Water-cooling pressure probe for measuring interstage three-dimensional dynamic high-temperature flow field of turbine

Abstract

The utility model belongs to the technical field of high-temperature flow field pressure testing, and discloses a water-cooling pressure probe for measuring a turbine interstage three-dimensional dynamic high-temperature flow field, which is characterized by comprising a probe head, a support rod, a mounting seat and a lock cover. The probe head comprises a cylinder and a cylinder beveled body which share the same bottom surface, and two dynamic pressure sensors are packaged in the probe head. The diagonal plane of the cylindrical beveling body and the side face of the cylinder are each provided with a pressure sensing hole, and the pressure sensing holes are communicated with a pressure sensor. A plug board with a vortex generating device is arranged in the probe head and the support rod, so that heat convection between cooling water and the pressure measuring channel is enhanced. Three-dimensional flow parameters such as a pitch angle, a deflection angle, total pressure, static pressure and Mach number in a turbine interstage flow field can be measured through calibration of a calibration wind tunnel. Compared with an existing probe, the probe can realize flow field measurement in a high-temperature environment, prevents a sensor at the head of the probe from temperature drift and even damage due to heating, and further ensures the accuracy of measured data.

Description

Technical Field

[0001] The present invention belongs to the technical field of high-temperature pressure testing, and relates to a dynamic pressure measurement device for a three-dimensional flow field. Specifically, it relates to a water-cooled pressure probe for measuring the three-dimensional dynamic high-temperature flow field between turbine stages, which is applicable to measuring the circumferential distribution of three-dimensional flow parameters such as pitch angle, yaw angle, total pressure, static pressure, and Mach number in the three-dimensional flow field between turbine stages. Background Art

[0002] To obtain the performance parameters of turbine components in an engine and the internal flow field structure, it is necessary to measure the pressure between its stages. Currently, in engineering practice, contact pressure probes are mainly used to achieve this. However, the existing pressure probe materials cannot withstand temperatures exceeding 1000K, and the head of the dynamic pressure sensor cannot withstand temperatures exceeding 500K, which causes the probe to be damaged during the measurement process and makes the measurement impossible to carry out.

[0003] With the pursuit of high performance in modern engines, most turbine blades adopt swept and curved styling designs, and the blade curvature changes greatly. This means that the airflow angle will also change greatly after passing through one stage of blades. The angle difference in different blade height directions is even greater, which can reach a range of ±60° or higher. The angle range measured by a conventional five-hole probe is about ±15°, making it difficult to meet the measurement requirements in the complex internal flow environment between turbine stages. To solve this problem, the common practice in engineering is currently to increase the number of holes on the probe, such as seven-hole, twelve-hole, and eighteen-hole probes. However, with the increase in the number of holes, the diameter of the probe strut and the size of the probe head will become larger, which will not only cause more serious interference to the flow field but also make it difficult to meet the requirements for high-resolution measurement in a narrow space.

[0004] At the same time, due to the rotation of the turbine rotor, using a conventional steady-state pressure probe cannot measure the dynamic flow field at the rotor outlet and cannot distinguish the circumferential distribution of the flow parameters from the pressure surface to the suction surface at the rotor outlet. A hot-wire anemometer can measure the dynamic velocity signal at the rotor outlet but cannot provide dynamic pressure information. Turbine experiments are more eager to obtain measurement data containing dynamic pressure information between turbine stages. For the transonic three-dimensional flow field at the turbine rotor outlet, it is hoped to obtain the circumferential distribution of three-dimensional flow parameters such as pitch angle, yaw angle, total pressure, static pressure, and Mach number from the pressure surface to the suction surface at the rotor outlet, which is used to verify the design of the rotor and flow field diagnosis in order to improve the performance of the turbine.

[0005] Currently, the existing probe for measuring the rotor outlet (patent for invention: a conical double-hole dynamic pressure probe for measuring the transonic three-dimensional flow at the rotor outlet, 2017101188295) is limited by the materials of the probe housing and the dynamic sensor and cannot measure the three-dimensional dynamic high-temperature flow field between turbine stages.

[0006] It is not easy to make the size of a dynamic pressure probe small. A large size will seriously interfere with the measured flow field. On the other hand, the cost of a dynamic pressure probe is too high. For existing probes with a water-cooling structure (invention patent: A water-cooled probe, 2017207630951), cooling water is introduced through a single water inlet, which may result in uneven water inlet and then local ablation of the probe. At the same time, such probes also have problems such as large volume and inability to measure three-dimensional flow field dynamic parameters.

[0007] Existing pressure probes are difficult to meet the test requirements for measuring the three-dimensional dynamic high-temperature flow field between turbine stages, especially at an extreme high temperature of 2000K. Therefore, there is an urgent need for a water-cooled dynamic pressure probe that is suitable for high temperatures, prevents local ablation, and can achieve wide-range measurement of three-dimensional flow field parameters between turbine stages. Summary of the Invention

[0008] The technical problem to be solved by the present invention is: In view of the fact that existing pressure probes cannot meet the test requirements for measuring the three-dimensional dynamic high-temperature flow field between turbine stages, especially the three-dimensional dynamic flow field test requirements at an extreme high temperature of 2000K, to invent a water-cooled dynamic pressure probe that is resistant to high temperatures and can measure three-dimensional dynamic flow field parameters between turbine stages.

[0009] When measuring the pressure of the three-dimensional flow field between turbine stages, the ambient temperature is too high, and the pressure sensor at the probe head is damaged. Therefore, a cooling measure needs to be taken to reduce the air flow temperature near the pressure sensor at the probe head. For this purpose, the present invention provides a water-cooled pressure probe for measuring the three-dimensional dynamic high-temperature flow field between turbine stages. When actually measuring the three-dimensional flow field between the turbine stages of an aeroengine, the pitch angle is measured by the pressure sensing holes on the beveled cylindrical surface of the probe head, and another pressure sensing hole is directly facing the gas flow direction. The deflection angle of the probe is adjusted by a displacement mechanism, and the flow field under different conditions is measured at different deflection angles. During the measurement, cooling water is introduced into the water inlet pipe. The cooling water enters the probe interior through three circumferentially wide-angle arranged water inlets, flows into the probe interior from the water inlet side of the plug plate, generates turbulence after passing through the vortex generator, and at the same time forms a high-speed jet of cooling water and impacts the wall surface near the pressure sensing holes. The boundary layer of the impacted position area becomes thinner, intensifying the heat exchange between the cooling water and the wall surface, increasing the local heat transfer coefficient, and thus strengthening the convective heat transfer between the cooling water and the shell wall near the pressure sensing holes. At the same time, the structure of the vortex generator itself has outward protruding fins, which also helps the convective heat transfer between the cooling water inside the probe and the plug plate. The plug plate is directly connected to the probe housing, and the heat can be quickly transferred from the probe housing to the plug plate area through heat conduction, further enhancing the overall heat dissipation effect of the probe. Compared with the existing probe, this probe has fewer pressure sensing holes and a smaller probe head volume, so it has a higher spatial resolution. At the same time, this probe has strong high-temperature resistance, which can reduce the temperature around the dynamic pressure sensor inside the pressure measurement channel to below 500K, and thus realize the measurement of three-dimensional flow field parameters such as the pitch angle, deflection angle, total pressure, static pressure, and Mach number between the turbine stages of an aeroengine.

[0010] The solution of the present invention is:

[0011] 1. A water-cooled pressure probe for measuring the three-dimensional dynamic high-temperature flow field between turbine stages, comprising a middle pressure sensing hole (1), a top pressure sensing hole (2), a probe strut (3), a mounting base (4), a locking cover (5), and the probe tail is provided with a No. 1 water inlet (6), a No. 2 water inlet (7), a No. 3 water inlet (8), a No. 1 cable channel (9), a No. 2 cable channel (10), a No. 1 water outlet (11), a No. 2 water outlet (12), and a No. 3 water outlet (13). There is a plug board (14) inside the probe head and the strut, and a vortex generating device (15) is provided on the plug board. It is characterized in that: the probe head has a cylindrical shape, the diameter of the probe head is 4 mm to 12 mm, the length is 12 mm to 50 mm, and the inner and outer edges of the head are both provided with continuously curved rounded corners with a radius of 0.2 mm to 1.5 mm; the probe head (1) is welded to the probe strut (3), the probe strut (3) is cylindrical, with a diameter of 10 mm to 30 mm, the probe housing is made of stainless steel material and coated with high-temperature heat-insulating paint, the probe head is provided with a middle pressure sensing hole (1) and a top pressure sensing hole (2), corresponding to two pressure measurement channels respectively, pressure sensors are installed in the pressure measurement channels of the probe head, and the number of sensors is the same as the number of pressure measurement holes. The cables of the sensors are sleeved inside the probe and led out from the No. 1 cable channel (9) and the No. 2 cable channel (10) at the probe tail. The measurement accuracy of the sensors is 0.1% to 0.5%, and the natural frequency is 300 Hz to 500 kHz.

[0012] 2. The middle pressure sensing hole (1) has a bend angle of 75° to 105°, a diameter of 0.6 mm to 1.5 mm, and the distance between the center line of the middle pressure sensing hole (1) and the lowest point of the cylindrical inclined section is 1 mm to 5 mm; the top pressure sensing hole (2) has a bend angle of 120° to 160°, a diameter of 0.6 mm to 1.5 mm, and the distance between the center line of the top pressure sensing hole (2) and the lowest point of the cylindrical inclined section is 1 mm to 5 mm.

[0013] 3. The plug board (14) is perpendicular to the central axis of the top pressure sensing hole (2) and evenly divides the inside of the probe strut into two parts. The thickness of the plug board (14) is 1 mm to 3 mm; the vortex generating device (15) is a "V"-shaped rib, the included angle of the "V" shape is 30° to 60°, and the outer extension length is 0.5 mm to 1.5 mm.

[0014] 4. The 1st water inlet (6), 2nd water inlet (7), 3rd water inlet (8), 1st water outlet (11), 2nd water outlet (12), and 3rd water outlet (13) are circumferentially arranged at the probe tail. Among them, the centers of the 2nd water inlet (7), 2nd water outlet (12), 1st cable channel (9), and 2nd cable channel (10) are collinear; the circumferential angles between the 1st water inlet (6), 3rd water inlet (8), and 2nd water inlet (7) are 40° to 80°, and the circumferential angles between the 1st water outlet (11), 3rd water outlet (13), and 2nd water outlet (12) are 40° to 80°; the 1st water inlet (6), 2nd water inlet (7), and 3rd water inlet (8) are circumferentially arranged at the probe bottom, which can make the water inlet more uniform.

[0015] 5. Calibrate a water-cooled pressure probe for measuring the three-dimensional dynamic high-temperature flow field between turbine stages in a calibration wind tunnel. The calibrated Mach number range is 0.1 Mach to 0.9 Mach, the deflection angle is -80° to 80°, and the pitch angle is -40° to 40°. The calibration method includes the following steps:

[0016] Step 1: Clamp the probe using a displacement mechanism and adjust the probe position so that the pressure sensing hole (1) in the middle of the probe head is basically facing the airflow direction. Next, rotate the probe 80° clockwise and counterclockwise respectively, measure the measured pressure P1 of the middle pressure sensing hole (1) and the measured pressure P4 of the top pressure sensing hole (2) at different angles, and use polynomial fitting to obtain the calibration curve of P1 and the deflection angle α.

[0017] Step 2: Repeat Step 1 after adjusting the pitch angle of the probe using the displacement mechanism to obtain the calibration curves of the measured pressure P1 of the middle pressure sensing hole (1), the measured pressure P4 of the top pressure sensing hole (2), the deflection angle α, and the pitch angle β of the probe at different pitch angles β; In particular, the maximum value P of P1 on each calibration curve 1max is the total incoming flow pressure, and the pressure value corresponding to the rotation angle (α ± 40°) that is 40° apart from the angle α0 corresponding to P 1max is the static pressure, and the pitch angle corresponding to the angle β0 corresponding to P 1max is 0°.

[0018] Step 3: Define the pitch angle coefficient as:

[0019]

[0020]

[0021] where, K β 、K t 、K s are the pitch angle coefficient, total pressure coefficient, and static pressure coefficient respectively, p1 is the measured pressure of the middle pressure sensing hole (1), p 1max$p_1$ is the maximum pressure measured by the pressure sensing hole (1) at the current pitch angle, $p_4$ is the pressure measured by the top pressure sensing hole (2), and $p$ t is the total incoming flow pressure, and $p$ s is the static incoming flow pressure;

[0022] Using the above definitions, calibration surfaces of the pitch angle coefficient, total pressure coefficient, and static pressure coefficient at different deflection angles are obtained;

[0023] During actual measurement, the displacement mechanism is used to drive the probe to rotate, and the pressure values of the middle pressure sensing hole (1) and the top pressure sensing hole (2) at different deflection angles are obtained. According to the definitions of the pitch angle coefficient, total pressure coefficient, and static pressure coefficient in Step 1, Step 2, and Step 3, and then the actual measured deflection angle, pitch angle, total pressure, static pressure, and Mach number are calculated by interpolating the calibration surface.

[0024] In the present invention, a water-cooled pressure probe for measuring the three-dimensional dynamic high-temperature flow field between turbine stages can obtain calibration data after being calibrated in a calibration wind tunnel. When actually measuring the three-dimensional flow field between the turbine stages of an aeroengine, the displacement mechanism is used to adjust the deflection angle of the probe, and the flow fields under different working conditions are measured at different deflection angles. Several sets of unsteady pressure data are measured by the dynamic pressure sensors inside the probe, and the calibration data obtained from the calibration wind tunnel is used for data processing. Furthermore, three-dimensional flow parameters such as the pitch angle, deflection angle, total pressure, static pressure, and Mach number in the three-dimensional flow field between the turbine stages of the aeroengine can be obtained. After injecting cooling water, dynamic measurement of the flow field parameters can be realized in a high-temperature environment of 2000K, and the frequency response of the probe exceeds 25kHz.

[0025] The present invention, a water-cooled pressure probe for measuring the three-dimensional dynamic high-temperature flow field between turbine stages, has the following beneficial effects:

[0026] Beneficial effect 1: The probe can realize measurement in a high-temperature environment. After being calibrated in a calibration wind tunnel, the present invention can be used to measure three-dimensional flow field parameters such as the total pressure, static pressure, deflection angle, pitch angle, and Mach number of the three-dimensional flow field between the turbine stages of an aeroengine, providing measured data for improving the performance of the aeroengine turbine. Compared with the probes for conventional measurement, the probe can realize measurement in a high-temperature environment. After injecting cooling water, the cooling effect around the sensing part of the probe is improved, and the temperature around the head of the dynamic pressure sensor inside the probe is reduced to below 500K.

[0027] Beneficial effect 2: The probe can reduce the interference caused by the reflection of the pressure wave to the upstream of the flow field. The pressure measurement channels at the probe head are all bent at a certain angle, which can avoid pressure pulsation and prevent the direct impact of the scouring of high-temperature gas flow on the sensing part of the pressure sensor, thereby extending the service life of the pressure sensor. In addition, when the pressure wave propagates, it will be reflected. When the pressure wave propagates to one end of the pipeline, the wave will be reflected back from the end of the pipeline. The pressure sensing holes at the probe head are bent at a certain angle, which can reduce the interference caused by the reflection of the pressure wave to the upstream of the flow field and make the measurement more accurate.

[0028] Beneficial effect 3: Avoid local ablation of the probe. When the cooling water enters through the three water inlets, it can ensure uniform water inlet, avoid the formation of cavities inside the probe and insufficient heat exchange, and thus prevent the occurrence of local ablation.

[0029] Beneficial effect 4: The internal cooling structure of the probe can enhance the convective heat transfer between the cooling water and the pressure measurement channel. After the cooling water flows through the water inlet side of the baffle plate, it passes through the eddy current generator to generate turbulence, and directly scours the shell wall near the pressure sensing hole, strengthening the convective heat transfer between the cooling water and the shell of the pressure measurement channel, making the probe have stronger high-temperature resistance.

[0030] Beneficial effect 5: Avoid stress concentration at the probe tail shell. Three drain holes are evenly arranged circumferentially at the bottom of the probe, which can prevent stress concentration at the probe tail shell caused by excessive local water pressure.

[0031] Beneficial effect 6: The probe is clamped by the displacement mechanism, and the probe rotates around its own axis at different blade heights to measure the flow field structure with large changes in the air flow angle. This can reduce the number of openings, making the cooling effect of the cooling water on the pressure measurement channel of the probe better. At the same time, the probe is rotated by the displacement mechanism, which can also meet a wider range of measurement requirements, making the probe head smaller in volume and meeting the requirements for high resolution in narrow spaces. Description of the Drawings

[0032] Figure 1 is the overall structural schematic diagram of a water-cooled pressure probe for measuring the three-dimensional dynamic high-temperature flow field in the turbine stage in the embodiment of the present invention.

[0033] Figure 2 is Figure 1 the front view of

[0034] Figure 3 is Figure 1 the top view of

[0035] Figure 4 is Figure 2 the sectional view taken along the A-A section of

[0036] Figure 5 is Figure 2Cross-sectional view of the B-B section

[0037] Figure 6 is Figure 2 Cross-sectional view of the C-C section

[0038] Figure 7 is Figure 2 Cross-sectional view of the D-D section

[0039] Wherein: 1 - middle pressure sensing hole, 2 - top pressure sensing hole, 3 - probe support rod, 4 - mounting base, 5 - lock cover, 1st cable channel (9), 2nd cable channel (10), 1st water outlet (11), 2nd water outlet (12), 3rd water outlet (13), 14 - plug board, 15 - eddy current generating device Specific implementation manner

[0040] The present invention will be described in detail below in conjunction with the accompanying drawings and a specific implementation case, 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

[0041] As Figure 1 shown, in this embodiment, a water-cooled pressure probe for measuring the three-dimensional dynamic high-temperature flow field between turbine stages is introduced, which consists of a middle pressure sensing hole (1) for measuring the incoming flow pressure and a top pressure sensing hole (2) for measuring the pitch angle, a probe support rod (3), a mounting base (4), a lock cover (5), with a 1st water inlet (6), 2nd water inlet (7), 3rd water inlet (8) at the tail of the probe, 1st cable channel (9), 2nd cable channel (10) and 1st water outlet (11), 2nd water outlet (12), 3rd water outlet (13); there is a plug board (14) inside the probe head and the support rod, and an eddy current generating device (15) is provided on the plug board; the pressure sensor is installed at the probe head, and the number of sensors is the same as the number of pressure measuring holes. The cables of the sensors are sleeved inside the probe and led out from the tail of the probe. The measurement accuracy of the sensors is 0.1%, and the natural frequency is 380 kHz. The diameter of the probe head is 8 mm and the length is 24 mm. The outer edge line of the probe head adopts a continuously curved fillet with a radius of 0.5 mm. The probe support rod (3) is cylindrical with a diameter of 12 mm

[0042] Figure 2 And Figure 3 shown are the front view and top view of the probe introduced in this embodiment. The eddy current generating device (15) on the internal plug board (14) has an appearance in the shape of a "V", and the included angle of the "V" shape is 40°

[0043] As Figure 4As shown in the figure, in this embodiment, the pressure sensing holes at the head of the probe all have bent angles at a certain angle, which can avoid pressure pulsation and prevent the direct impact of high-temperature gas flow scouring on the sensing part of the pressure sensor, thereby extending the service life of the pressure sensor; the pressure sensing hole (1) has a 90° bent angle, a diameter of 1.5 mm, and the distance between the pressure sensing hole (1) and the lowest point of the cylindrical inclined plane is 2 mm; the pressure sensing hole (2) has a 120° bent angle, a diameter of 1.5 mm, and the distance between the pressure sensing hole (2) and the lowest point of the cylindrical inclined plane is 2 mm.

[0044] As Figure 5 shown in the figure, in this embodiment, three water inlets and three water outlets are circumferentially arranged at the tail of the probe. Among them, the centers of the water inlet (7), the water outlet (12), the cable channel (9), and the cable channel (10) are collinear; the No. 1 water inlet (6) and the No. 3 water inlet (8) are symmetrically arranged on both sides of the No. 2 water inlet (7), and the No. 1 water outlet (11) and the No. 3 water outlet (13) are symmetrically arranged on both sides of the No. 2 water outlet (12); cooling water enters through the three water inlets, which can ensure uniform water inlet, avoid the occurrence of cavities inside the probe and insufficient heat exchange, and thus prevent local ablation; the circumferential angles between the water inlets (6), (8) and the water inlet (7) at the tail of the probe are 60°, and the circumferential angles between the No. 1 water outlet (11), the No. 3 water outlet (13) and the No. 2 water outlet (12) are 60°.

[0045] Figure 6 Shown is a cross-sectional view of the internal plug (14) of the probe introduced in this embodiment. The top cross-section of the plug passes through the central axis of the middle pressure sensing hole (1).

[0046] As Figure 7 shown in the figure, in this embodiment, the probe internally contains a plug (14) with a vortex generating device (15) on the water inlet side; cooling water enters the probe through the three No. 1 water inlets (6), No. 2 water inlets (7), and No. 3 water inlets (8) arranged at wide circumferential angles, flows into the probe from the water inlet side of the plug (14), and generates turbulence after passing through the vortex generating device (15), strengthening the convective heat transfer between the cooling water and the shell wall near the middle pressure sensing hole (1) and the top pressure sensing hole (2); at the same time, the structure of the vortex generating device (15) itself has outward protruding fins, which also helps the convective heat transfer between the cooling water inside the probe and the plug; the plug is directly connected to the probe housing, and the heat can be quickly transferred from the probe housing to the plug area through heat conduction, thereby enhancing the overall heat dissipation effect of the probe; the thickness of the plug (14) inside the probe is 3 mm, and the outer extension length is 0.6 mm.

[0047] Further, a water-cooled pressure probe for measuring the three-dimensional dynamic high-temperature flow field between turbine stages is calibrated in a calibration wind tunnel. The calibrated Mach number range is 0.1 Mach to 0.9 Mach, the deflection angle is -80° to 80°, and the pitch angle is -40° to 40°. The calibration method includes the following steps:

[0048] Step 1: Clamp the probe using a displacement mechanism and adjust the probe position so that the pressure sensing hole (1) in the middle of the probe head is basically facing the airflow direction. Next, rotate the probe 80° clockwise and counterclockwise respectively, measure the measured pressure P1 of the middle pressure sensing hole (1) and the measured pressure P4 of the top pressure sensing hole (2) at different angles, and use polynomial fitting to obtain the calibration curve of P1 and the deflection angle α;

[0049] Step 2: Repeat Step 1 after adjusting the pitch angle of the probe using the displacement mechanism to obtain the calibration curves of the measured pressure P1 of the middle pressure sensing hole (1), the measured pressure P2 of the top pressure sensing hole (2), the deflection angle α, and the pitch angle β at different pitch angles β of the probe; In particular, the maximum value P of P1 on each calibration curve 1max is the total pressure of the incoming flow, and the pressure value corresponding to the rotation angle (α ± 40°) that is 40° apart from the angle α0 corresponding to P 1max is the static pressure, and the pitch angle corresponding to the angle β0 corresponding to P 1max is 0°;

[0050] Step 3: Define the pitch angle coefficient as:

[0051]

[0052] where K β 、K t 、K s are the pitch angle coefficient, the total pressure coefficient, and the static pressure coefficient respectively, p1 is the pressure measured by the middle pressure sensing hole (1), p 1max is the maximum pressure measured by the middle pressure sensing hole (1) at the current pitch angle, p4 is the pressure measured by the top pressure sensing hole (2), p t is the total pressure of the incoming flow, p s is the static pressure of the incoming flow;

[0053] Using the above definitions, obtain the calibration surfaces of the pitch angle coefficient, the total pressure coefficient, and the static pressure coefficient at different deflection angles;

[0054] During actual measurement, drive the probe to rotate using a displacement mechanism to obtain the pressure values of the middle pressure sensing hole (1) and the top pressure sensing hole (2) at different deflection angles. According to the definitions of the pitch angle coefficient, the total pressure coefficient, and the static pressure coefficient in Step 1, Step 2, and Step 3, and then calculate the actual measured deflection angle, pitch angle, total pressure, static pressure, and Mach number by interpolating the calibration surface.

[0055] A water-cooled pressure probe for measuring the three-dimensional dynamic high-temperature flow field between turbine stages introduced in the embodiments of the present invention can obtain calibration data through calibration in a calibration wind tunnel. When actually measuring the three-dimensional flow field between the turbine stages of an aero-engine, the pressure sensing holes (1) in the middle of the head of the cylindrical double-hole water-cooled dynamic pressure probe are facing the oncoming flow direction, the pitch angle is measured by the pressure sensing hole (2) at the top, and the deflection angle of the probe is adjusted by using a displacement mechanism. The flow field under different working conditions is measured at different deflection angles. Several sets of unsteady pressure data are measured by the dynamic pressure sensor inside the probe, and data processing is carried out by using the obtained calibration data of the calibration wind tunnel, so that three-dimensional flow parameters such as pitch angle, deflection angle, total pressure, static pressure, Mach number, etc. in the three-dimensional flow field between the turbine stages of the aero-engine can be obtained. After cooling water is introduced, dynamic measurement of flow field parameters can be realized in a high-temperature environment of 2000K, and the frequency response of the probe exceeds 25kHz.

Claims

1. A water-cooled pressure probe for measuring three-dimensional dynamic high-temperature flow fields between turbine stages, characterized in that: The probe support rod comprises a middle pressure sensing hole (1), a top pressure sensing hole (2), a probe support rod (3), a mounting seat (4), a locking cover (5), a No. 1 water inlet (6), a No. 2 water inlet (7), a No. 3 water inlet (8), a No. 1 cable channel (9), a No. 2 cable channel (10), a No. 1 water outlet (11), a No. 2 water outlet (12), and a No. 3 water outlet (13); an insert plate (14) is provided inside the probe support rod; a vortex generating device (15) is provided on the water inlet side surface of the insert plate, which can generate turbulence on the water inlet side to enhance heat exchange; The probe head has a diameter of 4 mm to 12 mm and a length of 12 mm to 50 mm. The inner and outer edges of the head are continuously rounded with a radius of 0.2 mm to 1.5 mm. The probe support rod (3) is cylindrical with a diameter of 10 mm to 20 mm. The probe shell is made of stainless steel and is coated with a high temperature resistant heat insulating coating. The middle pressure sensing hole (1) has a bending angle of 75° to 105°, a diameter of 0.6 mm to 1.5 mm, and a distance between the center line of the middle pressure sensing hole (1) and the lowest point of the cylindrical oblique section of 1 mm to 5 mm; the top pressure sensing hole (2) has a bending angle of 120° to 160°, a diameter of 0.6 mm to 1.5 mm, and a distance between the center line of the top pressure sensing hole (2) and the lowest point of the cylindrical oblique section of 1 mm to 5 mm; The plug plate (14) is perpendicular to the central axis of the top pressure sensing hole (2) and evenly divides the inside of the probe support rod into two parts. The thickness of the plug plate (14) is 1 mm to 3 mm. The vortex generating device (15) is a "V"-shaped rib, the "V"-shaped angle is 30° to 60°, and the extension length is 0.5 mm to 1.5 mm. The sensor is installed on the probe head, and the number of sensors is consistent with the number of pressure measuring holes. The sensor cable is set inside the probe and led out from the tail of the probe. The sensor measurement accuracy is 0.1% to 0.5%, and the natural frequency is 300Hz to 500kHz. The probe tail is provided with three water inlets and three water outlets arranged at a wide angle in the circumferential direction, wherein the centers of the No. 2 water inlet (7), the No. 2 water outlet (12), the No. 1 cable channel (9), and the No. 2 cable channel (10) are collinear; the circumferential angles between the No. 1 water inlet (6), the No. 3 water inlet (8) and the No. 2 water inlet (7) are 40° to 80°, and the circumferential angles between the No. 1 water outlet (11), the No. 3 water outlet (13) and the No. 2 water outlet (12) are 40° to 80°.

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