CN105588144B - Flame smooth combustion apparatus and flame smooth burning method for gas-turbine combustion chamber - Google Patents
Flame smooth combustion apparatus and flame smooth burning method for gas-turbine combustion chamber Download PDFInfo
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- CN105588144B CN105588144B CN201610118888.8A CN201610118888A CN105588144B CN 105588144 B CN105588144 B CN 105588144B CN 201610118888 A CN201610118888 A CN 201610118888A CN 105588144 B CN105588144 B CN 105588144B
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- combustion chamber
- bluff body
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- body portion
- gas
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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 present invention provides a kind of flame smooth combustion apparatus and flame smooth burning method for gas-turbine combustion chamber, the front wall portion of combustion chamber is provided with nozzle, the flame smooth combustion apparatus includes multiple ventilation bluff bodies being arranged on the front wall portion of the combustion chamber, and multiple ventilation bluff bodies are evenly arranged around the lateral surface of the nozzle；The air inlet end face of the ventilation bluff body is provided with the venting flow path connected with the inside of the combustion chamber, the venting flow path extending radially outwardly from the outside of the nozzle along the nozzle；The venting flow path gradually expands outwardly along gas circulating direction.Two standing vortexes can be formed in a combustion chamber using the device of the present invention, flame smooth combustion apparatus of the invention and flame smooth burning method have preferably steady combustion ability compared with existing structure.
Description
Technical field
The present invention relates to gas-turbine combustion chamber technical field, more particularly to a kind of fire for gas-turbine combustion chamber
Flame smooth combustion apparatus and flame smooth burning method.
Background technology
Gas turbine is extensive due to having the advantages that simple in construction, single-machine capacity is big, weight and size is small, mobility is good
Be applied to many industrial circles such as aviation, ship, electric power, oil.Critical piece of the combustion chamber as gas turbine, in structure
It is upper that there is essentially identical feature, factor and combustion in terms of the aerothermodynamic when structure type of combustion chamber is based on combustion chamber operational
Common prescription of the basic law that burning process is followed in terms of the two consider and design, and factor is for example in terms of aerothermodynamic
Combustor exit temperature, stability, starting ignition, efficiency of combustion, durability, disposal of pollutants characteristic etc..The main work(in combustion chamber
It can be diffusion reduction of speed, fuel preparation, form the stable flame in low regime or recirculating zone.The optimization design of head of combustion chamber structure, elder generation
It is the important channel for solving above-mentioned technological challenge to enter fuel-oil atmozation mode and advanced combustion chamber cooling technology.
According to Theory of Combustion, to stablize flame in high velocity air, it is necessary to some spatial points are at least inside burner inner liner
Place's construction local air flow speed equal region, i.e., commonly called igniting with the flame propagation velocity of combustion mixture at this
Source.In a combustion chamber, the designing points of flame smooth combustion apparatus are construction low speeds flow regions.Conventional construction low speeds flow region
Method can be divided into two kinds, one kind is to use entity structure, such as strong eddy flow, sudden expansion, groove, another then use pneumatic knot
Structure, such as contrainjection, transverse injection.The method in existing construction low speeds flow region can be only formed a standing vortex, stable combustion
The ability of burning is very limited.
The effect of flame smooth combustion apparatus in a combustion chamber can be summarized as following three points：1) formed and flowed back in flame tube head
Area, the air velocity of combustion chamber is lowered into, so as to form stable ignition source in flame tube head, ensures that combustion chamber steadily may be used
Worked by ground；2) coordinate with pressure atomized fog jet, played an important role in terms of promoting fuel oil to crush atomization；3) it is burner inner liner
Head provides appropriate air, ensures that head has suitable excess air coefficient.As can be seen here, the weight as combustion chamber flame drum
Component is wanted, flame smooth combustion apparatus has comprehensive influence to the service behaviour of combustion chamber, and the lifting to combustion chamber overall performance has
Greatly facilitate effect.Existing chamber structure can be only formed a standing vortex, and the ability of stable burning is very limited.
The content of the invention
In view of the above the shortcomings that prior art, the technical problem to be solved in the present invention is that providing one kind can realize
Two standing vortexes, there is the flame smooth combustion apparatus and flame smooth burning method for gas-turbine combustion chamber of preferably steady combustion ability.
In order to solve the above-mentioned technical problem, the present 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 the flame smooth combustion apparatus includes multiple be arranged on the front wall portion of the combustion chamber
Ventilation bluff body, multiple ventilation bluff bodies are evenly arranged around the lateral surface of the nozzle；The air inlet end face of the ventilation bluff body
It is provided with the venting flow path that is connected with the inside of the combustion chamber, the venting flow path is from the outside of the nozzle along the spray
Mouth extends radially outwardly；The venting flow path gradually expands outwardly along gas circulating direction.
Preferably, the radial section where the gas outlet of the venting flow path is vertical with the front wall portion.
Preferably, the gas outlet of the venting flow path is on the medial surface of the front wall portion of the combustion chamber.
Preferably, each ventilation bluff body includes the first bluff body portion and the second bluff body portion that one end is connected, and described the
Two bluff body portions are obliquely installed relative to the first bluff body portion, the other end in the first bluff body portion and the second bluff body portion
The opening portion formed between the other end is towards nozzle；The air inlet end face in the first bluff body portion is provided with first flow, and described
The air inlet end face in two bluff body portions is provided with second flow channel；The first flow connects with the second flow channel, forms venting flow path；
The angle formed between the first flow and the second flow channel is runner angle；The runner angle is with the vent flow
The gas circulating direction in road gradually increases.
Further, the first bluff body portion and the second bluff body portion are plate body, the outside in the first bluff body portion
Angle between the lateral surface and the front wall portion in face and the second bluff body portion is all higher than 90 degree.
The invention further relates to a kind of flame of the flame smooth combustion apparatus for gas-turbine combustion chamber described in use surely to fire
Method, several primary holes are circumferentially evenly arranged on the side of combustion chamber, and several described primary holes are in described
The middle part of combustion chamber；Nozzle sprays into fuel oil to the inside of the combustion chamber, and the inside of the combustion chamber carries out combustion reaction；It is described
Air is passed through in primary holes, meanwhile, air is also by described in the venting flow path gradually expanded outwardly the entrance of the ventilation bluff body
The inside of combustion chamber, and form the axial flow in the same direction with the axial direction of the combustion chamber and be affixed to the oblique air-flow of wall flowing,
The axial flow forms one-level standing vortex；Oblique air current flow to the combustion chamber middle part when, by the sky of the primary holes
The effect of gas jet, mutually blending, form two level standing vortex；High temperature reflux of the one-level standing vortex by the inside of the combustion chamber
Effect, prevapourising, pre- cracking are carried out to the fuel oil that the nozzle sprays；The two level standing vortex is to stablize flame region, fuel oil
Burnt in the stable flame region.
As described above, the flame smooth combustion apparatus and flame smooth burning method for gas-turbine combustion chamber of the present invention, has
Following beneficial effect：
The flame smooth combustion apparatus of the present invention has the venting flow path of multiple expansion shapes, is formed after gas is by venting flow path
Air-flow, occur that, by wind region, a part of air-flow is the axle in the same direction with the axial direction of the combustion chamber in the gas outlet of venting flow path
To air-flow, axial flow can form one-level standing vortex by wind region；The fuel oil to be gushed out from nozzle first passes around one-level standing vortex,
Prevapourising and pre- cracking are carried out in the presence of high temperature reflux, contributes to the atomization and fully burning of fuel oil；Another part air-flow is
The oblique air-flow of wall flowing is affixed to, during the middle part of oblique air current flow to the combustion chamber, by the jet action of primary holes,
Mutually blending, forms two level standing vortex region, and two level standing vortex is stablizing flame region, fuel oil is a large amount of as flame region is stablized
Burning, combustion process is from rich oil to oil-poor transition, primary zone of the stable flame region equivalent to traditional combustion room so that fuel with
Air fully reacts.Two standing vortexes, flame smooth combustion apparatus of the invention can be formed in a combustion chamber using the device of the present invention
And flame smooth burning method has preferably steady combustion ability compared with existing structure.
Brief description of the drawings
Structural representation when the flame smooth combustion apparatus for gas-turbine combustion chamber that Fig. 1 is shown as the present embodiment uses
Figure.
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 embodiment
Dimensional structure diagram at face.
Fig. 3 is shown as the vent flow of the ventilation bluff body of the flame smooth combustion apparatus for gas-turbine combustion chamber of the present embodiment
Dimensional structure diagram at the gas outlet 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 embodiment
Schematic cross-section at face.
Fig. 5 is shown as the vent flow of the ventilation bluff body of the flame smooth combustion apparatus for gas-turbine combustion chamber of the present embodiment
Schematic cross-section at the gas outlet in road.
Fig. 6 is shown as the flame smooth combustion apparatus for gas-turbine combustion chamber of the present embodiment and stayed in use, forming one-level
Whirlpool and the schematic diagram of two level standing vortex.
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 paths
321 gas outlets
410 first bluff body portions
411 first flows
420 second bluff body portions
421 second flow channels
510 one-level standing vortexes
520 two level standing vortexes
α runner angles
Embodiment
Embodiments of the present invention are illustrated by particular specific embodiment below, those skilled in the art can be by this explanation
Content disclosed by book understands other advantages and effect of the present invention easily.
Refer to accompanying drawing.It should be clear that structure, ratio, size depicted in this specification institute accompanying drawings etc., only coordinating
Content disclosed in specification, so that those skilled in the art understands and reads, it is enforceable to be not limited to the present invention
Qualifications, therefore do not have technical essential meaning, the modification of any structure, the change of proportionate relationship or the adjustment of size,
Do not influence under the effect of present invention can be generated and the purpose that can reach, all should still fall in disclosed technology contents
Obtain in the range of covering.Meanwhile cited such as " on ", " under ", "left", "right", " centre " and " one " in this specification
Term, be merely convenient to understanding for narration, and be not used to limit the enforceable scope of the present invention, the change of its relativeness or
Adjustment, in the case where changing technology contents without essence, when being also considered as the enforceable category of the present invention.
As shown in Figures 1 to 6, the flame smooth combustion apparatus for gas-turbine combustion chamber 100 of the present embodiment, combustion chamber
100 include combustion barrel body 120 and the front wall portion 110 being arranged on combustion barrel body 120, and front wall portion 110 is provided with nozzle
200, the jet 210 of nozzle 200 is stretched into combustion barrel body 120；Circumferentially uniform cloth on the side of combustion barrel body 120
Several primary holes 121 are equipped with, and several primary holes 121 are in the middle part of combustion barrel body 120；In the present embodiment, main combustion
The aperture in hole 121 is 8mm, and combustion barrel body 120 is cylinder；
Flame smooth combustion apparatus includes the ventilation bluff body 300, Duo Getong on multiple front wall portions 110 for being arranged at combustion chamber 100
Gas 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 chamber
The venting flow path 320 of 100 inside connection, radially outward the prolonging from the outside of nozzle 200 along nozzle 200 of venting flow path 320
Stretch；Venting flow path 320 gradually expands outwardly along gas circulating direction, and the size of venting flow path 320 is along gas circulation side
To gradual increase.
Flame smooth combustion apparatus has the venting flow path 320 of multiple expansion shapes, because venting flow path 320 is outside nozzle 200
Portion extends radially outwardly along nozzle 200, and venting flow path 320 gradually expands outwardly along gas circulating direction, and vent flow
The size in road 320 gradually increases along gas circulating direction；So after gas is by gradually expanding outwardly venting flow path 320
Air-flow is formed, occurs that, by wind region, a part of air-flow is the axial direction with combustion chamber 100 in the gas outlet 321 of venting flow path 320
Axial flow in the same direction, axial flow can form one-level standing vortex 510 by wind region；The fuel oil to be gushed out from nozzle 200 is first
By one-level standing vortex 510, prevapourising and pre- cracking are carried out in the presence of the internal high temperature backflow of combustion barrel body 120, is helped
In the atomization and fully burning of fuel oil；Another part air-flow is to be affixed to the oblique air-flow that wall flows, oblique air current flow to combustion
When burning the middle part of room 100, by the jet action of primary holes 121, the region of two level standing vortex 520, the conduct of two level standing vortex 520 are formd
Stablize flame region, stablizing flame region, fuel oil largely burns, and combustion process stablizes flame zone from rich oil to oil-poor transition
Primary zone of the domain equivalent to traditional combustion room 100 so that fuel fully reacts with air.
Radial section where the gas outlet 321 of venting flow path 320 is vertical with front wall portion 110.The structure can be easy to shape
Into one-level standing vortex 510 and two level standing vortex 520, then the region that one-level standing vortex 510 and two level standing vortex 520 are formed can be by obvious area
Not.
The gas outlet 321 of venting flow path 320 is on the medial surface 111 of the front wall portion 110 of combustion chamber 100.The structure makes
Axial flow can form one-level standing vortex 510 in the position of the jet 210 closer to nozzle 200.
In the present embodiment, each bluff body 300 of ventilating includes the first bluff body portion 410 and the second bluff body portion that one end is connected
420, the second bluff body portion 420 is obliquely installed relative to the first bluff body portion 410, the other end and the second bluff body in the first bluff body portion 410
The opening portion formed between the other end in portion 420 is towards nozzle 200；The air inlet face in the first bluff body portion 410 is provided with first flow
411, the air inlet face in the second bluff body portion 420 is provided with second flow channel 421；First flow 411 connects with second flow channel 421, forms
Venting flow path 320；The angle formed between first flow 411 and second flow channel 421 is runner angle α；Runner angle α is with logical
The gas circulating direction of flow channel 320 gradually increases.
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, more
Individual ventilation bluff body 300 is evenly arranged around the lateral surface of nozzle 200, it becomes possible to forms star structure；The quantity of ventilation bluff body 300
For even number, in the present embodiment, the quantity of ventilation bluff body 300 is 6, because runner angle α is with the gas of venting flow path 320
Circulating direction gradually increases, that is, forms the star structure with the venting flow path 320 gradually expanded, and makes the present embodiment
The structure of flame smooth combustion apparatus is more compact.Connected by the first bluff body portion 410 and the second bluff body portion 420 formed with angle
Structure, the oblique air-flow for enabling to first flow 411 to be discharged with second flow channel 421 are converged, and make each ventilation bluff body 300
Oblique air-flow more concentrate, improve the flow and flow rate of oblique air-flow, be easy to be formed stable two level standing vortex 520.
In the present embodiment, the distance of ventilation bluff body 300 and the lateral surface of nozzle 200 is less than ventilation bluff body 300 and front wall portion
The distance at 110 edges, so, the axial flow for forming one-level standing vortex 510 can be close to the jet 210 of nozzle 200, and one-level is stayed
Whirlpool 510 can fully carry out prevapourising and pre- cracking to fuel oil.
Due in the present embodiment, the radial section of first flow 411 and second flow channel 421 is rectangle, the first bluff body portion 410
Plate body is disposed as with the second bluff body portion 420, and the lateral surface in the lateral surface in the first bluff body portion 410 and the second bluff body portion 420 is with before
Angle between wall portion 110 is all higher than 90 degree.The structure make the overall structure in the first bluff body portion 410 and the second bluff body portion 420 with
The structure for the venting flow path 320 gradually expanded is consistent.
Using the flame smooth burning method of the flame smooth combustion apparatus for gas-turbine combustion chamber 100 of the present embodiment, nozzle
200 spray into fuel oil to the inside of combustion chamber 100, and the inside of combustion chamber 100 carries out combustion reaction；Air is passed through in primary holes 121,
Meanwhile air enters the inside of combustion chamber 100, and shape also by the venting flow path 320 gradually expanded outwardly of ventilation bluff body 300
Into the axial flow in the same direction with the axial direction of combustion chamber 100 and be affixed to wall flowing oblique air-flow, axial flow formed one-level stay
Whirlpool 510；Oblique air current flow to combustion chamber 100 middle part when, acted on by the air-spray of primary holes 121, mutually blending,
Form two level standing vortex 520；One-level standing vortex 510 is acted on by the high temperature reflux of the inside of combustion chamber 100, and nozzle 200 is sprayed
Fuel oil carry out prevapourising, pre- cracking；To stablize flame region, fuel oil stably fires stablizing flame region two level standing vortex 520
Burn.
In the present embodiment, each bluff body 300 of ventilating is connected and formed by the first bluff body portion 410 and the second bluff body portion 420
Structure with angle, even number ventilation bluff body 300 are the axially symmetric structures using the axis of nozzle 200 as symmetry axis, each
The structure of bluff body 300 of ventilating is identical, and the medial surface 111 of each venting flow path 320 and the front wall portion 110 of combustion chamber 100 forms bluff body knot
Structure, after being passed through air in venting flow path 320, flowed back in the standing vortex that small size is occurred by wind face axial flow, i.e., one-level is stayed
Whirlpool 510, this region can form prevapourising, pre- splitting action to fuel oil.Multiple venting flow paths 320 form a circle into star knot
Structure, the middle part of combustion barrel body 120 cause combustion barrel sheet due to being acted on there is provided the air-spray of primary holes 121, primary holes 121
Low-pressure area centered on the middle part of body 120, oblique air-flow acceptor center low-pressure area effect, forms two level standing vortex 520, turns into combustion chamber
100 main recirculating zone.Two standing vortexes can be formed in combustion chamber 100 using the device of the present invention, flame of the invention surely fires
Device and flame smooth burning method have preferably steady combustion ability compared with existing structure.
To sum up, the present invention effectively overcomes various shortcoming of the prior art and has high industrial utilization.
The above-described embodiments merely illustrate the principles and effects of the present invention, not for the limitation present invention.It is any ripe
Know the personage of this technology all can carry out modifications and changes under the spirit and scope without prejudice to the present invention to above-described embodiment.Cause
This, those of ordinary skill in the art is complete without departing from disclosed spirit and institute under technological thought such as
Into all equivalent modifications or change, should by the present invention claim be covered.
Claims (5)
1. a kind of 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 characterised in that several primary holes (121) have circumferentially been evenly arranged on the side of the combustion chamber (100),
And several described primary holes (121) are in the middle part of the combustion chamber (100)；
The flame smooth combustion apparatus includes the ventilation bluff body on multiple front wall portions (110) for being arranged at the combustion chamber (100)
(300), multiple ventilation bluff bodies (300) are evenly arranged around the lateral surface of the nozzle (200)；
The air inlet end face (310) of the ventilation bluff body (300) is provided with the vent flow connected with the inside of the combustion chamber (100)
Road (320), venting flow path (320) radially outward the prolonging from the outside of the nozzle (200) along the nozzle (200)
Stretch；The venting flow path (320) gradually expands outwardly along gas circulating direction；
Each ventilation bluff body (300) includes the first bluff body portion (410) and the second bluff body portion (420) that one end is connected, institute
The second bluff body portion (420) is stated to be obliquely installed relative to the first bluff body portion (410), the first bluff body portion (410) it is another
Hold the opening portion that is formed between the other end in the second bluff body portion (420) towards the nozzle (200)；First bluff body
Portion (410) is provided with first flow (411), and the second bluff body portion (420) is provided with second flow channel (421)；It is described first-class
Road (411) connects with the second flow channel (421), forms venting flow path (320)；The first flow (411) and described second
The angle formed between runner (421) is runner angle；The runner angle circulates with the gas of the venting flow path (320)
Direction gradually increases.
2. the flame smooth combustion apparatus according to claim 1 for gas-turbine combustion chamber, it is characterised in that：The ventilation
Radial section where the gas outlet (321) of runner (320) is vertical with the front wall portion (110).
3. the flame smooth combustion apparatus according to claim 1 for gas-turbine combustion chamber, it is characterised in that：The ventilation
The gas outlet (321) of runner (320) is on the medial surface (111) of the front wall portion (110) of the combustion chamber (100).
4. the flame smooth combustion apparatus according to claim 1 for gas-turbine combustion chamber, it is characterised in that：Described first
Bluff body portion (410) and the second bluff body portion (420) are plate body, the lateral surface of the first bluff body portion (410) and second blunt
Angle between the lateral surface and the front wall portion (110) in body portion (420) is all higher than 90 degree.
5. using the flame smooth burning method of the flame smooth combustion apparatus for gas-turbine combustion chamber described in claim 1, it is special
Sign is：
Nozzle (200) sprays into fuel oil to the inside of the combustion chamber (100), and the inside of the combustion chamber (100) burn instead
Should；In the primary holes (121) air is passed through, meanwhile, air gradually expands outwardly also by the ventilation bluff body (300)
Venting flow path (320) enters the inside of the combustion chamber (100), and forms the axle in the same direction with the axial direction of the combustion chamber (100)
To air-flow and the oblique air-flow for being affixed to wall flowing, the axial flow forms one-level standing vortex (510)；Oblique air current flow is to institute
When stating the middle part of combustion chamber (100), by the effect of the air-spray of the primary holes (121), mutually blending, form two level and stay
Whirlpool；
The one-level standing vortex (510) by the high temperature reflux of the inside of the combustion chamber (100) effect, to the nozzle
(200) fuel oil sprayed carries out prevapourising, pre- cracking；The two level standing vortex (520) is stablizes flame region, and fuel oil is described steady
Determine flame region burning.
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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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| CN108131685A (en) * | 2017-12-14 | 2018-06-08 | 西北工业大学 | Tiny engine combustion chamber multi-point injection evaporation tube |
| 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 |
| CN109631084B (en) * | 2018-12-13 | 2020-11-06 | 西安航天动力研究所 | Combustion chamber stabilizer of ramjet engine and flame stabilizing 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 |
| 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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| US7185494B2 (en) * | 2004-04-12 | 2007-03-06 | General Electric Company | Reduced center burner in multi-burner combustor and method for operating the combustor |
| JP2007163032A (en) * | 2005-12-14 | 2007-06-28 | Seiji Ohara | Oil-burning tube bundle combustion boiler using collision type atomizer |
| RU2386897C2 (en) * | 2007-06-13 | 2010-04-20 | Леонид Николаевич Парфёнов | Parfyonov flame device |
| US8800290B2 (en) * | 2007-12-18 | 2014-08-12 | United Technologies Corporation | Combustor |
| CN101776283B (en) * | 2009-01-13 | 2012-06-20 | 北京航空航天大学 | Flame stabilizer with jet injection |
| CN101725969B (en) * | 2010-01-19 | 2011-08-17 | 中国计量学院 | Low-NOx pulverized coal burner |
| CN103017203B (en) * | 2012-12-06 | 2016-05-25 | 成都中科航空发动机有限公司 | The fractional combustion chamber of a kind of main combustion stage loopful air inlet |
| CN103277816B (en) * | 2013-05-10 | 2015-09-09 | 南京航空航天大学 | Lean premixed preevaporated low emission standing vortex burning 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 |
| CN104748111B (en) * | 2015-03-24 | 2017-04-12 | 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 |
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