CN102200291B - Pneumatic primary level graded low-pollution combustion chamber - Google Patents
Pneumatic primary level graded low-pollution combustion chamber Download PDFInfo
- Publication number
- CN102200291B CN102200291B CN2011100765438A CN201110076543A CN102200291B CN 102200291 B CN102200291 B CN 102200291B CN 2011100765438 A CN2011100765438 A CN 2011100765438A CN 201110076543 A CN201110076543 A CN 201110076543A CN 102200291 B CN102200291 B CN 102200291B
- Authority
- CN
- China
- Prior art keywords
- main combustion
- combustion stage
- main
- combustion
- ring
- 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.)
- Active
Links
Images
Abstract
The invention discloses a pneumatic primary level graded low-pollution combustion chamber, which consists of a shunting diffuser, a combustion chamber outer case, a combustion chamber inner case, a fuel nozzle rod, a flame tube head, a flame tube outer wall and a flame tube inner wall, wherein the flame tube head mainly comprises a precombustion level, a main combustion level, an isolation section, a head splashing disc and a head end wall; the precombustion level stabilizes flame through a low-speed return flow zone generated by cyclone air which enters the combustion chamber through a cyclone assembly at the precombustion level; fuel at the main combustion level before a main combustion level graded ignition state is atomized under the action of airflow of an inner ring channel of the main combustion level; and the fuel after a main combustion level graded ignition state impacts the inner side of an inner ring of the main combustion level, and a pre-film vaporization mode is formed under the action of airflows of the inner ring and outer ring channels of the main combustion level. Therefore, main-level air fuel premixed gases before the main combustion level graded ignition state can stop for enough time in a main combustion zone, most of the main-level air fuel premixed gases after the combustion level graded ignition state do not enter the low-speed return flow zone stabilized flame, and complete combustion in the combustion chamber in various working states and reduction of pollution emission are guaranteed.
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, can guarantee that combustion chamber is in each state point efficient stable work, can both reach the purpose of the disposal of pollutants that reduces burning.
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 Trends of The Development of modern aeroengine combustion chamber is combustion with reduced pollutants.The aeroengine combustor buring chamber must meet the aero-engine emission standard of increasingly stringent.The CAEP6(Committee on Aviation Environmental Protection adopted at present) requirement of standard 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, at first GE has researched and developed dicyclo chamber combustion with reduced pollutants DAC(for GE90 and CFM56), PW company has adopted class RQL(fuel-rich combustion-put out soon-poor oil firing, Rich burn-Quench-Lean burn, be called for short RQL) low pollution combustor TALON II(is for PW4000 and 6000 series).Aspect low pollution combustor of future generation, GE company adopts LDM(Lean Direct Mixing Combustion, oil-poor direct hybrid combustor) the technology TAPS(Twin Annular Premixing Swirler that is its GEnx reseach of engine) low pollution combustor.This combustion chamber is in stand loopful verification experimental verification, and the NOx disposal of pollutants has reduced by 50% than CAEP2 discharge standard.It is TALON X that PW company has continued to adopt the RQL mode to propose the low pollution combustor that reduces the NOx disposal of pollutants, the head type adopted is the air atomizer spray nozzle of PW development of company, 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, for its engine rapids of new generation, reaches 1000.
And no matter be which kind of advanced person's low pollution combustor, its key technology reduces the NOx(nitrogen oxide exactly), the CO(carbon monoxide), the UHC(unburned hydrocarbons) and the combustion technology of smoldering, key problem is to reduce the temperature of combustion zone, make the combustion zone temperature field even simultaneously, the equivalent proportion that is whole and part is controlled, 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.Known according to mechanism and the result of the test of NOx and CO generation: the NOx that the primary zone equivalent proportion of combustion chamber produces in 0.6～0.8 scope and the discharge rule of CO(UHC and CO are similar) seldom.Based on this principle, take into account the discharge capacity of NOx and CO, UHC all 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.Current conventional combustion mode can't reduce NOx, CO and UHC.Reason is that the method for designing of current combustion chamber determines.For the conventional combustion chamber, when high power state, owing to adopting liquid mist diffusion combustion mode, the local equivalent proportion in combustion zone is always near 1, far away surpass the required equivalent proportion area requirement of above-mentioned combustion with reduced pollutants, although now the discharge of CO and UHC is low, it is maximum that the discharge 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, although now NOx discharge is low, CO and UHC discharge are very high again.In addition, because the conventional combustion chamber generally adopts diffusion combustion mode, local equivalent proportion is very inhomogeneous, therefore for the conventional combustion chamber, can't meet 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, this combustion chamber is meeting under each condition of work of aero-engine, can 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 fed by pre-combustion grade and main combustion stage, pre-combustion grade adopts swirl stabilized diffusion flame combustion method, and main combustion stage adopts the premix and pre-evaporation combustion method of the radial spray fuel feeding of pneumatic classification.Combustion chamber mainly is comprised 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, combustion chamber.The burner inner liner head mainly mainly is comprised 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 low speed recirculating zone that the pre-combustion grade utilization enters the rotational flow air generation of combustion chamber by the pre-combustion grade swirler assembly stabilizes the flame, pre-combustion grade swirler assembly and distance piece are threaded connection, 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, main combustion stage inward eddy device, the outer cyclone of main combustion stage, in main combustion stage outer shroud and main combustion stage, ring forms, 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 fuel nozzle distribution ring anchor ring, the main combustion stage nozzle is connected with the main combustion stage oil supply gallery, main combustion stage inward eddy device is welded on fuel nozzle and distributes the ring outside, in main combustion stage, boxing is connected on the main combustion stage inward eddy device outside, formed ring passage in main combustion stage between ring and fuel nozzle distribution ring in main combustion stage, the outer cyclone of main combustion stage is welded on the ring outside in 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 main combustion stage between ring, main combustion stage outer shroud and fuel nozzle distribute formation premix and pre-evaporation endless tube between ring, have main combustion stage outer shroud tangential admission groove on the main combustion stage outer shroud, fuel nozzle distributes ring and distance piece to be threaded connection, make 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 airflow function of ring passage atomization form fuel-air mixture, then flow 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 burner inner liner, major part stabilizes the flame and mixes with the low speed recirculating zone, when the rear state of main combustion stage classification point, except a part of fuel oil, in main combustion stage, encircle tunnel-shaped olefiant gas gaseous mixture, most of fuel oil is beaten the inboard of encircling 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 main combustion stage, 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 burner inner liner, under the igniting stabilized the flame in the low speed recirculating zone of pre-combustion grade, burnt, major part does not enter the low speed recirculating zone and stabilizes the 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, to main combustion stage nozzle and pre-combustion grade nozzle fuel feeding, the pre-combustion grade nozzle is threaded connection at fuel nozzle and distributes on ring, and the fuel nozzle bar is connected with outer combustion case.Head splash pan and head end wall welding, head end wall and burner inner liner outer wall are bolted, 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 is exactly mainly 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 the indoor whole combustion zone of control combustion, i.e. equivalent proportion uniformity, the excessive disposal of pollutants that also can greatly increase engine of local equivalent proportion caused 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, the use gas that makes to burn feeds combustion chamber from pre-combustion grade and main combustion stage respectively, and fuel oil is carried out to the classification infeed, control the equivalent proportion of fuel oil in combustion zone under aero-engine different operating state all in the combustion with reduced pollutants district, thereby reach the purpose that reduces the Air–pollution From Combustion emission.Pre-combustion grade state before the main pre-combustion grade classification points such as slow train starts, and keeps the equivalent proportion of the front state of main pre-combustion grade classification point combustion zone to drop in above-mentioned combustion with reduced pollutants equivalent proportion interval, and makes the good stability of burning, easily starts.When engine operation just starts main combustion stage after main pre-combustion grade classification point, before main combustion stage classification point during state, in main combustion stage, under the airflow function of ring passage, atomization forms fuel-air mixture, then flow 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 burner inner liner, major part stabilizes the flame and mixes with the low speed recirculating zone, the fuel-air mixture that guarantees main combustion stage has sufficient residence time, can completing combustion, thereby the efficiency of combustion of state before reducing near discharge amount of pollution classification point and improving main combustion stage classification point, after main combustion stage classification point, state encircles tunnel-shaped olefiant gas gaseous mixture in main combustion stage except a part of fuel oil, most of fuel oil is beaten the inboard of encircling 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 main combustion stage, 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 burner inner liner, under the igniting stabilized the flame in the low speed recirculating zone of pre-combustion grade, burnt, major part does not enter the low speed recirculating zone and stabilizes the flame, guarantee that the primary zone equivalent proportion is in the scope that discharge amount of pollution is less, thereby 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 reach sufficient burning under different conditions, simultaneously can carry out the equivalent proportion uniformity in control combustion district by controlling the main combustion stage mist of oil uniformity, degree of mixing and evaporativity, 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.
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 fed by pre-combustion grade and main combustion stage, and burner inner liner does not have primary holes, cold gas and mixed gas feed from burner inner liner, simplify chamber structure when increasing the combustion chamber effect.
(2) main combustion stage of the present invention adopts the combustion method of the premix and pre-evaporation of pneumatic classification.Pneumatic classification is simplified the main combustion stage structure when can under different conditions, obtain good fuel oil primary atomization effect, controls the main combustion stage gas mixture and obtain enough time of staying under different conditions in primary zone, forms uniform fuel-air mixture jet.After this strand of uniform fuel-air mixture jet 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 combustion method, main combustion stage adopts the premix and pre-evaporation combustion method of pneumatic classification, this combined burning pattern can realize the work of aeroengine combustor buring chamber efficient stable in broad working range, can realize the combustion chamber low pollution emission simultaneously.
The accompanying drawing explanation
Fig. 1 is structure cutaway view of the present invention;
Fig. 2 is burner inner liner head construction cutaway view of the present invention;
Fig. 3 is state work schematic diagram after main combustion stage classification point of the present invention;
Fig. 4 is state work schematic diagram before main combustion stage classification point of the present invention;
Fig. 5 is state work schematic diagram after burner inner liner head main combustion stage classification point of the present invention;
Fig. 6 is state work schematic diagram before 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 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;
Structural representation and cutaway view that Figure 10 is the outer cyclone of main of the present invention and main inward eddy device;
Figure 11 is pre-combustion grade swirler assembly schematic diagram of the present invention;
In figure: 1. shunting diffuser, 2. outer combustion case, 3. burner inner liner outer wall, 4. casing in 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 pan, 13. distance piece, 14. combustion chamber inlet air flow, 15. burner inner liner head air-flow, 16. main combustion stage outer shroud tangential gas flow, 17. main combustion stage axial flow, 18. pre-combustion grade air-flow, 19. combustion chamber ring cavity air-flow, 20. blending air-flow, 21. combustor exit air-flow, 22. state main combustion stage flame after main combustion stage classification point, 23. the low speed recirculating zone stabilizes the flame, 24. pre-combustion grade swirler assembly, 25. state main combustion stage flame before main combustion stage classification point, 26. state fuel-air mixture before main combustion stage classification point, 27. pre-combustion grade fuel oil liquid mist, 28. after main combustion stage classification point, the state main is broken the wall fuel oil, 29. state fuel-air mixture before main combustion stage classification point, 30. main combustion stage oil circuit, 31. pre-combustion grade oil circuit, 32. fuel nozzle distributes ring main combustion stage pipe, 33. main combustion stage oil supply gallery, 34. pre-combustion grade oil supply gallery, 35. main combustion stage nozzle, 36. fuel nozzle distributes ring, 37. the stifled ring of main combustion stage fuel feeding, 38. pre-combustion grade nozzle, 39. main combustion stage inward eddy device, 40. the outer cyclone of main combustion stage, 41. main combustion stage outer shroud tangential admission groove, 42. main combustion stage outer shroud, 43. ring in main combustion stage, 44. pre-combustion grade one-level cyclone, 45. pre-combustion grade second cyclone, 46. ring passage in main combustion stage, 47. premix and pre-evaporation endless tube, 48. main combustion stage outer ring channel.
The specific embodiment
As depicted in figs. 1 and 2, the present invention adopts the fractional combustion mode, the burning gas consumption is all fed by pre-combustion grade 10 and main combustion stage 9, and pre-combustion grade 10 adopts swirl stabilized diffusion flame combustion method, and main combustion stage 9 adopts the premix and pre-evaporation combustion method of the radial spray fuel feeding of pneumatic classification.Combustion chamber mainly is comprised 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, combustion chamber.Burner inner liner head 7 mainly mainly is comprised 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 is connected with outer combustion case 2.Head splash pan 12 and head end wall 11 welding, head end wall 11 is bolted with burner inner liner outer wall 3 and burner inner liner inwall 5, and head end wall 11 is located by connecting by radial and axial with main combustion stage outer shroud 42.The type of cooling of burner inner liner outer wall 3 and burner inner liner inwall 5 adopt air film cooling, disperse cooling or Compound cooling mode, wall surface temperature is controlled to the life-span of prolongation burner inner liner.
As Fig. 2,3,4,5, shown in 6, shunting diffuser 1 is divided into three strands by 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 burner inner liner inwall 5 from burner inner liner blending hole 8, with control combustion chamber outlet temperature, distributes.Burning use gas is all fed 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 fed by main combustion stage 9.Pre-combustion grade swirler assembly 24 is threaded connection with distance piece 13, 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.The low speed recirculating zone that pre-combustion grade 10 utilizations enter the rotational flow air generation of combustion chamber by pre-combustion grade swirler assembly 24 stabilizes the flame 23.After the required fuel oil of main combustion stage 9 is sprayed by main combustion stage nozzle 35, before main combustion stage classification point during state at first in main combustion stage under the airflow function of ring passage 46 atomization form the front state fuel-air mixture 26 of main combustion stage classification point, then flow into evaporation in premix and pre-evaporation endless tube 47, 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, burn under the low speed recirculating zone of pre-combustion grade 10 stabilizes the flame 23 igniting and form state main combustion stage flame 25 before main combustion stage classification point, major part stabilizes the flame 23 with the low speed recirculating zone and mixes, before making main combustion stage classification point, state fuel-air mixture 26 can access the sufficient time of staying, thereby reach the efficiency of combustion that improves the front state of main combustion stage classification point, reduce the purpose of the discharge amount of pollution of the front state of main combustion stage classification point, after main combustion stage classification point, state encircles in main combustion stage except a part of fuel oil passage 46 formation fuel-air mixtures, most of fuel oil is beaten the inboard of ring 43 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 in main combustion stage, evaporation in premix and pre-evaporation endless tube 47, and with the further blending of air, form uniform main combustion stage classification point in the exit of premix and pre-evaporation endless tube 47 after, state fuel-air mixture 29 enters burner inner liner outer wall 3 and burner inner liner inwall 5 inside, in the low speed recirculating zone of pre-combustion grade 10, stabilizing the flame under 23 igniting burns forms main combustion stage classification point state main combustion stage flame 22 afterwards, major part does not enter the low speed recirculating zone and stabilizes the flame 23, thereby after guaranteeing main combustion stage classification point, thereby state fuel-air mixture 29 reaches the reduction disposal of pollutants by primary zone as early as possible, the purpose that particularly NOx discharges.
As Fig. 7,8,9, shown in 10, main combustion stage 9 comprises that fuel nozzle distributes ring 43 in ring 36, the stifled ring 37 of main combustion stage fuel feeding, main combustion stage inward eddy device 39, the outer cyclone 40 of main combustion stage, main combustion stage outer shroud 42 and main combustion stage 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 is connected 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 axis of the fuel nozzle distribution ring 36 at main combustion stage nozzle 35 places and the axis of pre-combustion grade nozzle 38 are on same straight line, quantity 0<the p of main combustion stage nozzle 35≤50, main combustion stage nozzle corner cut is-90～90 degree.Main combustion stage inward eddy device 39 is welded on fuel nozzle and distributes ring 36 outsides, in main combustion stage, ring 43 is welded on main combustion stage inward eddy device 39 outsides, formed ring passage 46 in main combustion stage between ring 43 and fuel nozzle distribution ring 36 in main combustion stage, the outer cyclone 40 of main combustion stage is welded on ring 43 outsides in main combustion stage, main combustion stage outer shroud 42 is welded on the outer cyclone of main combustion stage 40 outsides, form main combustion stage outer ring channel 48 in main combustion stage outer shroud 42 and main combustion stage between ring 43, main combustion stage outer shroud 42 and fuel nozzle distribute formation premix and pre-evaporation endless tube 47 between ring 36, have main combustion stage outer shroud tangential admission groove 41 on 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 main combustion stage inward eddy device 39 and main combustion stage adopts; 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 main combustion stage outer shroud tangential admission groove 41 of main combustion stage outer shroud 42 is 10 °～80 °, identical or contrary with outer cyclone 40 rotation directions of main combustion stage.Fuel nozzle distributes ring 36 and distance piece 13 to be threaded connection, 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 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 is threaded connection at fuel nozzle and distributes on ring 36.
Progression 1≤the n of the cyclone that as shown in figure 11, pre-combustion grade swirler assembly 24 adopts≤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 first connect into an integral body, with distance piece 13, are connected 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 mode with second cyclone 45, and second cyclone 45 is threaded connection with distance piece 13, makes main combustion stage 9 and pre-combustion grade 10 interconnect.Pre-combustion grade swirler assembly 24 is threaded connection with distance piece 13, 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 jet.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 main combustion stage inward eddy device 39 and main combustion stage adopts; It is axial swirler that every grade of cyclone adopts the structure of cyclone, and rotation direction is selected in the same way; The tangential angle of main combustion stage outer shroud tangential admission groove 41 of main combustion stage outer shroud 42 is 30 °, identical with outer cyclone 40 rotation directions of main combustion stage.Fuel nozzle distributes ring 36 and distance piece 13 to be threaded connection, and makes main combustion stage 9 and pre-combustion grade 10 interconnect.Installation process intermediate fuel oil jet stem 6 is packed into together with pre-combustion grade 10 with main combustion stage 9 in combustion chamber, with head end wall 11 axially and radial location, form burner inner liner head 7.Head splash pan 12 and head end wall 11 welding, head end wall 11 is bolted with burner inner liner outer wall 3 and burner inner liner inwall 5.The low speed recirculating zone that pre-combustion grade 10 produces stabilizes the flame 23.After the required fuel oil of main combustion stage 9 is sprayed by main combustion stage nozzle 35, before main combustion stage classification point state at first in main combustion stage under the airflow function of ring passage 46 atomization form the front state fuel-air mixture 26 of main combustion stage classification point, burn under the low speed recirculating zone of pre-combustion grade 10 stabilizes the flame 23 igniting and form state main combustion stage flame 25 before main combustion stage classification point, major part stabilizes the flame 23 with the low speed recirculating zone and mixes, before making main combustion stage classification point, state fuel-air mixture 26 can access the sufficient time of staying, thereby reach the efficiency of combustion that improves the front state of main combustion stage classification point, reduce the purpose of the discharge amount of pollution of the front state of main combustion stage classification point, after main combustion stage classification point, state encircles in main combustion stage except a part of fuel oil passage 46 formation fuel-air mixtures, most of fuel oil is beaten the inboard of ring 43 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 in main combustion stage, form uniform main combustion stage classification point in the exit of premix and pre-evaporation endless tube 47 after, state fuel-air mixture 29 enters burner inner liner outer wall 3 and burner inner liner inwall 5 inside, in the low speed recirculating zone of pre-combustion grade 10, stabilizing the flame under 23 igniting burns forms main combustion stage classification point state main combustion stage flame 22 afterwards, major part does not enter the low speed recirculating zone and stabilizes the flame 23, thereby after guaranteeing main combustion stage classification point, thereby state fuel-air mixture 29 reaches the reduction disposal of pollutants by primary zone as early as possible, the purpose that particularly NOx discharges.The low pollution combustor that adopts as can be seen here 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, under blending hole air-flow auxiliary, also can obtain outlet temperature distribution performance preferably.
Non-elaborated part of the present invention belongs to general knowledge known in this field.
The above is only the preferred embodiment of the present invention; it should be pointed out that for those skilled in the art, under the premise without departing from the principles 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 (9)
1. a 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 comprised 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), combustion chamber, described burner inner liner head (7) mainly is comprised of pre-combustion grade (10), main combustion stage (9), distance piece (13), head splash pan (12) and head end wall (11), the burning gas consumption is all fed by pre-combustion grade (10) and main combustion stage (9), described pre-combustion grade (10) adopts swirl stabilized diffusion flame combustion method, and described pre-combustion grade (10) comprises pre-combustion grade swirler assembly (24) and pre-combustion grade nozzle (38), the low speed recirculating zone that the rotational flow air entered by pre-combustion grade swirler assembly (24) produces stabilizes the flame (23), 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 combustion method of the radial spray fuel feeding of pneumatic classification, and main combustion stage (9) comprises that fuel nozzle distributes ring (43) in ring (36), the stifled ring of main combustion stage fuel feeding (37), main combustion stage inward eddy device (39), the outer cyclone (40) of main combustion stage, main combustion stage outer shroud (42) and 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) is connected with main combustion stage oil supply gallery (33), main combustion stage inward eddy device (39) is welded on fuel nozzle and distributes ring (36) outside, in main combustion stage, ring (43) is welded on main combustion stage inward eddy device (39) outside, formed ring passage (46) in main combustion stage in main combustion stage between ring (43) and fuel nozzle distribution ring (36), the outer cyclone (40) of main combustion stage is welded on ring (43) outside in 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 main combustion stage between ring (43), main combustion stage outer shroud (42) and fuel nozzle distribute formation premix and pre-evaporation endless tube (47) between ring (36), have main combustion stage outer shroud tangential admission groove (41) on main combustion stage outer shroud (42), fuel nozzle distributes ring (36) and distance piece (13) to be threaded connection, make main combustion stage (9) and pre-combustion grade (10) interconnect by distance piece (13), after the required fuel oil of main combustion stage (9) is sprayed by main combustion stage nozzle (35), at first encircle atomization under the airflow function of passage (46) before main combustion stage classification point during state and form the front state fuel-air mixture (26) of main combustion stage classification point in main combustion stage, then flow into evaporation in premix and pre-evaporation endless tube (47), 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, burn under the low speed recirculating zone of pre-combustion grade (10) stabilizes the flame the igniting of (23) and form state main combustion stage flame (25) before main combustion stage classification point, major part stabilizes the flame (23) with the low speed recirculating zone and mixes, before making main combustion stage classification point, state fuel-air mixture (26) can access the sufficient time of staying, thereby reach the efficiency of combustion that improves the front state of main combustion stage classification point, reduce the purpose of the discharge amount of pollution of the front state of main combustion stage classification point, after main combustion stage classification point, state encircles in main combustion stage except a part of fuel oil passage (46) formation fuel-air mixture, most of fuel oil is beaten the inboard of ring (43) in main combustion stage, encircle in main combustion stage 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 in the exit of premix and pre-evaporation endless tube (47) after, state fuel-air mixture (29) enters burner inner liner outer wall (3) and burner inner liner inwall (5) inside, in the low speed recirculating zone of pre-combustion grade (10), stabilizing the flame under the igniting of (23) burns forms main combustion stage classification point state main combustion stage flame (22) afterwards, major part does not enter the low speed recirculating zone and stabilizes the flame (23), thereby guarantee main combustion stage classification point afterwards state fuel-air mixture (29) thus reach the reduction disposal of pollutants by primary zone as early as possible, the purpose that particularly NOx discharges, 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, to main combustion stage nozzle (35) and pre-combustion grade nozzle (38) fuel feeding, pre-combustion grade nozzle (38) is threaded connection at fuel nozzle and distributes on ring (36), fuel nozzle bar (6) is connected with outer combustion case (2).Head splash pan (12) and head end wall (11) welding, head end wall (11) is bolted with burner inner liner outer wall (3) and burner inner liner inwall (5), 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: at described burner inner liner outer wall (3) and burner inner liner inwall (5) rear portion, be provided with burner inner liner blending hole (8), blending air-flow (20) enters in burner inner liner outer wall (3) and burner inner liner inwall (5) from burner inner liner blending hole (8), with control combustion chamber outlet temperature, distributes.
3. 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 by 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 meet the demand of combustion chamber each several part to air mass flow.
4. a kind of low pollution combustor that adopts pneumatic main classification according to claim 1, it is characterized in that: described pre-combustion grade nozzle (38) is pressure atomized fog jet, pneumatic nozzle or combined nozzle.
5. 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 first connect into an integral body, with distance piece (13), are connected after forming pre-combustion grade swirler assembly (24) again.
6. 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 axis of the fuel nozzle distribution ring (36) at main combustion stage nozzle (35) place and the axis of pre-combustion grade nozzle (38) are on 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.
7. 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 described main combustion stage inward eddy device (39) and main combustion stage adopts; 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 °, identical or contrary with outer cyclone (40) rotation direction of main combustion stage.
8. a kind of low pollution combustor that adopts pneumatic main classification according to claim 1, it is characterized in that: the burning use gas of described combustion chamber is all fed 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 fed by main combustion stage (9).
9. 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 air film cooling, disperse cooling or Compound cooling mode, wall surface temperature is controlled to the life-span of prolongation 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 CN102200291A (en) | 2011-09-28 |
| CN102200291B true CN102200291B (en) | 2013-12-11 |
Family
ID=44661168
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011100765438A Active 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) |
Families Citing this family (17)
| 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 | Fuel and air mixing device for low-pollution burning chamber of gas turbine |
| 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 |
| CN103343985B (en) * | 2013-06-21 | 2015-07-08 | 北京航空航天大学 | Double-pre-film pneumatic nebulization low pollution combustor head structure |
| CN105202580A (en) * | 2015-10-16 | 2015-12-30 | 北京航空航天大学 | Low-pollution combustion chamber adopting forced diversion at primary combustion stage outlet |
| 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 |
| CN105716119B (en) * | 2016-03-22 | 2018-10-19 | 北京航空航天大学 | A kind of oil-poor direct injection low pollution combustor using 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 |
| CN106091013B (en) * | 2016-06-07 | 2018-08-10 | 中国科学院工程热物理研究所 | A kind of high temperature rise combustor structure of three-level stratified combustion |
| 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 |
| 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 |
| CN109945233B (en) * | 2019-03-20 | 2021-01-29 | 中国航发湖南动力机械研究所 | Combustion chamber, atomization device thereof and aviation gas turbine engine |
| 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 |
| 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 |
| 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 |
| 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 |
| CN114719293B (en) * | 2022-03-24 | 2023-05-26 | 西北工业大学 | Annular cavity afterburner structure |
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 active Active
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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102200291A (en) | 2011-09-28 |
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) | Counter-flow flame combustion chamber | |
| CN102175045B (en) | Low-emission combustion chamber with main combustible stage head part multi-point slant oil taking | |
| CN206281000U (en) | Pre-combustion grade uses the low emission combustor of double-deck axial swirler | |
| CN102901127B (en) | Premixing pre-evaporation low-pollution combustion chamber for main-combustion-stage double-layer pre-film three-cyclone | |
| CN102242939B (en) | Prefilming three-stage pre-mixing and pre-evaporating low-pollution combustor | |
| CN102022753B (en) | Low-pollution combustion chamber with premixed and pre-evaporated precombustion part | |
| CN206281002U (en) | Main combustion stage uses the low pollution combustor of the pre- reverse eddy flow of film radial direction two-stage of individual layer | |
| CN102032597B (en) | Premixing pre-vaporization combustion chamber for main combustible stage of discrete pipe | |
| CN105135478B (en) | A kind of main combustion stage uses the low pollution combustor of axially two-stage distributed cyclone | |
| CN102889617B (en) | Premixing and pre-evaporation combustor for main combustion stage using radial film formation | |
| CN101949551A (en) | Premix and pre-evaporation combustion chamber | |
| CN102242940B (en) | Three-stage structured pre-mixing and pre-evaporating low-pollution combustor | |
| JP2002195563A (en) | Method and device for reducing burner emission | |
| CN104406197A (en) | Low-emission reverse flow combustor adopting radial swirl injection and fuel oil grading schemes | |
| CN103185355B (en) | Premixing pre-evaporation low-pollution combustion chamber with multi-point axial double-stage air auxiliary atomizing nozzle main combustion stage | |
| CN101169252A (en) | Aerial engine lean premixed preevaporated low contamination combustion chamber | |
| CN103047683B (en) | Partial premixing and pre-evaporation combustion chamber with three-level oil passages | |
| CN104456628A (en) | Layered part premixing low-pollution combustor of main combustion level lean oil premixing | |
| CN103335333B (en) | Single-oil passage pre-diaphragm type staggered plate primary combustion stage premixing and pre-vaporizing low-pollution combustor | |
| CN108253455B (en) | Premixing and pre-evaporating ultra-low emission combustion chamber head and combustion chamber thereof | |
| CN104676648B (en) | Center fractionation based low-pollution combustor with RQL (rich burn-quench-lean burn) precombustion fraction and LPP (lean premixed prevaporized) main combustion fraction | |
| CN101285592A (en) | Integral fuel jet axial swirler pre-mixing preevaporated low pollution combustion-chamber |
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 |