CN203823810U - Advanced vortex combustor with flow deflectors - Google Patents
Advanced vortex combustor with flow deflectors Download PDFInfo
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- CN203823810U CN203823810U CN201420084504.1U CN201420084504U CN203823810U CN 203823810 U CN203823810 U CN 203823810U CN 201420084504 U CN201420084504 U CN 201420084504U CN 203823810 U CN203823810 U CN 203823810U
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- bluff body
- cavity
- blunt body
- combustor
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Abstract
The utility model discloses an advanced vortex combustor with flow deflectors. The advanced vortex combustor consists of a front blunt body, a concave cavity, a back blunt body, the flow deflectors and an air inlet channel, which are arranged in a combustor channel, wherein the front blunt body and the back blunt body are arranged in the combustor channel; the concave cavity is formed by the front blunt body and the back blunt body; the front wall surface of the front blunt body is flush with the channel; the back blunt body has a projecting expansion open structure; two flow deflectors are symmetrically arranged on the upper side and the lower side of the front blunt body; the air inlet channel consists of an upper small channel air inlet and a lower small channel air inlet. The advanced vortex combustor has the beneficial effects that the combustion performance is remarkably superior to the conventional blunt body combustor, the flame holding in the concave cavity and fuel gas blending are facilitated, the combustion efficiency is increased greatly, the outlet temperature distribution is improved, and NO discharge is reduced.
Description
Technical field
The utility model relates to a kind of device that rotary punching engine flows down at a high speed stable ignition burning and industry gas turbine high-efficient low polluting combustion that is applicable to, and is specifically related to a kind of advanced vortex combustion cavity with flow deflector.
Background technology
In modern aeroengine and industry gas turbine combustion chamber, advanced combustion method is to guarantee that main chamber performance meets the key that comprehensive Design requires comprehensively.U.S. Ramgen company has proposed the concept of advanced vortex combustion cavity (Advanced Vortex Combustor-AVC) in the development of rotary punching engine, in combustion chamber, arrange former and later two bluff bodies, the cavity forming between two bluff bodies catches backflow vortex and forms flame on duty region, and recirculating zone combustion product ignites primary combustion zone fuel and forms smooth combustion.Its seed region and primary zone are separate, can form stable backflow vortex to serving as incendiary source, the territory, primary zone of igniting under high speed incoming flow in cavity.That advanced vortex combustion cavity has is simple in structure, weight is light, flame stabilization field width and the plurality of advantages such as pollutant emission is low, is considered to the steady flame technology of potential high-performance low emission.
Stable ignition problem in advanced vortex combustion cavity cavity is the key of technique.Current investigative technique shows that cavity vortex pair structure is conducive to the performance of the combustion chamber of class in whirlpool combination property most.In cavity, vortex pair structure mainly relies on cavity front and back wall jet to form at present, at cavity front face, spray into fuel, blow in rear surface middle part, can in cavity, form small one and large one vortex pair structure, the maelstrom of downside plays point of safes burning things which may cause a fire disaster in burning, the micro cyclone of upside, near main flow, is conducive to the abundant blending of main flow and thermal source, improves combustibility.But cavity jet has certain deficiency: rear bluff body jet will arrive front bluff body rear end face could form vortex, and this just requires cavity length shorter, thereby causes ignition zone less.The air that rear bluff body sprays, due to close main flow, is subject to main flow impact and cannot forms stable double vortex structure.
Conventional dependence cavity jet forms the steady flame of the bluff body combustion chamber of vortex pair structure, need in cavity, arrange jet pipe or arrange jet orifice at bluff body wall, by mode of jet, fuel or air are sprayed into cavity, this mode has certain deficiency: the jet that enters cavity is easy to have influence on cavity spiral structure, and then it is stable to affect cavity flow field, is unfavorable for stable ignition; Can increase combustion chamber pitot loss, thereby combination property declines; Increase fuel consumption; Complex structure; It is more difficult that fuel and air mixing proportion are controlled.
Summary of the invention
The purpose of this utility model is to provide a kind of advanced vortex combustion cavity with flow deflector, its combustibility is obviously better than conventional bluff body combustion chamber, is conducive to strengthen the steady flame of cavity and gas mixing, increases substantially efficiency of combustion, improve outlet temperature and distribute, reduce NO discharge.
The utility model is achieved like this, by the front bluff body in chamber passage, cavity, rear bluff body, flow deflector and air intake duct, formed, it is characterized in that: in chamber passage, place front bluff body and rear bluff body, front bluff body and rear bluff body form cavity, front bluff body front face flushes with passage, rear bluff body is expansion type hatch frame, is positioned at the upper and lower bilateral symmetry layout of front bluff body and is provided with two flow deflectors, and air intake duct is upper and lower two passage aisle air inlets.
The cavity forming between front bluff body and rear bluff body that utilizes described in the utility model stabilizes the flame.
In the middle of rear bluff body described in the utility model, a passage is set, whole bluff body is divided into symmetrical two parts up and down, be convenient to the interior caloic of cavity and rear bluff body rear side and exchange.
Operation principle of the present utility model: the incoming flow of air inlet is through the shunting action of flow deflector, part air-flow enters primary zone, another part enters cavity generation vortex pair and serves as stable incendiary source, flow deflector shunting action can make combustion chamber in the situation that not relying on cavity jet, form two groups of development fully, evenly, symmetrical, stable vortex pair structure, maelstrom is wherein used for serving as stable incendiary source, micro cyclone is strengthened the blending of hot-fluid in main flow and cavity, heat and mass transfer enhancement, play the effect of covering main flow simultaneously, make incendiary source avoid the impact of main flow high velocity air.
Effect of the present utility model is: (1) its combustibility is obviously better than conventional bluff body combustion chamber, is conducive to strengthen the steady flame of cavity and gas mixing, increases substantially efficiency of combustion, improves outlet temperature and distributes, and reduces NO discharge; (2), when flow deflector structure parameter is suitable, low pressure drop, oligosaprobic smooth combustion can be realized in combustion chamber under lean-burn condition, and outlet temperature is evenly distributed; (3) without increasing in addition fuel in cavity, save fuel, at engineering manufacture view, compact conformation, is easy to processing, easy operating, and required parts can manufacture, and reduce costs, easy to maintenance.
Accompanying drawing explanation
Fig. 1 is structural representation of the present utility model.
Fig. 2 is the utility model cavity interior flow field distribution map.
Air inlet in the drawings, 1, front bluff body, 2, cavity, 3, rear bluff body, 4, flow deflector, 5, chamber passage, 6.
The specific embodiment
Below in conjunction with accompanying drawing, the utility model is further illustrated.
As shown in Figure 1, the utility model is to come like this work and enforcement, by the front bluff body 1 in chamber passage 5, cavity 2, rear bluff body 3, flow deflector 4 and air intake duct, formed, it is characterized in that: bluff body 1 and rear bluff body 3 before the interior placement of chamber passage 5, front bluff body 1 and rear bluff body 3 form cavity 2, front bluff body 1 front face flushes with chamber passage 5, rear bluff body 3 is expansion type hatch frame, be positioned at front bluff body Shang Xia 1 bilateral symmetry arrange and to be provided with two flow deflectors 4, air intake duct is upper and lower two passage aisle air inlets 6; In the middle of described rear bluff body 3, a passage is set, whole bluff body is divided into symmetrical two parts up and down, be convenient to the interior caloic of cavity and rear bluff body rear side and exchange; The cavity 2 forming between described front bluff body 1 and rear bluff body 3 stabilizes the flame.
The optimum size ratio of described each parts is: rear bluff body 3 is 0.7 with the width ratio of front bluff body 1, the length of cavity 2 is 0.6 times of front bluff body width, the vertical height of flow deflector 4 distance front bluff body 1 upper surfaces is 0.1 ~ 0.4 times of air intake duct width, the length that flow deflector 4 stretches into cavity 2 is 0.1 ~ 0.4 times of front bluff body 1 width, and the length of front bluff body 1 rear end face of flow deflector 4 distance is 0.1 ~ 0.2 times of cavity 2 length.
As shown in Figure 2, be the utility model combustion chamber cavity interior flow field distribution map, in the cavity of visible combustion chamber, formed two groups of vortex pair structures, and two groups of vortexs are full of cavity, symmetrically, independent between vortex, the steady flame effect of cavity is remarkable.
Claims (1)
1. the advanced vortex combustion cavity with flow deflector, by the front bluff body in chamber passage, cavity, rear bluff body, flow deflector and air intake duct, formed, it is characterized in that: in chamber passage, place front bluff body and rear bluff body, front bluff body and rear bluff body form cavity, front bluff body front face flushes with passage, be positioned at the upper and lower bilateral symmetry layout of front bluff body and be provided with two flow deflectors, rear bluff body is expansion type hatch frame, one passage is set in the middle of rear bluff body, whole bluff body is divided into symmetrical two parts up and down, and air intake duct is upper and lower two passage aisle air inlets.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
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CN201420084504.1U CN203823810U (en) | 2014-02-27 | 2014-02-27 | Advanced vortex combustor with flow deflectors |
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CN201420084504.1U CN203823810U (en) | 2014-02-27 | 2014-02-27 | Advanced vortex combustor with flow deflectors |
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CN203823810U true CN203823810U (en) | 2014-09-10 |
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CN201420084504.1U Expired - Fee Related CN203823810U (en) | 2014-02-27 | 2014-02-27 | Advanced vortex combustor with flow deflectors |
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Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN104359125A (en) * | 2014-10-30 | 2015-02-18 | 南京航空航天大学 | Central igniting mechanism of combustor of scramjet engine |
CN105020745A (en) * | 2015-07-15 | 2015-11-04 | 沈阳航空航天大学 | Standing vortex combustion chamber with guide plate and opening blunt body |
CN108954393A (en) * | 2018-09-30 | 2018-12-07 | 上海电力学院 | A kind of advanced standing vortex burning chamber of built-in flow spoiler |
CN109210573A (en) * | 2018-08-10 | 2019-01-15 | 江苏大学 | A kind of Novel variable-section aeroengine combustor buring room |
CN111023148A (en) * | 2020-01-14 | 2020-04-17 | 薛芳 | Adjustable spiral multi-stage oil-free coal powder igniter |
CN114777158A (en) * | 2022-05-13 | 2022-07-22 | 哈尔滨工程大学 | Combustion chamber mixing structure based on blunt body group |
-
2014
- 2014-02-27 CN CN201420084504.1U patent/CN203823810U/en not_active Expired - Fee Related
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN104359125A (en) * | 2014-10-30 | 2015-02-18 | 南京航空航天大学 | Central igniting mechanism of combustor of scramjet engine |
CN105020745A (en) * | 2015-07-15 | 2015-11-04 | 沈阳航空航天大学 | Standing vortex combustion chamber with guide plate and opening blunt body |
CN109210573A (en) * | 2018-08-10 | 2019-01-15 | 江苏大学 | A kind of Novel variable-section aeroengine combustor buring room |
CN109210573B (en) * | 2018-08-10 | 2023-08-18 | 江苏大学 | Novel variable cross-section aeroengine combustion chamber |
CN108954393A (en) * | 2018-09-30 | 2018-12-07 | 上海电力学院 | A kind of advanced standing vortex burning chamber of built-in flow spoiler |
CN111023148A (en) * | 2020-01-14 | 2020-04-17 | 薛芳 | Adjustable spiral multi-stage oil-free coal powder igniter |
CN114777158A (en) * | 2022-05-13 | 2022-07-22 | 哈尔滨工程大学 | Combustion chamber mixing structure based on blunt body group |
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C14 | Grant of patent or utility model | ||
GR01 | Patent grant | ||
CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140910 Termination date: 20150227 |
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EXPY | Termination of patent right or utility model |