CN101169252A - Aerial engine lean premixed preevaporated low contamination combustion chamber - Google Patents
Aerial engine lean premixed preevaporated low contamination combustion chamber Download PDFInfo
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- CN101169252A CN101169252A CNA200710178394XA CN200710178394A CN101169252A CN 101169252 A CN101169252 A CN 101169252A CN A200710178394X A CNA200710178394X A CN A200710178394XA CN 200710178394 A CN200710178394 A CN 200710178394A CN 101169252 A CN101169252 A CN 101169252A
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Abstract
The invention provides an aerial engine lean-oil pre-mixing pre-evaporation low-pollution combustion chamber, which consists of a head and a flame tube. The burning gas is fully supplied from the head of the combustion chamber, while the cooling gas and the mixed gas enter from the flame tube. The head is in double-ring cavity structure and is divided into a pre-burning stage and a main-burning stage; the pre-burning stage is arranged inside, and the main burning stage surrounds the pre-burning stage. The pre-burning stage includes a centrifugal nozzle and a swirler surrounding the centrifugal nozzle. The fuel oil sprayed out of the centrifugal nozzle is cut and broken by the air vortex from the swirler, and is mixed in the mixing cavity of the pre-burning stage, and then the fuel oil enters into the burning area to form the dispersing burning. Moreover, the main burning stage includes a direct air atomizing nozzle, a main swirler and a pre-mixing ring cavity; wherein, the main swirler is positioned at the upper reach of the nozzle, while the pre-mixing ring cavity is positioned at the lower reach of the nozzle. The fuel oil is firstly mixed with the air and atomized in the nozzle, and then is tangentially sprayed into the pre-mixing ring cavity for pre-mixing pre-evaporation, and finally the fuel oil enters into the burning area to form pre-mixing burning. Besides, convergent-divergent opening is arranged at the lower reach of the fuel oil outlets of the pre-burning stage and the main burning stage so as to prevent the tempering and carbon deposition. With simple structure, the invention, in the condition of ensuring the working state, can effectively reduce the pollution exhaust of the aerialengine.
Description
Technical field
The present invention relates to content is a kind of aerial engine lean premixed preevaporated low contamination combustion chamber, it is simple in structure in the aeroengine combustor buring chamber designed according to this invention, when guaranteeing combustion chamber stability and high efficiency work, can effectively reduce the Air discharging of aero-engine.
Background technology
The main development trend of aeroengine combustor buring chamber is combustion with reduced pollutants, to satisfy the aero-engine emission standard of increasingly stringent.Its requirement of CAEP4 standard of adopting at present can be described as suitable strictness, and is after 08 year that the CAEP6 standard that adopts is then strict especially, its NO
XDischarging is than the average emission level low 60% of present engine.Improve and only the structure of existing conventional engine chamber is done some, can not reach exhaust air pollution standards.Therefore the new combustion chamber of a generation, i.e. low pollution combustor have been drawn.
Two GE of leading company of Americanized aero-engine and PW have set about research to low pollution combustor, GE has has at first researched and developed dicyclo chamber combustion with reduced pollutants DAC (being used for GE90 and CFM56), PW company has adopted class RQL (fuel-rich combustion-put out soon-poor oil firing, Rich burn-Quench-Lean burn is called for short RQL) low pollution combustor TALON II (being used for PW4000 and 6000 series).Aspect low pollution combustor of future generation, it is TAPS (the Twin Annular Premixing Swirler) low pollution combustor of its GEnx reseach of engine that GE company adopts LDM (Lean Direct Mixing Combustion, oil-poor direct hybrid combustor) technology.This combustion chamber has entered the complete machine Qualify Phase, is about to evidence obtaining, in stand loopful verification experimental verification, and NO
XDisposal of pollutants has reduced by 50% than CAEP2 discharge standard.PW company continues to adopt the RQL mode to propose reduction NO
XThe low pollution combustor of disposal of pollutants is TALON X, and the head type of employing is the air atomizer spray nozzle of PW company development, and the combustion chamber is the monocycle chamber, and the result of the test on V2500 engine fan type test section has reduced by 50% than CAEP2 standard.It is ANTLE that Rolls-Royce company adopts the low pollution combustor of LDM technical development, and this combustion chamber is fractional combustion chamber, a monocycle chamber, its NO
XDisposal of pollutants has reduced by 50% than CAEP2 standard, is used for its engine rapids of new generation and reaches 1000.
And no matter be which kind of advanced person's low pollution combustor, its key technology reduces NO exactly
X(nitrogen oxide), CO (carbon monoxide), UHC (unburned hydrocarbons) and the combustion technology of smoldering, key problem is to reduce the temperature of combustion zone, make the combustion zone temperature field even simultaneously, promptly whole and local equivalent proportion control, and the uniformity of primary zone equivalent proportion depends primarily on the uniformity of fuel-oil atmozation and oil gas blending.
According to NO
XMechanism that produces with CO and result of the test be as can be known: the NO that the primary zone equivalent proportion of combustion chamber produces in 0.6～0.8 scope
XWith CO (the discharging rule of UHC and CO is similar) seldom.Based on this principle, take into account NO
XAll be in the low value scope with the discharge capacity of CO, UHC, should consider two factors: the average equivalent ratio in first primary zone, it two is uniformities of primary zone equivalent proportion, and all should be like this under the working condition of all aero-engines.And the uniformity of primary zone equivalent proportion depends primarily on the uniformity of fuel-oil atmozation and oil gas blending.This depends primarily on two aspects: the one, and the uniformity that the fuel particles diameter distributes, the i.e. distributing homogeneity of SMD; Second be the uniformity that the fuel oil oil mist concentration distributes.From combustion system, should adopt uniform premixed combustion, reach primary zone equivalent proportion uniformity requirement to reduce disposal of pollutants.
Present conventional combustion system can't reduce NO
X, CO and UHC discharging.Reason is that the method for designing of current combustion chamber determines.When big state, combustion zone temperature is that stoichiometric ratio is near 1 o'clock the ignition temperature at stoichiometric ratio, far surpasses the required equivalent proportion area requirement of above-mentioned combustion with reduced pollutants.During little state, the combustion zone equivalent proportion is very low again, far below the required equivalent proportion of above-mentioned combustion with reduced pollutants interval.In addition, diffusion combustion mode is all adopted in conventional at present burning, and local equivalent proportion is very inhomogeneous, therefore, is difficult to reach the requirement of combustion with reduced pollutants.
According to the achievement of basic research, thoroughly realize the combustion with reduced pollutants of aero-engine, must adopt lean premixed preevaporated burning, to take into account the stable operation range of combustion chamber simultaneously, i.e. stability.
Summary of the invention
Technology of the present invention is dealt with problems: overcome the deficiencies in the prior art, a kind of aerial engine lean premixed preevaporated low contamination combustion chamber is provided, is satisfying under the condition of work of aero-engine this combustion chamber, can effectively reduce the disposal of pollutants of aeroengine combustor buring chamber burning, comprises NO
X, smolder, CO and UHC, and simple in structure.
Technical solution of the present invention: a kind of aerial engine lean premixed preevaporated low contamination combustion chamber, to form by head and burner inner liner, burning tolerance is all infeeded by head of combustion chamber, and cold gas and mixed gas enter from burner inner liner; Described head is the dicyclo cavity configuration, comprises pre-combustion grade that is used for flame stabilization and startup that is positioned at ring and the main combustion stage that is positioned at the high-efficient low polluting combustion that is used for most of fuel oil of outer shroud; Described pre-combustion grade comprises swirl atomizer and around the cyclone of swirl atomizer, fuel oil is subjected to the shearing-crushing from the air swirl of cyclone after swirl atomizer ejection, and mixes to enter then in pre-combustion grade hybrid chamber zone and form diffusion combustion in the combustion zone; Main combustion stage is around pre-combustion grade, comprise direct-injection type air atomizer spray nozzle, main cyclone device and premix ring cavity, the main cyclone device is positioned at the upstream of direct-injection type air atomizer spray nozzle outlet, the jet expansion downstream is the premix ring cavity, fuel oil carries out mixed aerosol with air in advance in the direct-injection type air atomizer spray nozzle, peripheral jet goes into to carry out premix and pre-evaporation in the premix ring cavity then, enters the combustion zone at last and forms premixed combustion; Adopt contracting and extending port to prevent tempering and carbon distribution respectively in the downstream of pre-combustion grade and main combustion stage jet expansion.
Principle of the present invention is: generally speaking, the realization of aeroengine combustor buring chamber low pollution emission mainly is exactly by two aspects, and the one, control the overall equivalent proportion scope in internal combustion zone, whole combustion chamber; Second be the burning uniformity of whole combustion zone in the control combustion chamber, i.e. equivalent proportion uniformity, the excessive disposal of pollutants that also can increase engine greatly of local equivalent proportion that causes because of local rich oil.According to above-mentioned principle and consider the work characteristics of aeroengine combustor buring chamber, the present invention adopts: burning usefulness gas all infeeds from the head of combustion chamber, in the combustion zone, form poor oil firing, and by fuel oil classification measure, control combustion chamber equivalent proportion can both enter the combustion with reduced pollutants interval under aero-engine different operating state, to reduce all Air emissions.Cold gas and mixed gas all infeed from burner inner liner, and the control by the cooling air is flowed, and avoid producing too much carbon monoxide and unburned carbon hydrogen.Chamber head part pre-combustion grade and main combustion stage two-stage adopt the combination of two kinds of different fuel oil stand-by modes and two kinds of combustion modes, to take into account the performance requirement of low two contradictions of flameholding and disposal of pollutants.Pre-combustion grade starts under little states such as slow train, and the equivalent proportion of combustion zone drops in the above-mentioned combustion with reduced pollutants equivalent proportion interval when keeping little state, and makes the good stability of burning, starts easily.When engine operation just starts main combustion stage during at big state, main combustion stage is the premix and pre-evaporation pattern, and the equivalent proportion of control combustion zone is in above-mentioned combustion with reduced pollutants equivalent proportion interval, and guarantees local equivalent proportion uniformity height in the combustion zone.Adopt above-mentioned low pollution combustor, can guarantee under all duties in aeroengine combustor buring chamber, the whole equivalent proportion of combustion zone is controlled in the interval of combustion with reduced pollutants, control the equivalent proportion uniformity of combustion zone by the control main combustion stage mist of oil uniformity, degree of mixing and evaporativity simultaneously, disposal of pollutants is low, the aero-engine low pollution combustor performance requirement of good stability thereby reach.
The present invention's advantage compared with prior art is as follows:
1. combustion chambers burn is all infeeded by head, and cooling and blending etc. then enter from burner inner liner with gas, simplifies the structure of combustion chamber when increasing the combustion chamber effect.
2. main combustion stage adopts the peripheral jet of direct-injection type air atomizer spray nozzle, has not only improved the wall effect of beating of spraying, and makes fuel particles wideer in the distribution of circumferentially (or exhibition to), thereby has improved the distribution of oil gas mixing, has reduced circumferential spray site.
3. the ring cavity eddy flow is gone in the air atomizer spray nozzle peripheral jet, and fuel oil is through second-time breakage, and atomizing effect is better, realizes uniform premixed, and the good evaporation of fuel oil.
4. effectively prevent the carbon distribution and the tempering of nozzle by two contracting and extending ports of pre-combustion grade and main combustion stage, solve the key technology difficult problem of lean premixed preevaporated burning.
5. pass through the combined burning pattern of the premixed combustion of pre-combustion grade diffusion combustion and main combustion stage premixed prevapourising, realize the wide stable operation range and the low pollution emission of aeroengine combustor buring chamber, the comparable CAEP2 standard of disposal of pollutants reduces by 60%.
Description of drawings
Fig. 1 is a combustion chamber of the present invention frame diagram;
Fig. 2 is the head construction figure of combustion chamber of the present invention;
Fig. 3 is head oil supply structure figure for combustion chamber of the present invention A-A cross sectional view;
Fig. 4 is the air atomizer spray nozzle schematic cross-section for B-B cross section, combustion chamber of the present invention;
Fig. 5 is that the head end aperture is arranged schematic diagram for C-C cross section, combustion chamber of the present invention.
Among the figure: 1. Composite Double oil circuit, 2. main combustion stage fuel feeding road, 3. swirl atomizer, 4. cyclone, 5. pre-combustion grade inlet channel, 6. pre-combustion grade hybrid chamber, 7. cooling air channels, 8. main combustion stage premix gas passage, 9. pre-right level contracting and extending port, 10. fuel jet, 11. the oil gas mixed vent, 12. main cyclone devices, 13. main combustion stage premix ring cavities, 14. the cooling hole, 15. direct-injection type air atomizer spray nozzles, 27. main combustion stage contracting and extending ports, 28. flame tube wall, 29. blending hole, 30. combustion chambers burn zones.
Structure in the corresponding diagram, relate to following critical size: 16. grazing incidence angles, 17. oil gas mixed vent passage length, 18. fuel jet is to the distance of oil gas mixed vent, 19. fuel jet diameter, 20. oil gas mixed vent diameter, 21. the pre-combustion grade contracting and extending port shrinks angle, 22. pre-combustion grade contracting and extending port expansion angle, 23. swirl atomizer is exported to pre-combustion grade contracting and extending port throatpiston distance, 24. the main combustion stage contracting and extending port shrinks angle, 25. main combustion stage contracting and extending port expansion angles, 26. direct-injection type air atomizer spray nozzles are exported to main combustion stage contracting and extending port throatpiston distance.
The specific embodiment
As shown in Figure 1, 2, 3, the combustion chamber of the present invention's design is made up of head and burner inner liner, and burning usefulness gas all infeeds from the head, and other all infeeds from burner inner liner with gas, and blending hole 29 is set to adjust the combustor exit Temperature Distribution in the burner inner liner rear end.The primary structure of head is the circular rings cavity configuration, is divided into pre-combustion grade and main combustion stage, and pre-combustion grade comprises swirl atomizer 3 and around the cyclone 4 of swirl atomizer; Main combustion stage comprises direct-injection type air atomizer spray nozzle 15, main cyclone device 12 and premix ring cavity 13 around pre-combustion grade.The oil circuit 2 of pre-combustion grade swirl atomizer 3 and main combustion stage air atomizer spray nozzle 15 and oil jet 10 can be processed as a fuel feeding integral body, comprise that the mixed vent 11 of direct-injection type air atomizer spray nozzle 15, a plurality of parts of pre-combustion grade contracting and extending port 9 are processed as a toroidal cavity integral body.Be about to the cyclone and the toroidal cavity integral installation of two-stage combustion during installation earlier, can weld also and can pass through thread connection, push then in the burner inner liner and pass through bolting, will comprise that at last the whole correspondence of fuel feeding of swirl atomizer 3 pushes in the toroidal cavity integral body with flame tube wall.
In pre-combustion grade, fuel oil is subjected to the shearing-crushing from the shear flow that is looped around its cyclone 4 on every side via swirl atomizer 3 ejections, and enters primary zone, combustion chamber formation diffusion combustion with bigger spraying subtended angle; For main combustion stage, fuel oil is via fuel jet 10 ejections, with enter oil gas mixed vent 11 after the air mixing primary crushings in the premixed channel 8, tangentially spray into premix ring cavity 13 by oil gas mixed vent 11 again, the upstream of premix ring cavity 13 is equipped with cyclone 12, carry out second-time breakage under the effect of oil-gas two-phase flow eddy flow in premix ring cavity 13 of ejection, so just can better make fuel oil atomized, and the mode that adopts grazing incidence is improved fuel-oil atmozation along the circumferentially distribution of (or exhibition to), fuel oil mix well in premix ring cavity 13 with air and evaporate after enter the combustion zone, form premixed combustion.Contracting and extending port 9 is set in pre-combustion grade nozzle 3 downstreams and main combustion stage nozzle 15 downstreams are provided with carbon distribution and the tempering of contracting and extending port 27 to prevent nozzle, and can improve the petroleum distribution in downstream.At whole head, main combustion stage direct-injection type air atomizer spray nozzle 15 can determine according to required duty at the distributed quantity that makes progress in week, quantity be at least one so that along circumferential a plurality of distributions more even so that the oil gas in the combustion chamber mixes.
Be ring cavity around the head fuel feed pump, and on end wall, open aperture 14, as shown in Figure 5, the quantity of aperture 14 and distribution are decided on the quantity of air atomizer spray nozzle 15, diameter is less than 3mm, and the interval, angle of inclination of aperture 14 is at 10 °--and 40 °, its effect can be cooled off head on the one hand, can also stop main combustion stage oil gas mixed flow to contact with pre-combustion grade flame too early on the other hand, prevent tempering and carbon distribution.
Pre-combustion grade has enough spraying subtended angles to satisfy stable ignition performance, and the subtended angle of main combustion stage is then limited in order to avoid fuel oil is beaten wall.The air distribution of pre-combustion grade accounts for 5%～35% of whole burning tolerance, and the air distribution of main combustion stage accounts for 65%～95% of whole burning tolerance.
The cyclone 4 of pre-combustion grade and the main cyclone device 12 of main combustion stage can adopt radial swirler also can adopt axial swirler; The two-stage atomizing also can be adopted multistage cyclone.
There are relation in the throatpiston diameter D of pre-combustion grade contracting and extending port 9 and the outlet of this cross-sectional distance swirl atomizer 3 distance 23 between the spraying subtended angle α of i.e. L, and swirl atomizer 3
The contraction angle 21 of pre-combustion grade contracting and extending port 9 and the scope of expansion angle 22 at 30 ° in 160 °; The contraction angle 24 of the contracting and extending port 27 of main combustion stage and the scope of expansion angle 25 also 30 ° in 160 °, the angle of contracting and extending port is relevant with the expansion angle of nozzle, should correspondingly mate.
Main combustion stage direct-injection type air atomizer spray nozzle 15 adopts the mode of grazing incidence, and angle 16 scopes of grazing incidence are in 15 ° to 75 ° scopes.Main combustion stage adopts the fuel oil stand-by mode of direct-injection type air atomizer spray nozzle 15 peripheral jets, has not only simplified the head of combustion chamber structure, and has improved the distribution of the atomizing effect and the fuel particles of fuel oil.Main combustion stage direct-injection type air atomizer spray nozzle 15 realizes that by two coaxial apertures the diameter range of its fuel jet 10 is 0.3mm-3mm; Oil gas mixed vent 11 areas determine that with the ratio of the area of fuel jet 10 ratio of this area is less than 50 by the area of this spout 11.In the main combustion stage direct-injection type air atomizer spray nozzle 15, with the diameter d of oil gas mixed vent 11
jAs the dimensionless linear module, the height of premix air duct 8 is less than 4d
j, the passage length 17 of fuel jet 10 is less than 6d
j, the distance 18 of fuel jet 10 and 11 outlets of oil gas mixed vent is less than 10d
j
In main combustion stage direct-injection type air atomizer spray nozzle 15, the fuel oil of fuel jet 10 ejection mixes 11 spout peripheral jets by oil gas again after via the air pre-mixing fragmentation in the premixed channel 8 and goes into ring cavity 13.The main diameter and the tangential angle [alpha] of the distance that exports of diameter ratio, fuel jet outlet and the oil gas mixed vent of oil gas mixed vent 11 and spout with fuel jet 10 of the atomization of main combustion stage nozzle is relevant; Promptly height is relevant with length for the characteristic that air flow in premixed and prevapourising characteristic and the ring cavity 13 and the physical dimension of ring cavity 13, and oil gas mixed vent 11 be exported to the distance 26 of downstream contracting and extending port 27 throatpistons should be less than 20d
j
The cooling of burner inner liner is adopted the air film cooling, is impacted and disperse cooling or other compound type of cooling, with control flame tube wall temperature, and prevents that combustion flame from entering in the cold gas, to reduce the generation of CO and UHC; At the burner inner liner rear portion blending hole 29 is set, control combustor exit Temperature Distribution.
In the concrete case study on implementation, the gross gas-oil ratio of establishing Combustion chamber design point is 0.03, the about 2000mm of the total air inlet effective area in combustion chamber
2According to said method, the effective area of head air inlet accounts for the about 70% of whole combustion chamber air inlet effective area, and the combustion zone equivalent proportion is 0.63, belongs to poor oil firing, in the temperature range of low pollution emission.The air inlet effective area of cold gas and mixed gas accounts for the about 30% of total effective area, cooling wall and adjust the outlet Temperature Distribution.According to proportioning, the about 1400mm of the effective area of head air inlet
2, again according to the tolerance proportioning of head pre-combustion grade and main combustion stage, main combustion stage tolerance is distributed and is accounted for 80% of whole combustion air amounts here, and drawing pre-combustion grade and main combustion stage, to divide other air inlet effective area be 280mm
2And 1120mm
2The swirler of main combustion stage and pre-combustion grade all adopts primary axis to the vane type swirler, and according to the method for designing of cyclone, the cyclone external diameter that can draw pre-combustion grade and main combustion stage is respectively at 21mm and 71mm.For pre-combustion grade, the swirl atomizer subtended angle is 80 °, relation by itself and contracting and extending port throat diameter and throatpiston and jet expansion distance, the throat diameter that can obtain the pre-combustion grade contracting and extending port is 13mm, the distance of throatpiston and swirl atomizer outlet is 7.5mm, the subtended angle of contraction mouth is 60 °, and the extension mouth subtended angle is 110 °.For main combustion stage, in the air atomizer spray nozzle, the fuel jet diameter is 0.5mm, oil gas mixed vent diameter is 2.5mm, premix gas channel height is 2mm, and oil gas mixed vent passage is long to be 4mm, and the throatpiston distance that the oil gas mixed vent is exported to the main combustion stage contracting and extending port is 30mm, the contraction angle of main combustion stage contracting and extending port is 25 °, and expansion angle is 36 °.The main combustion stage air atomizer spray nozzle is along circumferentially evenly arranging 8.Aperture on the head end wall is with equidistant arrangement, and diameter is 0.5mm, and the angle of its inclination is 26 °.
Claims (13)
1. an aerial engine lean premixed preevaporated low contamination combustion chamber is made up of head and burner inner liner, it is characterized in that: burning tolerance is all infeeded by head of combustion chamber, and cold gas and mixed gas enter from burner inner liner; Described head is the dicyclo cavity configuration, comprises pre-combustion grade that is used for flame stabilization and startup that is positioned at ring and the main combustion stage that is positioned at the high-efficient low polluting combustion that is used for most of fuel oil of outer shroud; Described pre-combustion grade comprises swirl atomizer (3) and around the cyclone (4) of swirl atomizer (3), fuel oil is subjected to the shearing-crushing from the air swirl of cyclone (4) after swirl atomizer (3) ejection, and mixing enters formation diffusion combustion in the combustion zone (30) then in pre-combustion grade hybrid chamber (6) zone; Main combustion stage is around pre-combustion grade, comprise direct-injection type air atomizer spray nozzle (15), main cyclone device (12) and premix ring cavity (13), main cyclone device (12) is positioned at the upstream of direct-injection type air atomizer spray nozzle (15) outlet, direct-injection type air atomizer spray nozzle (15) outlet downstream is premix ring cavity (13), fuel oil carries out mixed aerosol with air in advance in direct-injection type air atomizer spray nozzle (15), peripheral jet goes in the premix ring cavity (13) to carry out premix and pre-evaporation then, enters combustion zone (30) at last and forms premixed combustion; Adopt the downstream of contracting and extending port (9) and main combustion stage jet expansion to adopt contracting and extending port (27) to prevent tempering and carbon distribution in the downstream of described pre-combustion grade jet expansion.
2. aerial engine lean premixed preevaporated low contamination combustion chamber according to claim 1, it is characterized in that: the air distribution of described pre-combustion grade accounts for 5%～35% of whole burning tolerance, and the air distribution of main combustion stage accounts for 65%～95% of whole burning tolerance.
3. aerial engine lean premixed preevaporated low contamination combustion chamber according to claim 1, it is characterized in that: the outlet distance (23) of the throatpiston diameter D of described pre-combustion grade contracting and extending port (9) and this cross-sectional distance swirl atomizer (3), be L, and have relation between the spraying subtended angle α of swirl atomizer (3)
4. according to claim 1 or 4 described aerial engine lean premixed preevaporated low contamination combustion chambers, it is characterized in that: the contraction angle (21) of described pre-combustion grade contracting and extending port (9) and the scope of expansion angle (22) at 30 ° in 160 °; The contraction angle (24) of the contracting and extending port of main combustion stage (27) and the scope of expansion angle (25) also 30 ° in 160 °, the angle of contracting and extending port is relevant with the expansion angle of nozzle atomization, should correspondingly mate.
5. aerial engine lean premixed preevaporated low contamination combustion chamber according to claim 1, it is characterized in that: described main combustion stage direct-injection type air atomizer spray nozzle (15) adopts the mode of grazing incidence, and the angle of grazing incidence (16) scope is in 15 ° to 75 ° scopes.
6. according to claim 1 or 6 described aerial engine lean premixed preevaporated low contamination combustion chambers, it is characterized in that: the diameter range of the fuel jet (10) of described main combustion stage direct-injection type air atomizer spray nozzle (15) is 0.3mm-3mm; Oil gas mixed vent (11) area determines that by the ratio of the area of the area of this spout (11) and fuel jet (10) ratio of this area is less than 50.
7. according to claim 1 or 6 described aerial engine lean premixed preevaporated low contamination combustion chambers, it is characterized in that: in the described main combustion stage direct-injection type air atomizer spray nozzle (15), with the diameter d of oil gas mixed vent (11)
jAs the dimensionless linear module, the height of premix air duct (8) is less than 4d
j, the passage length (17) of fuel jet (10) is less than 6d
j, the distance (18) of fuel jet (10) and oil gas mixed vent (11) outlet is less than 10d
j
8. according to claim 1 or 6 described aerial engine lean premixed preevaporated low contamination combustion chambers, it is characterized in that: in the described main combustion stage direct-injection type air atomizer spray nozzle (15), oil gas mixed vent (11) is exported to the distance 26 of downstream contracting and extending port (27) throatpiston less than 20d
j
9. according to claim 1 or 6 described aerial engine lean premixed preevaporated low contamination combustion chambers, it is characterized in that: the quantity of described main combustion stage direct-injection type air atomizer spray nozzle (15) is at least one and even along circumferential a plurality of distributions.
10. aerial engine lean premixed preevaporated low contamination combustion chamber according to claim 1, it is characterized in that: be ring cavity around the described head fuel feed pump, and on end wall, open aperture (14), the quantity of aperture (14) and distribution are decided on the quantity of air atomizer spray nozzle (15), diameter is less than 3mm, and the interval, angle of inclination of aperture (14) is at 10 °--and 40 °.
11. aerial engine lean premixed preevaporated low contamination combustion chamber according to claim 1, it is characterized in that: the type of cooling of described combustion chamber flame drum (28) adopts the air film cooling, impacts and disperse the cooling or the compound type of cooling, so that wall surface temperature is controlled, and prevent that by control combustion flame from entering in the cooling air film to the burner inner liner flow field, to reduce the generation of CO and UHC.
12. aerial engine lean premixed preevaporated low contamination combustion chamber according to claim 1 is characterized in that: at described burner inner liner rear portion blending hole (29) is set, with control combustor exit Temperature Distribution.
13. aerial engine lean premixed preevaporated low contamination combustion chamber according to claim 1 is characterized in that: adopt radial swirler at the cyclone (4) of described pre-combustion grade and the main cyclone device (12) of main combustion stage, or axial swirler; And can adopt multistage cyclone.
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| CN101776268A (en) * | 2010-02-25 | 2010-07-14 | 华北电力大学 | Method for cooling fuel spray nozzle of combustion chamber of high-hydrogen combustion turbine |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4478045A (en) * | 1980-03-07 | 1984-10-23 | Solar Turbines Incorporated | Combustors and gas turbine engines employing same |
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2007
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