Composite inner core supersonic cutting nozzle

Abstract

The utility model belongs to laser cutting equipment technical field relates to a kind of composite inner core supersonic cutting nozzle, including cutting nozzle shell, and the first layer annular inner core and second layer annular inner core being set in cutting nozzle shell, the first layer annular inner core is connected in the top of second layer annular inner core by annular retraction link segment, the outer periphery of the first layer annular inner core and second layer annular inner core is respectively spaced apart with multiple gas passages and multiple peripheral auxiliary channels, and multiple gas passages and multiple peripheral auxiliary channels are staggered arrangement between them.The utility model can realize the supersonic output of auxiliary gas, stable flow field and concentrated pressure by optimizing inner core structure, gas passage layout and nozzle geometry, significantly improve plate cutting efficiency and section quality, with the advantages of improving flow rate, optimizing flow field, improving quality, strong compatibility etc..

Description

Technical Field

[0001] This utility model belongs to the field of laser cutting equipment technology, specifically relating to a composite core supersonic cutting nozzle. Background Technology

[0002] As a key component of laser cutting equipment, the cutting nozzle's structural design directly determines the flow rate, pressure distribution, and flow field stability of the cutting assist gas, thus affecting metal cutting efficiency and cross-sectional quality. With the increasing demand for medium-thick plate cutting in the manufacturing industry, traditional cutting nozzles have gradually revealed the following technical shortcomings:

[0003] 1. Insufficient gas flow rate: Ordinary cutting nozzles are mostly single-layer channel structures, which cannot fully accelerate the auxiliary gas. The outlet flow rate is low, making it difficult to quickly blow away the cutting slag, resulting in low cutting efficiency and the problem of slag sticking to the cross-section.

[0004] 2. Poor flow field stability: Traditional cutting nozzles lack flow guidance and pressure concentration design. During the flow process, the gas is easily disturbed by the influx of external air, resulting in turbulent flow field and defects such as ripples and tilting on the cutting surface.

[0005] 3. Uneven pressure distribution: The existing nozzle gas channel layout is unreasonable, the outlet pressure is dispersed, and it is impossible to form a concentrated high-pressure airflow zone. When cutting medium and thick plates, it is difficult to penetrate the thick slag layer, and the cutting depth and quality are limited.

[0006] 4. Limited adaptability: Traditional cutting nozzles are mostly fixed structures, which cannot flexibly adjust airflow parameters according to the thickness and material of the plate, resulting in poor compatibility with cutting workpieces of different specifications. Utility Model Content

[0007] The purpose of this invention is to solve the problems of insufficient flow velocity, turbulent flow field, and pressure dispersion in the existing cutting nozzle, and to design a composite inner core supersonic cutting nozzle with supersonic airflow output, stable flow field, and concentrated pressure.

[0008] To achieve the above objectives, the technical solution adopted by this utility model is: a composite inner core supersonic cutting nozzle, including a cutting nozzle shell, and a first annular inner core and a second annular inner core disposed inside the cutting nozzle shell. The first annular inner core is connected above the second annular inner core through an annular inward connecting section. The outer periphery of the first annular inner core and the second annular inner core are respectively provided with multiple gas channels and multiple peripheral auxiliary channels at intervals, and the multiple gas channels and multiple peripheral auxiliary channels are staggered.

[0009] Preferably, the peripheral auxiliary channel is located at the upper end of the second annular inner core, and the lower end of the second annular inner core has an inwardly inclined conical design.

[0010] Preferably, a conical flow guide space is formed between the lower end of the second annular inner core and the outer shell of the nozzle, and the upper and lower ends of the conical flow guide space are respectively connected to the peripheral auxiliary channel and the main nozzle.

[0011] Preferably, a boss structure is formed between adjacent peripheral auxiliary channels, and the boss structure is used to limit and cooperate with the stepped surface inside the nozzle shell.

[0012] Preferably, there are four gas channels and four peripheral auxiliary channels, and the gas channels have a structure that is wider at the top and narrower at the bottom.

[0013] Preferably, the top of the cutting nozzle housing is connected to a threaded tube, and the threaded tube is provided with external threads.

[0014] Preferably, the bottom of the cutting nozzle shell has a concave curved surface design.

[0015] After adopting the above technical solution, the composite inner core supersonic cutting nozzle provided by this utility model has the following beneficial effects:

[0016] (1) Increased flow rate: Through multiple expansion acceleration and pressure concentration design, this utility model can achieve supersonic output of outlet airflow, with a flow rate significantly higher than that of traditional composite cutting nozzles;

[0017] (2) Flow field optimization: This utility model can form a stable "diamond wave" flow field, reduce external interference, and reduce the ripple defects of the cut section by 30%;

[0018] (3) Quality improvement: This utility model is designed for cutting medium-thick plates of 3-50mm, improving the flatness of the cross section by 20% and reducing the slag adhesion rate to below 5%, which can reduce subsequent processing steps;

[0019] (4) Strong compatibility: This utility model can be adapted to various cutting auxiliary gases such as oxygen, nitrogen, and air, and can meet the cutting needs of medium and thick plates of different materials such as carbon steel, aluminum plate, and stainless steel. Attached Figure Description

[0020] Figure 1 This is a cross-sectional view of the structure of a composite inner core supersonic cutting nozzle according to this utility model;

[0021] Figure 2 This is a schematic diagram of the structure of a composite inner core supersonic cutting nozzle according to the present invention;

[0022] Figure 3 This is a schematic diagram of the structure of the first annular inner core and the second annular inner core in this utility model.

[0023] Among them: 1. Cutting nozzle shell, 2. First layer annular inner core, 3. Second layer annular inner core, 4. Gas channel, 5. Inward connecting section, 6. Outer auxiliary channel, 7. Conical guide space, 8. Main nozzle, 9. Concave curved surface structure. Detailed Implementation

[0024] The present invention will now be described in further clear and complete detail with reference to the accompanying drawings and specific embodiments. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of them. The following description of at least one exemplary embodiment is merely illustrative and is in no way intended to limit the present invention or its application or use. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without inventive effort are within the scope of protection of the present invention.

[0025] It should be noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the exemplary embodiments according to this application. As used herein, the singular form is intended to include the plural form as well, unless the context clearly indicates otherwise. Furthermore, it should be understood that when the terms "comprising" and / or "including" are used in this specification, they indicate the presence of features, steps, operations, devices, components, and / or combinations thereof.

[0026] Unless otherwise specifically stated, the relative arrangement, numerical expressions, and values ​​of the components and steps described in these embodiments do not limit the scope of this invention. It should also be understood that, for ease of description, the dimensions of the various parts shown in the drawings are not drawn to actual scale. Techniques, methods, and devices known to those skilled in the art may not be discussed in detail, but where appropriate, such techniques, methods, and devices should be considered part of the specification. In all examples shown and discussed herein, any specific values ​​should be interpreted as merely exemplary and not as limitations. Therefore, other examples of exemplary embodiments may have different values. It should be noted that similar reference numerals and letters in the following drawings denote similar items; therefore, once an item is defined in one drawing, it need not be further discussed in subsequent drawings.

[0027] In the description of this utility model, it should be understood that the directional terms such as "front, back, up, down, left, right", "horizontal, vertical, horizontal" and "top, bottom" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this utility model and simplifying the description. Unless otherwise stated, these directional terms do not indicate or imply that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation on the scope of protection of this utility model. The directional terms "inner" and "outer" refer to the inner and outer contours of each component itself.

[0028] For ease of description, spatial relative terms such as "above," "on top of," "on the upper surface of," "above," etc., are used herein to describe the spatial positional relationship of a device or feature as shown in the figures to other devices or features. It should be understood that spatial relative terms are intended to encompass different orientations in use or operation beyond the orientation of the device as described in the figures. For example, if the device in the figures were inverted, a device described as "above" or "on top of" other devices or structures would subsequently be positioned as "below" or "under" other devices or structures. Thus, the exemplary term "above" can include both "above" and "below." The device may also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatial relative descriptions used herein will be interpreted accordingly.

[0029] Furthermore, it should be noted that the use of terms such as "first" and "second" to define components is merely for the purpose of distinguishing the corresponding components. Unless otherwise stated, the above terms have no special meaning and therefore cannot be construed as limiting the scope of protection of this utility model.

[0030] This utility model discloses a composite core supersonic cutting nozzle, such as... Figure 1-3 As shown, it includes a cutting nozzle shell 1, and a first annular inner core 2 and a second annular inner core 3 disposed inside the cutting nozzle shell 1. The first annular inner core 2 is connected above the second annular inner core 3 through an annular inward connecting section 5. Multiple gas channels 4 and multiple peripheral auxiliary channels 6 are distributed at intervals on the outer periphery of the first annular inner core 2 and the second annular inner core 3, and the multiple gas channels 4 and multiple peripheral auxiliary channels 6 are staggered.

[0031] The second-layer annular inner core 3 includes an upper end and a lower end. The upper end of the first-layer annular inner core 2, the annular inward connecting section 5, and the second-layer annular inner core 3 adopts a concentric annular structure design. The lower end of the second-layer annular inner core 3 adopts a concentric and inwardly inclined conical annular design. The nozzle shell 1 can cooperate with the upper and lower ends of the second-layer annular inner core 3 to form a parallel space and a conical guide space 7 at the corresponding upper and lower ends. The upper and lower ends of the conical guide space 7 are respectively connected to the parallel space and the main nozzle 8. Specifically, four gas channels 4 are distributed at intervals on the outer periphery of the first-layer annular inner core 2. The gas channels 4 have a structure design that is wider at the top and narrower at the bottom to provide an initial acceleration path for the gas. Four peripheral auxiliary channels 6 are also provided, distributed at intervals on the second-layer annular inner core 3. The upper part, located in the parallel space, can connect with the conical guide space 7. Furthermore, through the interlacing of the outer auxiliary channel 6 and the gas channel 4, the gas can be guided to undergo multiple expansion and acceleration inside the nozzle, forming a triangular high-pressure zone in the main nozzle 8, ultimately achieving supersonic airflow output. The pressure concentration is increased by 25%, ensuring that the high-pressure airflow can penetrate the slag layer of medium and thick plates. At the same time, the design of the conical guide space 7 can enhance the stability of the flow field and the gas focusing, enabling the airflow to converge at a specific angle (15-30°), thus avoiding the effect of airflow dispersion. In addition, the diameter of the main nozzle 8 can be optimized by replacing the traditional expansion curve with two arcs (the two have a 90% similarity in shape), solving the problem of gas over-expansion caused by the large outlet diameter of the traditional supersonic nozzle, so that the airflow can still maintain a stable supersonic state outside the nozzle, ensuring cutting depth and efficiency.

[0032] Furthermore, a boss structure is formed between adjacent peripheral auxiliary channels 6. The boss structure is used to limit the engagement with the stepped surface inside the nozzle housing 1, thus ensuring the stability of the nozzle structure. The top of the nozzle housing 1 is connected to a threaded tube with external threads. The bottom of the nozzle housing 1 is designed with a concave curved surface structure 9. In this way, the concave curved surface structure 9 can increase the angle of gas entering the nozzle and the gap between the plate, reduce the horizontal velocity component of the airflow, and reduce the disturbance of the airflow caused by the influx of external air. At the same time, it works in conjunction with the conical guide space 7 to form a stable "diamond wave" flow field at the outlet, reducing the flow field turbulence by 40%.

[0033] When this composite inner core supersonic cutting nozzle is used, the cutting auxiliary gas (such as oxygen, pressure 0.6-1.0 bar) enters the nozzle shell 1 and first undergoes initial acceleration through the four "wide at the top and narrow at the bottom" gas channels 4 of the first annular inner core 2. Then, the airflow enters the second composite inner core 3 through the annular concave connecting section 5, and undergoes multiple expansion accelerations in the parallel space and the conical guide space 7. At the same time, the peripheral auxiliary channel 6 guides part of the airflow, and after adjusting the flow direction through the guide slope on one side of the second composite inner core 3 and the concave curved surface structure 9 on one side of the nozzle shell 1, it merges with the airflow of the second composite inner core 3 at the main nozzle 8, forming a triangular high-pressure zone and a "diamond wave" flow field, and finally acts on the metal cutting area with supersonic airflow.

[0034] When cutting 3-10mm thin medium plates: use 0.4-0.6 bar oxygen to take advantage of the flow field stability and ensure the flatness of the cross section;

[0035] When cutting medium plates with a thickness of 10-50mm: increase the gas pressure to 0.6-1.6 bar, and use the concentrated pressure of the triangular high-pressure zone to penetrate the thick molten slag layer to ensure cutting depth and efficiency;

[0036] When cutting aluminum plates and stainless steel materials from 3-50mm: switch the auxiliary gas to air. Through the airflow acceleration and focusing design of the composite inner core, the problem of insufficient air pressure is reduced, while ensuring that the slag on the bottom of the aluminum plate is reduced and the cut surface of the stainless steel is not too blackened by oxidation.

[0037] Tests showed that when using the composite inner core supersonic cutting nozzle of this invention to cut 20mm carbon steel, the cutting speed reached 1.6m / min (20% higher than the traditional composite cutting nozzle), the surface roughness Ra≤6.3μm (the traditional cutting nozzle Ra≈12.5μm), and the slag adhesion rate was only 3%, meeting the high-precision cutting requirements of medium and thick plates.

[0038] The above description is only a preferred embodiment of the present utility model, but the protection scope of the present utility model is not limited thereto. Any equivalent substitutions or changes made by those skilled in the art within the technical scope disclosed in the present utility model, based on the technical solution and the inventive concept of the present utility model, should be included within the protection scope of the present utility model.

Claims

1. A composite core supersonic cutting nozzle, characterized in that: It includes a cutting nozzle shell (1), and a first annular inner core (2) and a second annular inner core (3) disposed inside the cutting nozzle shell (1). The first annular inner core (2) is connected above the second annular inner core (3) through an annular inward connecting section (5). The outer periphery of the first annular inner core (2) and the second annular inner core (3) are respectively provided with multiple gas channels (4) and multiple peripheral auxiliary channels (6) at intervals, and the multiple gas channels (4) and multiple peripheral auxiliary channels (6) are staggered.

2. The composite core supersonic cutting nozzle according to claim 1, characterized in that: The peripheral auxiliary channel (6) is located at the upper end of the second annular inner core (3), and the lower end of the second annular inner core (3) has an inwardly inclined conical design.

3. The composite core supersonic cutting nozzle according to claim 2, characterized in that: The lower end of the second layer annular inner core (3) forms a conical guide space (7) between the cutter nozzle shell (1) and the upper and lower ends of the conical guide space (7) are respectively connected to the peripheral auxiliary channel (6) and the main nozzle (8).

4. The composite core supersonic cutting nozzle according to claim 1, characterized in that: A boss structure is formed between adjacent peripheral auxiliary channels (6), and the boss structure is used to limit the engagement with the stepped surface inside the nozzle shell (1).

5. A composite core supersonic cutting nozzle according to claim 1, characterized in that: The gas channel (4) and the peripheral auxiliary channel (6) are each provided with four, and the gas channel (4) has a structure design that is wider at the top and narrower at the bottom.

6. The composite core supersonic cutting nozzle according to claim 1, characterized in that: The top of the cutting nozzle housing (1) is connected to a threaded tube, which has external threads.

7. A composite core supersonic cutting nozzle according to claim 1, characterized in that: The bottom of the cutting nozzle shell (1) is designed with a concave curved surface structure (9).

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