CN102200291A - Pneumatic primary level graded low-pollution combustion chamber - Google Patents
Pneumatic primary level graded low-pollution combustion chamber Download PDFInfo
- Publication number
- CN102200291A CN102200291A CN2011100765438A CN201110076543A CN102200291A CN 102200291 A CN102200291 A CN 102200291A CN 2011100765438 A CN2011100765438 A CN 2011100765438A CN 201110076543 A CN201110076543 A CN 201110076543A CN 102200291 A CN102200291 A CN 102200291A
- Authority
- CN
- China
- Prior art keywords
- main combustion
- combustion stage
- main
- stage
- combustion
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Landscapes
- Combustion Of Fluid Fuel (AREA)
Abstract
一种采用气动主级分级的低污染燃烧室，由分流式扩压器、燃烧室外机匣、燃烧室内机匣、燃油喷嘴杆、火焰筒头部、火焰筒外壁和火焰筒内壁组成。火焰筒头部主要由预燃级、主燃级、隔离段、头部挡溅盘和头部端壁组成。预燃级利用由预燃级旋流器组件进入燃烧室的旋流空气产生的低速回流区稳定火焰。主燃级燃油在主燃级分级点前状态在主燃级内环通道的气流作用下雾化；在主燃级分级点后状态打在在主燃级内环的内侧，在主燃级内环通道和主燃级外环通道的气流的作用下形成预膜蒸发模式。使主燃级分级点前状态主级空气燃油预混气在主燃区内能够得到充足的停留时间，主燃级分级点后状态主级空气燃油预混气大部分不进入低速回流区稳定火焰，保证燃烧室各个工作状态下的充分燃烧和污染排放量的降低。
A low-pollution combustion chamber adopting aerodynamic main stage classification, which is composed of a split diffuser, a casing outside the combustion chamber, a casing inside the combustion chamber, a fuel nozzle rod, the head of the flame cylinder, the outer wall of the flame cylinder and the inner wall of the flame cylinder. The head of the flame tube is mainly composed of pre-combustion stage, main combustion stage, isolation section, head splash plate and head end wall. The precombustion stage stabilizes the flame using the low velocity recirculation zone created by the swirled air entering the combustion chamber from the precombustion stage swirler assembly. The main combustion grade fuel is atomized under the action of the airflow of the main combustion stage inner ring channel before the main combustion stage classification point; after the main combustion stage classification point, the state is on the inner side of the main combustion stage inner ring, and in the main combustion The pre-film evaporation mode is formed under the action of the airflow of the ring channel and the outer ring channel of the main combustion stage. Make the main-stage air-fuel premixed gas in the state before the classification point of the main combustion stage obtain sufficient residence time in the main combustion zone, and most of the main-stage air-fuel premixed gas in the state after the classification point of the main combustion stage do not enter the low-velocity recirculation area to stabilize the flame , to ensure full combustion and reduction of pollution emissions in each working state of the combustion chamber.
Description
Technical field
The present invention relates to a kind of low pollution combustor that adopts pneumatic main classification, adopt the chamber structure of organizational form of this pneumatic main classification simple, the combustion chamber can be guaranteed in each state point efficient stable work, the purpose of the disposal of pollutants that reduces burning can both be reached.
Background technology
The key property of modern aeroengine combustion chamber and structure distribution have reached quite high level, but for the modern aeroengine combustion chamber, still have a large amount of difficult problems and challenge, the development and application of new material, new technology, new construction, new ideas is only and guarantees that it continues progressive source.The main development trend of modern aeroengine combustion chamber is combustion with reduced pollutants.The aero-engine emission standard of increasingly stringent must be satisfied in the aeroengine combustor buring chamber.The requirement of CAEP6 (the Committee on Aviation Environmental Protection) standard that adopts at present is very strict; particularly to the NOx emission requirement; and along with the enhancing of people to environmental protection consciousness, later requirement will be more strict.
Two GE of leading company of US Airways 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 is in stand loopful verification experimental verification, and the NOx disposal of pollutants has reduced by 50% than CAEP2 discharge standard.The low pollution combustor that PW company continues to adopt the RQL mode to propose reduction NOx disposal of pollutants is TALON X, the head type that adopts is the air atomizer spray nozzle of PW company development, 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, and its NOx disposal 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, the combustion technology that its key technology reduces NOx (nitrogen oxide), CO (carbon monoxide), UHC (unburned hydrocarbons) exactly and smolders, 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.
The present invention be directed to the new method of aero-engine combustion with reduced pollutants.Mechanism that produces according to NOx and CO and result of the test be as can be known: NOx that the primary zone equivalent proportion of combustion chamber produces in 0.6～0.8 scope and CO (the discharging rule of UHC and CO is similar) are seldom.Based on this principle, the discharge capacity of taking into account NOx and CO, UHC all is in the low value scope, should consider two factors: the average equivalent ratio in first primary zone, it two is uniformities of primary zone average equivalent ratio, 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 NOx, CO and UHC.Reason is that the method for designing of current combustion chamber determines.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, the required equivalent proportion area requirement of above-mentioned combustion with reduced pollutants that surpasses far away, though this moment CO and the discharging of UHC low, it is maximum that the discharging of NOx reaches.When low power state, the combustion zone equivalent proportion is very low again, and far below the required equivalent proportion of above-mentioned combustion with reduced pollutants interval, though this moment, the NOx discharging was low, CO and UHC discharging are very high again.In addition, because diffusion combustion mode is generally adopted in conventional combustion chamber, local equivalent proportion is very inhomogeneous, therefore for conventional combustion chamber, can't satisfy the low pollution requirement in whole engine operation scope.
Summary of the invention
Technology of the present invention is dealt with problems: a kind of low pollution combustor that adopts pneumatic main classification is provided, is satisfying under each condition of work of aero-engine this combustion chamber, can both effectively reduce the disposal of pollutants of aeroengine combustor buring chamber burning, comprise NOx, smolder, CO and UHC, and simple in structure.
Technical solution of the present invention: the low pollution combustor that adopts pneumatic main classification is the monocycle cavity configuration, adopt the fractional combustion mode, the burning gas consumption is all infeeded by pre-combustion grade and main combustion stage, pre-combustion grade adopts swirl stabilized diffusion flame burning organizational form, and main combustion stage adopts the premix and pre-evaporation burning organizational form of the radial spray fuel feeding of pneumatic classification.The combustion chamber mainly is made up of casing, fuel nozzle bar, burner inner liner head, burner inner liner outer wall and burner inner liner inwall in shunting diffuser, outer combustion case, the combustion chamber.The burner inner liner head mainly mainly is made up of pre-combustion grade, main combustion stage, distance piece, head splash pan and head end wall the burner inner liner head.Pre-combustion grade comprises pre-combustion grade swirler assembly, pre-combustion grade nozzle, the pre-combustion grade utilization is entered the low speed recirculating zone retention flame of the rotational flow air generation of combustion chamber by the pre-combustion grade swirler assembly, pre-combustion grade swirler assembly and distance piece are by being threaded, the pre-combustion grade nozzle is positioned at the pre-combustion grade swirler assembly, and coaxial with the pre-combustion grade swirler assembly.Main combustion stage comprises that fuel nozzle distributes ring, the stifled ring of main combustion stage fuel feeding, cyclone in the main combustion stage, the outer cyclone of main combustion stage, ring is formed in main combustion stage outer shroud and the main combustion stage, the stifled ring of main combustion stage fuel feeding distributes the ring inwall to be welded to connect with fuel nozzle, formed the main oil supply gallery, have row main combustion stage nozzle radially on the fuel nozzle distribution ring anchor ring, the main combustion stage nozzle links to each other with the main combustion stage oil supply gallery, cyclone is welded on the fuel nozzle distribution ring outside in the main combustion stage, boxing is connected on the cyclone outside in the main combustion stage in the main combustion stage, formed ring passage in the main combustion stage in the main combustion stage between ring and the fuel nozzle distribution ring, the outer cyclone of main combustion stage is welded on the ring outside in the main combustion stage, the main combustion stage outer shroud is welded on the outer cyclone of the main combustion stage outside, form the main combustion stage outer ring channel in main combustion stage outer shroud and the main combustion stage between the ring, main combustion stage outer shroud and fuel nozzle distribute formation premix and pre-evaporation endless tube between the ring, have main combustion stage outer shroud tangential admission groove on the main combustion stage outer shroud, fuel nozzle distributes ring and distance piece by being threaded, and makes main combustion stage and pre-combustion grade interconnect.After the required fuel oil of main combustion stage is sprayed by the main combustion stage nozzle, before main combustion stage classification point during state at first in main combustion stage under the air-flow effect of ring passage atomizing form fuel-air mixture, flow into then in the premix and pre-evaporation endless tube and evaporate, and with the further blending of air, form uniform fuel-air mixture in the exit of premix and pre-evaporation endless tube and enter pars intramuralis in burner inner liner outer wall and the burner inner liner, major part is mixed with the low speed recirculating zone retention flame; When the state of main combustion stage classification point back except a part of fuel oil encircles tunnel-shaped olefiant gas gaseous mixture in main combustion stage, most of fuel oil is beaten the inboard of encircling in main combustion stage, in main combustion stage, form pre-film evaporation pattern under the effect of the air-flow of ring passage and main combustion stage outer ring channel, in the premix and pre-evaporation endless tube, evaporate, and with the further blending of air, form uniform fuel-air mixture in the exit of premix and pre-evaporation endless tube and enter pars intramuralis in burner inner liner outer wall and the burner inner liner, burn under the igniting of the low speed recirculating zone of the pre-combustion grade retention flame, major part does not enter the low speed recirculating zone retention flame.Fuel nozzle bar inside has main combustion stage oil circuit and pre-combustion grade oil circuit, fuel nozzle bar and fuel nozzle distribute boxing to connect, main combustion stage oil circuit and pre-combustion grade oil circuit distribute ring inner main combustion stage oil supply gallery and pre-combustion grade oil supply gallery to communicate with fuel nozzle respectively, phase main combustion stage nozzle and pre-combustion grade nozzle fuel feeding, the pre-combustion grade nozzle distributes on the ring by being threaded in fuel nozzle, and the fuel nozzle bar links to each other with outer combustion case.Head splash pan and head end wall welding, head end wall is connected by bolt with the burner inner liner outer wall, and head end wall and main combustion stage outer shroud are located by connecting by radial and axial.
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: the design philosophy of fractional combustion, make burning usefulness gas infeed the combustion chamber from pre-combustion grade and main combustion stage respectively, and fuel oil is carried out classification infeed, the control equivalent proportion of fuel oil in the combustion zone under aero-engine different operating state all in the combustion with reduced pollutants district, thereby reach the purpose that reduces the Air emission.Pre-combustion grade state before main pre-combustion grade classification points such as slow train starts, and keeps the equivalent proportion of the preceding state combustion zone of main pre-combustion grade classification point to drop in the above-mentioned combustion with reduced pollutants equivalent proportion interval, and makes the good stability of burning, starts easily.When engine operation just starts main combustion stage behind main pre-combustion grade classification point, before main combustion stage classification point during state, atomizing forms fuel-air mixture under the air-flow effect of ring passage in main combustion stage, flow into then in the premix and pre-evaporation endless tube and evaporate, and with the further blending of air, form uniform fuel-air mixture in the exit of premix and pre-evaporation endless tube and enter pars intramuralis in burner inner liner outer wall and the burner inner liner, major part is mixed with the low speed recirculating zone retention flame, the fuel-air mixture that guarantees main combustion stage has sufficient residence time, can completing combustion, thus reduce near the discharge amount of pollution the classification point and improve the efficiency of combustion of the preceding state of main combustion stage classification point; State is except a part of fuel oil encircles tunnel-shaped olefiant gas gaseous mixture in main combustion stage behind main combustion stage classification point, most of fuel oil is beaten the inboard of encircling in main combustion stage, in main combustion stage, form pre-film evaporation pattern under the effect of the air-flow of ring passage and main combustion stage outer ring channel, in the premix and pre-evaporation endless tube, evaporate, and with the further blending of air, form uniform fuel-air mixture in the exit of premix and pre-evaporation endless tube and enter pars intramuralis in burner inner liner outer wall and the burner inner liner, under the igniting of the low speed recirculating zone of the pre-combustion grade retention flame, burn, major part does not enter the low speed recirculating zone retention flame, guarantee that the primary zone equivalent proportion is in the discharge amount of pollution small range, thus reduce near the design point operating mode discharge amount of pollution and improve the main combustion stage classification point efficiency of combustion of state afterwards.Adopt above-mentioned low pollution combustor, can guarantee that the aeroengine combustor buring chamber is under all duties, the equivalent proportion of combustion zone all is controlled in the interval of combustion with reduced pollutants, and can guarantee that the main combustion stage gas mixture can both reach sufficient burning under different conditions, simultaneously can control the equivalent proportion uniformity of combustion zone, thereby reach that the disposal of pollutants of aero-engine low pollution combustor is low, good stability and the high performance requirement of efficiency of combustion by the control main combustion stage mist of oil uniformity, degree of mixing and evaporativity.
The present invention's advantage compared with prior art is as follows:
(1) combustion chamber of the present invention is the monocycle cavity configuration, adopt the conceptual design of fractional combustion, the burning gas consumption is all infeeded by pre-combustion grade and main combustion stage, and burner inner liner does not have primary holes, cold gas and mixed gas infeed from burner inner liner, simplify chamber structure when increasing the combustion chamber effect.
(2) main combustion stage of the present invention adopts the burning organizational form of the premix and pre-evaporation of pneumatic classification.Pneumatic classification can obtain to simplify the main combustion stage structure in the good fuel oil primary atomization effect under different conditions, and control main combustion stage gas mixture obtains enough time of staying in the primary zone under different conditions, form uniform fuel-air mixture jet.After the uniform fuel-air mixture jet of this strand was lighted, fuel-air mixture can be complete in extremely short time internal combustion, thereby reduce the disposal of pollutants of combustion chamber.
(3) pre-combustion grade of the present invention adopts swirl stabilized diffusion flame burning organizational form, main combustion stage adopts the premix and pre-evaporation burning organizational form of pneumatic classification, this combined burning pattern can realize the work of aeroengine combustor buring chamber efficient stable in the working range of broadness, can realize the combustion chamber low pollution emission simultaneously.
Description of drawings
Fig. 1 is a structure cutaway view of the present invention;
Fig. 2 is a burner inner liner head construction cutaway view of the present invention;
Fig. 3 is a main combustion stage classification point of the present invention back state work schematic diagram;
Fig. 4 is a state work schematic diagram before the main combustion stage classification point of the present invention;
Fig. 5 is a burner inner liner head main combustion stage classification point of the present invention back state work schematic diagram;
Fig. 6 is a state work schematic diagram before the burner inner liner head main combustion stage classification point of the present invention;
Fig. 7 is that fuel nozzle bar of the present invention and fuel nozzle distribute ring structure signal and cutaway view;
Fig. 8 is a fuel nozzle bar polycrystalline substance schematic diagram of the present invention;
Fig. 9 is main combustion stage structural representation of the present invention and cutaway view;
Figure 10 is the structural representation and the cutaway view of cyclone in outer cyclone of main of the present invention and the main;
Figure 11 is a pre-combustion grade swirler assembly schematic diagram of the present invention;
Among the figure: 1. shunting diffuser, 2. outer combustion case, 3. burner inner liner outer wall, 4. casing in the combustion chamber, 5. burner inner liner inwall, 6. fuel nozzle bar, 7. burner inner liner head, 8. burner inner liner blending hole, 9. main combustion stage, 10. pre-combustion grade, 11. head end wall, 12. head splash pans, 13. distance piece, 14. the combustion chamber inlet air flow, 15. burner inner liner head air-flows, 16. main combustion stage outer shroud tangential gas flow, 17. main combustion stage axial flow, 18. the pre-combustion grade air-flow, 19. combustion chamber ring cavity air-flows, 20. blending air-flows, 21. combustor exit air-flow, 22. main combustion stage classification point back state main combustion stage flame, the 23. low speed recirculating zone retentions flame, 24. pre-combustion grade swirler assemblies, 25. state main combustion stage flame before the main combustion stage classification point, 26. state fuel-air mixture before the main combustion stage classification point, 27. pre-combustion grade fuel oil liquid mists, 28. main combustion stage classification points back state main is broken the wall fuel oil, 29. state fuel-air mixture before the main combustion stage classification point, 30. main combustion stage oil circuit, 31. pre-combustion grade oil circuits, 32. fuel nozzles distribute ring main combustion stage pipe, 33. main combustion stage oil supply gallery, 34. the pre-combustion grade oil supply gallery, 35. main combustion stage nozzles, 36. fuel nozzles distribute ring, 37. the stifled ring of main combustion stage fuel feeding, 38. cyclone in the pre-combustion grade nozzle, 39. main combustion stages, the outer cyclone of 40. main combustion stages, 41. main combustion stage outer shroud tangential admission groove, 42. ring in the main combustion stage outer shroud, 43. main combustion stages, 44. pre-combustion grade one-level cyclones, 45. pre-combustion grade second cyclone, 46. ring passage in the main combustion stage, 47. premix and pre-evaporation endless tubes, 48. main combustion stage outer ring channels.
The specific embodiment
As depicted in figs. 1 and 2, the present invention adopts the fractional combustion mode, the burning gas consumption is all infeeded by pre-combustion grade 10 and main combustion stage 9, and pre-combustion grade 10 adopts swirl stabilized diffusion flame burning organizational form, and main combustion stage 9 adopts the premix and pre-evaporation burning organizational form of the radial spray fuel feeding of pneumatic classification.The combustion chamber mainly is made up of casing 4, fuel nozzle bar 6, burner inner liner head 7, burner inner liner outer wall 3 and burner inner liner inwall 5 in shunting diffuser 1, outer combustion case 2, the combustion chamber.Burner inner liner head 7 mainly mainly is made up of pre-combustion grade 10, main combustion stage 9, distance piece 13, head splash pan 12 and head end wall 11 the burner inner liner head.Fuel nozzle bar 6 links to each other with outer combustion case 2.11 welding of head splash pan 12 and head end wall, head end wall 11 and burner inner liner outer wall 3 and burner inner liner inwall 5 are connected by bolt, and head end wall 11 and main combustion stage outer shroud 42 are located by connecting by radial and axial.The type of cooling of burner inner liner outer wall 3 and burner inner liner inwall 5 adopts the air film cooling, disperses the cooling or the compound type of cooling, wall surface temperature is controlled the life-span that prolongs burner inner liner.
As Fig. 2,3,4,5, shown in 6, shunting diffuser 1 is divided into three strands with combustion chamber inlet air flow 14: one is that burner inner liner head air-flow 15, all the other two strands are combustion chamber ring cavity air-flow 19, and blending air-flow 20 enters in burner inner liner outer wall 3 and the burner inner liner inwall 5 from burner inner liner blending hole 8, with control combustor exit Temperature Distribution.Burning usefulness gas is all infeeded by burner inner liner head 7, the air distribution accounts for 40%～80% of combustion chamber inlet air flow: the cooling institute air demand of head end wall 11 accounts for 0%～25% of whole burning tolerance, 10 air demands of pre-combustion grade account for 10%～40% of whole burning tolerance, and all the other are infeeded by main combustion stage 9.Pre-combustion grade swirler assembly 24 and distance piece 13 are by being threaded, and pre-combustion grade nozzle 38 is positioned at pre-combustion grade swirler assembly 24, and coaxial with pre-combustion grade swirler assembly 24, and pre-combustion grade nozzle 38 is pressure atomized fog jet, pneumatic nozzle or combined nozzle.Pre-combustion grade 10 is utilized the low speed recirculating zone retention flame 23 that is entered the rotational flow air generation of combustion chamber by pre-combustion grade swirler assembly 24.After main combustion stage 9 required fuel oils are sprayed by main combustion stage nozzle 35, before main combustion stage classification point during state at first in main combustion stage under the air-flow effect of ring passage 46 atomizing form the preceding state fuel-air mixture 26 of main combustion stage classification point, flow into evaporation in the premix and pre-evaporation endless tube 47 then, and with the further blending of air, form uniform fuel-air mixture in the exit of premix and pre-evaporation endless tube 47 and enter burner inner liner outer wall 3 and burner inner liner inwall 5 inside, state main combustion stage flame 25 before the formation main combustion stage of under the igniting of the low speed recirculating zone of pre-combustion grade 10 retention flame 23, the burning classification point, major part is mixed with the low speed recirculating zone retention flame 23, state fuel-air mixture 26 can access the sufficient time of staying before making main combustion stage classification point, thereby reach the efficiency of combustion that improves the preceding state of main combustion stage classification point, reduce the purpose of the discharge amount of pollution of the preceding state of main combustion stage classification point; Encircling passage 46 except a part of fuel oil at main combustion stage classification point back state in main combustion stage forms the fuel-air mixture, most of fuel oil is beaten the inboard of ring 43 in main combustion stage, in main combustion stage, form pre-film evaporation pattern under the effect of the air-flow of ring passage 46 and main combustion stage outer ring channel 48, evaporation in premix and pre-evaporation endless tube 47, and with the further blending of air, form uniform main combustion stage classification point back state fuel-air mixture 29 in the exit of premix and pre-evaporation endless tube 47 and enter burner inner liner outer wall 3 and burner inner liner inwall 5 inside, under the igniting of the low speed recirculating zone of pre-combustion grade 10 retention flame 23, burn and form main combustion stage classification point back state main combustion stage flame 22, major part does not enter the low speed recirculating zone retention flame 23, thereby thereby state fuel-air mixture 29 reaches the reduction disposal of pollutants by the primary zone as early as possible after guaranteeing main combustion stage classification point, particularly the purpose of NOx discharging.
As Fig. 7,8,9, shown in 10, main combustion stage 9 comprises that fuel nozzle distributes in ring 36, the stifled ring 37 of main combustion stage fuel feeding, the main combustion stage in cyclone 39, the outer cyclone 40 of main combustion stage, main combustion stage outer shroud 42 and the main combustion stage ring 43 to form, and the stifled ring 37 of main combustion stage fuel feeding distributes ring 36 inwalls to be welded to connect with fuel nozzle, has formed main oil supply gallery 33, have row main combustion stage nozzle 35 radially on fuel nozzle distribution ring 36 anchor rings, main combustion stage nozzle 35 links to each other with main combustion stage oil supply gallery 33.Main combustion stage nozzle 35 adopts at fuel nozzle and distributes the spray regime of opening a plurality of holes on ring 36 anchor rings, the fuel nozzle at main combustion stage nozzle 35 places distributes the axis of ring 36 and the axis of pre-combustion grade nozzle 38 to be on the same straight line, quantity 0＜p≤50 of main combustion stage nozzle 35, main combustion stage nozzle corner cut are-90～90 degree.Cyclone 39 is welded on fuel nozzle distribution ring 36 outsides in the main combustion stage, ring 43 is welded on cyclone 39 outsides in the main combustion stage in the main combustion stage, formed ring passage 46 in the main combustion stage in the main combustion stage between ring 43 and the fuel nozzle distribution ring 36, the outer cyclone 40 of main combustion stage is welded on ring 43 outsides in the main combustion stage, main combustion stage outer shroud 42 is welded on outer cyclone 40 outsides of main combustion stage, form main combustion stage outer ring channel 48 in main combustion stage outer shroud 42 and the main combustion stage between the ring 43, main combustion stage outer shroud 42 and fuel nozzle distribute formation premix and pre-evaporation endless tube 47 between the ring 36, have main combustion stage outer shroud tangential admission groove 41 on the main combustion stage outer shroud 42, the mode of fluting can be circular hole or groove or square hole or half hole.The progression 1 of the cyclone that the outer cyclone 40 of cyclone 39 and main combustion stage adopts in the main combustion stage; It is axial swirler that every grade of cyclone adopts the structure of cyclone, can select in the same way or oppositely; The main combustion stage outer shroud tangential admission groove 41 tangential angles of main combustion stage outer shroud 42 are 10 °～80 °, and are identical or opposite with outer cyclone 40 rotation directions of main combustion stage.Fuel nozzle distributes ring 36 and distance piece 13 by being threaded, and makes main combustion stage 9 and pre-combustion grade 10 interconnect.Fuel nozzle bar 6 inside have main combustion stage oil circuit 30 and pre-combustion grade oil circuit 31, fuel nozzle bar 6 distributes ring 36 welding with fuel nozzle, main combustion stage oil circuit 30 and pre-combustion grade oil circuit 31 distribute the main combustion stage oil supply gallery 33 and the pre-combustion grade oil supply gallery 34 of ring 36 inside to communicate with fuel nozzle respectively, phase main combustion stage nozzle 35 and pre-combustion grade nozzle 38 fuel feeding, pre-combustion grade nozzle 38 distributes on the ring 36 by being threaded in fuel nozzle.
As shown in figure 11, progression 1≤n≤5 of the cyclone of pre-combustion grade swirler assembly 24 employings; It is axial swirler that every grade of cyclone adopts the structure of cyclone, or radial swirler, or the tangential swirl device; When the progression n=1 of pre-combustion grade swirler assembly 24, cyclone directly is connected with distance piece 13; When the progression 1＜n of pre-combustion grade swirler assembly 24≤5, cyclones at different levels connect into an integral body earlier, are connected with distance piece 13 after forming pre-combustion grade swirler assembly 24 again.
In specific embodiments, pre-combustion grade swirler assembly 24 adopts the two-stage radial swirler of n=2, one-level cyclone 44 adopts welding connecting modes with second cyclone 45, and second cyclone 45 and distance piece 13 make main combustion stage 9 and pre-combustion grade 10 interconnect by being threaded.Pre-combustion grade swirler assembly 24 and distance piece 13 are by being threaded, and pre-combustion grade nozzle 38 is positioned at pre-combustion grade swirler assembly 24, and pre-combustion grade nozzle 38 adopts pressure atomized fog jets.The quantity p=20 of main combustion stage nozzle 35, main combustion stage nozzle corner cut is 90 degree.The mode of the fluting of main combustion stage outer shroud tangential admission groove 41 can be rectangular channel.The progression 1 of the cyclone that the outer cyclone 40 of cyclone 39 and main combustion stage adopts in the main combustion stage; It is axial swirler that every grade of cyclone adopts the structure of cyclone, and rotation direction is selected in the same way; The main combustion stage outer shroud tangential admission groove 41 tangential angles of main combustion stage outer shroud 42 are 30 °, and are identical with outer cyclone 40 rotation directions of main combustion stage.Fuel nozzle distributes ring 36 and distance piece 13 by being threaded, and makes main combustion stage 9 and pre-combustion grade 10 interconnect.Installation process intermediate fuel oil jet stem 6 is packed into main combustion stage 9 and pre-combustion grade 10 in the combustion chamber, with head end wall 11 axially and radial locations, form burner inner liner head 7.11 welding of head splash pan 12 and head end wall, head end wall 11 and burner inner liner outer wall 3 and burner inner liner inwall 5 are connected by bolt.The low speed recirculating zone retention flame 23 that pre-combustion grade 10 produces.After main combustion stage 9 required fuel oils are sprayed by main combustion stage nozzle 35, state at first atomizes under the air-flow effect of ring passage 46 in main combustion stage and forms the preceding state fuel-air mixture 26 of main combustion stage classification point before main combustion stage classification point, state main combustion stage flame 25 before the formation main combustion stage of under the igniting of the low speed recirculating zone of pre-combustion grade 10 retention flame 23, the burning classification point, major part is mixed with the low speed recirculating zone retention flame 23, state fuel-air mixture 26 can access the sufficient time of staying before making main combustion stage classification point, thereby reach the efficiency of combustion that improves the preceding state of main combustion stage classification point, reduce the purpose of the discharge amount of pollution of the preceding state of main combustion stage classification point; Encircling passage 46 except a part of fuel oil at main combustion stage classification point back state in main combustion stage forms the fuel-air mixture, most of fuel oil is beaten the inboard of ring 43 in main combustion stage, in main combustion stage, form pre-film evaporation pattern under the effect of the air-flow of ring passage 46 and main combustion stage outer ring channel 48, form uniform main combustion stage classification point back state fuel-air mixture 29 in the exit of premix and pre-evaporation endless tube 47 and enter burner inner liner outer wall 3 and burner inner liner inwall 5 inside, under the igniting of the low speed recirculating zone of pre-combustion grade 10 retention flame 23, burn and form main combustion stage classification point back state main combustion stage flame 22, major part does not enter the low speed recirculating zone retention flame 23, thereby thereby state fuel-air mixture 29 reaches the reduction disposal of pollutants by the primary zone as early as possible after guaranteeing main combustion stage classification point, particularly the purpose of NOx discharging.This shows that the low pollution combustor that adopts pneumatic main classification can effectively reduce the disposal of pollutants of combustion chamber in the working range of aero-engine broadness when guaranteeing the efficient stable burning, at the auxiliary outlet temperature distribution performance preferably that also can obtain down of blending hole air-flow.
The non-elaborated part of the present invention belongs to general knowledge known in this field.
The above only is a preferred implementation of the present invention; should be pointed out that for those skilled in the art, under the prerequisite that does not break away from the principle of the invention; can also make some improvements and modifications, these improvements and modifications also should be considered as protection scope of the present invention.
Claims (10)
1. low pollution combustor that adopts pneumatic main classification, it is characterized in that: described combustion chamber is the monocycle cavity configuration, adopt the fractional combustion mode, described combustion chamber is made up of casing (4), fuel nozzle bar (6), burner inner liner head (7), burner inner liner outer wall (3) and burner inner liner inwall (5) in shunting diffuser (1), outer combustion case (2), the combustion chamber; Described burner inner liner head (7) mainly is made up of pre-combustion grade (10), main combustion stage (9), distance piece (13), head splash pan (12) and head end wall (11) the burner inner liner head; The burning gas consumption is all infeeded by pre-combustion grade (10) and main combustion stage (9); Described pre-combustion grade (10) adopts swirl stabilized diffusion flame burning organizational form, and described pre-combustion grade (10) comprises pre-combustion grade swirler assembly (24) and pre-combustion grade nozzle (38); The low speed recirculating zone retention flame (23) that the rotational flow air that is entered by pre-combustion grade swirler assembly (24) produces, pre-combustion grade swirler assembly (24) is threaded with distance piece (13), pre-combustion grade nozzle (38) is positioned at pre-combustion grade swirler assembly (24), and coaxial with pre-combustion grade swirler assembly (24); Described main combustion stage (9) adopts the premix and pre-evaporation burning organizational form of the radial spray fuel feeding of pneumatic classification, and main combustion stage (9) comprises that fuel nozzle distributes ring (43) in cyclone (39) in ring (36), the stifled ring of main combustion stage fuel feeding (37), the main combustion stage, the outer cyclone (40) of main combustion stage, main combustion stage outer shroud (42) and the main combustion stage; The stifled ring of main combustion stage fuel feeding (37) distributes ring (36) inwall to be welded to connect with fuel nozzle, formed main oil supply gallery (33), have row main combustion stage nozzle (35) radially on fuel nozzle distribution ring (36) anchor ring, main combustion stage nozzle (35) links to each other with main combustion stage oil supply gallery (33), cyclone (39) is welded on fuel nozzle distribution ring (36) outside in the main combustion stage, ring (43) is welded on cyclone (39) outside in the main combustion stage in the main combustion stage, formed ring passage (46) in the main combustion stage in the main combustion stage between ring (43) and the fuel nozzle distribution ring (36), the outer cyclone (40) of main combustion stage is welded on ring (43) outside in the main combustion stage, main combustion stage outer shroud (42) is welded on the outer cyclone (40) of the main combustion stage outside, form main combustion stage outer ring channel (48) in main combustion stage outer shroud (42) and the main combustion stage between the ring (43), main combustion stage outer shroud (42) and fuel nozzle distribute formation premix and pre-evaporation endless tube (47) between the ring (36), have main combustion stage outer shroud tangential admission groove (41) on the main combustion stage outer shroud (42), fuel nozzle distributes ring (36) and distance piece (13) by being threaded, and makes main combustion stage (9) and pre-combustion grade (10) interconnect; After the required fuel oil of main combustion stage (9) is sprayed by main combustion stage nozzle (35), the air-flow effect that at first encircles passage (46) before the main combustion stage classification point during state in main combustion stage atomizing down forms the preceding state fuel-air mixture (26) of main combustion stage classification point, flow into evaporation in the premix and pre-evaporation endless tube (47) then, and with the further blending of air, form uniform fuel-air mixture in the exit of premix and pre-evaporation endless tube (47) and enter burner inner liner outer wall (3) and burner inner liner inwall (5) inside, state main combustion stage flame (25) before the formation main combustion stage of under the igniting of the low speed recirculating zone of pre-combustion grade (10) retention flame (23), the burning classification point, major part is mixed with the low speed recirculating zone retention flame (23), state fuel-air mixture (26) can access the sufficient time of staying before making main combustion stage classification point, thereby reach the efficiency of combustion that improves the preceding state of main combustion stage classification point, reduce the purpose of the discharge amount of pollution of the preceding state of main combustion stage classification point; Encircling passage (46) except a part of fuel oil at main combustion stage classification point back state in main combustion stage forms the fuel-air mixture, most of fuel oil is beaten the inboard of ring (43) in main combustion stage, in main combustion stage, encircle under the effect of air-flow of passage (46) and main combustion stage outer ring channel (48) and form pre-film evaporation pattern, evaporation in premix and pre-evaporation endless tube (47), and with the further blending of air, form uniform main combustion stage classification point back state fuel-air mixture (29) in the exit of premix and pre-evaporation endless tube (47) and enter burner inner liner outer wall (3) and burner inner liner inwall (5) inside, under the igniting of the low speed recirculating zone of pre-combustion grade (10) retention flame (23), burn and form main combustion stage classification point back state main combustion stage flame (22), major part does not enter the low speed recirculating zone retention flame (23), thereby guarantee main combustion stage classification point back state fuel-air mixture (29) thus reach the reduction disposal of pollutants by the primary zone as early as possible, the NOx purpose of discharging particularly; Fuel nozzle bar (6) inside has main combustion stage oil circuit (30) and pre-combustion grade oil circuit (31), fuel nozzle bar (6) distributes ring (36) welding with fuel nozzle, main combustion stage oil circuit (30) and pre-combustion grade oil circuit (31) distribute ring (36) inner main combustion stage oil supply gallery (33) and pre-combustion grade oil supply gallery (34) to communicate with fuel nozzle respectively, phase main combustion stage nozzle (35) and pre-combustion grade nozzle (38) fuel feeding, pre-combustion grade nozzle (38) distributes on the ring (36) by being threaded in fuel nozzle, and fuel nozzle bar (6) links to each other with outer combustion case (2).Head splash pan (12) and head end wall (11) welding, head end wall (11) is connected by bolt with burner inner liner inwall (5) with burner inner liner outer wall (3), and head end wall (11) is located by connecting by radial and axial with main combustion stage outer shroud (42).
2. a kind of low pollution combustor that adopts pneumatic main classification according to claim 1, it is characterized in that: state is 20%～40% of a combustion chamber maximum rating before the described main pre-combustion grade classification point, state is 30%～50% of a combustion chamber maximum rating before the main pre-combustion grade classification point, and main combustion stage classification point back state is 30%～100% of a combustion chamber maximum rating.
3. a kind of low pollution combustor that adopts pneumatic main classification according to claim 1, it is characterized in that: be provided with burner inner liner blending hole (8) at described burner inner liner outer wall (3) and burner inner liner inwall (5) rear portion, blending air-flow (20) enters in burner inner liner outer wall (3) and the burner inner liner inwall (5) from burner inner liner blending hole (8), with control combustor exit Temperature Distribution.
4. a kind of low pollution combustor that adopts pneumatic main classification according to claim 1, it is characterized in that: described shunting diffuser (1) is divided into three strands with combustion chamber inlet air flow (14): one is that burner inner liner head air-flow (15), all the other two strands are combustion chamber ring cavity air-flow (19), to satisfy the demand of combustion chamber each several part to air mass flow.
5. a kind of low pollution combustor that adopts pneumatic main classification according to claim 1 is characterized in that: described pre-combustion grade nozzle (38) is pressure atomized fog jet, pneumatic nozzle or combined nozzle.
6. a kind of low pollution combustor that adopts pneumatic main classification according to claim 1 is characterized in that: the span of the progression n of the cyclone that described pre-combustion grade swirler assembly (24) adopts is 1≤n≤5; It is axial swirler that every grade of cyclone adopts the structure of cyclone, or radial swirler, or the tangential swirl device; When the progression n=1 of pre-combustion grade swirler assembly (24), cyclone directly is connected with distance piece (13); When the progression 1＜n of pre-combustion grade swirler assembly (24)≤5, cyclones at different levels connect into an integral body earlier, are connected with distance piece (13) after forming pre-combustion grade swirler assembly (24) again.
7. a kind of low pollution combustor that adopts pneumatic main classification according to claim 1, it is characterized in that: described main combustion stage nozzle (35) adopts at fuel nozzle and distributes the spray regime of opening a plurality of holes on ring (36) anchor ring, the fuel nozzle at main combustion stage nozzle (35) place distributes the axis of ring (36) and the axis of pre-combustion grade nozzle (38) to be on the same straight line, the quantity p value of main combustion stage nozzle (35) is 0＜p≤50, and main combustion stage nozzle corner cut is-90～90 degree.
8. a kind of low pollution combustor that adopts pneumatic main classification according to claim 1 is characterized in that: the progression 1 of the cyclone that the outer cyclone (40) of cyclone (39) and main combustion stage adopts in the described main combustion stage; It is axial swirler that every grade of cyclone adopts the structure of cyclone, can select in the same way or oppositely; The tangential angle of the main combustion stage outer shroud tangential admission groove (41) of main combustion stage outer shroud (42) is 10 °～80 °, and is identical or opposite with outer cyclone (40) rotation direction of main combustion stage.
9. a kind of low pollution combustor that adopts pneumatic main classification according to claim 1, it is characterized in that: the burning usefulness gas of described combustion chamber is all infeeded by burner inner liner head (7), the air distribution accounts for 40%～80% of combustion chamber inlet air flow: the cooling institute air demand of head end wall (11) accounts for 0%～25% of whole burning tolerance, pre-combustion grade (10) institute air demand accounts for 10%～40% of whole burning tolerance, and all the other are infeeded by main combustion stage (9).
10. a kind of low pollution combustor that adopts pneumatic main classification according to claim 1, it is characterized in that: the burner inner liner outer wall (3) of described combustion chamber and the type of cooling of burner inner liner inwall (5) adopt the air film cooling, disperse the cooling or the compound type of cooling, wall surface temperature is controlled the life-span that prolongs burner inner liner.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011100765438A CN102200291B (en) | 2011-03-29 | 2011-03-29 | Pneumatic primary level graded low-pollution combustion chamber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011100765438A CN102200291B (en) | 2011-03-29 | 2011-03-29 | Pneumatic primary level graded low-pollution combustion chamber |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102200291A true CN102200291A (en) | 2011-09-28 |
| CN102200291B CN102200291B (en) | 2013-12-11 |
Family
ID=44661168
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011100765438A Expired - Fee Related CN102200291B (en) | 2011-03-29 | 2011-03-29 | Pneumatic primary level graded low-pollution combustion chamber |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102200291B (en) |
Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102506446A (en) * | 2011-10-13 | 2012-06-20 | 中国科学院工程热物理研究所 | Fuel and air mixing device for low-pollution burning chamber of gas turbine |
| CN103047682A (en) * | 2012-12-27 | 2013-04-17 | 中国燃气涡轮研究院 | Partial pre-mixing and pre-evaporation burning chamber with prefilm type nozzle |
| CN103343985A (en) * | 2013-06-21 | 2013-10-09 | 北京航空航天大学 | Double-pre-film pneumatic nebulization low pollution combustor head structure |
| CN103868099A (en) * | 2012-12-13 | 2014-06-18 | 中航商用航空发动机有限责任公司 | Aerial engine combustion chamber and aerial engine comprising same |
| CN105716119A (en) * | 2016-03-22 | 2016-06-29 | 北京航空航天大学 | Lean direct injection low-emission combustor adopting effervescent atomizers |
| CN105823087A (en) * | 2016-03-22 | 2016-08-03 | 北京航空航天大学 | Low-pollution combustor with main combustion grade adopting effervescent atomizer |
| CN106091013A (en) * | 2016-06-07 | 2016-11-09 | 中国科学院工程热物理研究所 | A kind of high temperature rise combustor structure of three stage layered burnings |
| CN106594801A (en) * | 2015-10-16 | 2017-04-26 | 中航商用航空发动机有限责任公司 | Low-pollution combustion chamber adopting forced diversion at main-combustion-stage outlet |
| CN107013941A (en) * | 2016-01-27 | 2017-08-04 | 中航商用航空发动机有限责任公司 | Combustion chamber fuel nozzle arrangement |
| CN108916911A (en) * | 2018-04-27 | 2018-11-30 | 北京航空航天大学 | A kind of pre-combustion grade uses the center classification low emission combustor head of pre- diaphragm plate structure |
| CN109404966A (en) * | 2018-12-04 | 2019-03-01 | 新奥能源动力科技（上海）有限公司 | Chamber head part device and gas turbine |
| CN109945233A (en) * | 2019-03-20 | 2019-06-28 | 中国航发湖南动力机械研究所 | Combustion chamber and its atomising device, aero gas turbine engine |
| CN112066415A (en) * | 2019-06-10 | 2020-12-11 | 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 |
| CN113137636A (en) * | 2021-04-15 | 2021-07-20 | 中国航发湖南动力机械研究所 | Double-oil-way nozzle structure |
| CN113251440A (en) * | 2021-06-01 | 2021-08-13 | 成都中科翼能科技有限公司 | Multi-stage partition type combustion structure for gas turbine |
| CN114719293A (en) * | 2022-03-24 | 2022-07-08 | 西北工业大学 | An annular cavity afterburner structure |
| CN115264534A (en) * | 2021-04-29 | 2022-11-01 | 中国航发商用航空发动机有限责任公司 | Swirler, flame tube and aeroengine |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1278013A2 (en) * | 2001-07-17 | 2003-01-22 | Mitsubishi Heavy Industries, Ltd. | Pilot burner, premixing combustor, and gas turbine |
| DE60016345T2 (en) * | 1999-09-23 | 2005-11-10 | Nuovo Pignone Holding S.P.A. | Premixing chamber for gas turbines |
| CN101737802A (en) * | 2009-11-27 | 2010-06-16 | 北京航空航天大学 | Central cavity stable fire tangential combustion chamber |
| CN101788157A (en) * | 2010-01-26 | 2010-07-28 | 北京航空航天大学 | Low-pollution combustion chamber provided with premixing and pre-evaporating ring pipe |
-
2011
- 2011-03-29 CN CN2011100765438A patent/CN102200291B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE60016345T2 (en) * | 1999-09-23 | 2005-11-10 | Nuovo Pignone Holding S.P.A. | Premixing chamber for gas turbines |
| EP1278013A2 (en) * | 2001-07-17 | 2003-01-22 | Mitsubishi Heavy Industries, Ltd. | Pilot burner, premixing combustor, and gas turbine |
| CN101737802A (en) * | 2009-11-27 | 2010-06-16 | 北京航空航天大学 | Central cavity stable fire tangential combustion chamber |
| CN101788157A (en) * | 2010-01-26 | 2010-07-28 | 北京航空航天大学 | Low-pollution combustion chamber provided with premixing and pre-evaporating ring pipe |
Cited By (29)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102506446B (en) * | 2011-10-13 | 2013-10-09 | 中国科学院工程热物理研究所 | A fuel and air mixing device for a low-pollution combustor of a gas turbine |
| CN102506446A (en) * | 2011-10-13 | 2012-06-20 | 中国科学院工程热物理研究所 | Fuel and air mixing device for low-pollution burning chamber of gas turbine |
| CN103868099A (en) * | 2012-12-13 | 2014-06-18 | 中航商用航空发动机有限责任公司 | Aerial engine combustion chamber and aerial engine comprising same |
| CN103868099B (en) * | 2012-12-13 | 2016-02-10 | 中航商用航空发动机有限责任公司 | Aeroengine combustor buring room and aero-engine thereof |
| CN103047682A (en) * | 2012-12-27 | 2013-04-17 | 中国燃气涡轮研究院 | Partial pre-mixing and pre-evaporation burning chamber with prefilm type nozzle |
| CN103343985A (en) * | 2013-06-21 | 2013-10-09 | 北京航空航天大学 | Double-pre-film pneumatic nebulization low pollution combustor head structure |
| CN103343985B (en) * | 2013-06-21 | 2015-07-08 | 北京航空航天大学 | A double pre-film pneumatic atomization low-pollution combustor head structure |
| CN106594801B (en) * | 2015-10-16 | 2019-06-18 | 中国航发商用航空发动机有限责任公司 | The outlet of the main combustion stage adopts a low-polluting combustion chamber with forced diversion |
| CN106594801A (en) * | 2015-10-16 | 2017-04-26 | 中航商用航空发动机有限责任公司 | Low-pollution combustion chamber adopting forced diversion at main-combustion-stage outlet |
| CN107013941A (en) * | 2016-01-27 | 2017-08-04 | 中航商用航空发动机有限责任公司 | Combustion chamber fuel nozzle arrangement |
| CN107013941B (en) * | 2016-01-27 | 2019-09-17 | 中国航发商用航空发动机有限责任公司 | Combustion chamber fuel nozzle arrangement |
| CN105823087A (en) * | 2016-03-22 | 2016-08-03 | 北京航空航天大学 | Low-pollution combustor with main combustion grade adopting effervescent atomizer |
| CN105823087B (en) * | 2016-03-22 | 2018-10-19 | 北京航空航天大学 | A kind of main combustion stage uses the low pollution combustor of effervescent atomizer |
| CN105716119A (en) * | 2016-03-22 | 2016-06-29 | 北京航空航天大学 | Lean direct injection low-emission combustor adopting effervescent atomizers |
| CN106091013A (en) * | 2016-06-07 | 2016-11-09 | 中国科学院工程热物理研究所 | A kind of high temperature rise combustor structure of three stage layered burnings |
| CN108916911A (en) * | 2018-04-27 | 2018-11-30 | 北京航空航天大学 | A kind of pre-combustion grade uses the center classification low emission combustor head of pre- diaphragm plate structure |
| CN108916911B (en) * | 2018-04-27 | 2019-12-03 | 北京航空航天大学 | A kind of pre-combustion grade uses the center classification low emission combustor head of pre- diaphragm plate structure |
| CN109404966A (en) * | 2018-12-04 | 2019-03-01 | 新奥能源动力科技（上海）有限公司 | Chamber head part device and gas turbine |
| CN109404966B (en) * | 2018-12-04 | 2024-03-22 | 新奥能源动力科技（上海）有限公司 | Combustion chamber head device and gas turbine |
| CN109945233A (en) * | 2019-03-20 | 2019-06-28 | 中国航发湖南动力机械研究所 | Combustion chamber and its atomising device, aero gas turbine engine |
| CN112066415A (en) * | 2019-06-10 | 2020-12-11 | 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 |
| CN112066415B (en) * | 2019-06-10 | 2022-04-01 | 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 |
| CN113137636A (en) * | 2021-04-15 | 2021-07-20 | 中国航发湖南动力机械研究所 | Double-oil-way nozzle structure |
| CN113137636B (en) * | 2021-04-15 | 2022-05-17 | 中国航发湖南动力机械研究所 | Double-oil-way nozzle structure |
| CN115264534A (en) * | 2021-04-29 | 2022-11-01 | 中国航发商用航空发动机有限责任公司 | Swirler, flame tube and aeroengine |
| CN115264534B (en) * | 2021-04-29 | 2023-09-26 | 中国航发商用航空发动机有限责任公司 | Cyclone, flame tube and aeroengine |
| CN113251440A (en) * | 2021-06-01 | 2021-08-13 | 成都中科翼能科技有限公司 | Multi-stage partition type combustion structure for gas turbine |
| CN113251440B (en) * | 2021-06-01 | 2021-11-30 | 成都中科翼能科技有限公司 | Multi-stage partition type combustion structure for gas turbine |
| CN114719293A (en) * | 2022-03-24 | 2022-07-08 | 西北工业大学 | An annular cavity afterburner structure |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102200291B (en) | 2013-12-11 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102200291B (en) | Pneumatic primary level graded low-pollution combustion chamber | |
| CN101709884B (en) | Premixing and pre-evaporating combustion chamber | |
| CN101799174B (en) | Main combustible stage tangential oil supply premix and pre-evaporation combustion chamber | |
| CN101694301B (en) | Hedge Flame Combustion Chamber | |
| CN104406197B (en) | Low-emission reverse flow combustor adopting radial swirl injection and fuel oil grading schemes | |
| CN103123122B (en) | The lean premixed preevaporated low contamination combustion chamber that a kind of main fuel oil directly sprays | |
| WO2020001606A1 (en) | Low pollution combustor and combustion control method therefor | |
| EP2481982B2 (en) | Mixer assembly for a gas turbine engine | |
| CN100557317C (en) | A lean-fuel premixed pre-evaporation low-pollution combustor for an aero-engine | |
| CN102175045B (en) | Low-emission combustion chamber with main combustible stage head part multi-point slant oil taking | |
| CN102032597B (en) | Premixing pre-vaporization combustion chamber for main combustible stage of discrete pipe | |
| CN102901127B (en) | Premixing pre-evaporation low-pollution combustion chamber for main-combustion-stage double-layer pre-film three-cyclone | |
| CN108561897B (en) | Partial premixing and pre-evaporating ultralow emission combustion chamber for enhancing oil-gas mixing | |
| JP2002195563A (en) | Method and device for reducing burner emission | |
| CN101949551A (en) | Premix and pre-evaporation combustion chamber | |
| CN103697500B (en) | The premixed preevaporated low contamination combustion chamber of a kind of pair of pre-membrane type main combustion stage of oil circuit four eddy flow | |
| CN103185355B (en) | Premixing pre-evaporation low-pollution combustion chamber with multi-point axial double-stage air auxiliary atomizing nozzle main combustion stage | |
| US20150121882A1 (en) | Mixer assembly for a gas turbine engine | |
| CN103047683B (en) | Partial premixing and pre-evaporation combustion chamber with three-level oil passages | |
| CN105135478B (en) | A kind of main combustion stage uses the low pollution combustor of axially two-stage distributed cyclone | |
| CN108253455B (en) | Premixing and pre-evaporating ultra-low emission combustion chamber head and combustion chamber thereof | |
| CN102242939A (en) | Prefilming three-stage pre-mixing and pre-evaporating low-pollution combustor | |
| CN204372988U (en) | A kind of low emission reverse flow type combustor | |
| CN102889617B (en) | Premixing and pre-evaporation combustor for main combustion stage using radial film formation | |
| CN103629696B (en) | A kind of combustion chamber fuel oil sprays and mixing arrangement and combustion chamber thereof |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20131211 |