Ultrasonic probe structure and ultrasonic electromagnetic instrument

Abstract

The invention relates to the field of ultrasonic flaw detection electromagnetic equipment, in particular to an ultrasonic probe structure and an ultrasonic electromagnetic instrument. The ultrasonic probe structure is arranged on the surface of gas injection equipment and comprises a shell, and at least one gas groove body is arranged in the shell; the air groove body is provided with a forked structure, and the forked structure divides the air groove body into a main air groove and at least two auxiliary air grooves which are symmetrically arranged relative to the main air groove; each auxiliary gas groove is connected with a throttling gas channel, and the outer end of each throttling gas channel is communicated with a pressure cavity used for diffusing gas and forming a uniform gas film support. Through cooperation of step throttling and an external pressure cavity, suspension stability is achieved, and the problem that in the prior art, an ultrasonic detection head lacks effective suspension buoyancy, and consequently detection is not accurate is solved.

Description

Technical Field

[0001] The present application relates to the field of ultrasonic flaw detection electromagnetic equipment, and in particular to an ultrasonic probe structure and an ultrasonic electromagnetic instrument. Background Art

[0002] In the field of ultrasonic flaw detection, traditional technologies have shown certain shortcomings when detecting internal defects in materials. In particular, when detecting subtle surface defects (such as surface unevenness), the probe often exhibits instability, such as tilt or vibration, which directly leads to inaccurate test data.

[0003] In addition, in actual applications, the current probe sensor cannot form a stable air film lubrication due to the lack of an effective suspension support mechanism, which makes it difficult for the probe to remain stable during the detection process, thereby affecting the accuracy and efficiency of the detection.

[0004] This shows that there is still much room for improvement in the stable suspension buoyancy of existing ultrasonic flaw detection technology.

[0005] To this end, the above problems need to be solved. Summary of the Invention

[0006] The present application provides an ultrasonic probe structure that achieves suspension stability through step-by-step throttling in conjunction with an external pressure chamber, thereby solving the problem in the prior art of ultrasonic probes lacking effective suspension buoyancy, resulting in inaccurate detection.

[0007] In the first aspect, the ultrasonic probe structure includes a shell in which at least one air slot body is provided; the air slot body is provided with a bifurcation structure, which divides the air slot body into a main air slot and at least two auxiliary air slots symmetrically arranged relative to the main air slot; each auxiliary air slot is connected to a throttling air duct, and the outer end of the throttling air duct is connected to a pressure chamber used to diffuse gas and form a uniform air film support.

[0008] Furthermore, each of the auxiliary gas grooves is located on the same radial horizontal plane.

[0009] Furthermore, the throttling air passage has a first section and a second section that are interconnected, and the inner diameter of the first section is greater than the inner diameter of the second section.

[0010] Furthermore, the cross section of the bifurcation structure is T-shaped.

[0011] Furthermore, an assembly groove is provided around the opening of the air tank body, and a sealing ring is embedded in the assembly groove.

[0012] Furthermore, the sealing ring has a silicone layer and a rigid support layer;

[0013] Wherein, the silica gel layer is coated on the outer surface of the rigid support layer.

[0014] Furthermore, the pressure chamber includes a first chamber and a second chamber that are interconnected;

[0015] The longitudinal section of the first cavity is a rectangle, and the longitudinal section of the second cavity is a cone that is narrow at the top and wide at the bottom.

[0016] Furthermore, the shell is provided with two independent air tank bodies, forming two independent main air duct systems, each main air duct system includes the bifurcation structure and symmetrically arranged auxiliary air tanks, a throttling air duct connected to the auxiliary air tanks and a pressure chamber connected to the throttling air duct.

[0017] Furthermore, each main airway system is symmetrically arranged about the central axis of the ultrasound probe structure and is located on the same radial plane.

[0018] In addition, an ultrasonic electromagnetic instrument is proposed, which includes an equipment body and the above-mentioned ultrasonic probe structure.

[0019] The above technical solution provided by the embodiment of the present application has the following advantages compared with the prior art:

[0020] This ultrasonic probe structure uses an external gas injection device to seal the gas tank body, forming a sealed main airway. Gas is diverted through a bifurcated structure in the main airway to an auxiliary gas tank, and a throttled airway controls the flow rate into the pressure chamber. After diffusion, a uniform gas film is formed, providing stable levitation. The symmetrically arranged auxiliary gas tanks utilize the symmetrical gas flow diversion characteristics to automatically compensate for pressure fluctuations caused by surface unevenness, thereby resolving the problem in existing probes that lack stable buoyancy, resulting in probe tilt or vibration, and thus inaccurate test data. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the present application and, together with the description, serve to explain the principles of the present application.

[0022] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, for ordinary technicians in this field, other drawings can be obtained based on these drawings without any creative work.

[0023] One or more embodiments are exemplarily illustrated by pictures in the corresponding drawings. These exemplifications do not constitute limitations on the embodiments. Elements with the same reference numerals in the drawings are represented as similar elements. Unless otherwise stated, the figures in the drawings do not constitute proportional limitations.

[0024] Figure 1 This is a schematic diagram of the upper surface structure of the ultrasound probe structure of this application;

[0025] Figure 2 This is a schematic diagram of the structure of the air tank body and the assembly tank of this application;

[0026] Figure 3 A cross-sectional view of the sealing ring of the present application;

[0027] Figure 4 This is a schematic diagram of the structure of the T-shaped airway of this application;

[0028] Figure 5 A cross-sectional structural diagram of the throttling channel and the pressure chamber of the present application;

[0029] Figure 6 This is a schematic structural diagram of the dual main airway system of this application;

[0030] Figure 7 This is a structural schematic diagram of the ultrasonic electromagnetic instrument of the present application equipped with the ultrasonic probe structure.

[0031] Description of reference numerals:

[0032] 1. Shell; 2. Air tank body; 3. Opening; 4. Assembly groove; 5. Sealing ring; 6. Silicone layer; 7. Rigid support layer; 8. Main air tank; 9. Through hole; 10. Bifurcation structure; 11. Auxiliary air tank; 12. Throttling air duct; 121. First section; 122. Second section; 13. Pressure chamber; 131. First chamber; 132. Second chamber; 14. Main air duct system; 100. Ultrasonic probe structure. DETAILED DESCRIPTION

[0033] To make the purpose, technical solutions, and advantages of the embodiments of this application more clear, the technical solutions in the embodiments of this application will be clearly and completely described below in conjunction with the drawings in the embodiments of this application. Obviously, the described embodiments are part of the embodiments of this application, not all of the embodiments. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of this application.

[0034] The disclosure below provides many different embodiments or examples for implementing different structures of the present application. In order to simplify the disclosure of the present application, the components and settings of specific examples are described below. Of course, these are merely examples and are not intended to limit the present application. In addition, the present application may repeat reference numbers and / or letters in different examples. Such repetition is for the purpose of simplicity and clarity and does not in itself indicate the relationship between the various embodiments and / or settings discussed.

[0035] For ease of description, spatially relative terms may be used herein to describe the relative position or movement of one element or feature relative to another element or feature as shown in the figures, such as "inside," "outside," "inside," "outside," "below," "beneath," "above," "above," "front," "back," and the like. Such spatially relative terms are intended to include different orientations of the device in use or operation other than the orientation depicted in the figures. For example, if the device in the figures undergoes a positional flip or a change in posture or a change in motion, then these directional indications will also change accordingly. For example, an element described as "below" or "below" another element or feature will subsequently be oriented as "above" or "above" another element or feature. Thus, the example term "below" can include both above and below orientations. The device may be oriented otherwise (rotated 90 degrees or in other orientations) and the spatially relative descriptors used herein will be interpreted accordingly.

[0036] In order to solve the problem that the ultrasonic detection head in the prior art lacks effective suspension buoyancy, resulting in inaccurate detection.

[0037] The present invention provides an ultrasonic probe structure installed on the surface of a gas injection device, including a shell, which is designed to be integrally formed or split (for example, an upper shell and a lower shell), wherein the split structure is assembled and fixed by screws, snaps, or ultrasonic pressing. The assembled probe body is installed on the surface of the gas injection device by fasteners such as bolts. During operation, the gas injection device inputs gas to the probe, and the gas flows through the internal channel and is ejected onto the surface of the object being tested. This technical solution uses the air pressure difference to generate a suspension force to form an air film with a suspension height of several microns to several hundred microns. This provides an ideal working environment for subsequent ultrasonic flaw detection. The structure has the characteristics of high strength, good durability, and flexible installation, which can ensure the accuracy and reliability of flaw detection.

[0038] like Figures 1 to 5 As shown, in this embodiment, the ultrasonic probe structure includes a shell 1, in which at least one air slot body 2 is provided; the air slot body 2 is provided with a bifurcation structure 10, and the bifurcation structure 10 divides the air slot body 2 into a main air slot 8 and at least two auxiliary air slots 11 symmetrically arranged relative to the main air slot 8; each auxiliary air slot 11 is connected to a throttling air channel 12, and the outer end of the throttling air channel 12 is connected to a pressure chamber 13 for diffusing gas and forming a uniform air film support.

[0039] When in use, the shell 1 is used to be assembled on an external gas injection device, and the external gas injection device is covered on the gas tank body 2 to close the opening 3 of the gas tank body 2 to form a closed airway, and then the closed airway is injected with gas through the gas injection port provided on the external gas injection device.

[0040] Specifically, after flowing out of the gas injection port, the gas first flows along the main gas groove 8. When it reaches the bifurcated structure 10, the airflow is evenly distributed to the auxiliary gas grooves 11. It then enters the throttle air channel 12 for flow regulation. The throttle air channel 12 runs through the upper and lower surfaces of the housing 1 to guide the airflow in the auxiliary gas grooves 11 into the pressure chamber 13. Within the pressure chamber 13, the airflow is fully diffused and evenly ejected, forming a stable air film between the surface of the lower housing 1 and the object being inspected, providing an ideal suspension working environment for ultrasonic testing.

[0041] It should be noted that if Figure 2 As shown, the opening 3 of the gas tank body 2 is circumferentially provided with an assembly groove 4, into which a sealing ring 5 is embedded. It should be understood that this design ensures that the connection between the gas tank body 2 and the external device is a sealed connection, preventing lateral gas leakage and causing pressure fluctuations in the gas tank body 2.

[0042] In a specific embodiment, the shape of the sealing ring 5 is adapted to the shape of the gas tank body 2 to shield the gas tank body 2. A through hole 9 is provided on the sealing ring 5, which is connected to the gas injection port of an external gas injection device and is used to guide the gas flowing out of the gas injection port into the interior of the gas tank body 2.

[0043] In addition, the sealing ring 5 has a silicone layer 6 and a rigid support layer 7 ; wherein the silicone layer 6 is coated on the outer surface of the rigid support layer 7 .

[0044] like Figure 3 As shown, since the airflow flowing out from the air outlet of the external device is a high-pressure airflow, the sealing ring 5 with the rigid support layer 7 can effectively withstand the impact of the high-pressure airflow, and avoid the sealing ring 5 from deforming due to the impact of the high-pressure airflow during use, resulting in poor sealing effect at the connection between the air tank body 2 and the external device. The rigid support surface is made of stainless steel, and the stainless steel skeleton can enhance the physical strength and rigidity of the sealing ring 5, making it not easy to deform under the working conditions of high-pressure gas, and can maintain stable sealing performance, reduce lateral gas leakage, and improve the uniformity of air film pressure. Of course, the rigid support layer 7 is not limited to stainless steel. Other metal materials with a certain strength can also be used. The specific one to be used depends on the actual use requirements.

[0045] In one embodiment, Figure 1As shown, the bifurcated structure 10 divides the main air slot 8 into two completely symmetrical auxiliary air slots 11. These two auxiliary air slots 11 not only lie in the same radial horizontal plane, but also have their central planes of symmetry completely overlap, ensuring uniform and symmetrical airflow distribution. This precisely symmetrical design maintains balanced airflow pressure on both sides, effectively avoiding air film fluctuations caused by uneven airflow.

[0046] When the detection surface is uneven, the traditional single-channel design will cause the airflow pressure to drop suddenly due to changes in local resistance, leading to problems such as uneven air film thickness, probe shaking and distortion of detection data. In order to solve this technical problem, the core innovation of this embodiment is to optimize the design of the single main air groove 8 into two completely symmetrical auxiliary air grooves 11. These two auxiliary air grooves 11 are not only in the same radial horizontal plane, but also their symmetry center planes completely overlap. Based on the Bernoulli equation, it is calculated that this symmetrical structure can automatically adjust the airflow distribution on both sides: when the resistance on one side increases due to surface unevenness, the other side will compensate accordingly, thereby maintaining the dynamic balance of the overall airflow. This self-balancing feature ensures that the probe can maintain a stable air film thickness and uniform pressure distribution under various surface conditions, effectively eliminating the probe shaking phenomenon, and greatly improving the accuracy of the detection data.

[0047] The Bernoulli equation calculation formula is as follows:

[0048] P 21 +1 / 2ρV1 2 =P 22 +1 / 2ρV2 2 Among them, P 21 and P 22 are the pressures of the two auxiliary gas grooves 11 at their respective locations close to the throttling gas passage 12 , ρ is the gas density, and V1 and V2 are the flow velocities of the two auxiliary gas grooves 11 at their respective locations close to the throttling gas passage 12 .

[0049] It should be understood that in the same environment, the gas density ρ on the left and right sides is the same. For example, the pressure of the main gas tank 8 is P, and the pressure on both sides after bifurcation is P 21 and P 22 , when the left resistance becomes smaller: the left flow velocity V1 increases, according to the above Bernoulli equation, P 21 The airflow automatically replenishes to the left side; the right side flow velocity V2 decreases, P 22 As the airflow increases, the airflow is suppressed. Therefore, after the airflow is replenished to the left, the final P 21 ≈P 22 , that is, the pressure on both sides of the main gas tank 8 is almost the same, so as to achieve pressure self-balance. It should be noted that, P 21 and P 22 The values ​​of V1 and V2 can be obtained by testing using a pressure sensor and a flow rate sensor respectively.

[0050] Therefore, when the left side of the sprayed object's surface is concave (low airflow resistance) and convex (high resistance) on the right side, it can be understood that on the same surface, the concave area has more space to accommodate airflow, resulting in less airflow resistance, faster flow, and lower pressure on the concave surface. If the right side is convex, the pressure situation is the opposite. Therefore, in this usage scenario, the airflow on the left side is fast and the pressure is low, while the right side is slow and the pressure is high. The Bernoulli equation automatically adjusts the situation: the left side accelerates air supply due to low pressure, while the right side restricts flow due to high pressure. According to Bernoulli's principle, the pressure on both sides is eventually rebalanced, and the air film thickness is consistent.

[0051] The air flow flows from the auxiliary air grooves 11 at both ends to the throttling air channel 12. Since the inner diameter of the throttling air channel 12 is smaller than the width of the auxiliary air grooves 11, the air flow flows from the wider auxiliary air grooves 11 to the narrow throttling air channel 12, and the flow rate becomes faster, in preparation for the subsequent air flow to enter the pressure chamber 13.

[0052] After the air flow enters the pressure chamber 13 from the narrower throttle air passage 12, since the inner diameter of the pressure chamber 13 is larger than the inner diameter of the throttle air passage 12, the air flow suddenly enters the wide space from the narrow space, and the air pressure is released and diffused, quickly covering the entire pressure chamber 13, so that the air flow in the pressure chamber 13 diffuses from the outlet of the throttle air passage 12 to the periphery of the pressure chamber 13 to form a uniform air film.

[0053] In summary, the present invention enables the ultrasonic probe to have an adaptive airflow balancing function through an innovative bifurcated flow channel design. This structure diverts the main air slot 8 into multiple symmetrically arranged auxiliary air slots 11. Based on the principle of low-pressure priority compensation in fluid mechanics, when detecting uneven surfaces, the structure automatically adjusts the branch airflows: the side with lower air pressure obtains more airflow compensation until the pressure in each channel reaches equilibrium. This dynamic self-balancing mechanism ensures that the air film ejected from each pressure chamber 13 maintains a uniform and stable pressure and thickness, completely solving the problem of uneven air film caused by air pressure imbalance when traditional probes are used to detect complex surfaces, and significantly improving detection accuracy and reliability.

[0054] For example, in a preferred embodiment, Figure 4 As shown, the cross-section of the bifurcation structure 10 is T-shaped. It should be understood that this embodiment uses the T-shaped bifurcation structure 10 to divide the main air groove 8 into two symmetrical airflows. During use, first, the geometric symmetry is used to achieve initial pressure balance between the airflows on both sides. Second, when the unevenness of the detection surface causes air pressure changes, the structure can automatically adjust the airflow distribution to quickly restore pressure balance. Finally, combined with the subsequent flow channel design, it ensures that the output air film is uniform and stable.

[0055] In this embodiment, the length of the main air groove 8 is 22 mm, and the total length of the two auxiliary air grooves 11 is 45 mm. The width of the main air groove 8 and the auxiliary air groove 11 are both 8 mm, and the depth is 7 mm. It should be noted that these specific dimensions are merely examples to illustrate the technical solution. In actual applications, the dimensions of the main air groove 8 and the auxiliary air groove 11 can be adjusted as needed. As long as the structure meets the requirements of this solution, the air pressure in the auxiliary air groove 11 can be calculated according to Bernoulli's principle.

[0056] It should also be noted that in this embodiment, the aspect ratio of the length and width of the throttle passage 12 ranges from 1 to 5. For example, if the length of the throttle passage 12 is 20 mm and its width is 4 mm, the aspect ratio is 5. It should also be noted that the width of the throttle passage 12 is the value of the narrowest point of the passage diameter in the longitudinal direction.

[0057] It should be understood that this design avoids excessive pressure drop caused by an excessively long throttle duct 12. For example, if the throttle duct 12 is 25 mm long and 4 mm wide, then the aspect ratio is greater than 5, resulting in excessive pressure drop and hindering the formation of an air film in the rear pressure chamber 13. In this case, the length of the throttle duct 12 should be shortened to ensure that the air flow velocity from the throttle duct 12 to the pressure chamber 13 is conducive to the formation of an air film. Conversely, if the throttle duct 12 is too short, turbulence is likely to occur, which is also not conducive to the formation of an air film in the rear pressure chamber 13. Therefore, it is more appropriate to set the aspect ratio of the length / width of the throttle duct 12 within a range of 1 to 5. In addition, the width of the throttle duct 12 should be smaller than the width of the auxiliary air groove 11. For example, the ratio of the width of the throttle duct 12 to the auxiliary air groove 11 should be between 1 / 3 and 2 / 3. This range helps the air flow in the auxiliary air groove 11 flow into the throttle duct 12.

[0058] When the airflow enters the throttle air passage 12 from the auxiliary air groove 11, the diameter of the throttle air passage 12 is smaller than the flow path of the auxiliary air groove 11. For example, the ratio of the diameter of the throttle air passage 12 to the flow path of the auxiliary air groove 11 is 1:2. Therefore, the single airflow enters the throttle air passage 12 with a smaller diameter from the larger flow path, and the airflow speed increases accordingly. This acceleration process prepares the subsequent airflow for entering the pressure chamber 13.

[0059] In addition, the ratio of the diameter of the pressure chamber 13 to the diameter of the throttling air channel 12 (ie, the width of the throttling air channel 12) is in the range of three to ten times, to avoid the diameter ratio being too large or too small, which affects the pressure equalization and causes the air film to fail to form.

[0060] That is, when high-speed airflow enters pressure chamber 13 from throttle passage 12, the cross-sectional area of ​​the chamber suddenly expands, causing the airflow velocity to decrease rapidly. The airflow then diffuses radially from the outlet of throttle passage 12, becoming evenly distributed circumferentially under the guidance of the chamber walls, ultimately forming a stable and uniform air film layer around the periphery of pressure chamber 13. This process achieves effective conversion and uniform distribution of airflow energy, providing a stable air film support for subsequent testing.

[0061] Furthermore, the airflow direction of the throttle air channel 12 is perpendicular to the airflow direction of the auxiliary air slot 11 and the main air slot 8, forming an orthogonal steering structure. It should be understood that the orthogonal steering structure creates local flow resistance, forcing the airflow to undergo a 90° deflection at the intersection of the auxiliary air slot 11 and the throttle air channel 12. This sudden change in flow direction causes the airflow to flow from the wide auxiliary air slot 11 into the narrow throttle air channel 12, accelerating the airflow velocity and also effectively eliminating turbulence generated by the airflow at the auxiliary air slot 11, ensuring the stability of the airflow entering the pressure chamber 13.

[0062] In another embodiment, the cross section of the bifurcated structure 10 also includes a Y-shape. The working principle of the Y-shaped airflow is the same as that of the T-shaped bifurcated structure above. The air pressure at both ends of the auxiliary air groove can also be calculated by the Bernoulli equation, which will not be elaborated here.

[0063] Further, such as Figure 5 As shown, the throttling air passage 12 has a first section 121 and a second section 122 that are connected to each other, and the inner diameter of the first section 121 is greater than the inner diameter of the second section 122 .

[0064] The inner diameter of the first section 121 of the throttling air duct 12 is smaller than the initial aperture of the connection between the auxiliary air groove 11 and the throttling air duct 12, and the longitudinal section of the connection presents a tapered structure that gradually narrows from top to bottom, so that the airflow from the auxiliary air groove 11 converges here and enters the first section 121 more smoothly. Subsequently, the airflow flows along the first section 121 to the second section 122, and the connection between the two sections also adopts a tapered design to further compress the airflow and enhance its convergence effect. Finally, the connection between the second section 122 and the pressure chamber 13 still maintains a tapered transition that gradually narrows from top to bottom, so that the airflow enters the spacious pressure chamber 13 from the narrow second section 122, and can enter the pressure chamber 13 at a higher speed, forming a diffused airflow with sufficient explosive power, thereby stably forming an air film in the pressure chamber 13.

[0065] Further, such as Figure 5 As shown, the pressure chamber 13 includes a first chamber 131 and a second chamber 132 that are interconnected; wherein the longitudinal section of the first chamber 131 is rectangular, and the longitudinal section of the second chamber 132 is a cone that is narrow at the top and wide at the bottom.

[0066] It should be understood that as the airflow flows from the second section 122 into the first cavity 131, it diffuses. As the airflow flows from the first cavity 131 into the second cavity 132, it further diffuses, ultimately achieving uniform circumferential overflow. This structure ensures a uniform and stable air film, significantly improving the probe's levitation performance and operational reliability.

[0067] Furthermore, in some specific usage scenarios, such as Figure 6 As shown, the upper shell 1 is provided with two independent air trough bodies 2, which form two independent main airway systems 14 when combined with external air injection equipment. Each main airway system 14 includes a bifurcation structure 10 and symmetrically arranged auxiliary air troughs 11, a throttling airway 12 connected to the auxiliary air trough 11, and a pressure chamber 13 connected to the throttling airway 12.

[0068] It should be understood that by providing two independent main airway systems 14 in the upper shell 1, significant technological advancements have been achieved: each main airway system 14 includes a complete airflow path. This dual-system design effectively solves the problem of insufficient air film coverage when a single airway probe is inspecting large or irregular surfaces, significantly improving the air film coverage range. At the same time, the two independent systems can autonomously adjust airflow distribution based on the flatness differences in different areas of the surface, achieving dynamic pressure balance based on the Bernoulli principle. This structure completely eliminates the air film pressure imbalance phenomenon commonly seen in traditional single-system probes when inspecting complex surfaces, enabling the probe to maintain a stable operating state under various inspection conditions. It is particularly suitable for large workpieces and high-precision inspection scenarios, significantly improving the reliability of inspection results.

[0069] Furthermore, each main airway system 14 is symmetrically arranged about the central axis of the ultrasound probe structure and is located on the same radial plane.

[0070] When in use, the two main airway systems 14 are symmetrically arranged so that the airflow reaction forces generated offset each other, eliminating probe deflection and ensuring absolute horizontal stability during the detection process; and the airflow fields of the two main airway systems 14 construct a complete and gapless air film coverage area on the detection surface; at the same time, the dual systems can synchronously respond to surface deformation, achieve collaborative pressure compensation through the Bernoulli effect, shorten the balance recovery time, and meet the detection needs of various uneven surfaces.

[0071] In addition, an ultrasonic electromagnetic instrument is proposed, such as Figure 7 As shown, the ultrasonic probe structure 100 includes an apparatus body and the aforementioned ultrasonic probe structure 100. The ultrasonic probe structure 100 is installed below the apparatus body. When performing flaw detection on uneven surfaces, an ultrasonic electromagnetic instrument equipped with this ultrasonic probe structure can automatically adapt to the surface unevenness and maintain stable suspension of the probe through dynamic pressure regulation, ensuring the formation of a uniform film and preventing the probe from shaking during operation, which could affect detection accuracy.

[0072] In the above embodiments, the description of each embodiment has its own focus. For parts that are not described in detail in a certain embodiment, reference can be made to the relevant descriptions of other embodiments.

[0073] In the description of this application, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise" and the like to indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on this application.

[0074] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of the technical features being referred to. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the features. Throughout the description of this application, "plurality" means two or more, unless otherwise specifically defined.

[0075] In this application, unless otherwise expressly specified or limited, terms such as "mounted," "connected," "connect," and "fixed" should be understood broadly. For example, they may refer to connection, detachable connection, or integration; mechanical connection or electrical connection; direct connection or indirect connection through an intermediate medium; and internal communication between two components or interaction between two components. Those skilled in the art will understand the specific meanings of the above terms in this application based on specific circumstances.

[0076] In this application, unless otherwise expressly specified or limited, a first feature being "above" or "below" a second feature may include the first and second features being in direct contact, or may include the first and second features being in contact not directly but through another feature between them. Moreover, a first feature being "above," "above," and "above" a second feature may include the first feature being directly above or obliquely above the second feature, or may simply mean that the first feature is higher in level than the second feature. A first feature being "below," "below," and "below" a second feature may include the first feature being directly below or obliquely below the second feature, or may simply mean that the first feature is lower in level than the second feature.

[0077] In the description of this specification, the reference terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" mean that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present application. In this specification, the schematic expressions of the above terms should not be understood as necessarily referring to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art can combine and combine different embodiments or examples described in this specification.

[0078] Obviously, those skilled in the art may make various modifications and variations to this application without departing from the spirit and scope of this application. Thus, as long as these modifications and variations of this application fall within the scope of the claims of this application and their equivalents, this application is intended to include these modifications and variations.

[0079] The above description is a specific embodiment of the present application, but the scope of protection of the present application is not limited thereto. Any person skilled in the art can easily conceive of various equivalent modifications or substitutions within the technical scope disclosed in this application, and such modifications or substitutions should be included in the scope of protection of this application. Therefore, the scope of protection of this application should be based on the scope of protection of the claims.

Claims

1. An ultrasonic probe structure is provided on the surface of a gas injection device, characterized in that: The invention comprises a shell, wherein at least one air tank body is provided in the shell; The air tank body is provided with a bifurcation structure, which divides the air tank body into a main air tank and at least two auxiliary air tanks symmetrically arranged relative to the main air tank; Each auxiliary air groove is connected to a throttling air channel, and the outer end of the throttling air channel is communicated with a pressure chamber used for diffusing gas and forming a uniform air film support.

2. The ultrasonic probe structure according to claim 1, wherein: The auxiliary gas grooves of each route are located on the same radial horizontal plane.

3. The ultrasonic probe structure according to claim 1, wherein: The throttling air passage comprises a first section and a second section which are connected to each other, and the inner diameter of the first section is greater than the inner diameter of the second section.

4. The ultrasonic probe structure according to claim 2, characterized in that: The cross section of the bifurcation structure is T-shaped.

5. The ultrasonic probe structure according to claim 1, characterized in that: An assembly groove is provided around the opening of the air tank body, and a sealing ring is embedded in the assembly groove.

6. The ultrasonic probe structure according to claim 5, characterized in that: The sealing ring comprises a silicone layer and a rigid support layer; Wherein, the silica gel layer is coated on the outer surface of the rigid support layer.

7. The ultrasonic probe structure according to claim 1, characterized in that: The pressure chamber includes a first chamber and a second chamber that are interconnected; The longitudinal section of the first cavity is a rectangle, and the longitudinal section of the second cavity is a cone that is narrow at the top and wide at the bottom.

8. The ultrasonic probe structure according to any one of claims 1 to 7, characterized in that: The shell is provided with two independent air tank bodies, forming two independent main airway systems, each main airway system includes a bifurcation structure and symmetrically arranged auxiliary air tanks, a throttling airway connected to the auxiliary air tanks, and a pressure chamber connected to the throttling airway.

9. The ultrasonic probe structure according to claim 8, characterized in that: Each main airway system is symmetrically arranged about the central axis of the ultrasound probe structure and is located on the same radial plane.

10. An ultrasonic electromagnetic instrument, comprising a device body and an ultrasonic probe structure according to claim 9.

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