CN102635578A - Multilevel lobed nozzle ejector with secondary-fluid sucking function - Google Patents
Multilevel lobed nozzle ejector with secondary-fluid sucking function Download PDFInfo
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- CN102635578A CN102635578A CN201110436863XA CN201110436863A CN102635578A CN 102635578 A CN102635578 A CN 102635578A CN 201110436863X A CN201110436863X A CN 201110436863XA CN 201110436863 A CN201110436863 A CN 201110436863A CN 102635578 A CN102635578 A CN 102635578A
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Abstract
The invention relates to a multilevel lobed nozzle ejector with a secondary-fluid sucking function, which belongs to the technical field of industrial air extracting and air-mixing strengthening and comprises straight sections and lobed sections. The straight sections are arranged on the lobed sections to form lobed nozzles, an ejector body comprises lobed nozzles of three levels or more than three levels, each level of the lobed nozzles are coaxial and arranged along the axial direction, and the diameter of the lobed nozzle of each latter level is larger than that of the lobed nozzle of the former level with the diameter of the first level served as the datum. The molded surface of the outlet portion of the multilevel lobed nozzle ejector with the secondary fluid sucking function is bended, so that the static pressure of the lobed nozzle outlet can be reduced, and the ejecting capability of the main fluid is improved. Compared with a single-level ejector, the multilevel lobed nozzle ejector is capable of improving the whole ejecting capability of the ejector and strengthening the mixing of the main fluid and the secondary fluid. The multilevel lobed nozzle ejector with the secondary-fluid sucking function is simple in structure and can be widely applied to industrial sites.
Description
Technical field
The present invention relates to a kind of multistage lobe nozzle ejector, belong to industrial bleed, the strengthening fluid hybrid technology field of taking out with suction a secondary fluid.
Background technique
Mixer-ejector is a kind of two fluid streams with different pressures, in co-flow, mixes the device that forms a kind of intermediate pressure fluid.Wherein, low-pressure fluid can be among the atmosphere environment sometimes.Its address is various, and the sparger of being called is arranged, jet pump; The ejector of being called is also arranged, jet pump, mixer and mixer-ejector.Book adopts comparatively wide in range title---mixer-ejector in the present patent application.High energy, high-pressure liquid wherein are called main fluid.Low energy, low-pressure fluid are called time fluid.Fluid after the two mixes is called fluid-mixing.
Mixer-ejector has all obtained using widely in each industrial department, for example: the coal dust that in station boiler, utilizes air ejector to use to the boiler furnace spray combustion; Utilize steam ejector from condenser, to take incoagulable gas away, for example patent " a kind of refrigerating circulatory device, the patent No.: 200720100919 " with ejector.In refrigeration technology, utilize the ejector pump to vacuumize, come the injection refrigeration through the latent heat of vaporization that the evaporation of liquid low pressure produces.In the heating and ventilation device, ejector can be used to form the major impetus in air channel, organizes continual air flow, for example patent " steam ejection formula heating arrangement, number of patent application: 99241198 ".In gas works, ejector is the important burning dispenser of combustion gas and air especially, for example " two-stage injection atmospheric burner, number of patent application: 95218056 ".In the course of conveying of bulk granular material and sticky material, ejector is the instrument that transports the easiest at last.The high pressure draught of main jet pipe (being called main flow) sprays from the main jet pipe; By gas or gas-solid mixture or the gas-liquid mixture (being called secondary flow) in the viscosity suction collection chamber of fluid; Be transported to mixing tube, discharge through the diffuser pipe diffusion, the basic structure of ejector just so.Mixer-ejector extensive use in each industrial department.The main flow fluid can be steam, air or liquid, and a secondary fluid can be gas or gas-solid mixture or gas-liquid mixture, is allowed a choice according to the demand of industrial department.
In the at present relevant patent of ejector, the shape of nozzles with injector is convergence circle jet pipe or straight tube basically, does not possess the function of strengthening main flow and secondary flow mixing.And in the industrial process, sometimes need be with sending into next production and processing link after main flow (for example air) and secondary flow (for example pulverized coal particle) mixing, this just needs a kind of special device or structure to realize.This patent, is realized utilizing the small flow main flow to aspirate big flow secondary flow through increasing the ability that injection progression strengthens ejector injection secondary flow to existing ejector structure; Simultaneously, adopt lobe shape jet pipe to strengthen the mixing between main flow and secondary flow, application prospect is arranged in industry.
Summary of the invention
The present invention is directed to the deficiency of above-mentioned existence, a kind of multistage lobe nozzle ejector with suction a secondary fluid is provided.
The present invention adopts following technological scheme:
A kind of multistage lobe nozzle ejector with suction a secondary fluid of the present invention comprises straight section and lobe section, and described straight section is arranged on the lobe section and forms lobe nozzle; The ejector body comprises that the lobe nozzle more than three grades or three grades forms, and described every grade of lobe nozzle is coaxial and arrange vertically, is benchmark with the diameter of first order lobe nozzle, and the diameter of the lobe nozzle of each grade is greater than the lobe nozzle diameter of previous stage backward.
Multistage lobe nozzle ejector with suction a secondary fluid of the present invention, the lobe section is made up of several crests and trough, and crest links to each other with trough and forms ring-type lobe section; The port diameter of ring-type lobe Duan Yiduan is less than the another port diameter.
Multistage lobe nozzle ejector with suction a secondary fluid of the present invention, the straight section on described every grade of lobe nozzle is identical with the diameter of the maximum diameter end of this grade lobe section.
Multistage lobe nozzle ejector with suction multiply a secondary fluid of the present invention, the gap between described every two-stage straight section forms the injection passage.
Beneficial effect
Multistage lobe nozzle ejector with suction a secondary fluid provided by the invention; Lobe nozzle produces a large amount of whirlpool arrays that flow in its outlet and downstream; Aggravated the mixing between main flow and secondary flow, with respect to the circle jet pipe, the enhancing mixed ability of lobe nozzle improves about 40%; Lobe nozzle can reduce lobe nozzle outlet static pressure in the bending of its outlet port profile, thereby strengthens the ejector capacity of main flow; With respect to single stage ejector, multistage lobe nozzle ejector not only can improve the whole ejector capacity of ejector, and can strengthen the mixing of main flow and secondary flow; This ejector is simple in structure, and industrial site applicatory is extensive.
Description of drawings
Fig. 1 is a lobe nozzle structural representation of the present invention;
Fig. 2 is a multistage lobe nozzle ejector structural representation of the present invention;
1 is the lobe nozzle straight section among the figure, the 2nd, and lobe nozzle lobe section, the 3rd, crest, the 4th, trough; The 5th, the one-level lobe nozzle, the 6th, the secondary lobe nozzle, 7 is three grades of lobe nozzles, the 8th, mixing tube; The 9th, one-level injection passage, the 10th, secondary injection passage, 11 is three grades of injection passages.
Embodiment
Below in conjunction with accompanying drawing to further explain of the present invention:
As shown in the figure: a kind of multistage lobe nozzle ejector with suction a secondary fluid, comprise straight section 1 and lobe section 2, described straight section 1 is arranged on the lobe section 2 and forms lobe nozzle; It is characterized in that: the ejector body comprises the lobe nozzle composition more than three grades or three grades; Described every grade of lobe nozzle is coaxial and arrange vertically; Diameter with first order lobe nozzle is a benchmark, and the diameter of the lobe nozzle of each grade is greater than the lobe nozzle diameter of previous stage backward.
Single lobe nozzle is made up of lobe nozzle straight section 1 and lobe nozzle lobe section 2.Multistage lobe nozzle ejector is as shown in Figure 2, is made up of one-level lobe nozzle 5, secondary lobe nozzle 6, three grades of lobe nozzles 7, mixing tubes 8.Main flow with certain pressure gets into one-level lobe nozzle 5; Go out the interruption-forming area of low pressure at lobe nozzle, first strand of a secondary fluid of injection is through one-level injection passage 9, and main flow flows along lobe nozzle crest 3 and produces the velocity component that flows radially outward; Secondary flow flows along the lobe nozzle trough and produces the velocity component that radially inwardly flows; Produce in lobe nozzle outlet and to flow to whirlpool, under the effect that flows to whirlpool, main flow and first burst of secondary flow are in the outlet mixed downstream of one-level lobe nozzle 5; Two strands of mixed fluids get into secondary lobe nozzle 6 in the lump; The lobe nozzle exit position produces the area of low pressure in the second level; Second burst of secondary flow of injection be through secondary injection path 10, and the mixed flow at the upper reaches and second burst of secondary flow are in the outlet mixed downstream of secondary lobe nozzle 6; Mixed flow gets into three grades of lobe nozzles 7; Produce the area of low pressure in 7 outlets of three grades of lobe nozzles; The 3rd burst of secondary flow of injection is through three grades of injection passages 11; Combined upstream stream and the 3rd burst of secondary flow get into mixing tube in the lump in the outlet mixed downstream of three grades of lobe nozzles 7, finally discharge multistage lobe ejector.Numerical result shows: at main flow flow 0.75kg/s, under the condition of stagnation temperature 820K, through multistage lobe nozzle ejector, the gas flow of injection external environment stagnation temperature 300K reaches 1.5kg/s altogether, whole ejector exit gas flow 2.25kg/s.The peak temperature of ejector exit gas is reduced to below the 480K, and mean temperature reaches below the 400K, and these data not only can explain that the injection volume of this ejector is big, and stronger mixed is arranged.
Say from structure; The factor that influences multistage lobe nozzle ejector performance (ability that ejector capacity, reinforcement main flow and secondary flow are mixed) has respectively: the progression of lobe nozzle; Ejector capacity strengthens along with the increase of lobe nozzle progression; But along with the increase of progression, the decay of main flow kinetic energy, ejector capacity is linear enhancing the along with progression not; Lobe nozzle lobe number, petal lobe nozzle lobe number increases, and flowing to the whirlpool number increases, and the mixing between main flow and secondary flow strengthens.The lobe nozzle expansion angle; Be the angle of crest and trough, along with the increase of expansion angle, main, inferior stream increases at the radial velocity component of lobe nozzle outlet; Lobe nozzle outlet port static pressure reduces; Flowing to whirlpool intensity simultaneously increases, thereby secondary flow flow and enhancing mixed ability all strengthen, and still excessive expansion angle can cause fluid on crest and trough face, to separate and produce loss.
Claims (4)
1. the multistage lobe nozzle ejector with suction a secondary fluid comprises straight section (1) and lobe section (2), and described straight section (1) is arranged in lobe section (2) and goes up the formation lobe nozzle; It is characterized in that: the ejector body comprises the lobe nozzle composition more than three grades or three grades; Described every grade of lobe nozzle is coaxial and arrange vertically; Diameter with first order lobe nozzle is a benchmark, and the diameter of the lobe nozzle of each grade is greater than the lobe nozzle diameter of previous stage backward.
2. the multistage lobe nozzle ejector with suction a secondary fluid according to claim 1 is characterized in that: lobe section (2) is made up of several crests (3) and trough (4), and crest (3) links to each other with trough (4) and forms ring-type lobe section; The port diameter of ring-type lobe Duan Yiduan is less than the another port diameter.
3. the multistage lobe nozzle ejector with suction a secondary fluid according to claim 1 and 2, it is characterized in that: the straight section (1) on described every grade of lobe nozzle is identical with the diameter of the maximum diameter end of this grade lobe section (2).
4. the multistage lobe nozzle ejector with suction a secondary fluid according to claim 1 is characterized in that: the gap between described every two-stage straight section (1) forms the injection passage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110436863XA CN102635578A (en) | 2011-12-23 | 2011-12-23 | Multilevel lobed nozzle ejector with secondary-fluid sucking function |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110436863XA CN102635578A (en) | 2011-12-23 | 2011-12-23 | Multilevel lobed nozzle ejector with secondary-fluid sucking function |
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| CN102635578A true CN102635578A (en) | 2012-08-15 |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105253629A (en) * | 2015-09-30 | 2016-01-20 | 山东钢铁股份有限公司 | Lobe type concentrated phase powder pumping system |
| CN105465048A (en) * | 2016-01-28 | 2016-04-06 | 中国科学院工程热物理研究所 | Fold-shaped pressure expander |
| CN108087303A (en) * | 2017-12-21 | 2018-05-29 | 南京航空航天大学 | Injection type centrifugal blower |
| CN109668739A (en) * | 2019-01-14 | 2019-04-23 | 南京航空航天大学 | A kind of test platform for more duct turbine nozzle Study on Integration |
| CN111042949A (en) * | 2019-11-19 | 2020-04-21 | 南京航空航天大学 | Wide-speed-range injection spray pipe integrated with aircraft and design method |
| CN111878253A (en) * | 2020-07-31 | 2020-11-03 | 中国人民解放军国防科技大学 | Wave-lobe rocket nozzle and rocket base combined circulating propulsion system |
| CN113550826A (en) * | 2021-07-28 | 2021-10-26 | 江苏科技大学 | Ejector device of exhaust volute of marine gas turbine |
| CN116163853A (en) * | 2023-02-16 | 2023-05-26 | 南京航空航天大学 | Lobe-adjustable spray pipe structure |
| CN116378847A (en) * | 2023-04-10 | 2023-07-04 | 南京航空航天大学 | Single-drive lobe nozzle structure with heat transfer and structural reinforcement |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US5440875A (en) * | 1993-06-25 | 1995-08-15 | United Technologies Corporation | Fixed geometry mixer/ejector suppression system for turbofan aircraft engines |
| US5761900A (en) * | 1995-10-11 | 1998-06-09 | Stage Iii Technologies, L.C. | Two-stage mixer ejector suppressor |
| CN101605978A (en) * | 2007-02-12 | 2009-12-16 | 斯奈克玛动力部件公司 | Make the method for the CMC flow mixer foliation structure of gas turbine aeroengine |
| WO2010120487A1 (en) * | 2009-04-16 | 2010-10-21 | Flodesign Wind Turbine Corporation | Wind turbine |
| CN102216604A (en) * | 2008-03-24 | 2011-10-12 | 弗洛设计风力涡轮机公司 | Turbine with mixers and ejectors |
-
2011
- 2011-12-23 CN CN201110436863XA patent/CN102635578A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5440875A (en) * | 1993-06-25 | 1995-08-15 | United Technologies Corporation | Fixed geometry mixer/ejector suppression system for turbofan aircraft engines |
| US5761900A (en) * | 1995-10-11 | 1998-06-09 | Stage Iii Technologies, L.C. | Two-stage mixer ejector suppressor |
| CN101605978A (en) * | 2007-02-12 | 2009-12-16 | 斯奈克玛动力部件公司 | Make the method for the CMC flow mixer foliation structure of gas turbine aeroengine |
| CN102216604A (en) * | 2008-03-24 | 2011-10-12 | 弗洛设计风力涡轮机公司 | Turbine with mixers and ejectors |
| WO2010120487A1 (en) * | 2009-04-16 | 2010-10-21 | Flodesign Wind Turbine Corporation | Wind turbine |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105253629A (en) * | 2015-09-30 | 2016-01-20 | 山东钢铁股份有限公司 | Lobe type concentrated phase powder pumping system |
| CN105465048A (en) * | 2016-01-28 | 2016-04-06 | 中国科学院工程热物理研究所 | Fold-shaped pressure expander |
| CN105465048B (en) * | 2016-01-28 | 2018-01-12 | 中国科学院工程热物理研究所 | A kind of fold shape diffuser |
| CN108087303A (en) * | 2017-12-21 | 2018-05-29 | 南京航空航天大学 | Injection type centrifugal blower |
| CN109668739A (en) * | 2019-01-14 | 2019-04-23 | 南京航空航天大学 | A kind of test platform for more duct turbine nozzle Study on Integration |
| CN111042949B (en) * | 2019-11-19 | 2021-06-29 | 南京航空航天大学 | Wide-speed-range injection spray pipe integrated with aircraft and design method |
| CN111042949A (en) * | 2019-11-19 | 2020-04-21 | 南京航空航天大学 | Wide-speed-range injection spray pipe integrated with aircraft and design method |
| CN111878253A (en) * | 2020-07-31 | 2020-11-03 | 中国人民解放军国防科技大学 | Wave-lobe rocket nozzle and rocket base combined circulating propulsion system |
| CN113550826A (en) * | 2021-07-28 | 2021-10-26 | 江苏科技大学 | Ejector device of exhaust volute of marine gas turbine |
| CN113550826B (en) * | 2021-07-28 | 2022-04-01 | 江苏科技大学 | Ejector device of exhaust volute of marine gas turbine |
| CN116163853A (en) * | 2023-02-16 | 2023-05-26 | 南京航空航天大学 | Lobe-adjustable spray pipe structure |
| CN116163853B (en) * | 2023-02-16 | 2023-08-11 | 南京航空航天大学 | Lobe-adjustable spray pipe structure |
| CN116378847A (en) * | 2023-04-10 | 2023-07-04 | 南京航空航天大学 | Single-drive lobe nozzle structure with heat transfer and structural reinforcement |
| CN116378847B (en) * | 2023-04-10 | 2023-09-29 | 南京航空航天大学 | Single-drive lobe nozzle structure with heat transfer and structural reinforcement |
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Application publication date: 20120815 |