CN111366295A - Supersonic steady-state pressure probe for reducing strut interference by utilizing plasma jet - Google Patents
Supersonic steady-state pressure probe for reducing strut interference by utilizing plasma jet Download PDFInfo
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- CN111366295A CN111366295A CN202010375531.4A CN202010375531A CN111366295A CN 111366295 A CN111366295 A CN 111366295A CN 202010375531 A CN202010375531 A CN 202010375531A CN 111366295 A CN111366295 A CN 111366295A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L23/00—Devices or apparatus for measuring or indicating or recording rapid changes, such as oscillations, in the pressure of steam, gas, or liquid; Indicators for determining work or energy of steam, internal-combustion, or other fluid-pressure engines from the condition of the working fluid
- G01L23/08—Devices or apparatus for measuring or indicating or recording rapid changes, such as oscillations, in the pressure of steam, gas, or liquid; Indicators for determining work or energy of steam, internal-combustion, or other fluid-pressure engines from the condition of the working fluid operated electrically
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L19/00—Details of, or accessories for, apparatus for measuring steady or quasi-steady pressure of a fluent medium insofar as such details or accessories are not special to particular types of pressure gauges
- G01L19/06—Means for preventing overload or deleterious influence of the measured medium on the measuring device or vice versa
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Abstract
The invention belongs to the technical field of supersonic flow field pressure testing, and particularly relates to a supersonic steady-state pressure probe for reducing support rod interference by utilizing plasma jet. The head of the probe is a steady-state pressure probe and is welded with the probe supporting rod; the pressure guiding pipe is packaged in the probe supporting rod, one end of the pressure guiding pipe is communicated with the pressure measuring hole at the head of the probe, and the other end of the pressure guiding pipe is led out from the tail of the probe supporting rod; the probe support rod comprises two mutually independent structures: a pressure leading pipe channel and a plasma generating cavity; the high-voltage trigger electrode, the anode and the cathode are arranged in the plasma generating cavity; the plasma generating cavity is provided with a contraction-shaped jet flow groove which is communicated with the lower stream of the probe supporting rod. The invention obviously enhances the control effect on the fluid around the supersonic pressure probe supporting rod by generating plasma in the plasma generating cavity in the supporting rod and generating air blowing and air suction effects around the probe supporting rod through the jet flow groove, can effectively weaken the blocking effect of the probe supporting rod and reduce the interference of the supporting rod on the measured flow field.
Description
Technical Field
The invention belongs to the technical field of flow field pressure testing, and particularly relates to a supersonic steady-state pressure probe for reducing support rod interference by utilizing plasma jet, which is suitable for measuring pressure in a supersonic steady-state flow field in an impeller machine.
Background
In the current measurement of supersonic steady-state flow fields at the inlet and the interstage of the impeller machine, performance parameters which are generally required to be obtained comprise total pressure, static pressure, Mach number, airflow angle and the like in order to know the characteristics of the flow field, and a contact type pressure probe is low in price, easy to implement and stable and reliable in measurement, so that the contact type pressure probe is always an important means for testing the supersonic flow field.
However, the contact pressure probe needs to be supported by a support rod when being inserted into a measured flow field for measurement, and as the Mach number of the supersonic flow field is more than 1.2 and even higher, and the aerodynamic resistance generated by the support rod is in direct proportion to the square of the speed, the blocking effect of the probe support rod in the supersonic flow field inevitably generates larger interference on the measured flow field, so that the increase of flow mixing loss, the reduction of component performance and even the influence on the normal operation of components are caused. Especially when the pressure probe is measured in a small compressor, the clogging effect is more severe and even causes the occurrence of stall surge. When the pressure probe is measured in a measured flow field with high Mach number, shock waves formed by incoming flow in front of a pressure probe support rod can change air flow parameters near the probe, and obvious three-dimensional unsteady trails can be generated behind the pressure probe support rod and can be propagated downstream along with the movement of impeller machinery, and even the upstream flow field can be influenced.
In the existing probe test technology, the influence problem of the probe support on the flow field is generally reduced by optimizing the size and the structure of the probe support so as to reduce the interference on the measured flow field. On one hand, the size of the probe supporting rod cannot be further reduced because the supersonic airflow can generate strong aerodynamic force on the probe supporting rod and is limited by the structural strength; on the other hand, the interference problem of the flow field of the traditional supersonic probe strut structure after the design is optimized is not obviously improved, and the conventional active control method cannot be applied to flow control of the supersonic flow field.
The problem of influence of the probe support rods on the measured flow field restricts deep research of researchers on the flow field in the impeller machine, and the requirement that parameter information such as pressure, Mach number and the like in the flow field is accurately obtained while interference on the measured flow field is generated as small as possible is difficult to meet. Therefore, a supersonic steady-state pressure probe for reducing strut interference by using plasma jet is urgently needed, and is used for measuring the pressure in supersonic steady-state flow fields of inlets and stages of supersonic air inlets, air compressors, turbines and the like in impeller machinery.
Disclosure of Invention
The invention provides a supersonic steady-state pressure probe for reducing the interference of a strut by utilizing plasma jet, aiming at the problem that the prior pressure probe generates the interference and the blocking effect on a measured flow field when measuring the parameters such as total pressure, static pressure, Mach number, airflow angle and the like of the supersonic steady-state flow field. Most importantly, the invention abandons the design thought of the traditional pressure probe supporting rod and the defect of low gas flow velocity induced by the traditional plasma generator, creatively applies the plasma to the design of the supersonic speed probe supporting rod, and makes up the defects of the traditional supersonic speed steady-state pressure probe in the flow field measurement.
The technical scheme of the invention is as follows:
1. the utility model provides an utilize plasma jet to reduce supersonic speed steady state pressure probe that branch disturbed, by probe branch (1), probe head (2), jet current groove (3), draw and press pipe (4), draw and press pipe passageway (5), plasma generation chamber (6), high pressure trigger electrode (7), positive pole (8), negative pole (9), tip thermal insulation insulating layer (10), lateral wall thermal insulation insulating layer (11), electrode extraction cable (12) are constituteed, its characterized in that: the probe head (2) is a stable pressure probe and is welded with the probe support rod (1); the pressure guiding pipe (4) is packaged in the probe supporting rod (1), one end of the pressure guiding pipe is communicated with the pressure measuring hole of the probe head part (2), and the other end of the pressure guiding pipe is led out from the tail part of the probe supporting rod (1); the probe support rod (1) comprises two mutually independent structures: a pressure leading pipe passage (5) and a plasma generating cavity (6); the high-voltage trigger electrode (7), the anode (8) and the cathode (9) are arranged in the plasma generation cavity (6), and the electrode lead-out cable (12) is led out from the tail part of the probe supporting rod (1); the plasma generating cavity (6) is provided with a contraction-shaped jet flow groove (3) which is communicated with the downstream of the probe supporting rod (1).
2. Furthermore, the probe head part (2) is wedge-shaped, the included angle of two side surfaces of the probe head part is 30-65 degrees, the length of the probe head part is 5-45 millimeters, and the probe head part can be a pressure probe with a single hole, three holes, four holes, five holes, seven holes and the like.
3. Furthermore, the front half part of the probe supporting rod (1) is in a wedge shape, and the included angle of two side surfaces of the probe supporting rod is 35-70 degrees; the latter half is semicircular, and the diameter is 3 mm-16 mm.
4. Furthermore, the inner wall of the plasma generation cavity (6) is cylindrical, the axis of the plasma generation cavity is parallel to the axis of a rear semicircle of the probe supporting rod (1), the diameter of the section of the plasma generation cavity is 2-6 mm, and the distance between the circle center of the plasma generation cavity and the circle center of the rear semicircle of the probe supporting rod (1) is 0-3 mm; the distance between the lower end of the plasma generating cavity (6) and the top end of the probe supporting rod (1) is 0.1-2 mm, and the height is determined according to the depth of the probe extending into a measured flow field.
5. Furthermore, the exhaust direction of the jet flow groove (3) is parallel to the main flow direction and is in a contraction shape along the exhaust direction, and the contraction type line can be a straight line, a Vickers curve, a bicubic curve and the like; the width of the outlet of the jet flow groove (3) is 0.2 mm-4 mm, and the length of the jet flow groove (3) is the same as the height of the plasma generation cavity (6).
6. Furthermore, the upper and lower ends of the high-voltage trigger electrode (7), the anode (8) and the cathode (9) are fixed in the plasma generation cavity (6) by an end heat insulation layer (10) to play roles of heat insulation, sealing and fixation; the probe supporting rod (1) is separated by a side wall heat insulation layer (11) to play a role in heat insulation and insulation.
7. Furthermore, the diameter of the high-voltage trigger electrode (7), the diameter of the anode (8) and the diameter of the cathode (9) are 0.5-1.5 mm, the distance between the high-voltage trigger electrode (7) and the cathode (9) is 0.2-1 mm, the distance between the high-voltage trigger electrode (7) and the cathode (9) is smaller than the distance between the anode (8) and the cathode (9), and the high-voltage trigger electrode is made of cerium-tungsten alloy, titanium alloy or stainless steel.
8. Further, a power supply required by the high-voltage trigger electrode (7) is a high-voltage pulse power supply, and the voltage is 1 kV-20 kV; the power supply required by the anode (8) is a direct current power supply, and the voltage is 300-800V.
9. Further, calibrating the probe through a supersonic calibration wind tunnel to obtain the aerodynamic calibration coefficients of the probe in different incoming flow directions and different Mach numbers, and determining the conditions of voltage, pulse parameters and the like of a power supply required by plasma generation under the conditions of known incoming flow pressure, direction and Mach number; in actual measurement, the total pressure, the static pressure, the Mach number and the airflow angle of a measured flow field are calculated by utilizing the probe pneumatic calibration coefficients of the supersonic calibration wind tunnel in different incoming flow directions and different Mach numbers, the conditions of voltage, pulse parameters and the like of a power supply required by plasma generation are set according to the obtained total pressure, static pressure, Mach number and airflow angle, the generation amount and the jet flow of the plasma are controlled, and the jet flow groove (3) generates blowing and suction actions around the probe supporting rod (1), so that the control effect on the fluid around the supersonic pressure probe supporting rod (1) is obviously enhanced, the blocking effect of the probe supporting rod (1) can be effectively weakened, and the interference of the probe supporting rod (1) on the measured flow field is reduced.
The invention has the beneficial effects that:
compared with the conventional supersonic steady-state flow field pressure probe, the supersonic steady-state pressure probe for reducing the interference of the support rod by using the plasma jet can achieve the following beneficial effects:
the beneficial effects are that: the invention obviously enhances the control effect on the fluid around the supersonic pressure probe supporting rod by generating plasma in the plasma generating cavity in the supporting rod and generating air blowing and air suction effects around the probe supporting rod through the jet flow groove, and can effectively reduce the interference and blockage effects of the probe supporting rod on the measured flow field.
The beneficial effects are that: the jet velocity of the plasma is realized by controlling the voltage and pulse parameters of different electrodes, and the power supply can be regulated and controlled according to the incoming flow Mach number and Reynolds number of the measured flow field, so that the generation of the plasma is controlled, and the optimal control effect on the fluid around the probe supporting rod is achieved. Compared with other control methods, the plasma jet does not need additional moving parts and gas source pipelines, and is a zero-mass control mode with light mass, quick response and simple structure.
The beneficial effects are three: the induction speed generated by the traditional plasma is not more than 10m/s, and the method can not be applied to the active control of supersonic airflow.
Drawings
FIG. 1 is a schematic diagram of a supersonic steady-state pressure probe with a plasma jet to reduce strut interference, according to an embodiment of the present invention.
FIG. 2 is a left side view of FIG. 1
Fig. 3 is a partially enlarged view of fig. 1.
Fig. 4 is a cross-sectional view of fig. 1.
Fig. 5 is a view from direction B of fig. 1.
FIG. 6 is a schematic structural diagram of a supersonic steady-state pressure probe for reducing strut interference using a plasma jet according to a second embodiment of the present invention.
FIG. 7 is a left side view of FIG. 6
Fig. 8 is a cross-sectional view of fig. 6.
Fig. 9 is a view from direction B of fig. 6.
Wherein: 1-probe supporting rod, 2-probe head, 3-jet flow groove, 4-pressure leading pipe, 5-pressure leading pipe channel, 6-plasma generating cavity, 7-high voltage trigger electrode, 8-anode, 9-cathode, 10-end heat insulation layer, 11-side wall heat insulation layer and 12-electrode leading-out cable.
Detailed Description
The following detailed description of the preferred embodiments of the present invention, taken in conjunction with the accompanying drawings, will make the advantages and features of the invention easier to understand by those skilled in the art, and thus will clearly and clearly define the scope of the invention.
The first embodiment is as follows:
for the measurement of the compressor interstage supersonic three-dimensional flow field, the measurement space is narrow, the incoming flow three-dimensional performance is strong, and in order to ensure the spatial resolution and the fine measurement, the following implementation mode can be adopted:
referring to FIGS. 1-5, a supersonic steady-state pressure probe for reducing strut interference using plasma jet is disclosed. By probe branch (1), probe head (2), jet current groove (3), draw and press pipe (4), draw and press pipe passageway (5), plasma generation chamber (6), high pressure trigger electrode (7), positive pole (8), negative pole (9), tip thermal insulation insulating layer (10), lateral wall thermal insulation insulating layer (11), electrode lead out cable (12) and constitute, its characterized in that: the probe head (2) is a stable pressure probe and is welded with the probe support rod (1); the pressure guiding pipe (4) is packaged in the probe supporting rod (1), one end of the pressure guiding pipe is communicated with the pressure measuring hole of the probe head part (2), and the other end of the pressure guiding pipe is led out from the tail part of the probe supporting rod (1); the probe support rod (1) comprises two mutually independent structures: a pressure leading pipe passage (5) and a plasma generating cavity (6); the high-voltage trigger electrode (7), the anode (8) and the cathode (9) are arranged in the plasma generation cavity (6), and the electrode lead-out cable (12) is led out from the tail part of the probe supporting rod (1); the plasma generating cavity (6) is provided with a contraction-shaped jet flow groove (3) which is communicated with the downstream of the probe supporting rod (1).
In this embodiment, the probe head (2) is a wedge-shaped four-hole pressure probe, and the included angle between the two side surfaces of the probe head is 37 degrees, and the length of the probe head is 30 mm.
The front half part of the probe supporting rod (1) is in a wedge shape, and the included angle of two side surfaces of the probe supporting rod is 42 degrees; the latter half is semicircular and has a diameter of 8 mm.
The inner wall of the plasma generation cavity (6) is cylindrical, the axis is parallel to the axis of the rear semicircle of the probe supporting rod (1), the diameter of the section is 4 mm, and the distance between the circle center of the plasma generation cavity and the circle center of the rear semicircle of the probe supporting rod (1) is 1.5 mm; the distance between the lower end of the plasma generating cavity (6) and the top end of the probe supporting rod (1) is 2 mm.
The exhaust direction of the jet flow groove (3) is parallel to the main flow direction and is in a contraction shape along the exhaust direction, the contraction molded line is a straight line, and the included angle between the molded line and the main flow direction is 40 degrees; the width of the outlet of the jet flow groove (3) is 0.4 mm, and the length of the jet flow groove (3) is the same as the height of the plasma generation cavity (6).
The upper and lower ends of the high-voltage trigger electrode (7), the anode (8) and the cathode (9) are fixed in the plasma generating cavity (6) by an end heat insulation layer (10) to play roles of heat insulation, sealing and fixation; the probe supporting rod (1) is separated by a side wall heat insulation layer (11) to play a role in heat insulation and insulation.
The diameters of the high-voltage trigger electrode (7), the anode (8) and the cathode (9) are all 0.8 mm, the distance between the high-voltage trigger electrode (7) and the cathode (9) is 0.4 mm, the distance between the anode (8) and the cathode (9) is 0.8 mm, and the materials are cerium-tungsten alloy.
The power supply required by the high-voltage trigger electrode (7) is a high-voltage pulse power supply, and the voltage is 3 kV; the power supply required by the anode (8) is a direct current power supply, and the voltage is 520V.
Calibrating the probe through a supersonic calibration wind tunnel to obtain the aerodynamic calibration coefficients of the probe in different incoming flow directions and different Mach numbers, and determining the conditions such as voltage, pulse parameters and the like of a power supply required by plasma generation under the conditions of known incoming flow pressure, direction and Mach number; in actual measurement, the total pressure, the static pressure, the Mach number, the airflow deflection angle and the airflow pitch angle of a measured flow field are calculated by utilizing the probe pneumatic calibration coefficients of different incoming flow directions and different Mach numbers obtained by the supersonic calibration wind tunnel, the total pressure, the static pressure, the Mach number, the airflow deflection angle and the airflow pitch angle are obtained according to the total pressure, the static pressure, the Mach number, the airflow deflection angle and the airflow pitch angle, the conditions of voltage, pulse parameters and the like of a power supply required by plasma generation are set, the generation amount and the jet flow of the plasma are controlled, blowing and suction effects are generated around the probe supporting rod (1) through the jet flow groove (3), the control effect on fluid around the supersonic pressure probe supporting rod (1) is obviously enhanced, the blocking effect of the probe supporting rod (1) can be effectively weakened, and the interference.
Example two:
in order to obtain the total pressure, static pressure and Mach number parameters of the inlet of the compressor, the following implementation modes are selected to measure the two-dimensional flow field of the outlet on the premise of ensuring the structural strength of the probe supporting rod:
referring to FIGS. 6-9, a supersonic steady-state pressure probe for reducing strut interference using plasma jet according to the present invention is shown. By probe branch (1), probe head (2), jet current groove (3), draw and press pipe (4), draw and press pipe passageway (5), plasma generation chamber (6), high pressure trigger electrode (7), positive pole (8), negative pole (9), tip thermal insulation insulating layer (10), lateral wall thermal insulation insulating layer (11), electrode lead out cable (12) and constitute, its characterized in that: the probe head (2) is a stable pressure probe and is welded with the probe support rod (1); the pressure guiding pipe (4) is packaged in the probe supporting rod (1), one end of the pressure guiding pipe is communicated with the pressure measuring hole of the probe head part (2), and the other end of the pressure guiding pipe is led out from the tail part of the probe supporting rod (1); the probe support rod (1) comprises two mutually independent structures: a pressure leading pipe passage (5) and a plasma generating cavity (6); the high-voltage trigger electrode (7), the anode (8) and the cathode (9) are arranged in the plasma generation cavity (6), and the electrode lead-out cable (12) is led out from the tail part of the probe supporting rod (1); the plasma generating cavity (6) is provided with a contraction-shaped jet flow groove (3) which is communicated with the downstream of the probe supporting rod (1).
In this embodiment, the probe head (2) is a wedge-shaped three-hole pressure probe, the included angle between the two side surfaces of the probe is 40 degrees, and the length of the probe is 25 millimeters.
The front half part of the probe supporting rod (1) is in a wedge shape, and the included angle of two side surfaces of the probe supporting rod is 45 degrees; the latter half is semicircular and has a diameter of 6 mm.
The inner wall of the plasma generation cavity (6) is cylindrical, the axis is parallel to the axis of the rear semicircle of the probe supporting rod (1), the diameter of the section is 3 mm, and the distance between the circle center of the plasma generation cavity and the circle center of the rear semicircle of the probe supporting rod (1) is 1.5 mm; the distance between the lower end of the plasma generating cavity (6) and the top end of the probe supporting rod (1) is 2 mm.
The exhaust direction of the jet flow groove (3) is parallel to the main flow direction and is in a contraction shape along the exhaust direction, and the contraction molded line is a Vickers curve; the width of the outlet of the jet flow groove (3) is 0.5 mm, and the length of the jet flow groove (3) is the same as the height of the plasma generation cavity (6).
The upper and lower ends of the high-voltage trigger electrode (7), the anode (8) and the cathode (9) are fixed in the plasma generating cavity (6) by an end heat insulation layer (10) to play roles of heat insulation, sealing and fixation; the probe supporting rod (1) is separated by a side wall heat insulation layer (11) to play a role in heat insulation and insulation.
The diameters of the high-voltage trigger electrode (7), the anode (8) and the cathode (9) are all 0.6 mm, the distance between the high-voltage trigger electrode (7) and the cathode (9) is 0.3 mm, the distance between the anode (8) and the cathode (9) is 0.72 mm, and the materials are cerium-tungsten alloy.
The power supply required by the high-voltage trigger electrode (7) is a high-voltage pulse power supply, and the voltage is 2.8 kV; the power supply required by the anode (8) is a direct current power supply, and the voltage is 470V.
Calibrating the probe through a supersonic calibration wind tunnel to obtain the aerodynamic calibration coefficients of the probe in different incoming flow directions and different Mach numbers, and determining the conditions such as voltage, pulse parameters and the like of a power supply required by plasma generation under the conditions of known incoming flow pressure, direction and Mach number; in actual measurement, the total pressure, the static pressure, the Mach number and the airflow deflection angle of a measured flow field are calculated by utilizing the probe pneumatic calibration coefficients of different incoming flow directions and different Mach numbers obtained by the supersonic calibration wind tunnel, the conditions of voltage, pulse parameters and the like of a power supply required by plasma generation are set according to the obtained total pressure, static pressure, Mach number and airflow deflection angle, the generation amount and the jet flow of the plasma are controlled, and the blowing and suction effects are generated around the probe supporting rod (1) through the jet flow groove (3), so that the control effect on the fluid around the supersonic pressure probe supporting rod (1) is obviously enhanced, the blocking effect of the probe supporting rod (1) can be effectively weakened, and the interference of the probe supporting rod (1) on the measured flow field is reduced.
Claims (1)
1. The utility model provides an utilize plasma jet to reduce supersonic speed steady state pressure probe that branch disturbed, by probe branch (1), probe head (2), jet current groove (3), draw and press pipe (4), draw and press pipe passageway (5), plasma generation chamber (6), high pressure trigger electrode (7), positive pole (8), negative pole (9), tip thermal insulation insulating layer (10), lateral wall thermal insulation insulating layer (11), electrode extraction cable (12) are constituteed, its characterized in that: the probe head (2) is a stable pressure probe and is welded with the probe support rod (1); the pressure guiding pipe (4) is packaged in the probe supporting rod (1), one end of the pressure guiding pipe is communicated with the pressure measuring hole of the probe head part (2), and the other end of the pressure guiding pipe is led out from the tail part of the probe supporting rod (1); the probe support rod (1) comprises two mutually independent structures: a pressure leading pipe passage (5) and a plasma generating cavity (6); the high-voltage trigger electrode (7), the anode (8) and the cathode (9) are arranged in the plasma generation cavity (6), and the electrode lead-out cable (12) is led out from the tail part of the probe supporting rod (1); the plasma generating cavity (6) is provided with a contraction-shaped jet flow groove (3) which is communicated with the downstream of the probe supporting rod (1);
the probe head (2) is wedge-shaped, the included angle of two side surfaces of the probe head is 30-65 degrees, the length of the probe head is 5-45 millimeters, and the probe head can be a pressure probe with a single hole, three holes, four holes, five holes, seven holes and the like;
the front half part of the probe supporting rod (1) is in a wedge shape, and the included angle of two side surfaces of the probe supporting rod is 35-70 degrees; the rear half part is a semicircle with the diameter of 3 mm-16 mm;
the inner wall of the plasma generation cavity (6) is cylindrical, the axis is parallel to the axis of the rear semicircle of the probe supporting rod (1), the diameter of the section is 2-6 mm, and the distance between the circle center of the plasma generation cavity and the circle center of the rear semicircle of the probe supporting rod (1) is 0-3 mm; the distance between the lower end of the plasma generating cavity (6) and the top end of the probe supporting rod (1) is 0.1-2 mm, and the height is determined according to the depth of the probe extending into a measured flow field;
the exhaust direction of the jet flow groove (3) is parallel to the main flow direction and is in a contraction shape along the exhaust direction, and the contraction type line can be a straight line, a Vickers curve, a bicubic curve and the like; the width of the outlet of the jet flow groove (3) is 0.2 mm-4 mm, and the length of the jet flow groove (3) is the same as the height of the plasma generation cavity (6);
the upper and lower ends of the high-voltage trigger electrode (7), the anode (8) and the cathode (9) are fixed in the plasma generating cavity (6) by an end heat insulation layer (10) to play roles of heat insulation, sealing and fixation; the probe supporting rod (1) is separated by a side wall heat insulation layer (11) to play a role in heat insulation and insulation;
the diameters of the high-voltage trigger electrode (7), the anode (8) and the cathode (9) are 0.5-1.5 mm, the distance is 0.2-1 mm, the distance between the high-voltage trigger electrode (7) and the cathode (9) is smaller than the distance between the anode (8) and the cathode (9), and the materials are cerium-tungsten alloy, titanium alloy or stainless steel and the like;
the power supply required by the high-voltage trigger electrode (7) is a high-voltage pulse power supply, and the voltage is 1 kV-20 kV; the power supply required by the anode (8) is a direct current power supply, and the voltage is 300-800V;
calibrating the probe through a supersonic calibration wind tunnel to obtain the aerodynamic calibration coefficients of the probe in different incoming flow directions and different Mach numbers, and determining the conditions such as voltage, pulse parameters and the like of a power supply required by plasma generation under the conditions of known incoming flow pressure, direction and Mach number; in actual measurement, the total pressure, the static pressure, the Mach number and the airflow angle of a measured flow field are calculated by utilizing the probe pneumatic calibration coefficients of the supersonic calibration wind tunnel in different incoming flow directions and different Mach numbers, the conditions of voltage, pulse parameters and the like of a power supply required by plasma generation are set according to the obtained total pressure, static pressure, Mach number and airflow angle, the generation amount and the jet flow of the plasma are controlled, and the jet flow groove (3) generates blowing and suction actions around the probe supporting rod (1), so that the control effect on the fluid around the supersonic pressure probe supporting rod (1) is obviously enhanced, the blocking effect of the probe supporting rod (1) can be effectively weakened, and the interference of the probe supporting rod (1) on the measured flow field is reduced.
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| CN202010375531.4A CN111366295A (en) | 2020-05-07 | 2020-05-07 | Supersonic steady-state pressure probe for reducing strut interference by utilizing plasma jet |
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| CN202010375531.4A CN111366295A (en) | 2020-05-07 | 2020-05-07 | Supersonic steady-state pressure probe for reducing strut interference by utilizing plasma jet |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113340561A (en) * | 2021-08-02 | 2021-09-03 | 中国空气动力研究与发展中心空天技术研究所 | Eccentric cylindrical single-hole pneumatic probe for measuring precision in high altitude |
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2020
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113340561A (en) * | 2021-08-02 | 2021-09-03 | 中国空气动力研究与发展中心空天技术研究所 | Eccentric cylindrical single-hole pneumatic probe for measuring precision in high altitude |
| CN113340561B (en) * | 2021-08-02 | 2021-10-29 | 中国空气动力研究与发展中心空天技术研究所 | Eccentric cylindrical single-hole pneumatic probe for measuring precision in high altitude |
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