through the adjustment of the opening degree of the air inlet switch valve. Therefore, the Mach number calibration range is widened, and an adjustment result with higher adjustment precision can be obtained.
Drawings
The above and other features, properties and advantages of the present invention will become more apparent from the following description of the embodiments with reference to the accompanying drawings, in which:
FIG. 1 is a layout view of a probe calibration wind tunnel test stand.
FIG. 2 is a diagram of a layout of measuring points of a probe calibration wind tunnel test stand.
Fig. 3 is a sectional view taken along line a-a in fig. 1.
Detailed Description
The present invention will be further described with reference to the following embodiments and drawings, and more details will be set forth in the following description in order to provide a thorough understanding of the present invention, but it is obvious that the present invention can be implemented in various other ways different from those described herein, and those skilled in the art can make similar generalizations and deductions according to the actual application without departing from the spirit of the present invention, and therefore, the scope of the present invention should not be limited by the contents of the embodiments.
It should be noted that these and other figures are given by way of example only and are not drawn to scale, and should not be construed as limiting the scope of the invention as it is actually claimed.
As shown in fig. 1, the probe calibration wind tunnel test stand includes an air inlet pipeline, which is a pipeline located on the upstream side of a test area 7, and an air inlet switch valve 2, a main regulating valve 3, an auxiliary regulating valve 4, a pressure stabilizing component 5, a nozzle 6, and the like are arranged in the air inlet pipeline. The probe calibration wind tunnel test bed further comprises an emptying pipeline, wherein the emptying pipeline is led out from the air inlet pipeline at the upstream side of the air inlet switch valve 2, and more specifically is arranged between the main pipeline switch valve 1 and the air inlet switch valve 2. The opening degree of the intake opening/closing valve 2 is adjustable.
The mach number of the test area is calculated mainly based on two pressure measuring points in fig. 2, wherein P is the total pressure average value of the airflow after rectification and pressure stabilization in the pressure stabilizing part 5, the number of the measuring points can be distributed according to the actual use condition, generally, the total pressure measuring points are 4-8, and are circumferentially and uniformly distributed at the position 1/4 behind the pressure stabilizing part 5. And p is the average value of static pressure measuring points on the wall surface of the outlet of the spray pipe 6, the measuring points are distributed on the end walls of the non-spray pipe molded surfaces at the two sides of the outlet of the spray pipe 6, and the number of the measuring points is determined according to the size of the end walls.
The working principle of the probe calibration wind tunnel test bed is that air enters a system, a real-time test section Mach number Ma is calculated according to the pressure measurement point mean value P and the value P, and the ideal state calculation formula is as follows:
Ma＝((k-1)/2*(1-(P*/p)^((k-1)/k)))^(1/2)
where k is the air heat transfer coefficient, typically k is 1.4;
according to the calculated Mach number Ma and the target Mach number Ma0Adjusting the main regulator valve 3 to make the calculated Mach number Ma approach the target Mach number Ma0The adjusting mode is as follows: ma > Ma0Closing the main regulating valve 3; ma < Ma0The main regulator valve 3 is opened. If the Mach number Ma appears in the adjusting process, the main adjusting valve 3 is actuated with the minimum precision, and the Mach number Ma is calculated at the target Ma0When the value fluctuates around, the auxiliary control valve 4 is adjusted to adjust the mach number Ma. If the main regulating valve 3 and the auxiliary regulating valve 4 can not achieve the regulating precision by regulating simultaneously, the air inlet switch valve 2 and the air release valve 10 are regulated if necessary to reduce the air inlet pressure, so that the requirement of improving the regulating precision is met, in addition, under partial working conditions, the inlet pressure requirement is lower, the opening degree of the air inlet switch valve 2 is reduced, the regulating speed of the main regulating valve 3 and the auxiliary regulating valve 4 can be further improved, and the response speed of the tester is improved.
In the air inlet pipeline, the main pipeline switch valve 1 mainly plays a role in protecting safety, and cuts off air supply of the whole tester in emergency.
For anti-icing, the supplied dry air enters the whole tester from an air inlet system through a matched air source compressor set and a drying device, which are not shown in the figure and can be understood as being connected to an air inlet of the whole probe calibration wind tunnel test stand or an air inlet of an air inlet pipeline.
The nozzle 6 comprises a nozzle box located on the outer side, the probe calibration wind tunnel test bed is provided with a standard interface at the connecting position of the nozzle 6, fig. 3 shows a flange or a mounting edge of the nozzle box, and a bolt hole 61 and a positioning pin hole 2 are arranged on each mounting edge. The nozzle 6 is positioned with the pressure stabilizing part 5 or the standard interface on the downstream side of the pressure stabilizing part 5 through the positioning pin hole 2, and then the bolt penetrates through the bolt hole 61 to be connected with the flange. The standard interface can ensure that the calibration wind tunnel test stand can achieve the aim only by redesigning one set of spray pipe section when the capability of the calibration wind tunnel test stand is required to be expanded. The probe calibration wind tunnel test stand is provided with a plurality of spray pipes 6 and has the function of realizing the capability of large-range Mach number calibration in a single tester, wherein the Mach number is 1 or below, namely, one set of spray pipes can be used for the calibration of the sonic probe and the subsonic probe, and special piping is required to be arranged for the calibration of the supersonic probe. The spray pipes 6 are detachably connected, so that the spray pipes 6 are replaceable, a plurality of groups of spray pipes can be matched with the probe calibration test bed, and connection precision and calibration capacity are expanded. As shown in fig. 3, the nozzle block 63 is disposed on the opposite side of the nozzle box and embedded in the nozzle box, the nozzle block 63 and the nozzle box are separately formed, so as to reduce the processing difficulty, the nozzle block 63 provides a profile of a flow passage required by the nozzle 6, and the positioning pin hole 62 is disposed and used for ensuring the center line of the nozzle and the center line of the tester and ensuring the uniformity of the air flow. In one embodiment, the nozzle blocks 63 are also configured to be replaceable, for example, to replace different groups of nozzle blocks for different Mach numbers, such that the nozzle boxes do not need to be replaced.
With continued reference to fig. 1, the probe calibration wind tunnel test stand further comprises an injection cylinder 8, and the uniformity of the fluid in the test area is guaranteed while the gas at the rear end of the test area 7 is injected.
The exhaust valve 9 is a switch valve and is used for preventing the emptying valve 10 from being fully opened and preventing the rear end airflow from reversely flowing back to the test area when the air inlet switch valve 2 is in a fully closed state.
According to the embodiment, the requirement of the Mach number of the air flow in the test section is adjusted and controlled through the combination of the valves, so that the blowing test requirement is met, and the low Mach number calibration control precision is improved through a multi-valve group method. Through the method for replacing a plurality of sets of spray pipes, the calibration capability of a set of test bed in a wide range from low Mach number to high Mach number can be calibrated. The spray pipe section adopts a fixed interface mode, so that a plurality of groups of spray pipes can be matched with the probe calibration test bed, and the connection precision and the calibration capability are ensured to be expanded. Meanwhile, the condition that the spray pipe is frozen under the high Mach calibration working condition is solved by adopting the air inlet source drying treatment.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make various changes and modifications without departing from the spirit and scope of the present invention. Therefore, any modification, equivalent changes and modifications made to the above embodiments according to the technical spirit of the present invention, all without departing from the content of the technical solution of the present invention, fall within the scope of protection defined by the claims of the present invention.
Claims (11)
1. The probe calibration wind tunnel test bed comprises an air inlet pipeline, wherein the air inlet pipeline is provided with an adjusting valve, and the probe calibration wind tunnel test bed is characterized in that the air inlet pipeline is arranged on the upstream side of the adjusting valve and is further provided with an air inlet switch valve, and the opening degree of the air inlet switch valve is adjustable.
2. The probe calibration wind tunnel test stand according to claim 1, wherein the air inlet pipeline is further connected with a vent pipeline on the upstream side of the air inlet switch valve, and a vent valve is arranged in the vent pipeline.
3. The probe calibration wind tunnel test stand according to claim 2, wherein the air inlet pipeline is further provided with a main pipeline switching valve which is located on an upstream side of a connection position to the emptying pipeline.
4. The probe calibration wind tunnel test stand according to claim 1, wherein said regulating valve comprises a main regulating valve and an auxiliary regulating valve connected in parallel.
5. The probe calibration wind tunnel test stand according to claim 1, wherein the air inlet duct is further provided with a pressure stabilizing member and a nozzle pipe located on the downstream side of the regulating valve, the nozzle pipe being located on the downstream side of the pressure stabilizing member, the nozzle pipe being arranged to be replaceable, the probe calibration wind tunnel test stand comprising a plurality of the nozzle pipes corresponding to different mach number configurations.
6. The probe calibration wind tunnel test stand of claim 5 wherein said nozzle includes a nozzle box and a nozzle block formed separately from the nozzle box, said nozzle block providing a flow path profile of the nozzle.
7. The probe calibration wind tunnel test stand according to claim 1, wherein the air inlet pipeline is further provided with a pressure stabilizing component and a nozzle located at the downstream side of the regulating valve, the nozzle comprises a nozzle box and a nozzle block formed separately from the nozzle box, and the nozzle block provides a flow channel profile of the nozzle.
8. The probe calibration wind tunnel test stand of claim 7 wherein said nozzle box is configured with a plurality of sets of nozzle blocks corresponding to different mach numbers, one selected from said plurality of sets of nozzle blocks being removably mounted in said nozzle box.
9. A probe calibration wind tunnel test stand according to any one of claims 5 to 7 wherein said air inlet duct is provided with a standard interface for alternative connection to a plurality of nozzles.
10. A probe calibration wind tunnel test stand according to any one of claims 1 to 8 wherein the air inlet conduit further comprises a test zone, an indexing barrel and an exhaust valve arranged in series downstream of the test zone.
11. The probe calibration wind tunnel test stand according to any one of claims 1 to 8, further comprising a drying device disposed on the air intake side of the air intake duct, such that the air entering the probe calibration wind tunnel test stand is dry air.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120082694.3U CN213874884U (en) | 2021-01-13 | 2021-01-13 | Probe calibration wind tunnel test stand |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120082694.3U CN213874884U (en) | 2021-01-13 | 2021-01-13 | Probe calibration wind tunnel test stand |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN213874884U true CN213874884U (en) | 2021-08-03 |
Family
ID=77045296
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202120082694.3U Active CN213874884U (en) | 2021-01-13 | 2021-01-13 | Probe calibration wind tunnel test stand |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN213874884U (en) |
-
2021
- 2021-01-13 CN CN202120082694.3U patent/CN213874884U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Chupp et al. | Evaluation of internal heat-transfer coefficients for impingement-cooled turbine airfoils. | |
| CN111238759B (en) | Icing wind tunnel pressure measurement test method | |
| CN112304554B (en) | Method for improving practicability of characteristic curve of annular gap pressure regulating valve of wind tunnel | |
| CN104360702B (en) | Dynamic aviation Thermodynamic test system and dynamic temperature, pressure environment control method | |
| CN108458852A (en) | A kind of high-temperature tunnel quick changeable temperature potential device and alternating temperature voltage-transforming method | |
| Brown et al. | Heat transfer correlation for anti-icing systems | |
| CN114018532B (en) | Test method for continuous variable total pressure of hypersonic wind tunnel | |
| US20140208755A1 (en) | Gas Turbine Air Mass Flow Measuring System and Methods for Measuring Air Mass Flow in a Gas Turbine Inlet Duct | |
| CN111537181B (en) | Thermal noise wind tunnel based on arc heating and test method | |
| CN112179664B (en) | Adjustable low-pressure ignition experimental system for researching sub-super mixed flow | |
| CN213874884U (en) | Probe calibration wind tunnel test stand | |
| Moore et al. | Surface curvature effects on film cooling performance for shaped holes on a model turbine blade | |
| Liu et al. | The effects of inlet Reynolds number, exit Mach number and incidence angle on leading edge film cooling effectiveness of a turbine blade in a linear transonic cascade | |
| CN101140162A (en) | Method for measuring flow area of hole with complex profile by supercritical pressure ratio | |
| Byerley et al. | Detailed heat transfer measurements near and within the entrance of a film cooling hole | |
| CN115452312B (en) | Hot gas flow measurement and control method and system | |
| CN216594069U (en) | High-precision low-turbulence flow supply system | |
| Ferro et al. | Experimental study on turbulent asymptotic suction boundary layers | |
| Moore et al. | Adiabatic Effectiveness and Thermal Field Measurements of a Shaped Hole in the Showerhead of a Model Turbine Blade | |
| Zhang et al. | Turbine blade film cooling study: the effects of film hole location on the pressure side | |
| Wilcox et al. | Space Launch System Booster Separation Aerodynamic Testing at the NASA Langley Unitary Plan Wind Tunnel | |
| CN115372013A (en) | Comprehensive test platform and test method for engine and air entraining system | |
| McClintic et al. | The effect of internal cross-flow on the adiabatic effectiveness of compound angle film cooling holes | |
| Zhang et al. | The Effect of Compound Angle on Nozzle Suction Side Film Cooling | |
| Sooriyakumaran | Experimental study of profile losses in three transonic turbine cascades |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |