CN102242939A - Prefilming three-stage pre-mixing and pre-evaporating low-pollution combustor - Google Patents
Prefilming three-stage pre-mixing and pre-evaporating low-pollution combustor Download PDFInfo
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Abstract
The invention provides a prefilming three-stage pre-mixing and pre-evaporating low-pollution combustor which comprises a diffuser, an outer combustor case, an inner combustor case, a flame cylinder outer wall, a flame cylinder inner wall and a combustor head, wherein all the air for combustion enters a flame cylinder from the combustor head; the combustor head adopts a multi-stage combustion scheme which includes one precombustion stage and two main combustion stages; a premixed combustion mode is used for the main combustion stages; and a diffusion combustion mode with stable cyclone is used for the precombustion stage. The main combustion stage is structurally divided into two stages, thus avoiding the increase of pollutant emissions caused by poor main-stage oil and gas mixing during stage transfer under the condition of one main combustion stage, and simultaneously reducing the pollutant emissions by 30% in the working condition without affecting combustion stability; and a prefilming nozzle is used for the second main combustion stage, thus ensuring fuel oil to be distributed more uniformly and further reducing the pollutants in the large working condition in comparison with a discrete nozzle. Thus, pollutant emissions generated in the whole landing and take-off cycle of the aero-engine combustor is reduced without affecting combustion stability.
Description
Technical field
The present invention relates to a kind of aero-gas turbine low pollution combustor that utilizes the premix and pre-evaporation combustion technology.Adopt the pattern of fractional combustion, main combustion stage adopts the mode of premixed combustion, is mainly used in the disposal of pollutants that reduces under the big operating mode; Pre-combustion grade adopts the mode of diffusion combustion, is guaranteeing combustion chamber smooth combustion, and main combustion stage adopts the mode of the premix and pre-evaporation burning that divides two-stage, reduces the disposal of pollutants of the whole LTO circulation of aero-engine.
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 civil aviation engine chamber is combustion with reduced pollutants.The civil aviation engine chamber must satisfy the aero-engine emission standard of increasingly stringent.CAEP6 (the Committee on Aviation Environmental Protection) standard that adopts is very strict to the regulation of pollutant effulent at present, particularly to the NOx emission requirement; And up-to-date CAEP8 standard has proposed to reduce by 15% on the discharge standard that is emitted on CAEP6 with NOx, along with the fast development of aircraft industry and improving constantly of people's environmental consciousness, following gas-turbine combustion chamber disposal of pollutants meeting is proposed higher requirement.
Two GE of leading company of US Airways engine and PW set about research already 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 RQL (fuel-rich combustion-extinguishing-poor oil firing, Rich burn-Quench-Lean burn is called for short RQL) low pollution combustor TALON II (being used for PW4000 and 6000 series).Aspect low pollution combustor of future generation, it is TAPS (the Twin Annular Premixing Swirler) low pollution combustor of its GEnx reseach of engine that GE company adopts LDM (Lean Direct Mixing Combustion, oil-poor direct hybrid combustor) technology.This combustion chamber is in stand loopful verification experimental verification, and the NOx disposal of pollutants has reduced by 50% than CAEP2 discharge standard.GE company has applied for multinomial United States Patent (USP): application number 6363726,6389815,6354072,6418726,0178732,6381964 and 6389815, all these patents all are that to adopt diffusion combustion, main combustion stage to adopt the burning organizational form of premixed combustion, purpose be the NOx discharging that reduces under the big operating mode of emission index maximum to pre-combustion grade.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.
The BJ University of Aeronautics ﹠ Astronautics of China has also applied for 200910238793.X to low pollution combustor, 201010101574.X, 201010034141.7,201010277014.X etc. multinomial patent, the scheme that adopts is that pre-combustion grade adopts diffusion combustion mode, main combustion stage adopts the premixed combustion mode, main combustion stage is a loop configuration, fuel feeding axially or radially, adopt multi-point injection or pre-film atomizing type, purpose is the NOx discharging that reduces under the big operating mode, thereby the discharging of the NOx of whole LTO circulation is reduced, but it is bigger further to reduce the emission level difficulty of NOx of whole LTO circulation.
Above-described patent, all be at big operating mode decline low pollution emission, and according to (the International Civil Aviation OrganiZation of International Civil Aviation Organization, ICAO) the emission index under Gui Ding the standard cycle, express this parameter with LTO Emission, be calculated as follows formula:
By following formula as can be known, LTO Emission is relevant with the NOx discharge capacity under four operating modes, and is promptly both relevant with the NOx discharging under the big operating mode, also relevant with the NOx discharging under the little operating mode.
Operational mode in the standard LTO circulation, thrust and the running time under each operational mode, as shown in the table.
Operational mode and time in the LTO circulation of table 1ICAO regulation
| Operational mode | Thrust is provided with | Running time (min) |
| (Take-off) takes off | 100％F oo | 0.7 |
| (Climb) climbs | 85％F oo | 2.2 |
| (Approach) marches into the |
30％F oo | 4.0 |
| Slide/ground idle speed (Taxi/ground idle) | 7％F oo | ?0 |
The thrust of routine or active service is discharged as following table, data from ICAO Emission data bank at the NOx of the CFM56-5B/3 of 140KN engine.
The NOx emission level of table 2CFM56-5B/3
| Parameter | Unit | Slow train | March into the arena | Climb | Take off |
| Emission index (EI) | g/(kgf) | 4.45 | 9.28 | 19.77 | 26.18 |
| Fuel flow | kg/s | 0.112 | 0.448 | 1.086 | 1.325 |
| Running time | g | 1560 | 240 | 132 | 42 |
| Discharge capacity | g/kN | 777.5 | 997.8 | 2834.1 | 1456.9 |
Fractional combustion is adopted in the combustion chamber, and pre-combustion grade is a diffusion combustion mode, and main combustion stage is the premixed combustion mode, has reduced the NOx discharging under the big operating mode, and the NOx that can reach discharging is as shown in the table:
The NOx emission level that table 3 main combustion stage adopts premixed combustion to reach
| Parameter | Unit | Slow train | March into the arena | Climb | Take off |
| NOx emission index (EI) | g/(kgf) | 4.45 | 9.28 | 4 | 4.1 |
| Fuel flow | kg/s | 0.112 | 0.448 | 1.086 | 1.325 |
| Running time | g | 1560 | 240 | 132 | 42 |
| Discharge capacity | g/kN | 777.5 | 997.8 | 594 | 228 |
Under little operating mode (ground idle speed, march into the arena), though the NOx emission index is lower, according to being higher than other big operating modes the running time under the as can be known little operating mode of table 1 far away, according to table 3 as can be known, when main combustion stage adopts the premixed combustion mode, NOx emission index under the big operating mode is reduced significantly, this moment pre-combustion grade the proportion maximum that in the disposal of pollutants discharging of whole LTO circulation, accounts for of NOx total emission volumn, therefore want further to reduce the NOx discharging of whole LTO circulation, just need to consider to reduce the NOx discharging of pre-combustion grade.
And no matter be which kind of advanced person's low pollution combustor, the combustion technology that its key technology reduces NOx (nitrogen oxide), CO (carbon monoxide), UHC (unburned hydrocarbons) exactly and smolders, key problem is to reduce the temperature of combustion zone, make the combustion zone temperature field even simultaneously, promptly whole and local equivalent proportion control, and the uniformity of primary zone equivalent proportion depends primarily on the uniformity of fuel-oil atmozation and oil gas blending.
The present invention be directed to the new method of aero-engine combustion with reduced pollutants.Mechanism that produces according to NOx and CO and result of the test be as can be known: NOx that the primary zone equivalent proportion of combustion chamber produces in 0.6～0.8 scope and CO (the discharging rule of UHC and CO is similar) are seldom.Based on this principle, the discharge capacity of taking into account NOx and CO, UHC all is in the low value scope, should consider two factors: the average equivalent ratio in first primary zone, it two is uniformities of primary zone average equivalent ratio, and all should be like this under the working condition of all aero-engines.And the uniformity of primary zone equivalent proportion depends primarily on the uniformity of fuel-oil atmozation and oil gas blending.This depends primarily on two aspects: the one, and the uniformity that the fuel particles diameter distributes, the i.e. distributing homogeneity of SMD; Second be the uniformity that the fuel oil oil mist concentration distributes.From combustion system, should adopt uniform premixed combustion, reach primary zone equivalent proportion uniformity requirement to reduce disposal of pollutants.
Present conventional combustion system can't reduce NOx, CO and UHC.Reason is that the method for designing of current combustion chamber determines.For conventional combustion chamber, when big state, owing to adopt liquid mist diffusion combustion mode, the local equivalent proportion in combustion zone is always near 1, the required equivalent proportion area requirement of above-mentioned combustion with reduced pollutants that surpasses far away, though this moment CO and the discharging of UHC low, it is maximum that the discharging of NOx reaches.When little state, the combustion zone equivalent proportion is very low again, and far below the required equivalent proportion of above-mentioned combustion with reduced pollutants interval, though this moment, the NOx discharging was low, CO and UHC discharging are very high again.In addition, because diffusion combustion mode is generally adopted in conventional combustion chamber, local equivalent proportion is inhomogeneous, therefore for conventional combustion chamber, can't satisfy the low pollution requirement in whole engine operation scope.
Summary of the invention
The technical problem to be solved in the present invention is: overcome the prior art deficiency, utilization premix and pre-evaporation combustion technology, provide a kind of pre-membrane type to divide the low pollution combustor of three grades of premix and pre-evaporations, the main combustion stage of this combustion chamber adopts the premixed combustion mode, can keep lower disposal of pollutants more than 30% operating mode; Pre-combustion grade adopts the mode of diffusion combustion, can guarantee the engine steady operation under little operating mode, thereby has reduced the disposal of pollutants in the whole LTO circulation.
The technical solution adopted for the present invention to solve the technical problems is: pre-combustion grade adopts the mode of diffusion combustion, and main combustion stage adopts the mode of dividing the two-stage premixed combustion.The monocycle cavity configuration is adopted in described combustion chamber, and it constitutes its outline by casing in outer combustion case and the combustion chamber; Outside air enters by diffuser, burner inner liner outer wall, burner inner liner inwall and head of combustion chamber are formed the combustion zone, combustion air all enters burner inner liner by head of combustion chamber, and dilution air is injected by outer blending hole on the burner inner liner outer wall and the interior blending hole on the burner inner liner inwall; Described head of combustion chamber adopts the fractional combustion scheme, is divided into main combustion stage and pre-combustion grade, and the main combustion stage outer shroud is connected and fixed with burner inner liner outer wall and burner inner liner inwall by the whole end wall of head, and interior ring cavity of main combustion stage and fuel nozzle are one; Pre-combustion grade connects with main combustion stage by the pre-combustion grade head end wall, and concentric with main combustion stage; Described pre-combustion grade comprises pre-combustion grade swirler assembly, pre-combustion grade nozzle, pre-combustion grade head end wall, the pre-combustion grade utilization enters the low speed recirculating zone retention flame that the rotational flow air of combustion chamber produces by the pre-combustion grade swirler assembly, and the pre-combustion grade swirler assembly is connected by encircling in pre-combustion grade head end wall and the main combustion stage 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; The pre-combustion grade head end wall is connected on interior ring of main combustion stage premix evaporator section and the outer endless tube of pre-combustion grade; Wherein the pre-combustion grade cyclone comprises the outer endless tube of pre-combustion grade, pre-combustion grade Venturi tube, pre-combustion grade swirler blades; Described main combustion stage is by the premix and pre-evaporation outer shroud, ring in the premix and pre-evaporation ring, main combustion stage fuel oil ring, ring in the pre-membrane type nozzle, pre-membrane type nozzle outer shroud, the outer cyclone of main combustion stage, cyclone formation in cyclone and the pre-membrane type nozzle in the main combustion stage, wherein cyclone encircles with pre-membrane type nozzle is interior in the main combustion stage, boxing is connected together in the premix and pre-evaporation ring, constituted ring cavity in the main combustion stage, the outer cyclone of main combustion stage constitutes the main combustion stage outer shroud with premix and pre-evaporation ring outer shroud, constituted the outer ring cavity of main combustion stage with pre-membrane type nozzle outer shroud, the inside and outside ring cavity of main is merged into the premix section after pre-membrane type nozzle; Described fuel nozzle is supplied with all fuel oils to the combustion chamber, and fuel nozzle comprises atomizer and pre-membrane type atomizer in pre-combustion grade atomizer, the main combustion stage, and fuel nozzle directly inserts the main combustion stage outer shroud from the upstream of head of combustion chamber; Wherein the pre-combustion grade atomizer is a single-nozzle, directly be inserted in the internal channel of pre-combustion grade nozzle locating ring downstream, fuel oil through the pre-combustion grade fuel pipe forms the pre-combustion grade mist of oil by the pre-combustion grade atomizer, the pre-combustion grade mist of oil is beaten on pre-combustion grade cyclone Venturi tube internal face and is formed oil film, under incoming flow effect, atomize, carry out diffusion combustion in the pre-combustion grade outlet through the pre-combustion grade internal channel; Atomizer is made up of direct projection spray orifice in fuel gallery in the main combustion stage and the main combustion stage in the main combustion stage, and ring constitutes main combustion stage fuel oil internal channel together in main combustion stage internal combustion oil ring and the premix and pre-evaporation ring, is a loop configuration; The ring upper edge circumferentially evenly has direct projection spray orifice in a plurality of main combustion stages in the premix and pre-evaporation ring, and fuel oil enters the main combustion stage fuel gallery by fuel pipe in the main combustion stage, forms ring spray mist in the multiply main combustion stage through direct projection spray orifice in the main combustion stage then, sprays to the premix section; Evaporate and the premix blending under the effect of ring mist of oil eddy flow in main combustion stage in the main combustion stage, in short physical dimension, realize the fuel oil rapid evaporation and with the even blending of air, enter the main combustion stage outlet through the premix section then and carry out premixed combustion, guarantee lower disposal of pollutants; Pre-membrane type atomizer is made up of ring, pre-membrane type nozzle outer shroud and pre-membrane type cyclone in the pre-membrane type nozzle; Fuel oil forms the even main combustion stage oil film of one deck through pre-membrane type cyclone and sprays to the premix section by pre-membrane type atomizer; The main combustion stage oil film evaporates under the effect of eddy flow inside and outside the main combustion stage and the premix blending, in short physical dimension, realize the fuel oil rapid evaporation and with the even blending of air, enter the main combustion stage outlet through the premix section then and carry out premixed combustion, guarantee lower disposal of pollutants.
Principle of the present invention is as follows: the equivalent proportion and the uniformity by control aeroengine combustor buring Indoor Combustion district reach the purpose that reduces disposal of pollutants.Combustion air all enters burner inner liner from head of combustion chamber, enters the burner inner liner burning again after making most fuel oil and air blending evenly, and it is favourable that control combustion zone equivalent proportion is reduced disposal of pollutants.Adopt the fractional combustion scheme, under little operating mode, have only the work of pre-combustion grade fuel feeding, under middle operating mode, the common fuel feeding work of main combustion stage one-level and pre-combustion grade, under big operating mode, the common fuel feeding work of main combustion stage and pre-combustion grade.Under little operating mode, have only the work of pre-combustion grade fuel feeding, the pre-combustion grade fuel oil in the burning of pre-combustion grade exit, is diffusion combustion mode through the pre-combustion grade atomizer; Because the pre-combustion grade outlet is stronger recirculating zone, therefore the pre-combustion grade fuel oil of diffusion combustion has guaranteed the stability of burning in this strong inverse flow district internal combustion; Under middle operating mode, main combustion stage and pre-combustion grade be fuel feeding work simultaneously, main combustion stage one-level fuel oil enters the air flow channel of cyclone through emple hole, under cyclonic action, evaporate in advance and with the air blending, participate in burning in the main combustion stage exit, be the premixed combustion mode, owing to looking after too big middle operating mode atomizing and the mixing variation of causing of main combustion stage flow number that big operating mode causes, guarantee the disposal of pollutants of middle operating mode when avoiding not classification of main combustion stage.Under big operating mode, main combustion stage and pre-combustion grade be fuel feeding work simultaneously, and the fuel flow of main combustion stage accounts for major part, pollutant emission is controlled by main combustion stage mainly, and the even fuel-air mixture premixed combustion that main combustion stage adopts, the equivalent proportion that makes the combustion zone in the lower scope of disposal of pollutants, thereby controlled disposal of pollutants under the big operating mode.Therefore, this type combustion chamber has guaranteed that aero-engine has low pollution emission in wide working range, thereby has further reduced the NOx discharging under the whole LTO circulation, has guaranteed combustion stability simultaneously.
The advantage that the present invention is compared with prior art had is as follows:
(1) pre-combustion grade of the present invention adopts the combustion system that diffusion combustion and premixed combustion combine, by fuel oil being divided three grades mode reach the purpose that two kinds of combustion systems coexist, when not influencing the combustion chamber job stability, reduced the disposal of pollutants under the full operating mode.
(2) main combustion stage is divided into two-stage, avoided under the situation of main combustion stage one-level, main oil gas mixes the increase of the disposal of pollutants that variation causes when changeing level, can with under the big operating mode and the disposal of pollutants under the little operating mode reduce simultaneously, thereby further reduced the disposal of pollutants of whole LTO circulation.
(3) pre-membrane type nozzle is adopted in the main combustion stage second level, and it is more even that fuel oil is distributed, and further reduces pollutant emission.
(4) the present invention adopts monocycle cavity combustion chamber structure, and combustion air is all infeeded by head, has only blending hole and necessary cooling hole on the burner inner liner, has modular characteristics, has simplified chamber structure, and main combustion stage and pre-combustion grade structure are simpler, are easy to processing.
Description of drawings
Fig. 1 is the engine structure schematic diagram;
Fig. 2 is a chamber structure cutaway view of the present invention;
Fig. 3 is a head of combustion chamber structure cutaway view of the present invention;
Fig. 4 is a pre-combustion grade structure cutaway view of the present invention;
Fig. 5 is head construction cutaway view of the present invention (not comprising jet stem);
Fig. 6 is a fuel nozzle structure cutaway view of the present invention;
Fig. 7 is a main combustion stage outer shroud cutaway view of the present invention;
Fig. 8 is a cutaway view of crossing direct projection orifice center cross section (A-A cross section) in the main combustion stage of the present invention;
Wherein 1 is low-pressure compressor, the 2nd, high-pressure compressor, the 3rd, combustion chamber, the 4th, high-pressure turbine, the 5th, low-pressure turbine, the 6th, outer combustion case, the 7th, casing in the combustion chamber, the 8th, burner inner liner outer wall, the 9th, burner inner liner inwall, the 10th, diffuser, the 11st, burner inner liner outer wall blending hole, the 12nd, burner inner liner inwall blending hole, the 13rd, head of combustion chamber, the 14th, main combustion stage, the 15th, pre-combustion grade, the 16th, fuel nozzle, the 17th, pre-combustion grade mist of oil, the 18th, ring mist of oil in the main combustion stage, the 19th, main combustion stage oil film, the 20th, pre-combustion grade swirler assembly, the 21st, pre-combustion grade nozzle, the 22nd, the pre-combustion grade head end wall, the 23rd, the outer endless tube of pre-combustion grade, the 24th, pre-combustion grade Venturi tube, the 25th, pre-combustion grade swirler blades, the 26th, pre-combustion grade nozzle locating ring, the 27th, pre-combustion grade internal channel, the 28th, pre-combustion grade fuel pipe, the 29th, pre-combustion grade Venturi tube internal face, the 30th, the pre-combustion grade outlet, the 31st, premix and pre-evaporation ring outer shroud, the 32nd, pre-membrane type nozzle cyclone, the 33rd, ring in the premix and pre-evaporation ring, the 34th, the outer cyclone of main combustion stage, the 35th, cyclone in the main combustion stage, the 36th, the outer ring cavity of main combustion stage, the 37th, ring cavity in the main combustion stage, the 38th, the premix section, the 39th, pre-combustion grade atomizer, the 40th, atomizer in the main combustion stage, the 41st, pre-membrane type atomizer, the 42nd, ring in the pre-membrane type nozzle, the 43rd, pre-membrane type nozzle outer shroud, the 44th, main combustion stage outer shroud, the 45th, main combustion stage fuel oil internal channel, the 46th, fuel pipe in the main combustion stage, the 47th, the outer fuel pipe of main combustion stage, the 48th, main combustion stage internal combustion oil ring, the 49th, main combustion stage outlet, the 50th, spray orifice in the main combustion stage, the 51st, the whole end wall of head.
The specific embodiment
Fig. 1 is the engine structure schematic diagram, comprises low-pressure compressor 1, high-pressure compressor 2, combustion chamber 3, high-pressure turbine 4 and low-pressure turbine 5.During engine operation, after air compresses through low-pressure compressor 1, enter high-pressure compressor 2, pressure-air enters in the combustion chamber 3 and oil inflame again, the high-temperature high-pressure fuel gas that the burning back forms enters into high-pressure turbine 4 and low-pressure turbine 5, drives high-pressure compressor 2 and low-pressure compressor 1 respectively by the turbine acting.
As shown in Figure 2, the monocycle cavity configuration is adopted in combustion chamber 3, and casing 7 has constituted the outline of combustion chamber in outer combustion case 6 and the combustion chamber, and is connected with high-pressure turbine 4 with the high-pressure compressor 2 of front and back.The incoming flow air of high-pressure compressor 2 enters the combustion chamber behind diffuser 10 process reduction of speed diffusions, finish burning with fuel oil in the space that burner inner liner outer wall 8, burner inner liner inwall 9 and head of combustion chamber 13 are surrounded.Zone before blending hole 11 and the interior blending hole 12 is the combustion zone outside, and dilution air enters burner inner liner from blending hole, and the high-temperature fuel gas blending with the combustion zone makes outlet temperature reach designing requirement.Head of combustion chamber 13 comprises main combustion stage 14, pre-combustion grade 15 and fuel nozzle 16, main combustion stage 14 is fixing with burner inner liner outer wall 8 and 9 welding of burner inner liner inwall by the whole end wall 51 of head, pre-combustion grade 15 then is fixedly connected by pre-combustion grade head end wall 22 and main combustion stage 14, and fuel nozzle 16 is supplied with whole fuel oils.Described head of combustion chamber 13 is along circumferentially evenly arranging, number is 10～60, the air capacity of head of combustion chamber 13 accounts for 20%～80% of combustion chamber total air, and wherein main combustion stage 14 accounts for 60%～90% of head air capacity, and pre-combustion grade 15 accounts for 10%～40% of head air capacity.
Fig. 3 is the cutaway view of a head of combustion chamber structure, can find out clearly that main combustion stage 14 and pre-combustion grade 15 are arranged together according to concentric mode.Fig. 4 is a pre-combustion grade structure cutaway view, and as can see from Figure 4, pre-combustion grade 15 is made up of pre-combustion grade cyclone 20.Can see that from Fig. 4, Fig. 5, Fig. 6 pre-combustion grade cyclone 20 is vane type cyclone or groove-type cyclone, the structure of cyclone can be axial swirler or radial swirler.When pre-combustion grade cyclone 20 adopts the single-stage cyclone, directly be connected with pre-combustion grade head end wall 22, when pre-combustion grade cyclone 20 adopted multistage cyclone, cyclones at different levels connected into an integral body earlier, were connected with pre-combustion grade head end wall 22 behind the composition pre-combustion grade cyclone 20 again.Pre-combustion grade cyclone 20 is connected the mode that adopts welding or screw thread to add locking to be realized with pre-combustion grade head end wall 22.Pre-combustion grade cyclone 20 comprises the outer endless tube 23 of pre-combustion grade, pre-combustion grade Venturi tube 24, pre-combustion grade swirler blades 25.Pre-combustion grade swirler blades 25 is circumferentially even arranges and welds thereon, thereby outer endless tube 23 of pre-combustion grade and pre-combustion grade Venturi tube 24 are linked together, and the blade angle degree of pre-combustion grade swirler blades 25 is 30 °～70 °.Pre-combustion grade atomizer 21 is single pressure atomized fog jet, pneumatic nozzle or combined nozzle, directly be inserted into 27 li of pre-combustion grade nozzle locating ring 26 downstream internal channels, fuel oil through pre-combustion grade fuel pipe 28 forms pre-combustion grade mist of oil 17 by pre-combustion grade atomizer 21,17 dozens of pre-combustion grade mist of oils form oil film on pre-combustion grade cyclone Venturi tube internal face 29, under incoming flow effect, atomize, carry out diffusion combustion in pre-combustion grade outlet 30 through pre-combustion grade internal channel 27.
From Fig. 3, Fig. 5 and Fig. 6 can see, main combustion stage 14 is by premix and pre-evaporation outer shroud 31, ring 33 in the premix and pre-evaporation ring, main combustion stage fuel oil ring 48, ring 42 in the pre-membrane type nozzle, pre-membrane type nozzle outer shroud 43, the outer cyclone 34 of main combustion stage, cyclone 32 formations in cyclone 35 and the pre-membrane type nozzle in the main combustion stage, wherein cyclone 35 encircles 42 with pre-membrane type nozzle is interior in the main combustion stage, ring 33 welds together in the premix and pre-evaporation ring, constituted ring cavity 37 in the main combustion stage, the outer cyclone 34 of main combustion stage constitutes main combustion stage outer shroud 44 with premix and pre-evaporation ring outer shroud 31, constituted the outer ring cavity 36 of main combustion stage with pre-membrane type nozzle outer shroud 43, the inside and outside ring cavity 36 of main is merged into premix section 38 after pre-membrane type nozzle; The outer cyclone 34 of cyclone 35 and main combustion stage is the vane type cyclone in the main combustion stage that main combustion stage 15 adopts, and the blade angle degree is 30 °～70 °.The structure of every grade blade formula cyclone is an axial swirler, or radial swirler, and the two-stage rotation direction is identical or opposite.
As seen from Figure 6, fuel nozzle 16 is supplied with all fuel oils to the combustion chamber, fuel nozzle 16 comprises atomizer 40 and pre-membrane type atomizer 41 in pre-combustion grade atomizer 39, the main combustion stage, and fuel nozzle 16 directly inserts the main combustion stage outer shroud 44 from the upstream of head of combustion chamber 13.
From Fig. 6, can see among Fig. 8 that atomizer 40 is made up of direct projection spray orifice 50 in main combustion stage fuel oil internal channel 45 and the main combustion stage in the main combustion stage, ring 33 constitutes main combustion stage fuel oil internal channel 45 together in main combustion stage internal combustion oil ring 48 and the premix and pre-evaporation ring, is a loop configuration.Ring 33 upper edges circumferentially evenly have direct projection spray orifice 50 in a plurality of main combustion stages in the premix and pre-evaporation ring, fuel oil enters main combustion stage fuel oil internal channel 45 by fuel pipe in the main combustion stage 46, form ring spray mist 18 in the multiply main combustion stage through direct projection spray orifice in the main combustion stage 50 then, in main combustion stage, spray in the ring cavity 37.Pre-membrane type atomizer 41 by encircle 42 in the pre-membrane type nozzle, pre-membrane type nozzle outer shroud 43 and pre-membrane type cyclone 32 form; Fuel oil sprays to premix section 38 by pre-membrane type atomizer 41, evaporate and the premix blending under the effect of the inside and outside eddy flow of main combustion stage, in short physical dimension, realize the fuel oil rapid evaporation and with the even blending of air, enter main combustion stage outlet 49 and carry out premixed combustion, guarantee lower disposal of pollutants.
The number of the outer direct projection spray orifice 50 of direct projection spray orifice and main combustion stage is 6～30 in the main combustion stage, the ratio of the number of outer cyclone 34 blades of cyclone 35 and main combustion stage and the number of direct projection nozzle opening is that the formed inclination angle of ring 33 walls is 10 °～90 ° in 1: 1～5: 1 and the premix and pre-evaporation ring in the main combustion stage.Direct projection spray orifice axial location is in blade path downstream in the blade path inside and outside the main combustion stage or inside and outside the main combustion stage, and the axial distance of outer vent is 20～50mm in the main combustion stage.Pre-membrane type nozzle 41 outlet axial locations axial distance of outer vent 49 in the main combustion stage is 20～50mm, can open tangential slot on the ring 33 in main premix and pre-evaporation outer shroud 31, the premix and pre-evaporation ring, tangential slot and the formed inclination angle of premix and pre-evaporation ring inner and outer ring 31,33 walls are 10 °～90 °, and axial location axial distance of outer vent 49 in the main combustion stage is 20～50mm.The ratio that the main combustion stage fuel oil accounts for total amount of fuel is 50%～90%.
Claims (10)
1. a pre-membrane type divides the low pollution combustor of three grades of premix and pre-evaporations, it is characterized in that: the monocycle cavity configuration is adopted in described combustion chamber, and it constitutes its outline by casing (7) in outer combustion case (6) and the combustion chamber; Outside air enters by diffuser (10); Burner inner liner outer wall (8), burner inner liner inwall (9) and head of combustion chamber (13) are formed the combustion zone, combustion air all enters burner inner liner by head of combustion chamber (13), and dilution air is injected by outer blending hole (11) on the burner inner liner outer wall (8) and the interior blending hole (12) on the burner inner liner inwall (9); Described head of combustion chamber (13) adopts the fractional combustion scheme, is divided into main combustion stage (14) and pre-combustion grade (15); Described pre-combustion grade (15) is connected with main combustion stage (14) by pre-combustion grade head end wall (22), and it is concentric with main combustion stage (14), pre-combustion grade (15) outwards comprises pre-combustion grade swirler assembly (20), pre-combustion grade nozzle (21), pre-combustion grade head end wall (22) by the center, pre-combustion grade nozzle (21) and pre-combustion grade swirler assembly (20) cooperate the location, and pre-combustion grade swirler assembly (20) is connected with pre-combustion grade head end wall (22); Pre-combustion grade (15) is utilized the low speed recirculating zone retention flame that is entered the rotational flow air generation of combustion chamber by pre-combustion grade swirler assembly (20), and pre-combustion grade swirler assembly (20) is connected by ring (33) in pre-combustion grade head end wall (22) and the main combustion stage premix and pre-evaporation section; Pre-combustion grade nozzle (21) is positioned at pre-combustion grade swirler assembly (20), and coaxial with pre-combustion grade swirler assembly (20); Pre-combustion grade head end wall (22) is connected in to be encircled in the main combustion stage premix evaporator section on (33) and the outer endless tube (23) of pre-combustion grade; Wherein pre-combustion grade cyclone (20) comprises the outer endless tube (23) of pre-combustion grade, pre-combustion grade Venturi tube (24), pre-combustion grade swirler blades (25), pre-combustion grade nozzle locating ring (26), and pre-combustion grade swirler blades (25) connects the outer endless tube (23) of pre-combustion grade, pre-combustion grade Venturi tube (24), pre-combustion grade nozzle locating ring successively; Described main combustion stage (14) is by premix and pre-evaporation outer shroud (31), ring (33) in the premix and pre-evaporation ring, main combustion stage fuel oil ring (48), ring (42) in the pre-membrane type nozzle, pre-membrane type nozzle outer shroud (43), the outer cyclone (34) of main combustion stage, cyclone (32) formation in cyclone (35) and the pre-membrane type nozzle in the main combustion stage, wherein encircle (42) in cyclone (35) and the pre-membrane type nozzle in the main combustion stage, ring (33) ring cavity (37) in the main combustion stage that links together in the premix and pre-evaporation ring, the outer cyclone (34) of main combustion stage constitutes main combustion stage outer shroud (44) with premix and pre-evaporation ring outer shroud (31), main combustion stage outer shroud (44) and pre-membrane type nozzle outer shroud (43) have constituted the outer ring cavity (36) of main combustion stage, the inside and outside ring cavity (36,37) of main is merged into premix section (38) after pre-membrane type nozzle; Main combustion stage outer shroud (44) is connected and fixed by the whole end wall of head (51) and burner inner liner outer wall (8) and burner inner liner inwall (9), and ring cavity (37) and fuel nozzle (16) are one in the main combustion stage; Described fuel nozzle (16) is supplied with all fuel oils to the combustion chamber, fuel nozzle (16) outwards comprises that by the center pre-combustion grade atomizer (39), the interior atomizer (40) of main combustion stage and pre-membrane type atomizer (41) are an integral body, pre-combustion grade atomizer (39) is connected with pre-combustion grade nozzle locating ring (26), and pre-membrane type atomizer (41) and main combustion stage outer shroud (44) cooperate the location; Fuel nozzle (16) directly inserts the main combustion stage outer shroud (44) from the upstream of head of combustion chamber (13); Wherein pre-combustion grade atomizer (21) is a single-nozzle, directly be inserted into pre-combustion grade nozzle locating ring (26) downstream internal channel (27) lining, fuel oil through pre-combustion grade fuel pipe (28) forms pre-combustion grade mist of oil (17) by pre-combustion grade atomizer (21), pre-combustion grade mist of oil (17) is beaten at pre-combustion grade cyclone Venturi tube internal face (29) and is gone up the formation oil film, under incoming flow effect, atomize, carry out diffusion combustion in pre-combustion grade outlet (30) through pre-combustion grade internal channel (27); Atomizer (40) is made up of direct projection spray orifice (50) in fuel gallery in the main combustion stage (45) and the main combustion stage in the main combustion stage, be fixed in ring (33) inboard in the premix and pre-evaporation ring, encircle (33) main combustion stage fuel oil internal channel (45) of looping structure together in main combustion stage internal combustion oil ring (48) and the premix and pre-evaporation ring; Ring (33) upper edge circumferentially evenly has direct projection spray orifice (50) in a plurality of main combustion stages in the premix and pre-evaporation ring, fuel oil enters main combustion stage fuel gallery (45) by fuel pipe (46) in the main combustion stage, pass through the interior ring spray mist (18) of direct projection spray orifice (50) formation multiply main combustion stage in the main combustion stage then, spray to premix section (38); Evaporate and the premix blending under the effect of ring mist of oil (18) eddy flow in main combustion stage in the main combustion stage, realize the fuel oil rapid evaporation and with the even blending of air, pass through premix section (38) then and enter main combustion stage outlet (49) and carry out premixed combustion, guarantee lower disposal of pollutants; Pre-membrane type atomizer (41) is made up of ring (42), outer shroud (43) and pre-membrane type cyclone (32) in the pre-membrane type nozzle, and ring (42) and pre-membrane type nozzle outer shroud (43) are connected to form circumferential weld in the pre-membrane type nozzle, and pre-membrane type cyclone is embedded in the circumferential weld; Fuel oil forms the even main combustion stage oil film of one deck (19) by pre-membrane type atomizer (41) through pre-membrane type cyclone (32) and sprays to premix section (38); Main combustion stage oil film (19) evaporates under the effect of eddy flow inside and outside the main combustion stage and the premix blending, realize the fuel oil rapid evaporation and with the even blending of air, pass through premix section (38) then and enter main combustion stage outlet (49) and carry out premixed combustion, guarantee lower disposal of pollutants.
2. a kind of pre-membrane type according to claim 1 divides the low pollution combustor of three grades of premix and pre-evaporations, it is characterized in that: described pre-combustion grade atomizer (21) is pressure atomized fog jet, pneumatic nozzle or combined nozzle.
3. a kind of pre-membrane type according to claim 1 divides the low pollution combustor of three grades of premix and pre-evaporations, it is characterized in that: described pre-combustion grade cyclone (20) is vane type or groove-type cyclone, blade angle degree and conduit angle are 30 °～70 °, and the progression n of pre-combustion grade cyclone (20) is 1≤n≤3; The structure of every grade blade formula cyclone is an axial swirler, or radial swirler; When pre-combustion grade cyclone (20) progression n=1, pre-combustion grade cyclone (20) directly connects with the whole end wall of pre-combustion grade head (22); When pre-combustion grade cyclone (20) progression n＞1, vane type cyclones at different levels connect into an integral body earlier, are connected with pre-combustion grade head end wall (22) after forming pre-combustion grade cyclone (20) again.
4. a kind of pre-membrane type according to claim 1 divides the low pollution combustor of three grades of premix and pre-evaporations, it is characterized in that: the required whole fuel oils in described fuel nozzle (16) supply combustion chamber, the ratio that the main combustion stage fuel oil accounts for total amount of fuel is 50%～90%.
5. a kind of pre-membrane type according to claim 1 divides the low pollution combustor of three grades of premix and pre-evaporations, it is characterized in that: the outer cyclone (34) of cyclone (35) and main combustion stage is the vane type cyclone in the described main combustion stage, and the blade angle degree is 30 °～70 °; The structure of every grade blade formula cyclone is an axial swirler, or radial swirler, and the two-stage rotation direction is identical or opposite.
6. a kind of pre-membrane type according to claim 1 divides the low pollution combustor of three grades of premix and pre-evaporations, it is characterized in that: the number of direct projection spray orifice (50) is 6～30 in the described main combustion stage, and the ratio of the number of the number of cyclone (35) blade and direct projection nozzle opening (50) is 1: 1～5: 1 in the main combustion stage.
7. a kind of pre-membrane type according to claim 1 divides the low pollution combustor of three grades of premix and pre-evaporations, it is characterized in that: the formed inclination angle of ring (33) wall is 10 °～90 ° in described direct projection spray orifice (50) and the premix and pre-evaporation ring, is 1: 2～1: 5 with the valid circulation area ratio of corresponding fuel gallery (45); Described direct projection spray orifice (50) axial location is 20～50mm apart from the axial distance of main combustion stage outlet (49).
8. a kind of pre-membrane type according to claim 1 divides the low pollution combustor of three grades of premix and pre-evaporations, it is characterized in that: described pre-membrane type nozzle (41) outlet axial location is 20～50mm apart from the axial distance of main combustion stage outlet (49).
9. a kind of pre-membrane type according to claim 1 divides the low pollution combustor of three grades of premix and pre-evaporations, it is characterized in that: open tangential slot on the ring (33) in described main premix and pre-evaporation outer shroud (31), the premix and pre-evaporation ring, the formed inclination angle of ring (33) wall is 10 °～90 ° in tangential slot and main premix and pre-evaporation outer shroud (31), the premix and pre-evaporation ring, and axial location is 20～50mm apart from the axial distance of main combustion stage outlet (49).
10. a kind of pre-membrane type according to claim 1 divides the low pollution combustor of three grades of premix and pre-evaporations, it is characterized in that: described head of combustion chamber (13) is along circumferentially evenly arranging, number is 10～60, the air capacity of head of combustion chamber (13) accounts for 20%～80% of combustion chamber total air, wherein main combustion stage (14) accounts for 60%～90% of head air capacity, and pre-combustion grade (15) accounts for 10%～40% of head air capacity.
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