CN109764357A - A kind of enhancing mixing device for sub--super shear flow - Google Patents
A kind of enhancing mixing device for sub--super shear flow Download PDFInfo
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- CN109764357A CN109764357A CN201811432779.9A CN201811432779A CN109764357A CN 109764357 A CN109764357 A CN 109764357A CN 201811432779 A CN201811432779 A CN 201811432779A CN 109764357 A CN109764357 A CN 109764357A
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Abstract
The invention discloses a kind of enhancing mixing device for sub--super shear flow, including enhancing mixing device ontology, enhance the upper lower wall surface of mixing device ontology two independent subsonic speed gas flows of formation between upper lower wall surface corresponding with combustion chamber respectively；Enhancing mixing device ontology include from front to back successively integrally connected solid head section, etc. straight cavity section and cavity section, offer the groove being respectively recessed towards respective side on the top plate of cavity section and the inner wall of bottom plate；Pass through from front to back in cavity section for central gas stream, forms recirculating zone in groove, flowed out by the rear end of cavity section, mixed with the subsonic airflow flowed out by subsonic speed gas flow.This is for Asia-super shear flow enhancing mixing device, so that air and combustion gas come into full contact with, and then increase the residence time of a combustion gas in a combustion chamber, the efficiency of combustion of a combustion gas is improved, to improve the overall performance of engine.
Description
Technical field
The invention belongs to assembly power technical field of engines, and in particular to a kind of enhancing for sub--super shear flow
Mixing device.
Background technique
In recent years, the development of assembly power engine increasingly accelerates, and embedded rocket type combined engine is preferable with it
Economical and wide operating range advantage is taken seriously, but the blending Chang Yiya-of the combustion gas and ram-air in the presence of it is super
The form of shear-mixed stream exists.Sub--super shear-mixed stream refers to that one identical subsonic flow of flow direction is super with one
Velocity of sound air-flow meets, and shear-mixed development is formed by compressible turbulent flow structure.But due to the big speed between two strands of air-flows
Degree difference and temperature difference have seriously affected the transmitting of the Energy-Momentum between two strands of air-flows, under this can make the working performance of engine serious
Drop improves its mixing efficiency, enhancing blends engineering with higher designed for the enhancing mixing device of sub--super shear-mixed
Value.
It is domestic at present that for the embedded rocket type combined engine Central Asia-super shear pattern, there is no feasible mixing enhancing sides
In addition to this formula is directed to the research of the super mixed intensified technology of shear-mixed stream of super- both at home and abroad, mainly uses flat plate shear form,
The research of cavity configuration convection current field structure influence is carried out, discovery is using after cavity configuration, and mixed layer scrollwork rises slightly in advance, stream
Field large-scale vortex structure is broken very fast.
Summary of the invention
It is a kind of for sub--super technical problem to be solved by the present invention lies in view of the above shortcomings of the prior art, providing
The enhancing mixing device of shear flow so that air and combustion gas come into full contact with, and then increases a combustion gas stopping in a combustion chamber
The time is stayed, the efficiency of combustion of a combustion gas is improved, to improve the overall performance of engine.
In order to solve the above technical problems, the technical solution adopted by the present invention is that, a kind of enhancing for sub--super shear flow
Mixing device, including enhancing mixing device ontology, enhancing mixing device ontology is for being placed in assembly power engine chamber
Inner Front End, front end enhance the upper lower wall surface of mixing device ontology upper lower wall corresponding with combustion chamber respectively towards direction of flow
Two independent subsonic speed gas flows are formed between face；Enhancing mixing device ontology includes the reality of successively integrally connected from front to back
Mind section, etc. straight cavity section and cavity section, cavity section be connected with cavity section, on the top plate of cavity section and the inner wall of bottom plate
The groove being respectively recessed towards respective side is offered, the position of upper and lower two grooves is corresponding；Groove is each perpendicular to direction of flow,
Width direction along cavity section opens up；Rear end in cavity section is provided with Laval nozzle, Laval nozzle back outlet patch
In the front end of groove；Pass through from front to back in cavity section for central gas stream, recirculating zone is formed in groove, after cavity section
End outflow accelerates to be mixed with the subsonic airflow flowed out by subsonic speed gas flow for supersonic flow.
Further, in the front end of cavity section and it is located at perforation on its left side wall or right side wall and offers one in outer
The central gas stream entrance that portion is connected.
Further, which is surrounded by two side plates of upper and lower two side plates and left and right, and the side plate of left and right two is upper
Lower end is more than the position where upper and lower two side plates, for being fastened in the card slot to burn in indoor left and right sidewall.
Further, which is wedgelike, and wedge head end comes towards air-flow to for subsonic speed gas to be divided into
Upper and lower two strands of air-flows.
Further, the left and right sides of the cavity section is open state or closed.
A kind of enhancing mixing device for sub--super shear flow of the present invention has the advantages that 1. are induced by cavity
Acoustic perturbation and from cavity rear be detached from large scale coherent structure enhance mixing, come into full contact with air and combustion gas, into
And increase the residence time of a combustion gas in a combustion chamber, the efficiency of combustion of a combustion gas is improved, to improve the whole of engine
Body performance.2. using the passive mixing enhancing technology of cavity form, with simple, the easy to process advantage of structure.
Detailed description of the invention
Fig. 1 is a kind of schematic perspective view of the enhancing mixing device for sub--super shear flow of the present invention.
Fig. 2 is a kind of structural schematic diagram of the enhancing mixing device for sub--super shear flow of the present invention.
The normalization thickness growth rate comparison diagram of the mixing device of Fig. 3 different configuration.
The Momentum mixing thickness comparison diagram of the mixing device of Fig. 4 different configuration.
Wherein: 1. head sections；2. central gas stream entrance；3. cavity section；3-1. groove；4. cavity section；4-1. or more two
Side plate；Two side plates of 4-2. or so；5. Laval nozzle；A. subsonic speed gas flow.
Specific embodiment
A kind of enhancing mixing device for sub--super shear flow of the present invention, as illustrated in fig. 1 and 2, including enhancing blending dress
Set ontology, enhancing mixing device ontology is for being placed in assembly power engine chamber Inner Front End, and front end is towards incoming flow side
To the upper lower wall surface for enhancing mixing device ontology forms two independent subsonic speed between upper lower wall surface corresponding with combustion chamber respectively
Gas flow a；Enhancing mixing device ontology include from front to back successively integrally connected solid head section 1, etc. straight 4 and of cavity section
Cavity section 3, cavity section 4 are connected with cavity section 3, offer on the top plate of cavity section 3 and the inner wall of bottom plate respectively towards right
The groove 3-1 for answering side recessed, the position of upper and lower two groove 3-1 are corresponding；Two groove 3-1 are each perpendicular to direction of flow, edge
The width direction of the cavity section 3 opens up；Rear end in cavity section 4 is provided with Laval nozzle 5,5 rear end of Laval nozzle
Outlet is affixed on the front end of groove 3-1；Pass through from front to back in cavity section 4 for central gas stream, forms reflux at groove 3-1
Area is flowed out by the rear end of cavity section 3, accelerates to be mixed with the subsonic airflow flowed out by subsonic speed gas flow a for supersonic flow
It closes.
Cavity section 4 front end and be located at perforation on its left side wall or right side wall and offer one and be connected in outside
Central gas stream entrance 2.Central gas stream entrance 2 and extraneous piping connection, high pressure gas are entered by the external world from central gas inflow entrance 2
Cavity supersonic runner flow to Laval nozzle 5.Supersonic flow after the acceleration of supersonic speed Laval nozzle 5, flow to cavity
After section 3, a recirculating zone can be formed in cavity section 3, is filled substantially with entire cavity section 3, so recirculating zone is larger, meanwhile,
The acoustic perturbation and mixing can be enhanced from the large scale coherent structure that cavity rear is detached from that groove 3-1 induces；Cavity section 3 is divided
Reattachment point from stream is located substantially near rear inflection point, and the shock strength of formation is weaker, and pitot loss is smaller.
The head sections 1 of enhancing mixing device ontology in the present invention are wedgelike, and wedge head end comes towards air-flow to use
Two strands of air-flows above and below being divided into subsonic speed gas.It shrinks the opposite side of the upper lower wall surface of head sections 1 from back to front toward each other.Gas
Vertically two skirt walls surface currents are dynamic for stream, are supersonic speed central jet making space.
It is coupled to realize with engine chamber, cavity section 4 is by upper and lower two side plate 4-1 and controls two side plates
4-2 is surrounded, and the upper and lower side of the two side plate 4-2 in left and right is more than the position where upper and lower two side plate 4-1, for being fastened in burning
In card slot in indoor left and right sidewall.It is easy for installation, do not need additional sealing device.The left and right sides of cavity section 3 is set as
Open state or closed, without specific requirement.Wherein the upper and lower side of the two side plate 4-2 in left and right is more than upper and lower two side plate 4-1
The position at place refers to that the upper end of the two side plate 4-2 in left and right is more than the upper end of upper and lower two side plate 4-1, and lower end is more than up and down
The lower end of two side plate 4-1.
By the enhancing mixing device with fluted 3-1 structure in the present invention and the mixing device point without groove structure
Experiment and numerical simulation study are not carried out, and experimental condition is that supersonic speed Mach number is 2.1, and subsonic speed Mach number is 0.75 left side
The right side, experimental study are captured by schlieren method convection current field structure, extract the super shear layer thickness in Asia-in result, and calculating is returned
The one shear layer thickness growth rate changed；Numerical simulation is by extracting the Momentum mixing thickness in result, to mixed effect momentum
Mixing thickness is characterized.Supersonic speed Mach number is 2.1, and subsonic speed Mach number is 0.75 or so,
Wherein: Momentum mixing thickness reflects the development and evolution in flow field deeply, large vortex stucture to and wait processes, lead
It will being evenly distributed degree and assess the height momentum thickness of mixability and consider presence due to shear layer based on velocity field
Caused by momentum flow rate loss.
Test result in bibliography is as benchmark.Wherein, what is provided in document is two bursts of differences in the same direction and parallel
The shear-mixed of the air-flow of speed normalizes thickness growth rate as shown in curve in Fig. 3.
In the present invention, test with groove 3-1 structure and without the mixing device of groove structure, the difference of the two structure
Un-grooved 3-1 has been only that it, the mixing device without groove structure is inventor's initial design, and the characterization result in experiment is such as
Under: without groove structure result as shown in circle in figure, by contrast with result by references more coincide, show the present invention used
Schlieren experiment system can be used for the research of sub--super mixed intensified effect of shear-mixed stream.
And the experimental result with fluted 3-1 configuration is as shown in cross in figure, in figure it is found that in the present invention with recessed
The enhancing mixing device of slot structure has preferable mixed intensified effect, compared with the mixing device without groove structure,
Normalization shear layer growth rate averagely increases 31.12%.That is, the blending with fluted 3-1 structure in the present invention
Compared with the device in the prior art that can be realized shear-mixed, normalization shear layer growth rate averagely increases device
31.12%.
Meanwhile numerical experiments have also been carried out, the Momentum mixing thickness extracted from numerical simulation result is along flow direction
Variation, as shown in Figure 4, wherein abscissa indicates that some puts the distance apart from nozzle exit in flow field, can obtain from figure
It arrives, with the development in flow field, increases obviously with curved cavity Momentum mixing thickness, which has apparent mixed intensified effect
Fruit.
Claims (5)
1. a kind of enhancing mixing device for sub--super shear flow, which is characterized in that including enhancing mixing device ontology, institute
Enhancing mixing device ontology is stated for being placed in assembly power engine chamber Inner Front End, front end is towards direction of flow, institute
The upper lower wall surface for stating enhancing mixing device ontology forms two independent subsonic speed between upper lower wall surface corresponding with combustion chamber respectively
Gas flow (a)；
The enhancing mixing device ontology include from front to back successively integrally connected solid head section (1), etc. straight cavity section (4)
With cavity section (3), the cavity section (4) is connected with cavity section (3), the top plate of the cavity section (3) and the inner wall of bottom plate
On offer respectively towards respective side be recessed groove (3-1), the position of upper and lower two grooves (3-1) is corresponding, the groove
(3-1) is each perpendicular to direction of flow, and the width direction along the cavity section (3) opens up；
Rear end in the cavity section (4) is provided with Laval nozzle (5), and Laval nozzle (5) back outlet is affixed on
The front end of the groove (3-1)；
Pass through from front to back in the cavity section (4) for central gas stream, recirculating zone is formed at groove (3-1), by cavity section
(3) rear end outflow, accelerates to be mixed with the subsonic airflow flowed out by subsonic speed gas flow (a) for supersonic flow.
2. a kind of enhancing mixing device for sub--super shear flow according to claim 1, which is characterized in that in institute
It states the front end of cavity section (4) and is located at perforation on its left side wall or right side wall and offer the center being connected in outside
Air flow inlet (2).
3. according to claim 2, which is characterized in that the cavity section (4) is by upper and lower two side plates (4-1) and left and right two
A side plate (4-2) surrounds, and the upper and lower side of two side plates (4-2) in the left and right is more than two side plates (4-1) places up and down
Position, for being fastened in the card slot to burn in indoor left and right sidewall.
4. a kind of enhancing mixing device for sub--super shear flow according to claim 3, which is characterized in that described
Head sections (1) are wedgelike, and wedge head end comes towards air-flow to for subsonic speed gas to be divided into two strands of air-flows up and down.
5. a kind of enhancing mixing device for sub--super shear flow according to claim 4, which is characterized in that described
The left and right sides of cavity section (3) is open state or closed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201811432779.9A CN109764357B (en) | 2018-11-28 | 2018-11-28 | A reinforcing mixing device for inferior-super shear flow |
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| CN201811432779.9A CN109764357B (en) | 2018-11-28 | 2018-11-28 | A reinforcing mixing device for inferior-super shear flow |
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| CN109764357A true CN109764357A (en) | 2019-05-17 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112179664A (en) * | 2020-08-29 | 2021-01-05 | 西北工业大学 | Adjustable low-pressure ignition experimental system for researching sub-super mixed flow |
| CN112282972A (en) * | 2020-10-21 | 2021-01-29 | 西北工业大学 | Low-pressure sub-super shear flow experiment system with high-temperature subsonic air |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20010019041A1 (en) * | 2000-02-18 | 2001-09-06 | L'air Liquide, Societe Anonyme | Process and unit for plasma-arc working with a gas having controlled O2 and N2 contents |
| JP3246153B2 (en) * | 1994-01-21 | 2002-01-15 | 石川島播磨重工業株式会社 | Exhaust nozzle for supersonic aircraft |
| CN101053857A (en) * | 2007-02-12 | 2007-10-17 | 曹学文 | Super-sonic diffuser for super-sonic vortex flow natural gas separator |
| CN102384473A (en) * | 2010-08-25 | 2012-03-21 | 中国科学院工程热物理研究所 | Flameless trapped vortex burner for gas turbine |
| CN103925116A (en) * | 2014-04-28 | 2014-07-16 | 中国航天空气动力技术研究院 | Sliding arc ignition device |
| CN104100420A (en) * | 2008-07-03 | 2014-10-15 | Hrd有限公司 | System for generating aerated fuels |
| US20150013305A1 (en) * | 2009-11-19 | 2015-01-15 | U.S.A. As Represented By The Administrator Of The National Aeronautics And Space Administration | Dual-Mode Combustor |
| CN107013327A (en) * | 2017-02-17 | 2017-08-04 | 北京动力机械研究所 | A kind of double combustion chamber's scramjet engine and its control method |
| CN108561897A (en) * | 2017-12-27 | 2018-09-21 | 中国航发四川燃气涡轮研究院 | A kind of partly-premixed prevapourising minimum discharge combustion chamber for strengthening air-fuel mixture |
| CN108709715A (en) * | 2018-05-25 | 2018-10-26 | 西北工业大学 | A kind of adjustable sub--super shear layer research experiment device of incoming parameter wide scope |
-
2018
- 2018-11-28 CN CN201811432779.9A patent/CN109764357B/en not_active Expired - Fee Related
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP3246153B2 (en) * | 1994-01-21 | 2002-01-15 | 石川島播磨重工業株式会社 | Exhaust nozzle for supersonic aircraft |
| US20010019041A1 (en) * | 2000-02-18 | 2001-09-06 | L'air Liquide, Societe Anonyme | Process and unit for plasma-arc working with a gas having controlled O2 and N2 contents |
| CN101053857A (en) * | 2007-02-12 | 2007-10-17 | 曹学文 | Super-sonic diffuser for super-sonic vortex flow natural gas separator |
| CN104100420A (en) * | 2008-07-03 | 2014-10-15 | Hrd有限公司 | System for generating aerated fuels |
| US20150013305A1 (en) * | 2009-11-19 | 2015-01-15 | U.S.A. As Represented By The Administrator Of The National Aeronautics And Space Administration | Dual-Mode Combustor |
| CN102384473A (en) * | 2010-08-25 | 2012-03-21 | 中国科学院工程热物理研究所 | Flameless trapped vortex burner for gas turbine |
| CN103925116A (en) * | 2014-04-28 | 2014-07-16 | 中国航天空气动力技术研究院 | Sliding arc ignition device |
| CN107013327A (en) * | 2017-02-17 | 2017-08-04 | 北京动力机械研究所 | A kind of double combustion chamber's scramjet engine and its control method |
| CN108561897A (en) * | 2017-12-27 | 2018-09-21 | 中国航发四川燃气涡轮研究院 | A kind of partly-premixed prevapourising minimum discharge combustion chamber for strengthening air-fuel mixture |
| CN108709715A (en) * | 2018-05-25 | 2018-10-26 | 西北工业大学 | A kind of adjustable sub--super shear layer research experiment device of incoming parameter wide scope |
Non-Patent Citations (1)
| Title |
|---|
| 汤祥: ""RBCC支板火箭超燃模态动态过程与性能研究"", 《中国优秀博士学位论文全文数据库 工程科技Ⅱ辑》 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112179664A (en) * | 2020-08-29 | 2021-01-05 | 西北工业大学 | Adjustable low-pressure ignition experimental system for researching sub-super mixed flow |
| CN112179664B (en) * | 2020-08-29 | 2021-07-23 | 西北工业大学 | Adjustable low-pressure ignition experimental system for researching sub-super mixed flow |
| CN112282972A (en) * | 2020-10-21 | 2021-01-29 | 西北工业大学 | Low-pressure sub-super shear flow experiment system with high-temperature subsonic air |
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