A supersonic cyclone condensation separation device with a nozzle having an internal corrugated structure

Abstract

The present invention discloses a supersonic cyclone condensation separation device with a nozzle having an internal corrugated structure, belonging to the technical field of gas-liquid two-phase flow separation. The supersonic cyclone condensation separation device comprises: a cyclone generating section, a supersonic nozzle section, a supersonic deceleration section, and a subsonic deceleration diffuser section, all arranged coaxially and fixedly; axial flow guide vanes, a condensate collection chamber, and a central guide cone; axial flow guide vanes fixedly assembled with the central guide cone within the cyclone generating section; internal corrugations arranged along the axis of the inner wall surface of the supersonic nozzle section, with the inner diameter of the internal corrugations at the outlet section being equal to the inner diameter of the supersonic deceleration section; and an oblique inlet provided at the entrance of the condensate collection chamber, with the internal corrugations of the outlet section of the supersonic nozzle section communicating with the oblique inlet, so that condensate from the supersonic nozzle section enters the condensate collection chamber through the oblique inlet. This improves the reliability and adaptability of the separator to working conditions.

Description

Technical Field

[0001] The present invention belongs to the technical field of gas-liquid two-phase flow separation, and more specifically, relates to a supersonic cyclone condensation separation device having a nozzle with an inner corrugated structure. Background Art

[0002] Compared with conventional separation technologies such as gravity separation, inertial separation and membrane separation, supersonic cyclone separation technology has the advantages of good compactness, simple structure and high removal depth of wet components. Since the technical principle was proposed, it has attracted the attention of many research institutions and scholars at home and abroad. It is a new gas-liquid two-phase separation technology with great application prospects.

[0003] Compared to conventional gas-liquid two-phase flow separation technologies, supersonic cyclonic separation integrates phase change condensation, cyclonic separation, and expansion and pressure recovery processes, making the separation device very compact. However, there are also problems such as the internal flow field being highly sensitive to external boundary conditions and the susceptibility of shock waves to form within the condensate separation section. To this end, patent CN200810011258.6 proposes a conical core supersonic cyclone separation device, which changes the complex nozzle inner surface profile processing into the outer surface processing of the core cone, reducing the processing complexity of the nozzle section; patents CN201210229819.6 and CN201710468051.0 respectively use movable cone core and secondary reflow schemes to further enhance the working condition adaptability and condensate separation ability of the supersonic cyclone device; patent CN201610578253.6 proposes a supersonic cyclone separator structure, constructs a secondary throat diffuser downstream of the supersonic nozzle, and uses multi-porous tapered sections and multi-porous gradually expanding sections to control the shock wave position in the separation zone downstream of the supersonic nozzle. Constrained by the principle of supersonic cyclone separation, a drainage device must be installed at the supersonic nozzle outlet, but the flow field at the supersonic outlet is still in a supersonic state. The change of the flow field boundary conditions at the supersonic nozzle outlet will interfere with the flow field and cause shock waves, causing the condensed droplets to evaporate and gasify again, affecting the final effect of supersonic cyclone separation.

[0004] The measures adopted in the prior art have stabilized the working flow field of the supersonic cyclone separator to a certain extent, but the shock wave phenomenon at the discharge port cannot be completely avoided. The prior art still has problems with secondary evaporation and excessive pressure loss in supersonic cyclone separation. Summary of the Invention

[0005] In view of the defects of the related art, the purpose of the present invention is to provide a supersonic cyclone condensation separation device with an internal corrugated structure in the nozzle, aiming to solve the problems of secondary evaporation and excessive pressure loss in supersonic cyclone separation.

[0006] To achieve the above-mentioned object, the present invention provides a supersonic swirl condensation separation device with a nozzle having an internal corrugated structure, comprising: a swirl generating section, a supersonic nozzle section, a supersonic deceleration section, a subsonic deceleration diffuser section, axial flow guide vanes, a condensate collection chamber, and a central guide cone;

[0007] The swirl generating section, supersonic nozzle section, supersonic deceleration section and subsonic deceleration diffuser section are coaxially arranged and fixedly connected;

[0008] The swirl generating section is arranged at the front end of the supersonic nozzle section, and the swirl generating section is provided with an axial flow guide vane fixedly assembled with the central guide cone;

[0009] The supersonic deceleration section is arranged at the rear end of the supersonic nozzle section, the inner wall surface of the supersonic nozzle section is arranged with inner corrugations along the axis, and the inner diameter of the inner corrugations of the outlet cross section of the supersonic nozzle section is equal to the inner diameter of the supersonic deceleration section;

[0010] The condensate collection chamber is arranged around the outside of the inlet of the supersonic deceleration section, and the condensate collection chamber is coaxially arranged with the supersonic deceleration section; an oblique inlet is provided at the inlet of the condensate collection chamber, and the inner corrugation of the outlet cross-section of the supersonic nozzle section is connected to the oblique inlet of the condensate collection chamber, so that the condensate of the supersonic nozzle section enters the condensate collection chamber through the oblique inlet.

[0011] Optionally, a condensate discharge outlet is provided at the lower end portion of the condensate collection chamber in the vertical direction, for discharging the condensate in the condensate collection chamber.

[0012] Optionally, the outer side of the axial flow guide vane is fixedly mounted relative to the inner side of the swirl generating section pipe wall;

[0013] The guide deflection angle of the axial flow guide blade is 5° to 30°.

[0014] Optionally, the front end and the rear end of the central guide cone both adopt a conical guide structure, the front end angle of the central guide cone is 20° to 40°, and the rear end angle of the central guide cone is 40° to 60°.

[0015] Optionally, the supersonic nozzle section includes a converging section and a diverging section connected together, and the airflow flow cross-section in the supersonic nozzle section changes in a converging-diverging manner; the inner corrugation is arranged on the inner wall surface of the diverging section of the supersonic nozzle section.

[0016] Optionally, the inner corrugations are continuous inner corrugations or spaced inner corrugations.

[0017] Optionally, the corrugated structure in the wall of the diverging section of the supersonic nozzle is a sinusoidal wave, satisfying the following equations (1) to (3):

[0018]

[0019] s=r·θ (3)

[0020] Where A is the oscillation amplitude of the inner corrugation structure, ω is the oscillation wave number of the inner corrugation structure, is the phase angle, r and θ are the average radius and central angle of the supersonic nozzle expansion section, respectively.

[0021] Optionally, the oscillation amplitude A of the inner corrugated structure has a value range of (1% to 5%)r;

[0022] The value range of the oscillation wave number ω of the inner corrugated structure is 5% to 10%.

[0023] Optionally, the subsonic deceleration diffuser section consists of a straight section and an expansion section, the straight section is inside the condensate collection chamber, and the expansion section is outside the condensate collection chamber.

[0024] Optionally, the half angle of the expansion section is 5° to 15°.

[0025] Compared with the prior art, the above technical solutions conceived by the present invention can achieve the following beneficial effects:

[0026] 1. The present invention provides a supersonic cyclone condensation separation device with an inner corrugated structure on a nozzle. By arranging the inner corrugated structure on the inner wall surface of the supersonic nozzle section, on the one hand, a condensate discharge channel is constructed in the supersonic nozzle section, so as to prevent the high-speed rotating airflow in the supersonic nozzle section from sucking up the condensate film, causing the liquid film to break, which is not conducive to the discharge of the condensate; on the other hand, the inner diameter of the inner corrugation at the tail end of the supersonic nozzle section is equal to the inner diameter of the deceleration diffuser inlet (supersonic deceleration section), so that the intersection section of the supersonic nozzle section and the downstream deceleration diffuser section has a smooth transition without a significant sudden change in the flow channel area, thereby minimizing the influence of the change of the boundary conditions at this location on the supersonic flow field, thereby weakening the shock wave phenomenon caused by the geometric boundary sudden change at the discharge port of the supersonic cyclone separator, solving the problems of re-evaporation of condensate droplets and excessive gasification pressure loss caused by the shock wave, and improving the reliability and working condition adaptability of the supersonic cyclone separator.

[0027] 2. The present invention provides a supersonic cyclone condensation separation device with an internal corrugated structure in the nozzle. The internal corrugated opening of the outlet cross section of the supersonic nozzle section is connected to the oblique inlet of the condensate collection chamber. The condensate flows out of the supersonic nozzle section through the condensate discharge channel constructed by the internal corrugated structure and enters the condensate collection chamber through the oblique inlet, which does not affect the discharge of the device while further weakening the shock wave phenomenon at the discharge outlet. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 This is a structural schematic diagram of a supersonic cyclone condensation separation device with an internal corrugated nozzle structure provided by an embodiment of the present invention;

[0029] Figure 2 Schematic diagram of the structure of the supersonic nozzle section and the corrugations in its cross section in an embodiment of the present invention;

[0030] Figure 3 Schematic diagram of the internal corrugation structure of the present invention, wherein (a) is continuous internal corrugation and (b) is spaced internal corrugation.

[0031] In the above drawings, the same reference numerals have the same meanings, and the reference numerals in the drawings are: 1-supersonic swirler inlet, 2-swirl generating section, 3-axial flow guide vane, 4-supersonic nozzle section, 5-condensate collection chamber, 6-supersonic deceleration section, 7-subsonic deceleration diffuser section, 8-condensate discharge outlet, 9-bevel inlet, 10-center guide cone. DETAILED DESCRIPTION

[0032] In order to make the objectives, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely for the purpose of explaining the present invention and are not intended to limit the present invention. In addition, the technical features involved in the various embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.

[0033] The contents involved in the above embodiment are described below in conjunction with a preferred embodiment.

[0034] In the prior art, there are still problems of secondary evaporation and excessive pressure loss in supersonic cyclone separation. In order to further weaken the shock wave phenomenon at the discharge port and solve the problems caused by the shock wave phenomenon, a supersonic cyclone condensation separation device with an internal corrugated structure in the nozzle is proposed as provided in an embodiment of the present invention.

[0035] like Figure 1 As shown, a supersonic swirl condensation separation device with an internal corrugated nozzle structure includes: a swirl generating section 2, a supersonic nozzle section 4, a supersonic deceleration section 6, a subsonic deceleration diffuser section 7, an axial flow guide vane 3, a condensate collection chamber 5 and a central guide cone 10;

[0036] The swirl generating section 2, the supersonic nozzle section 4, the supersonic deceleration section 6 and the subsonic deceleration diffuser section 7 are coaxially arranged and fixedly connected;

[0037] The swirl generating section 2 is provided at the front end of the supersonic nozzle section 4, and an axial flow guide vane 3 fixedly assembled with the central guide cone 10 is arranged in the swirl generating section 2;

[0038] The supersonic deceleration section 6 is provided at the rear end of the supersonic nozzle section 4. The inner wall surface of the supersonic nozzle section 4 is provided with inner corrugations along the axis. The inner diameter of the inner corrugations at the outlet cross section of the supersonic nozzle section 4 is equal to the inner diameter of the supersonic deceleration section 6.

[0039] The condensate collecting chamber 5 is arranged around the outside of the inlet of the supersonic deceleration section 6, and the condensate collecting chamber 5 and the supersonic deceleration section 6 are coaxially arranged; an oblique inlet 9 is provided at the inlet of the condensate collecting chamber 5, and the inner corrugation of the outlet cross-section of the supersonic nozzle section 4 is connected to the oblique inlet 9 of the condensate collecting chamber 5, so that the condensate of the supersonic nozzle section 4 enters the condensate collecting chamber 5 through the oblique inlet 9.

[0040] Optionally, the supersonic nozzle section 4 includes a converging section and a diverging section connected together, and the airflow flow cross-section in the supersonic nozzle section changes in a converging-diverging manner; the inner corrugation is arranged on the inner wall surface of the diverging section of the supersonic nozzle section.

[0041] Reference Figure 1 When a supersonic cyclone condensation separation device with an inner corrugated structure provided by an embodiment of the present invention starts working, the moist airflow enters the supersonic cyclone condensation separation device through the supersonic cyclone separator inlet 1, and the moist airflow flows in the device and forms an axial cyclone airflow under the guidance of the axial flow guide vanes 3 installed on the central guide cone 10; according to the law of conservation of angular momentum, the axial cyclone airflow gradually forms a strong cyclone field at the inlet of the supersonic nozzle section 4 and then enters the gradually expanding section of the supersonic nozzle section 4, and at the supersonic The expansion of the wet gas in the diverging section of the nozzle section 4 is accelerated, causing both the temperature and pressure to drop significantly. When the airflow temperature drops below the saturation temperature, the wet components therein condense into condensate droplets, which rotate and adhere to the wall under the action of a strong vortex field and enter the inner corrugated structure provided on the inner wall surface of the diverging section of the supersonic nozzle section 4. Under the shear action of the airflow, the condensate flows downstream along the inner corrugated grooves and enters the condensate collection chamber 5 through the oblique inlet 9 at the entrance of the condensate collection chamber 5, effectively avoiding the secondary entrainment and fragmentation of the rotating airflow.

[0042] Optionally, a condensate discharge port 8 is provided at the lower end portion of the condensate collecting chamber 5 in the vertical direction, for discharging the condensate in the condensate collecting chamber.

[0043] Since the inner diameter of the corrugation at the outlet of the supersonic nozzle section 4 is guaranteed to be consistent with the inner diameter of the inlet of the supersonic deceleration section 6, the cross-sectional area of ​​the airflow does not change significantly, so the aerodynamic shock wave phenomenon caused by the change of the supersonic flow field boundary can be greatly weakened, and the secondary evaporation of condensate caused by the shock wave heating can be avoided. After the dehumidified dry gas is decelerated to subsonic speed by the oblique shock wave in the supersonic deceleration section 6, it enters the subsonic deceleration and expansion section 7 for further deceleration and expansion, and the total pressure is restored as much as possible.

[0044] Optionally, the outer side of the axial flow guide vane is fixedly mounted relative to the inner side of the swirl generating section pipe wall;

[0045] The guide deflection angle of the axial flow guide blade is 5° to 30°.

[0046] The axial flow guide vane needs to consider the guide rotation effect and flow resistance loss. According to experiments, when the guide deflection angle ranges from 5° to 30°, a relatively optimal state can be achieved in terms of guide rotation and reducing flow resistance loss.

[0047] Optionally, the front end and the rear end of the central guide cone both adopt a conical guide structure, the front end angle of the central guide cone is 20° to 40°, and the rear end angle of the central guide cone is 40° to 60°.

[0048] When the front and rear angles are too large, flow separation will occur, which will reduce the quality of the subsequent flow field and increase flow losses. The above-mentioned angle range of the front and rear angles can avoid causing excessive flow separation and reduce friction losses.

[0049] In the above embodiment, optionally, Figure 3 As shown, the inner corrugations are continuous inner corrugations or spaced inner corrugations. Figure 3 (a) is a continuous internal corrugation. Figure 3 Middle (b) shows the internal ripples with interval distribution.

[0050] like Figure 2 As shown, the inner corrugation takes a sinusoidal wave as an example, and provides a schematic cross-sectional structure diagram of the supersonic nozzle section 4 in the form of a circumferential arrangement of the inner corrugation.

[0051] The corrugated structure in the wall of the diverging section of the supersonic nozzle is a sinusoidal wave, satisfying the following equations (1) to (3):

[0052]

[0053] s=r·θ (3)

[0054] Where A is the oscillation amplitude of the inner corrugation structure, ω is the oscillation wave number of the inner corrugation structure, is the phase angle, r and θ are the average radius and central angle of the supersonic nozzle expansion section, respectively.

[0055] In order to avoid the influence of the inner corrugation structure on the supersonic airflow in the supersonic nozzle section 4, the amplitude A of the inner corrugation should not be too large, but the amplitude A of the inner corrugation should not be too small to avoid congestion of condensate discharge. Therefore, the amplitude A of the inner corrugation is approximately 1% to 5% of the cross-sectional radius of the supersonic nozzle section 4, that is, the value range of A is (1% to 5%) r, and the value range of the oscillation wave number ω of the inner corrugation structure is 5% to 10%.

[0056] Optionally, the subsonic deceleration diffuser section consists of a straight section and an expansion section, the straight section is inside the condensate collection chamber, and the expansion section is outside the condensate collection chamber.

[0057] Optionally, the half angle of the expansion section is 5° to 15°.

[0058] The subsonic deceleration diffuser section is divided into a straight section and an expansion section. The straight section generates a weak oblique shock wave to decelerate the supersonic flow to subsonic speed, and the subsequent expansion section can further decelerate the subsonic flow. This setting can recover part of the gas kinetic energy and reduce the pressure loss of the entire device; the angle range selected for the half-angle of the expansion section can prevent flow separation, and its effect is the same as the angle setting effect of the front end angle and the rear end angle of the aforementioned central guide cone.

[0059] The present invention provides a supersonic cyclone condensation separation device with a nozzle having an inner corrugated structure. The inner corrugated structure is constructed on the inner wall surface of the supersonic nozzle section to form a condensate transport channel, while avoiding the deposited condensate in the inner corrugations from being affected by the secondary suction of the rotating airflow in the central area of ​​the supersonic nozzle section. In addition, the concave and convex characteristics of the inner corrugated structure are cleverly utilized to construct an oblique inlet of the condensate collection chamber between the supersonic nozzle section, the supersonic deceleration section and the condensate collection chamber. At the same time, no significant sudden change in flow channel area occurs at the outlet of the supersonic nozzle section and the inlet of the supersonic deceleration zone, thereby fundamentally eliminating the shock wave phenomenon at the discharge port of the traditional supersonic cyclone separation device, and further improving the working condition adaptability and reliability of the device.

[0060] It will be easily understood by those skilled in the art that the above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A supersonic cyclone condensation separation device with a nozzle having an internal corrugated structure, characterized in that: include: Swirl generating section, supersonic nozzle section, supersonic deceleration section, subsonic deceleration diffuser section, axial flow guide vanes, condensate collection chamber and central guide cone; The swirl generating section, supersonic nozzle section, supersonic deceleration section and subsonic deceleration diffuser section are coaxially arranged and fixedly connected; The swirl generating section is arranged at the front end of the supersonic nozzle section, and the swirl generating section is provided with an axial flow guide vane fixedly assembled with the central guide cone; The supersonic deceleration section is arranged at the rear end of the supersonic nozzle section, the inner wall surface of the supersonic nozzle section is arranged with inner corrugations along the axis, and the inner diameter of the inner corrugations of the outlet cross section of the supersonic nozzle section is equal to the inner diameter of the supersonic deceleration section; The condensate collection chamber is arranged around the outside of the inlet of the supersonic deceleration section, and the condensate collection chamber is coaxially arranged with the supersonic deceleration section; an oblique inlet is provided at the inlet of the condensate collection chamber, and the inner corrugation of the outlet cross-section of the supersonic nozzle section is connected to the oblique inlet of the condensate collection chamber, so that the condensate of the supersonic nozzle section enters the condensate collection chamber through the oblique inlet.

2. The supersonic cyclone condensation separation device according to claim 1, characterized in that: A condensate discharge port is provided at the lower end portion of the condensate collection chamber in the vertical direction, for discharging the condensate in the condensate collection chamber.

3. The supersonic cyclone condensation separation device according to claim 1, characterized in that: The outer side of the axial flow guide blade is fixedly installed relative to the inner side of the swirl generating section pipe wall; The guide deflection angle of the axial flow guide blade is 5° to 30°.

4. The supersonic cyclone condensation separation device according to claim 1, characterized in that: The front end and the rear end of the central guide cone both adopt a conical guide structure. The front end angle of the central guide cone is 20° to 40°, and the rear end angle of the central guide cone is 40° to 60°.

5. The supersonic cyclone condensation separation device according to claim 1, characterized in that: The supersonic nozzle section includes a gradually converging section and a gradually expanding section connected together, and the airflow flow cross section in the supersonic nozzle section changes in a gradually converging-gradually expanding manner; the inner corrugation is arranged on the inner wall surface of the gradually expanding section of the supersonic nozzle section.

6. The supersonic cyclone condensation separation device according to claim 5, characterized in that: The inner corrugations are continuous inner corrugations or spaced inner corrugations.

7. The supersonic cyclone condensation separation device according to claim 6, characterized in that: The corrugated structure in the wall of the diverging section of the supersonic nozzle is a sinusoidal wave, satisfying the following equations (1) to (3): s=r·θ (3) Where A is the oscillation amplitude of the inner corrugation structure, ω is the oscillation wave number of the inner corrugation structure, is the phase angle, r and θ are the average radius and central angle of the supersonic nozzle expansion section, respectively.

8. The supersonic cyclone condensation separation device according to claim 7, characterized in that: The oscillation amplitude A of the inner corrugated structure has a value range of (1% to 5%)r; The value range of the oscillation wave number ω of the inner corrugated structure is 5% to 10%.

9. The supersonic cyclone condensation separation device according to claim 1, characterized in that: The subsonic deceleration diffuser section consists of a straight section and an expansion section, the straight section is inside the condensate collection chamber, and the expansion section is outside the condensate collection chamber.

10. The supersonic cyclone condensation separation device according to claim 9, characterized in that: The half angle of the expansion section is 5° to 15°.

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