CN202315566U - Gas supersonic speed condensation and cyclone separation spray pipe - Google Patents

Abstract

The utility model relates to a gas supersonic speed condensation and cyclone separation spray pipe which is mainly composed of a central body, a cyclone vane, a contraction section and an expansion section. The gas supersonic speed condensation and cyclone separation spray pipe is mainly applied to gas purification, and is particularly applied to the fields of natural gas dewatering and heavy hydrocarbon separation. According to the utility model, the cyclone vane of the gas supersonic speed condensation and cyclone separation spray pipe is designed with an ellipse vane method, thereby effectively strengthening cyclone; eddy dissipation is effectively reduced because of the central body; a contraction section curve can ensure that airflow can be stably quickened to sound velocity; and the expansion section is in a diverging structure, and the simple straight-line design of the similar device is abandoned; the curve design of the gas supersonic speed condensation and cyclone separation spray pipe can avoid the influence of expansion wave, and the aerodynamic performance is better; in the spray pipe, the speed of the airflow is supersonic speed, and retention time is very short, so that no hydrate is formed, and any chemical agents and relevant recovery systems do not need to be added; and the gas supersonic speed condensation and cyclone separation spray pipe is provided with a nonmotile part which supports unmanned operation. Thus the gas supersonic speed condensation and cyclone separation spray pipe has the advantages of compact structure and small occupied space, is especially suitable for development of boundary, desert and offshore oil-gas fields, and has wide application prospect.

Description

A kind of gas supersonic speed is condensed and the cyclonic separation jet pipe

Technical field:

The present invention relates to a kind of gas supersonic speed and condense and the cyclonic separation jet pipe, be mainly used in gas purification, particularly gas dehydration such as separates at the field with heavy hydrocarbon.

Background technology:

Traditional gas dewatering technology mainly contains cooling method, absorption process, absorption method and membrane separation process.The principle that cooling method utilizes the water content of gas to reduce along with the rising of decrease of temperature or pressure realizes gas dewatering, mainly comprises direct cooling method, pressurization cooling method, swell refrigeration method and vapour compression refrigeration method etc.In order to prevent to form hydrate, need heating system or needs to add hydrate inhibitor and corresponding recovery system.Absorption process is to utilize gas this principle of different solubility in liquid to realize gas dewatering, and this class methods technological process is complicated, and equipment is many, and system is huge.Absorption method is a kind of surface of solids transport phenomenon; It utilizes the porous solid absorbent to make hydrone under the effect of molecular attraction or chemical bonding force, be attracted to the surface of solids; Thereby reach the purpose of gas dewatering, its major defect is that equipment is more, and investment and operating cost are high.The principle of membrane separation process is under pressure-driven; By each component in the gas the lip-deep adsorption capacity of polymeric membrane and in film different permeabilities carry out gas dewatering; But membrane separation process is applied in the existing industry on a large scale, has problems such as one-time investment is big.

The supersonic speed cyclone separation process is a new technology that is applied to gas dehydration in recent years; The external Shell Oil Company have carried out relevant research work respectively with the ENGO oil company; Mainly develop " TwisterI " first generation, " TwisterII " second generation and " 3S " three kinds of supersonic speed cyclone separation devices, and applied for multinomial patent.Patent US 6513345B1, US 6524368B2, US 3773825B2, US 6962199B1; US 7261766B2; The core of US 7318849B2, US 7494535B2, WO2003/092850A1, WO 2004/020074A1 etc. is aerofoil profile to be installed in the supersonic speed section produce stronger eddy flow, but because the conversion of speed occurs under the supersonic speed condition, is easy to generate shock wave after the aerofoil profile; Destroy the low-temp low-pressure environment, reduce the separative efficiency of supersonic speed separator.U.S. Pat 7357825B2, US 2008/0196581A1 and US 2010/0147021A1 are arranged in swirl-flow devices before the jet pipe; Help obtaining eddy flow field preferably; But the processing and the installation difficulty of device are big; Especially the concentric degree of centerbody and shell is difficult to guarantee, thereby causes the instability of eddy flow field easily.Patent EP 1131588B1, US 6372019B1 and US 2010/0147023A1 are installed in rotational flow generator before the Laval jet pipe, and shock wave is controlled easily, but rotation gas after getting into the Laval jet pipe whirlpool dissipation takes place easily, has reduced separative efficiency.

Domestic China Petroleum Univ. (East-China), Beijing University of Technology, Dalian University of Technology, Xi'an Communications University and BJ University of Aeronautics & Astronautics have carried out relevant research work to the supersonic speed cyclone separation process.Chinese patent ZL 200410074338.8 adopts swirl-flow devices to be installed in the mode of supersonic speed section, is prone to produce shock wave; Application number 200810224499.9 patents and application number 200910093744.1 patents are installed in high-speed flow area with swirl vane, and the fluid flow losses are big; Patent ZL200610043158.2, application number 200610105199.X and ZL 200910023458.8 etc. exist rotation gas the problem that dissipates in the whirlpool take place easily; Patent ZL200810011258.6 takes the fluid tangential to get into the form of separator, and the pressure loss is bigger, has reduced total pressure recovery efficient; The patent structure of application number 200910081813.7 is similar with " TwisterII " separator, but the centering of its eddy current control volume is difficult more, is difficult to guarantee coaxial eddy flow; Be provided with the shock wave compressional zone after the application number 200910024347.9 patent supersonic speed sections of Xi'an Communications University, the supersonic speed compression is decelerated to subsonic speed, but volatilization again takes place in drop easily in the subsonic area, reduce the separative efficiency of separator; The essence of application number 200910084262.X patent is to increase treating capacity with the parallel connection of a plurality of supersonic speed separator tube; Application number 201010597341.3 patents have designed the supersonic speed cyclone separator of a plurality of outlets, have increased the gas entrainment of liquid outlet, and a plurality of outlet also is difficult to use at the scene.

Summary of the invention:

The objective of the invention is to overcome the deficiency of above-mentioned prior art, propose that a kind of compact conformation, eddy flow ability are strong, stable and reliable operation, and the gas supersonic speed that can effectively control the dilatational wave in the supersonic speed expansionary channel condense and the cyclonic separation jet pipe.

For achieving the above object, the technical scheme that the present invention adopts is: comprise straight length, centerbody, swirl vane, contraction section, expansion segment, entrance and exit, it is characterized in that: by the contraction-expanding nozzle of contraction section, expansion segment and centerbody looping; Contraction section is a tapered configuration, and expansion segment is the flaring structure; The swirl vane upper end is fixedly connected with the straight length internal face, and lower end and centerbody surface are fixedly connected.

Gas supersonic speed according to the invention condense with the cyclonic separation jet pipe in, the contraction-expanding nozzle of contraction section, expansion segment and centerbody looping forms subsonic speed contracted channel, throat and supersonic speed expansionary channel; Gas steadily quickens in contracted channel, reaches the velocity of sound in throat, in expansionary channel, reaches supersonic speed, forms low-temp low-pressure, causes condensing of water and heavy hydrocarbon component.

Gas supersonic speed according to the invention condense with the cyclonic separation jet pipe in, contraction section is a tapered configuration, its contour curve designs according to following curvilinear equation:

$D_x=D_{\mathrm{cr}}+(D_1-D_{\mathrm{cr}})[1-10{\left(\frac{x}{L_s}\right)}^3+15{\left(\frac{x}{L_s}\right)}^4-6{\left(\frac{x}{L_s}\right)}^5]$

Aforesaid equation is the x axle with the axis of contraction section, is the origin of coordinates with the center of circle of porch, D ₁And D _CrBe respectively the inlet diameter and the outlet diameter of contraction section, D _xDiameter of section for any x place; L _sBe contraction section length; Compare with the method for designing that generally contraction section is designed to straight line, this contraction section curve can guarantee effectively that air-flow steadily accelerates to the velocity of sound.

Gas supersonic speed according to the invention condense with the cyclonic separation jet pipe in, expansion segment is a flaring structure, its contour curve designs according to following curvilinear equation:

$D_{\mathrm{kx}}=\frac{D_{k1}}{\sqrt{1-[1-{\left(\frac{D_{k1}}{D_{k2}}\right)}^2]\frac{{[1-{\left(\frac{L_x-x}{L_k}\right)}^2]}^2}{{[1+\frac{1}{3}{\left(\frac{L_k-x}{L_k}\right)}^2]}^3}}}$

Aforesaid equation is the x axle with the axis of expansion segment, is the origin of coordinates with the center of circle of porch, D _K1And D _K2Be respectively the inlet diameter and the outlet diameter of expansion segment, D _K1=D _Cr, D _KxDiameter of section for any x place; L _kLength for expansion segment; Expansion segment adopts this curve design can avoid the influence of dilatational wave in the supersonic speed expansionary channel effectively, guarantees the stable of eddy flow field, and aeroperformance is better, and cyclonic separation efficient is higher.

Gas supersonic speed according to the invention condense with the cyclonic separation jet pipe in, centerbody occupy the jet pipe center, comprises semiellipsoid (11), straight section (12), converging transition (13) and cylindrical section (14); The length L 1 of straight section is: 0.5D _Z1≤L1≤5D _Z1, D _Z1Diameter for straight section; The contour curve of converging transition designs according to following curvilinear equation:

$D_{\mathrm{zx}}=D_{\mathrm{zcr}}+(D_{z1}-D_{\mathrm{zcr}})[1-10{\left(\frac{x}{L_z}\right)}^3+15{\left(\frac{x}{L_z}\right)}^4-6{\left(\frac{x}{L_z}\right)}^5]$

Aforesaid equation is the x axle with the axis of converging transition, is the origin of coordinates with the center of circle of porch, D _ZcrBe the outlet diameter of converging transition, D _ZxDiameter of section for any x place; L _zBe converging transition length, L _z=L _sThe inlet of converging transition and the inlet of contraction section are on the same cross section; According to angular momentum conservation law, the existence of converging transition can be strengthened eddy flow effectively.

The diameter of cylindrical section equals the outlet diameter of converging transition, and the length of cylindrical section equals the length L of expansion segment _kThe existence of cylindrical section can guarantee the coaxial eddy flow of fluid in the supersonic speed runner effectively, prevents the generation that dissipates in the whirlpool, thereby stablizes eddy flow field, strengthens and separates the ability of condensing drop, further improves separative efficiency.

Gas supersonic speed according to the invention condense with the cyclonic separation jet pipe in, swirl vane is an elliptical blade, circumferentially evenly is installed in the surface of straight section, the major semiaxis of swirl vane and semi-minor axis radius are respectively R1 and R2, R1=L1, R2≤R1, lobe numbers is 3～24; The swirl vane eddy flow ability of the type is strong, under the synergy of centerbody, can effectively strengthen and stable eddy flow, improves the separative efficiency of device.

The invention has the beneficial effects as follows: the swirl vane that circumferentially evenly is installed in the straight section surface has changed the flow direction of gas, and a part of axial velocity is converted into circumferential speed, makes gas get into jet pipe with the mode of eddy flow; And because the contracted channel area of annular reduces gradually, according to angular momentum conservation law, eddy flow will be strengthened greatly; Swirling eddy steadily quickens in the contracted channel of annular, reaches the velocity of sound in throat; Because the area of supersonic speed expansionary channel increases, air-flow forms low-temp low-pressure with continuing to be expanded to supersonic speed, and moisture or the water in the natural gas and heavy hydrocarbon component in the gas are condensed, and produces a large amount of drops that condenses; At this moment, the existence of centerbody can guarantee the coaxial eddy flow of supersonic speed expansionary channel inner fluid effectively, the whirlpool can not take place dissipate, and the drop that huge centrifugal force will condense gets rid of to wall, realizes gas-liquid separation.The existence of cylindrical section can guarantee the coaxial eddy flow of fluid in the supersonic speed runner effectively, prevents the generation that dissipates in the whirlpool, thereby stablizes eddy flow field, strengthens and separates the ability of condensing drop, further improves separative efficiency.

Description of drawings:

Fig. 1 is an overall structure sketch map of the present invention.

Fig. 2 is a centerbody structural representation of the present invention.

Fig. 3 is a swirl vane sketch map of the present invention.

Among the figure: 1-straight length, 2-centerbody, 3-swirl vane, 4-contraction section, 5-expansion segment, 6-outlet, 7-supersonic speed expansionary channel, 8-throat, 9-subsonic speed contracted channel, 10-inlet, 11-semiellipsoid, 12-straight section, 13-converging transition, 14-cylindrical section.

The specific embodiment:

Below in conjunction with accompanying drawing design feature of the present invention and operation principle are described further.

Like Fig. 1, Fig. 2 and shown in Figure 3, the present invention is mainly by straight length 1, centerbody 2, swirl vane 3, contraction section 4, expansion segment 5, inlet 10 with export 6 and constitute; Contraction-the expanding nozzle of contraction section 4, expansion segment 5 and centerbody 2 loopings forms subsonic speed contracted channel 9, throat 8 and supersonic speed expansionary channel 7; Swirl vane 3 upper ends and straight length 1 internal face are fixedly connected, and lower end and centerbody 2 surfaces are fixedly connected.

As shown in Figure 1, contraction section 4 of the present invention is a tapered configuration, and its contour curve designs according to following curvilinear equation:

$D_x=D_{\mathrm{cr}}+(D_1-D_{\mathrm{cr}})[1-10{\left(\frac{x}{L_s}\right)}^3+15{\left(\frac{x}{L_s}\right)}^4-6{\left(\frac{x}{L_s}\right)}^5]$

Aforesaid equation is the x axle with the axis of contraction section 4, is the origin of coordinates with the center of circle of contraction section 4 porch, D ₁And D _CrBe respectively the inlet diameter and the outlet diameter of contraction section 4, D _xDiameter of section for any x place; L _sBe contraction section length.

Expansion segment 5 of the present invention is a flaring structure, and its contour curve designs according to following curvilinear equation:

$D_{\mathrm{kx}}=\frac{D_{k1}}{\sqrt{1-[1-{\left(\frac{D_{k1}}{D_{k2}}\right)}^2]\frac{{[1-{\left(\frac{L_x-x}{L_k}\right)}^2]}^2}{{[1+\frac{1}{3}{\left(\frac{L_k-x}{L_k}\right)}^2]}^3}}}$

Aforesaid equation is the x axle with the axis of expansion segment 5, is the origin of coordinates with the center of circle of expansion segment 5 porch, D _K1And D _K2Be respectively the inlet diameter and the outlet diameter of expansion segment 5, D _K1=D _Cr, D _KxDiameter of section for any x place; L _kLength for expansion segment 5.

As depicted in figs. 1 and 2, centerbody 2 of the present invention occupy the jet pipe center, with contraction section 4 and expansion segment 5 concentrics, comprises semiellipsoid 11, straight section 12, converging transition 13 and cylindrical section 14; The length L 1 of straight section 12 is: 0.5D _Z1≤L1≤5D _Z1, D _Z1Diameter for straight section 12; The contour curve of converging transition 13 designs according to following curvilinear equation:

$D_{\mathrm{zx}}=D_{\mathrm{zcr}}+(D_{z1}-D_{\mathrm{zcr}})[1-10{\left(\frac{x}{L_z}\right)}^3+15{\left(\frac{x}{L_z}\right)}^4-6{\left(\frac{x}{L_z}\right)}^5]$

Aforesaid equation is the x axle with the axis of converging transition 13, is the origin of coordinates with the center of circle of converging transition 13 porch, D _ZcrBe the outlet diameter of converging transition 13, D _ZxDiameter of section for any x place; L _zBe converging transition 13 length, L _z=L _sThe inlet of the inlet of converging transition 13 and contraction section 4 is on the same cross section.

The diameter of cylindrical section 14 equals the outlet diameter of converging transition 13, and the length of cylindrical section 14 equals the length L of expansion segment 5 _k

As shown in figures 1 and 3, swirl vane 3 of the present invention is an elliptical blade, circumferentially evenly is installed in the surface of straight section 12, and the major semiaxis of swirl vane 3 and semi-minor axis radius are respectively R1 and R2, R1=L1, and R2≤R1, lobe numbers is 3～24.

Gap between contraction section 4 of the present invention and the converging transition 13 constitutes subsonic speed contracted channel 9, like Fig. 1 and Fig. 2, and owing to adopt the design of particular curve equation, can guarantee that gas steadily quickens, and reaches the velocity of sound at throat 8 places in this runner; Gap between expansion segment 5 and the cylindrical section 14 forms supersonic speed expansionary channel 7, and gas is accelerated to supersonic speed in this runner, forms low-temp low-pressure, and water and heavy hydrocarbon begin to condense.

Referring to Fig. 1, Fig. 2 and Fig. 3, the area of subsonic speed contracted channel 9 of the present invention reduces gradually, and according to angular momentum conservation law, the eddy flow that is produced by swirl vane 3 will be strengthened; And the existence of centerbody can guarantee the coaxial eddy flow of fluid in supersonic speed expansionary channel 7 effectively, owing to abandoned in the past simple orthoscopic design in such device, curve design of the present invention can be avoided the influence of dilatational wave, and aeroperformance is better; Coaxial eddy flow in the supersonic speed expansionary channel 7 produces huge centrifugal force, and the drop that will condense gets rid of to wall, realizes gas-liquid separation, has improved separative efficiency.

Operation principle of the present invention is: gas gets into this jet pipe by inlet 10; Under the effect of swirl vane 3; Part axial velocity is converted into circumferential speed, and gas gets into subsonic speed contracted channel 9, throat 8, supersonic speed expansionary channel 7 with the form of eddy flow, and gas is expanded to supersonic speed; Form low-temp low-pressure, moisture or the water in the natural gas and heavy hydrocarbon in the gas are condensed; Coaxial eddy flows in the existence assurance supersonic speed expansionary channel 7 of centerbody 2 can not sent out into the whirlpool and dissipate, thereby make the liquid that condenses under strong eddy flow centrifugal field effect, be thrown toward tube wall, realize gas-liquid separation efficiently.

Claims (2)

1. a gas supersonic speed is condensed and the cyclonic separation jet pipe; Comprise straight length (1), centerbody (2), swirl vane (3), contraction section (4), expansion segment (5), inlet (10) and outlet (6); It is characterized in that:, form subsonic speed contracted channel (9), throat (8) and supersonic speed expansionary channel (7) by the contraction-expanding nozzle of contraction section (4), expansion segment (5) and centerbody (2) looping; Contraction section (4) is a tapered configuration, and expansion segment (5) is the flaring structure; Swirl vane (3) upper end is fixedly connected with straight length (1) internal face, and lower end and centerbody (2) surface is fixedly connected;

The contour curve of contraction section (4) designs according to following curvilinear equation:

$D_x=D_{\mathrm{cr}}+(D_1-D_{\mathrm{cr}})[1-10{\left(\frac{x}{L_s}\right)}^3+15{\left(\frac{x}{L_s}\right)}^4-6{\left(\frac{x}{L_s}\right)}^5]$

Aforesaid equation is the x axle with the axis of contraction section (4), is the origin of coordinates with the center of circle of contraction section (4) porch, D ₁And D _CrBe respectively the inlet diameter and the outlet diameter of contraction section (4), D _xDiameter of section for any x place; L _sBe contraction section length;

The contour curve of expansion segment (5) designs according to following curvilinear equation:

$D_{\mathrm{kx}}=\frac{D_{k1}}{\sqrt{1-[1-{\left(\frac{D_{k1}}{D_{k2}}\right)}^2]\frac{{[1-{\left(\frac{L_x-x}{L_k}\right)}^2]}^2}{{[1+\frac{1}{3}{\left(\frac{L_k-x}{L_k}\right)}^2]}^3}}}$

Aforesaid equation is the x axle with the axis of expansion segment (5), is the origin of coordinates with the center of circle of expansion segment (5) porch, D _K1And D _K2Be respectively the inlet diameter and the outlet diameter of expansion segment (5), D _K1=D _Cr, D _KxDiameter of section for any x place; L _kLength for expansion segment (5);

Centerbody (2) occupy the jet pipe center, comprises semiellipsoid (11), straight section (12), converging transition (13) and cylindrical section (14); The length L 1 of straight section (12) is: 0.5D _Z1≤L1≤5D _Z1, D _Z1Diameter for straight section (12); The contour curve of converging transition (13) designs according to following curvilinear equation:

$D_{\mathrm{zx}}=D_{\mathrm{zcr}}+(D_{z1}-D_{\mathrm{zcr}})[1-10{\left(\frac{x}{L_z}\right)}^3+15{\left(\frac{x}{L_z}\right)}^4-6{\left(\frac{x}{L_z}\right)}^5]$

Aforesaid equation is the x axle with the axis of converging transition (13), is the origin of coordinates with the center of circle of converging transition (13) porch, D _ZcrBe the outlet diameter of converging transition (13), D _ZxDiameter of section for any x place; L _zBe converging transition (13) length, L _z=L _sThe inlet of the inlet of converging transition (13) and contraction section (4) is on the same cross section;

The diameter of cylindrical section (14) equals the outlet diameter of converging transition (13), and the length of cylindrical section (14) equals the length L of expansion segment (5) _k

2. gas supersonic speed according to claim 1 is condensed and the cyclonic separation jet pipe; It is characterized in that: swirl vane (3) is an elliptical blade; Circumferentially evenly be installed in the surface of straight section (12), the major semiaxis and the semi-minor axis radius of swirl vane (3) are respectively R1 and R2, R1=L1; R2≤R1, lobe numbers is 3～24.

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