CN115435929B - High-frequency total temperature and total pressure probe - Google Patents
High-frequency total temperature and total pressure probe Download PDFInfo
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- CN115435929B CN115435929B CN202210904137.4A CN202210904137A CN115435929B CN 115435929 B CN115435929 B CN 115435929B CN 202210904137 A CN202210904137 A CN 202210904137A CN 115435929 B CN115435929 B CN 115435929B
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- 239000000523 sample Substances 0.000 title claims abstract description 272
- 230000003068 static effect Effects 0.000 claims description 33
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- 238000010438 heat treatment Methods 0.000 claims description 10
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 claims description 9
- 238000003466 welding Methods 0.000 claims description 9
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- BASFCYQUMIYNBI-UHFFFAOYSA-N platinum Chemical compound [Pt] BASFCYQUMIYNBI-UHFFFAOYSA-N 0.000 claims description 6
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- 238000011088 calibration curve Methods 0.000 description 4
- 238000005086 pumping Methods 0.000 description 4
- 238000009530 blood pressure measurement Methods 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
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- 238000007789 sealing Methods 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
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- G—PHYSICS
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01D—MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
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Abstract
The invention belongs to the technical field of subsonic flow field parameter testing, and particularly relates to a high-frequency total temperature and total pressure probe, which comprises a probe head, a sonic nozzle, a hot wire, a probe support rod, a vacuum pump nozzle and a pressure sensor.
Description
Technical Field
The invention belongs to the technical field of flow field testing, and particularly relates to a high-frequency total temperature and total pressure probe which is suitable for measuring the total temperature and total pressure in a flow field and the change along with time, wherein the frequency response of the probe can reach more than 50 kHz.
Background
In an aeroengine test, accurate measurement of aerodynamic performance parameters of flow between a compressor and a turbine is still an important engineering problem, and is particularly critical to acquisition of temperature and pressure changes over time in a flow field, and acquisition of dynamic changes of temperature and pressure plays an important role in improving performance of the compressor and a fan and stability of the aeroengine.
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.
In addition, to obtain the dynamic temperature and pressure of the flow field, the pressure probe and the temperature probe are usually used separately to measure the pressure and the temperature respectively, and a mode of combining multiple probes is adopted to measure the measured flow field, so that the complexity of the test and the cost of the test are increased, and most importantly, the flow parameters measured by different probes cannot be ensured to come from the same flow line, and then extra errors are brought when parameters such as calculation speed are combined, so that the precision of the test is reduced. There is also a single temperature and pressure combination probe for simultaneously measuring the temperature and pressure across the acoustic flow field, but the temperature sensor of the existing temperature and pressure combination probe has the disadvantages of the temperature probe.
The principle is that the constant-temperature type heating wire is placed in front of the sonic nozzle, and the square of the output voltage of the bridge where the heating wire is located and the total temperature total pressure of fluid have a relation:
if the two wires are at different operating temperatures T w, the total temperature T t and the total pressure P t can be derived from the two voltage values measured simultaneously.
The Wang Hongwei et al of Beijing aviation aerospace university improves the structural design of a double-wire air suction type probe for measuring the dynamic total temperature and total pressure of a flow field, and adopts a single-hot-film technology to design an air suction type dynamic temperature sensing part.
The air suction type hot wire and dynamic pressure sensor combination probe acquire the total temperature through the relation between the total temperature and other parameters, and the measurement means is also an effective attempt to improve the dynamic temperature measurement frequency. The principle is that a hot wire is placed in front of a sonic jet pipe, the jet pipe is enabled to reach a congestion state through air suction, the relation between the output voltage of an electric bridge where the hot 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 a high-frequency pressure sensor, so that the total temperature of the air flow is deduced.
Existing aspirating hotwire/hotfilm probes, as well as combination probes with dynamic pressure sensors, although fluctuation in local total temperature and total pressure can be measured simultaneously, have some drawbacks. 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, so that the probes are difficult to ensure the main flow, and the measuring result is influenced. Second, the existing probe has a smaller insensitive angle, and when the deflection 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 frequency response of the probe is limited, and a higher frequency signal cannot be captured.
Therefore, in order to realize accurate measurement of total temperature and total pressure of the sub-tone dynamic flow field, it is highly desirable to develop a probe for measuring total temperature and total pressure of the sub-tone dynamic flow field so as to accurately measure dynamic changes of parameters such as total temperature and total pressure.
Disclosure of Invention
The invention relates to a high-frequency total temperature and total pressure probe, wherein the head of the probe is of an L-shaped cylindrical structure, a circular pipeline is arranged in the cylinder, a head channel and a sonic nozzle are arranged at the horizontal section of the head of the probe, two through holes are formed in the head of the probe and a cap cover part, two fork rods are inserted in the through holes, a hot wire is welded at the joint of the head of the probe and the cap cover horizontally, or a cap cover is not needed, a hot wire is welded vertically outside the windward side of the head of the probe, the leeward side of the head of the probe facing away from the nozzle is a rear probe cover, a pressure sensor is fixed under the head of the probe, a vacuum pump nozzle is arranged close to the tail of the probe support rod and is connected with the circular pipeline, 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 nozzle is lower than the total pressure of incoming flow, the sound velocity of the roar 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 invention 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 cos α1
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 invention, 2l/d is more than or equal to 500, and the invention can be regarded as an infinitely long heating wire in actual use. When the pitch angle is measured, the probe is not pumped, then the pitch angle of the probe is adjusted, and when the voltage of the hot wire reaches the maximum, namely the effective cooling speed sensed by the hot wire is maximum, the pitch angle is zero. 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 and the like, parameters of air flow such as static temperature, speed, density, entropy and the like can be deduced.
Therefore, when the invention is used, the probe can be not pumped, the deflection angle and the pitch 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 be vertical to the incoming flow, the static pressure of the incoming flow can be obtained, then the probe is rotated to be opposite to the incoming flow, and the dynamic total temperature and total pressure of the flow field are measured by adopting a pumping mode. When there is the cap, the hot wire welds in probe head and cap junction, is difficult for being blown off by the inflow, and when there is not the cap, the hot wire is directly located probe head windward side, and the change of inflow is felt at first to the hot wire, and flow field information is undistorted, can not receive the influence of probe itself. 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 invention provides a high-frequency total temperature and total pressure probe for measuring a subsonic dynamic flow field, which aims to solve the technical problems that: first, the problem of limited angle sensitivity of the original aspiration type probe is solved. Secondly, for the case that the heat wire is directly welded at the head of the probe, the problem that the flow field parameters sensed by the heat wire placed in the probe are different from the real flow field is solved; the condition that the hot wire is welded at the joint of the probe head and the cap cover solves the problem that the probe is easily blown off by incoming flow when being placed outside the probe. Third, the problem of low probe frequency response is solved. Fourth, the existing probes cannot measure the problems of total temperature, total pressure, static temperature, static pressure, mach number, deflection angle, pitch angle, speed, density and entropy of the subsonic dynamic flow field at the same time.
The technical scheme of the invention is as follows:
1. The utility model provides a high frequency total temperature, total pressure probe, by probe head (1), cap (2), sonic jet pipe (3), probe head through-hole (4), hot wire (5), fork arm (6), hot wire cable (7), probe back lid (8), probe branch (9), circular pipeline (10), head passageway (11), insulating glue (12), vacuum pump connect mouth (13), aviation plug (14), pressure probe (15), pressure sensor (16), pressure sensor cable (17) are constituteed, its characterized in that: the probe head (1) is of an L-shaped cylindrical structure, 2 through holes (4) are formed in the direction opposite to the incoming flow direction of the probe head (1), two fork rods (6) are distributed around the sonic nozzle (3), a hot wire (5) is welded between the two fork rods (6), the hot wire (5) is positioned at the joint of the probe head (1) and the cap (2), or is directly positioned outside the windward side of the probe head (1), the cap (2) is not needed, the fork rods (6) are connected with a hot wire cable (7) through the through holes (4) of the probe head, the hot wire cable (7) is led out by an aviation plug (14) connected with the tail of a probe rod (9), the leeward side of the probe rod (9) opposite to the nozzle is a probe rear cover (8), a vacuum pump joint nozzle (13) is arranged close to the tail of the probe rod, the pressure probe (15) is positioned under the probe head (1), a pressure sensor (16) is arranged in the pressure sensor cable (17) and is led out from the leeward side of the pressure sensor (16);
2. The probe head (1) is of an L-shaped cylindrical structure, wherein the diameter of a vertical section is 2-8 mm, the length is 10-45 mm, the diameter of a horizontal section is 2-8 mm, the length is 2-20 mm, a circular pipeline (10) is arranged on the vertical section of the probe head (1), the diameter of the circular pipeline is 1-7 mm, a head channel (11) is arranged on the horizontal section of the probe head (1), the diameter of the head channel (11) is the same as the diameter of an inlet of a sonic jet pipe (3), the diameter range is 0.5-9 mm, the length is 1-4 times of the diameter of the head channel, the circular pipeline (10) is communicated with a probe support rod (9), a probe rear cover (8) is arranged on the leeside of the probe head (1), the cross section of the probe rear cover is a fan ring, the center angle of the fan ring is 45-90 DEG, the length of the rear cover is 2-8 mm, and the rear cover is 1-4 mm away from the top end of the probe head along the axial top end of the cylinder;
3. The diameter of the leeward side of the cap cover (2) is the same as the diameter of the horizontal section (1) of the probe head, the length is 1-10 mm, the cap cover is connected with the probe head (1) in a welding or gluing mode, an air inlet channel is formed in the cap cover, the shape line of the windward side of the air inlet channel is Bernoulli's double-wire, and the leeward side of the air inlet channel is a head channel (11);
4. the shape line of the sonic jet pipe (3) is a Vidolichos curve, and the diameter of the inlet is in the range of 0.5 mm to 9 mm;
5. the diameter of the heating wire (5) is 1-30 micrometers, the length is 0.8-5 millimeters, and the heating wire (5) is made of tungsten wire, platinum wire or gold-plated tungsten wire by vertically placing and welding;
6. The fork rod (6) is conical, the head of the fork rod faces the incoming flow direction, the diameter is 0.1-0.3 mm, the length of the exposed probe of the head of the fork rod (6) is 0.1-1 mm, the fork rod (6) penetrates through the probe head through hole (4) to be connected with the hot wire cable (7), the hot wire (5) is welded at the joint of the probe head (1) and the cap (2), when the cap is not needed, the fork rod is directly welded outside the windward side of the probe head (1), the fork rod (6) is made of stainless steel, and insulating glue realizes insulation and fixation of the fork rod (6) and the probe head (1);
7. the probe support rod (9) is a cylinder with the diameter of 2-12 mm, and the tail passage aviation plug (14) is sealed and connected with the aviation plug (14) through threads;
8. The vacuum pump connector (13) is connected with the circular pipeline (10), the outer diameter of the pipe of the vacuum pump connector (13) is 1-4 mm, the inner diameter of the pipe is 0.5-3.5 mm, the hot wire cable (7) passes through the circular pipeline (10) to be connected with the aviation plug (14), and the diameter of the thread below the aviation plug (14) is 1-6 mm;
9. the diameter of the pressure probe (15) is 1.5-6 mm, and the pressure probe is fixed under the probe head (1) and the cap cover (2) in a welding or gluing mode; a pressure sensor (16) is arranged in the pressure probe (15), the diameter of the pressure sensor is 1-5 mm, and a pressure sensor cable (17) is led out from the leeward side of the pressure probe (15) and is sequentially clung to a lead wire on the leeward side of the probe support rod (9);
10. The application process of the invention is as follows: firstly, measuring a pitch angle, at the moment, not pumping air to the probe, then adjusting the pitch angle of the probe, when the voltage of the hot wire reaches the maximum, the axis of the probe is vertical to the incoming flow, and when a cap is arranged, omitting the step. And then measuring the total pressure, the static pressure and the deflection angle of the air flow through a pressure sensor. After the airflow direction or the change rule of the airflow direction is determined, the probe is rotated to enable the hot wire, the sonic nozzle and the pressure sensor to face the incoming flow, and then the measurement is carried out in an air extraction mode, and the dynamic total temperature and total pressure of the flow field can be obtained through the calibration coefficient of the pressure sensor and the calibration space of the hot wire, so that Mach number, static temperature, speed, density and entropy of the flow field can be obtained through calculation.
The high-frequency total temperature and total pressure probe has the following beneficial effects:
The beneficial effects are as follows: the invention can measure deflection angle. When the cap is not arranged, the pitch angle can be measured, when the device is used, the deflection angle of the flow field is 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 invention has no problem of small insensitive angle, the probe can acquire the change of deflection angle, and can measure the change of total temperature, total pressure and entropy of the flow field with large angle.
The beneficial effects are as follows: the invention uses the diameter range of the heating wire smaller, the thermal inertia of the heating wire is small, and the probe frequency response is high and can reach 50kHz. .
The beneficial effects are four: the probe is of an L-shaped cylindrical structure, so that the influence of the probe support rod on a measurement result is reduced, the size of the probe is small, the interference on a measured flow field is small, and the spatial resolution of the probe is improved.
The beneficial effects are five: 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.
The beneficial effects are six: the sonic nozzle uses a veduo-sinki curve, the nozzle flows more uniformly, and the interference to the heating wire is small.
The beneficial effects are that: when the cap is arranged, the hot wire is welded at the joint of the probe head and the cap, so that the probe is not easy to blow off by incoming flow; when the cap is not arranged, the hot wire is directly positioned outside the windward side of the probe head, the hot wire firstly senses the change of incoming flow, the flow field information is not distorted, and the influence of the probe is avoided.
Drawings
FIG. 1 is a schematic view of the structure of the capped probe of the present invention.
Fig. 2 is a right side view of fig. 1.
Fig. 3 is a left side view of fig. 1.
Fig. 4 is an a-direction view of fig. 1.
Fig. 5 is a B-direction view of fig. 1.
Wherein: 1-probe head, 2-cap, 3-sonic nozzle, 4-probe head through hole, 5-hot wire, 6-fork, 7-hot wire cable, 8-probe back cover, 9-probe strut, 10-circular tube, 11-head channel, 12-insulating glue, 13-vacuum pump nozzle, 14-aviation plug, 15-pressure probe, 16-pressure sensor, 17-pressure sensor cable.
FIG. 6 is a schematic diagram of the structure of the capless probe of the present invention.
Fig. 7 is a right side view of fig. 6.
Fig. 8 is a left side view of fig. 6.
Fig. 9 is an a-direction view of fig. 6.
Wherein: 1-probe head, 2-sonic nozzle, 3-probe head through hole, 4-hot wire, 5-fork rod, 6-hot wire cable, 7-probe back cover, 8-probe support rod, 9-circular pipeline, 10-head channel, 11-insulating glue, 12-vacuum pump connector, 13-aviation plug, 14-pressure probe, 15-pressure sensor and 16-pressure sensor cable.
Fig. 10 is a velocity component felt by the hot wire.
Detailed Description
The preferred embodiments of the present invention will be described in detail below with reference to the accompanying drawings so that the advantages and features of the present invention can be more easily understood by those skilled in the art, thereby making clear and defining the scope of the present invention.
Embodiment one:
As shown in fig. 1, a high-frequency total temperature and total pressure probe is composed of a probe head (1), a cap cover (2), a sonic nozzle (3), a probe head through hole (4), a hot wire (5), a fork rod (6), a hot wire cable (7), a probe rear cover (8), a probe support rod (9), a circular pipeline (10), a head channel (11), an insulating adhesive (12), a vacuum pump connector (13), an aviation plug (14), a pressure probe (15), a pressure sensor (16) and a pressure sensor cable (17), and is characterized in that: the probe head (1) is of an L-shaped cylindrical structure, 2 through holes (4) are formed in the direction opposite to the incoming flow direction of the probe head (1), two fork rods (6) are distributed around the sonic nozzle (3), the fork rods (6) extend out through the probe head through holes (4), a hot wire (5) is welded between the two fork rods (6), the fork rods (6) are connected with a hot wire cable (7) through the probe head through holes (4), the hot wire cable (7) is led out by an aviation plug (14) connected with the tail of a probe support rod (9), the leeward side of the probe support rod (9) opposite to the nozzle is a probe rear cover (8), a vacuum pump connector (13) is arranged near the tail of the probe support rod, a pressure probe (15) is positioned under the probe head (1), a pressure sensor (16) is arranged in the probe head, and the pressure sensor cable (17) is led out from the leeward side of the tail of the pressure sensor (16);
The probe head (1) is of an L-shaped cylindrical structure, wherein the diameter of a vertical section is 5 mm, the length of the probe head is 20 mm, the diameter of a horizontal section is 5.2 mm, the length of the probe head is 3.4 mm, a circular pipeline (10) is arranged on the vertical section of the probe head (1), the diameter of the circular pipeline is 4 mm, a head channel (11) is arranged on the horizontal section of the probe head (1), the diameter of the head channel (11) is the same as the diameter of an inlet of a sonic jet pipe (3), the length of the head channel is 3 times of the diameter of the head channel, the circular pipeline (10) is communicated with a probe support rod (9), a probe rear cover (8) is arranged on the lee side of the probe head (1), the cross section of the probe rear cover is a fan ring, the center angle of the fan ring is 74 DEG, and the length of the rear cover is 4 mm, and the rear cover is 1mm from the top end of the probe head along the axial direction;
The diameter of the leeward side of the cap cover (2) is the same as that of the horizontal section (1) of the probe head, the length of the leeward side is 1.8 mm, the leeward side is connected with the probe head (1) in a welding or gluing mode, an air inlet channel is formed in the cap cover, the shape line of the windward side of the air inlet channel is Bernoulli's double-wire, and the leeward side of the air inlet channel is a head channel (11);
the shape line of the sonic jet pipe (3) is a Vidolichos curve, and the diameter of the inlet is 1.5 mm;
the diameter of the hot wire (5) is 10 micrometers, the length is 3.4 millimeters, and the hot wire is vertically welded, and the material is tungsten wire, platinum wire or gold-plated tungsten wire;
the fork rod (6) is conical, the head of the fork rod faces the incoming flow direction, the diameter is 0.2 millimeter, the length of the head of the fork rod (6) exposed out of the probe is 0.3 millimeter, the interior of the fork rod penetrates through the probe head through hole (4) to be connected with the hot wire cable (7), the hot wire (5) is welded at the joint of the probe head (1) and the cap cover (2), the fork rod (6) is made of stainless steel, and the insulating glue realizes the fixation and insulation of the fork rod (6) and the probe head (1);
the probe support rod (9) is a cylinder with the diameter of 8mm, and the tail passage aviation plug (14) is sealed and connected with the aviation plug (14) through threads;
The vacuum pump connector (13) is connected with the circular pipeline (10), the outer diameter of the vacuum pump connector (13) pipe is 3 mm, the inner diameter of the vacuum pump connector is 2.4 mm, the hot wire cable (7) penetrates through the circular pipeline (10) to be connected with the aviation plug (14), and the diameter of threads below the aviation plug (14) is 2 mm.
The diameter of the pressure probe (15) is 3 mm, and the pressure probe is fixed under the probe head (1) and the cap cover (2) in a welding mode; the pressure probe (15) is internally provided with a pressure sensor (16), the diameter of the pressure sensor is 1.8 mm, and a pressure sensor cable (17) is led out from the leeward side of the pressure probe (15) and is sequentially clung to a lead wire on the leeward side of the probe support rod (9).
The application process of the invention is as follows: firstly, measuring deflection angles and static pressure, at the moment, measuring the deflection angles of air flow through a pressure sensor without pumping the probe, and rotating the probe to be vertical to the incoming flow direction after the air flow direction or the change rule of the air flow direction is determined, so that the static pressure of the incoming flow can be obtained. And then, the probe is rotated to enable the hot wire, the sonic nozzle and the pressure sensor to face the incoming flow, and then, the measurement is carried out in an air extraction mode, and the dynamic total temperature and total pressure of the flow field can be obtained through the calibration coefficient of the pressure sensor and the calibration space of the hot wire, so that the Mach number, the static temperature, the speed, the density and the entropy of the flow field can be obtained through calculation.
The invention relates to a high-frequency total temperature and total pressure probe for measuring an interstage dynamic flow field. The specific using method is as follows:
Before use, the probe of the invention needs to be calibrated with a pressure sensor and a hot wire respectively. The pressure sensor is calibrated in the calibration wind tunnel, and a calibration curve of the pressure sensor is determined to obtain a curve of deflection angle coefficient, total pressure coefficient and static pressure coefficient along with the change of the deflection angle; the hot wire is calibrated in a temperature and pressure calibration box, namely, the hot wire is pumped under different temperatures and pressures, and the change of the voltage of the hot wire along with the temperature and the pressure is determined through calibration.
When the probe is used, the probe is inserted into a measured flow field, when the probe starts to be used, the air suction is not performed, the pressure sensor is used for measuring the deflection angle of the air flow, after the air flow direction or the change rule of the air flow direction is determined, the probe is rotated to be vertical to the incoming flow direction, the static pressure measurement of the flow field is performed, the dynamic change of the static pressure is obtained, the probe is rotated to be opposite to the incoming flow and is subjected to air suction, the dynamic total pressure of the flow field is obtained through the pressure sensor, the change of the voltage along with time is obtained through the hot wire, and the value of the total pressure is brought into solution according to a known calibration curve, so that the total temperature can be obtained. And combining the following formulas to obtain the Mach number, static temperature, speed, density and entropy of the flow field.
c2＝γRTs
Wherein Pt and Ps are total and static pressures of the flow field, tt and Ts are total and static temperatures of the flow field, tables 1 and 2 below respectively show that the parameters come from different moments, gamma is an 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.
The probe can measure dynamic changes of total temperature, total pressure, static temperature, static pressure, deflection angle, mach number, speed and entropy of the subsonic flow field, namely two-dimensional full parameters of the interstage.
Embodiment two:
As shown in fig. 6, a high-frequency total temperature and total pressure probe is composed of a probe head (1), a sonic nozzle (2), a probe head through hole (3), a hot wire (4), a fork rod (5), a hot wire cable (6), a probe rear cover (7), a probe support rod (8), a circular pipeline (9), a head channel (10), insulating glue (11), a vacuum pump nozzle (12), an aviation plug (13), a pressure probe (14), a pressure sensor (15) and a pressure sensor cable (16), and is characterized in that: the probe head (1) is of an L-shaped cylindrical structure, 2 through holes (3) are formed in the direction opposite to the incoming flow direction of the probe head (1), two fork rods (5) are distributed around the sonic nozzle (2), the fork rods (5) extend out through the probe head through holes (3), a hot wire (4) is welded between the two fork rods (5), the fork rods (5) are connected with a hot wire cable (6) through the probe head through holes (3), the hot wire cable (6) is led out by an aviation plug (13) connected with the tail of a probe support rod (8), the leeward side of the probe support rod (8) opposite to the nozzle is a probe rear cover (7), a vacuum pump connector (12) is arranged near the tail of the probe support rod, a pressure probe (14) is positioned under the probe head (1), a pressure sensor (15) is arranged in the probe head, and a pressure sensor cable (16) is led out from the leeward side of the tail of the pressure sensor (15);
The probe head (1) is of an L-shaped cylindrical structure, wherein the diameter of a vertical section is 5 mm, the length is 20 mm, the diameter of a horizontal section is 5.2 mm, the length is 3.4 mm, a circular pipeline (9) is arranged on the vertical section of the probe head (1), the diameter of the circular pipeline is 4 mm, a head channel (10) is arranged on the horizontal section of the probe head (1), the diameter of the head channel (10) is the same as the diameter of an inlet of a sonic jet pipe (2), the length is 2.5 times of the diameter of the head channel, the circular pipeline (9) is communicated with a probe support rod (8), a probe rear cover (7) is arranged on the lee side of the probe head (1), the cross section of the probe rear cover is a fan ring, the central angle of the fan ring is 74 DEG, the length of the rear cover is 4 mm, and the rear cover is 1mm away from the top of the probe head along the axial top end of the cylinder;
The shape line of the sonic jet pipe (2) is a Vidolichos curve, and the diameter of the inlet is 1.5 mm;
the diameter of the hot wire (4) is 10 micrometers, the length is 3.4 millimeters, and the hot wire is vertically welded, and the material is tungsten wire, platinum wire or gold-plated tungsten wire;
The fork rod (5) is conical, the head of the fork rod faces the incoming flow direction, the diameter is 0.2 millimeter, the length of the head of the fork rod (5) exposed out of the probe is 0.3 millimeter, the interior of the fork rod penetrates through the probe head through hole (3) to be connected with the hot wire cable (6), the hot wire (4) is welded on the probe head (1), the fork rod (5) is made of stainless steel, and the insulating glue is used for fixing and insulating the fork rod (5) and the probe head (1);
The probe support rod (8) is a cylinder with the diameter of 8mm, and the tail passage aviation plug (13) is sealed and connected with the aviation plug (13) through threads;
The vacuum pump connector (12) is connected with the circular pipeline (9), the outer diameter of the vacuum pump connector (12) is 3 mm, the inner diameter of the vacuum pump connector is 2.4 mm, the hot wire cable (6) penetrates through the circular pipeline (9) to be connected with the aviation plug (13), and the diameter of threads below the aviation plug (13) is 2 mm.
The diameter of the pressure probe (14) is 3 mm, and the pressure probe is fixed under the probe head (1) in a welding mode; the pressure probe (14) is internally provided with a pressure sensor (15), the diameter of the pressure sensor is 1.8 mm, and a pressure sensor cable (16) is led out from the leeward side of the pressure probe (14) and is sequentially clung to a lead wire on the leeward side of the probe support rod (8).
The application process of the invention is as follows: firstly measuring a pitch angle, at the moment, not pumping the probe, then adjusting the pitch angle of the probe, and when the voltage of the hot wire reaches the maximum, enabling the axis of the probe to be perpendicular to the incoming flow. And then measuring the total pressure, the static pressure and the deflection angle of the air flow through a pressure sensor. After the airflow direction or the change rule thereof is determined, the probe is rotated to enable the hot wire, the sonic nozzle and the pressure sensor to face the incoming flow, and then the measurement is carried out in an air extraction mode, and the dynamic total temperature and total pressure of the flow field can be obtained through the calibration coefficient of the pressure sensor and the calibration space of the hot wire, so that the Mach number, the static temperature, the speed, the density and the entropy of the flow field can be obtained through calculation.
The invention relates to a high-frequency total temperature and total pressure probe for measuring an interstage dynamic flow field. The specific using method is as follows:
Before use, the probe of the invention needs to be calibrated with a pressure sensor and a hot wire respectively. The pressure sensor performs calibration in a calibration wind tunnel, the process is similar to that of a single-hole pressure probe, the pressure sensing hole is equivalent to a three-hole pressure probe by rotating the head of the probe, the pressure sensing hole senses flow field information from the same flow line in respective physical space, and the total pressure, static pressure and deflection angle calibration curves of the flow field of the measuring point are obtained by combined solution; the hot wire is calibrated in a temperature and pressure calibration box, namely, the air is pumped under different temperatures and pressures respectively, and the change of the voltage of the hot wire of the probe along with the temperature and the pressure is determined through calibration.
When the probe is used, the probe is inserted into a flow field to be tested, and when the probe starts to be used, the probe is not pumped, the displacement mechanism is used for rotating the probe, so that the hot wire senses the change of the incoming flow speed, the pitch angle of the incoming flow is determined, the pressure sensor is used for measuring the deflection angle of the air flow, the air flow direction or the change rule of the air flow direction is determined, the probe is rotated to be vertical to the incoming flow direction, the static pressure measurement of the flow field is carried out, the dynamic change of the static pressure is obtained, the probe is rotated to be opposite to the incoming flow and pumped, the dynamic total pressure of the flow field is obtained through the pressure sensor, the change of the voltage along with time is obtained through the hot wire, and the value of the total pressure is brought into solution according to a known calibration curve, so that the total temperature can be obtained. And combining the following formulas to obtain the Mach number, static temperature, speed, density and entropy of the flow field.
c2＝γRTs
Wherein Pt and Ps are total and static pressures of the flow field, tt and Ts are total and static temperatures of the flow field, tables 1 and 2 below respectively show that the parameters come from different moments, gamma is an 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.
The probe can measure dynamic changes of total temperature, total pressure, static temperature, static pressure, deflection angle, pitch angle, mach number, speed and entropy of the subsonic flow field, and can measure three-dimensional full parameters of the interstage.
Claims (1)
1. The utility model provides a high frequency total temperature, total pressure probe, by probe head (1), cap (2), sonic jet pipe (3), probe head through-hole (4), hot wire (5), fork arm (6), hot wire cable (7), probe back lid (8), probe branch (9), circular pipeline (10), head passageway (11), insulating glue (12), vacuum pump connect mouth (13), aviation plug (14), pressure probe (15), pressure sensor (16), pressure sensor cable (17) are constituteed, its characterized in that: the probe head (1) is of an L-shaped cylindrical structure, 2 through holes (4) are formed in the direction opposite to the incoming flow direction of the probe head (1), two fork rods (6) are distributed around the sonic nozzle (3), a hot wire (5) is welded between the two fork rods (6), the hot wire (5) is positioned at the joint of the probe head (1) and the cap cover (2), the fork rods (6) are connected with a hot wire cable (7) through the probe head through holes (4), the hot wire cable (7) is led out by an aviation plug (14) connected with the tail of the probe support rod (9), the leeward side of the probe support rod (9) opposite to the nozzle is a probe rear cover (8), a vacuum pump connector (13) is arranged close to the tail of the probe support rod, the pressure probe (15) is positioned under the probe head (1), a pressure sensor (16) is arranged in the probe, and the pressure sensor cable (17) is led out from the leeward side of the tail of the pressure sensor (16);
The probe head (1) is of an L-shaped cylindrical structure, wherein the diameter of a vertical section is 2-8 mm, the length is 10-45 mm, the diameter of a horizontal section is 2-8 mm, the length is 2-20 mm, a circular pipeline (10) is arranged on the vertical section of the probe head (1), the diameter of the circular pipeline is 1-7 mm, a head channel (11) is arranged on the horizontal section of the probe head (1), the diameter of the head channel (11) is the same as the diameter of an inlet of a sonic jet pipe (3), the diameter range is 0.5-9 mm, the length is 1-4 times of the diameter of the head channel, the circular pipeline (10) is communicated with a probe support rod (9), a probe rear cover (8) is arranged on the leeside of the probe head (1), the cross section of the probe rear cover is a fan ring, the center angle of the fan ring is 45-90 DEG, the length of the rear cover is 2-8 mm, and the rear cover is 1-4 mm away from the top end of the probe head along the axial top end of the cylinder;
The diameter of the leeward side of the cap cover (2) is the same as the diameter of the horizontal section of the probe head (1), the length is 1-10 mm, the cap cover is connected with the probe head (1) in a welding or gluing mode, an air inlet channel is formed in the cap cover, the shape line of the windward side of the air inlet channel is Bernoulli's double-wire, and the leeward side of the air inlet channel is a head channel (11);
the shape line of the sonic jet pipe (3) is a Vidolichos curve, and the diameter of the inlet is in the range of 0.5 mm to 9 mm;
The diameter of the heating wire (5) is 1-30 micrometers, the length is 0.8-5 millimeters, and the heating wire (5) is made of tungsten wire, platinum wire or gold-plated tungsten wire by vertically placing and welding;
The fork rod (6) is conical, the head of the fork rod faces the incoming flow direction, the diameter of the fork rod is 0.1-0.3 mm, the length of the exposed probe of the head of the fork rod (6) is 0.1-1 mm, the fork rod (6) penetrates through the probe head through hole (4) to be connected with the hot wire cable (7), the hot wire (5) is welded at the joint of the probe head (1) and the cap cover (2), the fork rod (6) is made of stainless steel, and insulating glue realizes insulation and fixation of the fork rod (6) and the probe head (1);
The probe support rod (9) is a cylinder with the diameter of 2-12 mm, and the tail passage aviation plug (14) is sealed and connected with the aviation plug (14) through threads;
The vacuum pump connector (13) is connected with the circular pipeline (10), the outer diameter of the pipe of the vacuum pump connector (13) is 1-4 mm, the inner diameter of the pipe is 0.5-3.5 mm, the hot wire cable (7) passes through the circular pipeline (10) to be connected with the aviation plug (14), and the diameter of the thread below the aviation plug (14) is 1-6 mm;
the diameter of the pressure probe (15) is 1.5-6 mm, and the pressure probe is fixed under the probe head (1) and the cap cover (2) in a welding or gluing mode; a pressure sensor (16) is arranged in the pressure probe (15), the diameter of the pressure sensor is 1-5 mm, and a pressure sensor cable (17) is led out from the leeward side of the pressure probe (15) and is sequentially clung to a lead wire on the leeward side of the probe support rod (9);
The application process of the invention is as follows: measuring total pressure, static pressure and deflection angle of the air flow by a pressure sensor; after the airflow direction or the change rule of the airflow direction is determined, the probe is rotated to enable the hot wire, the sonic nozzle and the pressure sensor to face the incoming flow, and then the measurement is carried out in an air extraction mode, and the dynamic total temperature and total pressure of the flow field can be obtained through the calibration coefficient of the pressure sensor and the calibration space of the hot wire, so that Mach number, static temperature, speed, density and entropy of the flow field can be obtained through calculation.
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| CN115901074B (en) * | 2022-12-13 | 2024-06-04 | 重庆大学 | Movable probe device for measuring pressure in spray pipe flow channel |
| CN116275763B (en) * | 2023-05-22 | 2023-08-18 | 中国航发四川燃气涡轮研究院 | Hot wire welding method and device for one-dimensional probe of hot wire anemometer |
| CN117761264B (en) * | 2024-02-22 | 2024-06-04 | 成都凯天电子股份有限公司 | Liquid water content detector and detection method based on total temperature measurement technology |
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