Water-cooling steady-state pressure probe with inward-concave quadrangular frustum pyramid structure at head

Abstract

The utility model belongs to the technical field of high-temperature pressure testing, and discloses a water-cooling steady-state pressure probe with a concave quadrangular frustum pyramid structure at the head for measuring a three-dimensional flow field at an outlet of a combustion chamber of an aero-engine, which is characterized by comprising a probe support rod, a probe head with a concave quadrangular frustum pyramid and a cooling structure in the probe head, the middle pressure measuring hole is located in the center of the upper bottom face of the quadrangular frustum pyramid, and the other four pressure measuring holes are located in the centers of the four side faces of the quadrangular frustum pyramid respectively. Three water inlet pipelines are arranged in the probe head and the supporting rod, the sections of water outlets of the water inlet pipelines are inclined, and the water inlet pipelines are located near the concave shell of the probe head and have special reinforcement measures. Water inlets of the water inlet pipelines are located at the tail of the probe, and meanwhile, four water outlets are evenly distributed in the tail of the probe in the circumferential direction, so that uneven stress distribution of the tail of the probe during water drainage is avoided. The device can measure parameters such as a pitch angle, a deflection angle, a Mach number, total pressure and static pressure of a three-dimensional flow field at an outlet of a combustion chamber of an aero-engine.

Description

Technical Field

[0001] The present invention belongs to the technical field of high-temperature pressure testing, and relates to a steady-state pressure measurement device for a three-dimensional flow field. Specifically, it relates to a water-cooled steady-state pressure probe with an inner concave frustum structure at the head, which is suitable for 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 at the combustion chamber outlet. Background Art

[0002] The improvement of the thrust of an aeroengine depends on the increase in the temperature at the combustion chamber outlet of the engine. For every 100 °C increase in the temperature before the turbine of an aeroengine, the maximum output power will increase by about 14% - 19%, and the gas cycle utilization efficiency will increase by 4% - 8%. In order to pursue this goal, the temperature at the combustion chamber outlet of an aeroengine can reach above 2000K. However, the commonly used materials for manufacturing the probe housing, such as 304 stainless steel, have a melting point of about 800K - 1000K and cannot withstand the high temperature at the combustion chamber outlet of the aeroengine. In addition, the conventional "L"-shaped probe head cannot extend into a relatively narrow space, and the conventional probe head will also interfere with the measurement of various flow field parameters. This poses great difficulties for measuring parameters such as pressure and Mach number in the flow field at the combustion chamber outlet of an aeroengine.

[0003] Although the "L"-shaped structure of the existing probe head (patent for invention: a dynamic five-hole probe, 201710342115.2) can reduce the influence of the probe head on the measurement, the "L"-shaped extension is relatively long, which causes great difficulties for the sealing work of the test component. In addition, since this probe does not design an effective thermal protection structure, the probe housing is extremely easy to be damaged during the measurement process, seriously affecting the progress of the experiment. Moreover, the existing probe with a water-cooling structure (patent for invention: a water-cooled probe, 2017207630951) can achieve a certain thermal protection effect, but there are still problems such as not having a high enough working temperature, a large volume, and being unable to measure three-dimensional flow field parameters.

[0004] Therefore, there is an urgent need to develop a three-dimensional, high-precision pressure probe that can work stably and reliably in a high-temperature environment, and has a good cooling effect on both the probe strut and the probe head, so as to meet the pressure test requirements in high-temperature environments with complex gas flows such as combustion chambers and turbines, and realize the steady-state measurement of parameters such as pitch angle, yaw angle, total pressure, static pressure, and Mach number in the flow field at high temperatures, providing excellent experimental data support for the design of high-performance advanced aeroengines.

[0005] The present invention relates to a water-cooled steady-state pressure probe with a concave frustum structure at the head, which can effectively cool the probe head and the support rod, and thus can perform steady-state pressure measurement of the flow field at high temperatures. At the same time, the probe can also extend into a relatively narrow space to measure the flow field parameters, and the interference of the probe head on the measurement of the flow field parameters is relatively small. After being calibrated in a calibration wind tunnel, the water-cooled steady-state pressure probe can perform steady-state measurement of parameters such as pitch angle, yaw angle, total pressure, static pressure, and Mach number of the flow field at high temperatures. Summary of the Invention

[0006] The technical problem to be solved by the present invention is that when measuring the three-dimensional flow field parameters at the outlet of the combustion chamber, the surrounding environment temperature is too high, which will damage the probe. Therefore, a cooling measure needs to be taken to reduce the overall temperature of the probe.

[0007] The present invention provides a water-cooled steady-state pressure five-hole probe with a concave frustum structure at the head and a special cooling structure inside the support rod. When measuring, cooling water is introduced into the water inlet of the probe water inlet channel, flows through the inside of the probe, and is discharged through the drain port at the tail of the probe. Compared with the existing probes, the probe head with a concave frustum can effectively reduce the volume of the probe head, enabling the probe to measure in a smaller space. At the same time, the pressure measurement channels on the side wall of the concave frustum are relatively dispersed, which is conducive to the heat exchange between the cooling water inside the probe and the wall of the pressure measurement channel, making the probe have stronger high-temperature resistance, so as to measure the three-dimensional flow field at the outlet of the aero-engine combustion chamber.

[0008] The solution of the present invention is as follows:

[0009] 1. A water-cooled steady-state pressure probe with a concave frustum structure at the head, characterized in that it includes a probe head (1), a probe support rod (2), a middle pressure measurement channel (3), a left pressure measurement channel (4), a right pressure measurement channel (5), an upper pressure measurement channel (6), a lower pressure measurement channel (7), a No. 1 water inlet channel (8), a No. 2 water inlet channel (9), a No. 3 water inlet channel (10), a No. 1 drain port (11), a No. 2 drain port (12), a No. 3 drain port (13), and a No. 4 drain port (14). A middle pressure measurement hole is opened on the upper bottom surface of the concave frustum, and four pressure measurement holes, namely left, right, upper, and lower, are opened on the side surface of the concave frustum, corresponding to the middle pressure measurement channel (3), the left pressure measurement channel (4), the right pressure measurement channel (5), the upper pressure measurement channel (6), and the lower pressure measurement channel (7) respectively. The center lines of each pressure measurement channel are perpendicular to the side surface or the upper bottom surface where the channel is located;

[0010] 2. Further, except for the concave part, the probe head (1) is composed of a hemisphere and a cylinder with a common bottom surface, with a diameter of 4 mm to 16 mm and a total length of 8 mm to 50 mm. The probe support rod (2) has a cylindrical shape, with a diameter of 8 mm to 32 mm and a length of 200 mm to 500 mm;

[0011] 3. Further, the concave surface of the probe head (1) is the upper bottom surface and its four side surfaces of a frustum of a quadrangular pyramid. The included angle between the side surface of the frustum of the quadrangular pyramid and the upper bottom surface is 100° - 160°. The upper bottom surface is a square with a side length of 1 mm - 4 mm. The central axis of the upper bottom surface of the frustum of the quadrangular pyramid is perpendicularly intersected with the central axis of the cylinder of the probe head (1), and the distance from the upper bottom surface of the concave frustum of the quadrangular pyramid to the central axis of the cylinder of the probe head (1) is 0 mm - 6 mm. At the connection between the side surface of the concave frustum of the quadrangular pyramid and the shell of the probe head (1), a double-twist line transition is adopted to reduce the separation of the air flow;

[0012] 4. Further, the water inlet system inside the probe consists of three water inlet channels. The No. 1 water inlet channel (8), the No. 2 water inlet channel (9), and the No. 3 water inlet channel (10) are circumferentially and uniformly distributed, with a diameter of 2 mm - 4 mm, and the distance from their central axes to the overall central axis of the probe is 4 mm - 7 mm. The No. 1 water inlet channel (8) and the No. 2 water inlet channel (9) are symmetrical. The lowest points of the inclined surfaces of the water outlets of these two water inlet channels are both 8 mm - 16 mm away from the highest point of the probe head (1), and the acute angles formed by the inclined surfaces of the water outlets of these two water inlet channels and the upper bottom surface of the concave frustum of the quadrangular pyramid are both 50° - 70°. The water inlet channel (10) is located directly below the concave frustum of the quadrangular pyramid. The highest point of the inclined surface of this water inlet channel is 2.5 mm - 4 mm away from the lowest point of the side surface of the concave frustum of the quadrangular pyramid where the lower pressure measurement channel (7) is located, and the acute angle formed by the inclined surface of the water outlet of this water inlet channel and the upper bottom surface of the concave frustum of the quadrangular pyramid is 50° - 70°;

[0013] 5. Further, the No. 1 drain port (11), the No. 2 drain port (12), the No. 3 drain port (13), and the No. 4 drain port (14) are circumferentially and uniformly arranged at the bottom of the probe. The diameter of each drain port is 2 mm - 5 mm, and the distance from the center of each drain port to the central axis of the probe support rod (2) is 3 mm - 8 mm.

[0014] In the present invention, a water-cooled steady-state pressure probe with a concave frustum of a quadrangular pyramid structure at the head can obtain calibration data through calibration in a wind tunnel. When actually measuring the three-dimensional flow field at the outlet of an aero-engine combustion chamber, the pressure measurement channel (3) in the probe head is aligned with the oncoming flow direction, and a displacement mechanism is used to adjust the pitch angle and yaw angle of the probe comb. The flow field under different working conditions is measured at different pitch angles and yaw angles respectively; by using the calibration data obtained from the calibration in the wind tunnel for data processing, three-dimensional flow parameters such as pitch angle, yaw angle, total pressure, static pressure, and Mach number in the three-dimensional flow field at the outlet of the aero-engine combustion chamber can be obtained.

[0015] The present invention, a water-cooled steady-state pressure probe with a concave frustum of a quadrangular pyramid structure at the head, has the following beneficial effects:

[0016] Beneficial effect 1: It can significantly reduce the temperature of the probe housing and can be used for measuring the three-dimensional flow field at the outlet of an aero-engine combustion chamber. Due to the water-cooling structure, after injecting cooling water, the overall cooling effect of the probe is improved, so that when the probe is in a high-temperature environment of 2000K, the temperature of the probe housing can be reduced to below 800K. After being calibrated in a calibration wind tunnel, the invention can be used to measure parameters such as total pressure, static pressure, pitch angle, yaw angle, Mach number, etc. of the three-dimensional flow field at the outlet of an aero-engine combustion chamber, providing measured data for improving the performance of the aero-engine combustion chamber.

[0017] Beneficial effect 2: It reduces the difficulty of sealing the probe strut and the measurement window during testing. Compared with the original "L"-shaped steady-state five-hole pressure probe, this probe can be used for testing in an environment with a relatively narrow space, reducing the difficulty of sealing the probe strut and the measurement window during testing.

[0018] Beneficial effect 3: It reduces the interference of the probe head on the measurement of flow field parameters. The probe head is composed of a hemisphere and a cylinder with a common bottom surface, which can effectively reduce the interference of the probe head on the measurement of flow field parameters.

[0019] Beneficial effect 4: The probe has stronger high-temperature resistance and a longer service life. The five pressure measurement channels are relatively scattered near the pressure measurement holes, which can strengthen the heat exchange between the cooling water and the pressure measurement channels, making the overall probe have stronger high-temperature resistance. And the centerlines of the five pressure measurement channels are perpendicular to the plane where the pressure measurement holes of each pipeline are located, which can prevent the high-temperature gas from directly scouring the wall surface of the pressure measurement channel housing, reducing the thermal stress of the pressure measurement channel housing and extending the service life of the probe.

[0020] Beneficial effect 5: When the coolant enters through the three water inlets, it can ensure uniform water inlet, avoid the occurrence of cavities inside the probe and insufficient heat exchange, and further prevent local ablation. At the same time, the water outlet of the water inlet channel is directly opposite to the concave position of the probe head, which can strengthen the impingement cooling effect at this position.

[0021] Beneficial effect 6: An integrated reinforcement structure is designed at a certain distance from the water outlet of the small water inlet channel. This reinforcement structure can effectively reinforce the water inlet pipe and the probe head housing, avoiding damage to the water inlet channel and the probe head housing. At the same time, the contact area between this reinforcement structure and the probe head housing is relatively large, and it can effectively transfer the heat of the probe head shell to the water inlet channel through heat conduction. And the contact area between the water inlet channel and the cooling water is very large, so the heat can be quickly transferred to the cooling water through convective heat transfer;

[0022] Beneficial effect 7: Four drain holes are evenly arranged circumferentially at the bottom of the probe, which can prevent stress concentration of the probe housing caused by excessive local water pressure. Description of the Drawings

[0023] Figure 1 This is a schematic diagram of the overall structure of a water-cooled steady-state pressure probe with an inner concave structure at the head in the first embodiment of the present invention.

[0024] Figure 2 This is a top view of the schematic diagram of the overall structure of a water-cooled steady-state pressure probe with an inner concave structure at the head in the first embodiment of the present invention.

[0025] Figure 3 This is a sectional view taken along the A-A section.

[0026] Figure 4 This is a sectional view taken along the B-B section.

[0027] Figure 5 This is a sectional view taken along the C-C section.

[0028] Figure 6 This is a sectional view taken along the D-D section.

[0029] Figure 7 This is a schematic diagram of the structure of a water-cooled steady-state pressure probe with an inner concave triangular prism structure at the head in the second embodiment of the present invention.

[0030] Figure 8 This is Figure 7 a sectional view taken along the E-E section of

[0031] Figure 9 This is a schematic diagram of the structure of a water-cooled steady-state pressure probe with an inner concave hexagonal prism structure at the head in the third embodiment of the present invention.

[0032] Figure 10 This is Figure 9 a sectional view taken along the E-E section of

[0033] Wherein: 1 - probe head, 2 - probe rod, 3 - middle pressure measurement channel, 4 - left pressure measurement channel, 5 - right pressure measurement channel, 6 - upper pressure measurement channel, 7 - lower pressure measurement channel, 8 - No. 1 water inlet channel, 9 - No. 2 water inlet channel, 10 - No. 3 water inlet channel, 11 - No. 1 drain port, 12 - No. 2 drain port, 13 - No. 3 drain port, 14 - No. 4 drain port, 15 - No. 1 pressure measurement channel, 16 - No. 2 pressure measurement channel, 17 - No. 3 pressure measurement channel, 18 - No. 4 pressure measurement channel, 19 - No. 5 pressure measurement channel, 20 - No. 6 pressure measurement channel, 21 - No. 7 pressure measurement channel, 22 - No. 8 pressure measurement channel, 23 - No. 9 pressure measurement channel, 24 - No. 10 pressure measurement channel, 25 - No. 11 pressure measurement channel. Specific embodiments

[0034] The present invention will be described in detail below in conjunction with the accompanying drawings and three specific implementation cases, so that the advantages and features of the present invention can be more easily understood by those skilled in the art, thereby making the protection scope of the present invention more clearly defined.

[0035] Specific implementation case 1:

[0036] As Figure 1 shown in Figure 2 In this embodiment, a water-cooled steady-state pressure probe with an inner concave frustum structure on the head is introduced. It is characterized in that it includes a probe head (1) with an inner concave frustum structure, a probe rod (2), a middle pressure measurement channel (3), a left pressure measurement channel (4), a right pressure measurement channel (5), an upper pressure measurement channel (6), a lower pressure measurement channel (7), a No. 1 water inlet channel (8), a No. 2 water inlet channel (9), a No. 3 water inlet channel (10), a No. 1 drain port (11), a No. 2 drain port (12), a No. 3 drain port (13), and a No. 4 drain port (14). The probe head (1) is composed of a hemisphere and a cylinder with a common bottom surface, with a diameter of 16 mm and a length of 35 mm. The probe rod (2) has a cylindrical shape, with a diameter of 24 mm and a length of 300 mm. The concave surface of the probe head (1) is the upper bottom surface of the frustum and its four side surfaces. The included angle between the side surface of the frustum and the upper bottom surface is 118°. The upper bottom surface is a square with a side length of 2 mm. The center line of the upper bottom surface of the frustum is perpendicular to the central axis of the cylinder of the probe head, and the central axis of the cylinder of the probe head (1) is in the plane where the upper bottom surface of the inner concave frustum is located. At the connection between the side surface of the inner concave frustum and the probe head (1), a double-twist line transition is used to reduce the separation of the air flow.

[0037] Part of the cooling structure inside the probe is as Figure 3 shown. The No. 3 water inlet channel (10) of the probe is located directly below the inner concave frustum. The distance from the highest point of the inclined surface of this water inlet channel to the lowest point of the side surface of the inner concave frustum where the lower pressure measurement channel (7) is located is 3 mm, and the acute angle between the inclined surface of the water outlet of this water inlet channel and the upper bottom surface of the inner concave frustum is 60°.

[0038] The relative positions of the water inlet channels inside the probe are as Figure 4 shown. The water inlet system inside the probe consists of three water inlet channels. The No. 1 water inlet channel (8), the No. 2 water inlet channel (9), and the No. 3 water inlet channel (10) are circumferentially and evenly distributed, with a diameter of 3 mm. The distance from their central axes to the overall central axis of the probe is 4 mm, and the No. 1 water inlet channel (8) and the No. 2 water inlet channel (9) are symmetric.

[0039] The No. 2 water inlet channel (9) inside the probe is as Figure 5 shown. The distance from the lowest point of the inclined surface of the water outlet of the No. 2 water inlet channel (9) inside the probe to the highest point of the probe head is 10 mm, and the acute angle between the inclined surface of the water outlet of this water inlet channel and the upper bottom surface of the inner concave frustum is 62°.

[0040] The distribution of the drain ports at the bottom of the probe is as Figure 6As shown, 1st drain port (11), 2nd drain port (12), 3rd drain port (13), and 4th drain port (14) are evenly arranged circumferentially at the bottom of the probe. The diameter of each drain port is 3 mm, and the center of each drain port is 5 mm away from the central axis of the probe support rod (2).

[0041] A water-cooled steady-state pressure probe with an inner concave frustum of a pyramid structure at the head introduced in the embodiment of the present invention can obtain calibration data through calibration in a wind tunnel. When actually measuring the three-dimensional flow field at the outlet of an aero-engine combustion chamber, the pressure measurement channel (3) in the head of the water-cooled steady-state pressure probe is facing the oncoming flow direction, and a displacement mechanism is used to adjust the pitch angle and yaw angle of the probe comb. The flow field under different working conditions is measured at different pitch angles and yaw angles. By using the obtained calibration data from the calibration wind tunnel for data processing, three-dimensional flow parameters such as pitch angle, yaw angle, total pressure, static pressure, and Mach number in the three-dimensional flow field at the outlet of the aero-engine combustion chamber can be obtained.

[0042] Specific implementation case two:

[0043] As Figure 7 shown, this embodiment introduces a water-cooled steady-state pressure probe with an inner concave triangular frustum structure at the head, which is characterized in that it includes a probe head (1) with an inner concave frustum of a pyramid structure, a probe support rod (2), a 1st pressure measurement channel (15), a 2nd pressure measurement channel (16), a 3rd pressure measurement channel (17), a 4th pressure measurement channel (18), a 1st water inlet channel (8), a 2nd water inlet channel (9), a 3rd water inlet channel (10), a 1st drain port (11), a 2nd drain port (12), a 3rd drain port (13), and a 4th drain port (14). The probe head (1) is composed of a hemisphere and a cylinder with a common bottom surface, with a diameter of 16 mm and a length of 35 mm. The probe support rod (2) has a cylindrical shape, with a diameter of 24 mm and a length of 300 mm.

[0044] The concave surface of the probe head (1) is the upper bottom surface of the triangular frustum and its three side surfaces. The angle between the side surface of the triangular frustum and the upper bottom surface is 125°. The upper bottom surface is an equilateral triangle with a side length of 3 mm. The center line of the upper bottom surface of the triangular frustum is perpendicular to and intersects the central axis of the cylinder of the probe head, and the central axis of the cylinder of the probe head (1) lies in the plane where the upper bottom surface of the inner concave triangular frustum is located; at the connection between the side surface of the inner concave triangular frustum and the probe head (1), a double-twist line transition is used to reduce the separation of the air flow.

[0045] The internal cooling structure of this probe is the same as that of Embodiment 1, and the layout of its cooling pipes and the distribution of drain ports at the bottom of the probe are as Figure 8As shown, the water inlet system inside the probe consists of three water inlet channels. The No. 1 water inlet channel (8), No. 2 water inlet channel (9), and No. 3 water inlet channel (10) are evenly distributed circumferentially, with a diameter of 3 mm. The distance between their central axes and the overall central axis of the probe is 4 mm. The No. 1 water inlet channel (8) and the No. 2 water inlet channel (9) are symmetrical. The No. 1 drain port (11), No. 2 drain port (12), No. 3 drain port (13), and No. 4 drain port (14) are evenly arranged circumferentially at the bottom of the probe. The diameter of each drain port is 3 mm, and the distance from the center of each drain port to the central axis of the probe support rod (2) is 5 mm.

[0046] In the example of the present invention, a water-cooled steady-state pressure probe with an inner concave triangular prism structure at the head is introduced. After calibration in a wind tunnel, calibration data can be obtained. When actually measuring the three-dimensional flow field at the outlet of an aeroengine combustion chamber, the No. 1 pressure measurement channel (15) at the head of the water-cooled steady-state pressure probe is facing the oncoming flow direction, and a displacement mechanism is used to adjust the pitch angle and yaw angle of the probe comb. The flow field under different working conditions is measured at different pitch angles and yaw angles. By using the calibration data obtained from the calibration wind tunnel for data processing, three-dimensional flow parameters such as pitch angle, yaw angle, total pressure, static pressure, and Mach number in the three-dimensional flow field at the outlet of the aeroengine combustion chamber can be obtained.

[0047] Specific implementation case three:

[0048] As Figure 9 shown, this embodiment introduces a water-cooled steady-state pressure probe with an inner concave hexagonal prism structure at the head, which is characterized in that it includes a probe head (1) with an inner concave hexagonal prism structure, a probe support rod (2), a No. 5 pressure measurement channel (19), a No. 6 pressure measurement channel (20), a No. 7 pressure measurement channel (21), a No. 8 pressure measurement channel (22), a No. 9 pressure measurement channel (23), a No. 10 pressure measurement channel (24), a No. 11 pressure measurement channel (25), a No. 1 water inlet channel (8), a No. 2 water inlet channel (9), a No. 3 water inlet channel (10), a No. 1 drain port (11), a No. 2 drain port (12), a No. 3 drain port (13), and a No. 4 drain port (14). The probe head (1) is composed of a hemisphere and a cylinder with a common bottom surface, with a diameter of 16 mm and a length of 35 mm. The probe support rod (2) has a cylindrical shape, with a diameter of 24 mm and a length of 300 mm.

[0049] The concave surface of the probe head (1) is the upper bottom surface of the hexagonal prism and its six side surfaces. The angle between the side surface of the hexagonal prism and the upper bottom surface is 108°. The upper bottom surface is a regular hexagon with a side length of 3 mm. The central axis of the upper bottom surface of the hexagonal prism is perpendicular to and intersects with the central axis of the cylinder of the probe head, and the distance between the central axis of the cylinder of the probe head (1) and the plane where the upper bottom surface of the inner concave hexagonal prism is located is 3 mm; at the connection between the side surface of the inner concave hexagonal prism and the probe head (1), a Vitosinsky curve is used for transition to reduce the separation of the air flow.

[0050] The internal cooling structure of this probe is the same as that of the first embodiment. The layout of its cooling pipes and the distribution of the drain ports at the bottom of the probe are as Figure 10 shown. The water inlet system inside the probe consists of three water inlet channels. The No. 1 water inlet channel (8), the No. 2 water inlet channel (9), and the No. 3 water inlet channel (10) are circumferentially and evenly distributed, with a diameter of 3 mm. The distance between their central axes and the overall central axis of the probe is 4 mm. The No. 1 water inlet channel (8) and the No. 2 water inlet channel (9) are symmetrical. The No. 1 drain port (11), the No. 2 drain port (12), the No. 3 drain port (13), and the No. 4 drain port (14) are circumferentially and evenly arranged at the bottom of the probe. The diameter of each drain port is 3 mm, and the distance from the center of each drain port to the central axis of the probe support rod (2) is 5 mm.

[0051] A water-cooled steady-state pressure probe with an internally concave hexagonal frustum structure at the head introduced in the example of the present invention can obtain calibration data through calibration in a wind tunnel. When actually measuring the three-dimensional flow field at the outlet of an aeroengine combustion chamber, the No. 5 pressure measurement channel (19) at the head of this water-cooled steady-state pressure probe is facing the oncoming flow direction, and a displacement mechanism is used to adjust the pitch angle and yaw angle of this probe comb. The flow field under different working conditions is measured at different pitch angles and yaw angles. By using the calibration data obtained from the calibration in the wind tunnel for data processing, three-dimensional flow parameters such as pitch angle, yaw angle, total pressure, static pressure, and Mach number in the three-dimensional flow field at the outlet of the aeroengine combustion chamber can be obtained.

Claims

1. A water-cooled steady-state pressure probe with a concave quadrangular pyramid structure on the head, characterized in that: The probe comprises a probe head (1), a probe support rod (2), a middle pressure measuring channel (3), a left pressure measuring channel (4), a right pressure measuring channel (5), an upper pressure measuring channel (6), a lower pressure measuring channel (7), a No. 1 water inlet channel (8), a No. 2 water inlet channel (9), a No. 3 water inlet channel (10), a No. 1 drainage outlet (11), a No. 2 drainage outlet (12), a No. 3 drainage outlet (13), and a No. 4 drainage outlet (14); wherein the concave surface of the probe head is a side surface of a quadrangular pyramid and an upper bottom surface of the quadrangular pyramid, and the concave surface is provided with five pressure measuring holes , respectively corresponding to the middle pressure measuring channel (3), the left pressure measuring channel (4), the right pressure measuring channel (5), the upper pressure measuring channel (6), and the lower pressure measuring channel (7); a double twisted line transition is used at the connection between the side of the concave quadrangular pyramid and the probe head shell to reduce the separation of the airflow; the center line of the middle pressure measuring channel (3) is tangent to the central axis of the quadrangular pyramid, and the center lines of the left pressure measuring channel (4), the right pressure measuring channel (5), the upper pressure measuring channel (6), and the lower pressure measuring channel (7) are respectively perpendicular to the side of the concave quadrangular pyramid where the pressure measuring channels are located; The probe head, except for the concave part, is composed of a hemisphere and a cylinder with a common bottom surface, with a diameter of 4 mm to 16 mm and a total length of 8 mm to 50 mm; The probe support rod shell is a cylinder with a diameter of 8 mm to 24 mm; The concave surface of the probe head is the upper bottom surface of a quadrangular pyramid and its four side surfaces, the angle between the side surface of the quadrangular pyramid and the upper bottom surface is 100° to 160°, the upper bottom surface is a square with a side length of 1 mm to 4 mm, the center line of the upper bottom surface of the quadrangular pyramid intersects perpendicularly with the central axis of the cylindrical body of the probe head, and the upper bottom surface of the concave quadrangular pyramid is 0 mm to 6 mm away from the central axis of the cylindrical body of the probe head; The water inlet system inside the probe is composed of three water inlet channels with water outlets as inclined surfaces, wherein the No. 1 water inlet channel (8), the No. 2 water inlet channel (9), and the No. 3 water inlet channel (10) are evenly distributed in the circumferential direction, and have a diameter of 2 mm to 4 mm, and the distance between the axis and the central axis of the probe as a whole is 4 mm to 7 mm; the No. 1 water inlet channel (8) and the No. 2 water inlet channel (9) are symmetrical, and the distance between the lowest point of the inclined surface of the water outlets of the two water inlet channels and the highest point of the probe head is 8 mm to 16 mm, and the acute angle between the inclined surface of the water outlets of the two water inlet channels and the bottom surface of the concave quadrangular prism is 50° to 70°; the No. 3 water inlet channel (10) is located directly below the concave quadrangular prism, and the distance between the highest point of the inclined surface of the water inlet channel and the lowest point of the side surface of the concave quadrangular prism where the lower pressure measuring channel (7) is located is 2.5 mm to 4 mm, and the acute angle between the inclined surface of the water outlet of the water inlet channel and the bottom surface of the concave quadrangular prism is 50° to 70°; A No. 1 drain port (11), a No. 2 drain port (12), a No. 3 drain port (13), and a No. 4 drain port (14) are evenly arranged around the bottom of the probe. The diameter of each drain port is 2 mm to 5 mm, and the center of each drain port is 3 mm to 8 mm away from the central axis of the probe support rod.

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