An aerosol nozzle

Abstract

The present invention relates to the technical field of powder raw material preparation, and specifically to an aerosol nozzle. It comprises a first spray disc cover, a second spray disc cover, and an inner rotor; the inner rotor comprises a connecting portion and a nozzle portion, a disturbance piece is provided on the outer wall of the nozzle portion, and the end of the disturbance piece extends to the end of the nozzle portion; the first spray disc cover comprises a conforming portion and a duct cavity, and a first gap exists between the outer wall of the conforming portion and the inner wall of the inner rotor; the inner wall of the nozzle of the second spray disc cover and the outer wall of the nozzle portion constitute a Laval nozzle structure, and the Laval nozzle structure comprises a second gap; a gas chamber is formed between the first spray disc cover and the second spray disc cover, a turbine impeller is provided in the gas chamber, and turbine blades are arranged in an array along the circumferential direction on the turbine impeller; and an air guide channel connected to the gas chamber. In response to the technical problem that the existing technology for preparing metal powder is not effective, the present invention can achieve high-frequency disturbance of the metal liquid film, so that the prepared powder has a narrower particle size and better sphericity.

Description

Technical Field

[0001] The invention relates to the technical field of powder raw material preparation, and in particular to an aerosol nozzle. Background Art

[0002] 3D printing, also known as additive manufacturing, is a technology that uses materials such as powdered metal to construct objects layer by layer, based on digital model files. The quality of powdered metal, as a raw material, is crucial to the quality of the final product. Currently, there are several methods for producing spherical metal powder in the industry, with atomization being the most popular method.

[0003] Existing technologies primarily improve metal powder production by adjusting molten metal properties, such as viscosity and flow rate, or by heating the atomizing gas to increase its initial velocity. However, powders produced using these techniques still suffer from poor sphericity, a wide distribution of powder strength, a high incidence of satellite and hollow powders, and a low yield per furnace.

[0004] In the process of studying the atomization of molten metal, it was found that when the supersonic atomizing gas forms a Mach ring, a gas reflux area from bottom to top appears in the internal space. The reflux gas impacts the molten metal, causing the liquid flow to form an umbrella-shaped liquid film. The metal powder is formed after the edge and middle part of the umbrella-shaped metal liquid film separate from the main body. Figure 8 , attached Figure 8 From the existing literature "Clogging of ladle nozzles during gas atomization in vacuum induction melting: Influence of draft tube geometry", the formation of umbrella-shaped liquid film and powder particles during the atomization process was simulated.

[0005] Based on existing research, some researchers have proposed using external energy to interfere with the liquid film state and improve powder quality: for example, applying high-frequency vibrations, or locally applying ultrasound or high-frequency magnetic fields. However, these methods require significant modifications to the nozzle structure or even the entire atomization device. Moreover, due to the high density and rapid flow rate of the liquid metal itself, these external effects are not significant, resulting in limited improvement in the quality of the prepared metal powder. Furthermore, they consume a lot of energy, increasing product costs. Summary of the Invention

[0006] Technical problem to be solved by the invention

[0007] In response to the technical problem that the existing technology for preparing metal powder is not effective, the present invention provides an aerosol nozzle, which uses high-frequency disturbance of the metal liquid film to keep the metal liquid film in a metastable state, making it easier to start breaking at the edge of the metal liquid film, thereby improving the breakage rate and making the prepared powder have a narrower particle size and better sphericity.

[0008] Technical Solution

[0009] In order to solve the above problems, the technical solution provided by the present invention is:

[0010] An aerosol nozzle comprises a first spray disc cover, a second spray disc cover, and an inner rotor; the inner rotor is located between the first spray disc cover and the second spray disc cover; the inner rotor comprises a connecting portion and a nozzle portion, the connecting portion is located on the side of the nozzle portion close to the first spray disc cover; at least one disturbance member is provided on the outer wall of the nozzle portion, the disturbance member is a protrusion or a groove, and the end of the disturbance member extends to the end of the nozzle portion; the first spray disc cover comprises a conforming portion and a duct cavity, the outer wall of the conforming portion matches the inner wall of the inner rotor, there is a first gap between the outer wall of the conforming portion and the inner wall of the inner rotor, and the duct cavity is arranged through the conforming portion; the second spray disc cover comprises a jet port, the jet port surrounds the outer periphery of the nozzle portion, and the inner wall of the jet port is aligned with The outer wall of the nozzle portion constitutes a Laval nozzle structure, and the Laval nozzle structure includes a second gap; a gas chamber is formed between the first spray disc cover and the second spray disc cover, and the gas chamber is connected to the Laval nozzle structure; at least one group of turbine components is arranged in the gas chamber; the turbine component includes at least one turbine impeller, and the turbine impeller is fixedly connected to the connecting portion, and turbine blades are arranged in an array along the circumferential direction on the turbine impeller, and the turbine blades are arranged obliquely; it also includes an air guide channel, and the air guide channel includes an air inlet and an air outlet, and the air inlet is located on the first spray disc cover or the second spray disc cover, and the air outlet is connected to the gas chamber, and the air outlet is located on the upper side, side side or oblique upper side of the turbine impeller.

[0011] Optionally, the turbine assembly further includes a turbine guide vane fan, which is fixedly connected to the first spray disc cover and is located on the side of the turbine impeller close to the first spray disc cover; the turbine guide vane fan includes a plurality of guide blades arranged in an array along a circumferential direction, and the inclination direction of the guide blades is opposite to that of the turbine blades.

[0012] Optionally, adjacent guide vanes form a first airflow channel along the axial direction of the turbine guide vane fan, and adjacent turbine blades form a second airflow channel along the axial direction of the turbine impeller, and the first airflow channel and the second airflow channel are convergently arranged along the axial direction.

[0013] Optionally, the turbine blades and the guide blades are twisted clockwise or counterclockwise along the radial extension direction, and the twisting directions of the turbine blades and the guide blades are opposite.

[0014] Optionally, at least one first vent is provided on the connecting portion, at least one airflow cavity connected to the outside is provided on the conformal portion, a second vent is provided on the airflow cavity, and the gas storage cavity, the first vent and the first gap, the second vent and the airflow cavity are all connected.

[0015] Optionally, a ring groove is provided on a side of the connecting portion close to the conformable portion, and the vent hole is provided through the ring groove.

[0016] Optionally, at least one compressor assembly is provided in the gas chamber, and the compressor assembly is located on a side of the turbine assembly close to the second spray disc cover; the compressor assembly includes a compressor impeller and a compressor static impeller, the compressor impeller is fixedly connected to the connecting part, the compressor static impeller is fixedly connected to the second spray disc cover, and the compressor impeller is located between the compressor static impeller and the turbine assembly; the compressor static impeller includes a plurality of guide vanes arranged in an array along a circumferential direction, and the compressor impeller includes a plurality of compression blades arranged in an array along a circumferential direction, the guide vanes are inversely inclined to the compression blades, and the compression blades are inversely inclined to the turbine blades.

[0017] Optionally, adjacent guide vanes form a third airflow channel along the axial direction of the compressor static impeller, and adjacent compressor blades form a fourth airflow channel along the axial direction of the compressor dynamic impeller, and the third airflow channel and the fourth airflow channel are diffusely arranged along the axial direction.

[0018] Optionally, the guide vanes and the compressor blades are twisted clockwise or counterclockwise along the radial extension direction, and the twisting directions of the guide vanes and the compressor blades are opposite.

[0019] Optionally, the first spray disc cover, the second spray disc cover and the inner rotor are made of metal, or a metal and ceramic composite material, or a ceramic material, or a polymer material.

[0020] Beneficial effects

[0021] Compared with the prior art, the technical solution provided by the present invention has the following beneficial effects:

[0022] In response to the technical problem that the existing technology for preparing metal powder is not effective, the present invention uses high-frequency disturbance of the metal liquid film to keep the metal liquid film in a metastable state, making it easier to begin to break at the edge of the metal liquid film, thereby improving the breakage rate and making the prepared powder have a narrower particle size and better sphericity. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 This is one of the structural schematic diagrams of an aerosol nozzle proposed in an embodiment of the present invention.

[0024] Figure 2 This is the second structural schematic diagram of an aerosol nozzle proposed in an embodiment of the present invention.

[0025] Figure 3 This is a schematic structural diagram of the inner rotor proposed in an embodiment of the present invention.

[0026] Figure 4This is a schematic diagram of the explosion structure of an aerosol nozzle proposed in an embodiment of the present invention.

[0027] Figure 5 This is a schematic cross-sectional view of an aerosol nozzle according to an embodiment of the present invention.

[0028] Figure 6 This is a schematic diagram of the unfolded blades of the turbine assembly proposed in an embodiment of the present invention.

[0029] Figure 7 This is a schematic diagram of the unfolded blades of the compressor assembly proposed in an embodiment of the present invention.

[0030] Figure 8 Schematic diagram of the simulation of the formation of umbrella-shaped liquid film and powder particles during the atomization process. DETAILED DESCRIPTION

[0031] In order to further understand the content of the present invention, the present invention is described in detail with reference to the accompanying drawings and embodiments.

[0032] The present application will be further described below in conjunction with the accompanying drawings and examples. It should be understood that the specific embodiments described herein are intended solely to illustrate the relevant inventions and are not intended to limit the inventions. It should also be noted that, for ease of description, only portions relevant to the invention are shown in the drawings. Terms such as "first" and "second" in the present application are provided for the convenience of describing the technical solutions of the present invention and do not have a specific limiting effect. They are general references and do not constitute a limitation on the technical solutions of the present invention. It should be noted that the embodiments and features therein in the present application may be combined with each other unless there is a conflict. In the description of the present invention, it should be noted that terms such as "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer" indicate positions or positional relationships based on the positions or positional relationships shown in the drawings. These terms are intended solely to facilitate the description of the present invention and simplify the description. They do not indicate or imply that the devices or components referred to must have a specific orientation, be constructed, or operate in a specific orientation. Therefore, they should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance. Unless otherwise clearly specified and limited, the terms "installed", "connected" and "connected" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, or it can be a communication between the two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to the specific circumstances. Multiple technical solutions in the same embodiment, as well as multiple technical solutions in different embodiments, can be arranged and combined to form new technical solutions that do not have contradictions or conflicts, all of which are within the scope of protection required by the present invention.

[0033] Example 1

[0034] Combined with attachment Figure 1-5This embodiment provides an aerosol nozzle, comprising a first spray disc cover 110, a second spray disc cover 120, and an inner rotor 130; the inner rotor 130 is located between the first spray disc cover 110 and the second spray disc cover 120; the inner rotor 130 comprises a connecting portion 131 and a nozzle portion 132, the connecting portion 131 is located on the side of the nozzle portion 132 close to the first spray disc cover 110; at least one disrupting member 135 is provided on the outer wall of the nozzle portion 132, the disrupting member 135 The end of the disrupter 135 extends to the end of the nozzle portion 132; the first spray disc cover 110 includes a conforming portion 111 and a conduit cavity 112, the outer wall of the conforming portion 111 matches the inner wall of the inner rotor 130, and there is a first gap 141 between the outer wall of the conforming portion 111 and the inner wall of the inner rotor 130, and the conduit cavity 112 is set through the conforming portion 111; the second spray disc cover 120 includes a jet port 121, and the jet port 121 Surrounding the outer periphery of the nozzle portion 132, the inner wall of the injection port 121 and the outer wall of the nozzle portion 132 constitute a Laval nozzle structure, and the Laval nozzle structure includes a second gap 142; a gas chamber 140 is formed between the first spray disc cover 110 and the second spray disc cover 120, and the gas chamber 140 is connected to the Laval nozzle structure; at least one group of turbine components is arranged in the gas chamber 140; the turbine component includes at least one turbine impeller 220, and the turbine impeller 220 is fixedly connected to the connecting portion 131, and turbine blades 221 are arranged in an array along the circumferential direction on the turbine impeller 220, and the turbine blades 221 are inclined; it also includes an air guide channel 113, and the air guide channel 113 includes an air inlet and an air outlet, and the air inlet is located on the first spray disc cover 110 or the second spray disc cover 120, and the air outlet is connected to the gas chamber 140, and the air outlet is located on the upper side, side or oblique upper side of the turbine impeller 220.

[0035] An aerosol nozzle of this embodiment utilizes the kinetic energy of the high-pressure gas input through the air guide channel 113 to drive the turbine impeller 220 to rotate at high speed, thereby driving the inner rotor 130 to rotate. Since one or more disturbance members 135, i.e., protrusions or grooves, are present on the outer wall of the inner rotor 130, the local intensity of the gas ejected from the second gap 142 is affected, thereby affecting the kinetic energy of the reflux gas at the outlet of the aerosol nozzle, so that the metal liquid film reaches a dynamically stable state, and the edges of the liquid film can be stably torn and broken into spherical metal powders, so that the particle size distribution of the obtained powder is narrowed, the satellite powder rate and the hollow rate are reduced, the yield rate is increased, and the preparation effect of the metal powder is improved.

[0036] An aerosol nozzle of this embodiment works as follows:

[0037] First, the guide tube is inserted into the duct cavity 112, molten metal liquid is introduced into the guide tube, and high-pressure gas is introduced into the atomizing nozzle from the gas guide channel 113. The high-pressure gas enters the gas chamber 140 from the gas guide channel 113 and impacts the turbine impeller 220. Part of the kinetic energy of the high-pressure gas will drive the turbine impeller 220 to rotate. Since the turbine impeller 220 is fixedly connected to the inner rotor 130, the connected inner rotor 130 rotates. Among them, the connecting portion 131 is used to realize the connection between the inner rotor 130 and the turbine impeller 220. It is conceivable that a bearing-like structure can be added between the inner rotor 130 and the first spray disc cover 110, especially between the inner rotor 130 and the conformal portion 111, to improve the rotation condition of the inner rotor 130.

[0038] It is conceivable that a group of turbine assemblies is a stage, a group of turbines is composed of at least one turbine impeller 220, and the turbine assembly can be provided with multiple stages to achieve a better mechanical energy conversion effect. Among them, the turbine blades 221 are tilted. Based on the setting of the air guide channel 113, the air outlet of the air guide channel 113 is located on the upper side, side side or oblique upper side of the turbine impeller 220. As a result, the high-pressure gas impacts the turbine blades 221 at a specific angle. The turbine blades 221 are subjected to pressure and can convert the kinetic energy of the high-pressure gas into mechanical energy, driving the inner rotor 130 to rotate. The setting of the turbine blades 221 also serves the purpose of uniforming the airflow and ensuring the stability of the airflow entering the Laval nozzle structure. It is conceivable that the setting of the first gap 141 is to prevent the inner rotor 130 from contacting the conformal portion 111 of the first spray disc cover 110, so as to avoid interfering with the high-speed rotation of the inner rotor 130.

[0039] In this embodiment, the structure of the air guide channel 113 is preferably a straight channel, and a curved channel shape is also feasible. The main body of the air guide channel 113 can be located only in the first spray disc cover 110 or the second spray disc cover 120, or it can pass through the interior of the first spray disc cover 110 and the second spray disc cover 120 at the same time. The air guide channel 113 only needs to ensure that it has an air inlet connected to the outside, and an air outlet from the upper side, side or oblique upper side of the turbine impeller 220 toward the turbine impeller 220. It can be imagined that it is sufficient to ensure that the high-pressure gas can blow the turbine impeller 220 from the upper side, side or oblique upper side of the turbine impeller 220.

[0040] The high-pressure gas then passes through the Laval nozzle structure and is ejected outward from the second gap 142, which serves as the gas outlet of the Laval nozzle structure. Because the outer wall of the nozzle portion 132 is provided with at least one disruptor 135, i.e., a protrusion or groove, extending to the end of the nozzle portion 132, the airflow ejected from the second gap 142 is disrupted by the protrusion or groove as the inner rotor 130 rotates at high speed, causing the airflow to continuously change. The second gap 142 is designed to prevent contact between the inner rotor 130 and the inner wall of the nozzle 121 of the second spray plate cover 120, thereby preventing interference with the high-speed rotation of the inner rotor 130.

[0041] The continuous change in airflow can be understood as follows: for example, if the outer wall of the inner rotor 130 is provided with a groove, and a point at the nozzle portion 132 is used as the observation point, a low pressure occurs at this location during one rotation cycle of the inner rotor 130. Then, as the inner rotor 130 rotates at high speed, a high-frequency pulsed airflow is formed at this location. Similarly, when the outer wall of the inner rotor 130 is provided with a protrusion extending to the end, from a certain point as the viewing angle, pressure changes will also occur, thereby forming a high-frequency pulsed airflow. It is conceivable that when different numbers of protrusions or grooves are provided, the above-mentioned pulse frequency will change, and the selection and adaptation should be made according to actual usage requirements. It is conceivable that the protrusion or groove on the outer wall of the nozzle portion 132 extends in the axial direction to the end of the nozzle portion 132. The above-mentioned effect can be achieved by using the protrusion or groove in the form of a straight extension or a curved extension.

[0042] After the airflow exits second gap 142, this rotating, high-frequency pulsed airflow creates a backflow, impacting the metal film and causing fluctuations on its lower surface. This fluctuation suppresses the fluctuations that form as the metal flow descends within the flow guide tube, maintaining the umbrella-shaped metal film in a dynamically stable state. This allows the edges of the metal film to be impacted by the gas blown out of second gap 142, resulting in a more stable production of metal powder of the same particle size. This narrows the particle size of the atomized powder, improves sphericity, and reduces the hollowness and number of satellite particles.

[0043] Example 2

[0044] Combined with attachment Figure 1-5 This embodiment proposes an aerosol nozzle, which can be improved on the basis of the above embodiment as follows: the turbine assembly also includes a turbine guide vane fan 210, which is fixedly connected to the first spray disc cover 110, and the turbine guide vane fan 210 is located on the side of the turbine impeller 220 close to the first spray disc cover 110; the turbine guide vane fan 210 includes a plurality of guide blades 211 arranged in an array along the circumferential direction, and the inclination direction of the guide blades 211 is opposite to that of the turbine blades 221.

[0045] In this embodiment, the turbine guide vane fan 210 serves to divide and organize the airflow. High-pressure gas enters the gas chamber 140 from the air guide channel 113 of the first spray disc cover 110. After passing through the turbine guide vane fan 210, the turbine guide vane fan 210 changes the speed and direction of the high-pressure gas. As can be appreciated, the turbine guide vane fan 210 is evenly distributed with guide blades 211, which divide the high-pressure airflow entering the gas chamber 140. The guide vanes 211 also have a diversion effect, directing the high-pressure gas toward the turbine blades 221 at a specific angle. This provides an appropriate airflow direction for the inlet of the working turbine impeller 220, allowing for high torque when passing through the turbine impeller 220. This also improves the operating conditions of the turbine impeller 220, enabling the turbine impeller 220 to achieve better mechanical energy conversion, improve the rotational stability of the turbine impeller 220, and thus improve the rotational stability of the inner rotor 130. This in turn improves the generation of high-frequency pulsed airflow at the second gap 142, ultimately improving the quality of metal powder preparation.

[0046] Example 3

[0047] Combined with attachment Figure 4 and 7 This embodiment proposes an aerosol nozzle, which can be improved on the basis of the above embodiment as follows: adjacent guide blades 211 form a first airflow channel 231 along the axial direction of the turbine guide vane fan 210, and adjacent turbine blades 221 form a second airflow channel 232 along the axial direction of the turbine impeller 220, and the first airflow channel 231 and the second airflow channel 232 are arranged to converge along the axial direction.

[0048] In this embodiment, the first air flow channel 231 and the second air flow channel 232 are arranged to converge in the axial direction, that is, the inlet area of ​​the first air flow channel 231 is larger than the outlet area of ​​the first air flow channel 231, and the inlet area of ​​the second air flow channel 232 is also larger than the outlet area of ​​the second air flow channel 232. On the one hand, the mechanical energy conversion effect of the turbine impeller 220 is improved, the rotation of the inner rotor 130 is improved, and ultimately the preparation quality of the metal powder is improved; on the other hand, the gas flowing out from the first air flow channel 231 and the second air flow channel 232 in the axial direction can expand, further playing a role in uniforming the air flow.

[0049] Example 4

[0050] Combined with attachment Figure 4 This embodiment proposes an aerosol nozzle, which can be improved as follows based on the above embodiment: the turbine blades 221 and the guide blades 211 are twisted clockwise or counterclockwise along the radial extension direction, and the twisting direction of the turbine blades 221 is opposite to that of the guide blades 211.

[0051] In the actual operation of the turbine blades 221 and the guide vanes 211, there are differences in their working conditions along the extension direction of the blades, that is, the blade height direction. Obviously, the linear velocity is the largest at the blade tip and the smallest at the blade root. Therefore, the interaction with the airflow at different positions is also different. Therefore, the turbine blades 221 and the guide vanes 211 of this embodiment have clockwise or counterclockwise twisting along the radial extension direction, so as to conform to the flow direction of the airflow and reduce the airflow loss at the blade root and the blade tip. Among them, the twisting direction of the turbine blades 221 and the guide vanes 211 is opposite, which is an adaptive adjustment based on the working principle of the single-stage turbine assembly. This embodiment can improve the rotation of the turbine impeller 220, thereby improving the preparation quality of the metal powder.

[0052] Example 5

[0053] Combined with attachment Figure 3-5 This embodiment proposes an aerosol nozzle, which can be improved on the basis of the above embodiment as follows: at least one first air vent 201 is provided on the connecting portion 131, at least one air flow cavity 203 connected to the outside is provided on the conformal portion 111, a second air vent 202 is provided on the air flow cavity 203, and the gas receiving cavity 140, the first air vent 201 are all connected to the first gap 141, the second air vent 202 and the air flow cavity 203.

[0054] In this embodiment, the first air vent 201 is provided to allow high-pressure gas to flow into the first gap 141. Similarly, the air flow chamber 203 is also used to allow high-pressure gas to flow into the first gap 141 through the second air vent 202, thereby forming an air layer. The air layer acts as an air bearing to prevent the inner rotor 130 from contacting the first spray disc cover 110, thereby avoiding interference with the high-speed rotation of the inner rotor 130.

[0055] Example 6

[0056] Combined with attachment Figure 3-5 This embodiment proposes an aerosol nozzle, which can be improved on the basis of the above embodiment as follows: the connecting portion 131 is provided with an annular groove 134 on the side close to the conformable portion 111, and the vent hole is provided through the annular groove 134.

[0057] In this embodiment, an annular groove 134 is further provided on the side of the connecting portion 131 close to the conformable portion 111. The surface formed by the annular groove 134 is used to accommodate the high-pressure gas flowing out of the first air vent 201 and the second air vent 202 to better form an air layer, thereby avoiding contact between the inner rotor 130 and the first spray disc cover 110, thereby avoiding interference with the high-speed rotation of the inner rotor 130.

[0058] Example 7

[0059] Combined with attachment Figure 4 and 5 , this embodiment proposes an aerosol nozzle, which can be improved as follows based on the above embodiment: at least one group of compressor components is arranged in the gas volume chamber 140, and the compressor component is located on the side of the turbine component close to the second spray disc cover 120; the compressor component includes a compressor impeller 240 and a compressor static impeller 250, the compressor impeller 240 is fixedly connected to the connecting portion 131, the compressor static impeller 250 is fixedly connected to the second spray disc cover 120, and the compressor impeller 240 is located between the compressor static impeller 250 and the turbine assembly; the compressor static impeller 250 includes a plurality of guide vanes 251 arranged in an array along the circumferential direction, the compressor impeller 240 includes a plurality of compression blades 241 arranged in an array along the circumferential direction, the guide vanes 251 are inclination direction opposite to that of the compression blades 241, and the inclination direction of the compression blades 241 is opposite to that of the turbine blades 221.

[0060] In this embodiment, the compressor impeller 240 is also connected to the inner rotor 130, and uses the power transmitted by the turbine impeller 220 to compress the gas that has lost some kinetic energy into the next stage. The compressor assembly of this embodiment plays a role in gas pressure compensation. The gas passing through the compressor impeller 240 enters the compressor static impeller 250, achieving a certain degree of gas pressure compensation, thereby compensating the air flow pressure entering the Laval nozzle structure and the air flow pressure ejected from the second gap 142, thereby improving the morphology of the umbrella-shaped liquid film and ultimately improving the preparation quality of the metal powder. Among them, the compressor static impeller 250 plays a role in uniforming the air flow, so that the kinetic energy of the gas is evenly distributed in the space. It is conceivable that the compressor assembly can be continuously provided with multiple stages to achieve better pressure compensation.

[0061] Example 8

[0062] Combined with attachment Figure 4 and 7 This embodiment proposes an aerosol nozzle, which can be improved on the basis of the above embodiment as follows: adjacent guide vanes 251 form a third air flow channel 233 along the axial direction of the compressor static impeller 250, and adjacent compressor blades 241 form a fourth air flow channel 234 along the axial direction of the compressor dynamic impeller 240, and the third air flow channel 233 and the fourth air flow channel 234 are arranged to diffuse along the axial direction.

[0063] The compressor assembly of this embodiment uses the principle of diffusion supercharging to increase the pressure. Therefore, the third air flow channel 233 and the fourth air flow channel 234 of this embodiment are diffusely arranged in the axial direction, so that the outlet area of ​​the third air flow channel 233 and the fourth air flow channel 234 is larger than the inlet area. In the process of gas flowing through the third air flow channel 233 and the fourth air flow channel 234, as the compressor impeller 240 continues to rotate at high speed, the pressure and speed of the high-pressure gas continue to change, thereby using the diffusion principle to increase the gas pressure.

[0064] Example 9

[0065] Combined with attachment Figure 4 This embodiment proposes an aerosol nozzle, which can be improved on the basis of the above embodiment as follows: the guide vanes 251 and the compressor blades 241 are twisted clockwise or counterclockwise along the radial extension direction, and the twisting directions of the guide vanes 251 and the compressor blades 241 are opposite.

[0066] In actual operation, the guide vanes 251 and compressor blades 241 exhibit differences in their operating conditions along the blade extension direction, i.e., along the blade height. Obviously, the linear velocity is greatest at the blade tip and smallest at the blade root. Consequently, the interaction with the airflow varies at different locations. Therefore, the guide vanes 251 and compressor blades 241 of this embodiment exhibit clockwise or counterclockwise twisting along their radial extension direction to align with the airflow and reduce airflow losses at the blade root and tip.

[0067] The torsion directions of the guide vanes 251 and the compressor blades 241 are opposite, which is an adaptive adjustment based on the working principle of a single-stage compressor assembly.

[0068] Example 10

[0069] Combined with attachment Figure 1-8 This embodiment proposes an aerosol nozzle, which can be improved as follows based on the above embodiment: the first spray disc cover 110, the second spray disc cover 120 and the inner rotor 130 are made of metal, or a metal and ceramic composite material, or ceramic material, or polymer material.

[0070] As you can imagine, the atomizing nozzle can handle different temperatures depending on the temperature of the metal liquid flow. For applications with low temperature requirements, polymer materials or steel materials such as stainless steel can be used. For relatively high temperature applications, titanium or even nickel-containing materials can be used. For applications with more stringent temperature requirements, ceramic materials or ceramic and metal composite materials can be used. When metal is used, due to its certain thermal conductivity, the high-pressure gas can be heated to further affect the tearing of the umbrella-shaped liquid film, thereby improving the preparation effect of the metal powder.

[0071] The above is a schematic description of the present invention and its embodiments, which is not restrictive. The drawings show only one embodiment of the present invention, and the actual structure is not limited thereto. Therefore, if a person skilled in the art is inspired by this and, without departing from the purpose of the present invention, designs a structure and embodiment similar to this technical solution without inventiveness, they shall fall within the scope of protection of the present invention.

Claims

1. An aerosol nozzle, characterized in that: The nozzle comprises a first spray disc cover, a second spray disc cover, and an inner rotor; the inner rotor is located between the first spray disc cover and the second spray disc cover; the inner rotor comprises a connecting portion and a nozzle portion, the connecting portion is located on a side of the nozzle portion close to the first spray disc cover; at least one disruptor is provided on the outer wall of the nozzle portion, the disruptor being a protrusion or a groove, the end of the disruptor extending to the end of the nozzle portion; The first spray disc cover includes a conformable portion and a conduit cavity, wherein an outer wall of the conformable portion matches an inner wall of the inner rotor, a first gap is formed between the outer wall of the conformable portion and the inner wall of the inner rotor, and the conduit cavity is provided through the conformable portion; The second spray plate cover includes a spray port, the spray port surrounds the outer periphery of the spray port portion, the inner wall of the spray port and the outer wall of the spray port portion form a Laval nozzle structure, and the Laval nozzle structure includes a second gap; A gas chamber is formed between the first spray disc cover and the second spray disc cover, and the gas chamber is communicated with the Laval nozzle structure; At least one turbine assembly is provided in the gas chamber; the turbine assembly includes at least one turbine impeller, the turbine impeller is fixedly connected to the connection portion, and turbine blades are arranged in an array along the circumferential direction on the turbine impeller, and the turbine blades are arranged obliquely; It also includes an air guide channel, which includes an air inlet and an air outlet. The air inlet is located on the first spray disc cover or the second spray disc cover, and the air outlet is connected to the gas chamber. The air outlet is located on the upper side, side side, or obliquely upper side of the turbine impeller.

2. An aerosol nozzle according to claim 1, characterized in that: The turbine assembly also includes a turbine guide vane fan, which is fixedly connected to the first spray disc cover and is located on the side of the turbine impeller close to the first spray disc cover; the turbine guide vane fan includes a plurality of guide blades arranged in an array along the circumferential direction, and the inclination direction of the guide blades is opposite to that of the turbine blades.

3. An aerosol nozzle according to claim 2, characterized in that: Adjacent guide vanes form a first airflow channel along the axial direction of the turbine guide vane fan, and adjacent turbine blades form a second airflow channel along the axial direction of the turbine impeller. The first airflow channel and the second airflow channel are convergently arranged along the axial direction.

4. The aerosol nozzle according to claim 2, characterized in that: The turbine blades and the guide blades are twisted clockwise or counterclockwise along the radial extension direction, and the twisting directions of the turbine blades and the guide blades are opposite.

5. The aerosol nozzle according to claim 1, characterized in that: At least one first vent is provided on the connecting portion, at least one air flow cavity connected to the outside is provided on the conformal portion, a second vent is provided on the air flow cavity, and the gas storage cavity, the first vent and the first gap, the second vent and the air flow cavity are all connected.

6. The aerosol nozzle according to claim 5, characterized in that: The connecting portion is provided with an annular groove on one side close to the conformable portion, and the vent hole is provided through the annular groove.

7. The aerosol nozzle according to claim 1, characterized in that: At least one compressor assembly is provided in the gas chamber, and the compressor assembly is located on a side of the turbine assembly close to the second spray disc cover; The compressor assembly includes a pneumatic impeller and a static impeller, the pneumatic impeller is fixedly connected to the connecting portion, the static impeller is fixedly connected to the second spray disc cover, and the pneumatic impeller is located between the static impeller and the turbine assembly; The compressor stator wheel includes a plurality of guide vanes arranged in an array along the circumferential direction, and the compressor dynamic impeller includes a plurality of compression blades arranged in an array along the circumferential direction. The inclination direction of the guide vanes is opposite to that of the compression blades, and the inclination direction of the compression blades is opposite to that of the turbine blades.

8. The aerosol nozzle according to claim 7, characterized in that: Adjacent guide vanes form a third airflow channel along the axial direction of the compressor impeller, and adjacent compressor blades form a fourth airflow channel along the axial direction of the compressor impeller. The third airflow channel and the fourth airflow channel are diffusely arranged along the axial direction.

9. The aerosol nozzle according to claim 7, characterized in that: The guide vanes and the compressor blades are twisted clockwise or counterclockwise along the radial extension direction, and the twisting directions of the guide vanes and the compressor blades are opposite.

10. The aerosol nozzle according to claim 1, characterized in that: The first spray disc cover, the second spray disc cover and the inner rotor are made of metal, or a metal and ceramic composite material, or a ceramic material, or a polymer material.

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