CN105588144A - Flame steady combustion device and method for combustion chamber of gas turbine - Google Patents
Flame steady combustion device and method for combustion chamber of gas turbine Download PDFInfo
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- CN105588144A CN105588144A CN201610118888.8A CN201610118888A CN105588144A CN 105588144 A CN105588144 A CN 105588144A CN 201610118888 A CN201610118888 A CN 201610118888A CN 105588144 A CN105588144 A CN 105588144A
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- combustion chamber
- bluff body
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
- F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
- F23R3/20—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection means
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Combustion Of Fluid Fuel (AREA)
Abstract
The invention provides a flame steady combustion device and method for a combustion chamber of a gas turbine. A nozzle is arranged on the front wall portion of the combustion chamber. The flame steady combustion device comprises a plurality of ventilation bluff bodies arranged on the front wall portion of the combustion chamber, and the ventilation bluff bodies are evenly arranged around the outer side face of the nozzle. The gas inlet end faces of the ventilation bluff bodies are provided with ventilation flow passes which communicate with the inside of the combustion chamber. The ventilation flow passes extend outwards in the radial direction of the nozzle from the outside of the nozzle. The ventilation flow passes are gradually expanded outwards in the gas circulation direction. By the adoption of the device, two standing vortexes can be formed in the combustion chamber. Compared with an existing structure, the flame steady combustion device and method has better steady combustion capacity.
Description
Technical field
The present invention relates to gas-turbine combustion chamber technical field, particularly relate to a kind of fire for gas-turbine combustion chamberFlame smooth combustion apparatus and flame smooth burning method.
Background technology
The advantages such as gas turbine is simple in structure owing to having, single-machine capacity is large, weight and size is little, mobility is good, by extensiveBe applied to many industrial circles such as aviation, boats and ships, electric power, oil. Combustion chamber is as the critical piece of gas turbine, in structureOn there is essentially identical feature, the version of combustion chamber is aerothermodynamic aspect factor and the combustion while working based on combustion chamberThe common requirement of these two aspects of the basic law that burning process is followed considers and designs, and aerothermodynamic aspect factor is for exampleCombustor exit temperature, stability, starting ignition, efficiency of combustion, durability, disposal of pollutants characteristic etc. The merit that combustion chamber is mainCan be that diffusion reduction of speed, fuel are prepared, form low regime or recirculating zone and stabilize the flame. The optimal design of head of combustion chamber structure, elder generationEntering fuel-oil atmozation mode and advanced combustion chamber cooling technology is the important channel that solves above-mentioned technological challenge.
According to Theory of Combustion, in high velocity air, stabilize the flame, must be at least some spatial point in burner inner liner insideThe region that place's structure local air flow speed equates with the flame propagation velocity of this place's combustion mixture, i.e. alleged igniting conventionallySource. In combustion chamber, the design main points of flame smooth combustion apparatus are structure low speed flow regions. Conventional structure low speed flow regionMethod can be divided into two kinds, one be adopt entity structure, as strong eddy flow, sudden expansion, groove etc., another kind adopts pneumatic knotStructure, as contrainjection, transverse injection etc. The method of existing structure low speed flow region can only form one and stay whirlpool, stable combustionThe ability of burning is very limited.
The effect of flame smooth combustion apparatus in combustion chamber can be summarized as following 3 points: 1) form and reflux at burner inner liner headDistrict, reduces the air velocity that enters combustion chamber, thereby forms stable ignition source at burner inner liner head, steadily can in guarantee combustion chamberBy ground work; 2) coordinate with pressure atomized fog jet, aspect the broken atomization of promotion fuel oil, playing an important role; 3) be burner inner linerHead provides appropriate air, ensures that head has applicable excess air coefficient. As can be seen here, as the weight of combustion chamber flame drumWant assembly, flame smooth combustion apparatus has comprehensive impact to the service behaviour of combustion chamber, and the lifting of combustion chamber overall performance is hadFacilitation greatly. Existing chamber structure can only form one and stay whirlpool, and the ability of smooth combustion is very limited.
Summary of the invention
The shortcoming of prior art in view of the above, the technical problem to be solved in the present invention is to provide one to realizeStay whirlpool for two, there is the flame smooth combustion apparatus for gas-turbine combustion chamber and the flame smooth burning method of better steady combustion ability.
In order to solve the problems of the technologies described above, the invention provides a kind of flame smooth combustion apparatus for gas-turbine combustion chamber,The front wall portion of combustion chamber is provided with nozzle, and described flame smooth combustion apparatus comprises on multiple front wall portions that are arranged at described combustion chamberVentilation bluff body, multiple described ventilation bluff bodies are evenly arranged around the lateral surface of described nozzle; The air inlet end face of described ventilation bluff bodyBe provided with and the venting flow path of the internal communication of described combustion chamber, described venting flow path is from the outside of described nozzle along described sprayExtending radially outwardly of mouth; Described venting flow path expands outwardly gradually along gas communication direction.
Preferably, the radial section at the place, gas outlet of described venting flow path is vertical with described front wall portion.
Preferably, on the medial surface of the front wall portion of the gas outlet of described venting flow path in described combustion chamber.
Preferably, each described ventilation bluff body comprises the first bluff body portion and the second bluff body portion that one end is connected, describedTwo bluff body portions are obliquely installed with respect to described the first bluff body portion, the other end of described the first bluff body portion and described the second bluff body portionThe peristome forming between the other end is towards nozzle; The air inlet end face of described the first bluff body portion is provided with first flow, and describedThe air inlet end face of two bluff body portions is provided with the second runner; Described first flow is communicated with described the second runner, forms venting flow path;The angle forming between described first flow and described the second runner is runner angle; Described runner angle is along with described ventilation is flowedThe gas communication direction in road increases gradually.
Further, described the first bluff body portion and described the second bluff body portion are plate body, the outside of described the first bluff body portionAngle between the lateral surface of face and the second bluff body portion and described front wall portion is all greater than 90 degree.
The invention still further relates to a kind of flame that adopts the described flame smooth combustion apparatus for gas-turbine combustion chamber surely firesMethod, on the side of combustion chamber along being circumferentially evenly arranged several primary holes, and described in several primary holes in describedThe middle part of combustion chamber; Nozzle sprays into fuel oil to the inside of described combustion chamber, and combustion reaction is carried out in the inside of described combustion chamber; DescribedIn primary holes, pass into air, meanwhile, described in air also enters by the venting flow path expanding outwardly gradually of described ventilation bluff bodyThe inside of combustion chamber, and the axial axial flow in the same way oblique air-flow mobile with being affixed to wall of formation and described combustion chamber,Described axial flow forms one-level and stays whirlpool; When oblique air current flow arrives the middle part of described combustion chamber, be subject to the sky of described primary holesThe effect of gas jet, blending mutually, forms secondary and stays whirlpool; Described one-level is subject to the high temperature reflux of the inside of described combustion chamber in whirlpoolEffect, the fuel oil of described nozzle ejection is carried out to prevapourising, pre-cracking; Described secondary is stayed whirlpool for stabilizing the flame region, fuel oilStabilize the flame zonal combustion described.
As mentioned above, the flame smooth combustion apparatus for gas-turbine combustion chamber of the present invention and flame smooth burning method, haveFollowing beneficial effect:
Flame smooth combustion apparatus of the present invention has the venting flow path of multiple expansion shapes, after gas is by venting flow path, formsAir-flow, there will be by wind region in the gas outlet of venting flow path, and a part of air-flow is and the axially axle in the same way of described combustion chamberTo air-flow, axial flow can formed one-level in whirlpool by wind region; First the fuel oil gushing out from nozzle stays whirlpool through one-level,Under the effect of high temperature reflux, carry out prevapourising and pre-cracking, contribute to fire oil atomization and fully burning; Another part air-flow isBe affixed to the oblique air-flow that wall flows, when oblique air current flow arrives the middle part of described combustion chamber, by the jet action of primary holes,Blending mutually, has formed secondary region in whirlpool, and secondary is stayed whirlpool as stabilizing the flame region, is stabilizing the flame region, and fuel oil is a large amount ofBurning, combustion process to oil-poor transition, stabilizes the flame the primary zone that region is equivalent to traditional combustion chamber by rich oil, make fuel withAir fully reacts. Adopt device of the present invention can in combustion chamber, form two and stay whirlpool, flame smooth combustion apparatus of the present inventionAnd flame smooth burning method has better steady combustion ability compared with existing structure.
Brief description of the drawings
Fig. 1 be shown as the present embodiment the flame smooth combustion apparatus for gas-turbine combustion chamber use time structural representationFigure.
Fig. 2 is shown as the inlet end of the ventilation bluff body of the flame smooth combustion apparatus for gas-turbine combustion chamber of the present embodimentThe perspective view at face place.
Fig. 3 is shown as the ventilation stream of the ventilation bluff body of the flame smooth combustion apparatus for gas-turbine combustion chamber of the present embodimentThe perspective view at the gas outlet place in road.
Fig. 4 is shown as the inlet end of the ventilation bluff body of the flame smooth combustion apparatus for gas-turbine combustion chamber of the present embodimentThe schematic cross-section at face place.
Fig. 5 is shown as the ventilation stream of the ventilation bluff body of the flame smooth combustion apparatus for gas-turbine combustion chamber of the present embodimentThe schematic cross-section at the gas outlet place in road.
When Fig. 6 is shown as the use of the flame smooth combustion apparatus for gas-turbine combustion chamber of the present embodiment, forms one-level and stayWhirlpool and secondary are stayed the schematic diagram in whirlpool.
Drawing reference numeral explanation
100 combustion chambers
110 front wall portions
The medial surface of 111 front wall portions
120 combustion barrel bodies
121 primary holes
200 nozzles
210 jets
300 ventilation bluff bodies
310 air inlet end faces
320 venting flow path
321 gas outlets
410 first bluff body portions
411 first flows
420 second bluff body portions
421 second runners
510 one-levels are stayed whirlpool
520 secondarys are stayed whirlpool
α runner angle
Detailed description of the invention
By particular specific embodiment explanation embodiments of the present invention, person skilled in the art scholar can be illustrated by this belowThe disclosed content of book is understood other advantages of the present invention and effect easily.
Refer to accompanying drawing. Notice, appended graphic the illustrated structure of this description, ratio, size etc., all only in order to coordinateThe content that description discloses, understands and reads for person skilled in the art scholar, not enforceable in order to limit the present inventionQualifications, thus the technical essential meaning of tool not, the adjustment of the modification of any structure, the change of proportionate relationship or size,Do not affect under effect that the present invention can produce and the object that can reach, all should still drop on disclosed technology contentsObtain in the scope that can contain. Meanwhile, in this description, quote as " on ", D score, " left side ", " right side ", " centre " and " one " etc.Term, also only for ease of the understanding of narration, but not in order to limit the enforceable scope of the present invention, the change of its relativeness orAdjust, changing under technology contents, when being also considered as the enforceable category of the present invention without essence.
As shown in Figures 1 to 6, the flame smooth combustion apparatus for gas-turbine combustion chamber 100 of the present embodiment, combustion chamber100 comprise combustion barrel body 120 and are arranged at the front wall portion 110 on combustion barrel body 120, and front wall portion 110 is provided with nozzle200, the jet 210 of nozzle 200 stretches in combustion barrel body 120; On the side of combustion barrel body 120 along circumferential evenly clothBe equipped with several primary holes 121, and several primary holes 121 middle parts in combustion barrel body 120; In the present embodiment, main combustionThe aperture in hole 121 is 8mm, and combustion barrel body 120 is cylindrical;
Flame smooth combustion apparatus comprises the ventilation bluff body 300 on multiple front wall portions 110 that are arranged at combustion chamber 100, Duo GetongGas bluff body 300 is evenly arranged around the lateral surface of nozzle 200; The air inlet end face 310 of ventilation bluff body 300 is provided with and combustion chamberThe venting flow path 320 of 100 internal communication, venting flow path 320 is from outside radially outward the prolonging along nozzle 200 of nozzle 200Stretch; Venting flow path 320 expands outwardly gradually along gas communication direction, and the size of venting flow path 320 is along gas communication sideTo increasing gradually.
Flame smooth combustion apparatus has the venting flow path 320 of multiple expansion shapes, because venting flow path 320 is from nozzle 200Portion extends radially outwardly along nozzle 200, and venting flow path 320 expands outwardly gradually along gas communication direction, and ventilation streamThe size in road 320 increases gradually along gas communication direction; So, when gas is by expanding outwardly gradually after venting flow path 320Form air-flow, there will be by wind region in the gas outlet 321 of venting flow path 320, a part of air-flow be with combustion chamber 100 axiallyAxial flow in the same way, axial flow can formed one-level in whirlpool 510 by wind region; The fuel oil gushing out from nozzle 200 firstStay whirlpool 510 through one-level, under the effect refluxing in the internal high temperature of combustion barrel body 120, carry out prevapourising and pre-cracking, helpIn combustion oil atomization and fully burning; Another part air-flow is to be affixed to the oblique air-flow that wall flows, and oblique air current flow is to combustionWhile burning the middle part of chamber 100, by the jet action of primary holes 121, formed secondary and stayed 520 regions, whirlpool, secondary is stayed whirlpool 520 conductsStabilize the flame region, stabilizing the flame region, fuel oil burns in a large number, and combustion process to oil-poor transition, stabilizes the flame district by rich oilTerritory is equivalent to the primary zone of traditional combustion chamber 100, and fuel is fully reacted with air.
The radial section at 321 places, gas outlet of venting flow path 320 is vertical with front wall portion 110. This structure can be convenient to shapeBecome one-level to stay whirlpool 510 and secondary and stay whirlpool 520, one-level stay whirlpool 510 and secondary stay the region that whirlpool 520 forms can be by obvious districtNot.
On the medial surface 111 of the front wall portion 110 of the gas outlet 321 of venting flow path 320 in combustion chamber 100. This structure makesAxial flow can form one-level in the position of the jet of more close nozzle 200 210 and stay whirlpool 510.
In the present embodiment, each ventilation bluff body 300 comprises the first bluff body portion 410 and the second bluff body portion that one end is connected420, the second bluff body portions 420 are obliquely installed with respect to the first bluff body portion 410, the other end of the first bluff body portion 410 and the second bluff bodyThe peristome forming between the other end of portion 420 is towards nozzle 200; The air inlet face of the first bluff body portion 410 is provided with first flowThe air inlet face of 411, the second bluff body portions 420 is provided with the second runner 421; First flow 411 is communicated with the second runner 421, formsVenting flow path 320; The angle forming between first flow 411 and the second runner 421 is runner angle α; Runner angle α is along with logicalThe gas communication direction of flow channel 320 increases gradually.
Each ventilation bluff body 300 is to form the structure with angle by the first bluff body portion 410 and the second bluff body portion 420, manyIndividual ventilation bluff body 300 is evenly arranged around the lateral surface of nozzle 200, just can form star structure; The quantity of ventilation bluff body 300For even number, in the present embodiment, the quantity of ventilation bluff body 300 is 6, because runner angle α is along with the gas of venting flow path 320Circulating direction increases gradually, namely formed the star structure of the venting flow path 320 gradually with expansion, makes the present embodimentThe structure of flame smooth combustion apparatus is more compact. Be connected to form by the first bluff body portion 410 and the second bluff body portion 420 with angleStructure, the oblique air-flow that can make first flow 411 and the second runner 421 discharge is converged, and makes each ventilation bluff body 300Oblique air-flow more concentrated, improve flow and the flow velocity of oblique air-flow, be convenient to form stable secondary and stay whirlpool 520.
In the present embodiment, ventilation bluff body 300 is less than ventilation bluff body 300 and front wall portion with the distance of the lateral surface of nozzle 200The distance at 110 edges, so forming one-level can be near the jet 210 of nozzle 200 in the axial flow in whirlpool 510, one-level is stayedPrevapourising and pre-cracking can be carried out to fuel oil fully in whirlpool 510.
In the present embodiment, the radial section of first flow 411 and the second runner 421 is rectangle, the first bluff body portion 410All be set to plate body with the second bluff body portion 420, the lateral surface of the lateral surface of the first bluff body portion 410 and the second bluff body portion 420 and frontAngle between wall portion 110 is all greater than 90 degree. The overall structure that this structure makes the first bluff body portion 410 and the second bluff body portion 420 withThe structure of the venting flow path 320 of expansion is consistent gradually.
Adopt the flame smooth burning method of the flame smooth combustion apparatus for gas-turbine combustion chamber 100 of the present embodiment, nozzle200 spray into fuel oil to the inside of combustion chamber 100, and combustion reaction is carried out in the inside of combustion chamber 100; In primary holes 121, pass into air,Meanwhile, air also enters the inside of combustion chamber 100 by the venting flow path expanding outwardly gradually 320 of ventilation bluff body 300, and shapeBecome the oblique air-flow mobile with being affixed to wall with the axial axial flow in the same way of combustion chamber 100, axial flow forms one-level and staysWhirlpool 510; When oblique air current flow arrives the middle part of combustion chamber 100, be subject to the effect of the air-spray of primary holes 121, blending mutually,Form secondary and stay whirlpool 520; One-level is subject to the effect of the high temperature reflux of the inside of combustion chamber 100 in whirlpool 510, nozzle 200 is sprayedFuel oil carry out prevapourising, pre-cracking; Secondary is stayed whirlpool 520 for stabilizing the flame region, and fuel oil fires stabilizing the flame regional stabilityBurn.
In the present embodiment, each ventilation bluff body 300 is connected to form by the first bluff body portion 410 and the second bluff body portion 420With the structure of angle, even number ventilation bluff body 300 is taking the axis of nozzle 200 axially symmetric structure as symmetry axis, eachVentilation bluff body 300 structures are identical, and the medial surface 111 of each venting flow path 320 and combustion chamber 100 front wall portions 110 forms bluff body knotStructure passes into after air in venting flow path 320, there will be the undersized whirlpool of staying to reflux by wind face axial flow, and one-level is stayedWhirlpool 510, this region can form prevapourising, pre-splitting action to fuel oil. Multiple venting flow path 320 form a circle into star knotStructure, the middle part of combustion barrel body 120 is owing to being provided with primary holes 121, and the air-spray effect of primary holes 121 makes combustion barrel originallyLow-pressure area centered by the middle part of body 120, the effect of oblique air-flow acceptor center low-pressure area, forms secondary and stays whirlpool 520, becomes combustion chamber100 main recirculating zone. Adopt device of the present invention can in combustion chamber 100, form two and stay whirlpool, flame of the present invention surely firesDevice and flame smooth burning method have better steady combustion ability compared with existing structure.
To sum up, the present invention has effectively overcome various shortcoming of the prior art and tool high industrial utilization.
Above-described embodiment is illustrative principle of the present invention and effect thereof only, but not for limiting the present invention. Any ripeThe personage who knows this technology all can, under spirit of the present invention and category, modify or change above-described embodiment. CauseThis, have in technical field under such as conventionally know the knowledgeable do not depart under disclosed spirit and technological thought completeAll equivalences that become are modified or change, and must be contained by claim of the present invention.
Claims (6)
1. for a flame smooth combustion apparatus for gas-turbine combustion chamber, the front wall portion (110) of combustion chamber (100) is provided with nozzle(200), it is characterized in that,
Described flame smooth combustion apparatus comprises the ventilation bluff body on multiple front wall portions (110) that are arranged at described combustion chamber (100)(300), multiple described ventilation bluff bodies (300) are evenly arranged around the lateral surface of described nozzle (200);
The air inlet end face (310) of described ventilation bluff body (300) is provided with the ventilation stream with the internal communication of described combustion chamber (100)Road (320), described venting flow path (320) is from outside radially outward the prolonging along described nozzle (200) of described nozzle (200)Stretch; Described venting flow path (320) expands outwardly gradually along gas communication direction.
2. the flame smooth combustion apparatus for gas-turbine combustion chamber according to claim 1, is characterized in that: described ventilationThe radial section at the place, gas outlet (321) of runner (320) is vertical with described front wall portion (110).
3. the flame smooth combustion apparatus for gas-turbine combustion chamber according to claim 1, is characterized in that: described ventilationOn the medial surface (111) of the front wall portion (110) of the gas outlet (321) of runner (320) in described combustion chamber (100).
4. the flame smooth combustion apparatus for gas-turbine combustion chamber according to claim 1, is characterized in that: described in eachVentilation bluff body (300) comprises the first bluff body portion (410) and the second bluff body portion (420) that one end is connected, described the second bluff body portion(420) be obliquely installed the other end of described the first bluff body portion (410) and described second with respect to described the first bluff body portion (410)The peristome forming between the other end of bluff body portion (420) is towards described nozzle (200);
Described the first bluff body portion (410) is provided with first flow (411), and described the second bluff body portion (420) is provided with the second runner(421); Described first flow (411) is communicated with described the second runner (421), forms venting flow path (320); Described first flow(411) angle forming and between described the second runner (421) is runner angle; Described runner angle is along with described venting flow path(320) gas communication direction increases gradually.
5. the flame smooth combustion apparatus for gas-turbine combustion chamber according to claim 4, is characterized in that: described firstBluff body portion (410) and described the second bluff body portion (420) are plate body, the lateral surface of described the first bluff body portion (410) and second bluntAngle between the lateral surface of body (420) and described front wall portion (110) is all greater than 90 degree.
6. adopt the flame smooth burning method of the flame smooth combustion apparatus for gas-turbine combustion chamber claimed in claim 1, its spyLevy and be:
On the side of combustion chamber (100) along being circumferentially evenly arranged several primary holes (121), and primary holes described in several(121) middle part in described combustion chamber (100);
Nozzle (200) sprays into fuel oil to the inside of described combustion chamber (100), burns instead in the inside of described combustion chamber (100)Should; Described primary holes passes into air in (121), and meanwhile, air is expanding outwardly by described ventilation bluff body (300) gradually alsoVenting flow path (320) enters the inside of described combustion chamber (100), and the axial axle in the same way of formation and described combustion chamber (100)To the air-flow oblique air-flow mobile with being affixed to wall, described axial flow forms one-level and stays whirlpool (510); Oblique air current flow is to instituteWhile stating the middle part of combustion chamber (100), be subject to the effect of the air-spray of described primary holes (121), blending mutually, forms secondary and staysWhirlpool;
Described one-level is subject to the effect of the high temperature reflux of the inside of described combustion chamber (100) in whirlpool (510), to described nozzle(200) fuel oil of ejection carries out prevapourising, pre-cracking; Described secondary is stayed whirlpool (520) for stabilizing the flame region, and fuel oil is described steadyDetermine flame region burning.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201610118888.8A CN105588144B (en) | 2016-03-02 | 2016-03-02 | Flame smooth combustion apparatus and flame smooth burning method for gas-turbine combustion chamber |
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| CN201610118888.8A CN105588144B (en) | 2016-03-02 | 2016-03-02 | Flame smooth combustion apparatus and flame smooth burning method for gas-turbine combustion chamber |
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| CN105588144B CN105588144B (en) | 2018-01-26 |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108131685A (en) * | 2017-12-14 | 2018-06-08 | 西北工业大学 | Tiny engine combustion chamber multi-point injection evaporation tube |
| CN108426267A (en) * | 2018-05-11 | 2018-08-21 | 北京航空航天大学 | A kind of folding V-type bluff body eddy flameholder |
| CN109631084A (en) * | 2018-12-13 | 2019-04-16 | 西安航天动力研究所 | Scramjet combustor stabilizer and steady flame method |
| CN114777158A (en) * | 2022-05-13 | 2022-07-22 | 哈尔滨工程大学 | Combustion chamber mixing structure based on blunt body group |
| CN117109029A (en) * | 2023-08-25 | 2023-11-24 | 西南科技大学 | Blunt body flame stabilizer and aeroengine combustion assembly |
Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20060288706A1 (en) * | 2004-04-12 | 2006-12-28 | General Electric Company | Method for operating a reduced center burner in multi-burner combustor |
| JP2007163032A (en) * | 2005-12-14 | 2007-06-28 | Seiji Ohara | Oil-burning tube bundle combustion boiler using collision type atomizer |
| WO2008153444A2 (en) * | 2007-06-13 | 2008-12-18 | Leonid Nikolaevich Parfenov | Flare device |
| US20090151360A1 (en) * | 2007-12-18 | 2009-06-18 | United Technologies Corporation | Combustor |
| CN101725969A (en) * | 2010-01-19 | 2010-06-09 | 中国计量学院 | Low-NOx pulverized coal burner |
| CN101776283A (en) * | 2009-01-13 | 2010-07-14 | 北京航空航天大学 | Flame stabilizer with jet injection |
| CN103017203A (en) * | 2012-12-06 | 2013-04-03 | 中国科学院工程热物理研究所 | Fractional combustion chamber |
| CN103277816A (en) * | 2013-05-10 | 2013-09-04 | 南京航空航天大学 | Lean oil pre-mixing pre-evaporation low-emission standing vortex combustion chamber |
| CN204176638U (en) * | 2014-10-22 | 2015-02-25 | 中节环（北京）环境科技股份有限公司 | The portable coal burner of bluff body |
| CN104748111A (en) * | 2015-03-24 | 2015-07-01 | 华南理工大学 | Micro-combustor for metal mesh heat storage and flame stabilization and combustion method thereof |
| CN205388321U (en) * | 2016-03-02 | 2016-07-20 | 上海电气燃气轮机有限公司 | A flame surely fires device for combustion chamber |
-
2016
- 2016-03-02 CN CN201610118888.8A patent/CN105588144B/en active Active
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20060288706A1 (en) * | 2004-04-12 | 2006-12-28 | General Electric Company | Method for operating a reduced center burner in multi-burner combustor |
| JP2007163032A (en) * | 2005-12-14 | 2007-06-28 | Seiji Ohara | Oil-burning tube bundle combustion boiler using collision type atomizer |
| WO2008153444A2 (en) * | 2007-06-13 | 2008-12-18 | Leonid Nikolaevich Parfenov | Flare device |
| US20090151360A1 (en) * | 2007-12-18 | 2009-06-18 | United Technologies Corporation | Combustor |
| CN101776283A (en) * | 2009-01-13 | 2010-07-14 | 北京航空航天大学 | Flame stabilizer with jet injection |
| CN101725969A (en) * | 2010-01-19 | 2010-06-09 | 中国计量学院 | Low-NOx pulverized coal burner |
| CN103017203A (en) * | 2012-12-06 | 2013-04-03 | 中国科学院工程热物理研究所 | Fractional combustion chamber |
| CN103277816A (en) * | 2013-05-10 | 2013-09-04 | 南京航空航天大学 | Lean oil pre-mixing pre-evaporation low-emission standing vortex combustion chamber |
| CN204176638U (en) * | 2014-10-22 | 2015-02-25 | 中节环（北京）环境科技股份有限公司 | The portable coal burner of bluff body |
| CN104748111A (en) * | 2015-03-24 | 2015-07-01 | 华南理工大学 | Micro-combustor for metal mesh heat storage and flame stabilization and combustion method thereof |
| CN205388321U (en) * | 2016-03-02 | 2016-07-20 | 上海电气燃气轮机有限公司 | A flame surely fires device for combustion chamber |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108131685A (en) * | 2017-12-14 | 2018-06-08 | 西北工业大学 | Tiny engine combustion chamber multi-point injection evaporation tube |
| CN108426267A (en) * | 2018-05-11 | 2018-08-21 | 北京航空航天大学 | A kind of folding V-type bluff body eddy flameholder |
| CN108426267B (en) * | 2018-05-11 | 2023-07-25 | 北京航空航天大学 | Folding V-shaped blunt body standing vortex flame stabilizer |
| CN109631084A (en) * | 2018-12-13 | 2019-04-16 | 西安航天动力研究所 | Scramjet combustor stabilizer and steady flame method |
| CN114777158A (en) * | 2022-05-13 | 2022-07-22 | 哈尔滨工程大学 | Combustion chamber mixing structure based on blunt body group |
| CN117109029A (en) * | 2023-08-25 | 2023-11-24 | 西南科技大学 | Blunt body flame stabilizer and aeroengine combustion assembly |
| CN117109029B (en) * | 2023-08-25 | 2024-02-02 | 西南科技大学 | Blunt body flame stabilizer and aeroengine combustion assembly |
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