CN111089701A - Multi-point full-parameter long-life measuring device for supersonic two-dimensional steady-state flow field - Google Patents
Multi-point full-parameter long-life measuring device for supersonic two-dimensional steady-state flow field Download PDFInfo
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- CN111089701A CN111089701A CN202010063666.7A CN202010063666A CN111089701A CN 111089701 A CN111089701 A CN 111089701A CN 202010063666 A CN202010063666 A CN 202010063666A CN 111089701 A CN111089701 A CN 111089701A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
- G01M9/065—Measuring arrangements specially adapted for aerodynamic testing dealing with flow
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- G—PHYSICS
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- 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
- G01D21/00—Measuring or testing not otherwise provided for
- G01D21/02—Measuring two or more variables by means not covered by a single other subclass
Abstract
The invention belongs to the technical field of flow field testing, and particularly relates to a multi-point full-parameter long-life measuring device for a supersonic two-dimensional flow field. After the device is calibrated through the calibration wind tunnel, a device calibration curve can be obtained; in actual measurement, based on data measured by the pressure measuring holes and the temperature sensor, total temperature, total pressure, static temperature, static pressure, Mach number, deflection angle, speed and density parameters of a measured two-dimensional steady-state flow field can be obtained simultaneously through data processing according to a calibration coefficient curve and a formula obtained by calibrating the wind tunnel, the service life of the temperature sensor is prolonged, the insensitive angle range of airflow is enlarged, and the measurement spatial resolution and the measurement precision are improved.
Description
Technical Field
The invention belongs to the technical field of flow field testing, and particularly relates to a multi-point full-parameter long-life measuring device for a supersonic two-dimensional steady-state flow field, which is suitable for multi-point measurement of full parameters such as total temperature, total pressure, static temperature, static pressure, Mach number, deflection angle, speed and density of a two-dimensional complex flow field of an air inlet channel, an air compressor, a turbine and the like of an aircraft engine.
Background
An aircraft engine is a complex power machine, a supersonic region exists in a flow field inside a modern aircraft engine, and severe working conditions also put higher requirements on a testing technology. In order to improve the design level of modern aircraft engines and strengthen the knowledge of internal flow fields, the supersonic flow fields need to be subjected to total temperature, total pressure, static temperature, static pressure, Mach number, deflection angle, speed and density full-parameter multipoint measurement.
Most of the existing measuring devices aim at subsonic flow fields, and in order to adapt to the characteristics of the subsonic flow fields, the existing measuring devices are generally cylindrical in shape. However, the cylindrical measuring device can cause large loss of detached shock waves in the supersonic flow field, which not only can generate large interference to the measured flow field, but also can affect the measuring precision of the measuring device, so that the measuring requirement of the supersonic flow field cannot be met.
When a conventional measuring device measures a plurality of parameters, a temperature measuring device and a pressure measuring device are generally used to measure a temperature parameter and a pressure parameter, respectively. The single device is also used for measuring the single parameter separately, the measuring mode increases the number of the measuring devices on one hand, and then increases the interference to the measured flow field, on the other hand, increases the complexity of the test and the cost of the test, and most importantly, the flow parameters measured by different measuring devices cannot be guaranteed to come from the same flow line, so that the spatial resolution of the measuring devices is greatly reduced, and the precision of the test is reduced.
Most of the existing measuring devices are single-point measurement, and when measuring multi-point parameters, a plurality of measuring devices need to be used simultaneously or the measuring devices need to be driven by a displacement mechanism to move for measurement. Meanwhile, the use of a plurality of measuring devices not only increases the cost of test and test, but also blocks the flow field and influences the measurement precision. The displacement mechanism drives the measuring device to cause time difference between multi-point measuring results, and the simultaneous multi-point measurement of the flow field cannot be realized. In addition, for supersonic flow field measurement, the measuring device is easily damaged by high-speed airflow impact, which requires the test process time to be as short as possible, so that simultaneous measurement of multiple parameters is more important for supersonic flow field test.
According to the design concept of the existing total temperature measuring device, the key of the temperature measuring device for accurately measuring the total temperature of the airflow lies in whether the airflow can be absolutely stagnant at a temperature measuring point or not, therefore, most of the existing temperature measuring devices are designed according to the requirement that a temperature sensor is over against a main stream, the head of the temperature measuring device adopts a stagnant cover structure to collect incoming flow, and the temperature sensor is placed in the stagnant cover; secondly, the strength of the sensor is generally improved by increasing the size of the temperature sensor, and the size of the stagnation cover is added, so that the size of the measuring device is large, and the spatial resolution of the measuring device is poor; thirdly, the insensitive angle of the airflow is small, and when the deflection angle of the incoming flow to be measured is large, the airflow cannot be fully stagnated, so that the surface heat exchange of the temperature sensor is insufficient, and the total temperature measurement error is large.
The existing temperature and pressure combined measuring device has the defects that the temperature sensor is over against the main flow, and the measurement result is not a single streamline parameter and is difficult to meet the measurement requirement under the severe condition of an ultrasonic flow field, so that a multipoint all-parameter long-life measuring device for a supersonic two-dimensional stable flow field is urgently needed, and is used for simultaneously measuring the total temperature, the total pressure, the static temperature, the static pressure, the Mach number, the deflection angle, the speed and the density of two-dimensional complex flow fields of an air inlet passage, an air compressor, a turbine and the like of an aircraft engine at multiple points.
Disclosure of Invention
The invention discloses a multi-point full-parameter long-life measuring device for a supersonic two-dimensional steady-state flow field, which is different from the design of a cylindrical head of a subsonic measuring device. Compared with the single-point measurement of the traditional measuring device, the head of the device provided by the invention contains a plurality of test units, so that the function of simultaneously testing multiple points by using a single measuring device is realized. In addition, the design idea of the traditional total temperature measuring device is abandoned, and based on years of research of the applicant, the invention creatively provides the layout and the structural design of placing the temperature sensor on the leeward side of the head of the probe, thereby effectively reducing the impact of the air flow on the temperature sensor caused by scouring of the temperature sensor and the influence of oil drops, dust and the like mixed in the air flow on the temperature sensor, greatly prolonging the service life of the temperature sensor and adapting to the requirements of supersonic speed testing of a flow field; the size of the head of the measuring device is effectively reduced, and the spatial resolution of the measuring device is improved; the convection heat transfer between the air flow and the temperature sensor is enhanced, and the temperature recovery coefficient is high and stable within a larger deflection angle range. Most importantly, the multipoint all-parameter long-life measuring device for the supersonic two-dimensional steady-state flow field can simultaneously measure the total temperature, the total pressure, the static temperature, the static pressure, the Mach number, the deflection angle, the speed and the density of multiple points of the two-dimensional steady-state supersonic flow field by adopting a single device.
The invention provides a multi-point full-parameter long-life measuring device for a supersonic two-dimensional steady-state flow field, which aims to solve the technical problems that: firstly, the existing measuring device cannot simultaneously measure all parameters of two-dimensional steady-state flow field total temperature, total pressure, static temperature, static pressure, Mach number, deflection angle, speed, density and the like at a plurality of spatial positions; secondly, the temperature sensor of the existing temperature measuring device is easy to damage and short in service life; thirdly, the existing measuring device has the problems of large size and poor spatial resolution; fourthly, the problem of small insensitive angle of airflow of the existing temperature measuring device is solved.
The technical scheme of the invention is as follows:
1. the utility model provides a multiple spot holoparameter long-life measuring device for supersonic speed two-dimensional steady state flow field, by device head (1), device branch (2) are constituteed, wherein device head (1) contains 3 ~ 9 test unit, every test unit contains temperature sensor (3), adiabatic insulating seal (4), temperature sensor cable draws forth passageway (5), pressure measurement mesopore (6), pressure measurement left hole (7), pressure measurement right hole (8), draw and press pipe passageway (9), temperature sensor cable (10) and draw and press pipe (11) to constitute, its characterized in that: the device head (1) is a triangular prism, the windward side is a symmetrical left side surface (12) and a symmetrical right side surface (13), the leeward side is a triangular prism rear side surface (14), the pressure measuring middle hole (6), the pressure measuring left hole (7) and the pressure measuring right hole (8) are respectively arranged on the intersection line of the left side surface (12) and the right side surface (13), and the rear side surface (14) of the device head (1) back to the pressure measuring middle hole (6) is provided with a temperature sensor (3);
2. furthermore, the side length of a triangular prism of the head part (1) of the device is 2-10 mm, the height of the triangular prism is 5-150 mm, the included angle between the left side surface (12) and the right side surface (13) is 36-72 degrees, the distance between the test units of the head part of the device is unequal, the two ends of the triangular prism are dense, the middle of the triangular prism is sparse, each test unit is axially provided with three circular pressure leading pipe channels (9) and a circular temperature sensor cable leading-out channel (5) which are not communicated with each other, the three circular pressure leading pipe channels (9) are respectively communicated with the pressure measuring middle hole (6), the pressure measuring left hole (7) and the pressure measuring right hole (8) and are respectively communicated with three pressure leading pipes (11) which are packaged at the joint of the head part (1) of the device and the device supporting rod (2), and the tail parts of the device supporting rod (2) are;
3. the pressure measuring center hole (6) is circular, the diameter is 0.1-1.8 mm, the center line of the pressure measuring center hole is perpendicular to and intersected with the center line of the triangular prism, the distances between the center line of the pressure measuring center hole (6) of the uppermost and lower testing units and the top end and the bottom end of the head part (1) of the device are 0.15-2.5 mm, and parameters in boundary layers of the casing and the hub can be measured; the pressure measuring left hole (7) and the pressure measuring right hole (8) are circular, the diameter of the pressure measuring left hole and the diameter of the pressure measuring right hole are 0.08-1 mm and smaller than the diameter of the pressure measuring middle hole (6), the center line of the pressure measuring left hole (7) and the center line of the pressure measuring right hole (8) are coplanar with the center line of the pressure measuring middle hole (6), the plane where the pressure measuring left hole and the pressure measuring right hole are located is perpendicular to the center line of the triangular prism of the head (1), the pressure measuring left hole (7) and the pressure measuring right hole (8) are symmetrical about the plane formed by the center line of the pressure measuring middle hole (6) and;
4. furthermore, the temperature sensor (3) is a thermocouple or a thermal resistor, the temperature sensor (3) can be armored or exposed, the head of the temperature sensor (3) extends out of the rear side surface (14) of the head (1) by 0.1-1.5 mm, the center line of the temperature sensor (3) is superposed with the center line of the pressure measuring center hole (6), the temperature sensor (3) is fixed through a heat insulation sealing element (4), and the temperature sensor cable (10) is led out of the tail of the device supporting rod (2) through a temperature sensor cable leading-out channel (5) in the device;
5. further, the device supporting rod (2) is cylindrical, the diameter of the device supporting rod is 4-15 mm, and the axis of the device supporting rod (2) is overlapped with the axis of the triangular prism of the device head (1);
6. further, the multi-point full-parameter long-life measuring device for the supersonic two-dimensional steady-state flow field is calibrated through a calibration wind tunnel, and a device calibration curve can be obtained; in actual measurement, based on data measured by the pressure measuring holes and the temperature sensor, total temperature, total pressure, static temperature, static pressure, Mach number, deflection angle, speed and density parameters of a measured two-dimensional steady-state flow field can be obtained simultaneously through data processing according to a calibration coefficient curve and a formula obtained by calibrating the wind tunnel, the service life of the temperature sensor is prolonged, the insensitive angle range of airflow is enlarged, and the measurement spatial resolution and the measurement precision are improved.
The invention has the beneficial effects that:
the beneficial effects are that:
the multipoint all-parameter long-life measuring device for the supersonic two-dimensional steady-state flow field can realize the measurement of total temperature, total pressure, static temperature, static pressure, Mach number, deflection angle, speed and density of multiple points of the two-dimensional steady-state supersonic flow field by using a single device, has compact structure and small size, effectively reduces the interference on the measured flow field, and improves the test precision; meanwhile, the test operation is simplified, and the test cost is reduced; the time of the test process is greatly shortened, and the supersonic flow field test task is guaranteed to be completed.
The beneficial effects are that:
the head of the multi-point full-parameter long-life measuring device for the supersonic two-dimensional steady-state flow field is a triangular prism, and when the measuring device extends into the supersonic flow field for measurement, shock waves are inevitably caused. Compared with the cylindrical structure in the prior art, the triangular prism structure can weaken the shock wave strength to the greatest extent, not only reduces the interference to a flow field, but also effectively improves the service life of the device and the measurement precision.
The beneficial effects are three:
the multipoint full-parameter long-life measuring device for the supersonic two-dimensional steady-state flow field is characterized in that a temperature sensor of the device is back to a main flow and is positioned in a low-speed separation area on the leeward side of the head of the device, so that the scouring of airflow on the temperature sensor is reduced, meanwhile, the influence of oil drops, dust and the like mixed in the airflow on the temperature sensor is reduced, and the service life of the temperature sensor is effectively prolonged; secondly, the strength requirement on the temperature sensor is low, and the size of the temperature sensor can be small, so that the size of the head of the device is effectively reduced, and the spatial resolution is improved; thirdly, the range of the separation low-speed area is large, and the heat exchange between the airflow and the temperature sensor is effectively enhanced by the vortex in the separation area, so that the temperature recovery coefficient is high and stable in a large deflection angle range during measurement;
the multi-point full-parameter long-life measuring device for the supersonic two-dimensional steady-state flow field can measure the total temperature, total pressure, static temperature, static pressure, Mach number, deflection angle, speed and density parameters of the supersonic two-dimensional steady-state flow field, and has the characteristics of small size, large air flow insensitivity angle, high spatial resolution, high reliability, high measurement precision and short test time.
Drawings
Fig. 1 is a schematic structural diagram of a first embodiment of the present invention.
Fig. 2 is a rear view of fig. 1.
Fig. 3 is a left side view of fig. 1.
Fig. 4 is a partial cross-sectional view of fig. 3.
Fig. 5 is a view from direction a of fig. 1.
Fig. 6 is a view from direction B of fig. 2.
Wherein: 1-device head, 2-device support rod, 3-temperature sensor, 4-heat insulation sealing element, 5-temperature sensor cable leading-out channel, 6-pressure measuring middle hole, 7-pressure measuring left hole, 8-pressure measuring right hole, 9-pressure leading pipe channel, 10-temperature sensor cable, 11-pressure leading pipe, 12-left side, 13-right side and 14-back side.
Fig. 7 is a schematic view of installation and use of the first embodiment of the invention.
Wherein: 1-inlet casing, 2-measuring device of the invention, 3-hub.
Fig. 8 is a schematic structural diagram of a second embodiment of the present invention.
Fig. 9 is a rear view of fig. 8.
Fig. 10 is a left side view of fig. 8.
Fig. 11 is a partial cross-sectional view of fig. 10.
Fig. 12 is a view from direction a of fig. 8.
Fig. 13 is a view from direction B of fig. 9.
Wherein: 1-device head, 2-device support rod, 3-temperature sensor, 4-heat insulation sealing element, 5-temperature sensor cable leading-out channel, 6-pressure measuring middle hole, 7-pressure measuring left hole, 8-pressure measuring right hole, 9-pressure leading pipe channel, 10-temperature sensor cable, 11-pressure leading pipe, 12-left side, 13-right side and 14-back side.
Fig. 14 is a schematic view of installation and use of the second embodiment of the present invention.
Wherein: 1-turbine rotor, 2-measuring device of the invention, 3-turbine stator.
Detailed Description
The following detailed description of the preferred embodiments of the present invention, taken in conjunction with the accompanying drawings, will make the advantages and features of the invention easier to understand by those skilled in the art, and thus will clearly and clearly define the scope of the invention.
The first embodiment is as follows:
for an aircraft engine inlet duct, the size is relatively large, the incoming flow speed is high, and impurities such as dust and water drops can be contained. The device head (1) and the device supporting rod (2) are required to be large in size so as to ensure strength and rigidity, 7 test units are selected for the device head (1), a pressure measurement middle hole (6), a pressure measurement left hole (7) and a pressure measurement right hole (8) are selected to be large in aperture so as to avoid impurity blockage, and an armored thermocouple is selected for the temperature sensor (3) so as to ensure the service life, so that the following implementation case can be adopted (the attached figures 1-7 are schematic diagrams of an embodiment):
1. the utility model provides a multiple spot holoparameter long-life measuring device for supersonic speed two-dimensional steady state flow field, comprises device head (1), device branch (2), wherein device head (1) contains 7 test unit, and every test unit contains temperature sensor (3), adiabatic insulating seal (4), temperature sensor cable extraction passageway (5), pressure measurement mesopore (6), pressure measurement left hole (7), pressure measurement right hole (8), draw and press pipe passageway (9), temperature sensor cable (10) and draw and press pipe (11) to constitute, its characterized in that: the device head (1) is a triangular prism, the windward side is a symmetrical left side surface (12) and a symmetrical right side surface (13), the leeward side is a triangular prism rear side surface (14), the pressure measuring middle hole (6), the pressure measuring left hole (7) and the pressure measuring right hole (8) are respectively arranged on the intersection line of the left side surface (12) and the right side surface (13), and the rear side surface (14) of the device head (1) back to the pressure measuring middle hole (6) is provided with a temperature sensor (3);
2. the side length of a triangular prism of the head part (1) of the device is 10 mm, the height of the triangular prism is 81 mm, the included angle between a left side surface (12) and a right side surface (13) is 60 degrees, the distance between adjacent pressure measuring mesopores of seven test units of the head part of the device is 5, 10, 25, 10 and 5 mm from top to bottom, each test unit is provided with three round pressure leading pipe channels (9) which are not communicated with each other and a round temperature sensor cable leading-out channel (5) along the axial direction, the three round pressure leading pipe channels (9) are respectively communicated with the pressure measuring mesopores (6), the pressure measuring left pore (7) and the pressure measuring right pore (8) and respectively communicated with three pressure leading pipes (11) which are packaged at the connection part of the head part of the device (1) and the device supporting rod (2), and the tail parts of the device supporting rod (2) are led out through the pressure leading;
3. the pressure measuring middle hole (6) is circular, the diameter is 1.2 mm, the center line of the pressure measuring middle hole is perpendicular to and intersected with the center line of the triangular prism, the distances between the center line of the pressure measuring middle hole (6) of the uppermost and lower end test units and the top end and the bottom end of the head part (1) of the device are 0.8 mm, and parameters in boundary layers of the casing and the hub can be measured; the pressure measuring left hole (7) and the pressure measuring right hole (8) are both circular, the diameter of the pressure measuring left hole and the pressure measuring right hole is 0.8 mm, the center line of the pressure measuring left hole (7) and the center line of the pressure measuring right hole (8) are coplanar with the center line of the pressure measuring middle hole (6), the plane where the pressure measuring left hole and the pressure measuring right hole are located is perpendicular to the center line of the triangular prism of the head (1), the pressure measuring left hole (7) and the pressure measuring right hole (8) are symmetrical about the plane formed by the center line of the pressure measuring middle hole (6) and the center line of the;
4. the temperature sensor (3) is an armored thermocouple, the head of the temperature sensor (3) extends out of the leeward side of the head by 1.5 mm, the center line of the temperature sensor (3) is superposed with the center line of the pressure measuring center hole (6), the temperature sensor (3) is fixed through a heat insulation sealing element (4), and a temperature sensor cable (10) is led out of the tail of the device supporting rod (2) through a temperature sensor cable leading-out channel (5) in the device;
5. the device supporting rod (2) is cylindrical, the diameter of the device supporting rod is 15 mm, and the axis of the device supporting rod (2) is coincided with the axis of the triangular prism of the device head (1).
The method needs standard wind tunnel calibration before use, and the calibration process specifically comprises the following steps:
step A: in a standard wind tunnel with known incoming flow mach number and velocity, the incoming flow is made to flow through the head of the measuring device;
and B: for a single measuring unit, measuring the pressure of 3 pressure measuring holes on the windward surface of the measuring device, and respectively recording the pressure values of 7 measuring units;
and C: for a single measuring unit, measuring the temperature of the armored thermocouple on the leeward side of the measuring device, and respectively recording the temperature values of 7 measuring units;
step D: defining the measurement pressure of the pressure measurement left hole (7) as P1The pressure in the pressure measuring mesopore (6) is P2The pressure measured by the pressure measuring right hole (8) is P3The measured temperature of the armored thermocouple is TsTotal pressure of incoming flow is PtIncoming static pressure of PsAnd the total pressure coefficient, the static pressure coefficient, the deflection angle coefficient and the total temperature recovery coefficient under different incoming flow Mach numbers can be obtained by the incoming flow total temperature Tx. The coefficients are defined as follows:
total pressure coefficient:
static pressure coefficient:
deflection angle coefficient:
coefficient of temperature recovery:
therefore, calibration curves of total pressure coefficients, static pressure coefficients, deflection angle coefficients and total temperature recovery coefficients of 7 test units under different Mach numbers and different deflection angles can be obtained.
After the calibration is completed, the test measurement can be carried out, and the measurement process of the invention comprises the following steps:
step A: placing the head of the device in a flow field of an air inlet passage of the aero-engine, and adjusting the air inlet passage of the aero-engine to enter a test state;
and B: for a single measuring unit, measuring the pressure of three pressure measuring holes, and respectively recording the pressure values of 7 measuring units;
and C: for a single measuring unit, measuring the temperature of the armored thermocouple, and respectively recording the temperature values of 7 measuring units;
step D: and (3) calculating a deflection angle coefficient according to data of the three pressure measuring holes and temperature data measured by the armored thermocouple, and then combining the calibrated coefficient curve to calculate a deflection angle, total pressure, static pressure, total temperature and Mach number by interpolation. The invention can also measure the incoming flow speed and density, and can solve by adopting the following formula:
c2＝γRTs
Ps＝ρRTs
wherein gamma is the adiabatic exponent of the flow field, Ma is the mach number of the flow field, v is the flow field velocity, c is the local acoustic velocity of the flow field, ρ is the incoming flow density, and R is the gas constant.
Example two:
for an aircraft engine turbine stage outlet, the incoming flow velocity is relatively low, the axial and radial dimensions are small, and the flow is complex. The device head (1) and the device supporting rod (2) should be selected to be small in size so as to reduce blockage as much as possible, the device head (1) is selected from 9 test units, the pressure measuring middle hole (6), the pressure measuring left hole (7) and the pressure measuring right hole (8) are selected to be small in aperture so as to improve spatial resolution, and the temperature sensor (3) is selected from a bare wire thermocouple so as to reduce the whole size of the device, so that the following implementation cases (figures 8-14 are schematic diagrams of an embodiment two) can be adopted:
1. the utility model provides a multiple spot holoparameter long-life measuring device for supersonic speed two-dimensional steady state flow field, comprises device head (1), device branch (2), and wherein device head (1) contains 9 test units, and every test unit contains temperature sensor (3), adiabatic insulating seal (4), temperature sensor cable extraction passageway (5), pressure measurement mesopore (6), pressure measurement left hole (7), pressure measurement right hole (8), draw and press pipe passageway (9), temperature sensor cable (10) and draw and press pipe (11) to constitute, its characterized in that: the device head (1) is a triangular prism, the windward side is a symmetrical left side surface (12) and a symmetrical right side surface (13), the leeward side is a triangular prism rear side surface (14), the pressure measuring middle hole (6), the pressure measuring left hole (7) and the pressure measuring right hole (8) are respectively arranged on the intersection line of the left side surface (12) and the right side surface (13), and the rear side surface (14) of the device head (1) back to the pressure measuring middle hole (6) is provided with a temperature sensor (3);
2. the side length of a triangular prism of the head part (1) of the device is 3 mm, the height of the triangular prism is 65 mm, the included angle between a left side surface (12) and a right side surface (13) is 60 degrees, the distance between every two adjacent pressure measuring middle holes of 9 test units of the head part of the device is 2, 5, 10, 15, 10, 5 and 2 mm from top to bottom, each test unit is provided with three circular pressure leading pipe channels (9) which are not communicated with each other and a circular temperature sensor cable leading-out channel (5) along the axial direction, the three circular pressure leading pipe channels (9) are respectively communicated with the pressure measuring middle holes (6), the pressure measuring left holes (7) and the pressure measuring right holes (8) and are respectively communicated with three pressure leading pipes (11) which are packaged at the connection part of the head part (1) of the device and a device supporting rod (2), and the tail parts of the device supporting rod (2) are led out through the;
3. the pressure measuring middle hole (6) is circular, the diameter is 0.8 mm, the center line of the pressure measuring middle hole is perpendicular to and intersected with the center line of the triangular prism, the distances between the center line of the pressure measuring middle hole (6) of the uppermost and lower end test units and the top end and the bottom end of the head part (1) of the device are 0.5 mm, and parameters in boundary layers of the casing and the hub can be measured; the pressure measuring left hole (7) and the pressure measuring right hole (8) are both circular, the diameter of the pressure measuring left hole and the pressure measuring right hole is 0.4 mm, the center line of the pressure measuring left hole (7) and the center line of the pressure measuring right hole (8) are coplanar with the center line of the pressure measuring middle hole (6), the plane where the pressure measuring left hole and the pressure measuring right hole are located is perpendicular to the center line of the triangular prism of the head (1), the pressure measuring left hole (7) and the pressure measuring right hole (8) are symmetrical about the plane formed by the center line of the pressure measuring middle hole (6) and the center line of the;
4. the temperature sensor (3) is a bare wire thermocouple, the head of the temperature sensor (3) extends out of the leeward side of the head by 0.5 mm, the center line of the temperature sensor (3) is superposed with the center line of the pressure measuring center hole (6), the temperature sensor (3) is fixed through a heat insulation sealing element (4), and a temperature sensor cable (10) is led out of the tail part of the device supporting rod (2) through a temperature sensor cable leading-out channel (5) in the device;
5. the device supporting rod (2) is cylindrical, the diameter of the device supporting rod is 5 mm, and the axis of the device supporting rod (2) is coincided with the axis of the triangular prism of the device head (1).
Claims (1)
1. The utility model provides a multiple spot holoparameter long-life measuring device for supersonic speed two-dimensional steady state flow field, by device head (1), device branch (2) are constituteed, wherein device head (1) contains 3 ~ 9 test unit, every test unit contains temperature sensor (3), adiabatic insulating seal (4), temperature sensor cable draws forth passageway (5), pressure measurement mesopore (6), pressure measurement left hole (7), pressure measurement right hole (8), draw and press pipe passageway (9), temperature sensor cable (10) and draw and press pipe (11) to constitute, its characterized in that: the device head (1) is a triangular prism, the windward side is a symmetrical left side surface (12) and a symmetrical right side surface (13), the leeward side is a triangular prism rear side surface (14), the pressure measuring middle hole (6), the pressure measuring left hole (7) and the pressure measuring right hole (8) are respectively arranged on the intersection line of the left side surface (12) and the right side surface (13), and the rear side surface (14) of the device head (1) back to the pressure measuring middle hole (6) is provided with a temperature sensor (3);
the side length of a triangular prism of the device head (1) is 2-10 mm, the height is 5-150 mm, the included angle between a left side surface (12) and a right side surface (13) is 36-72 degrees, the distance between the test units of the device head (1) is unequal, two ends are dense, the middle part is sparse, each test unit is provided with three circular pressure leading pipe channels (9) and a circular temperature sensor cable leading-out channel (5) which are not communicated with each other along the axial direction, the three circular pressure leading pipe channels (9) are respectively communicated with a pressure measuring middle hole (6), a pressure measuring left hole (7) and a pressure measuring right hole (8) and respectively communicated with three pressure leading pipes (11) which are packaged at the joint of the device head (1) and the device supporting rod (2), and the tail parts of the device supporting rod (2) are led out by the pressure leading pipes (11) through the pressure leading pipe channels (9;
the pressure measuring center hole (6) is circular, the diameter is 0.1-1.8 mm, the center line of the pressure measuring center hole is perpendicular to and intersected with the center line of the triangular prism, the distances between the center line of the pressure measuring center hole (6) of the uppermost and lower testing units and the top end and the bottom end of the head part (1) of the device are 0.15-2.5 mm, and parameters in boundary layers of the casing and the hub can be measured; the pressure measuring left hole (7) and the pressure measuring right hole (8) are circular, the diameter of the pressure measuring left hole and the diameter of the pressure measuring right hole are 0.08-1 mm and smaller than the diameter of the pressure measuring middle hole, the central line of the pressure measuring left hole (7) and the central line of the pressure measuring right hole (8) are coplanar with the central line of the pressure measuring middle hole (6), the plane where the pressure measuring left hole and the pressure measuring right hole are located is perpendicular to the central line of the triangular prism of the head part (1), the pressure measuring left hole (7) and the pressure measuring right hole (8) are symmetrical about the plane formed by the central line of the pressure measuring middle hole (6;
the temperature sensor (3) is a thermocouple or a thermal resistor, the temperature sensor (3) can be armored or exposed, the head of the temperature sensor (3) extends out of the rear side surface (14) of the head (1) by 0.1-1.5 mm, the center line of the temperature sensor (3) is overlapped with the center line of the pressure measuring center hole (6), the temperature sensor (3) is fixed through a heat insulation sealing element (4), and a temperature sensor cable (10) is led out of the tail of the device supporting rod (2) through a temperature sensor cable leading-out channel (5) in the device;
the device supporting rod (2) is cylindrical, the diameter of the device supporting rod is 4-15 mm, and the axis of the device supporting rod (2) is overlapped with the axis of the triangular prism of the device head (1);
a multipoint full-parameter long-life measuring device for a supersonic two-dimensional steady-state flow field is characterized in that a device calibration curve can be obtained after calibration of a calibration wind tunnel; in actual measurement, based on data measured by the pressure measuring holes and the temperature sensor, total temperature, total pressure, static temperature, static pressure, Mach number, deflection angle, speed and density parameters of a measured two-dimensional steady-state flow field can be obtained simultaneously through data processing according to a calibration coefficient curve and a formula obtained by calibrating the wind tunnel, the service life of the temperature sensor is prolonged, the insensitive angle range of airflow is enlarged, and the measurement spatial resolution and the measurement precision are improved.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112594064A (en) * | 2020-11-25 | 2021-04-02 | 北京航空航天大学 | S2 flow field diagnosis method based on interstage measurement parameters of axial flow compressor |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112594064A (en) * | 2020-11-25 | 2021-04-02 | 北京航空航天大学 | S2 flow field diagnosis method based on interstage measurement parameters of axial flow compressor |
| CN112594064B (en) * | 2020-11-25 | 2021-12-14 | 北京航空航天大学 | S2 flow field diagnosis method based on interstage measurement parameters of axial flow compressor |
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