Composite structure sweating cooling type full-circumferential high-temperature water-cooling dynamic pressure probe

Abstract

The utility model belongs to the technical field of high-temperature flow field pressure testing, and particularly relates to a sweating cooling type full-circumferential high-temperature water-cooling dynamic pressure probe with a composite structure. The device is composed of a probe supporting rod, a probe head, a sleeve, a mounting seat, a positioning hole, a cooling water inlet pipe, a water outlet pipe, a cable, a diverging wall surface, an impact wall surface, a current limiting wall surface, a circumferential separation baffle plate, a dynamic pressure sensor and the like. After the probe head is impacted and cooled by cooling water entering the probe through the water inlet pipe, one part of the cooling water permeates to the surface of the diverging wall surface in the radial direction to sweate and cool the probe, and the other part of the non-permeated part flows out of the probe in the axial direction after being heated through convection heat exchange. And the probe head is provided with a plurality of pressure measuring holes which are circumferentially arranged, so that full-circumferential flow field measurement can be realized. The probe cooling device has the advantages that the cooling efficiency of the probe is greatly improved by adopting sweating cooling, the probe supporting rod and the probe head can be cooled at the same time, the working life of the probe in an extreme high-temperature environment (the highest temperature is 2500 DEG C) is prolonged, and the reliability of a measurement result is improved.

Description

Technical Field

[0001] The present invention belongs to the technical field of dynamic pressure measurement in high-temperature flow fields, and particularly relates to a composite structure transpiration cooling type full-circumferential high-temperature water-cooled dynamic pressure probe, which is applicable to measuring flow field parameters such as dynamic total pressure, static pressure, velocity, Mach number, deflection angle, etc. in extreme high-temperature environments such as aero-engine combustors and turbines. The measurement range of the deflection angle can reach 360° in the full circumference. A composite structure transpiration cooling technology is adopted to achieve efficient cooling of the probe strut and the dynamic pressure sensor, ensuring that the probe can work reliably in an extreme high-temperature environment up to 2500°C. Background Art

[0002] The compressor, combustor, and turbine are the three core components of an aero-engine. With the rapid development of aerospace technology, the working environment of aero-engines has become extremely harsh. Among them, the temperatures at components such as the combustor and turbine continue to rise and have reached extremely high levels (up to 2300°C). Moreover, the high-temperature gas flow at the combustor outlet and turbine inlet has strong three-dimensionality, especially the large variation range of the gas flow deflection angle, which poses high requirements for the design of test probes in high-temperature environments such as combustors and turbines.

[0003] There are many difficulties in measuring the pressure field in such high-temperature environments. One of the main difficulties is that the pressure probe needs to have sufficient strength and reliability in a harsh environment, that is, it is required to ensure that the probe has an effective cooling structure and sufficient accuracy. Currently, there are mainly two cooling methods for pressure probes in high-temperature environments: film cooling and water cooling. Each of these two cooling methods has its own advantages, but each has certain technical defects, which affect the performance and service life of the probe.

[0004] The advantage of film cooling is that it is relatively easy to adjust the temperature and flow rate of the cooling air flow according to the mainstream temperature and flow rate. However, this cooling method has certain defects in cooling the probe head: If film holes are opened in the probe head, the ejected cooling air flow will interfere with the flow field at the probe head and affect the test accuracy. If no film holes are opened at the leading edge of the probe strut and only internal convective heat transfer is used for cooling, due to the small specific heat capacity of the gas, when the environment is extremely high-temperature (above 2000°C), the cooling effect provided by film cooling is limited, which may cause damage to the probe head.

[0005] The advantage of a water-cooled probe is that the flow of cooling water will not interfere with the flow field, and because the specific heat capacity of water is much greater than that of air, the cooling effect is better. However, the complexity of the water cooling system increases the difficulty of designing and maintaining water-cooled probes. The cooling water flow rate is difficult to adjust quickly when the test state changes, which may cause the local temperature of the probe to be too high or the pressure to be too high, increasing the risk of structural damage. At the same time, most of the existing water-cooled probes use the cooling water flow to absorb heat and heat up to cool the probe. This type of heat exchange process belongs to the sensible heat exchange process. When the measurement environment temperature rises, the required cooling water flow rate increases greatly. If the design of the cooling water flow channel in the probe is unreasonable, there will be problems such as large internal resistance, insufficient contact between the cooling water and the probe support rod, and dead water areas, resulting in unsatisfactory cooling effect. And because the probe is small in size, the operation of the water-cooled probe is more difficult.

[0006] Compared with the sensible heat exchange process that reduces the probe temperature through convection heat transfer, the latent heat exchange process that absorbs a large amount of heat through the phase change of matter (such as from liquid to gas, or from solid to liquid) has a more efficient cooling efficiency. And because the heat exchange amount in the latent heat exchange process is much greater than that in the sensible heat exchange process. Transpiration cooling is a common cooling method that uses latent heat exchange. The use of transpiration cooling can reduce the requirements of the probe for cooling water flow in extremely high temperature environments to a certain extent.

[0007] Another challenge is the limitation of the angle measurement range. In components such as combustion chambers, turbines, and even in variable cycle engines, high-temperature airflow has strong three-dimensionality, and the flow direction and velocity vector change dramatically. For example, due to the adjustment of the adjustable guide vanes in variable cycle engines, the airflow deflection angle can vary from -10° to 40°, while the angle measurement range of the commonly used five-hole pressure probe is around ±30°, or even smaller, which makes it difficult to meet the wide angle range testing requirements of complex flow fields. When faced with such complex flow fields, existing probes can often only provide data within a limited angle and cannot fully capture the true situation of the three-dimensional flow field, thus affecting the accuracy and comprehensiveness of the flow field analysis.

[0008] Insufficient angular measurement range will also reduce the resolution of the measurement data, affecting the capture and analysis of transient flow phenomena. Especially in flow fields with high turbulence or significant rotation effects, the probe needs to accurately measure parameters such as flow velocity and pressure within a larger angular range to obtain as complete data as possible, so as to accurately characterize the properties of the flow field and help researchers improve their comprehensive understanding of the flow field and optimize the design.

[0009] Two invention patents with publication numbers CN107063560A and CN107131999A respectively proposed a high-temperature water-cooled dynamic pressure probe and a high-temperature water-cooled steady-state pressure probe; a utility model patent with publication number CN206930646U proposed a water-cooled probe. The above water-cooled probes all utilize the sensible heat exchange process of cooling water absorbing the heat of the probe rod to cool the probe rod. In an extremely high-temperature environment, the cooling effect may be limited, affecting the accuracy of the probe measurement data and even causing damage to the probe; more importantly, the above water-cooled probes do not cool the probe head, which increases the risk of damage to the probe head due to high temperature.

[0010] Therefore, there is an urgent need to develop a pressure probe with a wide-angle measurement range, which can work stably and reliably in an extremely high-temperature environment (above 2000 °C) and can also cool the probe head, so as to meet the pressure test requirements in environments with increasingly high temperatures at components such as combustion chambers and turbines. Summary of the Invention

[0011] A full-circumferential high-temperature water-cooled dynamic pressure probe capable of working stably at extremely high temperatures according to the present invention. The probe rod part adopts a composite structure to realize the "sweating" function of the cooling water on the probe surface. The cooling water seeps out through the micropores on the probe surface and evaporates on the surface, which can take away a large amount of heat. Such heat exchange is a latent heat exchange process. During the sweating cooling process, the heat transfer amount can be calculated by the following relational formula:

[0012]

[0013] In the formula, Q evap is the latent heat transfer amount transferred through evaporative cooling, L v is the latent heat of vaporization of water (about 2.26×10 6 J / Kg), is the liquid evaporation rate, and its calculation formula is:

[0014]

[0015] In the above formula, P sat is the saturated water vapor pressure on the liquid surface, P is the water vapor pressure of the environment, R is the gas constant (for water vapor, about 461.5 J / (kg·K)), A evap represents the evaporation area.

[0016] In the convective heat exchange cooling process, the calculation relational formula for the sensible heat transfer amount is:

[0017] Q conv = h·A conv ·ΔT

[0018] In the above formula, Q convis the sensible heat transfer amount transferred by convective heat transfer, ΔT is the temperature difference, A conv is the heat transfer area, and h is the convective heat transfer coefficient. Inside the water-cooled probe, water undergoes turbulent flow in the stainless-steel pipe, and the convective heat transfer coefficient h is estimated by the Dittus-Boelter formula to be approximately 160.37 W / (m 2 ·K).

[0019] It can be seen from the above analysis that the heat absorbed during the sweating cooling (evaporative cooling) process is much greater than the cooling capacity absorbed by convective heat transfer under the same conditions. It can not only effectively reduce the surface temperature of the material, but also form a protective cooling layer to prevent the high-temperature gas flow from directly contacting the material surface, thereby greatly improving the high-temperature resistance performance of the material. The sweating cooling technology has the following advantages:

[0020] 1. High-efficiency cooling: Absorb heat through liquid evaporation to significantly reduce the surface temperature of the material.

[0021] 2. Thermal protection: Form a coolant layer to block the direct thermal shock of the high-temperature gas flow to the material.

[0022] 3. Self-adaptability: Automatically adjust the coolant seepage amount according to the ambient temperature change to achieve adaptive cooling.

[0023] The present invention provides a composite structure sweating-cooled full-circumferential high-temperature water-cooled dynamic pressure probe. The technical problems to be solved are: First, to solve the problem that existing pressure probes are difficult to operate and measure stably in extreme high-temperature (above 2000 °C) environments such as combustion chambers and turbines. Second, to solve the problem that the cavity effect of the dynamic pressure sensor inside the existing dynamic pressure probe is large and the frequency response is low in high-temperature environments. Third, to solve the problem that the existing probe has a small angle measurement range and is difficult to meet the measurement requirements of a large deflection angle range in a complex flow field with high turbulence and large pulsations. Fourth, to solve the problem that the internal cooling water flow of the existing water-cooled probe is difficult to quickly adjust and may boil and generate bubbles in the probe to block the flow channel.

[0024] The technical solution of the present invention is:

[0025] A composite structure transpiration cooling type full - circumferential high - temperature water - cooled dynamic pressure probe, comprising a probe rod (1), a full - circumferential porous probe head (2), a sleeve (3), a mounting seat (4), a positioning hole (5), a cooling water inlet pipe (6), a cooling water outlet pipe (7), a cable (8), a circumferential partition baffle (9), a first wall - the divergent wall (10), a second wall - the impingement wall (11), a third wall - the flow - limiting wall (12), a fourth wall - the outer wall of the probe rod (13), a dynamic pressure sensor (18), and a number of turbulator columns (14), divergent holes (15), impingement holes (16), flow - limiting holes (17); characterized in that: the full - circumferential porous probe head (2) is located at the top of the probe rod (1), the full - circumferential porous probe head (2) is internally provided with a dynamic pressure sensor (18) and has a plurality of pressure - measuring holes on its surface, the sleeve (3) is installed outside the probe rod (1), the mounting seat (4) is installed on the sleeve (3), the mounting seat (4) is provided with a positioning hole (5), the cooling water inlet pipe (6) and the cable (8) are both installed inside the probe rod (1), the cooling water outlet pipe (7) is installed on the sleeve (3) behind the mounting seat (4), and the cable (8) is installed inside the probe rod (1) and is arranged circumferentially around the cooling water inlet pipe (6).

[0026] Furthermore, the probe rod (1) is of a double - layer structure. The inner layer is connected to the cooling water inlet pipe (6) as the cooling water inlet flow channel. The outer layer is divided into six chambers by the circumferential partition baffle (9). Each chamber is respectively provided with 1 dynamic pressure sensor (18) and a cable (8), and each chamber and the third cooling flow channel together serve as the main cooling water circuit.

[0027] Furthermore, the outer diameter of the probe rod (1) is taken as 2 mm to 5 mm, the corresponding outer diameter of the sleeve (3) is taken as 4 mm to 10 mm, and the two are welded into an integral whole. The diameter of the cooling water inlet pipe (6) is 1 mm to 2 mm.

[0028] Furthermore, the full - circumferential porous probe head (2) is a cylindrical part at the top of the probe with an axial length from the end face being 3 times the outer diameter of the probe rod (1). The full - circumferential porous probe head (2) is provided with a plurality of pressure - measuring holes, which are respectively communicated with a plurality of dynamic pressure sensors (18) and the signals are led out of the probe through the cable (8). The pressure - measuring holes, the dynamic pressure sensors (18) and the cables (8) correspond one by one. Among them, the No. 1 pressure - measuring hole (21) corresponds to the No. 1 cable (81), the No. 2 pressure - measuring hole (22) corresponds to the No. 2 cable (82), the No. 3 pressure - measuring hole (23) corresponds to the No. 3 cable (83), the No. 4 pressure - measuring hole (24) corresponds to the No. 4 cable (84), the No. 5 pressure - measuring hole (25) corresponds to the No. 5 cable (85), the No. 6 pressure - measuring hole (26) corresponds to the No. 6 cable (86). The diameter of the pressure - measuring hole is 0.5 mm to 1.5 mm, and the included angle range between every two pressure - measuring holes is 30° to 60°.

[0029] Furthermore, the full circumferential porous probe (2) can be in any combination form of the probe shape (flat head or hemispherical) and the number of pressure measurement holes (6 to 10 holes) that meet the actual measurement requirements. For example, a flat-top 6-hole probe and a hemispherical 10-hole probe can respectively meet the measurement requirements of two-dimensional and three-dimensional flow fields.

[0030] Furthermore, a cooling water return pipeline is arranged inside the full circumferential porous probe (2), which connects the cooling water inlet pipeline and the outlet pipeline. The cooling water inlet pipe (6) directly leads to the full circumferential porous probe (2), and the full circumferential porous probe (2) can be cooled by impact. No divergence holes (15) are developed on the surface of the full circumferential porous probe (2) to avoid interference with the pressure measurement holes caused by the steam generated by evaporation cooling.

[0031] Furthermore, the sleeve (3) has a three-layer structure, including the first wall - divergence wall (10), the second wall - impact wall (11), and the third wall - flow-limiting wall (12). A first cooling channel is formed between the first wall - divergence wall (10) and the second wall - impact wall (11); a second cooling channel is formed between the second wall - impact wall (11) and the third wall - flow-limiting wall (12); a third cooling channel is formed between the third wall - flow-limiting wall (12) and the fourth wall - probe support rod outer wall (13). The above three cooling channels are cooling water permeation channels.

[0032] Furthermore, the mounting seat (4) is a runway-shaped mounting seat. The thickness of the mounting seat (4) is 2 to 5 millimeters, and two positioning holes (5) are opened on the mounting seat (4). The diameter of the positioning holes (5) is 2 to 3 millimeters.

[0033] Furthermore, 6 circumferential partition baffles (9) are evenly arranged circumferentially between the outer wall surface of the cooling water inlet pipe (6) and the first wall - divergence wall (10) to reduce the negative impact of gravity on the uneven distribution of cooling water. The circumferential partition baffles penetrate the second wall - impact wall (11), the third wall - flow-limiting wall (12), and the fourth wall - probe support rod outer wall (13), dividing the first cooling channel, the second cooling channel, the third cooling channel, and the cooling water return channel into 6 independent cooling regions circumferentially. The 6 cooling water return channels respectively correspond to the 6 independent cooling regions one by one.

[0034] Furthermore, the cooling water outlet pipe (7) is connected to the main cooling water circuit to timely discharge the cooling water whose temperature has risen to a certain extent inside the probe but has not entered the third flow channel between the fourth wall - probe support rod outer wall (13) and the flow-limiting wall (12), that is, to further absorb the part of the heat that has not been completely absorbed during the transpiration cooling process through the convective heat transfer of the flowing cooling water, thereby better protecting the dynamic pressure sensor (18).

[0035] Further, the first wall - the diverging wall (10) has inclined diverging holes (15) on its surface. These holes are evenly distributed circumferentially and staggered axially in a periodic manner, forming a diverging wall (10) with densely distributed diverging holes. The diverging holes (15) penetrate through the first wall - the diverging wall (10). Cooling water seeps out from the diverging holes to form a liquid film evaporation - cooled outer wall surface of the sleeve (3). The diameter of the diverging holes (15) is from 0.05 mm to 0.15 mm, and the inclination angle is from 30° to 60°.

[0036] Further, the diverging holes (15) are cylindrical holes with wavy protrusions on their inner walls, which allows the cooling water to seep out slowly to ensure good cooling effect. The height of the protrusions on the inner wall is from 0.01 mm to 0.03 mm.

[0037] Further, the second wall - the impinging wall (11) has evenly distributed impinging holes (16) on its surface. The impinging holes (16) connect the first cooling channel and the second cooling channel. Cooling water passes through the second wall - the impinging wall (11) from the second cooling channel and enters the first cooling channel, and impinges on the first wall - the diverging wall (10) for impingement cooling. The impinging holes (16) are straight holes and are axially staggered and periodically distributed on the second wall - the impinging wall (11). The diameter of the impinging holes is from 0.1 mm to 0.3 mm.

[0038] Further, several groups of flow - limiting holes (17) are evenly arranged circumferentially on the surface of the third wall - the flow - limiting wall (12). Since the thermal environments at different axial positions of the probe strut (1) may vary, and the required flow rates are also different, different numbers of flow - limiting holes (17) can be opened at different axial positions of the probe strut (1) according to the thermal environment of the probe to control the flow rate of the cooling water entering different positions, thereby controlling the cooling effect at different positions. The diameter of the flow - limiting holes (17) is from 0.2 mm to 0.4 mm.

[0039] Further, turbulators (14) are provided in the first cooling channel. They are evenly distributed circumferentially and staggered axially in a periodic manner, forming a group of turbulators with dense distribution. The upper and lower end surfaces of the turbulators (14) are fixedly connected to the first wall - the diverging wall (10) and the second wall - the impinging wall (11) to enhance the overall heat transfer performance. The diameter of the turbulators (14) is from 0.1 mm to 0.2 mm.

[0040] The composite - structure transpiration - cooled full - circumferential high - temperature water - cooled dynamic pressure probe of the present invention has the following beneficial effects:

[0041] Advantage 1: The present invention can cool the probe strut and the probe head simultaneously, effectively improving the working life and the upper limit of the working temperature of the probe in a high-temperature environment. The present invention synthesizes the research results of porous wall film cooling, turbulator enhanced convective heat transfer, transpiration cooling, etc., and proposes a transpiration cooling structure suitable for the probe. This transpiration cooling integrates the outstanding advantages of film cooling, turbulator enhanced heat transfer, and transpiration cooling. A large amount of heat is absorbed by the evaporation of the cooling water in the permeable part. The unpermeated cooling water part absorbs heat and rises in temperature, and then flows out through the water outlet pipe to further cool the probe and the dynamic pressure sensor. The probe head part adopts a reasonable structure design for impingement cooling, which can absorb a large amount of heat under the conditions of small probe size and limited cooling water flow, effectively improving the working life and the upper limit of the working temperature of the probe in a high-temperature environment (up to 2500 °C).

[0042] Advantage 2: Compared with other dynamic total pressure probes, the probe of the present invention can maintain better dynamic response ability and more accurate measurement results in a high-temperature environment. There are no diverging holes developed near the probe head of the probe of the present invention, avoiding interference to the pressure measurement holes. Combining with impingement cooling can effectively prevent the local temperature of the probe head from being too high. Compared with other water-cooled probes, the dynamic pressure sensor of the present invention can be installed closer to the pressure measurement holes on the probe head, effectively reducing the cavity effect between the pressure measurement holes on the probe head and the dynamic pressure sensor, thereby improving the dynamic response ability of the probe in a high-temperature environment and effectively ensuring the accuracy of the probe measurement results.

[0043] Advantage 3: Compared with other high-temperature water-cooled dynamic multi-hole pressure probes, the present invention can realize the measurement of the circumferential deflection angle. The high-temperature water-cooled pressure measurement probe of the present invention adopts a combination of impingement cooling and convective heat transfer cooling at the probe head to avoid the interference of the steam formed during the transpiration cooling process to the flow field at the pressure measurement holes while enabling the probe head to withstand a higher temperature. A plurality of circumferentially arranged pressure measurement holes are reasonably arranged on the cylindrical surface of the probe head, and the circumferential deflection angle can be measured.

[0044] Advantage 4: Compared with other forms of transpiration cooling structures, the present invention can effectively ensure an ideal and uniform transpiration effect. The present invention adopts a multi-layer permeable flow channel and a divergent hole form with wavy protrusions on the inner wall surface, which can effectively ensure that the cooling water oozes out of the probe surface at an appropriate speed and prevent the high-temperature gas from entering the probe interior through the divergent holes, ensuring an ideal and uniform divergence effect of the probe.

[0045] Advantage 5: The probe of the present invention is of an integrated design. Compared with other combined water-cooled probes, the probe of the present invention can maintain stable and reliable structure, accurate positioning under higher pressure, and has smaller system errors caused by combined installation. Description of the Drawings

[0046] Figure 1It is a schematic diagram of the overall structure of a composite structure transpiration cooling type full - circumferential high - temperature water - cooled dynamic pressure probe of the present invention.

[0047] Figure 2 They are the partial enlarged front view and side view of the probes in the two typical forms described in the claims.

[0048] Figure 3 It is Figure 1 the top view and the cross - sectional view of the A - A section.

[0049] Figure 4 It is Figure 2 the front - view semi - cross - sectional view of the flat - top probe head shown, where the solid arrow indicates the axial flow direction of the cooling water, and the hollow arrow indicates the radial penetration direction of the cooling water.

[0050] Figure 5 It is the cross - section of the diverging holes with wavy protrusions on the inner wall described in the claims, and the arrow represents the direction of water seepage and outflow.

[0051] Where: 1 - probe strut, 2 - full - circumferential porous probe head, 3 - sleeve, 4 - mounting seat, 5 - positioning hole, 6 - cooling water inlet pipe, 7 - cooling water outlet pipe, 8 - cable, 9 - circumferential partition plate, 10 - first wall - diverging wall, 11 - second wall - impact wall, 12 - third wall - flow - limiting wall, 13 - fourth wall - outer wall surface of the probe strut, 14 - turbulence cylinder, 15 - diverging hole, 16 - impact hole, 17 - flow - limiting hole, 18 - dynamic pressure sensor, 21 - pressure measurement hole No. 1, 22 - pressure measurement hole No. 2, 23 - pressure measurement hole No. 3, 24 - pressure measurement hole No. 4, 25 - pressure measurement hole No. 5, 26 - pressure measurement hole No. 6, 81 - cable No. 1, 82 - cable No. 2, 83 - cable No. 3, 84 - cable No. 4, 85 - cable No. 5, 86 - cable No. 6. Specific embodiments

[0052] The present invention will be described in detail below in conjunction with the accompanying drawings and two 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.

[0053] Embodiment 1:

[0054] Refer to Figure 1 、 Figures 3 to 5 and Figure 2The medium flat-top probe shown is a composite structure transpiration cooling type full circumferential high-temperature water-cooled dynamic pressure probe, including a probe strut (1), a full circumferential porous probe (2), a sleeve (3), a mounting seat (4), a positioning hole (5), a cooling water inlet pipe (6), a cooling water outlet pipe (7), a cable (8), a circumferential partition baffle (9), a first wall - divergent wall (10), a second wall - impingement wall (11), a third wall - flow-limiting wall (12), a fourth wall - outer wall of the probe strut (13), a dynamic pressure sensor (18), and a number of turbulators (14), divergent holes (15), impingement holes (16), and flow-limiting holes (17); characterized in that: the full circumferential porous probe (2) is located at the top of the probe strut (1), the dynamic pressure sensor (18) is installed inside the full circumferential porous probe (2), and multiple pressure measurement holes are opened on the surface. The sleeve (3) is installed outside the probe strut (1), the mounting seat (4) is installed on the sleeve (3), and a positioning hole (5) is provided on the mounting seat (4). The cooling water inlet pipe (6) and the cable (8) are both installed inside the probe strut (1), the cooling water outlet pipe (7) is installed on the sleeve (3) behind the mounting seat (4), and the cable (8) is installed inside the probe strut (1) and arranged circumferentially around the cooling water inlet pipe (6).

[0055] The probe strut (1) is a double-layer structure. The inner layer is connected to the cooling water inlet pipe (6) as the cooling water inlet flow channel. The outer layer is divided into six chambers by the circumferential partition baffle (9). One dynamic pressure sensor (18) and a cable (8) are placed in each chamber, and each chamber and the third cooling flow channel together serve as the main cooling water circuit.

[0056] In this embodiment, the outer diameter of the probe strut (1) is taken as 4 mm, the corresponding outer diameter of the sleeve (3) is taken as 6 mm, and the two are welded into a whole. The diameter of the cooling water inlet pipe (6) is 2 mm.

[0057] The full circumferential porous probe (2) is a cylindrical part at the top of the probe with an axial length from the end face being 3 times the outer diameter of the probe strut (1). Multiple pressure measurement holes are opened on the full circumferential porous probe (2), which are respectively connected to multiple dynamic pressure sensors (18), and the signals are led out of the probe through the cables (8). The pressure measurement holes, the dynamic pressure sensors (18), and the cables (8) correspond one by one. Among them, the No. 1 pressure measurement hole (21) corresponds to the No. 1 cable (81), the No. 2 pressure measurement hole (22) corresponds to the No. 2 cable (82), the No. 3 pressure measurement hole (23) corresponds to the No. 3 cable (83), the No. 4 pressure measurement hole (24) corresponds to the No. 4 cable (84), the No. 5 pressure measurement hole (25) corresponds to the No. 5 cable (85), and the No. 6 pressure measurement hole (26) corresponds to the No. 6 cable (86). In this embodiment, the diameter of the pressure measurement hole is 0.8 mm, and the included angle range between every two pressure measurement holes is 60°.

[0058] In this embodiment, the full circumferential porous probe (2) is in the form of a flat-top 6-hole probe, which can measure the deflection angle of 360° in the full circumference of the two-dimensional flow field.

[0059] A cooling water return pipeline is arranged inside the full circumferential porous probe (2), which connects the cooling water inlet pipeline and the outlet pipeline. Moreover, the cooling water inlet pipe (6) directly leads to the full circumferential porous probe (2), and the full circumferential porous probe (2) can be cooled by impact. No divergence holes (15) are developed on the surface of the full circumferential porous probe (2) to avoid the interference of the steam generated by evaporation cooling on the pressure measurement holes.

[0060] The sleeve (3) has a three-layer structure, including the first wall - the divergence wall (10), the second wall - the impact wall (11), and the third wall - the flow-limiting wall (12). A first cooling channel is formed between the first wall - the divergence wall (10) and the second wall - the impact wall (11); a second cooling channel is formed between the second wall - the impact wall (11) and the third wall - the flow-limiting wall (12); a third cooling channel is formed between the third wall - the flow-limiting wall (12) and the fourth wall - the outer wall surface of the probe strut (13). The above three cooling channels are cooling water permeation channels.

[0061] In this embodiment, the mounting seat (4) is in the shape of a runway. The thickness of the mounting seat (4) is 2 mm, and two positioning holes (5) are opened on the mounting seat (4). The diameter of the positioning holes (5) is 3 mm.

[0062] Six circumferential partition baffles (9) are evenly arranged circumferentially between the outer wall surface of the cooling water inlet pipe (6) and the first wall - the divergence wall (10) to reduce the negative impact of gravity on the uneven distribution of cooling water. The circumferential partition baffles penetrate through the second wall - the impact wall (11), the third wall - the flow-limiting wall (12), and the fourth wall - the outer wall surface of the probe strut (13), and divide the first cooling channel, the second cooling channel, the third cooling channel, and the cooling water return channel into 6 independent cooling regions along the circumference. The 6 cooling water return channels correspond to the 6 independent cooling regions one by one.

[0063] The cooling water outlet pipe (7) is connected to the main cooling water circuit, and timely discharges the cooling water whose temperature in the probe has risen to a certain degree but has not entered the third flow channel between the fourth wall - the outer wall surface of the probe strut (13) and the flow-limiting wall (12). That is, through the convective heat transfer of the flowing cooling water, the part of the heat that has not been completely absorbed in the transpiration cooling process is further absorbed, so as to better protect the dynamic pressure sensor (18).

[0064] The first wall - the diverging wall (10) has inclined diverging holes (15) on its surface, which are evenly distributed circumferentially and staggered axially in a periodic manner, forming a diverging wall (10) with uniformly dense diverging holes. The diverging holes (15) penetrate through the first wall - the diverging wall (10), and cooling water seeps out from the diverging holes to form a liquid film evaporation - cooled outer wall surface of the sleeve (3). In this embodiment, the diameter of the diverging holes (15) is 0.08, and the inclination angle is 50°.

[0065] In this embodiment, the diverging holes (15) are cylindrical holes with wavy protrusions on their inner walls, enabling the cooling water to seep out slowly to ensure good cooling effect. The height of the inner - wall protrusions is 0.02 millimeters.

[0066] The second wall - the impinging wall (11) has evenly - distributed impinging holes (16) on its surface. The impinging holes (16) connect the first cooling channel and the second cooling channel. Cooling water passes through the second wall - the impinging wall (11) from the second cooling channel and enters the first cooling channel, and performs impingement cooling on the first wall - the diverging wall (10). The impinging holes (16) are straight holes, which are axially staggered and periodically distributed on the second wall - the impinging wall (11). In this embodiment, the diameter of the impinging holes is 0.1 millimeters.

[0067] The third wall - the flow - limiting wall (12) has several groups of flow - limiting holes (17) evenly arranged circumferentially on its surface. Since the thermal environments at different axial positions of the probe strut (1) may vary, and the required flow rates are also different, different numbers of flow - limiting holes (17) can be opened at different axial positions of the probe strut (1) according to the thermal environment where the probe is located to control the flow rate of the cooling water entering different positions, thereby controlling the cooling effect at different positions. In this embodiment, the diameter of the flow - limiting holes (17) is 0.2 millimeters.

[0068] There are turbulators (14) in the first cooling channel, which are evenly distributed circumferentially and staggered axially in a periodic manner, forming a uniformly dense turbulator group. The upper and lower end surfaces of the turbulators (14) are fixedly connected to the first wall - the diverging wall (10) and the second wall - the impinging wall (11) to enhance the overall heat - transfer performance. In this embodiment, the diameter of the turbulators (14) is 0.1 millimeters.

[0069] The present invention can select appropriate layout parameters of the diverging holes according to the actual temperature range of the high - temperature flow field, and select appropriate supply pressure of the cooling water according to the test - environment pressure. By reasonably combining the three cooling methods of convective heat - transfer cooling, impingement cooling, and evaporation - endothermic cooling of the cooling water, the cooling effect of the probe is greatly improved, and it is ensured to be sufficiently uniform and ideal. Moreover, by using impingement cooling to cool the six - hole probe in the whole circumferential direction, the dynamic response ability, the measurement range of the deflection angle (which can reach 360°), and the upper limit of the working temperature (up to 2500 °C) of the pressure probe in the high - temperature two - dimensional flow field can be effectively improved.

[0070] Example 2:

[0071] Refer to Figures 3 to 5 and Figure 1 for the main structure and Figure 2 The hemispherical probe in shows a composite structure transpiration cooling type full - circumferential high - temperature water - cooled dynamic pressure probe, which includes a probe strut (1), a full - circumferential porous probe (2), a sleeve (3), a mounting seat (4), a positioning hole (5), a cooling water inlet pipe (6), a cooling water outlet pipe (7), a cable (8), a circumferential partition baffle (9), a first wall - the divergent wall (10), a second wall - the impingement wall (11), a third wall - the flow - limiting wall (12), a fourth wall - the outer wall of the probe strut (13), a dynamic pressure sensor (18), and a number of turbulators (14), divergent holes (15), impingement holes (16), and flow - limiting holes (17); characterized in that: the full - circumferential porous probe (2) is located at the top of the probe strut (1), the dynamic pressure sensor (18) is installed inside the full - circumferential porous probe (2), and multiple pressure - measuring holes are opened on the surface. The sleeve (3) is installed outside the probe strut (1), the mounting seat (4) is installed on the sleeve (3), and a positioning hole (5) is provided on the mounting seat (4). The cooling water inlet pipe (6) and the cable (8) are both installed inside the probe strut (1), the cooling water outlet pipe (7) is installed on the sleeve (3) behind the mounting seat (4), and the cable (8) is installed inside the probe strut (1) and arranged circumferentially around the cooling water inlet pipe (6).

[0072] The probe strut (1) is a double - layer structure. The inner layer is connected to the cooling water inlet pipe (6) as the cooling water inlet flow channel. The outer layer is divided into six chambers by the circumferential partition baffle (9), and multiple dynamic pressure sensors (18) and cables (8) are respectively placed. And each chamber and the third cooling flow channel together serve as the main cooling water circuit.

[0073] In this embodiment, the outer diameter of the probe strut (1) is 6 mm, the outer diameter of the corresponding sleeve (3) is 8 mm, and the two are welded into a whole. The diameter of the cooling water inlet pipe (6) is 2 mm.

[0074] The full - circumferential porous probe (2) is a cylindrical part where the axial length from the top of the probe to the end face is 3 times the outer diameter of the probe strut (1). Multiple pressure - measuring holes are opened on the full - circumferential porous probe (2), which are respectively connected to 10 dynamic pressure sensors (18), and the signals are led out of the probe through cables (8). The pressure - measuring holes, dynamic pressure sensors (18), and cables (8) correspond one by one. Among them, the No. 1 pressure - measuring hole (21) corresponds to the No. 1 cable (81), the No. 2 pressure - measuring hole (22) corresponds to the No. 2 cable (82), the No. 3 pressure - measuring hole (23) corresponds to the No. 3 cable (83), the No. 4 pressure - measuring hole (24) corresponds to the No. 4 cable (84), the No. 5 pressure - measuring hole (25) corresponds to the No. 5 cable (85), the No. 6 pressure - measuring hole (26) corresponds to the No. 6 cable (86), the No. 7 pressure - measuring hole (27) corresponds to the No. 7 cable (87), the No. 8 pressure - measuring hole (28) corresponds to the No. 8 cable (88), the No. 9 pressure - measuring hole (29) corresponds to the No. 9 cable (89), and the No. 10 pressure - measuring hole (210) corresponds to the No. 10 cable (810). In this embodiment, the diameter of the pressure - measuring hole is 0.8 mm, and the included angle range between every two pressure - measuring holes is 60°.

[0075] In this embodiment, the full - circumferential porous probe (2) is in the form of a hemispherical - shaped 10 - hole probe, which can measure the pitch angle in the range of - 20° to 50° and the yaw angle of 360° in the full circumference of the three - dimensional flow field.

[0076] A cooling water return pipeline is arranged inside the full - circumferential porous probe (2), which connects the cooling water inlet pipeline and the outlet pipeline. And the cooling water inlet pipe (6) directly leads to the full - circumferential porous probe (2), which can perform impingement cooling on the full - circumferential porous probe (2). No divergence holes (15) are opened on the surface of the full - circumferential porous probe (2) to avoid the interference of the steam generated by evaporation cooling on the pressure - measuring holes.

[0077] The sleeve (3) has a three - layer structure, including the first wall - the divergent wall (10), the second wall - the impingement wall (11), and the third wall - the flow - limiting wall (12). A first cooling channel is formed between the first wall - the divergent wall (10) and the second wall - the impingement wall (11); a second cooling channel is formed between the second wall - the impingement wall (11) and the third wall - the flow - limiting wall (12); a third cooling channel is formed between the third wall - the flow - limiting wall (12) and the fourth wall - the outer wall surface of the probe strut (13). The above - mentioned three cooling channels are cooling water permeation channels.

[0078] In this embodiment, the mounting seat (4) is in the shape of a runway. The thickness of the mounting seat (4) is 2 mm, and two positioning holes (5) are opened on the mounting seat (4), and the diameter of the positioning holes (5) is 3 mm.

[0079] Six circumferential partition baffles (9) are evenly arranged circumferentially between the outer wall surface of the cooling water inlet pipe (6) and the first wall - the divergent wall (10) to reduce the negative impact of gravity on the uneven distribution of cooling water. The circumferential partition baffles penetrate through the second wall - the impact wall (11), the third wall - the flow - limiting wall (12), and the fourth wall - the outer wall surface of the probe support rod (13), dividing the first cooling channel, the second cooling channel, the third cooling channel, and the cooling water return channel into six independent cooling regions circumferentially. The six cooling water return channels correspond to the six independent cooling regions one by one.

[0080] The cooling water outlet pipe (7) is connected to the main cooling water circuit to timely discharge the cooling water whose temperature has risen to a certain degree in the probe but has not entered the third flow channel between the fourth wall - the outer wall surface of the probe support rod (13) and the flow - limiting wall (12). That is, through the convective heat transfer of the flowing cooling water, the part of the heat that has not been completely absorbed in the transpiration cooling process is further absorbed, thereby better protecting the dynamic pressure sensor (18).

[0081] The surface of the first wall - the divergent wall (10) is provided with inclined divergent holes (15) which are evenly distributed circumferentially and staggeredly distributed axially in a periodical manner, forming a divergent wall (10) with uniformly dense divergent holes. The divergent holes (15) penetrate through the first wall - the divergent wall (10), and the cooling water seeps out from the divergent holes to form the outer wall surface of the film evaporation cooling sleeve (3). In this embodiment, the diameter of the divergent holes (15) is 0.1, and the inclination angle is 50°.

[0082] In this embodiment, the divergent holes (15) are cylindrical holes with wavy protrusions on the inner wall, so that the cooling water seeps out slowly to ensure good cooling effect. The height of the inner wall protrusion is 0.03 millimeters.

[0083] The surface of the second wall - the impact wall (11) is evenly provided with impact holes (16). The impact holes (16) connect the first cooling channel and the second cooling channel. The cooling water passes through the second wall - the impact wall (11) from the second cooling channel and enters the first cooling channel, and conducts impact cooling on the first wall - the divergent wall (10). The impact holes (16) are straight holes and are distributed axially and staggeredly in a periodical manner on the second wall - the impact wall (11). In this embodiment, the diameter of the impact holes is 0.1 millimeter.

[0084] A number of groups of flow - limiting holes (17) are evenly arranged circumferentially on the surface of the third wall - the flow - limiting wall (12). Since the thermal environments at different axial positions of the probe support rod (1) may be different, and the required flow rates are also different, different numbers of flow - limiting holes (17) can be opened at different axial positions of the probe support rod (1) according to the thermal environment of the probe to control the flow rate of the cooling water entering different positions, thereby controlling the cooling effect at different positions. In this embodiment, the diameter of the flow - limiting holes (17) is 0.2 millimeter.

[0085] There are turbulators (14) provided in the first cooling channel, which are evenly distributed circumferentially and staggered periodically axially, forming a group of turbulators with uniform and dense distribution. The upper and lower end faces of the turbulators (14) are fixedly connected to the first wall surface - the divergent wall surface (10) and the second wall surface - the impingement wall surface (11) to enhance the overall heat transfer performance. In this embodiment, the diameter of the turbulators (14) is 0.1 mm.

[0086] The present invention can select appropriate layout parameters of the divergent holes according to the actual temperature range of the high-temperature flow field, select appropriate cooling water supply pressure according to the test environment pressure. By reasonably combining the three cooling methods of convective heat transfer cooling of cooling water, impingement cooling and evaporation endothermic cooling, the cooling effect of the probe is greatly improved and ensured to be sufficiently uniform and ideal. The hemispherical 10-hole probe is cooled by impingement cooling, which can effectively improve the dynamic response ability, the measurement range of the deflection angle (which can reach 360°) and the upper limit of the working temperature (up to 2500 °C) of the pressure probe in the high-temperature three-dimensional flow field.

Claims

1. A composite structure sweat cooling type full circumferential high temperature water-cooled dynamic pressure probe, comprising a probe support rod (1), a full circumferential porous probe (2), a sleeve (3), a mounting seat (4), a positioning hole (5), a cooling water inlet pipe (6), a cooling water outlet pipe (7), a cable (8), a circumferential partition baffle (9), a first wall surface - a diverging wall surface (10), a second wall surface - an impact wall surface (11), a third wall surface - a flow limiting wall surface (12), a fourth wall surface - an outer wall surface of the probe support rod (13), a dynamic pressure sensor (18), and some interference flow columns (14), diverging holes (15), impact holes (16), and flow limiting holes (17); characterized in that: The omni-directional porous probe (2) is located at the top of the probe support rod (1), a dynamic pressure sensor (18) is installed inside the omni-directional porous probe (2), and a plurality of pressure measuring holes are opened on the surface; a sleeve (3) is installed outside the probe support rod (1), a mounting seat (4) is installed on the sleeve (3), a positioning hole (5) is provided on the mounting seat (4), a cooling water inlet pipe (6) and a cable (8) are both installed in the probe support rod (1), a cooling water outlet pipe (7) is installed on the sleeve (3) and behind the mounting seat (4), and the cable (8) is installed in the probe support rod (1) and arranged circumferentially around the cooling water inlet pipe (6); The probe support rod (1) is a double-layer structure, the inner layer is connected to the cooling water inlet pipe (6) as a cooling water inlet channel, and the outer layer is divided into six chambers by a circumferential partition baffle (9), each of which is provided with a plurality of dynamic pressure sensors (18) and cables (8), and each chamber and the third cooling channel together serve as a cooling water main circuit; The outer diameter of the probe support rod (1) is 2 mm to 5 mm, and the outer diameter of the corresponding sleeve (3) is 4 mm to 10 mm. The two are welded into a whole, and the diameter of the cooling water inlet pipe (6) is 1 mm to 2 mm. The omni-directional multi-hole probe (2) is a cylindrical part whose axial length from the top of the probe to the end face is three times the outer diameter of the probe support rod (1). The omni-directional multi-hole probe (2) is provided with a plurality of pressure measuring holes, which are respectively connected to a plurality of dynamic pressure sensors (18) and lead signals out of the probe through cables (8). The pressure measuring holes, the dynamic pressure sensors (18) and the cables (8) correspond to each other one by one, wherein the pressure measuring hole No. 1 (21) corresponds to the cable No. 1 (81), the pressure measuring hole No. 2 (22) corresponds to the cable No. 2 (82), the pressure measuring hole No. 3 (23) corresponds to the cable No. 3 (83), the pressure measuring hole No. 4 (24) corresponds to the cable No. 4 (84), the pressure measuring hole No. 5 (25) corresponds to the cable No. 5 (85), and the pressure measuring hole No. 6 (26) corresponds to the cable No. 6 (86). The diameter of the pressure measuring holes is 0.5 mm to 1.5 mm, and the angle between each two pressure measuring holes is in the range of 30° to 60°. The omni-circumferential multi-hole probe (2) is a flat-top 6-hole probe or a hemispherical 10-hole probe; A cooling water return pipeline is arranged inside the omni-directional porous probe (2), connecting the cooling water inlet pipeline and the outlet pipeline, and the cooling water inlet pipe (6) is directly connected to the omni-directional porous probe (2), so that the omni-directional porous probe (2) can be impact-cooled, and no scattered holes (15) are developed on the surface of the omni-directional porous probe (2); The sleeve (3) is a three-layer structure, comprising a first wall surface—a diverging wall surface (10), a second wall surface—an impact wall surface (11), and a third wall surface—a flow-limiting wall surface (12); a first cooling channel is formed between the first wall surface—a diverging wall surface (10) and the second wall surface—an impact wall surface (11); a second cooling channel is formed between the second wall surface—an impact wall surface (11) and the third wall surface—a flow-limiting wall surface (12); and a third cooling channel is formed between the third wall surface—a flow-limiting wall surface (12) and a fourth wall surface—an outer wall surface of a probe support rod (13); the above three cooling channels are cooling water infiltration channels; The mounting seat (4) is a runway-shaped mounting seat, the thickness of the mounting seat (4) is 2 mm to 5 mm, and two positioning holes (5) are opened on the mounting seat (4), and the diameter of the positioning holes (5) is 2 mm to 3 mm; Six circumferential partition baffles (9) are evenly arranged circumferentially between the outer wall surface of the cooling water inlet pipe (6) and the first wall surface—the divergent wall surface (10) to reduce the negative influence of gravity on the uneven distribution of cooling water. The circumferential partition baffles penetrate the second wall surface—the impact wall surface (11), the third wall surface—the flow limiting wall surface (12), and the fourth wall surface—the outer wall surface of the probe support rod (13), and divide the first cooling channel, the second cooling channel, the third cooling channel, and the cooling water return channel into six independent cooling areas along the circumferential direction. The six cooling water return channels correspond to the six independent cooling areas one by one. The cooling water outlet pipe (7) is connected to the cooling water main circuit to timely discharge the cooling water whose temperature in the probe rises to a certain level but fails to enter the third flow channel between the fourth wall surface (the outer wall surface of the probe support rod (13)) and the third wall surface (the flow limiting wall surface (12); The surface of the first wall surface, the diverging wall surface (10), is provided with inclined diverging holes (15), which are evenly distributed in the circumferential direction and staggered in the axial direction to form a wall surface evenly and densely covered with the diverging holes (15). The diverging holes (15) penetrate the first wall surface, the diverging wall surface (10). Cooling water seeps out of the diverging holes to form a liquid film evaporative cooling outer wall surface of the jacket (3). The diameter of the diverging holes (15) is 0.05 mm to 0.15 mm, and the inclination angle is 30° to 60°. The diverging hole (15) is a cylindrical hole with a wave-shaped protrusion on the inner wall, so that the cooling water can seep out slowly, and the height of the protrusion on the inner wall is 0.01 mm to 0.03 mm; The second wall surface (impact wall surface) (11) is evenly distributed with impact holes (16), the impact holes (16) connect the first cooling channel and the second cooling channel, cooling water passes through the second wall surface (impact wall surface) (11) from the second cooling channel into the first cooling channel, and performs impact cooling on the first wall surface (divergence wall surface) (10), the impact holes (16) are straight holes, axially staggered and periodically distributed on the second wall surface (impact wall surface) (11), and the impact holes have a diameter of 0.1 mm to 0.3 mm; A plurality of groups of flow limiting holes (17) are evenly arranged on the surface of the third wall surface (the flow limiting wall surface (12)) in the circumferential direction. Since the thermal environments at different axial positions of the probe support rod (1) may be different, the required flow rates may also be different. Different numbers of flow limiting holes (17) may be opened at different axial positions of the probe support rod (1) according to the thermal environment of the probe to control the flow of cooling water entering different positions. The diameter of the flow limiting holes (17) is 0.2 mm to 0.4 mm. The first cooling channel is provided with spoiler columns (14), which are evenly distributed in the circumferential direction and staggered and periodically distributed in the axial direction to form a uniformly dense spoiler column group. The upper and lower end surfaces of the spoiler columns (14) are fixedly connected to the first wall surface (divergent wall surface) (10) and the second wall surface (impact wall surface) (11). The diameter of the spoiler columns (14) is 0.1 mm to 0.2 mm.

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