CN108800206A - A kind of poor premix mould nozzle that fuel is sprayed from blade and loopful combustion chamber - Google Patents
A kind of poor premix mould nozzle that fuel is sprayed from blade and loopful combustion chamber Download PDFInfo
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- CN108800206A CN108800206A CN201810587000.4A CN201810587000A CN108800206A CN 108800206 A CN108800206 A CN 108800206A CN 201810587000 A CN201810587000 A CN 201810587000A CN 108800206 A CN108800206 A CN 108800206A
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- blade
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- sprayed
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Classifications
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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
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
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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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/58—Cyclone or vortex type combustion chambers
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
Abstract
The poor premix mould nozzle sprayed from blade the present invention relates to a kind of fuel and loopful combustion chamber, using poor premixed combustion technology, fuel injection orifice is radially even to be distributed on axial swirler blade, fuel/air rate is improved in radially-arranged uniformity, in addition the combustion equivalent ratio of swirl nozzle is 0.55-0.75, ensure that combustion zone temperature is relatively low and is uniformly distributed no hot spot, effectively reduces the generation of thermal NO；Axial swirler is low eddy flow, can shorten the residence time of high-temperature fuel gas, reduces NO_x formation, and can reduce swirling eddy turbulence pulsation, reduces and tempering and hugging risk occurs；Cyclone outer wall upper wall surface divergence hole can reduce wall temperature and boundary-layer fuel/air rate, reduce and spontaneous combustion and tempering risk occurs；In Actual combustion room, the poor lean premixed combustor head of multiple spot is formed by the swirl nozzle of a certain number of identical sizes of reasonable Arrangement, and using the supply of main mould fuel staging, it can be achieved that low pollution emission of the combustion chamber within the scope of full working scope is horizontal.
Description
Technical field
The invention belongs to gas-turbine combustion chamber field, it is related to a kind of poor premix mould nozzle that fuel is sprayed from blade and complete
Ring combustion chamber, it is specifically a kind of to be suitable for low pollution combustor and the low swirl nozzle scheme based on poor premixed combustion technology.
Background technology
In recent years, with the sternness further of problem of environmental pollution, people's environmental consciousness is also increasingly stronger, no matter for aviation
Engine or ground gas turbine, pollutant emission require increasingly strict.Such as International Civil Aviation Organization (ICAO) subordinate's ring
The series of standards that border protective committee (CAEP) formulates is made that sternly carbon monoxide, unburned hydrocarbon and nitrogen oxides discharge
Lattice provide that Certification could be obtained by only meeting the engine of emission request；And it is directed to ground gas turbine, although not uniting
One emission standard, but since its long-time is the ground handling the characteristics of, the pollution of this area has also been formulated in various regions in succession
Object discharges criterion, and its discharge criterion is harsher compared to aero-engine, it is therefore necessary to greatly develop combustion with reduced pollutants skill
Art is to reduce gas turbine pollutant emission level, to meet the present and following higher emission request.
Currently, ground gas turbine combustion with reduced pollutants technology includes mainly：" wet " low emissions combustion technology, catalysis burning are super
Low emission technology and " dry " low emissions combustion technology.Due to " wet " low emissions combustion technology to CO discharge and component life it is negative
The technical bottleneck that influence and catalytic combustion technology are encountered, therefore dry low emissions combustion technology is still later gas turbine
The main direction of development.Due to harsh pollutant emission requirement, current " dry " low emissions combustion technology is mainly using premix combustion
Burning mode, fuel enters back into combustion zone burning after being sufficiently mixed with excess air, by adjusting working as fuel-air mixture
Ratio is measured to control combustion zone flame temperature, and avoids hot localised points, to achieve the purpose that reduce NOx emission.
Cyclone is the important composition component of gas-turbine combustion chamber, effect be for stablize flame and promote fuel/
Air mixes.In the past in order to pursue the fuel/air mixture blending uniformity and combustion stablized effect, the high swirl strength of generally use
Cyclone.But the theory by recent years and experimental study, high swirl strength cyclone one side will increase high-temperature fuel gas and firing
The indoor residence time is burnt, the production quantity of nitrogen oxides is increased, the indoor gas turbulence pulsation of burning is on the other hand will increase, increases
Add poor premix mode that the risk of tempering and hugging occurs, therefore is become using the development that low swirl nozzle is low pollution combustor
Gesture.
It is domestic that there are many patent applications about poor premix low pollution combustor in recent years.201410697493.9 disclosure of patent
A kind of gas-turbine combustion chamber revolves jet nozzle, including jet nozzle component and swirl nozzle component, passes through and increases jet stream
The ratio of nozzle assembly mixture reduces the swirl strength of combustion chamber gases, reduces flame temperature and gas stay time, from
And reduce discharged nitrous oxides；Patent 2011510117272.4 discloses a kind of low eddy flow of low-pollution burning chamber of gas turbine
Premixing nozzle, uses the radial swirler of weak swirl strength, reduces the high-temperature fuel gas residence time, and using cyclone runner and
Center flow channels spray the mode of fuel to improve fuel/air mixture mixture homogeneity jointly.Above-mentioned combustion chamber spray is found by analysis
Mouth structure is all made of fuel fabrication spray regime and is mixed to enhance fuel/air mixture, complicated, furthermore cyclone is all made of straight leaf
Flow separation easily occurs for piece, and flow losses are big, and without the measure for explicitly preventing tempering and spontaneous combustion.
Invention content
Technical problems to be solved
In order to avoid the shortcomings of the prior art, the present invention proposes a kind of poor premix mould nozzle that fuel is sprayed from blade
And loopful combustion chamber, it is suitable for the poor premix mould nozzle that the fuel of low-pollution burning chamber of gas turbine is sprayed from blade, the program
It is simple in structure, it both can guarantee being sufficiently mixed for fuel/air mixture, moreover it is possible to reduce flow separation, reduce flow resistance loss, while taking and arranging
Apply the risk for reducing and tempering, spontaneous combustion and hugging occurring.The program can be applied by rational arrangement mode and hierarchical approaches
On the gas-turbine combustion chamber of large, medium and small power.
Technical solution
A kind of poor premix mould nozzle that fuel is sprayed from blade, including cyclone outer wall and axial swirler；Its feature exists
In：The axial swirler is low eddy flow axial swirler, and the cyclone inner wall 6 at low 7 center of eddy flow axial swirler is fuel
Line entry 7, the cyclone inner wall 6 between the blade of low eddy flow axial swirler 9 are equipped with rectangular opening and form blade The fuel stream
Road entrance 8 on the blade back of each blade of low eddy flow axial swirler 9, is equipped with multiple spray-holes 13 so that fuel is from cartridge
Road entrance 7 enters, and by blade fuel flow path entrance 8, enters premix section 2 via spray-hole 13；Low eddy flow axial swirler 9 with
The cyclone outer wall that section 2 is premixed between exit orifice section 11 is equipped with multiple wall surfaces and dissipates aperture 10, after exit orifice section 11
For low swirl nozzle outlet 12；The blade of the low eddy flow axial swirler 9 is bent blade, is uniformly distributed circumferentially, blade angle
Degree is 30 °~45 °；The internal diameter D of the low swirl nozzle outlet 12 is 25mm~60mm, premixes the ratio between segment length S and internal diameter D
It is 0.5~1.2.
The blade of the low eddy flow axial swirler 9 is 6-20,8 number of blade fuel flow path entrance between blade
It is equal.
Spray-hole 13 on the blade back is 2-5.
The blade angle of the bent blade of the low eddy flow axial swirler 9 is 30 °~45 °.
The wall surface diverging aperture 10 is evenly distributed along the axial and circumferential directions, is dissipated between the axial spacing of aperture and circumferential direction
Away from for 4mm~7mm.
The cyclone outlet converging portion is 35 ° -55 ° with horizontal direction angle α.
The combustion zone equivalent proportion of the low swirl nozzle scheme is 0.55-0.75.
A kind of loopful combustion chamber that the poor premix mould nozzle sprayed from blade using the fuel is constituted, including outer burner inner liner
15, flame cylinder 19 and head flanges 14；It is characterized in that：Multiple poor premix mould nozzles sprayed from blade, radially by interior
And divide three layers outside and be arranged in head flanges 14, radially three nozzles, one group of main mould and the secondary mode spacing of two one group of nozzles are divided
Cloth.
The poor premix mould nozzle of described same group of slave blade injection shares one for cartridge.
Distance S1 and internal layer swirl nozzle are with flame cylinder distance S4 between the outer layer swirl nozzle and outer burner inner liner
4mm-8mm, radial distance S2 and S3 are 3mm-5mm between swirl nozzle, and circumferential space D 1 is 10mm-30mm between swirl nozzle.
Advantageous effect
The poor premix mould nozzle and loopful combustion chamber that a kind of fuel proposed by the present invention is sprayed from blade are fired using poor premix
Burning technology, fuel injection orifice is radially even to be distributed on axial swirler blade, improves fuel/air rate radially-arranged
Uniformity, in addition the combustion equivalent ratio of swirl nozzle is 0.55-0.75, ensures that combustion zone temperature is relatively low and is uniformly distributed no heat
Point effectively reduces the generation of thermal NO；Axial swirler is low eddy flow, when can shorten the stop of high-temperature fuel gas
Between, NO_x formation is reduced, and swirling eddy turbulence pulsation can be reduced, reduces and tempering and hugging risk occurs；Eddy flow
Device outer wall upper wall surface divergence hole can reduce wall temperature and boundary-layer fuel/air rate, reduce and spontaneous combustion and tempering risk occurs；In reality
In combustion chamber, the poor lean premixed combustor head of multiple spot is formed by the swirl nozzle of a certain number of identical sizes of reasonable Arrangement, and
Using the supply of main mould fuel staging, it can be achieved that low pollution emission of the combustion chamber within the scope of full working scope is horizontal.
Possessed advantage is as follows compared with prior art by the present invention：
The cyclone angle of swirl nozzle scheme is 30 ° -45 °, is weak rotation, and it is strong on the one hand to weaken air stream turbulence pulsation
Degree reduces the risk that tempering and hugging occurs, on the other hand can shorten the residence time of high-temperature fuel gas in the combustion chamber；It adopts
With fuel-lean combustion mode, work equivalent proportion is between 0.55-0.75, and combustion zone temperature is relatively low at this time, effectively reduces the life of NOx
At；By radially opening a certain number of fuel injection holes in swirler blades, point of fuel/air rate radially can be improved
Cloth uniformity reduces NOx emission to effectively avoid combustion zone hot spot from occurring；Cyclone outer wall wall surface diverging aperture can reduce
The fuel/air rate of wall temperature and wall surface boundary-layer, to effectively reduce the risk that spontaneous combustion and tempering occurs；Since air is through convergence
Section accelerates outflow swirl nozzle, so generation tempering risk can be reduced；It is simple and compact for structure, easy to process and assembly, a fixed number
The identical swirl nozzle of amount can form the poor lean premixed combustor head of multiple spot by rational arrangement mode.
Description of the drawings
Fig. 1：The low poor premixing nozzle sectional view of eddy flow of the present invention
Fig. 2：The low poor premixing nozzle axonometric drawing of eddy flow of the present invention
Fig. 3：The low poor premixing nozzle axial swirler axonometric drawing of eddy flow of the present invention
The poor premix of Fig. 4 multiple spots of the embodiment of the present invention fires loopful head of combustion chamber axonometric drawing
Fig. 5：The poor premix of multiple spot of the embodiment of the present invention fires loopful head of combustion chamber left view
In figure：The poor premixing nozzle of the low eddy flows of 1-, 2- premix section, 3- cyclone outer walls, 4- blade fuel flow paths, 5- eddy flow streams
Road, 6- cyclone inner walls, 7- fuel conduit entrances, 8- blade fuel flow path entrances, the low eddy flow axial swirlers of 9-, 10- wall surfaces
Dissipate aperture, 11- exit orifice sections, the low swirl nozzle outlets 12-, 13- fuel injection holes, 14- head flanges, the outer flames of 15-
Cylinder, 16- head of combustion chamber Local maps, 17- pair moulds, 18- main moulds, 19- flame cylinders, the low swirl nozzle Local maps of 20-.
Specific implementation mode
In conjunction with embodiment, attached drawing, the invention will be further described：
The present invention uses following technical scheme：A kind of premix mould nozzle arrangements that fuel is sprayed from blade, including low eddy flow
Axial swirler, cyclone outer wall, cyclone inner wall, eddy flow runner, fuel conduit entrance, blade fuel flow path entrance, blade
Fuel flow path, fuel injection hole, premix section, exit orifice section, swirl nozzle outlet and wall surface dissipate aperture.The eddy flow stream
Road is surrounded by cyclone outer wall, low eddy flow axial swirler and cyclone inner wall, and eddy flow flow paths downstream is premix section, followed by
Exit orifice section and swirl nozzle outlet, the speed in downstream is flowed to for improving fuel/air mixture, is reduced and is occurred to be tempered
Risk.The wall surface diverging aperture is located on the cyclone outer wall at premix section, for reducing wall temperature and boundary-layer internal combustion
Material/air ratio reduces the risk that tempering and spontaneous combustion occurs.The low eddy flow axial swirler blade is hollow, is blade
Fuel flow path, blade fuel flow path entrance are located on cyclone inner wall.The fuel injection orifice is radially uniform from inside to outside
Ground is opened on each swirler blades blade back, can improve fuel/air rate in radial mixture homogeneity.The certain amount
The poor premixing nozzle of low eddy flow can be applied in big or middle and low power combustion gas by rational arrangement mode and fuel staging mode
On turbine combustion room.
The combustion zone equivalent proportion of the poor premixing nozzle scheme of the low eddy flow is 0.55-0.75.
The swirler blades are bent blade, are uniformly distributed circumferentially, and the number of blade is 6-20.
The cyclone is low eddy flow, and blade angle is 30 ° -45 °.
The blade fuel flow path entrance and blade fuel flow path is consistent with swirler blades number, is 6-20.
The fuel injection hole is radially opened on swirler blades blade back, according to swirler blades size, Mei Gexuan
Stream device blade opens 2-5 spray-hole.
The cyclone outlet converging portion is 35 ° -55 ° with horizontal direction angle α.
The internal diameter D of the swirl nozzle scheme is 25mm-60mm, and premix the ratio between segment length S and internal diameter D are 0.5-1.2.
The wall surface diverging aperture is evenly distributed in along the axial and circumferential directions on the cyclone outer wall at premix section, diverging
The axial spacing of aperture and circumferential spacing are 4mm-7mm.
Arrangement mode of the swirl nozzle on loopful combustion chamber uses divides three layers of arrangement, each eddy flow from inside to outside
Nozzle is all identical, radially triplets or two one group, and ternary is main mould, and two one group is secondary mould, same group
Swirl nozzle share one for cartridge.
Arrangement of the swirl nozzle on loopful combustion chamber, distance S1 and interior between outer layer swirl nozzle and outer burner inner liner
Layer swirl nozzle and flame cylinder distance S4 are 4mm-8mm, and radial distance S2 and S3 are 3mm-5mm, eddy flow spray between swirl nozzle
Circumferential space D 1 is 10mm-30mm between mouth.
Specific embodiment：
As shown in Figs. 1-3, an embodiment of the present invention provides the poor premixing nozzle of low eddy flow that a kind of fuel is sprayed from blade, packets
It includes including low eddy flow axial swirler 9, cyclone outer wall 3, cyclone inner wall 6, eddy flow runner 5, fuel conduit entrance 7, blade
Fuel flow path entrance 8, blade fuel flow path 4, fuel injection hole 13, premix section 2, exit orifice section 11, swirl nozzle outlet 12
Aperture 10 is dissipated with wall surface.The eddy flow runner 5 is by cyclone outer wall 3, low eddy flow axial swirler 9 and cyclone inner wall 6
It surrounds, the low eddy flow axial swirler eddy flow angle takes 30 ° -45 °, is weak rotation, can reduce the turbulent flow arteries and veins of swirling eddy
Dynamic, capable of also shortening high-temperature fuel gas, residence time, swirler blades number are 6-20 in the combustion chamber.5 downstream of eddy flow runner is pre-
Mixed section 2, followed by exit orifice section 11 and swirl nozzle outlet 12, the exit orifice section 11 is with horizontal line angle α
35 ° -55 °, the fuel/air mixture rate of outflow is improved, reduces and tempering risk occurs.The fuel injection hole 13 is radially
It is evenly distributed on 9 blade of axial swirler, according to swirler blades size, 2-5 fuel injection hole is opened on each blade, is carried
High fuel/air mixture is in radial mixture homogeneity.Fuel is flowed into from fuel conduit entrance 7, through on cyclone inner wall 6
Blade fuel flow path entrance 8 flows into blade fuel flow path 4, is finally sprayed from the fuel injection hole 13 in swirler blades,
It meets and mixes in eddy flow runner with the swirling eddy generated through axial swirler, then further mixing is equal at premix section
It is even, finally accelerate through exit orifice section, downstream burns from swirl nozzle outlet stream, the combustion equivalent in low swirl nozzle downstream
Than controlling between 0.55-0.75, being poor premixed combustion, can effectively reduce the production quantity of nitrogen oxides.The wall surface diverging
Aperture 10 is uniformly distributed along the axial and circumferential directions on cyclone outer wall 3, and axial and circumferential spacing is 4mm-7mm, can effectively reduce wall
The fuel/air rate of mild wall surface boundary-layer, reduces the risk that spontaneous combustion and tempering occurs.
It as illustrated in figures 4-5, can be certain by reasonable Arrangement according to practical gas-turbine combustion chamber power and size
The poor premixing nozzle of low eddy flow of the identical size of quantity forms the poor lean premixed combustor head of multiple spot.The poor premix spray of the low eddy flow
Mouth 1 can radially divide three layers to be distributed in head flanges 14 from inside to outside, and outer layer is identical with the swirl nozzle number of middle layer,
Internal layer swirl nozzle number is the half of outer layer, wherein radially two swirl nozzles form combustion chamber pair mould 17, radially three
A swirl nozzle forms combustion chamber main mould 18, and all pair moulds all spray fuel work under the small work condition state in combustion chamber, and main mould is
It is classified spray fuel work with the increase of combustion chamber operating mode, main mould classification work series is chosen as according to combustion chamber condition range
6-15 grades, distance S1 of the outer layer swirl nozzle away from outer burner inner liner 15 is with internal layer swirl nozzle away from 19 distance S4 of flame cylinder
Take 4mm-8mm, the radial spacing S2 and S3 of adjacent swirl nozzle that 3mm-5mm, circumferential space D 1 is taken to take 10mm-30mm.
The course of work of the present invention is as follows：
Air generates weak rotational flow through low eddy flow axial swirler 9, and fuel is flowed into from fuel conduit entrance 7, successively
Blade fuel flow path entrance 8 and blade fuel flow path 4 are flowed through, is finally sprayed from fuel injection hole 13.The fuel of ejection and rotation
Air-flow meets mixing in eddy channel 5, is further mixed in premix section 2, and then the mixing of uniformly mixed fuel/air mixture
Acceleration of the object Jing Guo exit orifice section 11 flows to downstream from low swirl nozzle outlet 12, carries out stablizing burning in downstream.In addition,
Portion of air can dissipate aperture 10 by the wall surface on cyclone outer wall 3 and flow into swirl nozzle, in 3 inside of cyclone outer wall
Adherent uniform air film is formed, wall temperature is on the one hand reduced, on the other hand reduces wall surface boundary-layer fuel/air rate, and then reduce
Spontaneous combustion and tempering risk occurs.
Claims (10)
1. the poor premix mould nozzle that a kind of fuel is sprayed from blade, including cyclone outer wall and axial swirler；It is characterized in that：
The axial swirler is low eddy flow axial swirler, and the cyclone inner wall (6) at low eddy flow axial swirler (7) center is fuel
Line entry (7), the cyclone inner wall (6) between the blade of low eddy flow axial swirler (9) are equipped with rectangular opening and form blade
Fuel flow path entrance (8) on the blade back of each blade of low eddy flow axial swirler (9), is equipped with multiple spray-holes (13) so that
Fuel enters from fuel conduit entrance (7), by blade fuel flow path entrance (8), enters premix section via spray-hole (13)
(2)；The cyclone outer wall that section (2) is premixed between low eddy flow axial swirler (9) and exit orifice section (11) is equipped with multiple walls
Face dissipates aperture (10), is that low swirl nozzle exports (12 after exit orifice section (11)；The low eddy flow axial swirler (9)
Blade be bent blade, be uniformly distributed circumferentially, blade angle is 30 °~45 °；The low swirl nozzle exports the interior of (12)
Diameter D is 25mm~60mm, and premix the ratio between segment length S and internal diameter D are 0.5~1.2.
2. the poor premix mould nozzle that fuel is sprayed from blade according to claim 1, it is characterised in that：The low eddy flow is axial
The blade of cyclone (9) is 6-20, and blade fuel flow path entrance (8) number between blade is equal.
3. the poor premix mould nozzle that fuel according to claim 1 or claim 2 is sprayed from blade, it is characterised in that：On the blade back
Spray-hole (13) be 2-5.
4. the poor premix mould nozzle that fuel according to claim 1 or claim 2 is sprayed from blade, it is characterised in that：The low eddy flow
The blade angle of the bent blade of axial swirler (9) is 30 °~45 °.
5. the poor premix mould nozzle that fuel is sprayed from blade according to claim 1, it is characterised in that：The wall surface diverging
Aperture (10) is evenly distributed along the axial and circumferential directions, and the axial spacing and circumferential spacing for dissipating aperture are 4mm~7mm.
6. the poor premix mould nozzle that fuel is sprayed from blade according to claim 1, it is characterised in that：The cyclone goes out
Mouth converging portion is 35 ° -55 ° with horizontal direction angle α.
7. the poor premix mould nozzle that fuel is sprayed from blade according to claim 1, it is characterised in that：The low swirl nozzle
The combustion zone equivalent proportion of scheme is 0.55-0.75.
8. a kind of loopful constituted using the poor premix mould nozzle that fuel is sprayed from blade any one of described in claim 1~7 is fired
Burn room, including outer burner inner liner (15), flame cylinder (19) and head flanges (14)；It is characterized in that：It is multiple from blade spray
Poor premix mould nozzle radially divides three layers to be arranged in head flanges (14) from inside to outside, radially three nozzles, one group of main mould
It is distributed with the secondary mode spacing of two one group of nozzles.
9. loopful combustion chamber according to claim 8, it is characterised in that：The poor premix mould of described same group of slave blade injection
Nozzle shares one for cartridge.
10. loopful combustion chamber according to claim 8, it is characterised in that：The outer layer swirl nozzle and outer burner inner liner spacing
It is 4mm-8mm from S1 and internal layer swirl nozzle and flame cylinder distance S4, radial distance S2 and S3 are 3mm- between swirl nozzle
5mm, circumferential space D 1 is 10mm-30mm between swirl nozzle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810587000.4A CN108800206A (en) | 2018-06-06 | 2018-06-06 | A kind of poor premix mould nozzle that fuel is sprayed from blade and loopful combustion chamber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810587000.4A CN108800206A (en) | 2018-06-06 | 2018-06-06 | A kind of poor premix mould nozzle that fuel is sprayed from blade and loopful combustion chamber |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108800206A true CN108800206A (en) | 2018-11-13 |
Family
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810587000.4A Pending CN108800206A (en) | 2018-06-06 | 2018-06-06 | A kind of poor premix mould nozzle that fuel is sprayed from blade and loopful combustion chamber |
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| CN (1) | CN108800206A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114110589A (en) * | 2020-08-31 | 2022-03-01 | 芜湖美的厨卫电器制造有限公司 | Nozzle, combustor and gas heater |
| CN114353082A (en) * | 2020-09-30 | 2022-04-15 | 芜湖美的厨卫电器制造有限公司 | Nozzle, combustor and gas heater |
| CN115451432A (en) * | 2022-09-22 | 2022-12-09 | 中国联合重型燃气轮机技术有限公司 | Micro-mixing nozzle assembly and system for fuel of combustion chamber of gas turbine |
| CN116336501A (en) * | 2023-03-30 | 2023-06-27 | 中国航发沈阳发动机研究所 | Backfire-preventing low-emission nozzle for combustion chamber of gas turbine |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114110589A (en) * | 2020-08-31 | 2022-03-01 | 芜湖美的厨卫电器制造有限公司 | Nozzle, combustor and gas heater |
| CN114110589B (en) * | 2020-08-31 | 2024-06-21 | 芜湖美的厨卫电器制造有限公司 | Nozzle, burner and gas water heater |
| CN114353082A (en) * | 2020-09-30 | 2022-04-15 | 芜湖美的厨卫电器制造有限公司 | Nozzle, combustor and gas heater |
| CN115451432A (en) * | 2022-09-22 | 2022-12-09 | 中国联合重型燃气轮机技术有限公司 | Micro-mixing nozzle assembly and system for fuel of combustion chamber of gas turbine |
| CN115451432B (en) * | 2022-09-22 | 2024-03-12 | 中国联合重型燃气轮机技术有限公司 | Micro-mixing nozzle assembly and system for fuel in combustion chamber of gas turbine |
| CN116336501A (en) * | 2023-03-30 | 2023-06-27 | 中国航发沈阳发动机研究所 | Backfire-preventing low-emission nozzle for combustion chamber of gas turbine |
| CN116336501B (en) * | 2023-03-30 | 2024-06-07 | 中国航发沈阳发动机研究所 | Backfire-preventing low-emission nozzle for combustion chamber of gas turbine |
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Application publication date: 20181113 |
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