CN101709884B - Premixing and pre-evaporating combustion chamber - Google Patents
Premixing and pre-evaporating combustion chamber Download PDFInfo
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- CN101709884B CN101709884B CN200910238793XA CN200910238793A CN101709884B CN 101709884 B CN101709884 B CN 101709884B CN 200910238793X A CN200910238793X A CN 200910238793XA CN 200910238793 A CN200910238793 A CN 200910238793A CN 101709884 B CN101709884 B CN 101709884B
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Abstract
一种预混预蒸发燃烧室，燃烧室为单环腔结构，采用分级燃烧的概念设计，燃烧用气量全部由预燃级和主燃级供入，预燃级采用旋流稳定的扩散火焰燃烧组织方式，主燃级采用预混预蒸发燃烧组织方式。燃烧室主要由分流式扩压器、燃烧室外机匣、燃烧室内机匣、燃油喷嘴、预燃级、主燃级、火焰筒外壁和火焰筒内壁组成。预燃级利用由预燃级旋流器组件进入燃烧室的旋流空气产生的低速回流区稳定火焰；主燃级所需的燃油由主燃级喷嘴喷出后，首先在主燃级喷嘴预膜空气环的气流作用下雾化形成油气混合气，然后流入预混预蒸发段中蒸发，并与空气进一步掺混，在预混预蒸发段的出口处形成均匀的油气混合气射流进入火焰筒，在预燃级火焰的引燃下进行燃烧。本发明结构简单，在保证航空发动机正常工作状态的同时能有效的降低污染排放。
A premixed pre-evaporation combustion chamber, the combustion chamber is a single-ring cavity structure, adopts the conceptual design of staged combustion, the combustion gas is all supplied by the pre-combustion stage and the main combustion stage, and the pre-combustion stage adopts a swirling stable diffusion flame combustion The organization method, the main combustion stage adopts the premixed pre-evaporation combustion organization method. The combustion chamber is mainly composed of a split diffuser, a casing outside the combustion chamber, a casing inside the combustion chamber, a fuel nozzle, a pre-combustion stage, a main combustion stage, the outer wall of the flame tube and the inner wall of the flame tube. The pre-combustion stage stabilizes the flame by using the low-velocity recirculation zone generated by the swirling air that enters the combustion chamber from the pre-combustion stage swirler assembly; after the fuel required by the main combustion stage is sprayed from the nozzle of the main combustion stage, it first passes through the nozzle of the main combustion stage. Under the action of the airflow of the membrane air ring, the oil-gas mixture is atomized to form a mixed gas, and then flows into the pre-mixed pre-evaporation section for evaporation, and is further mixed with air, and a uniform jet of oil-air mixed gas is formed at the outlet of the pre-mixed pre-evaporation section and enters the flame tube , burning under the ignition of the pre-combustion flame. The invention has a simple structure and can effectively reduce pollution discharge while ensuring the normal working state of the aero-engine.
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 CAEP4 (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 TwinAnnular Premixing Swirler) low pollution combustor of its GEnx reseach of engine that GE company adopts LDM (Lean DirectMixing Combustion, oil-poor direct hybrid combustor) technology.This combustion chamber has got into the complete machine Qualify Phase, is about to evidence obtaining, and in stand loopful verification experimental verification, 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 premix and pre-evaporation burning organizational form 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: premix and pre-evaporation combustion chamber 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 premix and pre-evaporation burning organizational form, and cold gas and mixed gas infeed from burner inner liner.Premix and pre-evaporation combustion chamber 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 pre-combustion grade swirler assembly, pre-combustion grade nozzle, pre-combustion grade head end wall and pre-combustion grade head deflector; 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; Main combustion level comprises main combustion level nozzle, the preparatory film air of main combustion level nozzle ring, 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; Ring-shaped pressuring plate, main combustion level nozzle float in outer ring-shaped pressuring plate, the main combustion level premix and pre-evaporation section ring, main combustion level premix and pre-evaporation section outer shroud, main combustion level outlet water conservancy diversion of outer shroud, main combustion level nozzle that float supported and forms in ring, main combustion level nozzle floated in a main combustion level premix and pre-evaporation Duan Youzhu combustion level nozzle floated; Master's combustion level nozzle and the main combustion grade preparatory film air of nozzle ring encircles in main combustion level nozzle floats and main combustion level nozzle floats between the outer shroud; And it is coaxial with the pre-combustion grade nozzle; Main combustion level nozzle is employed in the multi-point injection mode that a plurality of spray site are set on the same circumference; The required fuel oil of main combustion level by the ejection of main combustion level nozzle after, at first, flow into the premix and pre-evaporation section then at the air-flow effect of the preparatory film air of main combustion level nozzle ring atomizing formation fuel-air mixture down; Fuel-air mixture evaporates in the premix and pre-evaporation section; And with the further blending of air, form uniform fuel-air mixture jet in the exit of premix and pre-evaporation section and get into burner inner liner, under the igniting of pre-combustion grade flame, burn.Fuel nozzle is made up of pre-combustion grade nozzle, main combustion level nozzle and fuel nozzle seat, and the pre-combustion grade nozzle all is connected on the fuel nozzle seat with main combustion level nozzle, and 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 a premix and pre-evaporation burning organizational form, 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 premix and pre-evaporation.Premix and pre-evaporation can make fuel oil and air mix, and forms uniform fuel-air mixture jet.When this strand uniformly the fuel-air mixture jet meet lighted after, 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 premix and pre-evaporation burning organizational form; 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 ring and a main combustion level outlet water conservancy diversion supporting construction sketch map in the main combustion level premix and pre-evaporation section of the present invention;
Fig. 7 is ring and a main combustion level outlet water conservancy diversion supporting construction cutaway view in the main combustion level premix and pre-evaporation section of the present invention;
Fig. 8 is a pre-combustion grade modular construction sketch map of the present invention;
Fig. 9 is a pre-combustion grade modular construction cutaway view of the present invention;
Figure 10 is a pre-combustion grade swirler assembly structural representation of the present invention;
Figure 11 is a pre-combustion grade swirler assembly structure cutaway view of the present invention;
Figure 12 is a specific embodiments burner inner liner structural representation of the present invention;
The fuel nozzle structural representation that Figure 13 adopts for the present invention;
The main combustion level nozzle arrangements cutaway view that Figure 14 adopts for the present invention;
Figure 15 arranges sketch map for the main combustion level nozzle ejection point that the present invention adopts.
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 sections, 22. pre-combustion grade swirler assemblies, 23. pre-combustion grade head end wall; 24. pre-combustion grade head deflector, 25. pre-combustion grade one-level cyclones, 26. pre-combustion grade one-level cyclone pressing plates, 27. pre-combustion grade second cyclones; 28. the main level premix and pre-evaporation section outer shroud that fires, the interior ring of 29. main combustion level premix and pre-evaporation sections, 30. main combustion levels export water conservancy diversion and support, the unsteady outer ring-shaped pressuring plate of 31. main combustion level nozzles; The outer shroud 32. main combustion level nozzle floats, ring-shaped pressuring plate in 33. main combustion level nozzles float, ring in 34. main combustion level nozzles float, 35. pre-combustion grade nozzles; 36. main combustion level nozzle, the preparatory film air of 37. main combustion level nozzles ring, 38. fuel nozzle seats, 39. main combustion levels.
The specific embodiment
As depicted in figs. 1 and 2; The premix and pre-evaporation combustion chamber 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 premix and pre-evaporation, 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 39 comprises main combustion level nozzle 36, the preparatory film air of main combustion level nozzle ring 37, 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 is like Fig. 4 and shown in Figure 5, in ring 34, main combustion level nozzle float in being floated by main combustion level nozzle ring-shaped pressuring plate 33, main combustion level nozzle float outer shroud 32, main combustion level nozzle float encircle 29 in outer ring-shaped pressuring plate 31, the main combustion level premix and pre-evaporation section, main combustion level premix and pre-evaporation section outer shroud 28 and main combustion level outlet water conservancy diversion support and 30 form.Main combustion level outlet water conservancy diversion supports 30 and works to connect ring 29 and main combustion level premix and pre-evaporation section outer shroud 28 in the main combustion level premix and pre-evaporation section on the one hand, plays adjustment on the other hand through main combustion level premix and pre-evaporation section 21 air stream outlet angles.Main combustion level outlet water conservancy diversion supports 30 blade quantity 0≤p≤30, and along the outlet circumference uniform distribution of ring 29 in the main combustion level premix and pre-evaporation section, the setting angle of blade is between-90 degree～90 degree.Specific embodiments is like Fig. 4, Fig. 5, Fig. 6 and shown in Figure 7.During installation, at first will lead a combustion level outlet water conservancy diversion support 30 with main combustion level premix and pre-evaporation section in encircle 29 and be connected, adoptable connected mode is whole manufacturing or screw thread or bolt or welding; Then with the two sub-assembly; Insert in the main combustion level premix and pre-evaporation section outer shroud 30; In guaranteeing main combustion level premix and pre-evaporation section, under the coaxial prerequisite of ring 29 and main combustion grade premix and pre-evaporation section outer shroud 30, use the connected mode of whole manufacturing or screw thread or bolt or welding to connect; Guarantee main combustion level nozzle float outer ring-shaped pressuring plate 31 with main fire grade premix and pre-evaporation section outer shroud 28 coaxial in; Adopt welding or screw thread or bolted mode; The main combustion level nozzle outer ring-shaped pressuring plate 31 that floats is linked together with a main combustion level premix and pre-evaporation section outer shroud 28, and will lead the combustion level nozzle outer shroud 32 that floats and be clipped in the main combustion level nozzle outer ring-shaped pressuring plate 31 that floats and fire between grade premix and pre-evaporation section outer shroud 28 with the master; Guarantee main combustion level nozzle encircle in ring-shaped pressuring plate 33 and the main combustion grade premix and pre-evaporation section in floating 29 coaxial in; Adopt welding or screw thread or bolted mode; Make main combustion level nozzle float in ring-shaped pressuring plate 33 and the main combustion level premix and pre-evaporation section ring 29 link together, and will lead combustion level nozzle float in ring 34 be clipped in main combustion level nozzle float in ring-shaped pressuring plate 33 and the main combustion level premix and pre-evaporation section between the ring 29; After above-mentioned installation steps are accomplished, 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 35, pre-combustion grade head end wall 23, pre-combustion grade head deflector 24, and pre-combustion grade 20 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 Figure 10 and shown in Figure 11, 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 ring 29 in pre-combustion grade head end wall 23 and the main combustion level premix and pre-evaporation section is 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; Through pre-combustion grade head end wall 23 ring 29 in pre-combustion grade swirler assembly 22 and the main combustion level premix and pre-evaporation section is fixed together; 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 swirler assembly 22.
After main combustion level premix and pre-evaporation section 21 and 22 installations of pre-combustion grade swirler assembly, insert main combustion level nozzle 36 and pre-combustion grade nozzle 35 at correspondence position, thereby accomplish the installation of burner inner liner head 14.
As depicted in figs. 1 and 2; Pre-combustion grade nozzle 35 all is installed on the fuel nozzle seat 38 with main combustion level nozzle 36; 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 35 can be a pressure atomized fog jet, also can be pneumatic nozzle, also can be combined nozzle.Pre-combustion grade nozzle 35 is corresponding with pre-combustion grade one-level cyclone 25, and the axis of the axis of pre-combustion grade nozzle 35 and pre-combustion grade one-level cyclone 25 coincides.Main combustion level nozzle 36 and the preparatory film air of main combustion level nozzle ring 37 are in main combustion level nozzle floats between ring 34 and the unsteady outer shroud 32 of main combustion level nozzle, and be and coaxial with pre-combustion grade nozzle 35.Main combustion level nozzle 36 is employed in the multi-point injection mode that a plurality of spray site are set on the same circumference; Shown in figure 15; The geometry of spray site can be number 0＜n≤300 of circle, rectangle, spray site, and the angular range between the axis of the spray line of single spray site and pre-combustion grade nozzle 35 is between-90 degree～90 degree.The preparatory film air of main combustion level nozzle ring 37 plays preliminary atomizing and scatters the fuel oil that ejects from main combustion level nozzle 36, adopts axial blade formula structure, and the setting angle of blade is between-90 degree～90 degree, quantity 0≤m≤300 of blade.The preparatory film air of main combustion level nozzle ring 37 can exist also and can not exist: when it exists; Can separately exist in the interior ring of main combustion level nozzle 36; Also can separately exist in the outer shroud of main combustion level nozzle 36, also can be present in the interior ring and the outer shroud of main combustion level nozzle 36 simultaneously.The connected mode of the preparatory film air of main combustion level nozzle ring 37 and main combustion level nozzle 36 can adopt the form of whole manufacturing or welding or screw thread or bolt.
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 39 respectively, is used for the atomizing and the burning of pre-combustion grade 20 and main combustion level 39 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 35 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 35 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 35 determines from atomizing under the acting in conjunction of the air swirl of pre-combustion grade swirler assembly 22 and distribution effect in 35 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 39 is after 36 ejections of main combustion level nozzle; At first under air-flow effect, atomize and form the mixed gas of oil gas through the preparatory film air of master's combustion level nozzle ring 37; Flow into main combustion level premix and pre-evaporation section 21 then; Oil gas after the atomizing mixes gas further atomizing and distribution in master's combustion level premix and pre-evaporation section 21; Exit in main combustion level premix and pre-evaporation section 21 forms uniform fuel-air mixture jet; 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 36 is employed in the multi-point injection mode that a plurality of spray site are set on the same circumference; The geometry of spray site can be number 0＜n≤300 of circle, rectangle, spray site, and the angular range between the axis of the spray line of single spray site and pre-combustion grade nozzle 35 is between-90 degree～90 degree.The selection of shape, number and the angle of main combustion level nozzle 36 spray site relies on fuel oil at a main combustion level nozzle 36, independently fire grade atomizing air of the preparatory film air of nozzle ring 37 and independently firing under grade acting in conjunction of the atomizing blending air-flow of premix and pre-evaporation section 21; 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 17 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 18 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 17 or burner inner liner inwall blending hole 18 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 12, Figure 13, Figure 14 and shown in Figure 15.Figure 12 is the burner inner liner structural representation, and Figure 13 is the structural representation of the fuel nozzle 11 of employing this moment, and Figure 14 is the structure cutaway view of main combustion level nozzle 36, and Figure 15 is that main level nozzle 36 spray site of firing are arranged sketch map.Shown in figure 12, 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 39: main combustion level 39 comprises a main combustion level nozzle 36, the preparatory film air of a main combustion level nozzle ring 37, a 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 Figure 10 and 11.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 13, and pre-combustion grade nozzle 35 is relative with pre-combustion grade one-level cyclone 25, and main combustion level nozzle 36 is corresponding with main combustion level premix and pre-evaporation section 21.When aero-engine is operated in low power state; The combustion chamber has only pre-combustion grade 20 fuel feeding; Main combustion level 39 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 39 while fuel feeding, pre-combustion grade 20 forms diffusion combustion in pre-combustion grade combustion zone 6, and main combustion level 39 forms the master in the periphery of pre-combustion grade combustion zone 6 and fires level combustion zone 7.Main combustion level 39 adopts the premix and pre-evaporation mode; Can required fuel oil that lead combustion level 39 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.
Claims (10)
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