CN101387469A - Supersonic nozzle of supersonic speed rotational flow natural gas separator - Google Patents
Supersonic nozzle of supersonic speed rotational flow natural gas separator Download PDFInfo
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- CN101387469A CN101387469A CNA2008101574722A CN200810157472A CN101387469A CN 101387469 A CN101387469 A CN 101387469A CN A2008101574722 A CNA2008101574722 A CN A2008101574722A CN 200810157472 A CN200810157472 A CN 200810157472A CN 101387469 A CN101387469 A CN 101387469A
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Abstract
The invention provides a supersonic jet tube used for a supersonic cyclone natural gas separator, which is a key part of the separator, and consists of a contraction tube section, an extension tube section and a rectifying tube section. A moulding surface curve of the contraction tube section is higher-order polynomial, and natural gas airflow is expanded and accelerated in the section to achieve sonic velocity so as to form a straight sonic flow. The moulding surface curve of the extension tube section consists of a plurality of sections of curve, and the sections are smoothly connected to reduce disturbance to the airflow. The moulding surface curve of the supersonic jet tube at inlet and outlet changes flatly, has small curvature change, and has weak influence on the flowing of fluid upstream and downstream without obvious inlet and outlet effect. The extension tube has smooth inlet transition with small disturbance to the fluid. The extension tube section has flat change of moulding surface curve, small airflow expansion rate and good flow speed evenness, thereby helping droplet condensation nucleus grow larger grain diameter for separating. The supersonic jet tube not only evenly accelerates the airflow, improves evenness and stability of flow field, and reduces turbulivity, so that outlet airflow has better airflow quality, and can form droplets with larger grain diameter to improve the separation efficiency of the supersonic cyclone natural gas separator.
Description
Affiliated technical field
The present invention relates to a kind of supersonic nozzle, it is the critical component of supersonic speed rotational flow natural gas separator, belongs to gas gathering and transportation, processing and processing technology field.
Background technology
Adopt the supersonic speed rotational flow natural gas separator of supersonic speed cyclone separation process development to form by members such as De Laval noz(zle), supersonic speed rectifying tube, wing of supersonic, diffuser pipes.It combines aerodynamics, thermodynamics and hydromechanical theory, collects the technologies such as cooling, the separation of spiral-flow type gas/liquid, recompression that expand and finishes in the device of an airtight compactness.Air-flow to supersonic speed, forms low-temp low-pressure through the De Laval noz(zle) adiabatic expansion.Low temperature makes heavy hydrocarbon in the natural gas and the moisture content nucleation of condensing, and grows into droplet, forms the gas-liquid mixed air-flow.Air-flow forms eddy flow through wing of supersonic and in the mode of centrifugation water in the air-flow and heavy hydrocarbon condensation drop is separated.The supersonic speed cyclone separator has airtight no leakage, advantages of compact and light structure, need not chemical agent, simple and reliable advantages such as (no moving-members), with traditional heating and anti-freezing with utilize the antifreeze gas gathering and transportation technology of antifreezing agent to compare, investment of gas gathering and transportation system and operating cost minimizing 10～25%.
Supersonic nozzle is the critical component of supersonic speed rotational flow natural gas separator, adiabatic expansion is to supersonic speed when air communication is crossed jet pipe, its temperature and pressure reduces, form low-temp low-pressure, heavy hydrocarbon in the natural gas and water vapour reach hypersaturated state to begin to condense, condense into nuclear phenomenon, droplet growth forms gas-liquid mixture.Existing both at home and abroad about supersonic nozzle research report, but these jet pipes all can not satisfy the requirement that the supersonic speed cyclone separator efficiently expands and lowers the temperature and separate well.The Shell Oil Company began to research and develop the Twister treating apparatus in 1997, were applied to the well head natural gas processing, made certain gains in theory research and device design.The Shell Oil Company to the jet pipe application of Twister device patent: NOZZLE FOR SUPERSONIC GAS FLOW AND AN INERTIA SEPRATOR[P] .US6,513,345 B1, Feb.4,2003.It is 0.1 micron～2.5 microns drop particle that this jet pipe can produce particle diameter, but this jet pipe is not considered the influence of factors such as flow velocity uniformity, the pressure loss to the supersonic speed rotational flow natural gas separator.Supersonic flow in the supersonic nozzle easily forms the self-oscillation phenomenon, causes reducing nozzle efficiency than the macro-energy loss; Supersonic flow flow velocity uniformity and stability are lower, can not satisfy the supersonic speed rotational flow natural gas separator well to the supersonic nozzle performance demands.
Summary of the invention
The objective of the invention is to overcome the shortcoming of above-mentioned technology, provide a kind of simple in structure, working stability, be easy to processing and manufacturing, and have flow velocity uniformity preferably, less energy loss can form big drop, be more conducive to gas-liquid separation, thereby improve the step-up ratio of supersonic speed rotational flow natural gas separator and the supersonic nozzle of separative efficiency.
For achieving the above object, the technical solution used in the present invention is: supersonic nozzle is formed by shrinking pipeline section, expansion pipeline section and rectification pipeline section.Collapsible tube segment type surface curve changes follows the higher order polynomial rule, and collapsible tube segment type surface curve two-end-point tangent line is parallel with axis, realizes being connected with the smooth of straight tube.The collapsible tube segment length is 0.5～5 times of nozzle entrance section caliber, and angle of throat is 6 °～45 °, shrinks the terminal straight tube that connects of pipeline section, enters uniformity, the stability of expanded gas flow in the expansion pipeline section with increase.The straight tube length of pipe section is 0.05～0.2 times of nozzle throat diameter.It is even, mild that collapsible tube segment type surface curve changes, and gas flow expands in contraction section and accelerates to velocity of sound straight flow.Convergent divergent channel segment type surface curve is made up of the multistage curve, its leading portion is arc section and straight wall section, arc section has realized that throat is connected with straight the smooth of wall section, arc radius is 1～30 times a throat diameter, straight wall segment length is 0.5～5 times a throat diameter, straight wall section is set helps the supersonic speed gas flow and be transformed into eddy flow, and expand with the eddy flow form and to quicken through wing of supersonic; Its back segment (wave absorption expansion segment) curve is the wave absorption curve, and this pipeline section becomes the even straight flow that satisfies the Mach number requirement to supersonic speed, to guarantee realizing that exit flow is even; The wave absorption expansion segment prevents to produce strong shock wave with the rear and front end straight tube is tangent to realize smooth the connection, reduces energy loss, and it is even, stable to help air-flow.The maximum swelling angle of wave absorption expansion segment is the Prandtl-Meyer angle of 0.2～0.8 times nozzle exit Mach number correspondence.The rectifying tube segment length is 10～50 times a caliber, and this pipeline section can increase the uniformity of supersonic speed gas flow, helps collision, the growth of drop.
Adopted the separator of above-mentioned supersonic nozzle, the low speed heavy pressure gas flow is converted into low temperature, at a high speed even axial flow efficiently, the pressure loss is little, does not have obvious self-oscillation phenomenon.This supersonic nozzle quickens the high-pressure natural gas flow expansion by shrinking pipeline section, be transformed into velocity of sound straight flow, by the expansion pipeline section gas flow is expanded again and quicken, by the wave absorption expansion segment air-flow is transformed to uniform straight flow at last, realize the expansion cooling of air-flow.Smooth transition between this each section of supersonic nozzle, variations in flow is evenly mild, has reduced the disturbance of stream field, has reduced energy loss, has improved expansion efficiency, easily forms the drop of greater particle size, helps realizing gas-liquid separation.
The present invention will be further described below in conjunction with accompanying drawing and exemplary embodiments (example).
Description of drawings
Fig. 1 is the profile according to supersonic nozzle proposed by the invention;
Fig. 2 is the contraction pipeline section profile according to supersonic nozzle proposed by the invention;
Fig. 3 is the expansion pipeline section profile according to supersonic nozzle proposed by the invention;
The specific embodiment
Accompanying drawing is a typical supersonic nozzle example according to the object of the invention design processing.This supersonic nozzle is a cylindrical housings.Fig. 1 is the profile of supersonic nozzle, constitutes by shrinking pipeline section (1), expansion pipeline section (2) and rectification pipeline section (3).
Fig. 2 is the contraction pipeline section profile of supersonic nozzle, and this example shrinks pipeline section and is made up of collapsible tube (4) and straight tube (5).Collapsible tube profile curve is a cubic polynomial, inlet diameter 100mm, and outlet diameter 12.4mm shrinks pipe range 186mm, and angle of throat is 15 °, collapsible tube arrival end and port of export tangent line and axially parallel.The long 1.0mm of the terminal straight tube of collapsible tube, this straight tube is the throat of supersonic nozzle, gas flow reaches the velocity of sound at this, forms straight sonic flow.
Fig. 3 is the expansion pipeline section profile of supersonic nozzle, is made of circular arc expansion segment (6), straight wall expansion segment (7) and wave absorption expansion segment (8).Circular arc expansion segment (6) profile curve is that radius is one section circular arc of 36mm, and circular arc and nozzle throat and straight wall expansion segment (7) are tangent, and transition is smooth.Straight wall expansion segment length 18mm.Wave absorption convergent divergent channel segment type surface curve is smooth with straight wall expansion segment (7) and rectification pipeline section (3) transition.The maximum swelling angle of wave absorption expansion segment is the Prandtl-Meyer angle of 0.25 times nozzle exit Mach number correspondence.The long 150mm of rectification pipeline section (3), gas flow forms even supersonic flow after the expansion pipeline section expands acceleration, and air-flow enters the laggard step rectification of rectification pipeline section, forms uniform supersonic speed straight flow.This rectification pipeline section can increase the uniformity of supersonic speed gas flow, and helps collision, the growth of drop.
This supersonic nozzle is converted into the even axial flow gas flow of supersonic speed efficiently with the low speed heavy pressure gas flow, the pressure loss is little, there is not obvious self-oscillation phenomenon, realized the expansion cooling of air-flow, reduced energy loss, improve expansion efficiency, can form the better fluid particle, helped realizing gas-liquid separation.
Claims (5)
1. a supersonic nozzle that is used for the supersonic speed rotational flow natural gas separator constitutes by shrinking pipeline section (1), expansion pipeline section (2) and rectification section (3).It is characterized in that shrink pipeline section (1) profile curvilinear motion and follow the higher order polynomial rule, length is 0.5～5 times of nozzle entrance section caliber, angle of throat is 6 °～45 °; Expansion pipeline section (2) profile curve is made up of the multistage curve, and its leading portion is arc section and straight wall section, and the back segment curve is the wave absorption curve, and expansion pipeline section maximum swelling angle is the Prandtl-Meyer angle of 0.2～0.8 times nozzle exit Mach number correspondence.
2. supersonic nozzle according to claim 1, it is characterized in that, shrinking pipeline section is made up of collapsible tube (4) and straight tube (5), collapsible tube (4) profile curve is a cubic polynomial, the end points tangent line is parallel with axis, realize and smooth connection of straight tube (5) that straight tube (5) length is 0.05～0.2 times of nozzle throat diameter.
3. supersonic nozzle according to claim 1, it is characterized in that, the expansion pipeline section comprises circular arc expansion pipeline section (6), straight wall expansion segment (7) and wave absorption expansion segment (8), the smooth connection of each section, circular arc expansion pipeline section (6) profile sweep is 1～30 times a throat diameter, and straight wall expansion pipeline section (7) length is 0.5～5 times throat diameter.
4. supersonic nozzle according to claim 1 is characterized in that, the smooth connection of circular arc convergent divergent channel (6) of the straight tube of contraction section (5) and expansion segment.
5. supersonic diffuser according to claim 1 is characterized in that, rectification section (3) is a straight tube, and length is 10～50 times caliber, rectification section (3) and wave absorption expansion smooth connection of pipeline section (8).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CNA2008101574722A CN101387469A (en) | 2008-10-11 | 2008-10-11 | Supersonic nozzle of supersonic speed rotational flow natural gas separator |
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| CNA2008101574722A CN101387469A (en) | 2008-10-11 | 2008-10-11 | Supersonic nozzle of supersonic speed rotational flow natural gas separator |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102302989A (en) * | 2011-05-18 | 2012-01-04 | 中国人民解放军国防科学技术大学 | Supersonic velocity spray pipe with shared throat part and design method of supersonic velocity spray pipe |
| CN102323961A (en) * | 2011-05-18 | 2012-01-18 | 中国人民解放军国防科学技术大学 | Asymmetric supersonic velocity spray pipe and design method thereof |
| CN102489081A (en) * | 2011-12-02 | 2012-06-13 | 文闯 | Air supersonic-velocity condensation and cyclone separation spray pipe |
| CN102539158A (en) * | 2011-12-23 | 2012-07-04 | 中国航天科技集团公司第六研究院第十一研究所 | Water-cooling sound velocity throat with small curvature radius and preparation method thereof |
| CN102606564A (en) * | 2012-04-13 | 2012-07-25 | 中国人民解放军国防科学技术大学 | Method and device for implementation of supersonic runner |
| CN107353957A (en) * | 2017-08-16 | 2017-11-17 | 中国石油大学(华东) | A kind of tapered cyclone-type supersonic nozzle |
| CN107376581A (en) * | 2017-08-16 | 2017-11-24 | 中国石油大学(华东) | A kind of flaring cyclone-type supersonic nozzle |
| CN107782495A (en) * | 2017-10-16 | 2018-03-09 | 中国航空工业集团公司北京长城计量测试技术研究所 | Supersonic speed exerciser is used in a kind of static probe calibration |
| CN111495670A (en) * | 2020-04-16 | 2020-08-07 | 上海交通大学 | Supersonic atomizing throttler device with self-excited oscillation mode |
| US11460244B2 (en) | 2016-06-30 | 2022-10-04 | Baker Hughes Oilfield Operations Llc | System and method for producing liquefied natural gas |
| CN116078088A (en) * | 2022-11-03 | 2023-05-09 | 中国石油大学(华东) | Air purification edulcoration device |
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2008
- 2008-10-11 CN CNA2008101574722A patent/CN101387469A/en active Pending
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102323961A (en) * | 2011-05-18 | 2012-01-18 | 中国人民解放军国防科学技术大学 | Asymmetric supersonic velocity spray pipe and design method thereof |
| CN102302989A (en) * | 2011-05-18 | 2012-01-04 | 中国人民解放军国防科学技术大学 | Supersonic velocity spray pipe with shared throat part and design method of supersonic velocity spray pipe |
| CN102489081A (en) * | 2011-12-02 | 2012-06-13 | 文闯 | Air supersonic-velocity condensation and cyclone separation spray pipe |
| CN102489081B (en) * | 2011-12-02 | 2013-08-21 | 文闯 | Air supersonic-velocity condensation and cyclone separation spray pipe |
| CN102539158A (en) * | 2011-12-23 | 2012-07-04 | 中国航天科技集团公司第六研究院第十一研究所 | Water-cooling sound velocity throat with small curvature radius and preparation method thereof |
| CN102539158B (en) * | 2011-12-23 | 2014-04-30 | 中国航天科技集团公司第六研究院第十一研究所 | Water-cooling sound velocity throat with small curvature radius and preparation method thereof |
| CN102606564A (en) * | 2012-04-13 | 2012-07-25 | 中国人民解放军国防科学技术大学 | Method and device for implementation of supersonic runner |
| CN102606564B (en) * | 2012-04-13 | 2013-10-02 | 中国人民解放军国防科学技术大学 | Method and device for implementation of supersonic runner |
| US11460244B2 (en) | 2016-06-30 | 2022-10-04 | Baker Hughes Oilfield Operations Llc | System and method for producing liquefied natural gas |
| CN107353957A (en) * | 2017-08-16 | 2017-11-17 | 中国石油大学(华东) | A kind of tapered cyclone-type supersonic nozzle |
| CN107376581A (en) * | 2017-08-16 | 2017-11-24 | 中国石油大学(华东) | A kind of flaring cyclone-type supersonic nozzle |
| CN107782495A (en) * | 2017-10-16 | 2018-03-09 | 中国航空工业集团公司北京长城计量测试技术研究所 | Supersonic speed exerciser is used in a kind of static probe calibration |
| CN107782495B (en) * | 2017-10-16 | 2019-10-01 | 中国航空工业集团公司北京长城计量测试技术研究所 | A kind of static probe calibration supersonic speed exerciser |
| CN111495670A (en) * | 2020-04-16 | 2020-08-07 | 上海交通大学 | Supersonic atomizing throttler device with self-excited oscillation mode |
| CN111495670B (en) * | 2020-04-16 | 2021-07-23 | 中国石油集团渤海钻探工程有限公司 | Supersonic atomizing throttler device with self-excited oscillation mode |
| CN116078088A (en) * | 2022-11-03 | 2023-05-09 | 中国石油大学(华东) | Air purification edulcoration device |
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