Air-cooled high-temperature alloy carbon black reaction furnace and combustion chamber head cyclone thereof

Abstract

The application discloses a gas-cooled high-temperature alloy carbon black reaction furnace and a combustion chamber head cyclone thereof, which comprises a radial vortex device, an upstream end of the radial vortex device is used for mounting a gas fuel nozzle, and a downstream end of the radial vortex device is connected with a throat pipe; further comprising a bevel vortex device located outside the throat pipe, an expansion sleeve connected with a downstream end of the bevel vortex device, a first annular gap is formed between the throat pipe and the bevel vortex device, and an end of the first annular gap towards the expansion sleeve is open. The purpose of the application is to provide a gas-cooled high-temperature alloy carbon black reaction furnace and a combustion chamber head cyclone thereof, so as to solve the problems of poor oil-gas mixing effect, limited organization combustion efficiency and the like of the gas-cooled high-temperature alloy carbon black reaction furnace in the prior art, and to realize the purposes of strengthening oil-gas mixing and downstream organization combustion of the gas-cooled high-temperature alloy carbon black reaction furnace and improving combustion efficiency.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of carbon black production, in particular to a gas-cooled high-temperature alloy carbon black reaction furnace and a combustion chamber head cyclone thereof. BACKGROUND

[0002] Carbon black is a product obtained by incomplete combustion or thermal decomposition of carbon-containing substances (coal, natural gas, heavy oil, fuel oil, etc.) under insufficient air, which can be used as black dye and reinforcing agent for rubber. The carbon black reaction furnace is a high-temperature device for producing carbon black, and the combustion chamber is the core equipment for producing carbon black in the carbon black reaction furnace. The combustion chamber of the traditional carbon black reaction furnace is made of steel shell and refractory bricks, so as to achieve the effect of resisting high-temperature gas above 2000℃. The refractory material of the reaction furnace wall is subjected to long-term scouring of high-temperature gas, and the particles of the refractory material flow to the downstream carbon black reaction zone, which seriously interferes with the quality of carbon black. Moreover, the refractory material of the throat section is scoured by the gas flow, the diameter of the throat increases, which leads to the reduction of gas flow speed, affects the atomization of fuel oil, and further affects the quality of carbon black formation. In order to overcome the above problems, the prior art has appeared a scheme that the combustion section and the throat section of the carbon black reaction furnace are cooled by cooling water to prevent ablation, but the equipment with water cooling has complex structure, high maintenance cost, and the core intellectual property rights belong to foreign manufacturers, which seriously restricts the development of China's carbon black industry.

[0003] In order to overcome the above defects, the applicant has previously applied for "a gas-cooled high-temperature alloy carbon black reaction furnace and a carbon black preparation method" (CN 112228872A), which discloses a gas-cooled carbon black reaction furnace, which can reduce the influence of gas scouring and improve the quality of carbon black. However, with the continuous development of research, the applicant found that although the gas fuel nozzle is inserted into the cyclone, if the conventional cyclone is used, there are still defects such as poor oil-gas mixing effect and limited downstream combustion efficiency. SUMMARY

[0004] The purpose of the present application is to provide a gas-cooled high-temperature alloy carbon black reaction furnace and a combustion chamber head cyclone thereof, so as to solve the problems of poor oil-gas mixing effect and limited downstream combustion efficiency of the prior art gas-cooled high-temperature alloy carbon black reaction furnace, and to realize the purpose of strengthening the oil-gas mixing and downstream combustion of the gas-cooled high-temperature alloy carbon black reaction furnace and improving the combustion efficiency.

[0005] The present application is realized by the following technical scheme:

[0006] The head swirler of the combustion chamber of the air-cooled high-temperature alloy carbon black reaction furnace comprises a radial vortex device, the upstream end of the radial vortex device is used for mounting a gas fuel nozzle, and the downstream end of the radial vortex device is connected with a throat pipe; further comprising a bevel vortex device located outside the throat pipe, and an expansion sleeve connected at the downstream end of the bevel vortex device, a first annular gap is formed between the throat pipe and the bevel vortex device, and the end of the first annular gap towards the expansion sleeve is open.

[0007] In view of the problems of poor oil-gas mixing effect and limited organization combustion efficiency of the air-cooled high-temperature alloy carbon black reaction furnace in the prior art, the present inventor found that the head gas inlet structure of the air-cooled high-temperature alloy carbon black reaction furnace is very important in a large number of researches, and therefore the present application first proposes a head swirler of the combustion chamber of the air-cooled high-temperature alloy carbon black reaction furnace, which comprises two vortex parts of a radial vortex device and a bevel vortex device, wherein the radial vortex device is used for making air enter the swirler in a radial direction and form a vortex, and the bevel vortex device is used for making air enter in a bevel direction and form a vortex. The upstream end of the radial vortex device is used for mounting a gas fuel nozzle, and the downstream end is connected with a throat pipe. The bevel vortex device is located outside the throat pipe, and a first annular gap is formed between the bevel vortex device and the radial vortex device. The end of the first annular gap towards the expansion sleeve is open, so that the air entering the swirler through the bevel vortex device is discharged towards the expansion sleeve. In use, the gas fuel nozzle is inserted into the upstream end of the head swirler, the gas fuel enters the swirler from the gas fuel nozzle, part of the air enters the swirler in a radial direction from the radial vortex device to form a primary vortex, and the gas fuel and the air are mixed in the swirler and then move towards the downstream end, pass through the throat pipe and enter the expansion sleeve. Another part of the air enters the swirler from the bevel vortex device to form a secondary vortex, and the secondary vortex moves towards the expansion sleeve after passing through the first annular gap.

[0008] Compared with the prior art, the present application has at least the following advantages: (1) through the cooperation of the radial vortex device and the bevel vortex device, a strong swirling gas flow with flame stabilizing effect and combustion strengthening effect can be formed, which significantly improves the aerodynamic characteristics of the fluid compared with the swirler using swirling vanes in the prior art, and has obvious advantages in improving the stability and efficiency of downstream combustion; (2) the existence of the expansion sleeve has a very significant effect on the stability of the head downstream combustion zone and the control of the excessively high wall temperature of the head transition stage; (3) the structure of the throat pipe and the first annular gap makes the two gas flows not interfere with each other before entering the expansion section, and the vortex gas flow discharged through the first annular gap moves along the inner wall of the expansion sleeve, which can protect the expansion sleeve from being eroded by high-temperature combustion gas; (4) compared with foreign water cooling technology, the structural complexity is significantly reduced, the production and maintenance costs are reduced, and the improvement of combustion efficiency and the protection of equipment are obviously beneficial.

[0009] Further, the radial vortex device comprises a plurality of annularly distributed slits, the slits have a fixed rotation direction, and the slits are used to communicate the inside and outside of the radial vortex device. The vortex device in the scheme is a slit type radial vortex device, a plurality of slits are annularly distributed on the vortex device, and the slits have a fixed rotation direction, that is, the axis of the slits is not in the radial direction, but is arranged in a certain rotation direction, so as to ensure that a plurality of gas flows enter the inside of the radial vortex device from the outside thereof in a specified rotation direction, thereby stably forming a primary vortex in the head swirler.

[0010] Further, the radial vortex device further comprises a front wall at the upstream end and a rear wall at the downstream end; the front wall comprises a conical section expanding towards the upstream end. The front wall and the rear wall are opposite side walls of the radial vortex device respectively, the throat pipe is connected with the rear wall, and the conical section is arranged to facilitate the gas fuel nozzle to be easily installed into the head swirler in blind installation.

[0011] Further, the oblique cutting vortex device comprises a plurality of annularly distributed oblique cutting holes, the oblique cutting holes have a fixed rotation direction, and the oblique cutting holes are used to communicate the first ring slit and the outside of the oblique cutting vortex device. The oblique cutting vortex is formed through a plurality of oblique cutting holes, and the oblique cutting holes have a fixed rotation direction, that is, the axis of the oblique cutting holes is not in the radial direction, but is arranged in a certain rotation direction, so as to ensure that a plurality of gas flows enter the inside of the oblique cutting vortex device from the outside thereof in a specified rotation direction, thereby stably forming a secondary vortex in the first ring slit.

[0012] Further, the flow rate of air in the throat pipe is 2 / 3 of the flow rate at the outlet end of the radial vortex device. The open end of the throat pipe is an air outlet of the secondary vortex, and the scheme can control the diameter of the throat pipe, so that the air speed in the throat pipe is 2 / 3 of the air speed at the outlet of the radial vortex device. After a large amount of research by the inventor, it is found that under this parameter, the primary vortex and the gas fuel can be fully mixed, and the mixed fluid can be continuously and stably output to the expansion sleeve after mixing, so that the best flame stabilizing effect can be achieved, and the flame shape of the downstream combustion area is not disturbed due to too fast or too slow flow rate of the mixed fluid in the throat pipe.

[0013] Further, the flow area of the first ring slit is greater than or equal to 1.5 times the inlet area of the oblique cutting vortex device. The scheme can make the flow rate of the secondary vortex flowing in the first ring slit be 2 / 3 of the flow rate at the outlet end of the oblique cutting vortex device, so as to continuously and stably output the secondary vortex to the expansion sleeve, so that the best flame stabilizing effect can be achieved, and the velocity shear layer between the secondary vortex and the primary vortex after entering the expansion sleeve is not too large, so that the flow state is stable, and the ablation protection of the expansion sleeve by the secondary vortex is ensured.

[0014] Further, the upstream end of the throat pipe and the downstream end of the radial vortex device are rounded, facilitating the smooth change of the airflow from radial to axial from the radial vortex device; the downstream end of the throat pipe has an outwardly expanding outflow section, which can make the fluid have an expanding trend before entering the expansion sleeve, ensuring that the downstream expansion sleeve fully plays a role in stabilizing the flame and strengthening combustion.

[0015] Further, the outflow angle of the outflow section is alpha, and the expansion angle of the expansion sleeve is beta.

[0016] Wherein alpha = 30°-50°, beta = alpha ± 5°.

[0017] In this scheme, the opening angle of the outflow section and the opening angle of the expansion sleeve differ by less than 5°, which can more effectively ensure that the velocity shear layer between the two stages of airflow is not too large, fully ensuring the stability of the flow state in the head vortex device.

[0018] Further, the radial vortex device, the throat pipe, the oblique cutting vortex device, and the expansion sleeve are coaxial.

[0019] A gas-cooled high-temperature alloy carbon black reaction furnace includes a shell, an air inlet assembly on the shell, a gas fuel inlet assembly, and a combustion chamber arranged in the shell, the combustion chamber has a throat section, the throat section is provided with a raw oil nozzle, the combustion chamber includes a flame tube, the flame tube is provided with a plurality of cooling holes, the head of the combustion chamber is provided with a plurality of head vortex devices in the application, and the gas fuel nozzle is inserted into the head vortex device.

[0020] The gas-cooled high-temperature alloy carbon black reaction furnace in the application forms a head air inlet structure by combining a radial vortex device and an oblique cutting hole, which can simplify the structure while matching each other, strengthen oil-gas mixing and downstream combustion organization, and improve combustion efficiency.

[0021] Compared with the prior art, the application has at least the following advantages and beneficial effects:

[0022] 1. The gas-cooled high-temperature alloy carbon black reaction furnace and the head vortex device of the combustion chamber thereof can form a strong swirling airflow with flame stabilizing and combustion strengthening effects by the cooperation of the radial vortex device and the oblique cutting vortex device, which significantly improves the aerodynamic characteristics of the fluid and has obvious advantages in improving the stability and efficiency of downstream combustion compared with the vortex device using the vortex blade in the prior art.

[0023] 2. The gas-cooled high-temperature alloy carbon black reaction furnace and the head vortex device of the combustion chamber thereof, the existence of the expansion sleeve has very significant effects on the stability of the head downstream combustion zone and the control of the excessively high wall temperature of the head transition stage.

[0024] 3. The air-cooled high-temperature alloy carbon black reaction furnace and the combustion chamber head vortex finder thereof, the structure of the throat pipe and the first ring gap makes the two air flows not interfere with each other before entering the expansion section, the vortex air flow sprayed through the first ring gap moves along the inner wall of the expansion sleeve, which can protect the expansion sleeve from being ablated by high-temperature combustion gas.

[0025] 4. The air-cooled high-temperature alloy carbon black reaction furnace and the combustion chamber head vortex finder thereof, compared with the water-cooling technology abroad, the structural complexity is significantly reduced, the production and maintenance costs are reduced, and the improvement of combustion efficiency and the protection of the equipment have obvious benefits. BRIEF DESCRIPTION OF DRAWINGS

[0026] The drawings described herein are used to provide further understanding of the embodiments of the present application, constitute a part of the present application, and do not constitute a limitation on the embodiments of the present application. In the drawings:

[0027] Figure 1 is a sectional view of the head vortex finder in the specific embodiment of the present application;

[0028] Figure 2 is a sectional view of the through Figure 1 B-B direction line;

[0029] Figure 3 is a sectional view of the through Figure 1 A-A direction line;

[0030] Figure 4 is a structural schematic view of the carbon black reaction furnace in the specific embodiment of the present application;

[0031] Figure 5 is a sectional view of the air inlet assembly in the specific embodiment of the present application;

[0032] Figure 6 is a sectional view of the through Figure 5 C-C direction line;

[0033] Figure 7 is a front view of the bottom cover plate in the specific embodiment of the present application;

[0034] Figure 8 is a partial schematic view of the ear in the specific embodiment of the present application;

[0035] Figure 9 is Figure 5 a partial enlarged view at D;

[0036] Figure 10 is a sectional view of the raw oil nozzle in the specific embodiment of the present application;

[0037] Figure 11 is a bottom surface schematic view of the raw oil nozzle in the specific embodiment of the present application;

[0038] Figure 12 For Figure 10 Close-up view at E in Figure 1.

[0039] Figure 13 Cross-sectional view of the location of the air inlet hole in the sleeve of the raw oil nozzle in the specific embodiment of the present application.

[0040] Markings in the drawings and corresponding names of parts:

[0041] 1 - air inlet assembly, 2 - bolt, 3 - first flange, 4 - ear, 5 - ear cavity, 6 - hanging ear, 7 - filter screen, 8 - drainage hole, 9 - second flange, 10 - shell, 11 - raw oil nozzle, 12 - air duct, 13 - pollution window, 14 - bottom cover plate, 15 - second bolt hole, 16 - stop structure, 17 - first bolt hole, 18 - radial vortex device, 19 - gas fuel nozzle, 20 - throat pipe, 21 - beveled vortex device, 22 - expansion sleeve, 23 - first annular gap, 24 - slot, 25 - front wall, 26 - rear wall, 27 - conical section, 28 - beveled hole, 29 - outflow section, 31 - gas fuel inlet assembly, 32 - throat section, 33 - raw oil nozzle, 34 - flame tube, 35 - lower oil pipe, 36 - nozzle head, 37 - sleeve, 38 - injection hole, 39 - gas-assisted atomizing hole, 40 - first gap, 41 - second annular gap, 42 - air inlet hole, 43 - lower heat insulation pipe, 44 - lower oil collecting cavity, 45 - upper oil pipe, 46 - upper oil collecting cavity, 47 - oil inlet connector, 48 - upper heat insulation pipe, 49 - second gap, 50 - nozzle cover plate. DETAILED DESCRIPTION

[0042] In order to make the purpose, technical solutions and advantages of the present application clearer and more apparent, the present application will be further described in detail below with reference to the embodiments and drawings, the illustrative embodiments of the present application and the description thereof are only used to explain the present application, and do not limit the present application.

[0043] Example 1:

[0044] As Figure 1 shown in the head swirl of the air-cooled high-temperature alloy carbon black reaction furnace combustion chamber, including radial vortex device 18, the upstream end of the radial vortex device 18 is used to install gas fuel nozzle 19, the downstream end of the radial vortex device 18 is connected to the throat pipe 20; It also includes a beveled vortex device 21 located outside the throat pipe 20, an expansion sleeve 22 connected to the downstream end of the beveled vortex device 21, a first annular gap 23 formed between the throat pipe 20 and the beveled vortex device 21, and an end of the first annular gap 23 open towards the expansion sleeve 22.

[0045] As Figure 2As shown, the radial vortex device 18 includes a plurality of annularly distributed slots 24, the slots 24 having a fixed rotation direction, and the slots 24 are used to connect the inside and outside of the radial vortex device 18.

[0046] like Figure 3 As shown, the oblique vortex device 21 includes a plurality of annularly distributed oblique holes 28. The oblique holes 28 have a fixed rotation direction and are used to connect the first annular slit 23 with the outside of the oblique vortex device 21.

[0047] pass Figure 2 and Figure 3 It can be seen that in this embodiment, the axes of the slot and the oblique hole are both on a plane passing through the radial direction, but neither of them is along the standard radial direction.

[0048] The rotation direction of the groove 24 and the rotation direction of the oblique cut hole 28 can be the same or opposite, with the opposite direction being the preferred option. The height of the first circumferential slit 23 is more than 1 mm.

[0049] In a more preferred embodiment, the rotation direction of the slot 24 can be clockwise or counterclockwise, and the inclination angle of the slot is 20° to 60°. The width, height, and number of slots together determine the effective flow area of ​​the radial vortex device 18, which is calculated based on the overall aerodynamic scheme and airflow distribution. In this embodiment, the number of slots is 8 to 20.

[0050] In a more preferred embodiment, the rotation direction of the beveled hole 28 can be clockwise or counterclockwise.

[0051] In a more preferred embodiment, the oblique cut hole 28 may have several turns; the diameter, number and number of oblique cut holes together determine the effective flow area of ​​the oblique vortex device 21. The diameter, number and number of oblique cut holes can be determined according to the overall aerodynamic scheme and airflow distribution.

[0052] When the beveled holes are made in several turns, the spacing between two adjacent turns is about 5mm, the hole diameter is 2mm to 4mm, and the number of holes per turn is 6-18; the beveled hole angle is 30° to 60°.

[0053] In a more preferred embodiment, although the rotation direction of each beveled hole within a single turn must be the same, the rotation direction of the beveled holes on any two turns can be in the same direction or in opposite directions.

[0054] Example 2:

[0055] A head vortex device for the combustion chamber of an air-cooled high-temperature alloy carbon black reactor, based on Embodiment 1, further includes a front wall 25 located at the upstream end and a rear wall 26 located at the downstream end; the front wall 25 includes a conical section 27 that expands towards the upstream end.

[0056] As shown in Figure 1 the upstream end of the throat pipe 20 is rounded with the downstream end of the radial vortex device 18; the downstream end of the throat pipe 20 has an outwardly expanding outflow section 29. The outflow angle of the outflow section 29 is a, and the expansion angle of the expansion sleeve 22 is b; wherein a = 30°-50°, b = a ± 5°.

[0057] In a more preferred embodiment, the wind speed inside the throat pipe is 2 / 3 of the flow speed at the outlet end of the radial vortex device 18 by controlling the pipe diameter of the throat pipe; that is, the minimum flow area inside the throat pipe 20 is 1.5 times the area at the outlet end of the radial vortex device 18.

[0058] In a more preferred embodiment, the flow area of the first annular slit 23 is greater than or equal to 1.5 times the inlet area of the beveled vortex device 21. The inlet area of the beveled vortex device 21 refers to the total inlet area of all beveled holes 28.

[0059] In a more preferred embodiment, the radial vortex device 18, the throat pipe 20, the beveled vortex device 21, and the expansion sleeve 22 are coaxial.

[0060] In a more preferred embodiment, as shown in Figure 1 the opening angle g of the conical section 27 is 20°-45°.

[0061] Example 3:

[0062] As shown in Figure 4 a gas-cooled high-temperature alloy carbon black reaction furnace, comprising a shell 10, an air inlet assembly 1 and a gas fuel inlet assembly 31 located on the shell 10, a combustion chamber arranged in the shell 10, the combustion chamber having a throat section 32, the throat section 32 being provided with a raw oil nozzle 33, the combustion chamber comprising a flame tube 34, the flame tube 34 being provided with a plurality of cooling holes, the head of the combustion chamber being provided with a plurality of head cyclones as claimed in any one of embodiments 1 or 2, and a gas fuel nozzle 19 being inserted into the head cyclone.

[0063] Example 4:

[0064] A gas-cooled high-temperature alloy carbon black reaction furnace, based on the embodiment 3, the air inlet assembly 1 is optimized and improved, as shown in Figures 5 to 9

[0065] ​It also includes a filter 7 installed inside the air intake assembly 1, the filter 7 having a conical structure that is smaller at the top and larger at the bottom; it also includes a cabin ear 4 located on the outer wall of the air intake assembly 1, the cabin ear 4 facing the bottom end of the filter 7, the cabin ear 4 and the air intake assembly 1 forming a cabin ear cavity 5, and a number of vent holes 8 located above the bottom end of the filter 7 are opened on the air intake assembly 1, the vent holes 8 communicating with the cabin ear cavity 5.

[0066] The bottom surface of the hatch ear 4 is provided with several sewage discharge windows 13, and also includes a bottom cover plate 14 that can be detachably connected to the bottom of the hatch ear 4. The bottom cover plate 14 is used to block the sewage discharge windows 13.

[0067] In this embodiment, the bottom cover plate is as follows: Figure 3 As shown, it is composed of two arc-shaped plates joined together to form a ring.

[0068] The bottom cover plate 14 is connected to the bottom of the hatch lug 4 by bolts 2. For example... Figure 6 As shown, the bottom of the lug 4 is provided with several first bolt holes 17 that match the bolts 2; as Figure 7 As shown, the bottom cover plate 14 has second bolt holes 15 that correspond one-to-one with the first bolt holes 17.

[0069] like Figure 8 As shown, several hanging ears 6 are evenly distributed in a ring on the inner wall of the air intake assembly 1, and the bottom end of the filter screen 7 is inserted into the hanging ears 6.

[0070] The bottom of the hatch lug 4 has a stop structure 16 that matches the bottom cover plate 14, and the bottom cover plate 14 is fitted into the stop structure 16. For example... Figure 9 As shown, the stop structure in this embodiment is a ring-shaped protrusion located on the outer side of the bottom of the ear 4, and its size is just enough to fit the bottom cover plate 14 into it.

[0071] like Figure 5 As shown, the air intake assembly 1 and the air duct 12 are sealed together by the first flange 3 and the second flange 9.

[0072] In a more preferred embodiment, such as Figure 5 As shown, the apex angle α1 of filter 7 is 60° to 90°.

[0073] In a more preferred embodiment, such as Figure 6 As shown, several sewage discharge windows 13 are evenly distributed in a ring on the bottom surface of the cabin ear.

[0074] In a more preferred embodiment, the thickness of the filter 7 is 1.5 mm to 2.0 mm.

[0075] In a more preferred embodiment, the gap between the ear loop 6 and the inner wall of the air intake assembly 1 is 2.0mm-2.5mm.

[0076] In a more preferred embodiment, the axial height of the cavity 5 is not less than 20 mm, and the radial width is not less than 15 mm.

[0077] In a more preferred embodiment, the thickness of the bottom cover plate is not less than 3 mm, and the width is smaller than that of the cavity; the bolt type is selected according to the size of the bottom cover plate.

[0078] The embodiment solves the problem that the flame tube of the air-cooled carbon black reaction furnace in the prior art is easily blocked by particulate pollutants in the air, and can remove the pollutants contained in the air and avoid the cooling holes on the flame tube being blocked. The particulate pollutants filtered by the filter screen flow along the outer wall of the conical filter screen, and finally gather between the bottom end of the filter screen and the inner wall of the air inlet assembly. When the particulate pollutants accumulate, they can flow into the cavity of the cavity through the drainage hole for storage. When the cavity of the cavity temporarily stores a large amount of particulate pollutants, the bottom cover plate can be removed, and the particulate pollutants can be discharged from the exhaust windows to clean the cavity of the cavity.

[0079] Embodiment 5:

[0080] An air-cooled high-temperature alloy carbon black reaction furnace, based on the embodiments 3 or 4, the raw oil nozzle 33 is improved, as shown in Figures 10 to 13 .

[0081] The raw oil nozzle comprises a lower oil pipe 35, a nozzle head 36 arranged at the bottom of the lower oil pipe 35, and a sleeve 37 sleeved on the outside of the lower oil pipe 35. The nozzle head 36 comprises a plurality of spray holes 38, the bottom of the sleeve 37 has a plurality of air-assisted atomization holes 39 matched with the spray holes 38, and the spray holes 38 are inserted into the air-assisted atomization holes 39. A first gap 40 is formed between the inner wall of the sleeve 37 and the outer wall of the lower oil pipe 35, and a plurality of second annular grooves 41 axially penetrating the sleeve 37 are formed between the sleeve 37 and the nozzle head 36. A plurality of air inlet holes 42 are formed in the side wall of the sleeve 37, the air inlet holes 42 are communicated with the first gap 40, and the first gap 40 is communicated with the second annular grooves 41.

[0082] As shown in Figure 11 and Figure 12 , the air-assisted atomization holes 39 correspond to the spray holes 38 one by one, and each air-assisted atomization hole 39 forms a second annular groove 41 with the nozzle head 36. The spray holes 38 are circularly arranged on the nozzle head 36, and the specific array mode can be seen from Figure 11 , which comprises a central spray hole located at the center of the nozzle head 36 and a plurality of arrayed spray holes uniformly distributed around the central spray hole.

[0083] The embodiment can determine the penetration depth and atomization effect of the fuel oil according to the mass flow rate of the raw oil, the size of the nozzle head 36, the number and diameter of the spray holes 38, and other parameters.

[0084] In a more preferred embodiment, asFigure 11 As shown in the figure, a center boss is arranged at the center of the bottom of the nozzle head 36, and an annular boss is arranged around the center boss, the center orifice is arranged on the center boss, and each array orifice is arranged on the annular boss; the gap between the center boss and the annular boss constitutes the annular gap of the center orifice, and the gap between the annular boss and the wall of the air-atomizing hole 39 constitutes the annular gap of the array orifice.

[0085] In a more preferred embodiment, the number of orifices 38 is 2-8.

[0086] In a more preferred embodiment, as shown in the figure, the upper end of the sleeve 37 is in sealing contact with the lower oil pipe 35; and the lower end of the sleeve 37 has the same number of air-atomizing holes 39 as the number of orifices 38, and each orifice 38 is coaxial with a corresponding air-atomizing hole 39. Figure 10

[0087] In a more preferred embodiment, the side of the sleeve is provided with a plurality of rows of air inlet holes in the axial direction, as shown in the figure, each row includes a plurality of annularly distributed air inlet holes. In specific use, the number of rows and the number of holes in each row are determined according to the demand for air-atomizing air, and preferably 1-3 rows, 4-16 holes per row, and the diameter of a single air inlet hole is 2-4 mm. Figure 13

[0088] The outer wall of the lower oil pipe 35 is sleeved with a lower heat insulation pipe 43, and the first gap 40 is located between the outer wall of the lower heat insulation pipe 43 and the inner wall of the sleeve 37.

[0089] As shown in the figure, the diameter of the bottom of the lower oil pipe 35 gradually expands from inside to outside; and the lower oil pipe 35 has a lower oil collecting cavity 44 between the bottom end and the nozzle head 36. The lower oil collecting cavity 44 in the embodiment is jointly surrounded by the bottom end of the lower oil pipe 35, the inner wall of the lower heat insulation pipe 43, and the top surface of the nozzle head 36. Figure 12

[0090] In a more preferred embodiment, as shown in the figure, the expansion angle α2 of the bottom of the lower oil pipe 35 is 90°±5°; and the axial height of the lower oil collecting cavity 44 is not less than 5 mm. Figure 12

[0091] It also includes an upper oil pipe 45 coaxial with and communicating with the lower oil pipe 35, the top end of the upper oil pipe 45 communicates with an upper oil collecting cavity 46, and the upper oil collecting cavity 46 is used for connecting an oil inlet nozzle 47. It also includes an upper heat insulation pipe 48 sleeved outside the upper oil pipe 45, and the inner wall of the upper heat insulation pipe 48 and the outer wall of the upper oil pipe 45 form a closed second gap 49. The top ends of the upper oil pipe 45 and the upper heat insulation pipe 48 are in sealing connection with a nozzle cover plate 50, and the upper oil collecting cavity 46 is located in the nozzle cover plate 50.

[0092] ​​​​In the embodiment, the inner diameter of the upper oil collecting cavity is larger than the inner diameter of the oil inlet connector and the oil supply pipe. The upper oil collecting cavity is coaxial with the oil supply pipe, and the oil supply pipe and the lower oil supply pipe are coaxial and have the same inner diameter. The oil inlet connector 47 is located on the side of the upper oil collecting cavity 46.

[0093] In the embodiment, the single raw oil beam is divided into multiple beams, which greatly increases the area of the oil beam surface in contact with the high-temperature combustion gas and strengthens the oil-gas mixing, so that a local over-rich area is not easily formed, which is conducive to the occurrence of carbon black chemical reactions. The raw oil can be fully mixed with air at the initial injection, and through the combined action of the annular gap and the injection hole, the liquid column surface is fully sheared and broken, finally achieving good initial atomization effect, which is conducive to improving the quality of carbon black.

[0094] It should be noted that, in this document, the terms such as first and second are used merely to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "contain" or any other variants thereof are intended to cover non-exclusive inclusion, so that the process, method, article or equipment including a series of elements not only includes those elements, but also includes other elements not explicitly listed or inherent to such process, method, article or equipment. In addition, the term "connected" used in this document can be directly connected or indirectly connected via other components without special description.

[0095] The above specific embodiments further illustrate the purpose, technical solutions and beneficial effects of the present application. It should be understood that the above description is only a specific embodiment of the present application and is not used to limit the protection scope of the present application. Any modification, equivalent replacement, improvement, etc. within the spirit and principles of the present application should be included in the protection scope of the present application.

Claims

1. A head cyclone for a combustion chamber of a gas-cooled superalloy carbon black reactor, characterized in that The radial vortex device (18) includes a plurality of annularly distributed slots (24) having a fixed rotation direction, and the slots (24) are used to communicate the inside and outside of the radial vortex device (18). The radial vortex device (18) includes a plurality of annularly distributed slots (24) having a fixed rotation direction, and the slots (24) are used to communicate the inside and outside of the radial vortex device (18). The radial vortex device (18) includes a plurality of annularly distributed slots (24) having a fixed rotation direction, and the slots (24) are used to communicate the inside and outside of the radial vortex device (18). The first annular gap (23) has an open end towards the expansion sleeve (22). The upstream end of the throat pipe (20) and the downstream end of the radial vortex device (18) are rounded; the downstream end of the throat pipe (20) has an outwardly expanding outflow section (29). The outflow angle of the outflow section (29) is α, and the expansion angle of the expansion sleeve (22) is β; wherein α=30°~50°, β=α±5°.

2. A gas cooled superalloy carbon black reactor combustion chamber head swirler according to claim 1, characterized in that, The radial vortex device (18) further includes a front wall (25) at the upstream end and a rear wall (26) at the downstream end; the front wall (25) includes a tapered section (27) expanding towards the upstream end.

3. A gas cooled superalloy carbon black reactor combustion chamber head swirler according to claim 1, wherein, The flow velocity of air in the throat pipe (20) is 2 / 3 of the flow velocity at the outlet end of the radial vortex device (18).

4. A gas cooled superalloy carbon black reactor combustion chamber head swirler according to claim 1, wherein, The radial vortex device (18), the throat pipe (20), the bevel vortex device (21) and the expansion sleeve (22) are coaxial.

5. A gas-cooled high-temperature alloy carbon black reactor, comprising a shell (10), an air inlet assembly (1) and a gas fuel inlet assembly (31) located on the shell (10), a combustion chamber provided in the shell (10), the combustion chamber having a throat section (32), a raw oil nozzle (33) being provided on the throat section (32), the combustion chamber comprising a flame tube (34), a plurality of cooling holes being provided on the flame tube (34), characterized in that, The combustion chamber head is provided with a plurality of head swirlers as claimed in any one of claims 1~4, and the gas fuel nozzle (19) is inserted into the head swirler.

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