Multi-point full-parameter long-life measurement device for supersonic two-dimensional steady-state flow field

Abstract

The present invention belongs to the technical field of flow field testing, and specifically relates to a multi-point full-parameter long-life measurement device for supersonic two-dimensional flow fields, which is composed of a device head and a device support rod. The device head includes seven test units, and each test unit is composed of a temperature sensor, a heat-insulating seal, a temperature sensor cable lead-out channel, a pressure measuring middle hole, a pressure measuring left hole, a pressure measuring right hole, a pressure pipe channel, a temperature sensor cable, and a pressure pipe. After the device of the present invention is calibrated by a calibration wind tunnel, a device calibration curve can be obtained; in actual measurement, based on the data measured by the pressure measuring hole and the temperature sensor, and then according to the calibration coefficient curve and formula obtained by the calibration wind tunnel calibration, through data processing, the total temperature, total pressure, static temperature, static pressure, Mach number, deflection angle, speed, and density parameters of the measured two-dimensional steady-state flow field can be obtained at the same time, which increases the life of the temperature sensor and the airflow insensitive angle range, and improves the measurement space resolution and measurement accuracy.

Description

Technical Field

[0001] The present invention belongs to the technical field of flow field testing, and specifically relates to a multi-point full-parameter long-life measurement device for supersonic two-dimensional steady-state flow fields, which is suitable for multi-point measurement of total temperature, total pressure, static temperature, static pressure, Mach number, deflection angle, speed, and density of two-dimensional complex flow fields such as aircraft engine inlets, compressors, and turbines. Background Art

[0002] Aircraft engines are complex power machines. Modern aircraft engines have supersonic flow fields. The harsh working conditions also put forward higher requirements for testing technology. In order to improve the design level of modern aircraft engines and strengthen the understanding of their internal flow fields, it is necessary to achieve multi-point measurement of all parameters of supersonic flow fields, including total temperature, total pressure, static temperature, static pressure, Mach number, deflection angle, speed, and density.

[0003] Most existing measuring devices are aimed at subsonic flow fields, and their shapes are usually cylindrical to adapt to the characteristics of subsonic flow fields. However, cylindrical measuring devices will cause large loss of body shock waves in supersonic flow fields, which will not only cause great interference to the measured flow field, but also affect the measurement accuracy of the measuring device, so they cannot meet the measurement requirements of supersonic flow fields.

[0004] When existing measuring devices perform multi-parameter measurements, they usually use temperature measuring devices and pressure measuring devices to measure temperature parameters and pressure parameters respectively. That is, a single device is used separately to measure a single parameter. This measurement method increases the number of measuring devices, thereby increasing the interference to the measured flow field, and increases the complexity of the test and the cost of the test. The most important thing is that the flow parameters measured by different measuring devices cannot be guaranteed to come from the same streamline, which greatly reduces the spatial resolution of the measuring device, thereby reducing the accuracy of the test.

[0005] Most of the existing measuring devices are single-point measurements. When measuring multi-point parameters, it is necessary to use multiple measuring devices at the same time or use a displacement mechanism to drive the measuring device to move for measurement. Using multiple measuring devices at the same time not only increases the cost of the test, but also blocks the flow field and affects the measurement accuracy. Driving the measuring device through a displacement mechanism will cause a time difference between the results of multi-point measurements, and it is impossible to achieve simultaneous multi-point measurement of the flow field. In addition, for supersonic flow field measurements, the measuring device will be easily damaged by the impact of high-speed airflow, which requires the test process to be as short as possible. Therefore, simultaneous measurement of multi-point parameters is even more important for supersonic flow field testing.

[0006] According to the existing design concept of total temperature measurement device, the key to accurately measure the total temperature of airflow by temperature measurement device is whether the airflow can be absolutely stagnant at the temperature measurement point. Therefore, most of the existing temperature measurement devices are designed according to the requirement that the temperature sensor is facing the mainstream. The head of the temperature measurement device adopts a stagnation cover structure to collect the incoming flow, and the temperature sensor is placed in the stagnation cover. The disadvantages are: first, the temperature sensor is directly washed by the fluid and is easily affected by oil droplets, dust, etc. mixed in the airflow, and is easy to be damaged; second, the strength of the sensor is usually improved by increasing the size of the temperature sensor, and coupled with the size of the stagnation cover, the size of the measurement device is large, which will make its spatial resolution poor; third, the airflow insensitive angle is small. When the deflection angle of the incoming flow to be measured is large, the airflow cannot be fully stagnant, which leads to insufficient heat exchange on the surface of the temperature sensor and a large error in the total temperature measurement.

[0007] There are also single temperature and pressure combined measuring devices that simultaneously measure the temperature and pressure of a single point in the flow field. The temperature sensors of the existing temperature and pressure combined measuring devices are all facing the mainstream, and they have the shortcomings of the above-mentioned temperature measuring devices. Moreover, the measurement results are not the parameters of a single streamline, which is difficult to meet the measurement requirements under the harsh conditions of the supersonic flow field. Therefore, there is an urgent need for a multi-point full-parameter long-life measurement device for supersonic two-dimensional steady-state flow fields, which can be used for multi-point simultaneous measurement of full parameters such as total temperature, total pressure, static temperature, static pressure, Mach number, deflection angle, speed, and density in two-dimensional complex flow fields such as aircraft engine inlets, compressors, and turbines. Summary of the invention

[0008] The present invention is a multi-point full-parameter long-life measurement device for supersonic two-dimensional steady-state flow fields. Different from the cylindrical head design of the subsonic measurement device, the head of the device of the present invention is a triangular prism, which is suitable for the measurement of supersonic flow fields. Compared with the single-point measurement of the traditional measurement device, the head of the device of the present invention contains multiple test units, which realizes the function of simultaneous multi-point testing using a single measurement device. In addition, the present invention abandons the design concept of the traditional total temperature measurement device, but based on the applicant's many years of research, creatively proposes a layout and structural design that places the temperature sensor on the leeward side of the probe head, effectively reducing the scouring of the temperature sensor by the airflow and the influence of oil droplets, dust, etc. mixed in the airflow on the temperature sensor, greatly extending the service life of the temperature sensor, and adapting to the requirements of supersonic flow field testing; effectively reducing the size of the head of the measurement device, improving the spatial resolution of the measurement device; strengthening the convective heat exchange between the airflow and the temperature sensor, and the temperature recovery coefficient is high and stable within a large deflection angle range. Most importantly, the present invention is a multi-point full-parameter long-life measurement device for supersonic two-dimensional steady-state flow fields. A single device can simultaneously measure the total temperature, total pressure, static temperature, static pressure, Mach number, deflection angle, velocity, and density at multiple points in a two-dimensional steady-state supersonic flow field.

[0009] The present invention provides a multi-point full-parameter long-life measurement device for a supersonic two-dimensional steady-state flow field, and the technical problems to be solved are: first, the existing measurement device cannot simultaneously measure the total temperature, total pressure, static temperature, static pressure, Mach number, deflection angle, speed, density and other full parameters of the two-dimensional steady-state flow field at multiple spatial positions; second, the temperature sensor of the existing temperature measurement device is easily damaged and has a short life; third, the existing measurement device is large in size and has poor spatial resolution; fourth, the existing temperature measurement device has a small airflow insensitive angle.

[0010] The technical solution provided by the present invention is:

[0011] 1. A multi-point full-parameter long-life measurement device for a supersonic two-dimensional steady-state flow field, comprising a device head (1) and a device support rod (2), wherein the device head (1) comprises 3 to 9 test units, each test unit comprising a temperature sensor (3), a heat-insulating seal (4), a temperature sensor cable lead-out channel (5), a pressure measuring middle hole (6), a pressure measuring left hole (7), a pressure measuring right hole (8), a pressure lead pipe channel (9), a temperature sensor cable (10) and a pressure lead pipe (11). 1), characterized in that: the head (1) of the device is a triangular prism, the windward side is a symmetrical left side (12) and right side (13), the leeward side is a rear side (14) of the triangular prism, the pressure measuring center hole (6), the pressure measuring left hole (7) and the pressure measuring right hole (8) are respectively opened on the intersection of the left side (12) and the right side (13), the left side (12) and the right side (13), and the temperature sensor (3) is installed on the rear side (14) of the head (1) of the device facing away from the pressure measuring center hole (6);

[0012] 2. Further, the side length of the triangular prism of the device head (1) is 2 to 10 mm, the height is 5 to 150 mm, the angle between the left side (12) and the right side (13) is 36 to 72 degrees, the distances between the test units of the device head are not equal, the two ends are densely packed and the middle is sparse, each test unit is provided with three mutually unconnected circular pressure-conducting pipe channels (9) and a circular temperature sensor cable lead-out channel (5) along the axial direction, the three circular pressure-conducting pipe channels (9) are respectively connected to the pressure measuring middle hole (6), the pressure measuring left hole (7), and the pressure measuring right hole (8), and are respectively connected to three pressure-conducting pipes (11) encapsulated at the connection between the device head (1) and the device support rod (2), and the pressure-conducting pipe (11) is led out of the tail of the device support rod (2) through the pressure-conducting pipe channel (9) in the device support rod (2);

[0013] 3. The pressure measuring hole (6) is circular with a diameter of 0.1 to 1.8 mm. Its center line is perpendicular to and intersects with the center line of the triangular prism. The distance between the center line of the pressure measuring hole (6) of the upper and lower test units and the top and bottom ends of the device head (1) is 0.15 to 2.5 mm, ensuring that the parameters in the boundary layer of the casing and the hub can be measured. The left pressure measuring hole (7) and the right pressure measuring hole (8) are both circular with a diameter of 0.08 to 1 mm, which is smaller than the diameter of the pressure measuring hole (6). The center line of the left pressure measuring hole (7) and the center line of the right pressure measuring hole (8) are coplanar with the center line of the pressure measuring hole (6), and the plane in which they are located is perpendicular to the center line of the triangular prism of the device head (1). The left pressure measuring hole (7) and the right pressure measuring hole (8) are symmetrical about the plane formed by the center line of the pressure measuring hole (6) and the center line of the triangular prism of the device head (1), and the center lines intersect on the center line of the triangular prism.

[0014] 4. Further, the temperature sensor (3) is a thermocouple or a thermal resistor. The temperature sensor (3) can be armored or bare. The head of the temperature sensor (3) extends 0.1 to 1.5 mm beyond the rear side (14) of the head (1). The center line of the temperature sensor (3) coincides with the center line of the pressure measuring hole (6). The temperature sensor (3) is fixed by a heat-insulating seal (4). The temperature sensor cable (10) is led out of the tail of the device support rod (2) through the temperature sensor cable lead-out channel (5) in the device.

[0015] 5. Furthermore, the device support rod (2) is cylindrical with a diameter of 4 to 15 mm, and the axis of the device support rod (2) coincides with the axis of the triangular prism of the device head (1);

[0016] 6. Furthermore, a multi-point full-parameter long-life measurement device for supersonic two-dimensional steady-state flow fields can obtain a device calibration curve after calibration through a calibration wind tunnel; in actual measurement, based on the data measured by the pressure measuring holes and temperature sensors, and then according to the calibration coefficient curve and formula obtained by the calibration wind tunnel calibration, through data processing, the total temperature, total pressure, static temperature, static pressure, Mach number, deflection angle, speed, and density parameters of the measured two-dimensional steady-state flow field can be obtained at the same time, which increases the life of the temperature sensor and the airflow insensitive angle range, and improves the measurement space resolution and measurement accuracy.

[0017] The beneficial effects of the present invention are:

[0018] Beneficial effect 1:

[0019] The multi-point full-parameter long-life measurement device for a supersonic two-dimensional steady-state flow field of the present invention can realize the total temperature, total pressure, static temperature, static pressure, Mach number, deflection angle, speed, and density measurement of multiple points in a two-dimensional steady-state supersonic flow field using a single device. It has a compact structure and a small size, effectively reduces interference to the measured flow field, and improves the test accuracy; at the same time, it simplifies the test operation and reduces the test cost; it greatly reduces the time of the test process, and provides a guarantee for completing the supersonic flow field test task.

[0020] Beneficial effect 2:

[0021] The head of the multi-point full-parameter long-life measurement device for a supersonic two-dimensional steady-state flow field of the present invention is a triangular prism. When the measurement device is extended into the supersonic flow field for measurement, shock waves will inevitably be caused. Compared with the cylindrical structure in the prior art, the triangular prism structure of the present invention can weaken the intensity of the shock wave to the greatest extent, which not only reduces the interference to the flow field, but also effectively improves the life of the device and the measurement accuracy.

[0022] Beneficial effect three:

[0023] The temperature sensor of the multi-point full-parameter long-life measurement device for a supersonic two-dimensional steady-state flow field of the present invention is located in a low-speed separation zone on the leeward side of the head of the device, facing away from the mainstream. Firstly, the scouring of the temperature sensor by the airflow is reduced, and at the same time, the influence of oil droplets, dust, etc. mixed in the airflow on the temperature sensor is reduced, and the service life of the temperature sensor is effectively improved; secondly, the strength requirement of the temperature sensor is relatively low, and the size of the temperature sensor can be relatively small, thereby effectively reducing the size of the head of the device and improving the spatial resolution; thirdly, the range of the separation low-speed zone is relatively large, and the opposing vortices in the separation zone effectively strengthen the heat exchange between the airflow and the temperature sensor, so the temperature recovery coefficient is high and stable within a relatively large deflection angle range during measurement;

[0024] The invention discloses a multi-point full-parameter long-life measuring device for a supersonic two-dimensional steady-state flow field, which can measure total temperature, total pressure, static temperature, static pressure, Mach number, deflection angle, velocity and density parameters of the supersonic two-dimensional steady-state flow field, and has the characteristics of small size, large airflow insensitive angle, high spatial resolution, high reliability, high measurement accuracy and short test process time. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 It is a structural diagram of embodiment 1 of the present invention.

[0026] Figure 2 yes Figure 1 Rear view of.

[0027] Figure 3 yes Figure 1 Left view of .

[0028] Figure 4 yes Figure 3 A partial cross-sectional view of .

[0029] Figure 5 yes Figure 1 A-direction view.

[0030] Figure 6 yes Figure 2 B view.

[0031] Among them: 1-device head, 2-device support rod, 3-temperature sensor, 4-thermal insulation seal, 5-temperature sensor cable lead-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, 14-rear side.

[0032] Figure 7 It is a schematic diagram of installation and use of the first embodiment of the present invention.

[0033] Among them: 1-air intake casing, 2-measuring device of the present invention, 3-wheel hub.

[0034] Figure 8 It is a structural diagram of embodiment 2 of the present invention.

[0035] Fig. 9 yes Figure 8 Rear view of.

[0036] Fig.10 yes Figure 8 Left view of .

[0037] Fig.11 yes Fig.10 A partial cross-sectional view of .

[0038] Fig.12 yes Figure 8 A-direction view.

[0039] Fig.13 yes Fig. 9 B view.

[0040] Among them: 1-device head, 2-device support rod, 3-temperature sensor, 4-thermal insulation seal, 5-temperature sensor cable lead-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, 14-rear side.

[0041] Fig.14 It is a schematic diagram of installation and use of the second embodiment of the present invention.

[0042] Among them: 1-turbine rotor, 2-measuring device of the present invention, 3-turbine stator. DETAILED DESCRIPTION

[0043] The preferred embodiments of the present invention are described in detail below in conjunction with the accompanying drawings so that the advantages and features of the present invention can be more easily understood by those skilled in the art, thereby making a clearer and more definite definition of the protection scope of the present invention.

[0044] Embodiment 1:

[0045] For aircraft engine air intakes, the size is relatively large, the incoming flow velocity is fast, and impurities such as dust and water droplets may be contained. The device head (1) and the device support rod (2) should be selected with larger sizes to ensure strength and rigidity. The device head (1) uses 7 test units, and the pressure measuring middle hole (6), pressure measuring left hole (7), and pressure measuring right hole (8) are selected with larger apertures to avoid clogging by impurities. The temperature sensor (3) uses an armored thermocouple to ensure life. Therefore, the following implementation case (attached) can be used. Figure 1-7 Schematic diagram of Example 1):

[0046] 1. A multi-point full-parameter long-life measurement device for a supersonic two-dimensional steady-state flow field, comprising a device head (1) and a device support rod (2), wherein the device head (1) comprises 7 test units, each of which comprises a temperature sensor (3), a heat-insulating seal (4), a temperature sensor cable lead-out channel (5), a pressure measuring middle hole (6), a pressure measuring left hole (7), a pressure measuring right hole (8), a pressure lead pipe channel (9), a temperature sensor cable (10) and a pressure lead pipe (11 ), characterized in that: the head (1) of the device is a triangular prism, the windward side is a symmetrical left side (12) and right side (13), the leeward side is a rear side (14) of the triangular prism, the pressure measuring center hole (6), the pressure measuring left hole (7) and the pressure measuring right hole (8) are respectively opened on the intersection of the left side (12) and the right side (13), the left side (12) and the right side (13), and the temperature sensor (3) is installed on the rear side (14) of the head (1) of the device facing away from the pressure measuring center hole (6);

[0047] 2. The side length of the triangular prism of the device head (1) is 10 mm, the height is 81 mm, the angle between the left side (12) and the right side (13) is 60 degrees, the distances between the adjacent pressure measuring holes of the seven test units of the device head are 5, 10, 25, 25, 10, and 5 mm from top to bottom, respectively, and each test unit is provided with three mutually unconnected circular pressure-conducting pipe channels (9) and a circular temperature sensor cable lead-out channel (5) along the axial direction, the three circular pressure-conducting pipe channels (9) are respectively connected to the pressure measuring hole (6), the left pressure measuring hole (7), and the right pressure measuring hole (8), and are respectively connected to three pressure-conducting pipes (11) encapsulated at the connection between the device head (1) and the device support rod (2), and the pressure-conducting pipe (11) is led out of the tail of the device support rod (2) through the pressure-conducting pipe channel (9) in the device support rod (2);

[0048] 3. The pressure measuring hole (6) is circular with a diameter of 1.2 mm. Its center line is perpendicular to and intersects with the center line of the triangular prism. The distance between the center line of the pressure measuring hole (6) of the upper and lower test units and the top and bottom ends of the device head (1) is 0.8 mm, ensuring that the parameters in the boundary layer of the casing and the hub can be measured; the left pressure measuring hole (7) and the right pressure measuring hole (8) are both circular with a diameter of 0.8 mm. The center line of the left pressure measuring hole (7) and the center line of the right pressure measuring hole (8) are coplanar with the center line of the pressure measuring hole (6), and the plane in which they are located is perpendicular to the center line of the triangular prism of the device head (1). The left pressure measuring hole (7) and the right pressure measuring hole (8) are symmetrical about the plane formed by the center line of the pressure measuring hole (6) and the center line of the triangular prism of the device head (1), and the center lines intersect on the center line of the triangular prism;

[0049] 4. The temperature sensor (3) is an armored thermocouple. The head of the temperature sensor (3) extends 1.5 mm beyond the leeward side of the head. The center line of the temperature sensor (3) coincides with the center line of the pressure measuring hole (6). The temperature sensor (3) is fixed by a heat-insulating seal (4). The temperature sensor cable (10) is led out of the tail of the device support rod (2) through the temperature sensor cable lead-out channel (5) in the device.

[0050] 5. The device support rod (2) is cylindrical with a diameter of 15 mm. The axis of the device support rod (2) coincides with the axis of the triangular prism of the device head (1).

[0051] The present invention needs to be calibrated in a standard wind tunnel before use, and the calibration process specifically includes the following steps:

[0052] Step A: In a standard wind tunnel with known incoming flow Mach number and speed, allow the incoming flow to flow through the head of the measuring device;

[0053] Step B: For a single measuring unit, measure the pressure of three pressure measuring holes on the windward surface of the measuring device, and record the pressure values ​​of seven measuring units respectively;

[0054] Step C: for a single measuring unit, measure the temperature of the armored thermocouple on the leeward side of the measuring device, and record the temperature values ​​of the seven measuring units respectively;

[0055] Step D: Define the pressure measured by the left pressure measuring hole (7) as P1, the pressure measured by the middle pressure measuring hole (6) as P2, the pressure measured by the right pressure measuring hole (8) as P3, and the temperature measured by the armored thermocouple as T s , the total pressure of the incoming flow is P t , the static pressure of the incoming flow is P s , total temperature of incoming flow T t , from which we can get the total pressure coefficient, static pressure coefficient, deflection angle coefficient, and total temperature recovery coefficient under different incoming flow Mach numbers. The definitions of each coefficient are as follows:

[0056] Total pressure coefficient:

[0057] Static pressure coefficient:

[0058] Deflection angle coefficient:

[0059] Temperature recovery coefficient:

[0060] Thus, the calibration curves of the total pressure coefficient, static pressure coefficient, deflection angle coefficient and total temperature recovery coefficient of the seven test units at different Mach numbers and different deflection angles can be obtained.

[0061] After the calibration is completed, the test measurement can be carried out. The measurement process of the present invention includes the following steps:

[0062] Step A: placing the head of the device in the flow field of the aircraft engine inlet duct, and adjusting the aircraft engine inlet duct to enter the test state;

[0063] Step B: For a single measuring unit, measure the pressures of three pressure measuring holes and record the pressure values ​​of seven measuring units respectively;

[0064] Step C: For a single measuring unit, measure the temperature of the armored thermocouple and record the temperature values ​​of the seven measuring units respectively;

[0065] Step D: Based on the data of the three pressure measuring holes and the temperature data measured by the armored thermocouple, the deflection angle coefficient is calculated, and then combined with the calibrated coefficient curve, the deflection angle, total pressure, static pressure, total temperature and Mach number are interpolated. The present invention can also measure the incoming flow velocity and density, which can be solved using the following formula:

[0066]

[0067] c 2 =γRT s

[0068] P s = ρRT s

[0069] Among them, γ is the adiabatic index of the flow field, Ma is the Mach number of the flow field, v is the flow field velocity, c is the local sound speed of the flow field, ρ is the incoming flow density, and R is the gas constant.

[0070] Embodiment 2:

[0071] At the turbine stage outlet of an aircraft engine, the incoming flow velocity is relatively small, the axial and radial dimensions are small, and the flow is complex. The device head (1) and the device support rod (2) should be selected to be smaller in size to minimize blockage. The device head (1) uses 9 test units, and the pressure measuring middle hole (6), pressure measuring left hole (7), and pressure measuring right hole (8) are selected to have smaller apertures to improve spatial resolution. The temperature sensor (3) uses a bare wire thermocouple to reduce the overall size of the device. Therefore, the following implementation case (attached) can be used. Figure 8-14 Schematic diagram of Example 2):

[0072] 1. A multi-point full-parameter long-life measurement device for a supersonic two-dimensional steady-state flow field, comprising a device head (1) and a device support rod (2), wherein the device head (1) comprises 9 test units, each test unit comprising a temperature sensor (3), a heat-insulating seal (4), a temperature sensor cable lead-out channel (5), a pressure measuring middle hole (6), a pressure measuring left hole (7), a pressure measuring right hole (8), a pressure lead pipe channel (9), a temperature sensor cable (10) and a pressure lead pipe (11 ), characterized in that: the head (1) of the device is a triangular prism, the windward side is a symmetrical left side (12) and right side (13), the leeward side is a rear side (14) of the triangular prism, the pressure measuring center hole (6), the pressure measuring left hole (7) and the pressure measuring right hole (8) are respectively opened on the intersection of the left side (12) and the right side (13), the left side (12) and the right side (13), and the temperature sensor (3) is installed on the rear side (14) of the head (1) of the device facing away from the pressure measuring center hole (6);

[0073] 2. The side length of the triangular prism of the device head (1) is 3 mm, the height is 65 mm, the angle between the left side (12) and the right side (13) is 60 degrees, the spacing between adjacent pressure measuring holes of the 9 test units of the device head is 2, 5, 10, 15, 15, 10, 5, and 2 mm from top to bottom, respectively, and each test unit is provided with three mutually unconnected circular pressure-conducting pipe channels (9) and a circular temperature sensor cable lead-out channel (5) along the axial direction, the three circular pressure-conducting pipe channels (9) are respectively connected to the pressure measuring middle hole (6), the pressure measuring left hole (7), and the pressure measuring right hole (8), and are respectively connected to three pressure-conducting pipes (11) encapsulated at the connection between the device head (1) and the device support rod (2), and the pressure-conducting pipe (11) is led out of the tail of the device support rod (2) through the pressure-conducting pipe channel (9) in the device support rod (2);

[0074] 3. The pressure measuring hole (6) is circular with a diameter of 0.8 mm. Its center line is perpendicular to and intersects with the center line of the triangular prism. The center lines of the pressure measuring holes (6) of the upper and lower test units are 0.5 mm away from the top and bottom ends of the device head (1), ensuring that the parameters in the boundary layer of the casing and the hub can be measured. The left pressure measuring hole (7) and the right pressure measuring hole (8) are both circular with a diameter of 0.4 mm. The center lines of the left pressure measuring hole (7) and the right pressure measuring hole (8) are coplanar with the center line of the pressure measuring hole (6), and the plane in which they are located is perpendicular to the center line of the triangular prism of the device head (1). The left pressure measuring hole (7) and the right pressure measuring hole (8) are symmetrical about the plane formed by the center line of the pressure measuring hole (6) and the center line of the triangular prism of the device head (1), and the center lines intersect on the center line of the triangular prism.

[0075] 4. The temperature sensor (3) is a bare wire thermocouple. The head of the temperature sensor (3) extends 0.5 mm beyond the leeward side of the head. The center line of the temperature sensor (3) coincides with the center line of the pressure measuring hole (6). The temperature sensor (3) is fixed by a heat-insulating seal (4). The temperature sensor cable (10) is led out of the tail of the device support rod (2) through the temperature sensor cable lead-out channel (5) in the device.

[0076] 5. The device support rod (2) is cylindrical with a diameter of 5 mm. The axis of the device support rod (2) coincides with the axis of the triangular prism of the device head (1).

Claims

1. A method for using a multi-point full-parameter long-life measurement device for a supersonic two-dimensional steady-state flow field to realize full-parameter multi-point measurement of a two-dimensional complex flow field such as an aircraft engine intake duct compressor turbine, etc. The structure of the multi-point full-parameter long-life measurement device for a supersonic two-dimensional steady-state flow field is composed of a device head (1) and a device support rod (2), wherein the device head (1) comprises 3 to 9 test units, each test unit comprises a temperature sensor (3), a heat insulation seal (4), a temperature sensor cable lead-out channel (5), a pressure measuring middle hole (6), a pressure measuring left hole (7), a pressure measuring right hole (8), a pressure lead pipe channel (9), a temperature sensor cable (10) and a pressure lead pipe (11), characterized in that: The head (1) of the device is a triangular prism, the windward side is a symmetrical left side (12) and right side (13), the leeward side is a rear side (14) of the triangular prism, the pressure measuring center hole (6), the pressure measuring left hole (7) and the pressure measuring right hole (8) are respectively opened on the intersection of the left side (12) and the right side (13), the left side (12) and the right side (13), and the temperature sensor (3) is installed on the rear side (14) of the head (1) of the device facing away from the pressure measuring center hole (6); The side length of the triangular prism of the device head (1) is 2 to 10 mm, the height is 5 to 150 mm, the angle between the left side (12) and the right side (13) is 36 to 72 degrees, the distances between the test units of the device head (1) are not equal, the two ends are densely packed and the middle is sparse, each test unit is provided with three mutually unconnected circular pressure-conducting pipe channels (9) and a circular temperature sensor cable lead-out channel (5) along the axial direction, the three circular pressure-conducting pipe channels (9) are respectively connected to the pressure measuring middle hole (6), the pressure measuring left hole (7), and the pressure measuring right hole (8), and are respectively connected to three pressure-conducting pipes (11) encapsulated at the connection between the device head (1) and the device support rod (2), the pressure-conducting pipe (11) is led out of the tail of the device support rod (2) through the pressure-conducting pipe channel (9) in the device support rod (2); The pressure measuring hole (6) is circular, with a diameter of 0.1-1.8 mm, and its center line is perpendicular to and intersects with the center line of the triangular prism. The distance between the center line of the pressure measuring hole (6) of the upper and lower test units and the top and bottom ends of the device head (1) is 0.15-2.5 mm, ensuring that the parameters in the boundary layer 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, with a diameter of 0.08-1 mm, and are smaller than the diameter of the pressure measuring hole. The center line of the left pressure measuring hole (7) and the center line of the right pressure measuring hole (8) are coplanar with the center line of the pressure measuring hole (6), and the plane they are located in is perpendicular to the center line of the triangular prism of the device head (1). The left pressure measuring hole (7) and the right pressure measuring hole (8) are symmetrical about the plane formed by the center line of the pressure measuring hole (6) and the center line of the triangular prism of the device head (1), and the center lines intersect on the center line of the triangular prism; The temperature sensor (3) is a thermocouple or a thermal resistor. The temperature sensor (3) is armored or bare. The head of the temperature sensor (3) extends 0.1 to 1.5 mm beyond the rear side (14) of the head of the device (1). The center line of the temperature sensor (3) coincides with the center line of the pressure measuring hole (6). The temperature sensor (3) is fixed by a heat-insulating seal (4). The temperature sensor cable (10) is led out of the tail of the device support rod (2) through a temperature sensor cable lead-out channel (5) in the device. The device support rod (2) is cylindrical, with a diameter of 4 to 15 mm, and the axis of the device support rod (2) coincides with the axis of the triangular prism of the device head (1); The use steps are as follows: Step 1: in a calibrated wind tunnel with known incoming flow Mach number and temperature, make the incoming flow flow through the head of the device to obtain the total pressure coefficient, static pressure coefficient, deflection angle coefficient, and total temperature recovery coefficient under different incoming flow Mach numbers; Step 2: Measure the pressure of the pressure sensing hole on the windward side of the device and the temperature of the temperature sensor on the leeward side under different working conditions; The third step: determine the calibration curves of total temperature and total pressure at different Mach numbers and different deflection angles through data processing based on the data obtained from the calibration; the fourth step: when in use, insert the device of the present invention into the measured flow field, perform data processing on the pressure and temperature signals obtained from the actual measurement, and realize multi-point measurement of all parameters such as total temperature, total pressure, static temperature, static pressure, Mach number, deflection angle, speed, and density of two-dimensional complex flow fields such as aircraft engine inlets, compressors, and turbines.

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