CN101799174B - Main combustible stage tangential oil supply premix and pre-evaporation combustion chamber - Google Patents
Main combustible stage tangential oil supply premix and pre-evaporation combustion chamber Download PDFInfo
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Abstract
The invention relates to a main combustion stage tangential oil supply premix and pre-evaporation combustion chamber. The combustion chamber is in a single-ring chamber structure and is designed by adopting the conceptual design of staging combustion, and all the used amount of gas for combustion is supplied by the precombustion stage and the main combustion stage. The combustion chamber mainly comprises a flow-dividing type diffuser, a combustion chamber outer case, a combustion chamber inner case, a fuel nozzle, the precombustion stage, the main combustion stage, a flame tube outer wall and a flame tube inner wall. The precombustion stage utilizes a low-speed flow returning zone generated by swirl air entering the combustion chamber by a precombustion stage swirler component; the fuel needed by the main combustion stage is ejected by the tangential main combustion stage nozzle, is atomized under the air flow effect generated by entering of atomized air of the main combustion stage nozzle into a pipe, then flows into a premix and pre-evaporation ring pipe for evaporation, and is further blended with air; and even oil-gas mixed gas formed at the outlet of the premix and pre-evaporation ring pipe enters a flame tube and combusts under the pilot combustion of the precombustion stage flame. The combustion chamber has simple structure, and can effectively reduce the discharge of pollution simultaneously while guaranteeing that an aeroengine is in normal working state.
Description
Technical field
The present invention relates to a kind of aero-gas turbine combustion chamber of adopting premix and pre-evaporation burning organizational form; Adopt the chamber structure of this premix and pre-evaporation burning organizational form simple; When guaranteeing combustion chamber efficient stable work, can reduce the disposal of pollutants of 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 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 EnvironmentalProtection) standard that adopts at present is very strict; Particularly to the NOx emission requirement; And Along with people's is to the enhancing of environmental protection consciousness, and 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 a type 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 AnnularPremixing Swirler) low pollution combustor of its GEnx reseach of engine that GE company adopts LDM (Lean Direct MixingCombustion, 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 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 with 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 and result of the test according to NOx and CO generation 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; Two factors of considered: 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 of fuel particles diameter Distribution, the i.e. distributing homogeneity of SMD; Second be the uniformity that the fuel oil oil mist concentration distributes.Say 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, the discharging of NOx reaches maximum.When low power state, the combustion zone equivalent proportion is very low again, and is interval far below the required equivalent proportion of above-mentioned combustion with reduced pollutants, 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 aeroengine combustor buring chamber of adopting the premix and pre-evaporation burning organizational form of main combustible stage tangential oil supply is provided; Is satisfying under the condition of work of aero-engine this combustion chamber; Can effectively reduce the disposal of pollutants of aeroengine combustor buring chamber burning; Comprise NOx, smolder, CO and UHC, and simple in structure.
Technical solution of the present invention: the premix and pre-evaporation combustion chamber of main combustible stage tangential oil supply 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 level; Pre-combustion grade adopts swirl stabilized diffusion flame burning organizational form, and main combustion level adopts the premix and pre-evaporation burning organizational form of tangential oil supply, and cold gas and mixed gas infeed from burner inner liner.The premix and pre-evaporation combustion chamber of main combustible stage tangential oil supply mainly is made up of casing, fuel nozzle, 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 is made up of pre-combustion grade and main combustion level: pre-combustion grade comprises deflector in pre-combustion grade swirler assembly, pre-combustion grade nozzle, pre-combustion grade head end wall and the pre-combustion grade head; Pre-combustion grade is utilized the low speed recirculating zone retention flame that is got into the rotational flow air generation of combustion chamber by the pre-combustion grade swirler assembly; The pre-combustion grade swirler assembly is connected through encircling in pre-combustion grade head end wall and the main combustion level premix and pre-evaporation section; The pre-combustion grade nozzle is positioned at the pre-combustion grade swirler assembly; And coaxial with the pre-combustion grade swirler assembly, deflector links to each other with the pre-combustion grade head end wall in the pre-combustion grade head; Main combustion level comprises main combustion level nozzle, main combustion level premix and pre-evaporation section, the main whole end wall of combustion level head and the whole deflector of main combustion level head; Main combustion level premix and pre-evaporation Duan Youzhu combustion level premix and pre-evaporation endless tube gets into pipe with main combustion level nozzle atomization air and forms; Main combustion level nozzle is positioned at main combustion level nozzle atomization air and gets into tube inlet; And coaxial with main combustion level nozzle atomization air entering pipe, main combustion level nozzle is employed in the spray regime that a plurality of single fuel nozzles are set on the same circumference, and the center of circle of this circumference is positioned on the axis of pre-combustion grade nozzle; The single-nozzle quantity that main combustion level nozzle adopts is corresponding with the quantity that main combustion level nozzle atomization air gets into pipe; Main combustion grade required fuel oil is at first fired the aerodynamic atomization formation fuel-air mixture that grade nozzle atomization air gets into pipe by the master after firing the ejection of level nozzle by the master, then inflow master combustion level premix and pre-evaporation endless tube; Fuel-air mixture evaporates in main combustion level premix and pre-evaporation endless tube; And with the further blending of air, form uniform fuel-air mixture jet in the exit of main combustion level premix and pre-evaporation endless tube and get in the burner inner liner, under the igniting of pre-combustion grade flame, burn; Main combustion level premix and pre-evaporation section links to each other with the burner inner liner outer wall with the burner inner liner outer wall through the whole end wall of main combustion level head, and the whole deflector of main combustion level head links to each other with the whole end wall of main combustion level head; The pre-combustion grade nozzle all is connected on the fuel nozzle seat with main combustion level nozzle, links to each other with outer combustion case through the fuel nozzle seat.
Principle of the present invention is: generally speaking, the realization of aeroengine combustor buring chamber low pollution emission mainly is exactly through two aspects, and the one, control the regional overall equivalent proportion scope of whole combustion chamber internal combustion; 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 level respectively; And fuel oil carried out classification infeed, the equivalent proportion of control 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 starts under little states such as slow train, and the equivalent proportion of combustion zone drops in the above-mentioned combustion with reduced pollutants equivalent proportion interval when keeping little state, and makes the good stability of burning, starts easily.When engine operation just starts main combustion level during at big state, main combustion level adopts the premix and pre-evaporation burning organizational form of tangential oil supply, and the equivalent proportion of control combustion zone is interval in above-mentioned combustion with reduced pollutants equivalent proportion.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; Can control the equivalent proportion uniformity of combustion zone through controlling the main combustion level mist of oil uniformity, degree of mixing and evaporativity simultaneously, the disposal of pollutants of aero-engine low pollution combustor is low, the performance requirement of good stability thereby reach.
The present invention's advantage compared with prior art is following:
(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 level, 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 level of the present invention adopts the burning organizational form of the premix and pre-evaporation of tangential oil supply.Tangential oil supply can be simplified main combustion level structure when obtaining good fuel oil primary atomization effect, premix and pre-evaporation can make fuel oil and the air after the atomizing further mix, and forms 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 level adopts the premix and pre-evaporation burning organizational form of tangential oil supply; 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 work sketch map of the present invention;
Fig. 2 is a structure cutaway view of the present invention;
Fig. 3 is a burner inner liner head construction cutaway view of the present invention;
Fig. 4 is a main combustion level premix and pre-evaporation section modular construction sketch map of the present invention;
Fig. 5 is a main combustion level premix and pre-evaporation section modular construction cutaway view of the present invention;
Fig. 6 is a pre-combustion grade modular construction sketch map of the present invention;
Fig. 7 is a pre-combustion grade modular construction cutaway view of the present invention;
Fig. 8 is a pre-combustion grade swirler assembly structural representation of the present invention;
Fig. 9 is a pre-combustion grade swirler assembly structure cutaway view of the present invention;
Figure 10 is a specific embodiments burner inner liner structural representation of the present invention;
The fuel nozzle structural representation that Figure 11 adopts for the present invention;
The main combustion level nozzle ejection mode sketch map that Figure 12 adopts for the present invention.
Among the figure: 1. combustion chamber inlet air flow, 2. burner inner liner head air-flow, 3. ring cavity air-flow outside the combustion chamber, 4. ring cavity air-flow in the combustion chamber, 5. combustor exit air-flow; 6. combustion level combustion zone, 8. shunting diffuser, 9. outer combustion case, 10. a casing in the combustion chamber are 7. led in the pre-combustion grade combustion zone; 11. fuel nozzle, the whole end wall of 12. main combustion level heads, the whole deflector of 13. main combustion level heads, 14. burner inner liner heads, 15. burner inner liner outer walls; 16. the burner inner liner inwall, 17. burner inner liner outer wall blending hole, 18. burner inner liner inwall blending hole, 19. diffusion cooling hole, 20. pre-combustion grade; 21. main combustion level premix and pre-evaporation section, 22. pre-combustion grade swirler assemblies, 23. pre-combustion grade head end wall, 24. pre-combustion grade head deflectors, 25. pre-combustion grade one-level cyclones; 26. pre-combustion grade one-level cyclone pressing plate, 27. pre-combustion grade second cyclones, 28. main combustion level premix and pre-evaporation endless tubes, 29. main combustion level nozzle atomization air get into pipe; 30. the pre-combustion grade nozzle, 31. main combustion level nozzles, 32. fuel nozzle seats, 33. main combustion levels.
The specific embodiment
As depicted in figs. 1 and 2; The premix and pre-evaporation combustion chamber of the tangential oil supply of the present invention's design 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 level, and pre-combustion grade adopts swirl stabilized diffusion flame burning organizational form; Main combustion level adopts the burning organizational form of the premix and pre-evaporation of tangential oil supply, and cold gas and mixed gas infeed from burner inner liner.This combustion chamber comprises two combustion zones---pre-combustion grade combustion zone 6 and main combustion level combustion zone 7; Two shared identical inner and outer boundaries in combustion zone; The external boundary of combustion zone is a burner inner liner outer wall 15; The inner boundary of combustion zone is a burner inner liner inwall 16, and burner inner liner outer wall 15 and the burner inner liner inwall 16 of annular is in the outer combustion case 9 of annular and combustion chamber between the casing 10.On burner inner liner outer wall 15, arrange to have burner inner liner outer wall blending hole 17; On burner inner liner inwall 16, arrange to have burner inner liner inwall blending hole 18; Blending usefulness gas is used to regulate the combustor exit Temperature Distribution through burner inner liner outer wall blending hole 17 and burner inner liner inwall blending hole 18 entering combustion chambers.Burner inner liner outer wall 15 also arranges to have cooling, the type of cooling can adopt the air film cooling, disperse the cooling or the compound type of cooling with burner inner liner inwall 16, is used to cool off the burner inner liner wall, guarantees the life-span of combustion chamber.In specific embodiments, the type of cooling of burner inner liner outer wall 15 and burner inner liner inwall 16 adopts disperses cooling, has diffusion cooling hole 19 at burner inner liner outer wall 15 and burner inner liner inwall 16, and the signal of diffusion cooling hole 19 is as depicted in figs. 1 and 2.
At the upper reaches of pre-combustion grade combustion zone 6 are burner inner liner heads 14, and burner inner liner head 14 comprises pre-combustion grade 20 and main combustion level 39, and burner inner liner head 14 is as shown in Figure 3.
Main combustion level 33 comprises main combustion level nozzle 31, main combustion level premix and pre-evaporation section 21, the main whole end wall 12 of combustion level head and the whole deflector 13 of main combustion level head.Main combustion level premix and pre-evaporation section 21 is connected with burner inner liner inwall 16 with burner inner liner outer wall 15 through the whole end wall 12 of main combustion level head, and connected mode can be welding or screw thread or bolt.Main combustion level premix and pre-evaporation section 21 gets into pipe 29 by main combustion level premix and pre-evaporation endless tube 28 with main combustion level nozzle atomization air and forms like Fig. 4 and shown in Figure 5.Air admission hole shape on the main combustion level premix and pre-evaporation endless tube 28 can be circular hole or half hole or square hole or groove, and the angle of perforate is-90～90 degree.Specific embodiments such as Fig. 4 and shown in Figure 5 are that circular hole is an example with the air admission hole on the main combustion level premix and pre-evaporation endless tube 28.During installation; Main combustion level nozzle atomization air entering pipe 29 and main combustion grade premix and pre-evaporation endless tube 28 are adopted the connected mode of whole manufacturings or screw thread or bolt or welding; Be combined into main combustion level premix and pre-evaporation section 21, can accomplish the installation of main combustion level premix and pre-evaporation section 21.
Pre-combustion grade 20 comprises pre-combustion grade swirler assembly 22, pre-combustion grade nozzle 30, pre-combustion grade head end wall 23, pre-combustion grade head deflector 24, and pre-combustion grade 20 is like Fig. 6 and shown in Figure 7, and pre-combustion grade swirler assembly 22 is like Fig. 8 and shown in Figure 9.Pre-combustion grade swirler assembly 22 is connected through ring 29 in pre-combustion grade head end wall 23 and the main combustion level premix and pre-evaporation section.Pre-combustion grade head end wall 23 is fired the mode that grade connected mode of the interior ring 29 of premix and pre-evaporation section can adopt whole manufacturing or screw thread or bolt or welding with the master.Progression 1≤n≤5 of the cyclone that pre-combustion grade swirler assembly 22 adopts.It can be axial swirler that every grade of cyclone can adopt the structure of cyclone, also can be radial swirler, also can be the tangential swirl device.When the progression n=1 of pre-combustion grade swirler assembly 22, can adopt the connected mode of welding or bolt or screw thread that cyclone directly is connected with pre-combustion grade head end wall 23; When the progression 1＜n of pre-combustion grade swirler assembly 18≤5; When guaranteeing that cyclones at different levels are coaxial; Adopt the connected mode of welding or bolt or screw thread that cyclones at different levels are connected into an integral body earlier, be connected with pre-combustion grade head end wall 23 again behind the composition pre-combustion grade swirler assembly 22.In specific embodiments; Adopting the second cyclone scheme with pre-combustion grade swirler assembly 22 is example; Like Fig. 6, Fig. 7, Fig. 8 and shown in Figure 9, pre-combustion grade swirler assembly 22 comprises pre-combustion grade one-level cyclone 25, pre-combustion grade one-level cyclone pressing plate 26 and pre-combustion grade second cyclone 27.During installation, at first adopt the mode of whole manufacturing or screw thread or bolt or welding that pre-combustion grade head end wall 23 and main combustion level premix and pre-evaporation endless tube 28 are linked together; Adopt the mode of screw thread or bolt or welding to be connected pre-combustion grade head deflector 24 then with pre-combustion grade head end wall 23; When guaranteeing that pre-combustion grade one-level cyclone 25 and pre-combustion grade second cyclone 27 are coaxial; Adopt welding or screw thread or bolted mode; Pre-combustion grade one-level cyclone pressing plate 26 and pre-combustion grade second cyclone 27 are linked together; And pre-combustion grade one-level cyclone 25 is clipped between pre-combustion grade one-level cyclone pressing plate 26 and the pre-combustion grade second cyclone 27, makes three parts connect into as a whole composition pre-combustion grade swirler assembly 22; Adopt welding or screw thread or bolted mode that pre-combustion grade swirler assembly 22 is fixed on the pre-combustion grade head end wall 23 then; Be connected the interior ring of pre-combustion grade swirler assembly 22 through pre-combustion grade head end wall 23 with main combustion level premix and pre-evaporation endless tube 28; Pre-combustion grade swirler assembly 22 and main combustion level premix and pre-evaporation section 21 are connected and fixed, thus the installation of completion pre-combustion grade 20.
After main combustion level premix and pre-evaporation section 21 and 22 installations of pre-combustion grade swirler assembly, insert main combustion level nozzle 31 and pre-combustion grade nozzle 30 at correspondence position, thereby accomplish the installation of burner inner liner head 14.
As depicted in figs. 1 and 2; Pre-combustion grade nozzle 30 all is installed on the fuel nozzle seat 32 with main combustion level nozzle 31; Be combined into the fuel nozzle 11 of an integral body, after the installation of accomplishing burner inner liner head 14, stretch into the combustion chamber from the opening part of outer combustion case 9; Insert correspondence position, thereby accomplish the installation of combustion chamber.Pre-combustion grade nozzle 30 can be a pressure atomized fog jet with the single fuel nozzle (34) that main combustion level nozzle 31 adopts, and can be pneumatic nozzle, also can be combined nozzle.Fuel nozzle 11 structures in the specific embodiments are shown in figure 11.Pre-combustion grade nozzle 30 is corresponding with pre-combustion grade one-level cyclone 25, and the axis of the axis of pre-combustion grade nozzle 30 and pre-combustion grade one-level cyclone 25 coincides.Main combustion level nozzle 31 is positioned at main combustion level nozzle atomization air and gets into pipe 29 inlets; And it is coaxial with main combustion level nozzle atomization air entering pipe 29; Main combustion level nozzle 31 is employed in the spray regime that a plurality of single fuel nozzles 34 are set on the same circumference; The center of circle of this circumference is positioned on the axis of pre-combustion grade nozzle 30, and the quantity of the single fuel nozzle 34 that main combustion level nozzle 31 adopts is corresponding with the quantity that main combustion level nozzle atomization air gets into pipe 29, quantity 0＜p≤50 of the single fuel nozzle 34 that main combustion level nozzle 31 adopts; The spray line of single fuel nozzle 34 and the corner cut A of circumference are-90～90 degree, and the injection signal of main combustion level nozzle 31 is shown in figure 12.
Behind the combustion chamber inlet air flow 1 entering combustion chamber; Be divided into three strands behind the deceleration diffusion through shunting diffuser 8: ring cavity air-flow 4 in ring cavity air-flow 3 and the combustion chamber outside burner inner liner head air-flow 2, the combustion chamber; To satisfy the demand of combustion chamber each several part to air mass flow; Rationalization's combustion chamber flow field is convenient to the tissue burning of efficient stable.
Burner inner liner head air-flow 2 all is that gas is used in burning; Account for 40%～80% of combustion chamber inlet air flow 1; Burner inner liner head air-flow 2 except 0%～25% is used to the cooling of pre-combustion grade head end wall 23 and the whole end wall 12 of main combustion level head, and all the other are infeeded by pre-combustion grade 20 and main combustion level 33 respectively, is used for the atomizing and the burning of pre-combustion grade 20 and main combustion level 33 corresponding fuel oils; 20 air demands of pre-combustion grade account for 10%～40% of whole burning tolerance, and all the other are infeeded by main combustion level 39.Pre-combustion grade 20 required fuel oils are after 30 ejections of pre-combustion grade nozzle; By air swirl shearing-crushing from pre-combustion grade swirler assembly 22; Form mist of oil, get into then that air swirl by pre-combustion grade swirler assembly 22 forms the low speed recirculating zone---pre-combustion grade combustion zone 6 forms diffusion combustion.Pre-combustion grade nozzle 30 can be a pressure atomized fog jet; It also can be pneumatic nozzle; It also can be combined nozzle; The selection dependence fuel oil of pre-combustion grade nozzle 30 determines from atomizing under the acting in conjunction of the air swirl of pre-combustion grade swirler assembly 22 and distribution effect in 30 combinations of pre-combustion grade nozzle: atomizing and distribution effect are good more, and the mist of oil distribution is even more, is beneficial to the oligosaprobic burning of 6 inner tissue's efficient stables in the pre-combustion grade combustion zone more.The required fuel oil of main combustion level 33 is after 31 ejections of main combustion level nozzle; At first atomizing forms fuel-air mixture under the air-flow effect that gets into pipe 29 through main combustion level nozzle atomization air; Flow into main combustion level premix and pre-evaporation endless tube 28 then; Evaporation and the distribution in main combustion level premix and pre-evaporation endless tube 28 of the mixed gas of oil gas after the atomizing; Exit in main combustion level premix and pre-evaporation section 21 forms uniform fuel-air mixture jet, and this fuel-air mixture jet is lighted under the igniting of pre-combustion grade flame, forms main combustion level combustion zone 7.Main combustion level nozzle 31 is positioned at main combustion level nozzle atomization air and gets into pipe 29 inlets; And it is coaxial with main combustion level nozzle atomization air entering pipe 29; Main combustion level nozzle 31 is employed in the spray regime that a plurality of fuel nozzles are set on the same circumference; The center of circle of this circumference is positioned on the axis of pre-combustion grade nozzle 30, and the nozzle quantity of employing is corresponding with the quantity that main combustion level nozzle atomization air gets into pipe 29, and the fuel nozzle quantity 0＜p≤spray line of 50 single-nozzles of employing and the corner cut A of circumference are-90～90 degree.Main combustion level nozzle 31 can be a pressure atomized fog jet; It also can be pneumatic nozzle; It also can be combined nozzle; The number of main combustion level nozzle and the selection of spray angle rely on fuel oil coming autonomous combustion level nozzle atomization air to get under the acting in conjunction of the atomizing air of pipe 29 and the evaporation mixing air-flow that comes autonomous combustion level premix and pre-evaporation endless tube 28; The uniformity coefficient that goes out the fuel-air mixture of interruption-forming in master's combustion level premix and pre-evaporation section 21 determines: the fuel-air mixture of formation is even more, is beneficial to more in main level combustion zone 7 inner tissues of firing rapidly and efficiently to stablize oligosaprobic burning.
Ring cavity air-flow 3 comprises that the cooling usefulness gas of burner inner liner outer wall 13 and the blending of burner inner liner outer wall blending hole 15 use gas outside the combustion chamber.Ring cavity air-flow 4 comprises that the cooling usefulness gas of burner inner liner inwall 14 and the blending of burner inner liner inwall blending hole 16 use gas in the combustion chamber.Wherein the cold gas of burner inner liner outer wall 13 or burner inner liner inwall 14 accounts for 0%～20% of combustion chamber inlet air flow 1, and the blending usefulness gas of burner inner liner outer wall blending hole 15 or burner inner liner inwall blending hole 16 accounts for 10%～30% of combustion chamber inlet air flow 1.
The combustion chamber overall structure of specific embodiments and fuel nozzle structure such as Figure 10, Figure 11 and shown in Figure 12.Figure 10 is the burner inner liner structural representation, and Figure 11 is the structural representation of the fuel nozzle 11 of employing at this moment, and Figure 12 is that 31 injections of main combustion level nozzle are illustrated.Shown in figure 10, burner inner liner head 14 is connected with burner inner liner inwall 16 with burner inner liner outer wall 15 through the whole end wall 12 of main combustion level head.Burner inner liner head 14 is made up of pre-combustion grade 20 and main combustion level 33: main combustion level 33 comprises main combustion level nozzle 31, main combustion level premix and pre-evaporation section 21, the main whole end wall 12 of combustion level head and the whole deflector 13 of main combustion level head, and main combustion level premix and pre-evaporation section 21 is like Fig. 4 and shown in Figure 5; Pre-combustion grade 20 comprises pre-combustion grade swirler assembly 22, pre-combustion grade nozzle 35, pre-combustion grade head end wall 23, pre-combustion grade head deflector 24, and pre-combustion grade swirler assembly 22 is shown in Fig. 8 and 9.Pre-combustion grade swirler assembly 22 is coaxial with main combustion level premix and pre-evaporation section 21, and the fuel nozzle 11 that adopt this moment is shown in figure 11, and pre-combustion grade nozzle 30 is relative with pre-combustion grade one-level cyclone 25, and main combustion level nozzle 31 is corresponding with main combustion grade nozzle atomization air entering hole 29.When aero-engine is operated in low power state; The combustion chamber has only pre-combustion grade 20 fuel feeding; Main combustion level 33 have only air through and fuel feeding not, the oil-gas ratio of control this moment is in oil-poor scope, formation diffusion combustion pre-combustion grade combustion zone 6 in; Thereby guaranteed reliable stability of engine chamber and starting characteristic, and reduced CO and UHC disposal of pollutants.When aero-engine is operated in high power state, pre-combustion grade 20 and main combustion grade 33 while fuel feeding, pre-combustion grade 20 forms diffusion combustion in pre-combustion grade combustion zone 6, and main combustion level 33 forms the master in the periphery of pre-combustion grade combustion zone 6 and fires level combustion zone 7.Main combustion level 33 adopts the premix and pre-evaporation mode of tangential oil supply; Can required fuel oil that lead combustion level 33 be mixed in main combustion level premix and pre-evaporation section 21 rapidly and uniformly on the one hand and form fuel-air mixture; This gaseous mixture can burn totally after getting into burner inner liner fast preferably; Thereby reduce the generation of NOx, on the other hand can CO and UHC burning that pre-combustion grade does not burn down is clean.This shows that premix and pre-evaporation combustion chamber 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 present invention does not set forth part in detail and 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 improvement and retouching, these improvement and retouching also should be regarded as protection scope of the present invention.
Claims (8)
1. the premix and pre-evaporation combustion chamber of main combustible stage tangential oil supply; It is characterized in that: said combustion chamber is the monocycle cavity configuration; Adopt the fractional combustion mode, the burning gas consumption is all infeeded by pre-combustion grade and main combustion level, and pre-combustion grade adopts swirl stabilized diffusion flame burning organizational form; Main combustion level adopts the premix and pre-evaporation burning organizational form of tangential oil supply, and cold gas and mixed gas infeed from burner inner liner; The premix and pre-evaporation combustion chamber of said main combustible stage tangential oil supply mainly is made up of casing (10), fuel nozzle (11), burner inner liner head (14), burner inner liner outer wall (15) and burner inner liner inwall (16) in shunting diffuser (8), outer combustion case (9), the combustion chamber; Burner inner liner head (14) is made up of pre-combustion grade (20) and main combustion level (33): pre-combustion grade (20) comprises deflector (24) in pre-combustion grade swirler assembly (22), pre-combustion grade nozzle (30), pre-combustion grade head end wall (23) and the pre-combustion grade head; Pre-combustion grade (20) is utilized the low speed recirculating zone retention flame that is got into the rotational flow air generation of combustion chamber by pre-combustion grade swirler assembly (22); Pre-combustion grade swirler assembly (22) is connected with main combustion level premix and pre-evaporation endless tube (28) through pre-combustion grade head end wall (23); Pre-combustion grade nozzle (30) is positioned at pre-combustion grade swirler assembly (22); And coaxial with pre-combustion grade swirler assembly (22), deflector (24) links to each other with pre-combustion grade head end wall (23) in the pre-combustion grade head; Main combustion level (33) comprises main combustion level nozzle (31), main combustion level premix and pre-evaporation section (21), the main whole end wall (12) of combustion level head and the whole deflector (13) of main combustion level head; Main combustion level premix and pre-evaporation section (21) gets into pipe (29) by main combustion level premix and pre-evaporation endless tube (28) and main combustion level nozzle atomization air and forms; Main combustion level nozzle (31) is positioned at main combustion level nozzle atomization air and gets into pipe (29) inlet; And it is coaxial with main combustion level nozzle atomization air entering pipe (29); Main combustion level nozzle (31) is employed in the spray regime that a plurality of single fuel nozzles (34) are set on the same circumference; The center of circle of this circumference is positioned on the axis of pre-combustion grade nozzle (30), and the quantity of the single fuel nozzle (34) of main combustion grade nozzle (31) employing is corresponding with the quantity that (29) are managed in the entering of main combustion level nozzle atomization air, after the required fuel oil of main combustion level (33) fires level nozzle (31) ejection by the master; The aerodynamic atomization that is at first got into pipe (29) by main combustion level nozzle atomization air forms fuel-air mixture; Flow into a main combustion level premix and pre-evaporation endless tube (28) then, fuel-air mixture evaporates in main combustion level premix and pre-evaporation endless tube (28), and with the further blending of air; Form uniform fuel-air mixture jet gets in the burner inner liner in the exit of main combustion level premix and pre-evaporation endless tube (28); Under the igniting of pre-combustion grade flame, burn, main combustion level premix and pre-evaporation section (21) links to each other with burner inner liner inwall (16) with burner inner liner outer wall (15) through the main combustion level whole end wall of head (12), and the main combustion level whole deflector of head (13) links to each other with the main combustion level whole end wall of head (12); Pre-combustion grade nozzle (30) and main combustion level nozzle (31) all are connected on the fuel nozzle seat (32), form fuel nozzle (11), and fuel nozzle (11) links to each other with outer combustion case (9) through fuel nozzle seat (32).
2. premix and pre-evaporation combustion chamber according to claim 1; It is characterized in that: be provided with burner inner liner outer wall blending hole (17) at described burner inner liner outer wall (15) rear portion; Be provided with burner inner liner inwall blending hole (18) at described burner inner liner inwall (16) rear portion; Blending usefulness gas gets into burner inner liner from burner inner liner outer wall blending hole (17) and burner inner liner inwall blending hole (18) respectively, with control combustor exit Temperature Distribution.
3. premix and pre-evaporation combustion chamber according to claim 1 and 2; It is characterized in that: described shunting diffuser (8) is divided into three strands with combustion chamber inlet air flow (1): ring cavity air-flow (4) in ring cavity air-flow (3) and the combustion chamber outside burner inner liner head air-flow (2), the combustion chamber, and to satisfy the demand of combustion chamber each several part to air mass flow.
4. premix and pre-evaporation combustion chamber according to claim 1 and 2 is characterized in that: the single fuel nozzle (34) that said pre-combustion grade nozzle (30) and main combustion level nozzle (31) adopt is pressure atomized fog jet, pneumatic nozzle or combined nozzle.
5. premix and pre-evaporation combustion chamber according to claim 1 is characterized in that: progression 1≤n≤5 of the cyclone that said pre-combustion grade swirler assembly (22) adopts; 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 (22), cyclone directly is connected with pre-combustion grade head end wall (23); When the progression 1＜n of pre-combustion grade swirler assembly (22)≤5, cyclones at different levels connect into an integral body earlier, are connected with pre-combustion grade head end wall (23) after forming pre-combustion grade swirler assembly (22) again.
6. premix and pre-evaporation combustion chamber according to claim 1; It is characterized in that: said main combustion level nozzle (31) is employed in the spray regime that a plurality of single fuel nozzles (34) are set on the same circumference; The center of circle of this circumference is positioned on the axis of pre-combustion grade nozzle (30); The quantity of the single fuel nozzle (34) that adopts is corresponding with the quantity that main combustion level nozzle atomization air gets into pipe (29); Quantity 0＜p≤50 of single fuel nozzle (34), the spray line of single fuel nozzle (34) and the corner cut A of circumference are-90～90 degree.
7. premix and pre-evaporation combustion chamber according to claim 1; It is characterized in that: the burning usefulness gas of said combustion chamber is all infeeded by burner inner liner head (14); Burner inner liner head air-flow accounts for 40%～80% of combustion chamber inlet air flow: the cooling institute air demand of pre-combustion grade head end wall (23) and the main combustion level whole end wall of head (12) accounts for 0%～25% of burner inner liner head air-flow; Pre-combustion grade (20) institute air demand accounts for 10%～40% of whole burning tolerance, and all the other main combustion level premix and pre-evaporation sections (21) by main combustion level (33) infeed.
8. premix and pre-evaporation combustion chamber according to claim 1; It is characterized in that: the burner inner liner outer wall (15) of said combustion chamber and the type of cooling of burner inner liner inwall (16) 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.
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| CN101949551A (en) * | 2010-09-09 | 2011-01-19 | 北京航空航天大学 | Premix and pre-evaporation combustion chamber |
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| CN113883550B (en) * | 2021-11-09 | 2022-11-15 | 浙江大学 | Low-emission backflow combustion chamber adopting circumferential tangential oil supply mode |
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| CN114484501A (en) * | 2022-02-16 | 2022-05-13 | 浙江意动科技股份有限公司 | Evaporation tube type combustion chamber |
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Application publication date: 20100811 Assignee: Beijing Beihang Advanced Industrial Technology Research Institute Co. Ltd. Assignor: Beihang University Contract record no.: 2014110000030 Denomination of invention: Main combustible stage tangential oil supply premix and pre-evaporation combustion chamber Granted publication date: 20120912 License type: Exclusive License Record date: 20140619 |
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