CN211696953U - Prismatic table five-hole probe for measuring dynamic full parameters of subsonic three-dimensional flow field - Google Patents
Prismatic table five-hole probe for measuring dynamic full parameters of subsonic three-dimensional flow field Download PDFInfo
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- CN211696953U CN211696953U CN202020072594.8U CN202020072594U CN211696953U CN 211696953 U CN211696953 U CN 211696953U CN 202020072594 U CN202020072594 U CN 202020072594U CN 211696953 U CN211696953 U CN 211696953U
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Abstract
The invention belongs to the technical field of turbine test and test, and discloses a prismatic table five-hole probe for measuring dynamic full parameters of a subsonic three-dimensional flow field, which comprises a probe supporting rod, a transition section, a probe head, a pressure sensor cable, a temperature sensor cable, a heat insulation sealing piece and a temperature sensor, wherein the probe supporting rod and the probe head are cylindrical and are connected through the transition section, a pressure measuring lower hole, a pressure measuring left hole, a pressure measuring right hole, a pressure measuring middle hole and a temperature measuring hole are positioned on a prismatic table protruding from the probe head, a groove is formed in the circumference of the temperature measuring hole, and the pressure sensor cable and the temperature sensor cable are led out of the tail of the probe through an inner. The invention can realize dynamic measurement of total pressure, static pressure, deflection angle, pitch angle, Mach number, density and three-dimensional speed at the same point in the flow field and total temperature and static temperature on the premise of reducing the influence of the flow around the probe head, has wider measurement range of the total temperature insensitive angle, and is suitable for measuring the full-parameter dynamic measurement of the three-dimensional flow field between stages of the aero-engine.
Description
Technical Field
The invention relates to the technical field of turbine test and test, in particular to a prismatic table five-hole probe for measuring dynamic full parameters of an subsonic three-dimensional flow field, which is used for dynamically measuring the full parameters of an air inlet channel, an interstage of a gas compressor and an inlet and outlet flow field of the gas compressor of an aircraft engine.
Background
At present, in the field of impeller mechanical testing, particularly in the field of aeroengine flow field testing, pressure probes and temperature probes are widely used for measuring pressure and temperature. Although the total pressure, the static pressure, the mach number and the flow direction can be measured by using the pressure probe, the temperature cannot be measured, and therefore, the flow velocity of the flow field cannot be calculated through data measured by the pressure probe. At present, the total temperature of incoming flow is usually measured by adopting a single total temperature probe, but the synchronous measurement of the total pressure, the static pressure, the pitch angle, the deflection angle, the Mach number, the density, the three-dimensional speed and the total temperature and the static temperature cannot be realized.
Although a few temperature and pressure combined probes exist, a temperature measuring hole and a pressure measuring hole are both in an ┃ -shaped structure which is directly arranged at the head of the probe, a ┃ columnar probe is punched on the wall surface and cannot realize three-dimensional measurement of flow field parameters, the probe capable of realizing the three-dimensional measurement has a one-shaped structure and an L-shaped structure, but the one-shaped probe cannot be installed in narrow space such as an aircraft engine stage for testing, and although the one-shaped probe can be installed at an aircraft engine inlet section, the head of the probe and a support rod can generate great influence on the flow field; the L-shaped probe is difficult to install in a narrow area between stages, and in addition, the bent section of the head part of the L-shaped probe has smaller influence on the head part of the probe and a measured flow field in the measurement process compared with the I-shaped probe, and the influence on the flow field can still cause inaccurate and non-negligible measurement results.
In the aspect of total temperature measurement, the conventional total temperature probe generally adopts a mode of chamfering a temperature measuring hole to enlarge an insensitive angle for temperature measurement, but the range of enlarging the insensitive angle for temperature measurement is limited, so that the measurement requirement of a complex flow field in an aircraft engine is difficult to meet. The existing dynamic measurement probe generally adopts a naked temperature sensor, and the temperature sensor is directly washed by fluid, is easily influenced by oil drops, dust and the like mixed in airflow and is easily damaged, so that the service life of the temperature sensor is shortened.
The inner molded surface of a total pressure hole of the conventional dynamic pressure probe is generally in straight transition, and the straight transition causes certain total pressure loss, so that the measurement result is inaccurate; in addition, straight transitions can lead to flow separation, and fluctuations caused by flow separation can interfere with the total pressure measurement; the total pressure holes and the static pressure holes of the existing dynamic pressure probe are generally formed in curved surfaces such as a cylindrical surface, the front end of the pressure sensor is a plane, therefore, the pressure sensor cannot be flush mounted, the pressure sensor is inevitably sharp after being mounted, flow separation can be caused, the total pressure and static pressure measurement results can be interfered by fluctuation caused by the flow separation, and the measurement results are inaccurate.
In summary, the existing probe applied to the field of testing the flow field of the aero-engine has the following defects: 1. the pressure probe can not realize the measurement of total temperature, static temperature and three-dimensional speed, the total temperature probe can only measure the total temperature of incoming flow, and can not realize the synchronous measurement of total pressure, static pressure, pitch angle, deflection angle, Mach number, density, three-dimensional speed and total temperature and static temperature; 2. in the existing temperature and pressure combined probe, the ┃ type can not realize the measurement of three-dimensional parameters of a flow field, the I type can not be applied to the test of an interstage narrow space of an aeroengine, the bent section of the head part of the L type probe can generate certain influence on the head part of the probe and the flow field to be measured, the measurement result is inaccurate, and the installation of the interstage narrow area is difficult; 3. the conventional total temperature probe generally adopts a mode of chamfering a temperature measuring hole to enlarge an insensitive angle for temperature measurement, but the range of enlarging the insensitive angle for temperature measurement is limited, so that the measurement requirement of a complex flow field in an aircraft engine is difficult to meet; 4. the existing dynamic measurement probe generally adopts a naked temperature sensor, and the temperature sensor is directly washed by fluid, is easily influenced by oil drops, dust and the like mixed in airflow and is easily damaged, so that the service life of the temperature sensor is shortened; 5. the inner molded surface of the total pressure hole of the existing dynamic pressure probe causes total pressure loss and flow separation, so that the total pressure measurement result is inaccurate, the matching of the opening surfaces of the total pressure hole and the static pressure hole and the pressure sensor also causes flow separation, and the measurement precision of the total pressure and the static pressure is reduced by the fluctuation caused by the flow separation.
Disclosure of Invention
The invention aims to solve the problems that the pressure probe in the prior probe three-dimensional testing field can not realize the measurement of total temperature, static temperature and three-dimensional speed, the total temperature probe can only measure the total temperature of incoming flow, and can not realize the synchronous measurement of total pressure, static pressure, pitch angle, deflection angle, Mach number, density, three-dimensional speed, total temperature and static temperature, the head of the prior temperature and pressure combined probe is wound to influence the measured flow field to cause inaccurate measurement result and difficult installation on a narrow area between stages, the prior total temperature probe generally adopts a temperature measuring hole chamfer mode to enlarge the insensitive angle range of temperature measurement to be limited, the dynamic total temperature measuring probe adopts an exposed temperature sensor to cause that the temperature sensor is directly washed by fluid and is easily damaged by oil drops, dust and the like mixed in the air flow, the internal profile of the total pressure hole of the dynamic pressure probe causes the inaccurate total pressure measurement result, and the configuration of the opening surface of the pressure hole and the pressure sensor is formed by the total pressure hole and the static pressure hole The resultant flow separation creates problems that reduce the accuracy of the total pressure and static pressure measurements.
Aiming at the defects in the prior art, the invention provides the frustum pyramid five-hole probe for measuring the dynamic full parameters of the subsonic three-dimensional flow field, the frustum pyramid structure with the protruding head can reduce the influence of the head flow of the probe on the measurement result of the probe, the pressure measuring holes are formed in all surfaces of the frustum pyramid, the measurement of the total pressure, the static pressure, the deflection angle, the pitch angle, the mach number, the density and the three-dimensional speed of the interstage flow field of the aero-engine can be realized, the grooves are formed around the temperature measuring holes, the insensitive angle range of the total temperature measurement is enlarged, the temperature sensor is positioned in the containing cavity in the head of the probe, compared with the existing dynamic total temperature measuring probe directly exposing the temperature sensor, the temperature sensor can be prevented from being directly washed by fluid and is not easy to be damaged by the influence of oil drops, dust and the like mixed in the airflow, the interior of the total pressure holes adopts a, the precision of total pressure measurement is improved, total pressure hole and static pressure hole are seted up on the terrace with edge surface, because the trompil face is the plane, can realize flushing installation of pressure sensor, reduced the flow separation, pressure measurement is more accurate.
In order to solve the technical problems, the technical scheme provided by the invention is as follows:
a prismatic table five-hole probe for measuring dynamic full parameters of a subsonic three-dimensional flow field is characterized by comprising a probe supporting rod (1), a transition section (2), a probe head (3), a pressure sensor cable (12), a temperature sensor cable (13), a heat insulation sealing element (14) and a temperature sensor (15), wherein the probe supporting rod (1) and the probe head (3) are cylindrical, and the probe head (3) is connected to the probe supporting rod (1) through the transition section (2); a protruding prismatic table structure is arranged on the probe head (3), a pressure measuring lower hole (4), a pressure measuring right hole (5), a pressure measuring left hole (6), a pressure measuring middle hole (7) and a temperature measuring hole (8) are located on the prismatic table of the probe head (3), the central lines of all the pressure measuring holes are perpendicular to the prismatic table surface where the pressure measuring holes are located, an upper groove (9), a right groove (10) and a left groove (11) are formed in the circumference of the temperature measuring hole (8), and a pressure sensor cable (12) and a temperature sensor cable (13) are led out of the tail portion of the probe through a channel in a probe supporting rod (1).
Preferably, the temperature measuring hole (8) is located right above the pressure measuring middle hole (7), the center lines of the pressure measuring right hole (5), the pressure measuring left hole (6) and the pressure measuring middle hole (7) are located on the same plane, the pressure measuring lower hole (4) is located on the frustum slope below the pressure measuring middle hole (7), the connecting line of the pressure measuring lower hole (4) and the center of the pressure measuring middle hole (7) and the connecting line of the pressure measuring middle hole (7) and the center of the temperature measuring hole (8) are located on the same plane, the distances from the pressure measuring right hole (5) and the pressure measuring left hole (6) to the left side and the right side of the plane where the pressure measuring lower hole (4) is located are equal, and the distances from the pressure measuring lower hole (.
Preferably, the diameters of the pressure measuring lower hole (4), the pressure measuring right hole (5), the pressure measuring left hole (6) and the pressure measuring middle hole (7) are the same and are all 0.2-2 mm, and the inlet wall surface of the pressure measuring middle hole (7) adopts a micro-damage convergent curved surface for smooth transition; (ii) a The diameter of the temperature measuring hole (8) is 0.3-5 mm, and the distance between the temperature measuring hole (8) and the pressure measuring middle hole (7) is 1.1-1.2 times of the diameter of the pressure measuring middle hole (7). The width of the notch of the temperature measuring hole (8) is 1/4 of the diameter of the temperature measuring hole (8), the length of the notch on the side surface of the prism table is 0.5-0.6 times of the height of the prism table, and the distance from the temperature sensor (15) to the temperature measuring hole is 0.4-0.5 times of the diameter of the probe.
Preferably, the height of the protruded frustum pyramid is 0.2-0.3 times of the diameter of the probe, the bottom surface of the frustum pyramid is tangent to the cylindrical surface of the head of the probe, the length of the frustum pyramid along the axial direction of the probe is 5-10 mm, the length of the other edge of the bottom surface of the frustum pyramid is 1/8-1/6 times of the circumference of the head of the probe, and the included angle between the lateral edge of the frustum pyramid and the top surface of the frustum pyramid is 120-150 degrees.
Preferably, the temperature sensor (15) is located inside a cylindrical cavity of the head of the probe, and the diameter of the cylindrical cavity is 1/6-1/5 times of the diameter of the head of the probe.
Preferably, the probe supporting rod (1) is of a cylindrical structure and plays a role in supporting, a channel is formed in the probe supporting rod (1), the pressure sensor cable (12) and the temperature sensor cable (13) are led out of the tail portion of the probe through the channel in the probe supporting rod (1), and the diameter of the probe supporting rod (1) is 6-8 mm.
Preferably, the temperature sensor (15) can be selected from a thermocouple, a thermal resistor or a fiber optic temperature sensor.
Preferably, through wind tunnel calibration, calibration and data processing, the frustum of pyramid five-hole probe for measuring the dynamic full parameters of the subsonic three-dimensional flow field can realize dynamic measurement of total pressure, static pressure, pitch angle, deflection angle, Mach number, density, three-dimensional speed, total temperature and static temperature at the same point in the flow field on the premise of reducing the influence of the head flow around of the probe, has a wider insensitive angle for measuring the total temperature, and can realize high-precision total pressure measurement.
The invention has the advantages and positive effects that:
the beneficial effects are that: compared with the existing I-shaped probe which directly punches on the side surface of a probe cylinder, the frustum structure protruding at the head of the frustum-shaped probe for measuring the dynamic full parameters of the subsonic three-dimensional flow field in the invention, can realize the three-dimensional measurement of the flow field parameters, compared with the existing one-shaped probe structure which is usually adopted for realizing the three-dimensional measurement and is provided with a hole on the top round platform, because the pressure measuring hole and the temperature measuring hole are positioned on the side surface of the probe, the probe is convenient to be arranged in narrow space such as an aircraft engine interstage and the like for testing, compared with the existing L-shaped probe structure which can realize three-dimensional testing of a flow field, because the size of the raised frustum pyramid structure at the head part of the probe is smaller than that of the bending section of the L-shaped probe, the frustum pyramid structure is more convenient to be arranged in a narrow area between stages, compared with the L-shaped probe, the probe has smaller influence on the head part and the flow field of the probe, and the accuracy of the test result is improved.
The beneficial effects are that: compared with the prior art, the prismatic table five-hole probe for measuring the dynamic full parameters of the subsonic three-dimensional flow field has the advantages that the grooves are formed around the temperature measuring holes, and when a main flow enters from the temperature measuring holes, the grooves can realize convective heat transfer aiming at the flow field with a complex incoming flow direction, so that the insensitive angle of temperature measurement is enlarged; the slotting part can realize air intake and exhaust in a self-adaptive manner, for example, when the main flow is opposite to the slotting at a certain time in a complex flow field, air is intake in the area, and the rest slotting area and the temperature measuring hole part can realize exhaust. Therefore, the heat convection is enhanced by slotting around the temperature measuring holes, so that the temperature measuring device has a wide total temperature measurement insensitive angle and improves the temperature measurement precision.
The beneficial effects are three: the temperature sensor is positioned in the cavity inside the probe head, and compared with the conventional dynamic total temperature measuring probe directly exposed out of the temperature sensor, the temperature sensor can be prevented from being directly washed by fluid and is not easily damaged due to the influence of oil drops, dust and the like mixed in airflow.
Compared with the prior art, the frustum-shaped five-hole probe for measuring the full dynamic parameters of the subsonic three-dimensional flow field can realize the synchronous measurement of total pressure, static pressure, pitch angle, deflection angle, Mach number, three-dimensional speed, total temperature and static temperature in the subsonic flow field test of the aircraft engine, namely the three-dimensional dynamic measurement of the full parameters of the subsonic flow field.
The beneficial effects are five: the interior of the total pressure hole adopts micro-loss convergent curved surface smooth transition, compared with the existing total pressure hole adopting straight transition, the total pressure loss and flow separation can be obviously reduced, the accuracy of total pressure measurement is improved, the total pressure hole and the static pressure hole are arranged on the surface of the prismatic table, compared with the existing pressure probe, because each surface of the prismatic table is a plane, the pressure sensor is generally a cylinder, the front end of the pressure sensor is a plane when the pressure sensor is installed, the flush installation of the pressure sensor can be realized when the opening surface is a plane, the flow separation is reduced, and the measurement of the total pressure and the static pressure is more accurate.
The invention has the characteristics of realizing dynamic measurement of total pressure, static pressure, pitch angle, deflection angle, Mach number, density, three-dimensional speed, total temperature and static temperature at the same point in a flow field on the premise of reducing the influence of the circumfluence of the probe head, having a wider insensitive angle for measuring the total temperature and realizing the measurement of the total pressure with higher precision.
Drawings
FIG. 1 is a front view of a probe structure according to an embodiment of the present invention.
FIG. 2 is a top view of a probe structure according to an embodiment of the invention.
FIG. 3 is a cross-sectional view of a prism structure of a probe structure according to an embodiment of the present invention.
FIG. 4 is a diagram of a pressure sensor cable channel arrangement according to an embodiment of the present invention.
FIG. 5 is a pressure measuring mesopore entrance section profile definition in accordance with an embodiment of the present invention.
FIG. 6 is a diagram of a probe installation according to an embodiment of the present invention.
FIG. 7 is a front view of a second probe structure according to an embodiment of the present invention.
FIG. 8 is a top view of a second probe structure according to an embodiment of the present invention.
FIG. 9 is a cross-sectional view of a prism structure of a second probe structure according to an embodiment of the present invention.
FIG. 10 is a diagram of a cable channel layout for a second pressure sensor in accordance with an embodiment of the present invention.
FIG. 11 is a pressure mesopore entrance section profile definition according to example two of the present invention.
FIG. 12 is a diagram of a probe installation according to an embodiment of the present invention.
Reference numbers and corresponding part and surface designations in the drawings: comprises 1-a probe supporting rod; 2-a transition section; 3-probe head; 4-measuring the pressure and discharging the hole; 5-pressure measurement of a right hole; 6-left hole for pressure measurement; 7-pressure measuring mesopores; 8-temperature measuring holes; 9-upper groove; 10-right groove; 11-left groove; 12-a pressure sensor cable; 13-temperature sensor cable; 14-a heat insulating seal; 15-temperature sensor.
Detailed Description
The invention aims to provide a frustum pyramid five-hole probe for measuring dynamic full parameters of an subsonic three-dimensional flow field, and aims to solve the problems that the head of the probe has large influence on the accuracy of a measurement result and the temperature measurement is insensitive to a small angle in the field of the current aeroengine flow field test.
The invention is described in detail below with reference to the drawings and examples so that the advantages and features of the invention may be more readily understood by those skilled in the art, and the scope of the invention will be clearly and clearly defined.
The first embodiment is as follows:
in the embodiment, the probe is used for the full parameter test of the compressor interstage flow field, and the probe is convenient to install due to the fact that the compressor interstage space is narrow and the probe is small in structural size.
As shown in fig. 1, fig. 2, fig. 3 and fig. 4, the embodiment describes a frustum pyramid five-hole probe for measuring dynamic full parameters of a subsonic three-dimensional flow field, which includes a probe support rod (1), a transition section (2), a probe head (3), a pressure sensor cable (12), a temperature sensor cable (13), a heat insulation sealing member (14) and a temperature sensor (15), wherein the probe support rod (1) and the probe head (3) are both cylindrical, and the probe head (3) is connected to the probe support rod (1) through the transition section (2); a protruding prismatic table structure is arranged on the probe head (3), a pressure measuring lower hole (4), a pressure measuring right hole (5), a pressure measuring left hole (6), a pressure measuring middle hole (7) and a temperature measuring hole (8) are located on the prismatic table of the probe head (3), the central lines of all the pressure measuring holes are perpendicular to the prismatic table surface where the pressure measuring holes are located, an upper groove (9), a right groove (10) and a middle groove (11) are formed in the circumference of the temperature measuring hole (8), and a pressure sensor cable (12) and a temperature sensor cable (13) are led out of the tail portion of the probe through a channel in a probe supporting rod (1).
In the embodiment, the temperature measuring hole (8) is positioned right above the pressure measuring middle hole (7), the pressure measuring right hole (5), the pressure measuring left hole (6) and the center line of the pressure measuring middle hole (7) are positioned on the same plane, the pressure measuring lower hole (4) is positioned on the frustum slope below the pressure measuring middle hole (7), the connecting line of the pressure measuring lower hole (4) and the center of the pressure measuring middle hole (7) and the connecting line of the pressure measuring middle hole (7) and the center of the temperature measuring hole (8) are positioned on the same plane, the distances from the pressure measuring right hole (5) and the pressure measuring left hole (6) to the left side and the right side of the plane where the pressure measuring lower hole (4) is positioned are equal, and the distances from the pressure measuring lower.
In the embodiment, the diameters of the pressure measuring lower hole (4), the pressure measuring right hole (5), the pressure measuring left hole (6) and the pressure measuring middle hole (7) are the same and are all 2mm, and the inlet wall surface of the pressure measuring middle hole (7) adopts a micro-damage convergent curved surface for smooth transition; (ii) a The diameter of the temperature measuring hole (8) is 3mm, and the distance between the temperature measuring hole (8) and the pressure measuring middle hole (7) is 1.1 times of the diameter of the pressure measuring middle hole (7). The width of the slot of the temperature measuring hole (8) is 1/4 of the diameter of the temperature measuring hole (8), the length of the slot on the side surface of the prism table is 0.5 time of the height of the prism table, and the distance from the temperature sensor (15) to the temperature measuring hole is 0.4 time of the diameter of the probe.
In this embodiment, the height of the protruded frustum pyramid is 0.2 times of the diameter of the probe, the bottom surface of the frustum pyramid is tangent to the cylindrical surface of the head of the probe, the length along the axial direction of the probe is 10mm, the length of the other edge of the bottom surface of the frustum pyramid is 1/6 times of the circumference of the head of the probe, and the included angle between the lateral edge of the frustum pyramid and the top surface of the frustum pyramid is 120 °.
In this embodiment, the temperature sensor (15) is located inside a cylindrical cavity in the head of the probe, the diameter of the cylindrical cavity being 1/6 times the diameter of the head of the probe.
In this embodiment, probe branch (1) is cylindrical structure, plays the supporting role, and probe branch (1) is inside to be opened there is the passageway, and pressure sensor cable (12) and temperature sensor cable (13) are through probe branch (1) interior passageway extraction probe afterbody, and probe branch (1) diameter is 6 mm.
In the embodiment, the temperature sensor (15) can be a thermocouple, a thermal resistor or a fiber optic temperature sensor.
FIG. 5 is a profile definition diagram of the inlet section of the pressure measuring mesopore, the following formula is a profile curve equation of a micro-loss convergent surface adopted for designing the inlet wall surface of the pressure measuring mesopore (7), and a connection point xm0.3 was chosen.
In the formula, R2Is the exit radius, L is the length of the pressure measuring central hole entrance section, R1Is the inlet radius, xmThe coordinates of the connecting points of the front section and the rear section.
The invention relates to a prismatic table five-hole probe for measuring dynamic full parameters of an subsonic three-dimensional flow field, which applies the characteristics of a fluid circumfluence probe, measures the pressure distribution on the surface of the probe by using a pressure measuring hole on the windward side of the surface of the probe, measures the total temperature of airflow by using a temperature sensor in a temperature measuring hole on the surface of the probe, and calculates the full parameters of the interstage three-dimensional flow field of a compressor by using a calibration coefficient obtained by standard wind tunnel calibration. The specific use method is as follows:
the probe of the invention needs to be calibrated before use, and a pneumatic calibration curve of the probe is obtained. The probe calibration is carried out in a calibration wind tunnel, the deflection angle and the pitch angle of the probe are changed within a calibration range under different Mach numbers, and a change curve of each calibration coefficient along with the deflection angle, the pitch angle and the Mach number can be obtained through pneumatic calibration; the calibration coefficients comprise a deflection angle coefficient, a pitch angle coefficient, a total pressure coefficient, a static pressure coefficient and a temperature recovery coefficient, and are defined as follows:
wherein, CpyCoefficient of deflection angle, CppCoefficient of deflection angle, CptIs the total pressure coefficient, CpsIs a static pressure coefficient, CTFor the recovery of coefficient of temperature, Pt、PsAnd Tt、TsRespectively calibrating the total pressure, static pressure, total temperature and static temperature of the wind tunnel incoming flow, P1、P2、P3、P4Respectively the pressure values measured by a pressure measuring middle hole, a pressure measuring left hole, a pressure measuring right hole and a pressure measuring lower hole, TpIs the temperature value measured by the temperature sensor.
As shown in FIG. 6, the flow field of the prismatic table five-hole probe for measuring the dynamic full parameters of the subsonic three-dimensional flow field is measured, the pressure measuring middle hole (7) faces to the incoming flow direction, and the central line of the probe supporting rod (1) is perpendicular to the incoming flow direction. The pressure measuring holes (7) in the probe head can measure the total pressure of incoming flow, the temperature measuring holes (8) can measure the total temperature of the incoming flow, and the deflection angle, the pitch angle, the total pressure, the static pressure and the Mach number are obtained through interpolation according to the pressure measured by the three pressure measuring holes, namely the pressure measuring lower hole (4), the pressure measuring right hole (5) and the pressure measuring left hole (6) and by combining with a known calibration coefficient curve. The incoming flow velocity is solved according to the following formula:
c2＝γRTs
PS＝ρRTS
wherein, PtAnd PsIs total pressure and static pressure of the flow field, gamma is adiabatic index of the flow field, TtAnd TsThe total temperature and the static temperature of the flow field, Ma is the Mach number of the flow field, v is the flow field velocity, rho is the density, c is the local acoustic velocity of the flow field, and R is the gas constant. And calculating the static temperature of the incoming flow according to the total temperature of the incoming flow, the adiabatic index and the Mach number.
Example two:
in the embodiment, the probe is used for measuring the full parameters of the outlet flow field of the compressor, and the size of the probe is determined according to the structural parameter range of the probe determined by the invention in order to ensure the rigidity and the strength of the probe and properly increase the structural size of the selected probe due to the large space of the outlet area of the compressor.
As shown in fig. 7, 8, 9 and 10, the embodiment describes a frustum pyramid five-hole probe for measuring dynamic full parameters of a subsonic three-dimensional flow field, which includes a probe support rod (1), a transition section (2), a probe head (3), a pressure sensor cable (12), a temperature sensor cable (13), a heat insulation sealing member (14) and a temperature sensor (15), wherein the probe support rod (1) and the probe head (3) are both cylindrical, and the probe head (3) is connected to the probe support rod (1) through the transition section (2); a protruding prismatic table structure is arranged on the probe head (3), a pressure measuring lower hole (4), a pressure measuring right hole (5), a pressure measuring left hole (6), a pressure measuring middle hole (7) and a temperature measuring hole (8) are located on the prismatic table of the probe head (3), the central lines of all the pressure measuring holes are perpendicular to the prismatic table surface where the pressure measuring holes are located, an upper groove (9), a right groove (10) and a left groove (11) are formed in the circumference of the temperature measuring hole (8), and a pressure sensor cable (12) and a temperature sensor cable (13) are led out of the tail portion of the probe through an inner channel of a probe supporting rod (1).
In the embodiment, the temperature measuring hole (8) is positioned right above the pressure measuring middle hole (7), the center lines of the pressure measuring right hole (5), the pressure measuring left hole (6) and the pressure measuring middle hole (7) are positioned on the same plane, the pressure measuring lower hole (4) is positioned on the frustum slope below the pressure measuring middle hole (7), the connecting line of the pressure measuring lower hole (4) and the center of the pressure measuring middle hole (7) and the connecting line of the pressure measuring middle hole (7) and the center of the temperature measuring hole (8) are positioned on the same plane, the distances from the pressure measuring right hole (5) and the pressure measuring left hole (6) to the left side and the right side on the surface where the pressure measuring lower hole (4) is positioned are equal, and the distances from the upper side and.
In the embodiment, the diameters of the pressure measuring lower hole (4), the pressure measuring right hole (5), the pressure measuring left hole (6) and the pressure measuring middle hole (7) are the same and are 2mm, and the inlet wall surface of the pressure measuring middle hole (7) adopts bicubic curve transition; the diameter of the temperature measuring hole (8) is 3mm, and the distance between the temperature measuring hole (8) and the pressure measuring middle hole (7) is 1.1 times of the diameter of the pressure measuring middle hole (7). The width of the slot of the temperature measuring hole (8) is 1/4 of the diameter of the temperature measuring hole (8), the length of the slot on the side surface of the prism table is 0.5 time of the height of the prism table, and the distance from the temperature sensor (15) to the temperature measuring hole is 0.4 time of the diameter of the probe.
In this embodiment, the height of the protruded frustum pyramid is 0.2 times of the diameter of the probe, the bottom surface of the frustum pyramid is tangent to the cylindrical surface of the head of the probe, the length along the axial direction of the probe is 10mm, the length of the other edge of the bottom surface of the frustum pyramid is 1/6 times of the circumference of the head of the probe, and the included angle between the lateral edge of the frustum pyramid and the top surface of the frustum pyramid is 120 °.
In this embodiment, the temperature sensor (15) is located inside a cylindrical cavity in the head of the probe, the diameter of the cylindrical cavity being 1/6 times the diameter of the head of the probe.
In this embodiment, probe branch (1) is cylindrical structure, plays the supporting role, and probe branch (1) is inside to be opened there is the passageway, and pressure sensor cable (12) and temperature sensor cable (13) are through probe branch (1) interior passageway extraction probe afterbody, and probe branch (1) diameter is 8 mm.
In the embodiment, the temperature sensor (15) can be a thermocouple, a thermal resistor or a fiber optic temperature sensor.
FIG. 11 is a profile definition diagram of the inlet section of the pressure measuring mesopore, the following formula is a profile curve equation of a micro-loss convergent surface adopted for designing the inlet wall surface of the pressure measuring mesopore (7), and a connection point xm0.3 was chosen.
In the formula, R2Is the exit radius, L is the length of the pressure measuring central hole entrance section, R1Is the inlet radius, xmThe coordinates of the connecting points of the front section and the rear section.
The invention relates to a prismatic table five-hole probe for measuring dynamic full parameters of an subsonic three-dimensional flow field, which applies the characteristics of a fluid circumfluence probe, measures the pressure distribution on the surface of the probe by using a pressure measuring hole on the windward side of the surface of the probe, measures the total temperature of airflow by using a temperature sensor in a temperature measuring hole on the surface of the probe, and calculates the full parameters of the interstage three-dimensional flow field of a compressor by using a calibration coefficient obtained by standard wind tunnel calibration. The specific use method is as follows:
the probe of the invention needs to be calibrated before use, and a pneumatic calibration curve of the probe is obtained. The probe calibration is carried out in a calibration wind tunnel, the deflection angle and the pitch angle of the probe are changed within a calibration range under different Mach numbers, and a change curve of each calibration coefficient along with the deflection angle, the pitch angle and the Mach number can be obtained through pneumatic calibration; the calibration coefficients comprise a deflection angle coefficient, a pitch angle coefficient, a total pressure coefficient, a static pressure coefficient and a temperature recovery coefficient, and are defined as follows:
wherein, CpyCoefficient of deflection angle, CppCoefficient of deflection angle, CptIs the total pressure coefficient, CpsIs a static pressure coefficient, CTFor the recovery of coefficient of temperature, Pt、PsAnd Tt、TsRespectively calibrating the total pressure, static pressure, total temperature and static temperature of the wind tunnel incoming flow, P1、P2、P3、P4Respectively the pressure values measured by a pressure measuring middle hole, a pressure measuring left hole, a pressure measuring right hole and a pressure measuring lower hole, TpIs the temperature value measured by the temperature sensor.
As shown in fig. 12, in the measured flow field of the prismatic table five-hole probe for measuring the dynamic full parameters of the subsonic three-dimensional flow field, the pressure measuring middle hole (7) faces to the incoming flow direction, and the central line of the probe supporting rod (1) is perpendicular to the incoming flow direction. The pressure measuring holes (7) in the probe head can measure the total pressure of incoming flow, the temperature measuring holes (8) can measure the total temperature of the incoming flow, and the deflection angle, the pitch angle, the total pressure, the static pressure and the Mach number are obtained through interpolation according to the pressure measured by the three pressure measuring holes, namely the pressure measuring lower hole (4), the pressure measuring right hole (5) and the pressure measuring left hole (6) and by combining with a known calibration coefficient curve. The incoming flow velocity is solved according to the following formula:
c2＝γRTs
PS＝ρRTS
wherein, PtAnd PsIs total pressure and static pressure of the flow field, gamma is adiabatic index of the flow field, TtAnd TsThe total temperature and the static temperature of the flow field, Ma is the Mach number of the flow field, v is the flow field velocity, rho is the density, c is the local acoustic velocity of the flow field, and R is the gas constant.
Although preferred embodiments have been described, various modifications and substitutions may be made thereto without departing from the spirit and scope of the invention. Accordingly, it is to be understood that the present invention has been described by way of illustration and not limitation.
Claims (1)
1. A prismatic table five-hole probe for measuring dynamic full parameters of a subsonic three-dimensional flow field is characterized by comprising a probe supporting rod (1), a transition section (2), a probe head (3), a pressure sensor cable (12), a temperature sensor cable (13), a heat insulation sealing element (14) and a temperature sensor (15), wherein the probe supporting rod (1) and the probe head (3) are cylindrical, and the probe head (3) is connected to the probe supporting rod (1) through the transition section (2); a protruding prismatic table structure is arranged on the probe head (3), a pressure measuring lower hole (4), a pressure measuring right hole (5), a pressure measuring left hole (6), a pressure measuring middle hole (7) and a temperature measuring hole (8) are positioned on the prismatic table of the probe head (3), the central lines of all the measuring holes are perpendicular to the prismatic table surface where the measuring holes are positioned, an upper groove (9), a right groove (10) and a left groove (11) are formed in the circumference of the temperature measuring hole (8), and a pressure sensor cable (12) and a temperature sensor cable (13) are led out of the tail part of the probe through a channel in the probe supporting rod (1);
the temperature measuring hole (8) is positioned right above the pressure measuring middle hole (7), the center lines of the pressure measuring right hole (5), the pressure measuring left hole (6) and the pressure measuring middle hole (7) are positioned on the same plane, the pressure measuring lower hole (4) is positioned on the frustum slope below the pressure measuring middle hole (7), the connecting line of the pressure measuring lower hole (4) and the pressure measuring middle hole (7) and the connecting line of the pressure measuring middle hole (7) and the temperature measuring hole (8) are positioned on the same plane, the distances from the pressure measuring right hole (5) and the pressure measuring left hole (6) to the left side and the right side of the surface where the pressure measuring lower hole (4) is positioned are equal, and the distances from the pressure measuring lower hole (4) to the upper;
the diameters of the pressure measuring lower hole (4), the pressure measuring right hole (5), the pressure measuring left hole (6) and the pressure measuring middle hole (7) are the same and are all 0.2-2 mm, and the inlet wall surface of the pressure measuring middle hole (7) adopts a micro-damage convergent curved surface for smooth transition; the diameter of the temperature measuring hole (8) is 0.3-5 mm, the distance between the temperature measuring hole (8) and the pressure measuring mesopore (7) is 1.1-1.2 times of the diameter of the pressure measuring mesopore (7), the width of a notch of the temperature measuring hole (8) is 1/4 times of the diameter of the temperature measuring hole (8), the length of the notch on the side surface of the prismatic table is 0.5-0.6 times of the height of the prismatic table, and the distance from the temperature sensor (15) to the temperature measuring hole is 0.4-0.5 times of the diameter of the probe;
the height of the protruded frustum pyramid is 0.2-0.3 times of the diameter of the probe, the bottom surface of the frustum pyramid is tangent to the cylindrical surface of the head of the probe, the length of the frustum pyramid along the axial direction of the probe is 5-10 mm, the length of the other edge of the bottom surface of the frustum pyramid is 1/8-1/6 times of the circumference of the head of the probe, and the included angle between the lateral edge of the frustum pyramid and the top surface of the frustum pyramid is 120-150 degrees;
the temperature sensor (15) is positioned in a cylindrical cavity at the head of the probe, and the diameter of the cylindrical cavity is 1/6-1/5 times of the diameter of the head of the probe;
the probe supporting rod (1) is of a cylindrical structure and plays a role in supporting, a channel is formed in the probe supporting rod (1), a pressure sensor cable (12) and a temperature sensor cable (13) are led out of the tail of the probe through the channel in the probe supporting rod (1), and the diameter of the probe supporting rod (1) is 6-8 mm;
the temperature sensor (15) can be selected from a thermocouple, a thermal resistor or a fiber optic temperature sensor.
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