CN115435930B - Using method of high-frequency probe for measuring three-dimensional full parameters between stages - Google Patents
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- 239000000523 sample Substances 0.000 title claims abstract description 181
- 238000000034 method Methods 0.000 title claims abstract description 37
- 239000007921 spray Substances 0.000 claims abstract description 26
- 230000003068 static effect Effects 0.000 claims description 23
- 230000008859 change Effects 0.000 claims description 15
- 238000010438 heat treatment Methods 0.000 claims description 13
- 239000003292 glue Substances 0.000 claims description 8
- 230000000087 stabilizing effect Effects 0.000 claims description 8
- 230000008569 process Effects 0.000 claims description 7
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 claims description 7
- 230000007704 transition Effects 0.000 claims description 4
- 239000000463 material Substances 0.000 claims description 3
- BASFCYQUMIYNBI-UHFFFAOYSA-N platinum Chemical compound [Pt] BASFCYQUMIYNBI-UHFFFAOYSA-N 0.000 claims description 3
- 238000011088 calibration curve Methods 0.000 claims description 2
- 238000000605 extraction Methods 0.000 claims description 2
- 238000005086 pumping Methods 0.000 claims description 2
- 230000004044 response Effects 0.000 description 11
- 238000005259 measurement Methods 0.000 description 9
- 230000009286 beneficial effect Effects 0.000 description 7
- 238000009529 body temperature measurement Methods 0.000 description 4
- 239000012530 fluid Substances 0.000 description 2
- 238000009530 blood pressure measurement Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 230000035945 sensitivity Effects 0.000 description 1
- 230000036962 time dependent Effects 0.000 description 1
Abstract
The invention belongs to the technical field of dynamic testing of high-frequency flow fields, and particularly relates to a use method of a three-dimensional full-parameter high-frequency probe for measuring an interstage. The probe head is of a 'runway-shaped' cylinder structure, a sound speed spray pipe is arranged on the opposite incoming flow surface of the cylinder, two fork rods are distributed up and down on the sound speed spray pipe, a hot wire is welded on the fork rods, a pressure sensing hole is arranged below the sound speed spray pipe, the pressure sensing hole is connected with a pressure sensor, a back cover of the probe head opposite to the spray pipe is arranged on the leeward side of the probe head, a vacuum pump nozzle is arranged near the tail of a probe support rod, and the tail of the probe support rod is connected with an aviation plug.
Description
Technical Field
The method belongs to the technical field of dynamic testing of high-frequency flow fields, and particularly relates to a use method of an inter-stage three-dimensional full-parameter high-frequency probe, which is suitable for measuring the change of full parameters such as total temperature, total pressure, static temperature, mach number, deflection angle, pitch angle, speed, density, entropy and the like in the flow fields along with time, wherein the frequency response of the probe can reach more than 50 kHz.
Background
The accurate measurement of aerodynamic performance parameters of compressor and turbine inter-stage flow is still an important engineering problem in the field of aeroengines. The flow characteristics between the compressor and the turbine are strong three-dimensional property, compressibility, instability and strong unsteadiness, the passing frequency of the blade reaches more than 10kHz, and the corresponding temperature field and pressure field are also dynamically changed at high frequency, so that the time-dependent change of the temperature and the pressure between the compressor and the turbine is difficult to accurately obtain. Therefore, in order to accurately obtain the dynamic pressure field and the dynamic temperature field between the compressor and the turbine, it is necessary to develop high-frequency dynamic pressure and temperature measurement means.
At present, a thermocouple and a thermal resistor are commonly adopted to obtain the dynamic temperature of a flow field, a high-frequency dynamic pressure probe is adopted to measure the dynamic pressure of the flow field, and a porous pressure probe is used to measure the direction of air flow. The frequency response of the existing dynamic pressure sensor can meet the measurement requirement of the compressor/turbine stage, the frequency response of the existing temperature sensor is low, even if the filament thermocouple temperature sensor with the highest frequency response is different from 10kHz by two orders of magnitude, the conventional temperature sensor is very difficult to measure the unsteady temperature field of the compressor/turbine stage.
The air suction type hot wire and dynamic pressure sensor combination probe obtains the total temperature through the relation between the total temperature and other parameters, and the measurement means is an effective attempt for improving the dynamic temperature measurement frequency. The probe consists of an air suction channel embedded with a hot wire and a dynamic pressure sensor, and the temperature measurement frequency response of the probe can reach 10kHz. The principle is that a heating wire is placed in front of a sonic nozzle, and the nozzle is in a choked state by air suction, so that a relation between the output voltage of a bridge where the heating wire is positioned and the total temperature and total pressure of air flow is obtained:
And then the dynamic total pressure of the air flow is obtained through the high-frequency pressure sensor, so that the total temperature of the air flow is deduced.
The invention discloses a dynamic entropy probe, which firstly uses two dynamic pressure sensors to measure total pressure and static pressure, and the relation between the total pressure, the static pressure and the Ma number is adopted:
And the mach number is obtained. Yankee considers the hot film voltage as a function of fluid velocity and air flow temperature, and then substitutes the velocity (mach number) obtained in the previous step into the function:
E2＝[A+B(ρU)n](Tw-rTT)
The total temperature of the air flow can be calculated.
The existing combined probe of the air suction type hot wire and the dynamic pressure sensor and the dynamic entropy probe have some defects although the fluctuation of the local total temperature and the total pressure can be measured at the same time. Firstly, the probes are designed according to the requirement of the main flow, but the pitch angle and the deflection angle of the air flow cannot be measured, and the air flow direction needs to be obtained in advance when the probes are used. Secondly, the existing probe has smaller insensitive angle, and when the deflection angle or pitch angle of the measured flow field exceeds 20 degrees, the measurement result can generate a very large error. Third, the heat-wire is placed inside the probe, and the flow field parameters felt by the heat-wire may be different from the real flow field, especially for dynamic measurement of high frequency response. Fourth, the probes are either "L" shaped or "one" shaped, which cannot be used for inter-stage flow field measurements because of the limited inter-stage width, which interferes with the blades. The "L" probe also has difficulty reaching narrow compressor or turbine stages. Fifth, the probe has a limited frequency response, and cannot capture a higher frequency signal, and the existing probe has a maximum frequency response of only 10kHz, and cannot measure a higher frequency temperature and pressure change. Sixth, the dynamic entropy probe described above can only measure incompressible flow fields, since its inventor believes that the hot film voltage is only related to fluid velocity and air flow temperature, the density ρ is assumed to be constant, which is the case for incompressible flow fields only.
Therefore, development of a use method for measuring the three-dimensional full-parameter high-frequency probe of the interstage is urgently needed to accurately measure the dynamic changes of full parameters such as total temperature, total pressure, static temperature, static pressure, mach number, deflection angle, pitch angle, speed, density, entropy and the like of the three-dimensional flow field of the interstage.
Disclosure of Invention
The use method of the three-dimensional full-parameter high-frequency probe for measuring the interstage is characterized in that the head of the probe is of a 'racetrack-shaped' cylinder structure, the top end of the probe is in arc smooth transition, a sonic nozzle is arranged at the arc part of the side face of the cylinder, two fork rods are distributed up and down on the sonic nozzle, a hot wire is welded on the sonic nozzle, the hot wire is parallel to or at a certain angle with the axis of the probe, a pressure sensing hole is formed below the sonic nozzle, the pressure sensing hole is connected with a pressure sensor, a probe rear cover is formed on the leeward side of the probe head of the back-facing nozzle, a vacuum pump nozzle is formed on the leeward side close to the tail of the probe support rod, and the tail of the probe support rod is connected with an aviation plug. The principle of measuring the total temperature is the same as that of the suction type hot wire and dynamic pressure sensor probe. When the ultrasonic jet nozzle is used, the vacuum pump nozzle is connected with the vacuum pump for exhausting, so that the back pressure of the jet pipe is lower than the total pressure of incoming flow, the sound velocity of the throat of the sonic jet pipe is reached, and the whole jet pipe reaches a choked state. At this time, the hot wire voltage is only a function of the total incoming flow temperature and total pressure, is irrelevant to the air flow speed, and meanwhile, the total incoming flow pressure parameter is obtained by combining the pressure sensor, so that the total air flow temperature is deduced.
On the basis, the method can also measure the incoming flow pitch angle, deflection angle and static pressure, and calculate the flow static temperature, speed, density and entropy. The principle is that for an infinitely long hot wire, its sensitivity to angle can be described as:
Veff＝V cosα1
where V eff is the effective cooling rate felt by the hot wire and α1 is the pitch angle of the probe, as shown in fig. 6. For the method, 2l/d is more than or equal to 500, and the method can be regarded as an infinitely long hot line in actual use. When the pitch angle is measured, the probe is not pumped, and then the pitch angle of the probe is adjusted, so that the pitch angle of incoming flow can be obtained. Meanwhile, the total pressure, the static pressure and the deflection angle of the air flow can be measured through the pressure sensing holes and the pressure sensors, and the principle is the same as that of a single-hole pressure probe. From the measured parameters of total temperature, total pressure, static pressure, pitch angle, deflection angle, etc., all parameters of the air flow such as static temperature, speed, density, entropy, etc. can be deduced.
When the method is used, the total pressure, the static pressure and the deflection angle of the airflow can be measured through the pressure sensor, after the airflow direction is determined, the probe is adjusted to be opposite to the main flow, and then the dynamic change of the incoming flow temperature is measured through air suction. The probe used in the method is I-shaped, has small size and is suitable for narrow inter-stage measurement. The sonic nozzle is arranged at the arc part of the side surface of the probe head cylinder, the heat wire firstly senses the change of incoming flow, the flow field information is not distorted, and the probe cannot be influenced. The sonic jet pipe molded line uses a Veduo-octyl curve, so that the jet pipe flows more uniformly, and the flow at the plane of the hot wire is not influenced. The hot wire can use 5 mu m gold-plated tungsten wire, and can reach the frequency response of more than 50kHz by matching with the latest CTA (constant temperature hot wire anemometer) module.
The application method of the three-dimensional full-parameter high-frequency probe for measuring the interstage is provided, and the technical problem to be solved is that: first, the problem that the air current pitch angle and deflection angle can not be measured by the original suction type hot wire and dynamic pressure sensor probe is solved. Secondly, the problem that the existing probe is small in insensitive angle, and when the pitch angle and the deflection angle of a measured flow field exceed 20 degrees, a very large error is generated in a measurement result is solved. Thirdly, the problem that probes of the original L-shaped structure and the original one-shaped structure are difficult to extend into a narrow compressor or turbine interstage for measurement is solved. Fourth, the problem that the flow field parameters sensed by the hot wires placed in the probe are different from the real flow field is solved. Fifth, the problem of low frequency response of the existing temperature probe is solved.
The technical proposal of the method is as follows:
1. The utility model provides a measure application method of three-dimensional full parameter high frequency probe between stages, by probe head (1), probe branch (2), hot wire (3), fork arm (4), sonic nozzle (5), cylindrical stable section (6), probe back lid (7), hot wire cable (8), vacuum pump connects mouth (9), aviation plug (10), probe head through-hole (11), insulating glue (12), circular pipeline (13), pressure sensing hole (14), pressure sensor (15), pressure sensor cable (16), pressure sensor passageway (17) are constituteed, its characterized in that: the probe head (1) is of a 'runway-shaped' cylinder structure, a cross section line of the probe head is composed of two equal-diameter semicircles and a rectangle, the top end of the probe head (1) is in arc smooth transition, a sound speed spray pipe (5) is arranged on the opposite incoming flow surface of the cylinder, two fork rods (4) are distributed up and down on the sound speed spray pipe, a heating wire (3) is welded on the sound speed spray pipe, a pressure sensing hole (14) is arranged below the sound speed spray pipe (5), the pressure sensing hole (14) is connected with a pressure sensor (15), a probe rear cover (7) is arranged on the lee side of the probe head (1) opposite to the spray pipe, a vacuum pump nozzle (9) is arranged near the tail of the probe support rod, and the tail of the probe support rod is connected with an aviation plug (10).
2. The diameter D of the two semi-circles of the probe head (1) is 2-8 mm, the width of the rectangular part is the same as the diameter of the semi-circles, the length is 0.5-3D, a circular pipeline (13) is axially arranged inside the probe head, and the diameter of the circular pipeline (13) is 1-7 mm.
3. The circular arc part on the side surface of the probe head part (1) is provided with a sonic nozzle (5), the contracted molded line of the nozzle can be a straight line, a Vitoxinyl curve or a lemniscate, the projected cross-sectional diameter of the nozzle inlet vertical to the axis of the probe head part (1) is 0.8-3 mm, the projected cross-sectional diameter of the nozzle outlet vertical to the axis of the probe head part (1) is 0.4-2 mm, the distance between the nozzle center line and the top end of the probe head part (1) is 2-8 mm, the sonic nozzle (5) is connected with a circular pipeline (13) through a cylindrical stabilizing section (6), the diameter of the cylindrical stabilizing section (6) is the same as the projected cross-sectional diameter of the nozzle inlet vertical to the axis of the probe head part (1), the leeward side opposite to the nozzle is provided with a probe rear cover (7), the cross-section of the nozzle is a fan ring, the fan ring central angle is 45-90 DEG, the length of the probe rear cover (7) is 2-8 mm, and the center position of the probe rear cover (7) is 2-8 mm from the top end of the probe head part (1).
4. The diameter of the heating wire (3) is 1-30 micrometers, the length is 0.8-2 millimeters, the material is tungsten wire, platinum wire or gold-plated tungsten wire, and the included angle between the heating wire and the axis of the probe is 0-15 degrees.
5. The fork rod (4) is conical, penetrates through the probe head through hole (11) and is connected and insulated with the probe head through insulating glue (12), the inside of the fork rod (4) is connected with the hot wire cable (8), the hot wire (3) is welded outside, the diameter of the head is 0.1-0.3 mm, and the length of the exposed probe of the fork rod (4) is 0.1-1 mm.
6. The probe support rod (2) is of a cylinder structure with the same shape as the probe head (1), and the tail part of the circular pipeline (13) is connected with the aviation plug (10) through threads; the vacuum pump connector (9) on the lee side of the probe support rod is connected with the circular pipeline (13), the outer diameter of the vacuum pump connector (9) is 1-4 mm, the inner diameter of the vacuum pump connector is 0.5-3.5 mm, the hot wire cable (8) penetrates through the circular pipeline (13) to be connected with the aviation plug (10), and the diameter of the screw thread below the aviation plug (10) is 1-6 mm.
7. The diameter of the pressure sensing hole is 0.1-2 mm, the distance between the center line of the pressure sensing hole and the center line of the sonic nozzle is 1-4 mm, the pressure sensor (15) is fixed on a pressure sensor channel (17) in the probe supporting rod (2), the diameter of the pressure sensor channel is 0.5-4 mm, and a pressure sensor cable (16) is led out of the tail of the probe from the sensor channel (17).
The method comprises the following using processes: when the probe is not aspirated, the pitch angle of the incoming flow is measured by a hot wire. And then measuring the total pressure, the static pressure and the deflection angle of the air flow through a pressure sensor. After the air flow direction or the change rule thereof is determined, the probe is rotated to enable the hot wire and the quick nozzle to face the incoming flow, and then the dynamic total temperature of the flow field is measured. Meanwhile, mach number, static temperature, speed, density and entropy of the flow field can be deduced.
The application method of the high-frequency probe for measuring the three-dimensional full parameters of the interstage has the following beneficial effects:
The beneficial effects are as follows: the method can measure the pitch angle and deflection angle of the airflow. When the flow field is used, the pitch angle and the deflection angle of the flow field are measured firstly, after the airflow direction or the change rule of the airflow direction is determined, the probe is rotated to enable the hot wire and the sound velocity spray pipe to face the incoming flow, then the dynamic total temperature and total pressure of the flow field are measured, and the engineering application is wider.
The beneficial effects are as follows: the method has no problem of small insensitive angle, does not limit the range of pitch angle and deflection angle when in use, and can measure the change of the full parameters of the flow field with large angle.
The beneficial effects are as follows: according to the method, the sonic jet pipe is arranged on the side face of the cylinder, the hot wire is welded at the inlet of the sonic jet pipe, so that the hot wire firstly senses the change of incoming flow, the flow field information is not distorted, and the interference caused by the structure of the probe is avoided.
The beneficial effects are four: the probe used in the method is I-shaped, has small size, is suitable for measuring the stages of a narrow compressor and a turbine, and improves the spatial resolution of the probe.
The beneficial effects are five: as the diameter of the heating wire is about 5 microns, the thermal inertia is very small, the frequency response can reach more than 50kHz, and the temperature measurement frequency is improved.
The beneficial effects are six: the fork rod penetrates through the pipe wall of the probe head, the fixation and insulation of the fork rod and the probe head are realized through insulating glue, the probe structure is simpler, and the insulativity and the sealing performance are good. The probe support rod is connected with the aviation socket through threads, so that the tightness is good, air leakage is prevented, and the operation is stable.
Drawings
FIG. 1 is a schematic diagram of a structure of a three-dimensional full-parameter high-frequency probe for measuring an interstage in an embodiment of the method.
Fig. 2 is a view in the a direction of fig. 1.
Fig. 3 is a left side view of fig. 1.
Fig. 4 is a right side view of fig. 1.
Fig. 5 is a bottom view of fig. 1.
Wherein: 1-probe head, 2-probe pole, 3-hot wire, 4-fork, 5-sonic nozzle, 6-cylindrical stabilizing section, 7-probe back cover, 8-hot wire cable, 9-vacuum pump nozzle, 10-aviation plug, 11-probe head through hole, 12-insulating glue, 13-circular pipe, 14-pressure sensing hole, 15-pressure sensor, 16-pressure sensor cable, 17-pressure sensor channel.
Fig. 6 is a velocity component felt by the hot wire.
Detailed Description
Preferred embodiments of the method are described in detail below with reference to the accompanying drawings so that the advantages and features of the method can be more readily understood by those skilled in the art, thereby making a clearer and more definite definition of the scope of protection of the method.
Embodiment one: fig. 1 to 5 show a three-dimensional full parameter high frequency probe between measuring stages, which comprises a probe head (1), a probe supporting rod (2), a hot wire (3), a fork rod (4), a sonic nozzle (5), a cylindrical stabilizing section (6), a probe rear cover (7), a hot wire cable (8), a vacuum pump joint nozzle (9), an aviation plug (10), a probe head through hole (11), insulating glue (12), a circular pipeline (13), a pressure sensing hole (14), a pressure sensor (15), a pressure sensor cable (16) and a pressure sensor channel (17), and is characterized in that: the probe head (1) is of a 'runway-shaped' cylinder structure, a cross section line of the probe head is composed of two equal-diameter semicircles and a rectangle, the top end of the probe head (1) is in arc smooth transition, a sound speed spray pipe (5) is arranged on the opposite incoming flow surface of the cylinder, two fork rods (4) are distributed up and down on the sound speed spray pipe, a heating wire (3) is welded on the sound speed spray pipe, a pressure sensing hole (14) is arranged below the sound speed spray pipe (5), the pressure sensing hole (14) is connected with a pressure sensor (15), a probe rear cover (7) is arranged on the lee side of the probe head (1) opposite to the spray pipe, a vacuum pump nozzle (9) is arranged near the tail of the probe support rod, and the tail of the probe support rod is connected with an aviation plug (10).
2. The diameter D of the two semi-circles of the probe head (1) is 2-8 mm, the width of the rectangular part is the same as the diameter of the semi-circles, the length is 0.5-3D, a circular pipeline (13) is axially arranged inside the probe head, and the diameter of the circular pipeline (13) is 1-7 mm.
3. The circular arc part on the side surface of the probe head part (1) is provided with a sonic nozzle (5), the contracted molded line of the nozzle can be a straight line, a Vitoxinyl curve or a lemniscate, the projected cross-sectional diameter of the nozzle inlet vertical to the axis of the probe head part (1) is 0.8-3 mm, the projected cross-sectional diameter of the nozzle outlet vertical to the axis of the probe head part (1) is 0.4-2 mm, the distance between the nozzle center line and the top end of the probe head part (1) is 2-8 mm, the sonic nozzle (5) is connected with a circular pipeline (13) through a cylindrical stabilizing section (6), the diameter of the cylindrical stabilizing section (6) is the same as the projected cross-sectional diameter of the nozzle inlet vertical to the axis of the probe head part (1), the leeward side opposite to the nozzle is provided with a probe rear cover (7), the cross-section of the nozzle is a fan ring, the fan ring central angle is 45-90 DEG, the length of the probe rear cover (7) is 2-8 mm, and the center position of the probe rear cover (7) is 2-8 mm from the top end of the probe head part (1).
4. The diameter of the heating wire (3) is 1-30 micrometers, the length is 0.8-2 millimeters, the material is tungsten wire, platinum wire or gold-plated tungsten wire, and the included angle between the heating wire and the axis of the probe is 0-15 degrees.
5. The fork rod (4) is conical, penetrates through the probe head through hole (11) and is connected and insulated with the probe head through insulating glue (12), the inside of the fork rod (4) is connected with the hot wire cable (8), the hot wire (3) is welded outside, the diameter of the head is 0.1-0.3 mm, and the length of the exposed probe of the fork rod (4) is 0.1-1 mm.
6. The probe support rod (2) is of a cylinder structure with the same shape as the probe head (1), and the tail part of the circular pipeline (13) is connected with the aviation plug (10) through threads; the vacuum pump connector (9) on the lee side of the probe support rod is connected with the circular pipeline (13), the outer diameter of the vacuum pump connector (9) is 1-4 mm, the inner diameter of the vacuum pump connector is 0.5-3.5 mm, the hot wire cable (8) penetrates through the circular pipeline (13) to be connected with the aviation plug (10), and the diameter of the screw thread below the aviation plug (10) is 1-6 mm.
7. The diameter of the pressure sensing hole is 0.1-2 mm, the distance between the center line of the pressure sensing hole and the center line of the sonic nozzle is 1-4 mm, the pressure sensor (15) is fixed on a pressure sensor channel (17) in the probe supporting rod (2), the diameter of the pressure sensor channel is 0.5-4 mm, and a pressure sensor cable (16) is led out of the tail of the probe from the sensor channel (17).
The method comprises the following using processes:
Before use, the probe used by the method is required to be calibrated, and firstly, the aspiration type hot wire and the pressure sensor are calibrated simultaneously, so that the change of the hot wire voltage on the probe along with the temperature and the pressure is obtained. The calibration of the probe is carried out in a temperature and pressure calibration box, the air extraction is carried out under different temperatures and pressures respectively, and the curve of the voltage of the probe heating wire along with the temperature and pressure change is determined through the calibration.
And then the dynamic pressure sensor is calibrated independently, the process is similar to the calibration process of a single-hole pressure probe, the pressure sensing hole is equivalent to a three-hole pressure probe by rotating the probe head, the pressure sensing hole senses flow field information from the same flow line in respective physical space, and the calibration curves of the total pressure, the static pressure and the deflection angle of the flow field of the measuring point are obtained by combined solution.
In use, the pitch angle of the incoming flow is measured by the hot wire when the probe is not aspirated. And then the total pressure, the static pressure and the deflection angle of the incoming flow are measured by using a pressure sensor, after the airflow direction or the change rule of the airflow direction is determined, a probe is rotated to enable a hot wire and a sound velocity spray pipe to face the incoming flow, and then a vacuum pump nozzle is connected to a vacuum pump for pumping air, so that the back pressure of the nozzle is lower than the total pressure of the incoming flow, the sound velocity is reached at the throat of the sound velocity spray pipe, and the whole spray pipe is in a choked state. At this time, the hot wire voltage is only a function of the total incoming flow temperature and total pressure, is irrelevant to the air flow speed, and meanwhile, the total air flow temperature is deduced by combining the total incoming flow pressure parameters obtained by the pressure sensor.
The following formula is combined:
c2＝γRTs
The Mach number, static temperature, speed, density and entropy of the flow field can be obtained. Wherein, P T and P s are total pressure and static pressure of the flow field, T T and T s are total gentle static temperature of the flow field, subscripts 1 and 2 respectively indicate that the parameters come from different moments, s is entropy of the flow field, gamma is adiabatic index of the flow field, ma is Mach number of the flow field, v is speed of the flow field, ρ is density, c is local sound velocity of the flow field, and R is gas constant.
Claims (1)
1. The utility model provides a measure application method of three-dimensional full parameter high frequency probe between stages, by probe head (1), probe branch (2), hot wire (3), fork arm (4), sonic nozzle (5), cylindrical stable section (6), probe back lid (7), hot wire cable (8), vacuum pump connects mouth (9), aviation plug (10), probe head through-hole (11), insulating glue (12), circular pipeline (13), pressure sensing hole (14), pressure sensor (15), pressure sensor cable (16), pressure sensor passageway (17) are constituteed, its characterized in that: the probe head (1) is of a 'racetrack-shaped' cylinder structure, a cross section line of the probe head is composed of two equal-diameter semicircles and a rectangle, the top end of the probe head (1) is in arc smooth transition, a sound speed spray pipe (5) is arranged on a cylinder opposite to an incoming flow surface, two fork rods (4) are distributed up and down on the sound speed spray pipe, a hot wire (3) is welded on the sound speed spray pipe, a pressure sensing hole (14) is arranged below the sound speed spray pipe (5), the pressure sensing hole (14) is connected with a pressure sensor (15), a probe rear cover (7) is arranged on the lee side of the probe head (1) opposite to the spray pipe, a vacuum pump joint mouth (9) is arranged near the tail of the probe support rod, and the tail of the probe support rod is connected with an aviation plug (10);
The diameter D of two semi-circles of the probe head (1) is 2-8 mm, the width of the rectangular part is the same as the diameter of the semi-circles, the length is 0.5-3D, a circular pipeline (13) is axially arranged inside the probe head, and the diameter of the circular pipeline (13) is 1-7 mm;
The circular arc part on the side surface of the probe head part (1) is provided with a sonic nozzle (5), the contracted molded line of the nozzle can be a straight line, a Vitoxinesky curve or a lemniscate, the projected cross-sectional diameter of the nozzle inlet vertical to the axis of the probe head part (1) is 0.8-3 mm, the projected cross-sectional diameter of the nozzle outlet vertical to the axis of the probe head part (1) is 0.4-2 mm, the distance between the nozzle center line and the top end of the probe head part (1) is 2-8 mm, the sonic nozzle (5) is connected with a circular pipeline (13) through a cylindrical stabilizing section (6), the diameter of the cylindrical stabilizing section (6) is the same as the projected cross-sectional diameter of the nozzle inlet vertical to the axis of the probe head part (1), the leeward side opposite to the nozzle is provided with a probe rear cover (7), the cross-section of the nozzle is a fan ring, the fan ring central angle is 45-90 DEG, the length of the probe rear cover (7) is 2-8 mm, and the center position of the probe rear cover (7) is 2-8 mm from the top end of the probe head part (1);
the diameter of the heating wire (3) is 1-30 micrometers, the length is 0.8-2 millimeters, the material is tungsten wire, platinum wire or gold-plated tungsten wire, and the included angle between the heating wire and the axis of the probe is 0-15 degrees;
The fork rod (4) is conical, penetrates through the probe head through hole (11) and is connected and insulated with the probe head through insulating glue (12), the inside of the fork rod (4) is connected with the hot wire cable (8), the hot wire (3) is welded outside, the diameter of the head is 0.1-0.3 mm, and the length of the exposed probe of the fork rod (4) is 0.1-1 mm;
The probe support rod (2) is of a cylinder structure with the same shape as the probe head (1), and the tail part of the circular pipeline (13) is connected with the aviation plug (10) through threads; the vacuum pump connector (9) on the lee side of the probe support rod is connected with the circular pipeline (13), the outer diameter of the vacuum pump connector (9) is 1-4 mm, the inner diameter of the vacuum pump connector is 0.5-3.5 mm, the hot wire cable (8) passes through the circular pipeline (13) to be connected with the aviation plug (10), and the diameter of the screw thread below the aviation plug (10) is 1-6 mm;
The diameter of the pressure sensing hole is 0.1-2 mm, the distance between the center line of the pressure sensing hole and the center line of the sonic nozzle is 1-4 mm, the pressure sensor (15) is fixed on a pressure sensor channel (17) in the probe supporting rod (2), the diameter of the pressure sensor channel is 0.5-4 mm, and a pressure sensor cable (16) is led out of the tail part of the probe from the sensor channel (17);
the method comprises the following using processes:
Before use, the probe used by the method is required to be calibrated, and firstly, the aspiration type hot wire and the pressure sensor are calibrated simultaneously, so that the change of the hot wire voltage on the probe along with the temperature and the pressure is obtained. The calibration of the probe is carried out in a temperature and pressure calibration box, the air extraction is carried out under different temperatures and pressures respectively, and the curve of the voltage of the probe heating wire along with the temperature and pressure change is determined through the calibration.
And then the dynamic pressure sensor is calibrated independently, the process is similar to the calibration process of a single-hole pressure probe, the pressure sensing hole is equivalent to a three-hole pressure probe by rotating the probe head, the pressure sensing hole senses flow field information from the same flow line in respective physical space, and the calibration curves of the total pressure, the static pressure and the deflection angle of the flow field of the measuring point are obtained by combined solution.
In use, the pitch angle of the incoming flow is measured by the hot wire when the probe is not aspirated. And then the total pressure, the static pressure and the deflection angle of the incoming flow are measured by using a pressure sensor, after the airflow direction or the change rule of the airflow direction is determined, a probe is rotated to enable a hot wire and a sound velocity spray pipe to face the incoming flow, and then a vacuum pump nozzle is connected to a vacuum pump for pumping air, so that the back pressure of the nozzle is lower than the total pressure of the incoming flow, the sound velocity is reached at the throat of the sound velocity spray pipe, and the whole spray pipe is in a choked state. At this time, the hot wire voltage is only a function of the total incoming flow temperature and total pressure, is irrelevant to the air flow speed, and meanwhile, the total air flow temperature is deduced by combining the total incoming flow pressure parameters obtained by the pressure sensor.
The following formula is combined:
c2＝γRTs
The Mach number, static temperature, speed, density and entropy of the flow field can be obtained. Wherein, P T and P s are total pressure and static pressure of the flow field, T T and T s are total gentle static temperature of the flow field, subscripts 1 and 2 respectively indicate that the parameters come from different moments, s is entropy of the flow field, gamma is adiabatic index of the flow field, ma is Mach number of the flow field, v is speed of the flow field, ρ is density, c is local sound velocity of the flow field, and R is gas constant.
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