Coaxial reverse double-atomization flame synthesis unit
Through the design of the coaxial reverse dual atomization flame synthesis unit, the problems of the traditional parallel atomization flame synthesis burner are solved, and the effect of efficient synthesis of nano powder materials is achieved.
Patent Information
- Application Number
- CN202411693001.9
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-11-25
- Publication Date
- 2025-02-28
AI Technical Summary
Traditional parallel atomized flame synthesis burners have problems such as large space occupation, not compact structure and complex gas circuit design, making it difficult to efficiently synthesize nano powder materials.
The coaxial reverse double atomization flame synthesis unit is adopted, through the design of the atomization nozzle assembly and the cyclone air assembly, a burner simultaneously constructs a double anti-precursor atomization air flow along the axial direction, forming a compact structure to facilitate arrangement in the cavity.
The construction of two atomized synthetic flames in a single burner is achieved, which improves the synthetic yield of nano powder materials, and has a compact structure and reduced footprint.
Smart Images
Figure CN119524786A_ABST
Abstract
Description
Technical Field
[0001] The invention belongs to the technical field of preparing nano powder materials by adopting an atomizing flame synthesis method, and in particular relates to a coaxial reverse double atomizing flame synthesis unit. Background Art
[0002] At present, the commonly used methods for preparing nanopowder materials in the world mainly include solid phase method, vapor phase deposition method, liquid phase precipitation method, sol-gel method, etc., but these methods also have corresponding bottlenecks and defects. For example, when using the solid phase method to prepare nanopowder materials, the particle size is often too large, the precision requirements of the equipment are also high, and it is easy to be uneven when mixing multiple materials.
[0003] In addition, since traditional processes such as solid-phase method and liquid-phase method have been developed for many years, there is not much room for breakthroughs. In contrast, the flame method is a technology with a strong "platform" attribute, which can flexibly produce different types of nano-powder materials and ensure the same product performance at large-scale production and laboratory levels. For a single burner, a single atomizing flame is usually organized on one side of the atomizing flame synthesis burner. When the synthesis amount of nano-powder materials needs to be greatly increased, it is often necessary to connect multiple atomizing flame synthesis burner groups in parallel to simultaneously carry out the synthesis of nano-powder materials. However, the above parallel process has typical problems:
[0004] 1) It is complicated to connect multiple atomizing synthetic burners in parallel, which requires a larger floor space and cavity for arrangement, and the overall structure is not compact enough;
[0005] 2) When multiple burners are connected in parallel, more complex gas and precursor pipeline organization and design are often required.
[0006] Therefore, further improvements are made to the above problems. Summary of the invention
[0007] The main purpose of the present invention is to provide a coaxial reverse double atomization flame synthesis unit, which integrates the traditional burner that forms a single atomization synthetic flame, and can construct a double atomization synthetic flame in the opposite axial direction of the burner. It has the advantages of a single burner constructing two atomization synthetic flames at the same time, a compact structure, and is easy to arrange in a cavity.
[0008] In order to achieve the above object, the present invention provides a coaxial reverse double atomization flame synthesis unit, comprising an atomization nozzle assembly (1) and a swirl gas assembly (2), wherein:
[0009] For the atomizing nozzle assembly (1), the liquid precursor and the shearing gas flow are respectively introduced through the precursor flow inlet pipe (16) and the shearing gas flow inlet pipe (17), so that the liquid precursor is ejected as a high-speed direct current jet at the two end outlets of the precursor channel (14), and the shearing gas flow is rotated at a high speed in the rotating flow intensification chamber (12), and finally flows out from the middle inflow area to the outlet areas at the two ends at a high speed, and after meeting the liquid precursor jet located in the central area of the high-speed rotating gas flow, a shearing and crushing effect is applied to the liquid precursor, thereby achieving instantaneous atomization of the liquid precursor;
[0010] For the swirl gas assembly (2), fuel gas and air flow are respectively introduced through the fuel gas inlet pipe (26) and the air inlet pipe (27), so that the fuel gas rotates at a high speed inside the annular fuel gas chamber, and under the swirl guiding action of the inner guide plates (25) located at both ends, it flows out from the upper and lower ends of the inner cylinder (23) in a high-speed rotation, and the air flow rotates at a high speed inside the annular air flow chamber, and under the swirl guiding action of the outer guide plates (24) located at both ends, it flows out from the upper and lower ends of the outer cylinder (21) in a high-speed rotation, thereby forming two coaxially oppositely distributed atomized synthesis flames on both sides at the same time, so as to synthesize nano-powder materials for the atomized liquid precursors at both ends.
[0011] As a further preferred technical solution of the above technical solution, the atomizing nozzle assembly (1) comprises a nozzle housing (11), a swirl flow intensification chamber (12), a nozzle center body (13), a precursor channel (14), a connecting hole (15), a precursor flow inlet pipe (16), and a shear gas inlet pipe (17), wherein:
[0012] The middle section of the nozzle shell (11) is a straight cylinder structure, and two cones are coaxially connected and connected at both ends of the straight cylinder, and the diameters of the cones at both ends gradually decrease as the distance from the straight cylinder increases; the middle area of the nozzle center body (13) is a cylinder, and two cones are coaxially connected and connected at both ends of the middle cylinder, and the diameters of the cones at both ends gradually decrease as the distance from the middle cylinder increases; the nozzle center body (13) is coaxially arranged inside the nozzle shell (11), so that the rotating flow intensification chamber (12) is formed between the outer wall surface of the nozzle center body (13) and the inner wall surface of the nozzle shell (11), and the rotating flow intensification chamber (12) is used to form a high-speed rotating airflow to cause the liquid precursor to be sheared and broken to form atomized droplets; inside the nozzle center body (13), a precursor channel (14) is coaxially opened, and the precursor channel (14) is used to circulate the liquid precursor.
[0013] As a further preferred technical solution of the above technical solution, the precursor flow inlet pipe (16) is a long straight tubular structure, one end of which passes through the nozzle housing (11) and the rotational flow intensification chamber (12), and the precursor flow inlet pipe (16) is vertically fixedly connected to the nozzle center body (13) at the middle position along the axial direction of the nozzle center body (13), and the connecting hole (15) is opened at the connection point, and the connection hole (15) is set to connect the precursor flow inlet pipe (16) with the internal channel of the nozzle center body (13);
[0014] The shear gas inlet pipe (17) is a tubular structure composed of a circular arc segment and a straight pipe segment, wherein the outlet of the circular arc segment is tangentially connected and communicated with the outer wall surface of the nozzle housing (11), and the straight pipe segment is arranged adjacent to the precursor flow inlet pipe (16) and located on the same plane.
[0015] As a further preferred technical solution of the above technical solution, the cyclone gas assembly (2) comprises an outer cylinder (21), a middle spacer ring (22), an inner cylinder (23), an outer guide plate (24), an inner guide plate (25), a fuel gas inlet pipe (26), an air inlet pipe (27), a filling body (28), an outer wedge-shaped guide body (29), and an inner wedge-shaped guide body (210), wherein:
[0016] The middle part of the outer cylinder (21) is a cylindrical cylinder. Two first cone cylinders are connected to both sides of the outer cylinder (21). The large diameter ends of the two first cone cylinders are coaxially connected and communicated with the two ends of the middle cylindrical cylinder, and the small diameter ends of the two first cone cylinders are coaxially connected and communicated with the two first diameter cylinders.
[0017] The middle spacer ring (22) is a cylindrical barrel structure;
[0018] The middle part of the inner cylinder (23) is a cylindrical cylinder. Two second cone cylinders are connected to both sides of the inner cylinder (23). The small diameter ends of the two second cone cylinders are coaxially connected and communicated with the two ends of the middle cylindrical cylinder, and the large diameter ends of the two second cone cylinders are coaxially connected and communicated with the two second diameter cylinders.
[0019] The inner cylinder (23), the middle spacer ring (22), and the outer cylinder (21) are coaxially sleeved and arranged in sequence from the inside to the outside.
[0020] As a further preferred technical solution of the above technical solution, an annular air flow chamber is formed between the outer cylinder (21) and the middle spacer ring (22); inside the air flow chamber, two outer guide plates (24) are arranged adjacent to the two end cones in the outer cylinder (21) respectively along the circumferential direction of the air flow chamber; the outer guide plates (24) are a plurality of plates arranged at a certain angle to the axial direction of the outer cylinder (21); the two guide plates arranged adjacent to the two end cones in the outer cylinder (21) are arranged symmetrically in an upper and lower manner, that is, the angles between the upper and lower outer guide plates (24) and the axial direction of the outer cylinder (21) are equal in size and opposite in direction; the arrangement of the two outer guide plates (24) guides the air flow flowing into the air flow chamber into a rotating flow with a certain tangential and axial speed, and simultaneously forms two oppositely arranged high-speed rotating air flows at the upper and lower end outlets of the outer cylinder (21);
[0021] An annular fuel gas chamber is formed between the middle spacer ring (22) and the inner cylinder (23); inside the fuel gas chamber, adjacent to the two end cones in the inner cylinder (23), two inner guide plates (25) are arranged respectively along the circumferential direction of the fuel gas chamber; the inner guide plates (25) are a plurality of plates arranged at a certain angle to the axial direction of the inner cylinder (23); the two guide plates arranged adjacent to the two end cones in the inner cylinder (23) are arranged symmetrically in an upper and lower manner, that is, the angles between the upper and lower inner guide plates (25) and the axial direction of the inner cylinder (23) are equal in size and opposite in direction; the arrangement of the two inner guide plates (25) guides the fuel gas flow flowing into the fuel gas chamber into a rotating flow with a certain tangential and axial speed, and simultaneously forms two oppositely arranged high-speed rotating fuel gas flows at the upper and lower end outlets of the inner cylinder (23).
[0022] As a further preferred technical solution of the above technical solution, the fuel gas inlet pipe (26) is a tubular structure composed of a circular arc segment and a straight pipe segment, wherein the circular arc segment passes through the outer cylinder (21) and is tangentially connected and communicated with the outer wall surface of the middle spacer ring (22), and the straight pipe segment is arranged adjacent to the straight pipe segment in the shear gas inlet pipe (17) and is located on the same plane;
[0023] The air inlet pipe (27) is a tubular structure composed of a circular arc segment and a straight pipe segment, wherein the circular arc segment is tangentially connected and communicated with the outer wall surface of the outer cylinder (21), and the straight pipe segment is arranged adjacent to the straight pipe segment in the fuel gas inlet pipe (26) and is located on the same plane.
[0024] As a further preferred technical solution of the above technical solution, the atomizing nozzle assembly (1) is coaxially arranged at the center of the inner cylinder (23), and the inlet ends of the precursor flow inlet pipe (16) and the shear gas inlet pipe (17) pass through the outer cylinder (21), the middle spacer ring (22) and the middle area of the inner cylinder (23) along the axial direction in sequence;
[0025] The air inlet pipe (27), the fuel gas inlet pipe (26), the shear gas inlet pipe (17), and the precursor flow inlet pipe (16) are arranged as a whole on the middle plane of the cyclone gas component (2) along the axial direction, and the straight pipe sections in the air inlet pipe (27), the fuel gas inlet pipe (26), the shear gas inlet pipe (17), and the precursor flow inlet pipe (16) are arranged closely from left to right in sequence.
[0026] As a further preferred technical solution of the above technical solution, the filling body (28) is filled in the middle area between the outer cylinder (21) and the middle spacer ring (22), and between the fuel gas inlet pipe (26) and the shear gas inlet pipe (17). The purpose of providing the filling body (28) is to stabilize the airflow in this area, thereby stabilizing the overall vortex field.
[0027] As a further preferred technical solution of the above technical solution, the outer wedge-shaped guide body (29) is provided in the middle area between the outer cylinder (21) and the middle spacer ring (22), and is located in the right area of the precursor flow inlet pipe (16), and is connected to the outer wall surface of the precursor flow inlet pipe (16); the outer wedge-shaped guide body (29) is a wedge-shaped structure, which is used to prevent the flow field from being disturbed due to the hard collision between the airflow and the outer wall of the precursor flow inlet pipe (16), thereby stabilizing the overall vortex field;
[0028] The inner wedge-shaped guide body (210) is arranged in the middle area between the inner cylinder (23) and the middle spacer ring (22), and is located in the right area of the precursor flow inlet pipe (16), and is connected to the outer wall surface of the precursor flow inlet pipe (16); the inner wedge-shaped guide body (210) is a wedge-shaped structure, which is used to prevent the flow field from being disturbed due to the hard collision between the airflow and the outer wall of the precursor flow inlet pipe (16), thereby stabilizing the overall vortex field.
[0029] The beneficial effects of the present invention are:
[0030] (1) Through an atomizing flame synthesis burner, it is possible to simultaneously construct an axially oriented double-reverse precursor atomizing gas flow;
[0031] (2) The present invention constructs reverse coaxial atomizing synthetic flames on both sides of the burner along the axial direction, thereby achieving two atomizing synthetic flames through one burner, which can increase the output of atomizing flame synthesized nano-powder materials;
[0032] (3) The burner has a compact structure, which facilitates integration with the interior of the combustion chamber, reduces floor space, and increases the compactness of the equipment. BRIEF DESCRIPTION OF THE DRAWINGS
[0033] Figure 1 It is a front view of the coaxial reverse double atomization flame synthesis unit of the present invention.
[0034] Figure 2 It is a bottom view of the coaxial reverse double atomization flame synthesis unit of the present invention.
[0035] Figure 3 It is the A-direction view of the coaxial reverse double atomization flame synthesis unit of the present invention.
[0036] Figure 4 It is the B-direction view of the coaxial reverse double atomization flame synthesis unit of the present invention.
[0037] Figure 5 It is a cross-sectional view of the AA section of the coaxial reverse double atomization flame synthesis unit of the present invention.
[0038] Figure 6 It is a BB cross-sectional view of the coaxial reverse double atomization flame synthesis unit of the present invention.
[0039] Figure 7 It is a plan view of the fuel gas annular cavity of the present invention.
[0040] Figure 8 It is a plan view of the air flow annular cavity of the present invention.
[0041] Fig. 9 It is a schematic diagram of the coaxial reverse double atomization flame distribution of the coaxial reverse double atomization flame synthesis unit of the present invention.
[0042] The reference numerals include: 1-atomizing nozzle assembly; 11-nozzle housing; 12-swirl flow intensification chamber; 13-nozzle center body; 14-precursor channel; 15-connecting hole; 16-precursor flow inlet pipe; 17-shear gas inlet pipe; 2-swirl gas assembly; 21-outer cylinder; 22-middle spacer ring; 23-inner cylinder; 24-outer guide plate; 25-inner guide plate; 26-fuel gas inlet pipe; 27-air inlet pipe; 28-filling body; 29-outer wedge-shaped guide body; 210-inner wedge-shaped guide body. DETAILED DESCRIPTION
[0043] The following description is used to disclose the present invention so that those skilled in the art can implement the present invention. The preferred embodiments described below are only examples, and those skilled in the art can think of other obvious variations. The basic principles of the present invention defined in the following description can be applied to other embodiments, variations, improvements, equivalents, and other technical solutions that do not deviate from the spirit and scope of the present invention.
[0044] In the preferred embodiment of the present invention, those skilled in the art should note that the liquid precursors and the like involved in the present invention may be regarded as prior art.
[0045] Preferred embodiments.
[0046] like Figure 1-9 As shown, the present invention discloses a coaxial reverse double atomization flame synthesis unit, comprising an atomization nozzle assembly (1) and a swirl gas assembly (2), wherein:
[0047] For the atomizing nozzle assembly (1), the liquid precursor and the shearing gas flow are respectively introduced through the precursor flow inlet pipe (16) and the shearing gas inlet pipe (17), so that the liquid precursor flows into the interior of the precursor channel (14) through the connecting hole (15), and finally ejects at the two end outlets of the precursor channel (14) as a high-speed direct current jet (forming a liquid precursor jet), and the shearing gas flow (air or other types of fuel) flows into the interior of the rotating flow intensification chamber (12) at a high speed along the tangential direction, rotates at a high speed in the rotating flow intensification chamber (12), and finally flows out from the middle inlet area to the outlet areas at the two ends at a high speed, and after meeting the liquid precursor jet located in the central area of the high-speed rotating gas flow, a shearing and crushing effect is applied to the liquid precursor, thereby achieving instantaneous atomization of the liquid precursor (breaking into fine droplets);
[0048] For the swirl gas assembly (2), the fuel gas and air flow are respectively introduced into the fuel gas inlet pipe (26) and the air inlet pipe (27), so that the fuel gas flows into the annular fuel gas chamber located between the inner cylinder (23) and the middle spacer ring (22) at a high speed along the tangential direction, rotates at a high speed inside the annular fuel gas chamber, and flows out from the upper and lower ends of the inner cylinder (23) at a high speed under the swirl guiding action of the inner guide plates (25) located at both ends, and at the same time, the air flow flows into the annular air flow chamber located between the outer cylinder (21) and the middle spacer ring (22) at a high speed along the tangential direction, rotates at a high speed inside the annular air flow chamber, and flows out from the upper and lower ends of the outer cylinder (21) at a high speed under the swirl guiding action of the outer guide plates (24) located at both ends, thereby forming two atomized synthetic flames coaxially and oppositely distributed on both sides at the same time, so as to synthesize nano-powder materials for the atomized liquid precursors at both ends. Through the flow organization mode of the above-mentioned airflow, on both sides of the coaxial reverse double atomizing flame synthesis unit described in the present invention, precursor atomized droplets, high-speed rotating atomizing shear airflow, high-speed rotating fuel gas and high-speed rotating air flow distributed in sequence from the inside to the outside are respectively constructed, so that two atomizing synthesis flames with coaxial reverse distribution can be formed on both sides of the coaxial reverse double atomizing flame synthesis unit at the same time, thereby improving the synthesis output of nano-powder materials of a single atomizing synthesis burner.
[0049] Specifically, if Figure 1 , Figure 5 and Figure 6 As shown, the atomizing nozzle assembly (1) comprises a nozzle housing (11), a swirl flow intensification chamber (12), a nozzle center body (13), a precursor channel (14), a connecting hole (15), a precursor flow inlet pipe (16), and a shear gas inlet pipe (17), wherein:
[0050] The middle section of the nozzle shell (11) is a straight cylinder structure, and two cones are coaxially connected and connected at both ends of the straight cylinder, and the diameters of the cones at both ends gradually decrease as the distance from the straight cylinder increases; the middle area of the nozzle center body (13) is a cylinder, and two cones are coaxially connected and connected at both ends of the middle cylinder, and the diameters of the cones at both ends gradually decrease as the distance from the middle cylinder increases; the nozzle center body (13) is coaxially arranged inside the nozzle shell (11), so that the rotating flow intensification chamber (12) is formed between the outer wall surface of the nozzle center body (13) and the inner wall surface of the nozzle shell (11), and the rotating flow intensification chamber (12) is used to form a high-speed rotating airflow to cause the liquid precursor to be sheared and broken to form atomized droplets; inside the nozzle center body (13), a precursor channel (14) is coaxially opened, and the precursor channel (14) is used to circulate the liquid precursor.
[0051] More specifically, the precursor flow inlet pipe (16) is a long straight tubular structure, one end of which passes through the nozzle housing (11) and the swirl flow intensification chamber (12), and the precursor flow inlet pipe (16) is vertically fixedly connected to the nozzle center body (13) at the middle position along the axial direction of the nozzle center body (13), and the connecting hole (15) is opened at the connection point, and the connection hole (15) is set to connect the precursor flow inlet pipe (16) with the internal channel of the nozzle center body (13);
[0052] The shear gas inlet pipe (17) is a tubular structure composed of a circular arc segment and a straight pipe segment, wherein the outlet of the circular arc segment is tangentially connected and communicated with the outer wall surface of the nozzle housing (11), and the straight pipe segment is arranged adjacent to the precursor flow inlet pipe (16) and located on the same plane.
[0053] Furthermore, if Figures 1 to 8 As shown, the cyclone gas assembly (2) comprises an outer cylinder (21), a middle spacer ring (22), an inner cylinder (23), an outer guide plate (24), an inner guide plate (25), a fuel gas inlet pipe (26), an air inlet pipe (27), a filling body (28), an outer wedge-shaped guide body (29), and an inner wedge-shaped guide body (210), wherein:
[0054] like Figure 6 As shown, the middle part of the outer cylinder (21) is a cylindrical cylinder, and two first cone cylinders are connected to both sides of the outer cylinder (21), respectively. The large diameter ends of the two first cone cylinders are coaxially connected and communicated with the two ends of the middle cylindrical cylinder, respectively, and the small diameter ends of the two first cone cylinders are coaxially connected and communicated with the two (small) first diameter cylinders, respectively;
[0055] like Figure 6 As shown, the middle spacer ring (22) is a cylindrical barrel structure;
[0056] like Figure 6 As shown, the middle part of the inner cylinder (23) is a cylindrical cylinder, and two second cone cylinders are connected to both sides of the inner cylinder (23), respectively. The small diameter ends of the two second cone cylinders are coaxially connected and communicated with the two ends of the middle cylindrical cylinder, respectively, and the large diameter ends of the two second cone cylinders are coaxially connected and communicated with the two (large) second diameter cylinders, respectively;
[0057] like Figure 6 As shown, the inner cylinder (23), the middle spacer ring (22), and the outer cylinder (21) are coaxially sleeved and arranged in sequence from the inside to the outside.
[0058] Furthermore, if Figures 1 to 8As shown, an annular air flow chamber is formed between the outer cylinder (21) and the middle spacer ring (22); inside the air flow chamber, two outer guide plates (24) are arranged adjacent to the two end cones in the outer cylinder (21) respectively along the circumferential direction of the air flow chamber; the outer guide plates (24) are a plurality of plates arranged at a certain angle to the axial direction of the outer cylinder (21); the two guide plates arranged adjacent to the two end cones in the outer cylinder (21) are arranged symmetrically in an upper and lower manner, that is, the angles between the upper and lower outer guide plates (24) and the axial direction of the outer cylinder (21) are equal in size and opposite in direction; the arrangement of the two outer guide plates (24) guides the air flow flowing into the air flow chamber into a rotating flow with a certain tangential and axial speed, and simultaneously forms two oppositely arranged high-speed rotating air flows at the upper and lower end outlets of the outer cylinder (21);
[0059] An annular fuel gas chamber is formed between the middle spacer ring (22) and the inner cylinder (23); inside the fuel gas chamber, adjacent to the two end cones in the inner cylinder (23), two inner guide plates (25) are arranged respectively along the circumferential direction of the fuel gas chamber; the inner guide plates (25) are a plurality of plates arranged at a certain angle to the axial direction of the inner cylinder (23); the two guide plates arranged adjacent to the two end cones in the inner cylinder (23) are arranged symmetrically in an upper and lower manner, that is, the angles between the upper and lower inner guide plates (25) and the axial direction of the inner cylinder (23) are equal in size and opposite in direction; the arrangement of the two inner guide plates (25) guides the fuel gas flow flowing into the fuel gas chamber into a rotating flow with a certain tangential and axial speed, and simultaneously forms two oppositely arranged high-speed rotating fuel gas flows at the upper and lower end outlets of the inner cylinder (23).
[0060] Preferably, if Figure 1 , Figure 2 and Figure 5 As shown, the fuel gas inlet pipe (26) is a tubular structure composed of a circular arc segment and a straight pipe segment, wherein the circular arc segment passes through the outer cylinder (21) and is tangentially connected and communicated with the outer wall surface of the middle spacer ring (22), and the straight pipe segment is arranged adjacent to the straight pipe segment in the shear gas inlet pipe (17) and is located on the same plane;
[0061] The air inlet pipe (27) is a tubular structure composed of a circular arc segment and a straight pipe segment, wherein the circular arc segment is tangentially connected and communicated with the outer wall surface of the outer cylinder (21), and the straight pipe segment is arranged adjacent to the straight pipe segment in the fuel gas inlet pipe (26) and is located on the same plane.
[0062] Preferably, if Figure 5As shown, the atomizing nozzle assembly (1) is coaxially arranged at the center of the inner cylinder (23), and the inlet ends of the precursor flow inlet pipe (16) and the shear gas inlet pipe (17) sequentially pass through the outer cylinder (21), the middle spacer ring (22) and the middle area of the inner cylinder (23) along the axial direction;
[0063] like Figure 1 , Figure 2 and Figure 5 As shown, the air inlet pipe (27), the fuel gas inlet pipe (26), the shear gas inlet pipe (17), and the precursor flow inlet pipe (16) are arranged as a whole on the middle plane of the swirl gas component (2) along the axial direction, and the straight pipe sections in the air inlet pipe (27), the fuel gas inlet pipe (26), the shear gas inlet pipe (17), and the precursor flow inlet pipe (16) are arranged closely from left to right in sequence.
[0064] Preferably, if Figure 5 As shown, the filling body (28) is filled in the middle area between the outer cylinder (21) and the middle spacer ring (22), and between the fuel gas inlet pipe (26) and the shear gas inlet pipe (17). The purpose of providing the filling body (28) is to stabilize the airflow in this area, thereby stabilizing the overall vortex field.
[0065] Preferably, if Figure 5 and Figure 8 As shown, the outer wedge-shaped guide body (29) is provided in the middle area between the outer cylinder (21) and the middle spacer ring (22), and is located in the right area of the precursor flow inlet pipe (16), and is connected to the outer wall surface of the precursor flow inlet pipe (16); the outer wedge-shaped guide body (29) is a wedge-shaped structure, which is used to prevent the flow field from being disturbed due to the hard collision between the airflow and the outer wall of the precursor flow inlet pipe (16), thereby stabilizing the overall swirl field;
[0066] like Figure 5 and Figure 7 As shown, the inner wedge-shaped guide body (210) is arranged in the middle area between the inner cylinder (23) and the middle spacer ring (22), and is located in the right area of the precursor flow inlet pipe (16), and is connected to the outer wall surface of the precursor flow inlet pipe (16); the inner wedge-shaped guide body (210) is a wedge-shaped structure, which is used to prevent the flow field turbulence caused by the hard collision of the airflow directly with the outer wall of the precursor flow inlet pipe (16), thereby stabilizing the overall vortex field.
[0067] It is worth mentioning that the technical features such as liquid precursors involved in the patent application of this invention should be regarded as prior art. The specific structure, working principle and possible control method and spatial arrangement method of these technical features can be selected according to the conventional methods in the field and should not be regarded as the inventive point of the patent of this invention. The patent of this invention will not be further elaborated.
[0068] For those skilled in the art, it is still possible to modify the technical solutions described in the aforementioned embodiments, or to make equivalent substitutions for some of the technical features therein. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.
Claims
1. A coaxial reverse double atomization flame synthesis unit, characterized in that: It comprises an atomizing nozzle assembly (1) and a cyclone gas assembly (2), wherein: For the atomizing nozzle assembly (1), the liquid precursor and the shearing gas flow are respectively introduced through the precursor flow inlet pipe (16) and the shearing gas flow inlet pipe (17), so that the liquid precursor is ejected as a high-speed direct current jet at the two end outlets of the precursor channel (14), and the shearing gas flow is rotated at a high speed in the rotating flow intensification chamber (12), and finally flows out from the middle inflow area to the outlet areas at the two ends at a high speed, and after meeting the liquid precursor jet located in the central area of the high-speed rotating gas flow, a shearing and crushing effect is applied to the liquid precursor, thereby achieving instantaneous atomization of the liquid precursor; For the swirl gas assembly (2), fuel gas and air flow are respectively introduced through the fuel gas inlet pipe (26) and the air inlet pipe (27), so that the fuel gas rotates at a high speed inside the annular fuel gas chamber, and under the swirl guiding action of the inner guide plates (25) located at both ends, it flows out from the upper and lower ends of the inner cylinder (23) in a high-speed rotation, and the air flow rotates at a high speed inside the annular air flow chamber, and under the swirl guiding action of the outer guide plates (24) located at both ends, it flows out from the upper and lower ends of the outer cylinder (21) in a high-speed rotation, thereby forming two coaxially oppositely distributed atomized synthesis flames on both sides at the same time, so as to synthesize nano-powder materials for the atomized liquid precursors at both ends.
2. A coaxial reverse double atomization flame synthesis unit according to claim 1, characterized in that: The atomizing nozzle assembly (1) comprises a nozzle housing (11), a swirl flow intensification chamber (12), a nozzle center body (13), a precursor channel (14), a connecting hole (15), a precursor flow inlet pipe (16), and a shear gas inlet pipe (17), wherein: The middle section of the nozzle shell (11) is a straight cylinder structure, and two cones are coaxially connected and connected at both ends of the straight cylinder, and the diameters of the cones at both ends gradually decrease as the distance from the straight cylinder increases; the middle area of the nozzle center body (13) is a cylinder, and two cones are coaxially connected and connected at both ends of the middle cylinder, and the diameters of the cones at both ends gradually decrease as the distance from the middle cylinder increases; the nozzle center body (13) is coaxially arranged inside the nozzle shell (11), so that the rotating flow intensification chamber (12) is formed between the outer wall surface of the nozzle center body (13) and the inner wall surface of the nozzle shell (11), and the rotating flow intensification chamber (12) is used to form a high-speed rotating airflow to cause the liquid precursor to be sheared and broken to form atomized droplets; inside the nozzle center body (13), a precursor channel (14) is coaxially opened, and the precursor channel (14) is used to circulate the liquid precursor.
3. A coaxial reverse double atomization flame synthesis unit according to claim 2, characterized in that: The precursor flow inlet pipe (16) is a long straight tubular structure, one end of which passes through the nozzle housing (11) and the swirl flow intensification chamber (12). The precursor flow inlet pipe (16) is vertically fixedly connected to the nozzle center body (13) at the middle position of the nozzle center body (13) along the axial direction, and the connecting hole (15) is opened at the connection point. The connection hole (15) is set to connect the precursor flow inlet pipe (16) with the internal channel of the nozzle center body (13); The shear gas inlet pipe (17) is a tubular structure composed of a circular arc segment and a straight pipe segment, wherein the outlet of the circular arc segment is tangentially connected and communicated with the outer wall surface of the nozzle housing (11), and the straight pipe segment is arranged adjacent to the precursor flow inlet pipe (16) and located on the same plane.
4. A coaxial reverse double atomization flame synthesis unit according to claim 3, characterized in that: The cyclone gas assembly (2) comprises an outer cylinder (21), a middle spacer ring (22), an inner cylinder (23), an outer guide plate (24), an inner guide plate (25), a fuel gas inlet pipe (26), an air inlet pipe (27), a filling body (28), an outer wedge-shaped guide body (29), and an inner wedge-shaped guide body (210), wherein: The middle part of the outer cylinder (21) is a cylindrical cylinder. Two first cone cylinders are connected to both sides of the outer cylinder (21). The large diameter ends of the two first cone cylinders are coaxially connected and communicated with the two ends of the middle cylindrical cylinder, and the small diameter ends of the two first cone cylinders are coaxially connected and communicated with the two first diameter cylinders. The middle spacer ring (22) is a cylindrical barrel structure; The middle part of the inner cylinder (23) is a cylindrical cylinder. Two second cone cylinders are connected to both sides of the inner cylinder (23). The small diameter ends of the two second cone cylinders are coaxially connected and communicated with the two ends of the middle cylindrical cylinder, and the large diameter ends of the two second cone cylinders are coaxially connected and communicated with the two second diameter cylinders. The inner cylinder (23), the middle spacer ring (22), and the outer cylinder (21) are coaxially sleeved and arranged in sequence from the inside to the outside.
5. A coaxial reverse double atomization flame synthesis unit according to claim 4, characterized in that: An annular air flow chamber is formed between the outer cylinder (21) and the middle spacer ring (22); inside the air flow chamber, two outer guide plates (24) are arranged adjacent to the two end cones in the outer cylinder (21) and respectively along the circumferential direction of the air flow chamber; the outer guide plates (24) are a plurality of plates arranged at a certain angle to the axial direction of the outer cylinder (21); the two guide plates arranged adjacent to the two end cones in the outer cylinder (21) are arranged symmetrically in an upper and lower manner, that is, the angles between the upper and lower outer guide plates (24) and the axial direction of the outer cylinder (21) are equal in size and opposite in direction; the arrangement of the two outer guide plates (24) guides the air flow flowing into the air flow chamber into a rotating flow with a certain tangential and axial speed, and simultaneously forms two oppositely arranged high-speed rotating air flows at the upper and lower end outlets of the outer cylinder (21); An annular fuel gas chamber is formed between the middle spacer ring (22) and the inner cylinder (23); inside the fuel gas chamber, adjacent to the two end cones in the inner cylinder (23), two inner guide plates (25) are arranged respectively along the circumferential direction of the fuel gas chamber; the inner guide plates (25) are a plurality of plates arranged at a certain angle to the axial direction of the inner cylinder (23); the two guide plates arranged adjacent to the two end cones in the inner cylinder (23) are arranged symmetrically in an upper and lower manner, that is, the angles between the upper and lower inner guide plates (25) and the axial direction of the inner cylinder (23) are equal in size and opposite in direction; the arrangement of the two inner guide plates (25) guides the fuel gas flow flowing into the fuel gas chamber into a rotating flow with a certain tangential and axial speed, and simultaneously forms two oppositely arranged high-speed rotating fuel gas flows at the upper and lower end outlets of the inner cylinder (23).
6. A coaxial reverse double atomization flame synthesis unit according to claim 5, characterized in that: The fuel gas inlet pipe (26) is a tubular structure composed of a circular arc section and a straight pipe section, wherein the circular arc section passes through the outer cylinder (21) and is tangentially connected and communicated with the outer wall surface of the middle spacer ring (22), and the straight pipe section is arranged adjacent to the straight pipe section in the shear gas inlet pipe (17) and is located on the same plane; The air inlet pipe (27) is a tubular structure composed of a circular arc segment and a straight pipe segment, wherein the circular arc segment is tangentially connected and communicated with the outer wall surface of the outer cylinder (21), and the straight pipe segment is arranged adjacent to the straight pipe segment in the fuel gas inlet pipe (26) and is located on the same plane.
7. A coaxial reverse double atomization flame synthesis unit according to claim 6, characterized in that: The atomizing nozzle assembly (1) is coaxially arranged at the center of the inner cylinder (23), and the inlet ends of the precursor flow inlet pipe (16) and the shear gas inlet pipe (17) sequentially pass through the outer cylinder (21), the middle spacer ring (22) and the middle area of the inner cylinder (23) along the axial direction; The air inlet pipe (27), the fuel gas inlet pipe (26), the shear gas inlet pipe (17), and the precursor flow inlet pipe (16) are arranged as a whole on the middle plane of the cyclone gas component (2) along the axial direction, and the straight pipe sections in the air inlet pipe (27), the fuel gas inlet pipe (26), the shear gas inlet pipe (17), and the precursor flow inlet pipe (16) are arranged closely from left to right in sequence.
8. A coaxial reverse double atomization flame synthesis unit according to claim 7, characterized in that: The filling body (28) is filled in the middle area between the outer cylinder (21) and the middle spacer ring (22), and between the fuel gas inlet pipe (26) and the shear gas inlet pipe (17). The purpose of providing the filling body (28) is to stabilize the airflow in this area, thereby stabilizing the overall vortex field.
9. The coaxial reverse double atomization flame synthesis unit according to claim 8, characterized in that: The outer wedge-shaped guide body (29) is provided in the middle area between the outer cylinder (21) and the middle spacer ring (22), and is located in the right area of the precursor flow inlet pipe (16), and is connected to the outer wall surface of the precursor flow inlet pipe (16); the outer wedge-shaped guide body (29) is a wedge-shaped structure, and is used to prevent the flow field from being disturbed due to the hard collision between the airflow and the outer wall of the precursor flow inlet pipe (16), thereby stabilizing the overall swirl field; The inner wedge-shaped guide body (210) is arranged in the middle area between the inner cylinder (23) and the middle spacer ring (22), and is located in the right area of the precursor flow inlet pipe (16), and is connected to the outer wall surface of the precursor flow inlet pipe (16); the inner wedge-shaped guide body (210) is a wedge-shaped structure, which is used to prevent the flow field from being disturbed due to the hard collision between the airflow and the outer wall of the precursor flow inlet pipe (16), thereby stabilizing the overall vortex field.