Concave ball socket probe for measuring three-dimensional steady-state high-temperature flow field

Abstract

The utility model belongs to the technical field of high-temperature pressure testing, and discloses an inward-concave ball socket probe for measuring a three-dimensional steady-state high-temperature flow field, which is characterized by comprising a probe support rod, a probe head with an inward recess and a cooling structure in the probe head, the probe head is provided with five pressure measuring holes, a pressure guide pipe is packaged in the probe support rod, and the probe support rod is provided with a pressure sensor. One end is communicated with the pressure sensing hole of the probe head, and the other end is led out from the tail of the probe support rod. Five water inlet pipelines are arranged in the probe head and the support rod, water inlets of the water inlet pipelines are arranged at the tail of the probe, water outlets of the water inlet pipelines are arranged near a concave shell of the probe head, special reinforcement measures are provided, and water outlets are circumferentially and uniformly arranged at the tail of the probe, so that stress concentration at the tail of the support rod of the probe during water drainage can be reduced, and the service life of the probe is prolonged. The device can measure the pitch angle, the deflection angle, the Mach number, the total pressure, the static pressure and other parameters of the three-dimensional flow field at the outlet of the aero-engine combustion chamber.

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 concave spherical socket probe for measuring a three-dimensional steady-state high-temperature flow field, 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 combustor outlet. Background Art

[0002] The increase in the thrust of an aeroengine depends on the increase in the temperature at the combustor 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 combustor 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 combustor outlet of an aeroengine. Moreover, 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 combustor 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 part is relatively long, which causes great difficulties for the sealing work of the test component. In addition, since this probe does not design a corresponding 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 airflows such as combustors 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 concave spherical socket probe for measuring a three-dimensional steady-state high-temperature flow field, which can effectively cool the probe head and the strut, 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 also 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 pressure of the three-dimensional flow field at the combustion chamber outlet, the surrounding environment temperature is too high, and the too high temperature will damage the probe. Therefore, a cooling measure needs to be taken to reduce the temperature around the probe strut.

[0007] To this end, the present invention provides a water-cooled pressure probe for measuring a three-dimensional steady-state flow field, with an inner concave structure at the head and a special cooling structure inside the strut. During measurement, the coolant is introduced into the probe water inlet, flows through the inside of the probe, and is discharged through the drain pipe. Compared with the original probe, the probe head with an inner concave structure can effectively reduce the volume of the probe head, enabling the probe to measure in a narrower space. At the same time, a special cooling structure is added inside the probe, which can effectively cool the whole probe, making the probe have stronger high-temperature resistance and be more suitable for measuring the flow field at the combustion chamber outlet of an aeroengine.

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

[0009] 1. A concave spherical socket probe for measuring a three-dimensional steady-state high-temperature flow field, characterized in that it includes a probe head (1), a probe strut (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 small water inlet channel (8), a No. 2 small water inlet channel (9), a No. 3 small water inlet channel (10) and a small water inlet pipe support structure (11), a No. 1 large water inlet channel (12), a No. 2 large water inlet channel (13), a left drain port (14), an upper drain port (15), a right drain port (16), and a lower drain port (17);

[0010] 2. Further, the probe head (1) is composed of a hemisphere and a cylinder with a common bottom surface, its diameter is 4 mm to 16 mm, and its length is 8 mm to 50 mm. The diameter of the probe strut (2) is 8 mm to 24 mm, and its length is 150 mm to 300 mm;

[0011] 3. Further, the concave surface of the probe head (1) is a spherical crown surface, its diameter is 4 mm to 16 mm, and the center of the sphere of this spherical crown surface is 2 mm to 8 mm away from the central axis. At the connection between this spherical crown surface and the probe head (1), a Witoldski curve or a lemniscate is used for transition;

[0012] 4. Further, the water inlet system inside the probe consists of five water inlet channels. The No. 1 small water inlet channel (8), the No. 2 small water inlet channel (9), and the No. 3 small water inlet channel (10) are circumferentially distributed, and the included angle between two adjacent water inlet channels is 15° - 60°.

[0013] 5. Further, the water outlet of the No. 2 small water inlet channel (9) is directly opposite to the connection part of the lower pressure measurement channel (7) and the housing of the probe head (1), and the distance between the water outlet of the No. 2 small water inlet channel (9) and the central axis of the spherical crown surface is 2 mm - 6 mm.

[0014] 6. Further, the distances from the water outlets of the No. 1 small water inlet channel (8) and the No. 3 small water inlet channel (10) to the water outlet of the No. 2 small water inlet channel (9) are 2 mm - 4 mm.

[0015] 7. Further, at a position 3 mm - 8 mm away from the water outlet of the No. 2 small water inlet channel (9) is the support structure (11) of the small water inlet pipe, and the thickness of this support structure is 2 mm - 6 mm.

[0016] 8. Further, the No. 1 large water inlet channel (12) and the No. 2 large water inlet channel (13) are centrosymmetric about the central axis of the probe support rod (2), and the water outlets of the No. 1 large water inlet channel (12) and the No. 2 large water inlet channel (13) are directly opposite to the left pressure measurement channel (4) and the right pressure measurement channel (5) respectively.

[0017] 9. Further, the diameters of the No. 1 small water inlet channel (8), the No. 2 small water inlet channel (9), and the No. 3 small water inlet channel (10) are 1 mm - 3 mm, and the diameters of the No. 1 large water inlet channel (12) and the No. 2 large water inlet channel (13) are 2 mm - 4 mm.

[0018] 10. Further, the left drain port (14), the upper drain port (15), the right drain port (16), and the lower drain port (17) are circumferentially and evenly arranged at the bottom of the probe. The diameters of each drain port are 2 mm - 5 mm, and the distances from the centers of each drain port to the central axis of the probe support rod (2) are 3 mm - 8 mm.

[0019] The present invention, an in - concave spherical socket probe for measuring a three - dimensional steady - state high - temperature flow field, has the following beneficial effects:

[0020] Beneficial effect one: It 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, its overall temperature can be reduced to below 500K. After being calibrated in a calibration wind tunnel, the invention can be used to measure parameters such as the 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.

[0021] Beneficial effect 2: It can reduce the sealing difficulty of the probe rod 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 a relatively narrow space, reducing the sealing difficulty of the probe rod and the measurement window during testing.

[0022] Beneficial effect 3: It can reduce the interference of the probe head on the flow field. The probe head is composed of a hemisphere and a cylinder with a common bottom surface, which can effectively reduce the interference caused by the probe head on the measurement of flow field parameters.

[0023] Beneficial effect 4: It can avoid the occurrence of local ablation of the probe. When the coolant enters through the five water inlets, it can ensure uniform water inlet, avoid the appearance of cavities inside the probe and insufficient heat transfer, thereby preventing the occurrence of local ablation. At the same time, the outlet of the water inlet channel is directly opposite to the concave position of the probe head, which can strengthen the impact cooling effect at this position.

[0024] Beneficial effect 5: It can quickly transfer the heat on the surface of the probe housing to the cooling water inside the probe. An integrated reinforcing rib plate is designed at a certain distance from the outlet of the small water inlet channel. This reinforcing device 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 reinforcing device and the probe head housing is relatively large, which can effectively transfer the heat of the probe head to the reinforcing device by heat conduction, and the contact area between this device and the cooling water is very large, so the heat can be quickly transferred to the cooling water through convective heat transfer.

[0025] Beneficial effect 6: It can prevent stress concentration of the probe caused by excessive local water pressure. Four drain ports 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

[0026] Figure 1 It 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 an embodiment of the present invention.

[0027] Figure 2 It is a left view of the overall structure of a water-cooled steady-state pressure probe with an inner concave structure at the head in an embodiment of the present invention.

[0028] Figure 3 It is a sectional view taken along the line A-A.

[0029] Figure 4 It is a sectional view taken along the line B-B.

[0030] Figure 5 It is a sectional view taken along the line C-C.

[0031] Figure 6It is a sectional view taken along the D-D plane.

[0032] Figure 7 It is a sectional view taken along the E-E plane.

[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 small water inlet channel, 9 - No. 2 small water inlet channel, 10 - No. 3 small water inlet channel, 11 - small water inlet pipe support structure, 12 - No. 1 large water inlet channel, 13 - No. 2 large water inlet channel, 14 - left drain port, 15 - upper drain port, 16 - right drain port, 17 - lower drain port. Specific Embodiment

[0034] The present invention will be described in detail below in conjunction with the accompanying drawings and a specific embodiment, 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.

[0035] As Figure 1 shown in Figure 2 In this embodiment, a concave spherical socket probe for measuring a three-dimensional steady-state high-temperature flow field is introduced. It mainly consists of a probe head (1), 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 small water inlet channel (8), a No. 2 small water inlet channel (9), a No. 3 small water inlet channel (10) and a small water inlet pipe support structure (11), a No. 1 large water inlet channel (12), a No. 2 large water inlet channel (13), a left drain port (14), an upper drain port (15), a right drain port (16), and a lower drain port (17). Its characteristics are as follows: 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 20 mm and a length of 200 mm. The concave surface of the probe head (1) is a spherical crown surface with a diameter of 16 mm, and the center of the spherical crown surface is 8 mm away from the central axis. A Witowsky curve is used for transition at the connection between the crown surface and the probe head (1) to reduce the separation of the air flow. Five pressure measurement holes are evenly arranged in a "cross" shape on the probe head (1) in the concave part, 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).

[0036] The cooling structure inside the probe is as Figure 3As shown in the figure, the water inlet system inside the probe consists of five water inlet channels; the No. 1 small water inlet channel (8), the No. 2 small water inlet channel (9), and the No. 3 small water inlet channel (10) are circumferentially distributed, and the included angle between two adjacent water inlet channels is 28°; the No. 1 large water inlet channel (12) and the No. 2 large water inlet channel (13) are centrosymmetric about the central axis of the probe rod, and the water outlets of the No. 1 large water inlet channel (12) and the No. 2 large water inlet channel (13) are respectively facing the left pressure measurement channel (4) and the right pressure measurement channel (5). Among them, the diameters of the No. 1 small water inlet channel (8), the No. 2 small water inlet channel (9), and the No. 3 small water inlet channel (10) are 1.5 mm, and the diameters of the No. 1 large water inlet channel (12) and the No. 2 large water inlet channel (13) are 2.5 mm.

[0037] The distribution of the drain outlets at the bottom of the probe is as Figure 4 shown. The left drain outlet (14), the upper drain outlet (15), the right drain outlet (16), and the lower drain outlet (17) are evenly arranged circumferentially at the bottom of the probe. The diameter of each drain outlet is 3 mm, and the center of each drain outlet is 6 mm away from the central axis of the probe rod (2).

[0038] The cooling structure inside the probe is as Figure 5 shown. At a distance of 6 mm from the water outlet of the No. 1 large water inlet channel (12) is the small water inlet pipe support structure (11), and the thickness of this structure is 3 mm.

[0039] The cross-section of the reinforcement device at the probe head (1) is as Figure 6 shown. This small water inlet pipe support structure (11) can effectively reinforce the water inlet pipe and the shell of the probe head (1), avoiding damage to each water inlet channel and the shell of the probe head (1). At the same time, the contact area between the small water inlet pipe support structure (11) and the shell of the probe head (1) is relatively large, and the heat of the probe head (1) can be effectively transferred to the small water inlet pipe support structure (11) through heat conduction. And the contact area of this device with the cooling water is very large, so the heat can be transferred to the cooling water through convective heat transfer relatively quickly.

[0040] The cross-sectional positions of the drain outlets of each water inlet channel inside the probe are as Figure 7 shown. The water outlet of the No. 2 small water inlet channel (9) is facing the connection between the lower pressure measurement channel (7) and the shell of the probe head (1); the water outlet of the No. 2 small water inlet channel (9) is 6 mm away from the central axis of the spherical crown surface, and the water outlets of the No. 1 small water inlet channel (8) and the No. 3 small water inlet channel (10) are 2 mm away from the water outlet of the No. 2 small water inlet channel (9).

[0041] A concave spherical socket probe for measuring a three-dimensional steady-state high-temperature flow field 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 at the outlet of an aero-engine combustion chamber, the pressure sensing holes in the head of the water-cooled steady-state pressure probe are 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 fields under different operating conditions are 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 aero-engine combustion chamber can be obtained.

Claims

1. A concave ball-socket probe for measuring three-dimensional steady-state high-temperature flow fields, characterized in that: The probe head (1) comprises a 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) in a probe support rod (2), a No. 1 small water inlet channel (8), a No. 2 small water inlet channel (9), a No. 3 small water inlet channel (10) and a small water inlet pipe support structure (11), a No. 1 large water inlet channel (12), a No. 2 large water inlet channel (13), a left drainage port (14), an upper drainage port (15), a right drainage port (16), and a lower drainage port (17); the concave surface of the probe head (1) is a spherical crown surface, and a double twisted line or a Witosinski curve transition is adopted at the connection between the spherical crown surface and the probe head (1) to reduce the separation of airflow; The central axis of the middle pressure measuring channel (3) coincides with the central axis of the spherical crown surface of the probe head (1), and the central axes 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 parallel to the central axis of the spherical crown surface; The probe head (1) is composed of a hemisphere and a cylinder with a common bottom surface, and has a diameter of 4 mm to 16 mm and a length of 8 mm to 50 mm; The probe support rod (2) is a cylinder with a diameter of 8 mm to 24 mm and a length of 150 mm to 300 mm; The concave surface of the probe head (1) is a spherical crown surface, the diameter of which is 4 mm to 10 mm, and the center of the spherical crown surface is 2 mm to 8 mm away from the central axis; The small water inlet channel No. 1 (8), the small water inlet channel No. 2 (9), and the small water inlet channel No. 3 (10) are distributed in the circumferential direction, and have a diameter of 1 mm to 3 mm. The angle between two adjacent water inlet channels is 15° to 60°, and the water outlet of the small water inlet channel No. 2 (9) is directly opposite to the connection between the lower pressure measuring channel (7) and the probe head (1); the water outlet of the small water inlet channel No. 2 (9) is 2 mm to 6 mm away from the central axis of the spherical crown surface, and the water outlets of the small water inlet channel No. 1 (8) and the small water inlet channel No. 3 (10) are 2 mm to 4 mm away from the water outlet of the small water inlet channel No. 2 (9); and a special reinforcement device is provided at a distance of 3 mm to 8 mm from the water outlet of the small water inlet channel No. 2 (9), and the thickness of the reinforcement device is 2 mm to 6 mm; The No. 1 large water inlet channel (12) and the No. 2 large water inlet channel (13) are centrally symmetrical about the central axis of the probe support rod (2), and the water outlets of the No. 1 large water inlet channel (12) and the No. 2 large water inlet channel (13) are respectively opposite to the left pressure measuring channel (4) and the right pressure measuring channel (5), and have a diameter of 2 mm to 4 mm; The bottom of the probe is evenly arranged with a left drainage port (14), an upper drainage port (15), a right drainage port (16), and a lower drainage port (17) in the circumferential direction. The diameter of each drainage port is 2 mm to 5 mm, and the center of each drainage port is 3 mm to 8 mm away from the central axis of the probe support rod (2).

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