CN206526609U - Double venturi PARAMETERS VARYING OF THE SUPERSONIC LOW TEMPERATURE GAS helical flow gas fractionation units - Google Patents
Double venturi PARAMETERS VARYING OF THE SUPERSONIC LOW TEMPERATURE GAS helical flow gas fractionation units Download PDFInfo
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- CN206526609U CN206526609U CN201720158139.8U CN201720158139U CN206526609U CN 206526609 U CN206526609 U CN 206526609U CN 201720158139 U CN201720158139 U CN 201720158139U CN 206526609 U CN206526609 U CN 206526609U
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Abstract
The utility model discloses a kind of pair of venturi PARAMETERS VARYING OF THE SUPERSONIC LOW TEMPERATURE GAS helical flow gas fractionation unit, including inducer, first row Scroll-type blade, dead band area, second row Scroll-type blade, supersonic nozzle air-flow accelerating region, collection section, clean gas supersonic deceleration area, the first bank of compressors type blade, the second bank of compressors type blade, subsonic flow deceleration area, conical inner body and runner shell, compared with prior art, the utility model is simple in construction, small volume, safeguards simple.It is unattended usually without regular maintenance；Without external enwergy consumption；The loss of natural gas interior energy is low, and operational efficiency is high, is not required into gas add chemical addition agent, no harmful liquid or gas are discharged, the public hazards, good environmental protection such as present apparatus noiseless, vibration；, can be unattended without regular maintenance during operation, no material consumption during operation, operating cost is low.
Description
Technical field
The utility model is related to the gas fractionation units such as oil, natural gas, chemical industry and metallurgy, more particularly to a kind of pair of venturi
PARAMETERS VARYING OF THE SUPERSONIC LOW TEMPERATURE GAS helical flow gas fractionation unit.
Background technology
1) conventional natural gas handling process need to respectively be dehydrated, take off hydrocarbon, and equipment is huge, high energy consumption, and operating cost is high, generally de-
Water need to add the chemical addition agents such as hydrate inhibitor, there is pollution after discharge to environment, endanger human health.
2) in number of patent application 200716101510.8, publication number CN101037629A, not to ultrasonic dehydration device
Illustrate, only drawn the schematic diagram of simple Laval nozzle, how gasless swirl-flow devices produce supersonic speed eddy flowNothing
How separator, no normal shock wave position, stablize the measures such as shock wave, does not reach industrial purpose.
3) in number of patent application 201520910766.7, Authorization Notice No. CN205133538u, gas is produced in air inlet section
The blade design of the circumferential eddy flow of stream is not right, the blade profile illustrated by patent, can not produce air-flow circumferential high speed rotating flow in jet pipe
Dynamic, in supersonic speed section, venturi is not known, and normal shock wave position is not known yet.Therefore, the patent has guidance quality mistake to user.
Above-mentioned several dewaterings are all difficult to meet land, the purification of ocean wet gas.Land and ocean natural gas exploitation
Compact in the urgent need to compact structure, flowing is stable, the high-efficiency dehydration of energy-conserving and environment-protective, de- hydrocarbon device.
Utility model content
The purpose of this utility model is that provides a kind of pair of venturi PARAMETERS VARYING OF THE SUPERSONIC LOW TEMPERATURE GAS spiral to solve the above problems
Flowing gas separator.
The utility model is achieved through the following technical solutions above-mentioned purpose：
The utility model includes inducer, first row Scroll-type blade, dead band area, second row Scroll-type blade, supersonic speed
Nozzle gas flow accelerating region, collection section, clean gas supersonic deceleration area, the first bank of compressors type blade, the second bank of compressors
Type blade, subsonic flow deceleration area, conical inner body and runner shell, the end of the runner shell are set to the import
Section, the first row Scroll-type blade is installed in the inducer, and the second row Scroll-type blade is installed on described first
The rear of Scroll-type blade is arranged, is the dead band between the first row Scroll-type blade and the second row Scroll-type blade
Area, the rear of the second row Scroll-type blade is described in collection section is arranged at described in the supersonic nozzle air-flow accelerating region
The side of supersonic nozzle air-flow accelerating region, the clean gas supersonic deceleration area is arranged at the side of the collection section,
The first bank of compressors type blade is located at the rear in the clean gas supersonic deceleration area, the second bank of compressors type leaf
Piece is arranged at the rear of the first bank of compressors type blade, and the subsonic flow deceleration area is arranged at the second row compression
Cone centered on the rear of type blade, the tube wall of the runner shell.
The beneficial effects of the utility model are：
The utility model is a kind of pair of venturi PARAMETERS VARYING OF THE SUPERSONIC LOW TEMPERATURE GAS helical flow gas fractionation unit, compared with prior art,
The utility model is that aerofluid principle of dynamics is applied to the innovative technology that natural gas is separated, and is that resource is developed with environment-friendly high-efficiency
Comprehensive utilization, the advanced innovative technology of resource recycling.Compared with current domestic original technology and Patents with bright
Aobvious innovation effect is as follows：
1 is simple in construction, small volume, safeguards simple.It is unattended usually without regular maintenance；
2 consume without external enwergy；
The loss of 3 natural gas interior energies is low, and operational efficiency is high, lower than existing dewatering type water dew point more than 18 DEG C, and outlet is natural
Atmospheric pressure drop is reduced, in the case of rate of recovery identical, using this patent compared with using J-T valves, reduces power consumption 50-70%,
Work done during compression 15-20% can be reduced by substituting expanding machine with the present apparatus；
4 are not required into gas add chemical addition agent, no harmful liquid or gas discharge, present apparatus noiseless, vibration etc.
Public hazards, good environmental protection；
5 this patents are higher by about 30% than the J-T expansion throttling valve rate of recovery, higher than the expanding machine rate of recovery by more than 10%；
, can be unattended without regular maintenance during the operation of 6 this patents, no material consumption during operation, operating cost is low.
Brief description of the drawings
Fig. 1 is structural representation of the present utility model；
Fig. 2 is the change schematic diagram of gas of the present utility model speed on streamline in dead band；
Fig. 3 is Scroll-type blade construction schematic diagram of the present utility model.
In figure：1- inducers, 2- first row Scroll-type blades, 3- dead bands area, 4- second row Scroll-type blades, 5- supersonic speed
Nozzle gas flow accelerating region, 6- collects section, 7- clean gas supersonic decelerations area, 8- the first bank of compressors type blades, 9- second
Bank of compressors type blade, 10- subsonic flow deceleration areas, 11- conical inner bodies, 12- runner shells.
Embodiment
The utility model is described in further detail below in conjunction with the accompanying drawings：
As shown in Figure 1：The utility model includes inducer 1, first row Scroll-type blade 2, dead band area 3, second row turbine
Type blade 4, supersonic nozzle air-flow accelerating region 5, collection section 6, clean gas supersonic deceleration area 7, the first bank of compressors type
Blade 8, the second bank of compressors type blade 9, subsonic flow deceleration area 10, conical inner body 11 and runner shell 12, the runner
The end of shell is set to the inducer, and the first row Scroll-type blade is installed in the inducer, the second row
Scroll-type blade is installed on the rear of the first row Scroll-type blade, the first row Scroll-type blade and the second row whirlpool
It is the dead band area between wheel-type blade, the rear of the second row Scroll-type blade is the supersonic nozzle air-flow accelerating region
Described to collect the side that section is arranged at the supersonic nozzle air-flow accelerating region, the clean gas supersonic deceleration area is set
In the side of the collection section, the first bank of compressors type blade is located at behind the clean gas supersonic deceleration area
Side, the second bank of compressors type blade is arranged at the rear of the first bank of compressors type blade, and the subsonic flow subtracts
Fast area is arranged at cone centered on the rear of the second bank of compressors type blade, the tube wall of the runner shell.
The natural gas of normal temperature enters present apparatus inducer 1, and the gas velocity of inflow is very low, due to center cone in inducer
Body radius is continuously increased, and the circulation area of runner is constantly declined, air velocity is also continuously increased, and air-flow static temperature is begun to decline.
Air-flow flows into Scroll-type blade 2, and because center bevel radius continues to increase, outer wall runner is gradually tapered up, circulation area further under
Drop.Air-flow is further speeded up in Scroll-type blade conduit, while airflow direction changes with the change in blade profile conduit direction, is made
Air-flow is changed into obliquely flow by axial direction, and the helical flow that air-flow forms larger speed is flowed into dead band 3.Due to dead band
Runner radius in 3 constantly reduces along streamline, and circulation area continues to reduce, and is continuously increased flow velocity, rotates about the axis speed v θ
Also increase.On same streamline, curl is constant, i.e. v θ r=C (C is constant), and wherein v θ are around axis rotation on gas streamline
The circumferential speed turned, r is streamline radius, when r is smaller, v θ bigger (see Fig. 2).According to the change of r radiuses on streamline, gas is calculated
The flow parameter (to ensure that air-flow is not separated in dead band 3) of Scroll-type blade 4 is flowed into, air-flow enters Scroll-type blade conduit
In, the continuation of runner circulation area reduces, and air-flow continues to accelerate, and occurs first venturi in blade exit runner, appearance at this
Mach number is equal to 1.0, in venturi backward, flow area increase, supersonic speed rotational flow occurs.Air-flow enters supersonic speed section 5, stream
Road circulation area increase, air velocity increase, temperature drop, usual gasflow mach number increases to Ma=1.6-1.7, gas flow temperature
Subzero less than 70 DEG C are dropped sharply to, the steam in natural gas and more than C3 lighter hydrocarbons is rapidly changed into micro- ice pellets and liquid hydrocarbon,
Because gas is in high speed rotational flow, powerful centrifugal force is produced, micro- ice pellets and liquid hydrocarbon that proportion is bigger than natural gas is existed
The runner outer wall of supersonic speed section 5 is moved in the presence of centrifugal force, into ice and liquid hydrocarbon collecting box 6, separation water, liquid hydrocarbon is carried out
And natural gas.The clean natural gas of collecting box is introduced into still with supersonic flow inlet/outlet section 7, this section of circulation area slightly reduces, and makes
Supersonic airstream slows down, but still is flowed into supersonic speed in compressor type blade 8, in the runner of type blade 8 of calming the anger, circulation area
It is gradually reduced, air-flow constantly slows down in blade conduit, airflow direction is later half in blade conduit from circumferentially gradually to axially translated
There is one of normal shock wave in portion.Occur second venturi of this patent at this, air-flow becomes subsonic speed, but air-flow stream by normal shock wave
Dynamic direction is still not up to axially.Air-flow is flowed into type blade 9 of calming the anger, because import is subsonic speed, in order to continue to reduce air-flow
The gentle circulation of speed is changed into axial flowing, and the circulation area at this continues to increase, and blade profile conduit direction also gradually goes to axial direction, made
Airflow direction switchs to axial direction, and the speed that speed also drops to conveyance conduit is flowed into natural gas pipeline.
Double throat design technologies in distinctive supersonic speed runner are utilized in this patent, but are drawn and cut down different from double venturis
That jet pipe.It is thorough when occurring pressure change fluctuated in natural-gas transfer pipeline, it is ensured that working stability in supersonic speed section 5
Bottom solve single throat design in previous patent supersonic flow dynamic instability and production yields be unstable or processing after it is natural
The underproof problem of gas dew point.
This patent first row Scroll-type blade, when air-flow flows through the blade, its speed is accelerating, and makes airflow direction to week
To flowing (see Fig. 3), this and number of patent application 201520910766.7,3 in Authorization Notice No. CN205133538u be to have this
Matter it is different, 3 blade profile direction is not right in the figure, and inlet air flow is axially, exit flow can not produce week also close to axial direction
To point speed of rotation, it is impossible to produce the speed that rotates in a circumferential direction, this misleads person of ordinary skill in the field.This patent Scroll-type
Blade design is first selected Attacking angle, inlet air flow angle, outlet flow angle, blade profile maximum camber point position and blade profile thickness minute
Cloth.Blade profile deviation angle is calculated according to above parameter, blade profile exit angle is determined and is calculated by blade profile inlet air flow angle and the angle of attack
Blade profile inlet air flow angle.By above parameter calculate blade profile mean camber line, provide blade profile front and rear edge radius, and point of maximum thickness position and
Thickness, adds defined blade profile thickness, is generally pressed from leading edge to point of maximum thickness thickness distribution respectively on blade profile mean camber line vertical line
3 equation of n th order n functions of chord length, point of maximum thickness to rear edge thickness is that the quadratic equation functional relation of chord length is determined.On mean camber line
Each point after adding thickness has been wired to the blade back leaf basin molded line (see Fig. 3) of blade profile, carries out aerodynamic analysis after blade shaping, if full
Whether sufficient design requirement, air-flow uniformly accelerates in conduit, whether has separation at blade back, whether profile loss meets requirement, no
Meet and then change blade design parameter, untill design requirement is met.
3 be the convergent dead band of runner in the technical scheme of this patent, further speeds up the air-flow flowed out in 2, air-flow rotation
Being flowed into after the speed increase turned in second row Scroll-type blade, 4 (does not have) runner further to reduce in other patents, air-flow adds
Speed, flow expansion accelerates in blade profile passage, and air-flow is further speeded up around the circumferential speed of axis, and being formed in blade profile exit should
First venturi of device, makes the Mach number of locality reach 1.0.
Air-flow continues to accelerate into supersonic speed section 5 after blade exit, and runner, which gradually expands, reaches gasflow mach number
More than 1.6, gas temperature dramatic decrease to subzero less than 70 DEG C, the circumferential speed that air-flow is rotated about the axis reach 400m/s with
On, produce centrifugal force.Under the influence of centrifugal force, air-flow reclaimed water, micro- ice pellets and more than C3 liquid hydrocarbon and sub-fraction natural gas are made
Into section 6 is collected, remaining clean natural gas enters in air stream enter runner 7, continues toward Way out motion, under gas flow slightly has
Drop, declines gasflow mach number, but air-flow still flows into compressor type blade 8 with supersonic speed.
Blade 8 makes flow slowing down, airflow direction progressively to axial torsion, but because gasflow mach number is larger, torsion angle
Degree can not be too big, typically in below 200C, makes to produce one of normal shock wave in blade profile conduit, here it is so-called second venturi,
Air velocity becomes subsonic flow from supersonic speed, and the purpose so done has two：First is occurred without just in supersonic nozzle
Shock wave, second is to make shock wave arrange 8 the latter half of of blade profile passage in blade normal shock wave occur, even if pressure in natural gas pipeline
During rising, shock wave only moves forward a segment distance still in blade profile conduit, as long as shock wave is not pushed out before the import of leaf row 8,
Shock wave is in blade 8, and flowing is stable in supersonic nozzle.Actually natural gas pipeline pressure oscillation is much smaller than shock wave
Pressure oscillation required outside blade profile conduit is moved to, so the patent makes not have normal shock wave in supersonic nozzle, no matter gas transmission
Pipeline pressure is raised, and air current flow is stable in supersonic nozzle, and gas-liquid separation is also stability and high efficiency.9 are arranged in blade, is
Subsonic flow is further slowed down, airflow direction is further reversed until axially, then inputting in natural gas line.
Formative method and design on type blade 8 and 9 of calming the anger is similar substantially with Scroll-type blade design, but blade profile
Flowing is to slow down in conduit, so the camber of blade profile mean camber line, thickness distribution, deviation angle and the angle of attack and Scroll-type blade are in number
There is obvious difference in value, it will meet the characteristics of type blades flows of calming the anger are inverse pressure flowings, to supersonic speed blade profile, its import
Flowing is supersonic, and blade profile import need to be avoided, which to have, very strong normal shock wave can not occurs in strong bow-wave, conduit.So,
Conduit interior air-flow must gradually slow down, the Mach number before control normal shock wave, reduce normal shock wave loss as far as possible, meanwhile, work as gas transmission
In pipeline during pressure oscillation, normal shock wave can not be shifted onto at blade profile conduit import, so the position arrangement of normal shock wave is in blade profile conduit
Second half section.It must accomplish that air-flow can not produce separation at blade profile blade back, reduce air-flow as far as possible when type blade is calmed the anger in design
Flow losses, expand the stability range that air-flow flows in blade conduit.
In the design, Scroll-type blade and type blade design of calming the anger have special design programming respectively, and runner is set
Meter is, according to natural gas property, tentatively to give each blade and discharge into outlet parameter, redesign out the inside and outside channel size of runner.According to
Given parameter, the gas stream in runner is calculated with the calculation procedure and natural gas physical function parameter of full Three Dimensional Viscous gas
Dynamic parameter, if meet design, is such as unsatisfactory for changing design runner and blade profile again, untill satisfaction.
General principle of the present utility model and principal character and advantage of the present utility model has been shown and described above.One's own profession
The technical staff of industry is it should be appreciated that the utility model is not restricted to the described embodiments, described in above-described embodiment and specification
Simply illustrate principle of the present utility model, on the premise of the utility model spirit and scope are not departed from, the utility model is also
Various changes and modifications are had, these changes and improvements are both fallen within the range of claimed the utility model.The utility model
Claimed scope is by appended claims and its equivalent thereof.
Claims (1)
1. a kind of pair of venturi PARAMETERS VARYING OF THE SUPERSONIC LOW TEMPERATURE GAS helical flow gas fractionation unit, it is characterised in that：Including inducer, first row whirlpool
Wheel-type blade, dead band area, second row Scroll-type blade, supersonic nozzle air-flow accelerating region, collection section, clean gas supersonic speed
Deceleration area, the first bank of compressors type blade, the second bank of compressors type blade, subsonic flow deceleration area, conical inner body and runner
Shell, the end of the runner shell is set to the inducer, and the first row Scroll-type blade is installed on the inducer
Interior, the second row Scroll-type blade is installed on the rear of the first row Scroll-type blade, the first row Scroll-type blade
It is the dead band area between the second row Scroll-type blade, the rear of the second row Scroll-type blade is the supersonic speed
The side that section is arranged at the supersonic nozzle air-flow accelerating region is collected described in nozzle gas flow accelerating region, the clean gas surpasses
Velocity of sound deceleration area is arranged at the side of the collection section, and the first bank of compressors type blade is located at the clean gas Supersonic
The rear of fast deceleration area, the second bank of compressors type blade is arranged at the rear of the first bank of compressors type blade, described
Subsonic flow deceleration area is arranged at cone centered on the rear of the second bank of compressors type blade, the tube wall of the runner shell
Body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720158139.8U CN206526609U (en) | 2017-02-22 | 2017-02-22 | Double venturi PARAMETERS VARYING OF THE SUPERSONIC LOW TEMPERATURE GAS helical flow gas fractionation units |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720158139.8U CN206526609U (en) | 2017-02-22 | 2017-02-22 | Double venturi PARAMETERS VARYING OF THE SUPERSONIC LOW TEMPERATURE GAS helical flow gas fractionation units |
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| Publication Number | Publication Date |
|---|---|
| CN206526609U true CN206526609U (en) | 2017-09-29 |
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|---|---|---|---|
| CN201720158139.8U Expired - Fee Related CN206526609U (en) | 2017-02-22 | 2017-02-22 | Double venturi PARAMETERS VARYING OF THE SUPERSONIC LOW TEMPERATURE GAS helical flow gas fractionation units |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108514805A (en) * | 2018-05-03 | 2018-09-11 | 闫家义 | Non-concentric variable cross-section GWF devices |
| CN110129105A (en) * | 2018-11-28 | 2019-08-16 | 陆庆飞 | A kind of liquefaction of supersonic speed and helical flow separator |
| CN115219147A (en) * | 2022-09-15 | 2022-10-21 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Adjustable fan blade type second throat and test section Mach number control method |
-
2017
- 2017-02-22 CN CN201720158139.8U patent/CN206526609U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108514805A (en) * | 2018-05-03 | 2018-09-11 | 闫家义 | Non-concentric variable cross-section GWF devices |
| CN108514805B (en) * | 2018-05-03 | 2021-12-28 | 闫家义 | High-speed vortex flow gas separation device |
| CN110129105A (en) * | 2018-11-28 | 2019-08-16 | 陆庆飞 | A kind of liquefaction of supersonic speed and helical flow separator |
| CN115219147A (en) * | 2022-09-15 | 2022-10-21 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Adjustable fan blade type second throat and test section Mach number control method |
| CN115219147B (en) * | 2022-09-15 | 2022-11-18 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Adjustable fan blade type second throat and test section Mach number control method |
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| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170929 Termination date: 20210222 |
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| CF01 | Termination of patent right due to non-payment of annual fee |