CN106524223A - Combustion chamber with main nozzle module and micro nozzle module - Google Patents
Combustion chamber with main nozzle module and micro nozzle module Download PDFInfo
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- CN106524223A CN106524223A CN201611163961.XA CN201611163961A CN106524223A CN 106524223 A CN106524223 A CN 106524223A CN 201611163961 A CN201611163961 A CN 201611163961A CN 106524223 A CN106524223 A CN 106524223A
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- Prior art keywords
- micro
- nozzle
- fuel
- micro nozzle
- main
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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
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
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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
- F23R3/52—Toroidal combustion chambers
Abstract
The invention discloses a combustion chamber with a main nozzle module and a micro nozzle module. The combustion chamber comprises a pressure expander, the main nozzle module, the micro nozzle module, a flame cylinder and a combustion chamber box, wherein the main nozzle module and the micro nozzle module are arranged at the front end of the flame cylinder; the micro nozzle module includes multiple micro nozzles; the outer diameters of the micro nozzles are 3-15 mm; the center distances of the adjacent micro nozzles are 1.1-2 times of the outer diameters of the micro nozzles; the micro nozzle module includes multiple matching rings; the matching rings are as many as main nozzles of the main nozzle module; and the main nozzles of the main nozzle module are assembled in the matching rings. The combustion chamber can be applied to a gas turbine, an aeroengine and a boiler, comprises such four fuel injecting modes as front fuel injection, main premixed fuel injection, dispersed fuel injection and micro premixed fuel injection, and facilitates realization of efficient combustion organization and flexible working condition adjustment when keeping low emission.
Description
Technical field
The present invention relates to a kind of burner, particularly relates to a kind of combustion with main jet nozzle assembly and micro nozzle component
Burn room and the gas turbine using which, aero-engine and boiler.
Background technology
Gas turbine is a kind of important motivity equipment that chemical energy is converted to mechanical energy, defeated in distributed energy, pipeline
Send, the aspect such as emergency power supply, ship power is widely used.A kind of important type of gas turbine is passed through by aero-engine
Remodeling, this boat remodeling gas turbine are compared to internal combustion engine, excellent with lightweight, small volume, fast, the efficiency height of startup etc.
Gesture.Aero-engine remodeling ground gas turbine technology path be usually：Fanjet fan cuts top, changes fuel oil combustor
For gas combustion chamber, cancelling jet pipe increases power turbine output power, increases or transform corresponding auxiliary system.The technology road
Line at home and abroad has successful story.What is faced during aero-engine to be modified as ground gas turbine at present is main
Technical difficulty be combustor low stain transformation.From the transformation of aero-engine earthward gas turbine so that aeroplane engine
Machine changes into electric power or power output by thrust output so that final products need the technical standard for meeting also to there occurs change.
Have to meet the relevant criterion that country is formulated for ground gas turbine after being changed to ground gas turbine, wherein most importantly will
Meet the environmental standard of gas turbine pollutant emission.
Simultaneously because environmental problem is increasingly serious, the phenomenon such as the normal hazes for occurring of Jing, acid rain has had a strong impact on the life of people
It is living.Country produces the discharge of the combustion apparatus such as boiler, gas turbine and aero-engine etc. of pollutant and has formulated sternly for control
The standard of lattice, non-compliant used equipment gradually will be eliminated, and new equipment would not allow for listing.Current gas turbine etc. burns
The main pollutant effulent of equipment is carbon monoxide (CO), nitrogen oxides (NOX) and unburned hydrocarbon (UHC).Wherein, CO and UHC
Discharge concerned countries standard has been met by technological progress, the emission for needing strict control is NOX。NOXFormation mechanism
Including：Heating power type, Quick-type and fuel type, wherein heating power type mechanism are that current combustion equipment generates NOXDominant mechanism.Heating power
Type NOXThe reaction of nitrogen and oxygen in air under hot environment, therefore reduce NOXMajor measure be reduce it is burned
The temperature of journey Flame, universal measure are to adopt premixed combustion.
Common premixed combustion equipment such as gas turbine low discharging burning chamber, in order to realize the abundant premix of fuel and air
Have to increase fuel with the length of air pre-mixing section；In order to stablizing for premixed flame also needs to increase combustion space, cause combustion
Burn the volume increase of room burner inner liner；Also need to increase the structures such as resonator cavity to control premixed combustion vibration, cause total burning
Cell structure is heavy and complicated.Combustion System and adjustment are also very complicated simultaneously, need to increase many regulating valves and pipeline.It is such
Combustion technology whether has many drawbacks to boiler or gas turbine.Come particularly with retrofiting from aero-engine
Gas turbine, due to the compact conformation of aero-engine itself, the bags it is limited, using the transformation required for prior art
Workload is huge, and still faces the problems such as control is complicated, regulation is difficult.
The content of the invention
In view of this, present invention is primarily targeted at providing a kind of combustor and the gas turbine using which, aviation
Motivation and boiler, to solve at least one of above-mentioned technical problem.
To achieve these goals, as one aspect of the present invention, the invention discloses a kind of carry main jet nozzle assembly
With the combustor of micro nozzle component, including diffuser, main jet nozzle assembly, micro nozzle component, burner inner liner and combustion box,
Wherein described diffuser is arranged on the combustion box end, by the High Temperature High Pressure air reduction of speed diffusion into combustor；Institute
State burner inner liner to be arranged in the combustion box, Cooling Holes of the portion of air on the burner inner liner wall enter described
In burner inner liner, the high-temperature part of the burner inner liner is cooled down；It is characterized in that：
The burner inner liner front end is provided with the main jet nozzle assembly and micro nozzle component, the big portion entered by diffuser pipe
Divide air after the air duct of the main jet nozzle assembly and micro nozzle component is mixed with the fuel for spraying into, in the flame
Cylinder roasting；
The micro nozzle component includes fuel manifold and N number of micro nozzle unit, and wherein N is natural number, and miniature spray
Mouth unit sector meets N × β=360 between angle β and micro nozzle element number N；The micro nozzle unit is comprising some
The external diameter of individual micro nozzle, wherein micro nozzle is 3～15mm, and adjacent micro nozzle centre-to-centre spacing is the 1.1 of micro nozzle external diameter
～2 times；And
Match somebody with somebody cyclization, and the main burner of the quantity with cyclization and main jet nozzle assembly comprising several in the micro nozzle unit
Quantity is equal, and the main burner of the main jet nozzle assembly is assemblied in described matching somebody with somebody in cyclization.
As another aspect of the present invention, the invention also discloses a kind of combustion gas wheel using combustor as above
Machine, aero-engine and boiler.
Understood based on above-mentioned technical proposal, the present invention is had the advantage that relative to existing premixed combustion technology：(1) it is right
The agent structure of gas turbine changes little, is particularly suited for boat remodeling gas turbine；(2) using micro nozzle spray fuel, combustion
Material is mixed with air fully, easily reaches lower burning and exhausting, emission CO, NO of the combustorX25ppm@can be less than
15%O2, meet the requirement of the national standards such as GB13223；(3) multichannel fuel staging can realize flexible firing optimization；(4) adopt
The combustion oscillation problem that premixed combustion faces is inhibited effectively with preposition fuel injection.
Description of the drawings
Fig. 1 is the structural representation with main burner and the combustor of micro nozzle of the present invention；
Fig. 2 is A-A profiles in Fig. 1；
Fig. 3 is the main nozzle structure schematic diagram of the combustor of the present invention；
Fig. 4 is C-C profiles in Fig. 3；
Fig. 5 is the three dimensional sectional view of main burner shown in Fig. 3；
Fig. 6 is the arrangement schematic diagram of the micro nozzle component of the combustor of the present invention；
Schematic diagrams of the Fig. 7 for single micro nozzle structure in the micro nozzle component shown in Fig. 6；
Fig. 8 is B-B profiles in Fig. 7；
Fig. 9 is the three-dimensional sectional structural representation of the micro nozzle component of the present invention；
Figure 10 is the three dimensional sectional view with main burner and the combustor of micro nozzle of the present invention；
Figure 11 is a kind of structural representation of application of the technical scheme in point pipe-type chamber.
Specific embodiment
To make the object, technical solutions and advantages of the present invention become more apparent, below in conjunction with specific embodiment simultaneously reference
Accompanying drawing, is described in further detail to the present invention, but does not therefore limit the present invention in the range of the embodiment.
The invention discloses a kind of combustor with main jet nozzle assembly and micro nozzle component, including diffuser, main jet
Nozzle assembly, micro nozzle component, burner inner liner and combustion box, wherein diffuser are arranged on combustion box end, will enter
The High Temperature High Pressure air reduction of speed diffusion of combustor；Burner inner liner is arranged in combustion box, and burner inner liner front end is provided with main burner
Component and micro nozzle component, the most of air entered by diffuser pipe is by the main jet nozzle assembly and micro nozzle component
After air duct is mixed with the fuel for spraying into, in flame cylinder roasting；Remaining portion of air is cold on burner inner liner wall
But hole is entered in burner inner liner, and the high-temperature part of burner inner liner is cooled down.
The micro nozzle component includes fuel manifold and N number of micro nozzle unit, and wherein N is natural number, and micro nozzle
Unit sector meets N × β=360 between angle β and micro nozzle element number N；Micro nozzle unit is miniature comprising several
The external diameter of nozzle, wherein micro nozzle is 3～15mm, and adjacent micro nozzle centre-to-centre spacing is 1.1～2 times of micro nozzle external diameter；
And
Match somebody with somebody cyclization, and the main jet unrounded number of the quantity with cyclization and main jet nozzle assembly comprising several in micro nozzle unit
Equal, the main burner of main jet nozzle assembly is assemblied in this with cyclization.
Preferably, the combustor also includes the preposition fuel injection assemblies between diffuser and main jet nozzle assembly,
The preposition fuel injection assemblies include preposition fuel injection pipe, for preposition fuel being sprayed in the high velocity air after diffuser,
Quickly blend with air, play a part of to suppress combustion oscillation.
Preferably, the airflow direction discharged of the fuel injection direction of preposition fuel injection assemblies and diffuser into 60 °～
120 ° of angles, preferred value are 90 °；
Preposition fuel injection pipe is a ring-shaped round pipe with fuel orifice, and which passes through mouthpiece and is fixed on diffuser
On casing wall afterwards.
Preferably, main jet nozzle assembly includes double-channel spray nozzle bar, fuel distributor and main burner；Wherein the dual pathways is sprayed
Mouth bar includes two fuel channels, is input into main premix fuel and diffused fuel respectively.Main burner is by fuel injection blade, eddy flow leaf
Piece, central bluff body front end, central bluff body, fuel clapboard and nozzle casing etc. are constituted.
Preferably, meeting between the structural parameters of main jet nozzle assembly：
K/H=1.5～2.5, preferred value are 2；Wherein K be nozzle casing internal diameter, bluff body external diameter centered on H；
L/K=0.3～0.8, preferred value are 0.5；Distance centered on wherein L between bluff body end face and nozzle casing end face；
Swirl vane is 20 °～60 ° with the angle of central bluff body centrage, and preferred value is 35 °；
Fuel orifice is 10 °～60 ° with the angle of central bluff body centrage, and preferred value is 45 degree；
Every double-channel spray nozzle bar connects at least one main burner and corresponding fuel distributor.
Preferably, micro nozzle includes centrosome, the micro- swirl vane arranged around centrosome and surrounds micro- eddy flow leaf
The micro nozzle casing of piece, micro nozzle casing contain 1～8 micro-size fuel spray-hole；
Preferably, the front end of centrosome is streamlined structure；
Preferably, the quantity of micro- swirl vane is 2～12 in micro nozzle；
Preferably, centrosome external diameter is 0.2～0.6 with the ratio of micro nozzle casing internal diameter, preferred value is 0.5；
Preferably, micro nozzle is fixed between micro nozzle unit protecgulum and bonnet, and miniature spray in micro nozzle
Fuel orifice contained by mouth casing is included in the space that micro nozzle group protecgulum, bonnet and shell are formed.
Preferably, burner inner liner is made up of two concentric annulus；It is micro- in the front end of burner inner liner and micro nozzle component
The inside and outside arc surface of type nozzle housing is connected；The outside wall surface of burner inner liner is fixed on outer combustion case, the rear end of burner inner liner
It is overlapped on Gas Turbine entrance；
Preferably, the cooling of burner inner liner is using the one kind in gaseous film control, fin cooling, diverging cooling or its combination.
Preferably, the fuel injection manner of the combustor includes preposition fuel injection, main premix fuel injection, diffusion combustion
At least one of material injection and miniature premix fuel injection.
Preferably, the combustor is annular, is in charge of shape, ring-pipe type or single-tube combustor.
The invention also discloses a kind of gas turbine including combustor as above, aero-engine and boiler.
As a preferred embodiment of the present invention, the invention discloses a kind of combustor, including：Diffuser, preposition combustion
Material ejection assemblies, main jet nozzle assembly, micro nozzle component, burner inner liner and combustion box etc., wherein：
Main jet nozzle assembly includes double-channel spray nozzle bar, nozzle mounting seat, fuel distributor and main burner, wherein main burner by
Fuel injection blade, swirl vane, central bluff body front end, central bluff body, fuel clapboard and nozzle casing etc. are constituted；And
Micro nozzle component is made up of fuel manifold and micro nozzle unit etc., and wherein micro nozzle unit is by miniature spray
Mouth, micro nozzle monoreactant import, fuel uniform device, micro nozzle cell enclosure, micro nozzle unit protecgulum, micro nozzle
Unit bonnet, constitute with cyclization etc.；
Preposition fuel injection assemblies are made up of preposition fuel injection pipe, mouthpiece and mounting seat etc., its fuel injection direction
Into 60 °～120 ° angles, preferred value is 90 ° to the airflow direction discharged with diffuser.
In the combustor, main jet nozzle assembly spreads two-way fuel conduit comprising main premix, meets between its structural parameters：
K/H=1.5～2.5, preferred value are 2；L/K=0.3～0.8, preferred value are 0.5；Swirl vane and central bluff body centrage
Angle is 20 °～60 °, and preferred value is 35 °；Fuel orifice is 10 °～60 ° with the angle of central bluff body centrage, preferred value
For 45 degree；Every double-channel spray nozzle bar connects at least one main burner and corresponding fuel distributor.
In the combustor, micro nozzle component includes the individual micro nozzle units of N (N >=1), and wherein micro nozzle unit is fan-shaped
N × β=360 are met between angle β and micro nozzle element number N；Micro nozzle unit includes the quantity with cyclization and main jet
The main jet unrounded number that nozzle assembly is included is equal；Micro nozzle unit includes several micro nozzles, the wherein external diameter of micro nozzle
For 3～15mm, 1.1～2 times for micro nozzle external diameter of adjacent micro nozzle centre-to-centre spacing.
Micro nozzle includes centrosome, micro- swirl vane and micro nozzle casing etc., wherein micro nozzle casing contain 1～
8 micro-size fuel spray-holes, the front end of centrosome is streamlined structure；In micro nozzle, the quantity of micro- swirl vane is 2～12
Individual, centrosome external diameter is 0.2～0.6 with the ratio of micro nozzle casing internal diameter, and preferred value is 0.5；Micro nozzle is fixed on miniature
Between nozzle unit protecgulum and bonnet, and the fuel orifice in micro nozzle contained by micro nozzle casing is included in micro nozzle
In the space that group protecgulum, bonnet and shell are formed.
In the combustor, burner inner liner is mainly made up of two concentric annulus.The front end of burner inner liner and micro nozzle component
In the inside and outside arc surface of micro nozzle shell be connected；The outside wall surface of burner inner liner is fixed by a pin to outer combustion case
On, the rear end of burner inner liner is overlapped on Gas Turbine entrance.The wall of burner inner liner can be cold using gaseous film control, fin
But, the type of cooling of diverging cooling etc. and combination.
The preferred compositions of the combustor include preposition fuel injection, main premix fuel injection, diffused fuel and spray and micro-
Type premix four kinds of fuel injection manners such as fuel injection, but be not in the application must be while comprising these four fuel injection sides
Formula.
The invention also discloses a kind of send out including the gas turbine of the combustor with micro nozzle as above, aviation
The equipment such as motivation and boiler.
Explanation is further elaborated to specific embodiments of the present invention below in conjunction with the accompanying drawings.
Referring to Fig. 1,2, the invention discloses a kind of low emission combustor with main burner 320 and micro nozzle 420, its
Including diffuser 1, preposition fuel injection assemblies 2, main jet nozzle assembly 3, micro nozzle component 4, burner inner liner 5 and combustion box
(outer combustion case 6 and the indoor casing 7 of burning) etc..The combustion of main burner 320 and the combination of micro nozzle 420 is employed specifically
Material spray mode, specific propellant spray are realized by main jet nozzle assembly 3 and micro nozzle component 4.
Low emission combustor of the present invention is the critical piece of gas turbine, and its effect is the chemical energy for realizing fuel
To the conversion of heat energy, and reduce the generation of combustion process pollutant.From the High Temperature High Pressure air that gas turbine blower is discharged
After 1 reduction of speed diffusion of diffuser, most of air is entered in main jet nozzle assembly 3 of the present invention and micro nozzle component 4
Air duct in, after mixing with the corresponding fuel for spraying into, burnt in the downstream of main burner 320 and micro nozzle 420.Separately
A part is entered in burner inner liner through the Cooling Holes on 5 wall of burner inner liner, and the high-temperature part of burner inner liner is cooled down, fire is prevented
The ablation at high temperature of flame cylinder.As shown in Fig. 2,6,10,11, being unique in that for the present invention employs main burner 320 and miniature
The mode that nozzle 420 combines, realizes flexible burning tissues and adjustment.The indoor fuel of burning of the present invention is by work
With being divided into four kinds：Preposition fuel, main premix fuel, diffused fuel and micro- premix fuel.Preposition fuel is by preposition fuel injection
In high velocity air after the penetrating diffuser 1 of component 2, quickly blend with air, act primarily as the effect for suppressing combustion oscillation.Premix combustion
Material and micro- premix fuel are fully blended with air by main jet nozzle assembly 3 and micro nozzle component 4, are realized premixed combustion, are reached
Reduce combustion high temperature area, reduce NOxDeng the purpose of pollutant emission.Diffusion combustion is by the diffusion pipeline in main jet nozzle assembly 3
Spray in combustor main burning area, the effect of main stabilization flame under combustion chamber ignition and low operating mode.
As in Figure 3-5, main jet nozzle assembly of the present invention 3 include double-channel spray nozzle bar 302, nozzle mounting seat 301,
Fuel distributor 303 and main burner 320, wherein main burner 320 are by fuel injection blade 321, swirl vane 323, central bluff body
Front end 311, central bluff body 319, fuel clapboard 314 and nozzle casing 316 etc. are constituted, and refer to Fig. 3-5.Through main jet nozzle assembly
The fuel of 3 sprays is divided into two kinds：Main premix fuel and diffused fuel.Main premix fuel is by logical in double-channel spray nozzle bar 302
In passage 307 in 305 incoming fuel allotter 303 of road, through nozzle casing 316 and 321 installation site of fuel injection blade
In corresponding perforate incoming fuel eject blade 321 i.e. in passage 325, then the fuel orifice on the fuel injection blade 321
322 spray in the air of diffuser 1, blend to form combustion mixture with air.Diffused fuel is also by double-channel spray nozzle bar
302 feed, and which passes through in the passage 306 in the 304 incoming fuel allotter 303 of another passage in double-channel spray nozzle bar 302, wears
Cross the perforate corresponding with 323 installation site of swirl vane of nozzle casing 316 in 323 interior i.e. passage 324 of swirl vane, afterwards
Into in the circular passage 315 in central bluff body 319, spray from the fuel orifice 317 of 319 end face of central bluff body, with process
Air blending burning after 323 rotary steering of swirl vane.Diffused fuel is mainly used in combustion chamber ignition and low operating mode,
After flameholding and under high operating mode, diffused fuel is closed.Following relation is met in main jet nozzle assembly 3 between each structural parameters
(referring to Fig. 4,5)：1. K/H=1.5～2.5, preferred value is 2；2. L/K=0.3～0.8, preferred value is 0.5；3. swirl vane
323 is 20 degree to 60 degree with the angle of 319 centrage of central bluff body, and preferred value is 35 degree；4. fuel orifice 317 is blunt with center
The angle of 319 centrage of body is 10 degree to 60 degree, and preferred value is 45 degree；5. every connection of double-channel spray nozzle bar 302 at least one
Main burner and corresponding fuel distributor 303.
Micro nozzle component of the present invention 4 includes fuel manifold 401 and its interface 402 and micro nozzle unit 430
Deng wherein micro nozzle unit 430 is by micro nozzle 420, micro nozzle monoreactant import 412, fuel uniform device 413, micro-
Type nozzle unit shell 411, micro nozzle unit protecgulum 414, micro nozzle unit bonnet 415, with cyclization 416 etc. constitute, in detail
Carefully see Fig. 1～2 and Fig. 6-9.Fig. 6 and 9 shows the front view and partial sectional view of micro nozzle unit 430.Micro nozzle
Component 4 includes the individual micro nozzle units 430 of N (N >=1), and wherein micro nozzle unit 430 is in fan-shaped (see Fig. 6), wherein fan-shaped folder
N × β=360 are met between angle beta and micro nozzle element number N.Micro nozzle unit 430 matches somebody with somebody cyclization 416 comprising at least one,
Which is equal with the quantity of the main burner 320 that main jet nozzle assembly 3 is included.Micro nozzle unit 430 includes several micro nozzles
420, these micro nozzles 420 are full of the space formed with micro nozzle cell enclosure 411 with cyclization 416, and meet miniature spray
The requirement of 420 external diameter of mouth and spacing.The external diameter of micro nozzle 420 is 3～15mm, and 420 centre-to-centre spacing of adjacent micro nozzle is miniature
1.1～2 times of 420 external diameter of nozzle.Micro nozzle 420 includes centrosome 423, micro- swirl vane 424 and micro nozzle casing 422
Deng wherein micro nozzle casing 422 contains 1～8 micro-size fuel spray-hole 421, and the front end 425 of centrosome 423 is streamlined
Structure, refers to Fig. 7 and 8.The quantity of micro- swirl vane 424 that micro nozzle 420 is included be 2～12,423 external diameter of centrosome with
The ratio of 422 internal diameter of micro nozzle casing is 0.2～0.6.Micro nozzle 420 is fixed on micro nozzle unit protecgulum 414 and bonnet
Between 415, and the fuel orifice 421 in micro nozzle 420 contained by micro nozzle casing 422 is included in micro nozzle group protecgulum
414th, bonnet 415, and shell 411 formed space in.Fuel manifold 401 and each 412 phase of micro nozzle monoreactant import
Even, and by fuel manifold interface 402 fuel supply is obtained from outside through outer combustion case 6.The work of micro nozzle component 4
As process it is：Fuel passes through in 402 incoming fuel house steward 401 of fuel manifold interface, and enters through 430 fuel of micro nozzle unit
Mouthfuls 412 enter each micro nozzle unit 430, through fuel uniform device 413 even into micro nozzle assembly housing 411 with it is miniature
The space that nozzle sets protecgulum 414 and bonnet 415 are formed, afterwards the fuel orifice 421 in micro nozzle 420 enter miniature
In the annular space that nozzle casing 422 is formed with micro nozzle centrosome 423, being mixed to form with the air from diffuser 1 can
Combustion gaseous mixture, is burnt in 420 downstream of micro nozzle.
Burner inner liner of the present invention 5, is mainly made up of two concentric annulus, refers to Fig. 1 and Figure 10.Burner inner liner 5
Front end is connected with the inside and outside arc surface of the micro nozzle shell 411 in micro nozzle component 4, and the outside wall surface of burner inner liner 5 passes through
Pin is fixed on outer combustion case 6, and rear end is overlapped on Gas Turbine entrance.The wall of burner inner liner 5 can be adopted
Gaseous film control, fin cooling, diverging cooling etc. and the type of cooling of combination.
Preposition fuel injection assemblies 2 of the present invention, mainly by groups such as preposition fuel injection pipe, mouthpiece and mounting seats
Into referring to Fig. 1.Preposition fuel injection pipe is a ring-shaped round pipe with fuel orifice, and which passes through mouthpiece and is fixed on expansion
On casing wall after depressor 1, the fuel injection direction of preposition fuel injection pipe is with the airflow direction of the discharge of diffuser 1 into 60 °
～120 ° of angles, preferred value are 90 °, are beneficial to the blending of fuel and air.
Low emission combustor of the present invention, is mainly used in gas turbine, is particularly suited for boat remodeling gas turbine,
But it is not limited thereto.Especially it is noted that the fuel injection techniques of low emission combustor of the present invention and correlation, bag
The accompanying drawing of the present invention is included, is described as a example by this specific form all by toroidal combustion chamber, this does not represent the present invention
Toroidal combustion chamber is applicable only to, under the enlightenment of the present invention, is easily generalized to and is in charge of other shapes such as shape, ring-pipe type, single-tube
The gas-turbine combustion chamber of formula.Technology of the present invention can be used for combustion with adaptability reform by rational expansion simultaneously
The equipment of the operating on gaseous fuel such as gas boiler, drying heating.
The preferred compositions of the fuel injection manner such as main burner of the present invention described in detail above and micro nozzle,
Can be according to application scenario and the difference of working condition, using different assembled schemes in being embodied as.It is of the present invention low
Discharge combustor includes preposition fuel injection, main premix fuel injection, diffused fuel injection and miniature premix fuel injection etc.
The combination of four kinds of fuel injection manners, but be not in the application must be while comprising these four fuel injection manners.Such as may be used
To be only to contain main jet nozzle assembly 3 and preposition fuel injection assemblies 2, the low emission combustor of micro nozzle component 4 is not contained；
Can only contain micro nozzle component 4, and not contain the low emission combustor of other fuel injection manners.Specifically can basis
Application scenario and working condition flexible combination.
Embodiment 1
In the present embodiment by taking point pipe-type chamber as an example, its application in the type combustor is briefly introduced.It is in charge of shape
The basic structure of combustor is columnar, and burner inner liner and combustion box are all columnar.In the internal ring of toroidal combustion chamber
Under the extreme case of reduced radius to zero, toroidal combustion chamber is just similar with the basic structure of point pipe-type chamber.Figure 11 shows
Can be in a kind of employing main burner 320 in point pipe-type chamber and the concrete structure of the combination arrangement of micro nozzle 420.In Figure 11
In, center is a main burner 320, around main burner 320 arranges some micro nozzles 420.Figure 11 shows the present invention
A kind of concrete arrangement form for being in charge of shape head of combustion chamber nozzle for proposing, the other parts structure of combustor and tradition are in charge of shape
Combustor is similar to, and is also adopted by the structures such as cylinder type burner inner liner and changeover portion.Arrangement as shown in figure 11 can make full use of
Head of combustion chamber space, increases the AIR Proportional for premixed combustion, so as to reduce the equivalent proportion of fuel in nozzle, more has utilization
Reduce the NO in combustion productXDischarge.Can also be conducive to shortening the length of flame using the structure of micro nozzle simultaneously, such that it is able to
Using shorter burner inner liner, make combustion apparatus structure compacter.
Particular embodiments described above, has been carried out to the purpose of the present invention, technical scheme and beneficial effect further in detail
Describe in detail bright, it should be understood that the foregoing is only the specific embodiment of the present invention, be not limited to the present invention, it is all
Within the spirit and principles in the present invention, any modification, equivalent substitution and improvements done etc. should be included in the protection of the present invention
Within the scope of.
Claims (10)
1. a kind of combustor with main jet nozzle assembly and micro nozzle component, including diffuser, main jet nozzle assembly, micro nozzle
Component, burner inner liner and combustion box, wherein the diffuser is arranged on the combustion box end, by into combustor
High Temperature High Pressure air reduction of speed diffusion；The burner inner liner is arranged in the combustion box, and portion of air is through the flame
Cooling Holes on tube wall surface are entered in the burner inner liner, and the high-temperature part of the burner inner liner is cooled down；It is characterized in that：
The burner inner liner front end is provided with the main jet nozzle assembly and micro nozzle component, and the major part entered by diffuser is empty
Gas by the air duct of the main jet nozzle assembly and micro nozzle component with spray into fuel mix after, in the burner inner liner
Burning；
The micro nozzle component includes fuel manifold and N number of micro nozzle unit, and wherein N is natural number, and micro nozzle list
First sector meets N × β=360 between angle β and micro nozzle element number N；The micro nozzle unit is micro- comprising several
The external diameter of type nozzle, wherein micro nozzle is 3～15mm, and adjacent micro nozzle centre-to-centre spacing is the 1.1～2 of micro nozzle external diameter
Times；And
Match somebody with somebody cyclization, and the main jet unrounded number of the quantity with cyclization and main jet nozzle assembly comprising several in the micro nozzle unit
Equal, the main burner of the main jet nozzle assembly is assemblied in described matching somebody with somebody in cyclization.
2. combustor according to claim 1, it is characterised in that the combustor is also included positioned at the diffuser and master
Preposition fuel injection assemblies between nozzle assembly, the preposition fuel injection assemblies include preposition fuel injection pipe, for inciting somebody to action
Preposition fuel is sprayed in the high velocity air after the diffuser, is quickly blended with air, is played a part of to suppress combustion oscillation.
3. combustor according to claim 2, it is characterised in that the fuel injection direction of the preposition fuel injection assemblies
Into 60 °～120 ° angles, preferred value is 90 ° to the airflow direction discharged with the diffuser；
The preposition fuel injection pipe is a ring-shaped round pipe with fuel orifice, and which passes through mouthpiece and is fixed on diffuser
On casing wall afterwards.
4. combustor according to claim 1, it is characterised in that the main jet nozzle assembly includes double-channel spray nozzle bar, combustion
Material allotter and main burner；Wherein described double-channel spray nozzle bar includes two fuel channels, is input into main premix fuel and expansion respectively
Scattered fuel；
Main burner includes fuel injection blade, swirl vane, central bluff body front end, central bluff body, fuel clapboard and nozzle machine
Casket.
5. combustor according to claim 4, it is characterised in that meet between the structural parameters of the main jet nozzle assembly：
K/H=1.5～2.5, preferred value are 2；Wherein K be nozzle casing internal diameter, bluff body external diameter centered on H；
L/K=0.3～0.8, preferred value are 0.5；Distance centered on wherein L between bluff body end face and nozzle casing end face；
Swirl vane is 20 °～60 ° with the angle of central bluff body centrage, and preferred value is 35 °；
Fuel orifice is 10 °～60 ° with the angle of central bluff body centrage, and preferred value is 45 degree；
Every double-channel spray nozzle bar connects at least one main burner and corresponding fuel distributor.
6. combustor according to claim 1, it is characterised in that the micro nozzle includes centrosome, around centrosome
The micro- swirl vane for arranging and the micro nozzle casing for surrounding micro- swirl vane, the micro nozzle casing contain 1～8 it is miniature
Fuel orifice；
Preferably, the front end of centrosome is streamlined structure；
Preferably, the quantity of micro- swirl vane is 2～12 in micro nozzle；
Preferably, centrosome external diameter is 0.2～0.6, preferably 0.5 with the ratio of micro nozzle casing internal diameter；
Preferably, micro nozzle is fixed between micro nozzle unit protecgulum and bonnet, and micro nozzle machine in micro nozzle
Fuel orifice contained by casket is included in the space that micro nozzle group protecgulum, bonnet and shell are formed.
7. combustor according to claim 1, it is characterised in that the burner inner liner is made up of two concentric annulus；Fire
The front end of flame cylinder is connected with the inside and outside arc surface of the micro nozzle shell in micro nozzle component；The outside wall surface of burner inner liner is solid
It is scheduled on outer combustion case, the rear end of burner inner liner is overlapped on Gas Turbine entrance；
Preferably, the cooling of the burner inner liner is using the one kind in gaseous film control, fin cooling, diverging cooling or its combination.
8. combustor according to claim 1, it is characterised in that the fuel injection manner of the combustor includes preposition combustion
At least one of material injection, main premix fuel injection, diffused fuel injection and miniature premix fuel injection.
9. combustor according to claim 1, it is characterised in that the combustor is annular, is in charge of shape, ring-pipe type or list
Cast combustor.
10. a kind of gas turbine of the combustor using as described in claim 1 to 9 any one, aero-engine and pot
Stove.
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| CN201611163961.XA CN106524223B (en) | 2016-12-15 | 2016-12-15 | Combustion chamber with main nozzle assembly and mini-nozzle assembly |
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| CN106524223B CN106524223B (en) | 2023-06-02 |
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| CN110953603A (en) * | 2019-12-05 | 2020-04-03 | 中国航发四川燃气涡轮研究院 | Multi-oil-path fuel oil spraying device suitable for radial grading main combustion chamber |
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| CN113722833A (en) * | 2021-09-09 | 2021-11-30 | 湖南工业大学 | Turbofan engine residual service life prediction method based on dual-channel long-short time memory network |
| CN114294680A (en) * | 2021-12-29 | 2022-04-08 | 哈尔滨工业大学 | Micro-premix combustion chamber of center-staged gas turbine |
| DE102020128661A1 (en) | 2020-10-30 | 2022-05-05 | Rolls-Royce Deutschland Ltd & Co Kg | Nozzle for a combustion chamber of an engine with at least two nozzle heads |
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