CN115435930A - Three-dimensional full-parameter high-frequency probe for measuring interstage - Google Patents
Three-dimensional full-parameter high-frequency probe for measuring interstage Download PDFInfo
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- 230000003068 static effect Effects 0.000 claims description 20
- 230000008859 change Effects 0.000 claims description 10
- 238000000034 method Methods 0.000 claims description 7
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 claims description 7
- 230000000087 stabilizing effect Effects 0.000 claims description 6
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- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K13/00—Thermometers specially adapted for specific purposes
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- G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
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- G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
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Abstract
The invention belongs to the technical field of dynamic testing of high-frequency flow fields, and particularly relates to a three-dimensional full-parameter high-frequency probe for measuring interstage, which comprises a probe head, a probe supporting rod, a hot wire, a fork rod, a sonic nozzle, a probe rear cover, a hot wire cable, a vacuum pump nozzle, an aviation plug, a pressure sensing hole, a pressure sensor cable and a pressure sensor channel. The probe head is in a runway-shaped cylinder structure, a sound velocity spray pipe is arranged on the cylinder body opposite to an incoming flow surface, two fork rods are distributed on the sound velocity spray pipe from top to bottom, hot wires are welded on the sound velocity spray pipe, a pressure sensing hole is arranged below the sound velocity spray pipe and connected with a pressure sensor, a probe rear cover is arranged on the leeward side of the probe head back to the spray pipe, a vacuum pump connecting nozzle is arranged close to the tail of a probe supporting rod, and an aviation plug is connected to the tail of the probe supporting rod.
Description
Technical Field
The invention belongs to the technical field of dynamic testing of high-frequency flow fields, and particularly relates to a three-dimensional full-parameter high-frequency probe for measuring interstage, 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 and entropy of a flow field along with time, and the frequency response of the probe can reach over 50 kHz.
Background
Currently, accurate measurement of aerodynamic performance parameters of flow between compressor and turbine stages in the field of aeroengines remains an important engineering problem. The flow between the compressor and the turbine is characterized by strong three-dimension, compressibility, instability and strong non-stationarity, the passing frequency of the blade reaches above 10kHz, and the corresponding temperature field and pressure field are also dynamically changed at high frequency, so that the accurate acquisition of the temperature and pressure changes between the compressor and the turbine along with time is very difficult. 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 a high-frequency dynamic pressure and temperature measuring means.
At present, a thermocouple and a thermal resistor are commonly used for obtaining the dynamic temperature of a flow field, a high-frequency dynamic pressure probe is used for measuring the dynamic pressure of the flow field, and a porous pressure probe is used for measuring the direction of air flow. The frequency response of the existing dynamic pressure sensor can meet the measurement requirement of the compressor/turbine interstage, the frequency response of the existing temperature sensor is low, even the filament thermocouple temperature sensor with the highest frequency response has two orders of magnitude difference with 10kHz, and the measurement of the unsteady temperature field of the compressor/turbine interstage by using the traditional temperature sensor is very difficult.
The total temperature is obtained by the combined probe of the air-breathing hot wire and the dynamic pressure sensor through a relation formula of the total temperature and other parameters, and the measurement means is an effective attempt for improving the measurement frequency of the dynamic temperature. The air-breathing type hot wire and dynamic pressure sensor combined probe is originally designed by D.E.Van Zante at Iowa State university, the probe consists of an air-breathing type 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 hot wire is placed in front of a sonic nozzle, the nozzle is enabled to reach a choked state through air suction, and a relational expression between the output voltage of a bridge where the hot wire is located and the total temperature and pressure of an air flow is obtained:
and then obtaining the dynamic total pressure of the airflow through a high-frequency pressure sensor, and deducing the total temperature of the airflow.
Yanglin and the like invent a dynamic entropy probe, total pressure and static pressure are firstly measured by two dynamic pressure sensors, and the total pressure, the static pressure and the Ma number are expressed by a relational expression:
and further mach numbers are obtained. Yanlin considers the hot film voltage as a function of the fluid velocity and the air flow temperature, and then substitutes the velocity (mach number) obtained in the previous step into the function:
E 2 ＝[A+B(ρU) n ](T w -rT T )
the total temperature of the air flow can be calculated.
The existing aspirated hot-wire and dynamic pressure sensor combination probes, as well as dynamic entropy probes, while capable of measuring fluctuations in total pressure and total local temperature simultaneously, have some drawbacks. First, the probes are designed according to the requirements of the main stream, but the pitch angle and the deflection angle of the airflow cannot be measured, and the airflow direction needs to be acquired in advance when the probes are used. Secondly, the existing probe has a small insensitive angle, and when the deflection angle or the pitch angle of the measured flow field exceeds 20 degrees, a very large error is generated in a measurement result. Thirdly, a hot wire is placed inside the probe, and the flow field parameters sensed by the hot wire can be different from the real flow field, especially for the dynamic measurement of high frequency response. Fourth, the probes are all "L" or "line" type, which cannot be used for measuring the inter-stage flow field because of the limited inter-stage width, and the "line" type will interfere with the blade. The "L" probe is also difficult to reach into narrow compressor or turbine stages. Fifth, the frequency response of the probe is limited, and a higher frequency signal cannot be captured, and the maximum frequency response of the conventional probe is only 10kHz, and temperature and pressure changes at higher frequencies cannot be measured. Sixth, the dynamic entropy probe described above can only measure incompressible flow fields because the inventors believe that the hot film voltage is related only to fluid velocity and gas flow temperature, and the density ρ is assumed to be constant, which is only applicable to incompressible flow fields.
Therefore, it is urgently needed to develop a high-frequency probe for measuring the interstage three-dimensional full parameters so as to accurately measure the dynamic changes of the interstage three-dimensional flow field in the full parameters of total temperature, total pressure, static temperature, static pressure, mach number, deflection angle, pitch angle, speed, density, entropy and the like.
Disclosure of Invention
The invention relates to a high-frequency probe for measuring interstage three-dimensional full parameters, wherein the head of the probe is of a runway-shaped cylinder structure, the top end of the probe is in arc smooth transition, a sonic spray pipe is arranged on the arc part of the side surface of the cylinder, two fork rods are distributed above and below the sonic spray pipe, hot wires are welded on the sonic spray pipe, the hot wires are parallel to the axis of the probe or form a certain angle with the axis of the probe, a pressure sensing hole is formed below the sonic spray pipe, the pressure sensing hole is connected with a pressure sensor, a probe rear cover is formed on the leeward side of the head of the probe, which is back to the spray pipe, a vacuum pump connecting nozzle is formed on the leeward side close to the tail of a probe supporting rod, and the tail of the probe supporting rod is connected with an aviation plug. The principle of measuring the total temperature is the same as that of a suction type hot wire and dynamic pressure sensor combined probe. When the device is used, the vacuum pump connecting nozzle is connected with a vacuum pump to exhaust air, so that the back pressure of the spray pipe is lower than the total pressure of incoming flow, the throat of the sonic spray pipe reaches the sonic velocity, and the whole spray pipe reaches a choking state. At the moment, the hot wire voltage is only a function of the total temperature and the total pressure of the incoming flow, is independent of the speed of the air flow, and is combined with a pressure sensor to obtain the total pressure parameter of the incoming flow to deduce the total temperature of the air flow.
On the basis, the method can also measure the incoming flow pitch angle, the deflection angle and the static pressure, and simultaneously calculate the incoming 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:
V eff ＝V cos α1
wherein, V eff And α 1 is the pitch angle of the probe, which is the effective cooling rate felt by the hot wire, as shown in fig. 6. For the present invention, 2l/d is 500 or more, and in practical use, it can be regarded as an infinite hot line. When measuring pitch angle, do not carry out probeAnd (4) pumping air, and then adjusting the pitch angle of the probe to obtain the pitch angle of the incoming flow. Meanwhile, the total pressure, the static pressure and the deflection angle of the airflow can be measured through the pressure sensing holes and the pressure sensor, and the principle of the method is the same as that of the single-hole pressure probe. All the parameters of the air flow such as static temperature, speed, density, entropy and the like can be deduced according to the measured parameters such as total temperature, total pressure, static pressure, pitch angle, deflection angle and the like.
When the invention is used, the total pressure, the static pressure and the deflection angle of the airflow can be measured by the pressure sensor, after the airflow direction is determined, the probe is adjusted to enable the probe to be opposite to the main flow, and then air extraction is carried out to measure the dynamic change of the temperature of the incoming flow. The probe of the invention is I-shaped, has small size and is suitable for narrow interstage measurement. The sonic nozzle is arranged on the arc part of the side surface of the cylinder at the head of the probe, the hot wire firstly senses the change of the incoming flow, the flow field information is not distorted, and the influence of the probe is avoided. The molded line of the sonic nozzle uses a Victorius curve, the flow of the nozzle is more uniform, and the flow at the plane of the hot wire cannot be influenced. The hot wire can use 5 μm gold-plated tungsten wire, and can make the frequency response reach above 50kHz by matching with the latest CTA (constant temperature hot wire anemometer) module.
The invention provides a three-dimensional full-parameter high-frequency probe for measuring interstage, which aims to solve the technical problems that: firstly, the problem that the original air suction type hot wire and dynamic pressure sensor combined probe cannot measure the pitch angle and deflection angle of the airflow is solved. Secondly, the problem that the existing probe has a small insensitive angle and a great error is generated in a measurement result when the pitch angle and the deflection angle of a measured flow field exceed 20 degrees is solved. Thirdly, the problem that the probes of the original L-shaped structure and the I-shaped structure are difficult to extend into a narrow compressor or turbine stage for measurement is solved. Fourthly, the problem that the flow field parameters sensed by the hot wire placed in the probe are different from the real flow field is solved. And fifthly, the problem that the frequency response of the conventional temperature probe is low is solved.
The technical solution of the invention is as follows:
1. the utility model provides a measure three-dimensional full parameter high frequency probe between stage, by probe head (1), probe branch (2), hot line (3), fork arm (4), sonic nozzle (5), cylindrical stable section (6), lid (7) behind the probe, hot line cable (8), vacuum pump connector (9), aviation plug (10), probe head through-hole (11), insulating cement (12), circular pipeline (13), pressure-sensitive receiving hole (14), pressure sensor (15), pressure sensor cable (16), pressure sensor passageway (17) are constituteed, its characterized in that: probe head (1) is "runway shape" cylinder structure, its cross section line comprises two equal footpath semicircles and a rectangle, probe head (1) top is through arc smooth transition, the cylinder just opens one sound velocity spray tube (5) to the incoming flow face, two forks pole (4) of sound velocity spray tube upper and lower distribution have welded hot wire (3) on it, sound velocity spray tube (5) below is opened has pressure sensing hole (14), pressure sensing hole (14) are connected with pressure sensor (15), probe head (1) leeward side back to the spray tube is a probe back cover (7), it has a vacuum pump connector (9) to be close to probe branch afterbody, probe branch afterbody connection aviation plug (10).
2. The diameter D of two semicircles of probe head (1) is 2 ~ 8 millimeters, and the rectangle part width is the same with semicircular diameter, and length is 0.5D ~ 3D, along the axial inside division have circular pipeline (13), and the diameter of circular pipeline (13) is 1 ~ 7 millimeters.
3. The probe comprises a probe head (1), wherein a sound velocity spray pipe (5) is arranged on the arc part of the side surface of the probe head (1), the contracted molded line of the spray pipe can be a straight line, a WittonsisKing curve or a lemniscate, the section diameter of a projection of a spray pipe inlet vertical to the cylinder axis of the probe head (1) is 0.8-3 mm, the section diameter of a projection of a spray pipe outlet vertical to the cylinder axis of the probe head (1) is 0.4-2 mm, the distance between the spray pipe central line and the top end of the probe head (1) is 2-8 mm, the sound velocity spray pipe (5) is connected with a circular channel (13) through a cylindrical stabilizing section (6), the diameter of the cylindrical stabilizing section (6) is the same as that of the spray pipe inlet vertical to the cylinder axis of the probe head (1), a probe rear cover (7) is arranged on the leeward side opposite to the back of the spray pipe, the cross section of the probe rear cover is a fan ring, the fan ring central angle of the fan ring is 45-90 degrees, the length of the probe rear cover (7) is 2-8 mm, and the central position of the probe rear cover (7) is 2-8 mm from the top end of the probe head (1).
4. The diameter of the hot 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 hot wire and the axis of the probe is 0-15 degrees.
5. The fork rod (4) is conical, penetrates through the through hole (11) of the head of the probe and is connected and insulated with the head of the probe through insulating glue (12), the inside of the fork rod (4) is connected with a hot wire cable (8), the hot wire (3) is welded to the outside, the diameter of the head of the fork rod 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 supporting 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 leeward side of the probe supporting 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 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 from the center line to the center line of the sonic nozzle is 1-4 mm, the pressure sensor (15) is fixed in a pressure sensor channel (17) in the probe support rod (2), the diameter of the pressure sensor channel is 0.5-4 mm, and the pressure sensor cable (16) is led out of the tail part of the probe through the sensor channel (17).
The using process of the invention is as follows: when the probe is not aspirated, the pitch angle of the incoming flow is measured by the hot wire. Then the total pressure, static pressure and deflection angle of the airflow are measured by a pressure sensor. After the direction of the airflow or the change rule of the airflow is determined, the probe is rotated to enable the hot wire and the sonic nozzle to face the incoming flow, and then the dynamic total temperature of the flow field is measured. Meanwhile, the Mach number, static temperature, speed, density and entropy of the flow field can be deduced.
The invention discloses a three-dimensional full-parameter high-frequency probe for measuring interstage, which has the following beneficial effects:
the beneficial effects are that: the invention can measure the pitch angle and the yaw angle of the airflow. When the device 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 airflow nozzle to face the incoming flow, then the dynamic total temperature and the total pressure of the flow field are measured, and the engineering application is wider.
The beneficial effects are two: the invention has no problem of small insensitive angle, has no limit to the range of the pitch angle and the deflection angle when in use, and can measure the change of the full parameter of the flow field with large angle.
The beneficial effects are three: the sonic nozzle is arranged on the side surface of the cylinder, the hot wire is welded at the inlet of the sonic nozzle, and the hot wire can firstly feel the change of incoming flow, so that the flow field information is not distorted, and the interference caused by the structure of the probe can be avoided.
The beneficial effects are four: the probe is I-shaped, has small size, is suitable for measurement between a narrow gas compressor and a turbine, and improves the spatial resolution of the probe.
The beneficial effects are five: because the diameter of the hot wire is about 5 micrometers, the thermal inertia is small, the frequency response can reach more than 50kHz, and the measurement frequency of the temperature is improved.
The beneficial effects are six: the fork rod penetrates through the pipe wall of the head part of the probe, the fixing and the insulation of the fork rod and the head part of the probe are realized through insulating glue, the probe is simpler in structure, and the insulating property and the sealing property are good. The probe supporting rod is connected with the aviation socket through threads, the sealing performance is good, air leakage is prevented, and the work is stable.
Drawings
Fig. 1 is a schematic structural diagram of a three-dimensional full-parameter high-frequency probe for measuring interstage in an embodiment of the invention.
Fig. 2 is a view in the direction a 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 supporting rod, 3-hot wire, 4-fork rod, 5-sonic nozzle, 6-cylindrical stable section, 7-probe rear cover, 8-hot wire cable, 9-vacuum pump connector, 10-aviation plug, 11-probe head through hole, 12-insulating glue, 13-circular pipeline, 14-pressure sensing hole, 15-pressure sensor, 16-pressure sensor cable and 17-pressure sensor channel.
Fig. 6 is a velocity component felt by the hot wire.
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: as shown in fig. 1-5, it is a three-dimensional full parameter high frequency probe between measurement stage, by probe head (1), probe branch (2), hot wire (3), fork arm (4), sound velocity spray tube (5), cylindrical stable section (6), lid (7) behind the probe, hot wire cable (8), vacuum pump connector (9), aviation plug (10), probe head through-hole (11), insulating glue (12), circular pipeline (13), pressure-sensitive hole (14), pressure sensor (15), pressure sensor cable (16), pressure sensor passageway (17) are constituteed, its characterized in that: probe head (1) is "runway shape" cylinder structure, its cross section line comprises two equal footpath semicircles and a rectangle, probe head (1) top is through arc smooth transition, the cylinder just opens one sound velocity spray tube (5) to the incoming flow face, two forks pole (4) of sound velocity spray tube upper and lower distribution have welded hot wire (3) on it, sound velocity spray tube (5) below is opened has pressure sensing hole (14), pressure sensing hole (14) are connected with pressure sensor (15), probe head (1) leeward side back to the spray tube is a probe back cover (7), it has a vacuum pump connector (9) to be close to probe branch afterbody, probe branch afterbody connection aviation plug (10).
2. The diameter D of two semicircles of probe head (1) is 2 ~ 8 millimeters, and the rectangle part width is the same with semicircular diameter, and length is 0.5D ~ 3D, along the axial inside division have circular pipeline (13), and the diameter of circular pipeline (13) is 1 ~ 7 millimeters.
3. The probe head part (1) side circular arc part is provided with a sound velocity spray pipe (5), the contracted molded line of the spray pipe can be a straight line, a Wittonsisky curve or a lemniscate, the section diameter of a projection of a spray pipe inlet vertical to the cylinder axis of the probe head part (1) is 0.8-3 mm, the section diameter of a projection of a spray pipe outlet vertical to the cylinder axis of the probe head part (1) is 0.4-2 mm, the distance between the spray pipe central line and the top end of the probe head part (1) is 2-8 mm, the sound velocity spray pipe (5) is connected with a circular channel (13) through a cylindrical stabilizing section (6), the diameter of the cylindrical stabilizing section (6) is the same as the section diameter of a projection of the spray pipe inlet vertical to the cylinder axis of the probe head part (1), a probe rear cover (7) is arranged on the leeward side opposite to the back of the spray pipe, the cross section of the fan ring is a fan ring, the circle center angle of the fan ring is 45-90 degrees, 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 hot 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 hot wire and the axis of the probe is 0-15 degrees.
5. The fork rod (4) is conical, penetrates through the through hole (11) of the head of the probe and is connected and insulated with the head of the probe through insulating glue (12), the inside of the fork rod (4) is connected with a hot wire cable (8), the hot wire (3) is welded to the outside, the diameter of the head of the fork rod 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 supporting 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 leeward side of the probe supporting 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 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 from the center line to the center line of the sonic nozzle is 1-4 mm, the pressure sensor (15) is fixed in 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 through the sensor channel (17).
The using process of the invention is as follows:
before use, the probe of the invention needs to be calibrated, and the suction type hot wire and the pressure sensor are simultaneously calibrated, so that the change of the voltage of the hot wire 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, air extraction is carried out under different temperature and pressure respectively, and the curve of the hot wire voltage of the probe, which changes along with the temperature and the pressure, is determined through calibration.
And then, independently calibrating the dynamic pressure sensor, wherein the process is similar to the calibration process of a single-hole pressure probe, 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 rotating the head part of the probe, wherein the pressure sensing hole is equivalent to a three-hole pressure probe, and the pressure sensing holes sense the flow field information from the same streamline in respective physical spaces and are combined and solved.
In use, when the probe is not aspirated, the pitch angle of the incoming flow is measured by the hot wire. Then, a pressure sensor is used for measuring the total pressure, static pressure and deflection angle of incoming flow, after the direction of the air flow or the change rule of the air flow is determined, a probe is rotated to enable a hot wire and a sonic nozzle to face the incoming flow, then a vacuum pump connecting nozzle is connected to a vacuum pump for pumping, the back pressure of the nozzle is lower than the total pressure of the incoming flow, the throat of the sonic nozzle reaches the sonic velocity, and the whole nozzle reaches a choked state. At the moment, the hot wire voltage is only a function of the total temperature and the total pressure of the incoming flow, is independent of the speed of the air flow, and is combined with the total pressure parameter of the incoming flow obtained by the pressure sensor to deduce the total temperature of the air flow.
Combining the following formulas:
c 2 ＝γRT s
the Mach number, static temperature, speed, density and entropy of the flow field can be obtained. Wherein, P T And P s Is the total and static pressure, T, of the flow field T And T s Is the total and static temperature of the flow field, the subscripts 1, 2 indicate that the parameter is from different time points, respectively, and s is of the flow fieldEntropy, γ is the adiabatic exponent of the flow field, ma is the mach number of the flow field, v is the velocity of the flow field, ρ is the density, c is the local acoustic velocity of the flow field, and R is the gas constant.
Claims (1)
1. The utility model provides a measure three-dimensional full parameter high frequency probe between stage, by probe head (1), probe branch pole (2), hot line (3), fork arm (4), sonic nozzle (5), cylindrical stable section (6), lid (7) behind the probe, hot line cable (8), vacuum pump connector (9), aviation plug (10), probe head through-hole (11), insulating cement (12), circular pipeline (13), pressure-sensitive receiving 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, the cross section line of the probe head (1) consists of two equal-diameter semicircles and a rectangle, the top end of the probe head (1) is in smooth transition through an arc, a sonic spray pipe (5) is arranged on the cylinder just opposite to an incoming flow surface, two fork rods (4) are distributed on the sonic spray pipe up and down, hot wires (3) are welded on the sonic spray pipe, a pressure sensing hole (14) is formed below the sonic spray pipe (5), the pressure sensing hole (14) is connected with a pressure sensor (15), the leeward side of the probe head (1) back to the spray pipe is provided with a probe rear cover (7), the tail part of a probe support rod is close to a vacuum pump connector (9), and the tail part of the probe support rod is connected with an aviation plug (10);
the diameter D of two semicircles of the probe head (1) is 2-8 mm, the width of the rectangular part is the same as the diameter of the semicircle, the length is 0.5D-3D, a circular pipeline (13) is arranged along the axial inner part, and the diameter of the circular pipeline (13) is 1-7 mm;
the probe head part (1) side arc part is provided with a sonic nozzle (5), the contracted molded line of the nozzle can be a straight line, a Wittonsisky curve or a lemniscate, the section diameter of the projection of the nozzle inlet vertical to the cylinder axis of the probe head part (1) is 0.8-3 mm, the section diameter of the projection of the nozzle outlet vertical to the cylinder axis of the probe head part (1) is 0.4-2 mm, the distance between the nozzle central line and the top end of the probe head part (1) is 2-8 mm, the sonic nozzle (5) is connected with a circular channel (13) through a cylindrical stabilizing section (6), the diameter of the cylindrical stabilizing section (6) is the same as the section diameter of the projection of the nozzle inlet vertical to the cylinder 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 sonic nozzle is a fan ring, the fan ring central angle is 45-90 degrees, the length of the probe rear cover (7) is 2-8 mm, and the central 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 hot 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 hot wire and the axis of the probe is 0-15 degrees;
the fork rod (4) is conical, penetrates through the through hole (11) of the probe head and is connected and insulated with the probe head through an insulating adhesive (12), the inside of the fork rod (4) is connected with a hot wire cable (8), the outside of the fork rod is welded with a hot wire (3), the diameter of the head of the fork rod 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 supporting 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; a vacuum pump connector (9) on the leeward side of the probe supporting rod is connected with a 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, a hot wire cable (8) penetrates through the circular pipeline (13) to be connected with an aviation plug (10), and the diameter of a thread below the aviation plug (10) is 1-6 mm;
the diameter of the pressure sensing hole is 0.1-2 mm, the distance from the center line to the center line of the sonic nozzle is 1-4 mm, the pressure sensor (15) is fixed in a pressure sensor channel (17) in the probe support 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 through the sensor channel (17);
the application process of the invention is as follows: when the probe is not used for sucking air, the pitch angle of incoming flow is measured through the hot wire, then the total pressure, static pressure and deflection angle of the air flow are measured through the pressure sensor, after the direction of the air flow or the change rule of the air flow is determined, the probe is rotated to enable the hot wire and the speed spray pipe to face the incoming flow, the dynamic total temperature of the flow field is further measured, and meanwhile, the Mach number, the static temperature, the speed, the density and the entropy of the flow field can be deduced.
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| CN202210904281.8A CN115435930A (en) | 2022-07-29 | 2022-07-29 | Three-dimensional full-parameter high-frequency probe for measuring interstage |
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| CN202210904281.8A CN115435930A (en) | 2022-07-29 | 2022-07-29 | Three-dimensional full-parameter high-frequency probe for measuring interstage |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115901074A (en) * | 2022-12-13 | 2023-04-04 | 重庆大学 | Movable probe device for measuring pressure in flow channel of spray pipe |
| CN116275763A (en) * | 2023-05-22 | 2023-06-23 | 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 |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111076833A (en) * | 2020-01-14 | 2020-04-28 | 北京航空航天大学 | Double-sleeve hemispherical head total temperature probe with grooves in side surfaces |
| CN111076940A (en) * | 2020-01-14 | 2020-04-28 | 北京航空航天大学 | Prismatic table five-hole probe for measuring dynamic full parameters of subsonic three-dimensional flow field |
| CN111089704A (en) * | 2020-01-20 | 2020-05-01 | 北京航空航天大学 | Probe for measuring whole parameters of transonic three-dimensional steady-state flow field |
| WO2021174681A1 (en) * | 2020-03-06 | 2021-09-10 | 上海海事大学 | Composite five-hole pressure-temperature probe |
| CN218822484U (en) * | 2022-07-29 | 2023-04-07 | 北京航空航天大学 | Three-dimensional full-parameter high-frequency probe for measuring interstage |
-
2022
- 2022-07-29 CN CN202210904281.8A patent/CN115435930A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111076833A (en) * | 2020-01-14 | 2020-04-28 | 北京航空航天大学 | Double-sleeve hemispherical head total temperature probe with grooves in side surfaces |
| CN111076940A (en) * | 2020-01-14 | 2020-04-28 | 北京航空航天大学 | Prismatic table five-hole probe for measuring dynamic full parameters of subsonic three-dimensional flow field |
| CN111089704A (en) * | 2020-01-20 | 2020-05-01 | 北京航空航天大学 | Probe for measuring whole parameters of transonic three-dimensional steady-state flow field |
| WO2021174681A1 (en) * | 2020-03-06 | 2021-09-10 | 上海海事大学 | Composite five-hole pressure-temperature probe |
| CN218822484U (en) * | 2022-07-29 | 2023-04-07 | 北京航空航天大学 | Three-dimensional full-parameter high-frequency probe for measuring interstage |
Non-Patent Citations (1)
| Title |
|---|
| 熊兵;陈洪敏;文璧;张晓东;: "基于四孔压力探针技术的涡轮转子出口流场测量", 燃气涡轮试验与研究, no. 1, 15 December 2012 (2012-12-15) * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115901074A (en) * | 2022-12-13 | 2023-04-04 | 重庆大学 | Movable probe device for measuring pressure in flow channel of spray pipe |
| CN115901074B (en) * | 2022-12-13 | 2024-06-04 | 重庆大学 | Movable probe device for measuring pressure in spray pipe flow channel |
| CN116275763A (en) * | 2023-05-22 | 2023-06-23 | 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 |
| 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 |
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