Flow-adjustable supersonic hydrocyclone separation device

Abstract

The invention discloses a flow-adjustable supersonic rotational flow separation device which comprises a supersonic rotational flow separation device body, and the supersonic rotational flow separation device body comprises a steady flow contraction section, a diffusion separation section and a central rotational flow component. The steady-flow contraction section comprises a direct-flow steady-flow section and a Laval spray pipe gradual contraction section which is fixedly communicated with the right side of the direct-flow steady-flow section, and the diffusion separation section comprises a Laval spray pipe expansion section, an annular liquid collecting tank and a secondary diffusion section which are sequentially connected from left to right. By arranging a series of structures, the through-flow sectional area between the Laval spray pipe reducing section and the front-end rotational flow blade supporting body can be flexibly adjusted according to different gas flow requirements, so that the Laval spray pipe can be conveniently suitable for different gas flows, and the use flexibility is improved.

Description

Technical Field

[0001] The invention relates to the technical field of supersonic cyclone separation equipment, in particular to a supersonic cyclone separation device with adjustable flow rate. Background Art

[0002] In the field of natural gas extraction, the natural gas currently extracted is often saturated with water vapor and contains some heavy hydrocarbon components. In order to meet the requirements of natural gas export and use, water vapor, acid gas and heavy hydrocarbon components must be separated; traditional natural gas separation processes include cooling method, chemical absorption method, adsorption method and membrane separation method; however, these separation processes will have various disadvantages in the natural gas separation process, and it is urgent to propose a new natural gas separation method; supersonic cyclone separation technology is a major innovation in the field of natural gas processing; supersonic cyclone separation technology combines gas dynamics, engineering thermodynamics and fluid mechanics theory, and completes the expansion cooling, cyclone gas / liquid separation and recompression processes in a closed and compact device. This separation technology has the advantages of being simple and reliable, closed and leak-free, no need for chemicals, and supporting unmanned operation.

[0003] In this regard, publication number CN111763547A discloses a full swirl supersonic separation device, which includes a shell and a central swirl component. The shell includes a DC steady flow section, a Laval nozzle convergent section, and a Laval nozzle expansion section, and the central swirl component includes a front central swirl component and a rear central swirl component; the front central swirl component is located in the DC steady flow section and the Laval nozzle convergent section; the rear central swirl component is located in the Laval nozzle expansion section. When the gas enters the DC steady flow section and the Laval nozzle convergent section, the gas flow expands in a swirl state, and reaches supersonic speed after reaching the Laval nozzle expansion section, the temperature and pressure are further reduced, and the gas begins to condense. This process of swirl and condensation can effectively reduce the impact of droplet re-evaporation; in addition, a swirl component is also arranged in the Laval nozzle expansion section, and its swirl ability is strong and lasting, which ensures the separation effect and separation efficiency of the device.

[0004] The above technology discloses a full-vortex supersonic separation device, which achieves a long-lasting supersonic vortex separation effect. However, it still has the following shortcomings when used: the throat flow cross-sectional area formed between the Laval nozzle tapered section and the front vortex blade support body is fixed and cannot be flexibly adjusted according to flow requirements, making it difficult to adapt to different gas flow rates and having unsatisfactory flexibility of use. In view of this, the present application proposes a supersonic vortex separation device with adjustable flow rate to solve the above-mentioned problems. Summary of the invention

[0005] The object of the present invention is to provide a supersonic cyclone separation device with adjustable flow rate to solve the problems raised in the above background technology.

[0006] To achieve the above-mentioned purpose, the present invention provides the following technical solutions: a supersonic cyclone separation device with adjustable flow, comprising a supersonic cyclone separation device body, wherein the supersonic cyclone separation device body comprises a steady flow contraction section, a pressure diffusion separation section and a central cyclone component, wherein the steady flow contraction section comprises a direct flow steady flow section and a Laval nozzle tapered section connected and fixed to the right side of the direct flow steady flow section, wherein the pressure diffusion separation section comprises a Laval nozzle expansion section, an annular liquid collecting tank and a secondary pressure diffusion section connected in sequence from left to right, wherein the central cyclone component comprises a central cyclone component arranged in the direct flow steady flow section. A front swirl blade support body, a plurality of front swirl blades fixedly connected to the outside of the front swirl blade support body, a rear swirl blade support body fixed to the right side of the front swirl blade support body and located in the Laval nozzle expansion section, and a rear swirl blade fixed to the outside of the rear swirl blade support body; wherein other specific components and structures of the supersonic swirl separation device body and the supersonic swirl separation principle are prior art, and this composition and technology have also been disclosed in the above-mentioned prior art CN111763547A, which is the same as it, and will not be further elaborated on;

[0007] A linkage-type four-point uniformly adjustable telescopic mechanism is installed between the Laval nozzle convergence section and the Laval nozzle expansion section, and the linkage-type four-point uniformly adjustable telescopic mechanism includes an inner tube connected and fixed to the right end of the Laval nozzle convergence section, the outer sealing sliding sleeve of the inner tube is provided with an outer tube, the outer tube fixed sleeve is arranged on the outside of the Laval nozzle expansion section, an annular groove with an opening on the right side is provided on the inner side of the inner tube, the sealing sliding sleeve in the annular groove is provided with a circular tube fixedly connected to the left end of the Laval nozzle expansion section, the top, bottom, front side and rear side of the outer tube are fixedly connected with a threaded transverse guide drive assembly for driving the inner tube to move laterally, and the outer side of the outer tube is provided with a linkage rotary drive assembly for driving the four threaded transverse guide drive assemblies to rotate synchronously; the linkage rotary drive assembly is used to drive the four The four threaded cross-guide drive assemblies rotate synchronously, and the four threaded cross-guide drive assemblies are used to drive the inner tube to move horizontally left and right evenly and synchronously from four directions during rotation, and the inner tube is used to drive the Laval nozzle tapered section to move left and right to adjust the flow cross-sectional area formed between the Laval nozzle tapered section and the front swirl blade support body. When the flow rate and pressure are constant, the critical flow rate is fixed. When the two increase, the critical flow rate becomes larger, and the critical radius also increases, that is, the flow position radius. The flow space between the Laval nozzle tapered section and the front swirl blade support body is variable, so as to adapt to different gas flow rates. Specifically, when the flow rate increases, the Laval nozzle tapered section moves backward, and when the flow rate decreases, the Laval nozzle tapered section migrates, thereby achieving a flexible application effect with adjustable flow rate.

[0008] Preferably, the threaded cross-guide drive assembly includes a guide sleeve, the top, bottom, front side and rear side of the outer tube are respectively fixedly connected to the corresponding guide sleeve, the top, bottom, front side and rear side of the inner tube are fixedly connected with L-shaped rods, the four L-shaped rods are respectively slidably sleeved in the corresponding guide sleeves, the top, bottom, front side and rear side of the outer tube are respectively provided with screws, and the four L-shaped rods are respectively threadedly sleeved on the corresponding screws.

[0009] Preferably, the linked rotary drive assembly includes a circular box and an annular cover plate fixedly mounted on the outside of the outer tube, the annular cover plate is fixedly connected to the right side of the circular box, the circular box is rotatably mounted on four screws, the right ends of the four screws are fixedly connected to gears located in the circular box, the four gears are meshed with the same outer gear ring rotatably mounted on the outside of the outer tube, and a drive motor is fixedly installed on the top right side of the annular cover plate, the output shaft of the drive motor being fixedly connected to the right side of the gear above.

[0010] Preferably, the outer tube inner bonding sleeve is provided with a first sealing ring, and the inner side of the first sealing ring is slidably connected to the outer side of the inner tube.

[0011] Preferably, a second sealing ring is provided in the adhesive sleeve in the annular groove, and the inner side of the second sealing ring is slidably connected to the outer side of the circular tube.

[0012] Preferably, a thread groove is formed at the right end of the L-shaped rod and is threadably connected to the corresponding screw rod.

[0013] Preferably, an anti-slip block is fixedly connected to the inner wall of the L-shaped rod on the side away from the outer tube, and the anti-slip block is located on the right side of the corresponding guide sleeve.

[0014] Compared with the prior art, the present invention has the following beneficial effects:

[0015] 1. The Laval nozzle tapered section, Laval nozzle expansion section, circular tube, inner tube, outer tube, threaded cross-guide drive assembly and linked rotary drive assembly are arranged to facilitate flexible adjustment of the flow cross-sectional area between the Laval nozzle tapered section and the front swirl blade support body. When the flow rate and pressure are constant, the critical flow rate is fixed. When the two increase, the critical flow rate increases, and the critical radius also increases, that is, the flow position radius. The flow space between the Laval nozzle tapered section and the front swirl blade support body is variable, so that it can adapt to different gas flow rates. Specifically, when the flow rate increases, the Laval nozzle tapered section moves backward, and when the flow rate decreases, the Laval nozzle tapered section migrates, so as to achieve a flexible application effect of adjustable flow rate and improve the flexibility of use.

[0016] The present invention is provided with a series of structures, which facilitates flexible adjustment of the flow cross-sectional area between the Laval nozzle tapered section and the front swirl blade support body according to different gas flow requirements, thereby facilitating the application of different gas flow rates and improving the flexibility of use. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 This is a schematic structural diagram of a supersonic cyclone separation device with adjustable flow rate proposed by the present invention;

[0018] Figure 2 This is a schematic cross-sectional structure diagram of a supersonic cyclone separation device with adjustable flow rate proposed by the present invention;

[0019] Figure 3 for Figure 2 A schematic diagram of the enlarged structure of part A in the figure.

[0020] In the figure: 1, steady flow contraction section; 2, pressure expansion separation section; 3, direct current steady flow section; 4, Laval nozzle contraction section; 5, Laval nozzle expansion section; 6, annular liquid collecting tank; 7, secondary pressure expansion section; 8, front end swirl blade support body; 9, front end swirl blade; 10, rear end swirl blade support body; 11, rear end swirl blade; 100, inner tube; 101, outer tube; 102, round tube; 103, annular groove; 104, second sealing ring; 105, first sealing ring; 106, L-shaped rod; 107, threaded groove; 108, screw; 109, guide sleeve; 110, round box; 111, gear; 112, annular cover plate; 113, outer gear ring; 114, drive motor; 115, anti-slip block. DETAILED DESCRIPTION

[0021] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0022] like Figures 1 to 3 As shown, a flow-adjustable supersonic cyclone separation device proposed in this embodiment includes a supersonic cyclone separation device body, the supersonic cyclone separation device body includes a steady flow contraction section 1, a pressure diffusion separation section 2 and a central cyclone component, the steady flow contraction section 1 includes a direct flow steady flow section 3 and a Laval nozzle convergence section 4 connected and fixed to the right side of the direct flow steady flow section 3, the pressure diffusion separation section 2 includes a Laval nozzle expansion section 5, an annular liquid collecting tank 6 and a secondary pressure diffusion section 7 connected in sequence from left to right, and the central cyclone component includes a front end cyclone blade support body 8 arranged in the direct flow steady flow section 3, a plurality of front end cyclone blades 9 fixedly connected to the outside of the front end cyclone blade support body 8, a rear end cyclone blade support body 10 fixed to the right side of the front end cyclone blade support body 8 and located in the Laval nozzle expansion section 5, and a rear end cyclone blade 11 fixed to the outside of the rear end cyclone blade support body 10;

[0023] The other specific components and structures of the supersonic cyclone separation device body and the supersonic cyclone separation principle are prior art. In addition, this composition and technology have also been disclosed in the above-mentioned prior art CN111763547A, which is the same as it, and will not be further elaborated on;

[0024] A linkage-type four-point uniform telescopic mechanism is installed between the Laval nozzle convergent section 4 and the Laval nozzle expansion section 5. The linkage-type four-point uniform telescopic mechanism includes an inner tube 100 connected and fixed to the right end of the Laval nozzle convergent section 4. The outer sealing sliding sleeve of the inner tube 100 is provided with an outer tube 101, wherein the inner adhesive sleeve of the outer tube 101 is provided with a first sealing ring 105, and the inner side of the first sealing ring 105 is slidably connected with the outer side of the inner tube 100, so as to achieve the effect of sliding sealing between the outer side of the inner tube 100 and the inner side of the outer tube 101. The outer tube 101 is fixedly sleeved. The inner tube 100 is provided with an annular groove 103 with an opening on the right side, and a sealing sliding sleeve in the annular groove 103 is provided with a round tube 102 fixedly connected to the left end of the Laval nozzle expansion section 5, wherein a second sealing ring 104 is provided in the adhesive sleeve in the annular groove 103, and the inner side of the second sealing ring 104 is slidably connected to the outer side of the round tube 102, so as to achieve the effect of sliding sealing between the inner side of the inner tube 100 and the outer side of the round tube 102. With the cooperation of the first sealing ring 105 and the second sealing ring 104, a double sealing ring 104 is realized. The top, bottom, front and rear sides of the outer tube 101 are fixedly connected with threaded transverse guide drive components for driving the inner tube 100 to move laterally. The outer side of the outer tube 101 is sleeved with a linkage rotary drive component for driving four threaded transverse guide drive components to rotate synchronously. The linkage rotary drive component is used to drive the four threaded transverse guide drive components to rotate synchronously. The four threaded transverse guide drive components are used to drive the inner tube 100 to move horizontally from four directions uniformly and synchronously during rotation. The inner tube 100 is used to drive the Laval nozzle tapering section 4 to move left and right to adjust the nozzle. The flow cross-sectional area is formed between the whole and the front swirl blade support body 8. Since the critical flow rate is fixed when the flow rate and pressure are constant, when the two increase, the critical flow rate becomes larger, and the critical radius will also increase, that is, the flow position radius. The flow space between the Laval nozzle tapered section 4 and the front swirl blade support body 8 is variable, so as to adapt to different gas flow rates. Specifically, when the flow rate increases, the Laval nozzle tapered section 4 moves backward, and when the flow rate decreases, the Laval nozzle tapered section 4 migrates, thereby achieving a flexible application effect with adjustable flow rate.

[0025] Specifically, the threaded transverse guide drive assembly includes a guide sleeve 109, the top, bottom, front side and rear side of the outer tube 101 are fixedly connected to the corresponding guide sleeves 109, the top, bottom, front side and rear side of the inner tube 100 are fixedly connected with L-shaped rods 106, and the four L-shaped rods 106 are respectively slidably sleeved in the corresponding guide sleeves 109. The top, bottom, front side and rear side of the outer tube 101 are provided with screws 108, and the four L-shaped rods 106 are respectively threadedly sleeved on the corresponding screws 108, wherein the right end of the L-shaped rod 106 is provided with a thread groove 107 threadedly connected to the corresponding screw 108, and the screw 108 is used to rotate the inner tube 100. The threaded connection relationship between 08 and the thread groove 107 facilitates the effect of driving the L-shaped rod 106 to move horizontally to the left and right when the screw 108 rotates. An anti-slip block 115 is fixedly connected to the inner wall of the L-shaped rod 106 away from the outer tube 101, and the anti-slip block 115 is located on the right side of the corresponding guide sleeve 109; the set guide sleeve 109, L-shaped rod 106 and screw 108 cooperate, and when the four screws 108 rotate, the four L-shaped rods 106 are driven to slide horizontally to the left or right in the corresponding guide sleeve 109, respectively, and the four L-shaped rods 106 are used to realize the uniform and synchronous driving of the inner tube 100 to move horizontally to the left and right from four directions.

[0026] Furthermore, the linked rotary drive assembly includes a round box 110 and an annular cover plate 112 fixedly sleeved on the outside of the outer tube 101, the annular cover plate 112 is fixedly connected to the right side of the round box 110, the round box 110 is rotatably sleeved on four screws 108, wherein the left side of the round box 110 is provided with four circular through holes at equal intervals in a circular shape, a first bearing is fixedly sleeved in the circular through holes, the inner side of the inner ring of the first bearing is fixedly connected to the outer side of the screw 108, which plays the effect of rotatably installing the screw 108, the right ends of the four screws 108 are fixedly connected to gears 111 located in the round box 110, and the four gears 111 are meshed with an outer gear ring 113 rotatably sleeved on the outside of the outer tube 101, wherein the outer gear ring 113 is fixedly sleeved inside The fixed sleeve is provided with a second bearing, the inner ring of the second bearing is fixedly sleeved with the outer side of the outer tube 101, which plays the effect of rotatably installing the outer ring gear 113, and the right top of the annular cover plate 112 is fixedly installed with an output shaft and a driving motor 114 fixedly connected to the right side of the upper gear 111; the round box 110, the annular cover plate 112, the gear 111, the outer ring gear 113 and the driving motor 114 are coordinated, and the driving motor 114 is used to drive the upper gear 111 to rotate, and the upper gear 111 drives the outer ring gear 113 meshing with it to rotate, and the outer ring gear 113 drives the other three gears 111 to rotate. At this time, the four gears 111 rotate synchronously, and the four gears 111 are used to drive the four screws 108 to rotate synchronously.

[0027] The method of use of this embodiment is as follows: when the flow-adjustable supersonic cyclone separation device is used, the other specific components and structures of the supersonic cyclone separation device body and the supersonic cyclone separation principle are prior art. In addition, this component and technology have also been disclosed in the above-mentioned prior art CN111763547A, which is the same as it, and will not be further elaborated on;

[0028] When it is necessary to adjust the flow cross-sectional area between the Laval nozzle tapered section 4 and the front swirl blade support body 8 according to different gas flow rates, start the drive motor 114 to drive the upper gear 111 to rotate, and the upper gear 111 drives the outer gear ring 113 meshing with it to rotate, and the outer gear ring 113 drives the other three gears 111 to rotate. At this time, the four gears 111 rotate synchronously, and the four gears 111 drive the four screws 108 to rotate synchronously. When the four screws 108 rotate in the four thread grooves 107, under the action of the threaded connection, the four L-shaped rods 106 are driven to slide horizontally to the left or right in the corresponding guide sleeves 109 respectively, and the four L-shaped rods 106 are used to drive the inner tube 100 to move horizontally to the left or right from four directions uniformly and synchronously. The inner tube 100 moves horizontally on the inner side of the outer tube 101 and the outer side of the circular tube 102, and the inner tube 100 drives the Laval nozzle tapered section 4 to move left and right to adjust the flow cross-sectional area formed between it and the front swirl blade support body 8. When the flow rate and pressure are constant, the critical flow rate is fixed. When the two increase, the critical flow rate becomes larger, and the critical radius also increases, that is, the flow position radius. The flow space between the Laval nozzle tapered section 4 and the front swirl blade support body 8 is variable, so as to adapt to different gas flow rates. Specifically, when the flow rate increases, the Laval nozzle tapered section 4 moves backward, and when the flow rate decreases, the Laval nozzle tapered section 4 migrates, so as to achieve a flexible application effect with adjustable flow rate and improve the flexibility of use.

[0029] Finally, it should be noted that the above is only a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art can still modify the technical solutions described in the aforementioned embodiments or replace some of the technical features therein with equivalents. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A supersonic cyclone separation device with adjustable flow, comprising a supersonic cyclone separation device body, wherein the supersonic cyclone separation device body comprises a steady flow contraction section (1), a pressure expansion separation section (2) and a central cyclone component, characterized in that: The steady flow contraction section (1) comprises a direct flow steady flow section (3) and a Laval nozzle convergence section (4) connected and fixed to the right side of the direct flow steady flow section (3); the pressure diffuser and separation section (2) comprises a Laval nozzle expansion section (5), an annular liquid collecting tank (6) and a secondary pressure diffuser section (7) connected in sequence from left to right; the central swirl component comprises a front swirl blade support body (8) arranged in the direct flow steady flow section (3); a plurality of front swirl blades (9) fixedly connected to the outside of the front swirl blade support body (8); a rear swirl blade support body (10) fixed to the right side of the front swirl blade support body (8) and located in the Laval nozzle expansion section (5); and a rear swirl blade (11) fixed to the outside of the rear swirl blade support body (10).

2. The flow-adjustable supersonic cyclone separation device according to claim 1, characterized in that: A linkage type four-point uniform telescopic mechanism is installed between the Laval nozzle convergent section (4) and the Laval nozzle expansion section (5), and the linkage type four-point uniform telescopic mechanism comprises an inner tube (100) connected and fixed to the right end of the Laval nozzle convergent section (4), an outer tube (101) is provided on the outer sealing sliding sleeve of the inner tube (100), and the outer tube (101) is fixedly sleeved on the outer side of the Laval nozzle expansion section (5), an annular groove (103) with an opening on the right side is provided on the inner side of the inner tube (100), and a circular tube (102) fixedly connected to the left end of the Laval nozzle expansion section (5) is provided in the sealing sliding sleeve inside the annular groove (103), and a threaded transverse guide drive assembly for driving the inner tube (100) to move laterally is fixedly connected to the top, bottom, front side and rear side of the outer tube (101), and a linkage rotary drive assembly for driving four threaded transverse guide drive assemblies to rotate synchronously is sleeved on the outer side of the outer tube (101).

3. The flow-adjustable supersonic cyclone separation device according to claim 1, characterized in that: The threaded transverse guide drive assembly comprises a guide sleeve (109), the top, bottom, front side and rear side of the outer tube (101) are respectively fixedly connected to the corresponding guide sleeves (109), the top, bottom, front side and rear side of the inner tube (100) are all fixedly connected to L-shaped rods (106), the four L-shaped rods (106) are respectively slidably sleeved in the corresponding guide sleeves (109), the top, bottom, front side and rear side of the outer tube (101) are all provided with screw rods (108), and the four L-shaped rods (106) are respectively threadedly sleeved on the corresponding screw rods (108).

4. The flow-adjustable supersonic cyclone separation device according to claim 3, characterized in that: The linked rotary drive assembly comprises a round box (110) fixedly sleeved on the outside of the outer tube (101) and an annular cover plate (112); the annular cover plate (112) is fixedly connected to the right side of the round box (110); the round box (110) is rotatably sleeved on four screw rods (108); the right ends of the four screw rods (108) are fixedly connected to gears (111) located in the round box (110); the four gears (111) are meshed with an outer gear ring (113) rotatably sleeved on the outside of the outer tube (101); and a driving motor (114) whose output shaft is fixedly connected to the right side of the upper gear (111) is fixedly installed on the top right side of the annular cover plate (112).

5. The flow-adjustable supersonic cyclone separation device according to claim 1, characterized in that: The outer tube (101) is provided with a first sealing ring (105) in the adhesive sleeve, and the inner side of the first sealing ring (105) is slidably connected to the outer side of the inner tube (100).

6. The flow-adjustable supersonic cyclone separation device according to claim 1, characterized in that: A second sealing ring (104) is provided in the adhesive sleeve inside the annular groove (103), and the inner side of the second sealing ring (104) is slidably connected to the outer side of the circular tube (102).

7. The flow-adjustable supersonic cyclone separation device according to claim 3, characterized in that: The right end of the L-shaped rod (106) is provided with a thread groove (107) threadedly connected to the corresponding screw rod (108).

8. The flow-adjustable supersonic cyclone separation device according to claim 3, characterized in that: An anti-slip block (115) is fixedly connected to the inner wall of the L-shaped rod (106) on the side away from the outer tube (101), and the anti-slip block (115) is located on the right side of the corresponding guide sleeve (109).

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