CN103123122B - The lean premixed preevaporated low contamination combustion chamber that a kind of main fuel oil directly sprays - Google Patents
The lean premixed preevaporated low contamination combustion chamber that a kind of main fuel oil directly sprays Download PDFInfo
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- CN103123122B CN103123122B CN201210589590.7A CN201210589590A CN103123122B CN 103123122 B CN103123122 B CN 103123122B CN 201210589590 A CN201210589590 A CN 201210589590A CN 103123122 B CN103123122 B CN 103123122B
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Abstract
The present invention relates to the lean premixed preevaporated low contamination combustion chamber that a kind of main fuel oil directly sprays, belong to aero-engine field, core concept of the present invention carries out air classification and fuel oil classification, it is made up of level on duty/secondary mould and main/main mould, level on duty comprises one-level axial swirler (8), secondary axial swirler (9), sleeve (10) and level on duty and receives expansion section (20), form diffusion combustion, point of safes burning things which may cause a fire disaster is provided; Main comprises main cyclone (11), main fuel feed pump (15), collection chamber (16), fuel oil direct-injection type spout (17), main receipts expansion section (12) and main premix ring cavity (22), carry out partly-premixed prevapourising poor oil firing, reduce high temperature hotspot, thus reduce thermal NO
xdischarge.Combustion chamber of the present invention has the lean premixed preevaporated combustion mode of center Idea of Classification, can while not sacrificing other performances of combustion chamber, can effectively reduce the discharge of aeroengine combustor buring chamber contamination, comprise NOx, smolders, CO and UHC.
Description
Technical field
The present invention relates to the lean premixed preevaporated low contamination combustion chamber that a kind of main fuel oil directly sprays, belong to aero engine technology field.
Background technology
At present, civil engine is increasing to the pollutant of airborne release, is also on the rise to atmosphere pollution.In order to control the impact that aircraft engine emission causes environment, civil aircraft combustion chamber emission requirement meets International Civil Aviation Organization ICAO CAEP standard, and that perform at present is CAEP6, particularly to NO
xemission request is more and more stricter.In order to meet CAEP standard, Ge great aero-engine company and research institution all carry out the research of combustion with reduced pollutants technology, GE company develops dicyclo premixed swirl (Twin Annular Premixing Swirler, TAPS) combustion technology, discharge capacity is about lower by 65% than ICAO standard in 1996; Pu Hui company adopts RQL combustion technology to develop the 3rd generation TALON III combustion chamber.
What tradition military secret main chamber adopted is diffusion combustion, and under 100% operating mode, main combustion zone oil-gas ratio is the appropriate oil-gas ratio design of chemistry, and efficiency of combustion is high, but primary zone fuel gas temperature is very high, therefore can produce a large amount of thermal NO x; And when slow train operating mode, efficiency of combustion is low, incomplete combustion, therefore pollutant CO and UHC generates many.Therefore, conventional diffusion burn mode is difficult to reach current or low pollution emission requirement in the future.At present, lean premixed preevaporated low contamination combustion system is mainly adopted in the civil engine combustion chamber of grinding, most crucial thought carries out classification to air and fuel oil, air enters head of combustion chamber from main/main mould and level on duty/secondary mould respectively, level on duty generally adopts low discharge pressure atomized fog jet to carry out diffusion combustion mode, and main generally carries out partly-premixed burning, thus realizes the lean premixed preevaporated burning in combustion chamber, due to main-stage combustion homogeneous temperature, thus reduce pollutant NO
xdischarge.
Summary of the invention
The present invention is directed to the deficiency of the problems referred to above, the lean premixed preevaporated low contamination combustion chamber that a kind of main fuel oil directly sprays is proposed, this combustion chamber, under the performance condition meeting aero-engine, can effectively reduce the discharge of aeroengine combustor buring chamber contamination, comprise NOx, smolders, CO and UHC.
The present invention is the technical scheme solving the problems of the technologies described above proposition: the lean premixed preevaporated low contamination combustion chamber that a kind of main fuel oil directly sprays, comprise head of combustion chamber, burner inner liner, combustion chamber inner ring channel (25), combustion chamber outer ring channel (24), Fuel Injector Bar (21) and casing, Fuel Injector Bar (21) is arranged on casing (6), head of combustion chamber is connected with casing by Fuel Injector Bar (21), and head of combustion chamber, combustion chamber inner ring channel (25) and combustion chamber outer ring channel (24) design by assignment of traffic rule, described Fuel Injector Bar (21) is provided with two oil line pipes of level swirl atomizer (7) on duty and main fuel feed pump (15), described head of combustion chamber is circular dicyclo cavity configuration, be divided into level on duty/secondary mould (1) and main/main mould (2) two parts, and described main (2) is looped around the outer shroud of level on duty (1), described level on duty comprises one-level axial swirler (8), secondary axial swirler (9), sleeve (10) and level on duty are received and are expanded section (20), one-level axial swirler (8) and secondary axial swirler (9) rotation direction can identical also can be contrary, described one-level axial swirler (8) is looped around swirl atomizer (7) outside, and secondary axial swirler (9) is looped around the outside of one-level axial swirler (8), between described one-level axial swirler (8) and secondary axial swirler (9), connection value class receives and expands section (20), and level on duty receives the exit that expansion section (20) is positioned at one-level axial swirler (8), and sleeve (10) is arranged on the outside of secondary axial swirler (9), main comprises main cyclone (11), main fuel feed pump (15), collection chamber (16), fuel oil direct-injection type spout (17), main is received and is expanded section (12) and main premix ring cavity (22), described main cyclone (11) is looped around the outside of sleeve (10), and Fuel Injector Bar (21), main fuel feed pump (15), collection chamber (16), fuel oil direct-injection type spout (17), main cyclone (11), main premix ring cavity (22) connects successively, and fuel oil direct-injection type spout 17 is arranged in the blade path of main cyclone 11, described main is received and is expanded the outlet that section (12) is arranged on main premix ring cavity (22) simultaneously.
Further: between described main and level on duty, be provided with head inner ring cooling package (3), head inner ring cooling aperture (18) of air on head inner ring cooling package (3) enters, and carries out impinging cooling to head inner ring shelves splash basin (19); And between described main and burner inner liner, be provided with head outer shroud cooling package (4), head outer shroud cooling aperture (13) of air on head outer shroud cooling package (4) enters, and carries out impinging cooling to head outer shroud shelves splash basin (14).
Preferred: the blade of described one-level axial swirler (8), level on duty receives the blade of expansion section and secondary axial swirler (9) by overall machining, the mode such as monoblock cast or welding is processed to form, sleeve (10) welds with level shelves splash basin (19) on duty and head inner ring cooling package (3) and is connected, head inner ring cooling package (3) is connected with main (2) by welding or is connected by bolt, main (2) is welded to each other with head outer shroud cooling package (4) or bolt is connected, main collection chamber and main (2) can by weld or bolt is interconnected.
Preferred: the distributed quantity of described fuel oil direct-injection type spout (17) on annulus is 6 ~ 36.
Preferred: the eddy flow angle of described level one-level axial swirler (8) on duty is 20 ° ~ 45 °, the lobe numbers of one-level axial swirler (8) is 8 ~ 16, and the rotation direction of one-level axial swirler (8) blade can be clockwise or counterclockwise along airflow direction, contrary with spraying rotation direction in principle; Described level secondary axial swirler (9) blade angle on duty is 25 ° ~ 45 °, and lobe numbers is 8 ~ 20; Secondary axial swirler (9) vane cyclone setting angle is contrary or identical with one-level axial swirler (8) vane cyclone setting angle.
Preferred: the expansion angle of described sleeve (10) is 8 ° ~ 20 °.
Preferred: described main cyclone (11) is radial swirler or axial swirler; Described radial swirler blade angle is 40 ° ~ 60 °, and lobe numbers is 12 ~ 40; Described axial swirler blade angle is 30 ° ~ 70 °, and lobe numbers is 6 ~ 48.
Preferred: the air capacity of described head of combustion chamber accounts for 50% ~ 85% of combustion chamber total air, and wherein main combustion stage accounts for 60% ~ 90% of head air capacity, and pre-combustion grade accounts for 10% ~ 40% of head air capacity.
Preferred: the cooling of described burner inner liner (5) adopts all standing gaseous film control, impacts and disperse cooling or other Compound cooling mode, and described burner inner liner rear portion is furnished with multiple blending hole according to actual needs.
The course of work of the present invention:
After entering combustion chamber from the air of high-pressure compressor from diffuser (23), divide three tunnels to enter combustion chamber inner ring channel (25), head of combustion chamber and combustion chamber outer ring channel (24) respectively afterwards, the air of inner and outer rings passage enters burner inner liner from the blending hole burner inner liner (5) and film cooling holes respectively.In combustion chamber, burning use gas major part feeds from head, and other all feeds from burner inner liner with gas.And head of combustion chamber comprises level on duty (1) and main (2).In level on duty (1), fuel oil (accounting for 5% ~ 50% of total fuel oil) sprays through swirl atomizer (7) and carries out primary atomization, the shock be subject to from one-level axial swirler (8) air-flow be looped around around it is broken, form secondary-atomizing, then level receipts expansion section (20) outlet on duty carries out three atomizations by the shearing-crushing of one-level axial swirler (8) and secondary axial swirler (9) exit flow, gas mixture after blending enters combustor primary zone and carries out part diffusion combustion, forms point of safes burning things which may cause a fire disaster, for main, fuel oil (accounting for 50% ~ 95% of total fuel oil) enters main collection chamber (16) from fuel feed pump (15), spray through main fuel oil direct projection spout (17) respectively again, main fuel oil direct-injection type spout spray angle and axial location can be regulated, regulate main fuel-oil atmozation situation, because main fuel oil direct-injection type spout (17) is arranged in main blade path, and due to fuel oil injection direction and primary air flow direction mutually vertical or relative, fuel oil is under main Aerodynamic force action, realize broken, atomization, enter main premix ring cavity (22) afterwards, fuel oil and air continue to enter combustion zone after mixed assembling section evaporates in premix ring cavity (22), form lean premixed burning.
The lean premixed preevaporated low contamination combustion chamber that a kind of main fuel oil of the present invention directly sprays, compared to existing technology, has following beneficial effect:
1., because level on duty is made up of one-level or two-stage (comprise in the same way or oppositely) axial swirler and pressure atomized fog jet, form diffusion flame, therefore, it is possible to provide point of safes burning things which may cause a fire disaster, take into account igniting/extinguishment characteristics and slow train operating mode efficiency of combustion problem.
2. because main is made up of a radial swirler or axial swirler, cavity and the direct spray-hole of multiple fuel oil, thus carry out partly-premixed prevapourising homogenous combustion, reduce high temperature hotspot, thus NO under reducing large operating mode
x,smolder, CO and UHC discharge, simultaneously and the main fuel-oil atmozation mode structure of the type is simple.
3. because main combustion stage air inlet accounts for about 40% ~ 70% of whole diffuser air inlet, and fuel oil accounts for 50% ~ 95% of total fuel oil, and carry out partly-premixed prevapourising in the cavities, therefore premix and pre-evaporation burning is substantially realized, reduce pollutant emission, level on duty provides reliable and stable incendiary source simultaneously.
4. owing to being provided with, level on duty receives expansion section (20), main is received and expanded section (12), thus effectively prevents lean premixed preevaporated aflame tempering, nozzle deposit carbon problem.
5. because head inner ring cooling aperture (18) of air on head inner ring cooling package (3) enters, impinging cooling is carried out to head inner ring shelves splash basin (19), head outer shroud cooling aperture (13) of air on head outer shroud cooling package (4) enters simultaneously, impinging cooling is carried out to head outer shroud shelves splash basin (14), thus the service life of prolonging combustion room head.
6. because the cooling of burner inner liner (5) adopts all standing gaseous film control, impacts and disperse cooling or other Compound cooling mode, thus control flame tube wall surface temperature, thus extend burner inner liner service life; Blending hole is arranged according to actual needs at burner inner liner rear portion, thus control combustion room Exit temperature distribution.
Accompanying drawing explanation
Fig. 1 is the structural representation of the embodiment of the present invention;
Fig. 2 is the head of combustion chamber schematic enlarged-scale view of Fig. 1;
Wherein: 1. level on duty/secondary mould, 2. main/main mould, 3. head inner ring cooling package, 4. head outer shroud cooling package, 5. burner inner liner, 6. casing, 7. on duty grade of swirl atomizer, 8. one-level axial swirler, 9. secondary axial swirler, 10. sleeve, 11. main cyclones, 12. mains are received and are expanded section, 13. head outer shroud cooling apertures, 14. head outer shroud shelves splash basins, 15. main fuel feed pumps, 16. collection chambers, 17. fuel oil direct-injection type spouts, 18. head inner ring cooling apertures, 19. head inner ring shelves splash basins, 20. levels on duty are received and are expanded section, 21. Fuel Injector Bars, 22. main premix ring cavities, 23. diffusers, 24. combustion chamber outer ring channels, 25. combustion chamber inner ring channel.
Detailed description of the invention
Accompanying drawing discloses the structural representation of a preferred embodiment of the invention without limitation, explains technical scheme of the present invention below with reference to accompanying drawing.
Embodiment
The lean premixed preevaporated low contamination combustion chamber that a kind of main fuel oil of the present embodiment directly sprays is as Fig. 1, shown in 2, comprise head of combustion chamber, burner inner liner 5, combustion chamber inner ring channel 25, combustion chamber outer ring channel 24, Fuel Injector Bar 21 and casing, Fuel Injector Bar 21 is arranged on casing 6, be head of combustion chamber fuel feeding on the one hand, bear a part of mechanical force on the other hand, head of combustion chamber is connected with casing 6 by Fuel Injector Bar 21, and head of combustion chamber, combustion chamber inner ring channel 25 and combustion chamber outer ring channel 24 are by the design of assignment of traffic rule, in, the air of outer ring channel enters burner inner liner from the blending hole burner inner liner 5 and film cooling holes respectively, described Fuel Injector Bar 21 is provided with two oil line pipes of level swirl atomizer 7 on duty and main fuel feed pump 15, described head of combustion chamber is circular dicyclo cavity configuration, be divided into level on duty/secondary mould 1 and main/main mould 2 two parts, and described main 2 is looped around the outer shroud of level 1 on duty, described level on duty comprises one-level axial swirler 8, secondary axial swirler 9, sleeve 10 and level on duty are received and are expanded section 20, one-level axial swirler 8 and secondary axial swirler 9 rotation direction can identical also can be contrary, described one-level axial swirler 8 is looped around outside level swirl atomizer 7 on duty, and secondary axial swirler 9 is looped around the outside of one-level axial swirler 8, between described one-level axial swirler 8 and secondary axial swirler 9, connection value class receives and expands section 20, and level on duty receives the exit that expansion section 20 is positioned at one-level axial swirler 8, level on duty is received expansion section 20 and is equivalent to Venturi tube, the design of its contraction section angle and expansion segment angle is all very important, effectively can prevent tempering, nozzle deposit carbon, and sleeve 10 is arranged on the outside of secondary axial swirler 9, main comprises main cyclone 11, main fuel feed pump 15, collection chamber 16, fuel oil direct-injection type spout 17, main receipts expansion section 12 and main premix ring cavity 22, described main cyclone 11 is looped around the outside of sleeve 10, and Fuel Injector Bar 21, main fuel feed pump 15, collection chamber 16, fuel oil direct-injection type spout 17, main cyclone 11, main premix ring cavity 22 connect successively, and fuel oil direct-injection type spout 17 is arranged in the blade path of main cyclone 11, described main is received and is expanded the outlet that section 12 is arranged on main premix ring cavity 22 simultaneously.
Be provided with head inner ring cooling package 3 between described main 2 and level on duty 1, the head inner ring cooling aperture 18 of air on head inner ring cooling package 3 enters, and carries out impinging cooling to head inner ring shelves splash basin 19; And between described main and burner inner liner, being provided with head outer shroud cooling package 4, the head outer shroud cooling aperture 13 of air on head outer shroud cooling package 4 enters, and carries out impinging cooling to head outer shroud shelves splash basin 14.
The blade of described one-level axial swirler 8, level on duty are received the blade that expands section and secondary axial swirler 9 and are processed to form by overall machining, monoblock cast or the mode such as to weld, sleeve 10 welds with level shelves splash basin 19 on duty and head inner ring cooling package 3 and is connected, head inner ring cooling package 3 is connected with main 2 by welding or is connected by bolt, main 2 is welded to each other with head outer shroud cooling package 4 or bolt is connected, and main collection chamber and main 2 can by weld or bolt is interconnected.
Distributed quantity, spray angle and the axial distance of described fuel oil direct-injection type spout 17 on annulus can be determined according to required duty and main lobe numbers, the distributed quantity of described fuel oil direct-injection type spout 17 on annulus is 6 ~ 36, the spray angle of fuel oil direct-injection type spout 17 between-45 ° ~ 45 °, to make the air-fuel mixture in main premix chamber 22 more even; And different according to operating mode, the number that fuel oil direct-injection type spout 17 is opened can control.
The eddy flow angle of described level one-level axial swirler 8 on duty is 20 ° ~ 45 °, the lobe numbers of one-level axial swirler 8 is 8 ~ 16, specifically determine according to actual conditions, the rotation direction of one-level axial swirler 8 blade can be clockwise or counterclockwise along airflow direction, contrary with spraying rotation direction in principle; Described level secondary axial swirler 9 blade angle on duty is 25 ° ~ 45 °, and lobe numbers is 8 ~ 20; Secondary axial swirler 9 vane cyclone setting angle is contrary or identical with one-level axial swirler 8 vane cyclone setting angle.
The expansion angle of described sleeve 10 is 8 ° ~ 20 °.
Described main cyclone 11 is radial swirler or axial swirler; Described radial swirler blade angle is 40 ° ~ 60 °, and lobe numbers is 12 ~ 40; Described axial swirler blade angle is 30 ° ~ 70 °, and lobe numbers is 6 ~ 48.
The air capacity of described head of combustion chamber accounts for 50% ~ 85% of combustion chamber total air, and wherein main combustion stage accounts for 60% ~ 90% of head air capacity, and pre-combustion grade accounts for 10% ~ 40% of head air capacity.
The cooling of described burner inner liner 5 adopts all standing gaseous film control, impacts and disperse cooling or other Compound cooling mode, thus can control flame tube wall surface temperature, thus extends burner inner liner service life; Described burner inner liner rear portion is furnished with multiple blending hole according to actual needs, thus control combustion room Exit temperature distribution.
The course of work of the present invention:
After entering combustion chamber from the air of high-pressure compressor from diffuser 23, divide three tunnels to enter combustion chamber inner ring channel 25, head of combustion chamber and combustion chamber outer ring channel 24 respectively afterwards, the air of inner and outer rings passage enters burner inner liner from the blending hole burner inner liner 5 and film cooling holes respectively.In combustion chamber, burning use gas major part feeds from head, and other all feeds from burner inner liner with gas, and head of combustion chamber comprises level 1 on duty and main 2.In level 1 on duty, fuel oil (accounting for 5% ~ 50% of total fuel oil) sprays through swirl atomizer 7 and carries out primary atomization, the shock be subject to from one-level axial swirler 8 air-flow be looped around around it is broken, form secondary-atomizing, then the shearing-crushing that level receipts expansion section 20 on duty exports by one-level axial swirler 8 and secondary axial swirler 9 exit flow carries out three atomizations, gas mixture after blending enters combustor primary zone and carries out part diffusion combustion, forms point of safes burning things which may cause a fire disaster, for main, fuel oil (accounting for 50% ~ 95% of total fuel oil) enters main collection chamber 16 from fuel feed pump 15, spray through main fuel oil direct projection spout 17 respectively again, main fuel oil direct-injection type spout spray angle and axial location can be regulated, regulate main fuel-oil atmozation situation, because main fuel oil direct-injection type spout 17 is arranged in the blade path of main cyclone 11, and due to fuel oil injection direction and primary air flow direction mutually vertical or relative, fuel oil is under main Aerodynamic force action, realize broken, atomization, enter main premix ring cavity 22 afterwards, fuel oil and air continue to enter combustion zone after mixed assembling section evaporates in premix ring cavity 22, form lean premixed burning.
The preferred specific embodiment of the present invention described by reference to the accompanying drawings is above only for illustration of embodiments of the present invention; instead of as the restriction to aforementioned invention object and claims content and scope; every according to technical spirit of the present invention to any simple modification made for any of the above embodiments, equivalent variations and modification, all still belong to the technology of the present invention and rights protection category.
Claims (8)
1. the lean premixed preevaporated low contamination combustion chamber that directly sprays of a main fuel oil, comprise head of combustion chamber, burner inner liner, combustion chamber inner ring channel (25), combustion chamber outer ring channel (24), Fuel Injector Bar (21) and casing, Fuel Injector Bar (21) is arranged on casing (6), head of combustion chamber is connected with casing by Fuel Injector Bar (21), and head of combustion chamber, combustion chamber inner ring channel (25) and combustion chamber outer ring channel (24) design by air mass flow Distribution dynamics, described Fuel Injector Bar (21) is provided with two oil line pipes of level swirl atomizer (7) on duty and main fuel feed pump (15), it is characterized in that: described head of combustion chamber is circular dicyclo cavity configuration, be divided into level on duty/secondary mould (1) and main/main mould (2) two parts, and described main (2) is looped around the outer shroud of level on duty (1), described level on duty comprises one-level axial swirler (8), secondary axial swirler (9), sleeve (10) and level on duty are received and are expanded section (20), one-level axial swirler (8) and secondary axial swirler (9) rotation direction can identical also can be contrary, described one-level axial swirler (8) is looped around swirl atomizer (7) outside, and secondary axial swirler (9) is looped around the outside of one-level axial swirler (8), between described one-level axial swirler (8) and secondary axial swirler (9), connection value class receives and expands section (20), and level on duty receives the exit that expansion section (20) is positioned at one-level axial swirler (8), and sleeve (10) is arranged on the outside of secondary axial swirler (9), main comprises main cyclone (11), main fuel feed pump (15), collection chamber (16), fuel oil direct-injection type spout (17), main is received and is expanded section (12) and main premix ring cavity (22), described main cyclone (11) is looped around the outside of sleeve (10), and Fuel Injector Bar (21), main fuel feed pump (15), collection chamber (16), fuel oil direct-injection type spout (17), main cyclone (11), main premix ring cavity (22) connects successively, and fuel oil direct-injection type spout 17 is arranged in the blade path of main cyclone 11, described main is received and is expanded the outlet that section (12) is arranged on main premix ring cavity (22) simultaneously, head inner ring cooling package (3) is provided with between described main and level on duty, head inner ring cooling aperture (18) of air on head inner ring cooling package (3) enters, and carries out impinging cooling to head inner ring shelves splash basin (19), and between described main and burner inner liner, be provided with head outer shroud cooling package (4), head outer shroud cooling aperture (13) of air on head outer shroud cooling package (4) enters, and carries out impinging cooling to head outer shroud shelves splash basin (14).
2. the lean premixed preevaporated low contamination combustion chamber that directly sprays of main fuel oil according to claim 1, it is characterized in that: the blade of described one-level axial swirler (8), level on duty receives the blade of expansion section and secondary axial swirler (9) by overall machining, the mode such as monoblock cast or welding is processed to form, sleeve (10) is weldingly connected with level shelves splash basin (19) on duty and head inner ring cooling package (3), head inner ring cooling package (3) and main (2) are by being weldingly connected or being connected by bolt, main (2) is welded to each other with head outer shroud cooling package (4) or bolt is connected, main collection chamber and main (2) can by weld or bolt is interconnected.
3. the lean premixed preevaporated low contamination combustion chamber that directly sprays of main fuel oil according to claim 2, is characterized in that: the distributed quantity of described fuel oil direct-injection type spout (17) on annulus is 6 ~ 36.
4. the lean premixed preevaporated low contamination combustion chamber that directly sprays of main fuel oil according to claim 3, it is characterized in that: the eddy flow angle of described level one-level axial swirler (8) on duty is 20 ° ~ 45 °, the lobe numbers of one-level axial swirler (8) is 8 ~ 16, and the rotation direction of one-level axial swirler (8) blade is clockwise along airflow direction or counterclockwise, rotation direction is contrary with spraying; Described level secondary axial swirler (9) blade angle on duty is 25 ° ~ 45 °, and lobe numbers is 8 ~ 20; Secondary axial swirler (9) vane cyclone setting angle is contrary or identical with one-level axial swirler (8) vane cyclone setting angle.
5. the lean premixed preevaporated low contamination combustion chamber that directly sprays of main fuel oil according to claim 4, is characterized in that: the expansion angle of described sleeve (10) is 8 ° ~ 20 °.
6. the lean premixed preevaporated low contamination combustion chamber that directly sprays of main fuel oil according to claim 5, is characterized in that: described main cyclone (11) is radial swirler or axial swirler; Described radial swirler blade angle is 40 ° ~ 60 °, and lobe numbers is 12 ~ 40; Described axial swirler blade angle is 30 ° ~ 70 °, and lobe numbers is 6 ~ 48.
7. the lean premixed preevaporated low contamination combustion chamber that directly sprays of main fuel oil according to claim 6, it is characterized in that: the air capacity of described head of combustion chamber accounts for 50% ~ 85% of combustion chamber total air, wherein main accounts for 60% ~ 90% of head air capacity, and level on duty accounts for 10% ~ 40% of head air capacity.
8. the lean premixed preevaporated low contamination combustion chamber that directly sprays of main fuel oil according to claim 7, it is characterized in that: the cooling of described burner inner liner (5) adopts all standing gaseous film control, impacts and disperse cooling or other Compound cooling mode, and described burner inner liner rear portion is furnished with multiple blending hole according to actual needs.
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| CN201210589590.7A CN103123122B (en) | 2012-12-31 | 2012-12-31 | The lean premixed preevaporated low contamination combustion chamber that a kind of main fuel oil directly sprays |
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| CN201210589590.7A CN103123122B (en) | 2012-12-31 | 2012-12-31 | The lean premixed preevaporated low contamination combustion chamber that a kind of main fuel oil directly sprays |
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| CN113864823B (en) * | 2021-11-09 | 2022-08-26 | 滨州学院 | Turbine engine cyclic heating multistage combustion system |
| CN114738799B (en) * | 2022-04-20 | 2024-03-26 | 新奥能源动力科技（上海）有限公司 | Head assembly of dual-fuel combustion chamber, combustion chamber and gas turbine |
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