CN100543371C - A low-pollution combustion chamber with liquid mist injection premixed pre-evaporation in the turning area of radial swirler - Google Patents
A low-pollution combustion chamber with liquid mist injection premixed pre-evaporation in the turning area of radial swirler Download PDFInfo
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- CN100543371C CN100543371C CNB2008101050619A CN200810105061A CN100543371C CN 100543371 C CN100543371 C CN 100543371C CN B2008101050619 A CNB2008101050619 A CN B2008101050619A CN 200810105061 A CN200810105061 A CN 200810105061A CN 100543371 C CN100543371 C CN 100543371C
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 302
- 238000002347 injection Methods 0.000 title claims abstract description 38
- 239000007924 injection Substances 0.000 title claims abstract description 38
- 239000003595 mist Substances 0.000 title claims abstract description 28
- 239000007788 liquid Substances 0.000 title claims abstract description 27
- 238000001704 evaporation Methods 0.000 title claims abstract description 10
- 230000008020 evaporation Effects 0.000 title claims abstract description 10
- 239000000295 fuel oil Substances 0.000 claims abstract description 46
- 238000002156 mixing Methods 0.000 claims abstract description 22
- 239000000203 mixture Substances 0.000 claims abstract description 17
- 230000000694 effects Effects 0.000 claims abstract description 6
- 239000007921 spray Substances 0.000 claims description 64
- 239000003921 oil Substances 0.000 claims description 15
- 238000001816 cooling Methods 0.000 claims description 5
- 230000008602 contraction Effects 0.000 claims description 4
- 230000009977 dual effect Effects 0.000 claims description 3
- 239000003344 environmental pollutant Substances 0.000 abstract description 22
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- 238000010586 diagram Methods 0.000 description 16
- 239000000446 fuel Substances 0.000 description 10
- 238000010276 construction Methods 0.000 description 9
- 208000034953 Twin anemia-polycythemia sequence Diseases 0.000 description 4
- 230000004323 axial length Effects 0.000 description 4
- 238000009792 diffusion process Methods 0.000 description 4
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 2
- 229910052799 carbon Inorganic materials 0.000 description 2
- 230000007812 deficiency Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 230000001105 regulatory effect Effects 0.000 description 2
- 238000005496 tempering Methods 0.000 description 2
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 description 1
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- 150000001875 compounds Chemical class 0.000 description 1
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- 239000001257 hydrogen Substances 0.000 description 1
- 229910052739 hydrogen Inorganic materials 0.000 description 1
- 239000010761 intermediate fuel oil Substances 0.000 description 1
- JTJMJGYZQZDUJJ-UHFFFAOYSA-N phencyclidine Chemical class C1CCCCN1C1(C=2C=CC=CC=2)CCCCC1 JTJMJGYZQZDUJJ-UHFFFAOYSA-N 0.000 description 1
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Abstract
A kind of radial swirler turning zone liquid and mist injection premixing and prevapourising low pollution combustor, combustion chamber are the monocycle cavity configuration, are made up of head of combustion chamber and burner inner liner, and wherein head of combustion chamber comprises the pre-combustion grade that is positioned at the center and the main combustion stage of outer ring; Adopt behind the main combustion stage radial swirler, turn round liquid mist jet scheme in the district of main combustion stage fuel oil, the main combustion stage fuel oil was pre-mixed with air before spraying into the district of turning round, be injected to gas mixture in the district of turning round after the mixing again and form the premix and pre-evaporation gas mixture enter into the combustion zone and burn under the effect of main combustion stage radial swirler rotational flow gas, this combustion system can effectively reduce the discharging of combustion chamber pollutant; Behind the main combustion stage radial swirler, turn round the liquid mist jet in the district and the mobile length that can reduce the combustion chamber of turning round in the district of turning round of main combustion stage fuel oil simultaneously; The present invention is mainly used in the aeroengine combustor buring chamber, also can be used in industry gas turbine and the naval vessel gas-turbine combustion chamber, to reduce the pollutant of row in atmosphere.
Description
Technical field
The present invention relates to a kind of aeroengine combustor buring chamber technology, particularly a kind of radial swirler turning zone liquid and mist injection premixing and prevapourising low pollution combustor.
Background technology
The main development trend of aeroengine combustor buring is combustion with reduced pollutants, and the aero-engine emission standard of increasingly stringent must be satisfied in the aeroengine combustor buring chamber.The requirement of CAEP4 (the Committee on Aviation EnvironmentalProtection) standard that adopts at present is very strict, and is particularly to the NOx emission requirement, after 2008 that the CAEP6 standard that adopts is then more strict.The emission requirement of industry gas turbine reaches units---the requirement of ten thousand/concentration discharge.
In general, the aero-engine pollutant can be divided into two classes: because the pollutant that high flame temperature produces is nitrogen oxide (NOx); Because the pollutant that low flame temperature produces is carbon monoxide and unburned carbon hydrogen (CO and UHC).Mechanism that produces according to pollutant and experimental result as can be known, combustion chambers burn district equivalent proportion is in a very little scope (0.6～0.8), above-mentioned two big pollutants dischargings reach minimum.For conventional combustion chamber, when high power state, owing to adopt liquid mist diffusion combustion mode, the local equivalent proportion in combustion zone is always near 1, far away from the required equivalent proportion area requirement of above-mentioned combustion with reduced pollutants, so the discharging of CO and UHC is little, maximum but the discharging of NOx reaches.When low power state, the combustion zone equivalent proportion is very low again, far below the required equivalent proportion of above-mentioned combustion with reduced pollutants interval, the NOx discharging is low, but CO and UHC discharging are very high again, therefore for conventional combustion chamber, can't satisfy the low pollution requirement in whole engine operation scope.
GE engine company has proposed a kind of low pollution combustor-TAPS (Twin Annular Premixing Swirler), and head of combustion chamber comprises main combustion stage and pre-combustion grade, and main combustion stage and pre-combustion grade be fuel feeding respectively, realizes the subregion combustion system.According to this thinking, GE company has applied for several United States Patent (USP)s.Application number is respectively the main combustion stage scheme that 6389815,6354072,0178732 and 6381964 United States Patent (USP) proposes: the main combustion stage fuel oil is injected to turn round a certain position after the district of radial swirler, forms the premix and pre-evaporation gas mixture.From the accompanying drawing of these patents as can be known, the fuel oil spray site approximately is half of head of combustion chamber structure height to porch, combustion zone distance, for this fractional combustion chamber, the head construction height is greater than the head construction height of conventional combustion chamber, therefore the axial length of head of combustion chamber is oversize, thereby influences the length and the weight requirement of combustion chamber and even engine.At application number is to have this problem in 6453660 United States Patent (USP)s equally, the fuel oil spray site is 1/3rd of a head of combustion chamber structure height approximately to porch, combustion zone distance, and the main combustion stage fuel injection system is very complicated, causes the head of combustion chamber structure very complicated.Above-mentioned several United States Patent (USP) has all been realized the low pollution requirement in the whole engine operation scope, but main combustion stage fuel oil spray site all has a segment distance from the radial swirler outlet, and this segment distance has increased the head of combustion chamber axial length.Above-mentioned in addition United States Patent (USP) is just regulated the swirl strength of air by cyclone, and does not take measures to control the initial swirl strength of fuel oil.
Summary of the invention
The technical problem to be solved in the present invention is: overcome above-mentioned the deficiencies in the prior art, overcome above-mentioned the deficiencies in the prior art, the interior fuel oil liquid mist jet in district turns round behind the employing radial swirler, adopt the oil gas of fuel oil before entering the district of turning round to be pre-mixed and the district of turning round in the turn round type of flow of gas mixture behind radial swirler, reduce the distance that the fuel oil spray site enters the mouth to the combustion zone, thereby reduce the axial length of head of combustion chamber structure, can effectively reduce the combustion chamber disposal of pollutants simultaneously.
The technical solution adopted for the present invention to solve the technical problems is: a kind of radial swirler turning zone liquid and mist injection premixing and prevapourising low pollution combustor, form by head of combustion chamber 26 and burner inner liner, it is characterized in that: the combustion chamber is the monocycle cavity configuration, and head of combustion chamber 26 comprises the pre-combustion grade 24 that is positioned at the center and the main combustion stage 25 of outer ring; Main combustion stage 25 includes direct-injection type air atomizer spray nozzle 33 and main combustion stage radial swirler 34 again; The main combustion stage fuel oil 41 of direct-injection type air atomizer spray nozzle 33 ejections enters in the main combustion stage collection chamber 42 through main combustion stage fuel oil spray site 38; Main combustion stage direct-injection type air materialization nozzle air stream 39 also enters into collection chamber 42 simultaneously, oil gas is pre-mixed in collection chamber 42, mixed gas mixture is injected to the district 36 of turning round behind the main combustion stage radial swirler behind the main combustion stage radial swirler blade 37 in the hole from main combustion stage radial swirler left side wall 43 with the form of liquid mist again, under the rotational flow gas effect of main combustion stage radial swirler 34, form the premix and pre-evaporation gas mixture and enter into combustion zone 16 burnings, realize the radial swirler turning zone liquid and mist injection premixing and prevapourising combustion scheme.
Described main combustion stage direct-injection type air materialization nozzle air stream 39 can or be combined into collection chamber 42 by main combustion stage air atomizer spray nozzle air groove 47 or above-mentioned dual mode by main combustion stage air atomizer spray nozzle airport 46.
The swirl strength of the air of described direct-injection type air materialization nozzle air stream 39 ejections can be controlled by the angle of adjusting main combustion stage air atomizer spray nozzle airport 46 or main combustion stage air atomizer spray nozzle air groove 47.
The spray site 38 of the direct-injection type air atomizer spray nozzle 33 of described main combustion stage 25 is positioned on the main combustion stage radial swirler left side wall 43, and spray site 38 quantity are identical with main combustion stage radial swirler blade 37 quantity.
Described main combustion stage fuel oil spray site to the porch, combustion zone apart from the relation between 49x and the head of combustion chamber structure height 48y is:
The tolerance of described main combustion stage 25 accounts for 65%～95% of head of combustion chamber tolerance, and the tolerance of pre-combustion grade 24 accounts for 5%～35%.
Described burning gas consumption all infeeds from head of combustion chamber 26, does not have primary holes on the burner inner liner, has only cooling hole, outer blending hole 21 and interior blending hole 22.
It is adjustable in 0 ° to 180 ° that described main combustion stage is received expansion part contraction angle 45.
Operation principle of the present invention: the main combustion stage fuel oil be injected to turn round the district before with the rotational flow air premix, the gas mixture of this premix is ejected in the district of turning round behind the main combustion stage radial swirler blade again, the air-flow that turns round in distinguishing turns to further reinforcement oil gas to mix, this mixture enters into the primary zone and burns after forming the premix and pre-evaporation state under the effect of main combustion stage radial swirler rotational flow gas, form the premixed combustion mode.Can enter the district's rotational flow air swirl strength before that turns round by control simultaneously and control the swirl strength that entering liquid mist in the district of turning round, thereby adapt to different engine operating condition requirements.Pre-combustion grade adopts swirl atomizer and hydrocyclone structure, forms diffusion combustion mode, takes into account the performance requirement of flameholding and two contradictions of disposal of pollutants.This combustion system can be controlled the equivalent proportion of combustion chamber under different conditions, and this equivalent proportion is remained in the interval of low pollution emission, thereby helps controlling disposal of pollutants.Do not have primary holes on the combustion chamber flame drum, have only cooling hole and blending hole, the burning gas consumption all enters from head of combustion chamber.Main combustion stage and pre-combustion grade keep suitable tolerance to distribute, to adapt to different engine chamber working condition requirements.Control cooling air flows, and avoids producing too much CO and UHC.
Pre-combustion grade starts under low power 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 low power state, makes the good stability of burning, easily starting.When engine operation just starts main combustion stage during at high power state, the equivalent proportion of control combustion zone is in above-mentioned combustion with reduced pollutants equivalent proportion interval, and main combustion stage is the premix and pre-evaporation pattern, can guarantee the uniformity of local equivalent proportion in the combustion zone.Adopt this low pollution combustor head construction, can guarantee under all duties in aeroengine combustor buring chamber, the equivalent proportion of combustion zone is controlled in the interval of combustion with reduced pollutants, control the equivalent proportion uniformity of combustion zone simultaneously by the control main combustion stage mist of oil uniformity, degree of mixing and evaporativity, thereby it is low to reach disposal of pollutants, aeroengine combustor buring chamber performance requirements such as good stability.
Under a certain parameter (inlet velocity and temperature, pressure etc.) condition, fuel oil reaches that needed distance definition is L under a certain degree of mixing, consider from the disposal of pollutants angle, this length is the bigger the better, but consider that from tempering and spontaneous combustion angle this length again should not be too big, during therefore corresponding to a certain parameter, take all factors into consideration above-mentioned two factors, this length should be a definite value.For TAPS main combustion stage radial swirler scheme, the length of main combustion stage fuel oil spray site when fuel oil reaches a certain degree of mixing is L, and cyclone exports to the distance of spray site is Lsi, cyclone length is Ls, and the length when reaching a certain degree of mixing like this from the cyclone inlets to the fuel oil is L+Lsi+Ls.The present invention adopts radial swirler turning zone liquid and mist injection premixing and prevapourising combustion scheme scheme, length when reaching identical degree of mixing is Ls+L, removed the distance L si that cyclone exports to spray site, shortened the length of head of combustion chamber, in addition because fuel oil being pre-mixed before being injected to the district of turning round, further reduce the length of head of combustion chamber, thereby reduced the length and the weight of combustion chamber.Strengthen blending owing to the district's air-flow that turns round turns to simultaneously, mix thereby help main combustion stage oil gas.
The present invention's advantage compared with prior art is as follows:
1. the main combustion stage fuel oil of the present invention liquid mist jet in the district that behind radial swirler, turns round, when reaching identical degree of mixing and evaporativity, the distance shortening that needs, thus reduced the length of combustion chamber;
2. turn round behind the main combustion stage radial swirler of the present invention gas mixture in the district, because turning round of radial swirler downstream is mobile, when reaching identical degree of mixing and evaporativity, the distance that needs further shortens, thereby further reduces the length of combustion chamber;
3. the liquid mist jet that main combustion stage fuel oil of the present invention turns round behind cyclone and distinguishes is further strengthened blending owing to turn round turning to of air-flow of district, helps main combustion stage oil gas and mixes;
4. spray into the swirl strength of district's intermediate fuel oil that turns round by the air swirl strength control of adjusting and main combustion stage air atomizer spray nozzle fuel oil is pre-mixed, thereby adapt to Under Different Work Condition of Engine;
5. combustion chambers burn tolerance of the present invention 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;
6. the compound combustion mode of pre-combustion grade diffusion combustion of the present invention and the burning of main combustion stage premix and pre-evaporation has realized performance requirements such as aeroengine combustor buring chamber low pollution emission and wide stable operation range.
Description of drawings
Fig. 1 is the engine structure schematic diagram;
Fig. 2 is the chamber structure schematic diagram;
Fig. 3 is the enlarged diagram in the zone 3 of combustion chamber;
Fig. 4 is the 4-4 view among Fig. 3, and wherein Fig. 4 a is a main combustion stage air atomizer spray nozzle airport schematic diagram, and Fig. 4 b is a main combustion stage air atomizer spray nozzle air groove schematic diagram;
Fig. 5 is the fuel injection system schematic diagram, and wherein scheming A is that fuel oil is ejected into the schematic diagram in the transverse jet, and figure B is that TAPS main combustion stage fuel oil sprays schematic diagram, and figure C sprays schematic diagram for main combustion stage fuel oil of the present invention;
Among the figure: 10 engines, 11 low-pressure compressors, 12 high-pressure compressors, 13 combustion chambers, 14 high-pressure turbines, 15 low-pressure turbines, 16 combustion zones, 17 outer casings, casing in 18,19 outer flame tube walls, 20 interior flame tube walls, 21 outer blending hole, blending hole in 22,23 head end wall, 24 pre-combustion grade, 25 main combustion stages, 26 head constructions, 27 pre-combustion grade swirl atomizers, 28 pre-combustion grade cyclones, 29 pre-combustion grade are received and are expanded part, 30 pre-combustion grade hybrid chambers, 31 pre-combustion grade swirl atomizer fuel oils, 32 pre-combustion grade swirler blades, 33 direct-injection type air atomizer spray nozzles, 34 main combustion stage radial swirlers, 35 main combustion stages are received and are expanded part, the district of turning round behind the 36 main combustion stage radial swirlers, 37 main combustion stage radial swirler blades, 38 main combustion stage fuel oil spray site, 39 main combustion stage direct-injection type air atomizer spray nozzle air stream, 40 main combustion stage radial swirler right side walls, 41 main combustion stage fuel oils, 42 main combustion stage collection chambers, 43 main combustion stage radial swirler left side walls, 44 main combustion stage oil circuit collector rings, 45 main combustion stages are received and are expanded part contraction angle, 46 main combustion stage air atomizer spray nozzle airports, 47 main combustion stage air atomizer spray nozzle air grooves, 48 head of combustion chamber structure heights, the distance that 49 main combustion stage fuel oil spray site enter the mouth to the combustion zone.
The specific embodiment
Introduce the present invention in detail below in conjunction with the drawings and the specific embodiments.
Fig. 1 is the schematic diagram of an engine 10, and engine 10 comprises low-pressure compressor 11, high-pressure compressor 12, combustion chamber 13, high-pressure turbine 14 and low-pressure turbine 15.During engine 10 work, after air compresses through low-pressure compressor 11, enter high-pressure compressor 12 again, pressure-air enters into combustion chamber 13 burnings, fuel injection system is oil spout in high pressure draught, burns fully effectively in combustion chamber 13, and the burning back forms high-temperature high-pressure fuel gas, enter into high-pressure turbine 14 and low-pressure turbine 15, thereby promote the turbine acting.Fig. 2 is the schematic diagram of engine chamber 13, and the combustion chamber is the monocycle cavity configuration.Fig. 3 is the zoomed-in view in zone 3 in the combustion chamber 13, is the detailed structure of head of combustion chamber.Combustion chamber 13 comprises a combustion zone 16, and the external boundary of combustion zone is outer flame tube wall 19, and inner boundary is interior flame tube wall 20, the interior flame tube wall 20 of annular and outer flame tube wall 19 the interior casing 18 of annular and outside radial distribution between the casing 17.Blending hole 22 and outer blending hole 21 are used to adjust the combustor exit Temperature Distribution in arranging on inside and outside burner inner liner wall, also arrange on the inside and outside burner inner liner wall to cool off the hole (not shown), are used to cool off the burner inner liner wall, the life-span of assurance combustion chamber.16 upstream is a head construction 26 in the combustion zone, and head construction 26 is connected with the burner inner liner wall by head end wall 23.Head construction 26 comprises pre-combustion grade 24 and main combustion stage 25.Because there is not primary holes, so all burning gas consumptions all add from head of combustion chamber, and head of combustion chamber is exactly an oil-poor head like this, helps reducing the NOx disposal of pollutants.Pre-combustion grade 24 tolerance account for 5%～35% of head of combustion chamber tolerance, and main combustion stage 25 tolerance account for 65%～95% of head of combustion chamber tolerance.
Center pre-combustion grade 24 comprises central nozzle 27, cyclone 28 and receives and expand part 29.Receive expansion part 29 and formed pre-combustion grade hybrid chamber 30.Central nozzle 27 adopts swirl atomizers, and the fuel oil 31 of swirl atomizer ejection burns with the combustion zone that enters into the combustion chamber in the pre-combustion grade hybrid chamber after the rotational flow air of pre-combustion grade cyclone 28 mixes again.
Outer ring main combustion stage 25 comprises that direct-injection type air atomizer spray nozzle 33, main combustion stage radial swirler 34 and main combustion stage receipts expand part 35.Main combustion stage receive to expand part 35 and pre-combustion grade to be received the outside wall surface that expands part 29 and has formed the district 36 of turning round behind the main combustion stage radial swirler, and it is adjustable in 0 ° to 180 ° that main combustion stage is received the contraction angle 45 that expands part 35, to adapt to different engine chamber working condition requirements.The main combustion stage fuel oil 41 of direct-injection type air atomizer spray nozzle 33 enters main combustion stage collection chamber 42 through main combustion stage fuel oil spray site 38, simultaneously main combustion stage direct-injection type air atomizer spray nozzle air stream 39 also enters into collection chamber 42 from main combustion stage air atomizer spray nozzle airport 46 or main combustion stage air atomizer spray nozzle air groove 47, oil gas is pre-mixed the back and is injected to the district 36 of turning round behind the main combustion stage radial swirler in the hole from main combustion stage radial swirler left side wall 43 with the form of liquid mist again in collection chamber 42, mix the back with the rotational flow air of main combustion stage radial swirler 34 and form premixed prevapourising gas mixture, enter into combustion zone 16 burnings again.Main combustion stage radial swirler 34 is the one-level radial swirler.Main combustion stage oil circuit collector ring 44 is used for the fuel oil of each spray site of mean allocation, and hole diameter on the collector ring and quantity are regulated according to main combustion stage fuel-oil atmozation situation.The fuel oil of direct-injection type air atomizer spray nozzle 33 enters into main combustion stage radial swirler left side wall 43 by a hole, and main combustion stage oil circuit collector ring 44 makes fuel oil enter into collection chamber 42 uniformly this strand fuel oil mean allocation.In collection chamber 42, be pre-mixed with air stream 39 from the band eddy flow of main combustion stage air atomizer spray nozzle airport 46 or main combustion stage air atomizer spray nozzle air groove 47, can control swirl strength by the angle of adjusting main combustion stage air atomizer spray nozzle airport 46 or main combustion stage air atomizer spray nozzle air groove 47 by the air of hole or groove, thereby regulate the gas mixture swirl strength be injected in the district 36 of turning round behind the main combustion stage radial swirler, to adapt to Under Different Work Condition of Engine.Wherein Fig. 4 is the 4-4 view among Fig. 3, and wherein Fig. 4 a is a main combustion stage air atomizer spray nozzle airport schematic diagram, and Fig. 4 b is a main combustion stage air atomizer spray nozzle air groove schematic diagram; Gas mixture after being pre-mixed in collection chamber 42 is injected in the district 36 of turning round behind the main combustion stage radial swirler with the form of liquid mist again, forms the premix and pre-evaporation gas mixture and enter into the combustion zone and burn under the effect of the rotational flow air of main combustion stage radial swirler 34.The air that the main combustion stage fuel oil is pre-mixed can enter through main combustion stage air atomizer spray nozzle airport 46, also can enter through main combustion stage air atomizer spray nozzle air groove 47, or the combination of above-mentioned dual mode.Owing to turning to of air-flow in the district 36 of turning round behind the main combustion stage radial swirler strengthened blending, help main combustion stage oil gas better mixing, the disposal of pollutants of NOx when this premixed combustion mode can reduce high-power state.Above-mentioned main combustion stage fuel oil spray site enters the mouth to the combustion zone and is the sixth of head of combustion chamber structure height 48 apart from 49, spray site is positioned at the district of turning round behind the main combustion stage radial swirler, removed the distance L si that radial swirler exports to spray site, shown in 5C, fuel oil shown in the comparison diagram 5A is ejected into the schematic diagram in the transverse jet, spray schematic diagram with the TAPS main combustion stage fuel oil shown in Fig. 5 B, simultaneously because main combustion stage radial swirler downstream is turned round mobile, can know that the present invention can shorten the axial length of head of combustion chamber structure, thereby reduce the length and the weight of combustion chamber and engine.
During low power states such as engine 10 startings or slow train, pre-combustion grade 24 fuel feeding of combuster, main combustion stage 25 have only air through and fuel feeding not, the swirl atomizer 27 of pre-combustion grade makes combustion chambers burn district 16 form diffusion combustion mode, thereby guaranteed reliable stability of engine chamber and starting characteristic, and reduced CO and UHC disposal of pollutants.Engine 10 is operated in when high power state such as taking off or climbing, main combustion stage 25 and pre-combustion grade 24 be fuel feeding simultaneously, and the main combustion stage fuel oil 41 of main combustion stage direct-injection type air atomizer spray nozzle 33 is injected to behind the district's main combustion stage radial swirler that turns round in 36, the eddy flow of main combustion stage radial swirler 34 makes oil gas form the premix and pre-evaporation state, enter into combustion zone 16 burnings again, form the premixed combustion mode, can effectively reduce aero-engine NOx disposal of pollutants, guarantee performances such as high efficiency of combustion and uniform combustor exit Temperature Distribution simultaneously.And the receipts of main combustion stage 25 and pre-combustion grade 24 expansion part 29 and 35 can well prevent nozzle carbon distribution and tempering.
Head of combustion chamber installation and type of attachment are as follows: pre-combustion grade swirler blades 32 is received expansion part 29 with pre-combustion grade respectively and is connected with pre-combustion grade cyclone inwall, forms an integral body.Main combustion stage radial swirler left side wall 43 separated into two parts, on the left side is partly left fuel hole and the main combustion stage air atomizer spray nozzle airport 46 or the combustion level air atomizer spray nozzle air groove 47 of main combustion stage collection chamber 42, main combustion stage nozzle entrance, again main combustion stage oil circuit collector ring 44 is connected the inside of collection chamber, right-hand component and left-hand component with left side wall links into an integrated entity then, at last whole main combustion stage radial swirler left side wall 43 and pre-combustion grade is received expansion part 29 and links into an integrated entity.Main combustion stage radial swirler blade 37 is connected with main combustion stage radial swirler right side wall 40 with main combustion stage radial swirler left side wall 43 respectively, pre-combustion grade and main combustion stage cyclone have formed an integral body like this, at last fuel nozzle 27 is inserted in the pre-combustion grade cyclone, and is connected with the main combustion stage nozzle entrance.When engine chamber is installed, after burner inner liner and the casing installation, insert above-mentioned head construction (comprising fuel nozzle, main combustion stage and pre-combustion grade cyclone) from the nozzle mount pad of chamber front end, be connected with head end wall 23, head end wall 23 is connected by a loose collar with head construction 26, avoids the axial and thermal stress radially of combustion chamber.
Claims (8)
1, a kind of radial swirler turning zone liquid and mist injection premixing and prevapourising low pollution combustor, form by head of combustion chamber (26) and burner inner liner, it is characterized in that: the combustion chamber is the monocycle cavity configuration, and head of combustion chamber (26) comprises the pre-combustion grade (24) that is positioned at the center and the main combustion stage (25) of outer ring; Main combustion stage (25) includes direct-injection type air atomizer spray nozzle (33) and main combustion stage radial swirler (34) again; The main combustion stage fuel oil (41) of direct-injection type air atomizer spray nozzle (33) ejection enters in the main combustion stage collection chamber (42) through main combustion stage fuel oil spray site (38); Main combustion stage direct-injection type air materialization nozzle air stream (39) also enters into collection chamber (42) simultaneously, oil gas is pre-mixed in collection chamber (42), mixed gas mixture is injected to the district (36) of turning round behind the main combustion stage radial swirler behind the main combustion stage radial swirler blade (37) in the hole from main combustion stage radial swirler left side wall (43) with the form of liquid mist again, under the rotational flow gas effect of main combustion stage radial swirler (34), form the premix and pre-evaporation gas mixture and enter into combustion zone (16) burning, realize the radial swirler turning zone liquid and mist injection premixing and prevapourising combustion scheme.
2, a kind of radial swirler turning zone liquid and mist injection premixing and prevapourising low pollution combustor according to claim 1 is characterized in that: main combustion stage direct-injection type air materialization nozzle air stream (39) is by main combustion stage air atomizer spray nozzle airport (46) or be combined into collection chamber (42) by main combustion stage air atomizer spray nozzle air groove (47) or above-mentioned dual mode.
3, a kind of radial swirler turning zone liquid and mist injection premixing and prevapourising low pollution combustor according to claim 1 is characterized in that: the swirl strength of the air of direct-injection type air materialization nozzle air stream (39) ejection is controlled by the angle of adjusting main combustion stage air atomizer spray nozzle airport (46) or main combustion stage air atomizer spray nozzle air groove (47).
4, a kind of radial swirler turning zone liquid and mist injection premixing and prevapourising low pollution combustor according to claim 1, it is characterized in that: the spray site (38) of the direct-injection type air atomizer spray nozzle (33) of main combustion stage (25) is positioned on the main combustion stage radial swirler left side wall (43), and spray site (38) quantity is identical with main combustion stage radial swirler blade (37) quantity.
5, a kind of radial swirler turning zone liquid and mist injection premixing and prevapourising low pollution combustor according to claim 1 is characterized in that: main combustion stage fuel oil spray site to the relation between porch, combustion zone distance (49) x and head of combustion chamber structure height (48) y is:
6, a kind of radial swirler turning zone liquid and mist injection premixing and prevapourising low pollution combustor according to claim 1, it is characterized in that: the tolerance of main combustion stage (25) accounts for 65%～95% of head of combustion chamber tolerance, and the tolerance of pre-combustion grade (24) accounts for 5%～35%.
7, a kind of radial swirler turning zone liquid and mist injection premixing and prevapourising low pollution combustor according to claim 1, it is characterized in that: the burning gas consumption all infeeds from head of combustion chamber (26), do not have primary holes on the burner inner liner, have only cooling hole, outer blending hole (21) and interior blending hole (22).
8, a kind of radial swirler turning zone liquid and mist injection premixing and prevapourising low pollution combustor according to claim 1 is characterized in that: main combustion stage is received and is expanded part contraction angle (45) 0.To 180.Interior adjustable.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2008101050619A CN100543371C (en) | 2008-04-25 | 2008-04-25 | A low-pollution combustion chamber with liquid mist injection premixed pre-evaporation in the turning area of radial swirler |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2008101050619A CN100543371C (en) | 2008-04-25 | 2008-04-25 | A low-pollution combustion chamber with liquid mist injection premixed pre-evaporation in the turning area of radial swirler |
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| Publication Number | Publication Date |
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| CN101275751A CN101275751A (en) | 2008-10-01 |
| CN100543371C true CN100543371C (en) | 2009-09-23 |
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| CNB2008101050619A Expired - Fee Related CN100543371C (en) | 2008-04-25 | 2008-04-25 | A low-pollution combustion chamber with liquid mist injection premixed pre-evaporation in the turning area of radial swirler |
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Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20120144832A1 (en) * | 2010-12-10 | 2012-06-14 | General Electric Company | Passive air-fuel mixing prechamber |
| JP5134736B1 (en) * | 2012-03-23 | 2013-01-30 | 中外炉工業株式会社 | Combustion device and heating furnace |
| CN108204604B (en) * | 2018-03-13 | 2023-05-23 | 中国航空发动机研究院 | Combustion chamber multi-stage swirl nozzle with periodically varying outlet structure |
| CN112066414B (en) * | 2019-06-10 | 2022-04-12 | 中国航发商用航空发动机有限责任公司 | Combustion chamber, gas turbine and method for suppressing oscillatory combustion |
| CN111520756B (en) * | 2020-03-25 | 2022-03-15 | 西北工业大学 | Variable cross-section centrifugal nozzle |
| CN111649354B (en) * | 2020-06-15 | 2022-03-29 | 江苏科技大学 | Three-cyclone classification cyclone and combustion chamber thereof |
| CN112944395B (en) * | 2021-05-12 | 2021-09-07 | 成都中科翼能科技有限公司 | Combined premixer for gas turbine |
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2008
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