CN105180215A - Low-pollution combustion chamber with main combustion stage adopting single-layer pre-film radial two-grade reverse rotational flow - Google Patents
Low-pollution combustion chamber with main combustion stage adopting single-layer pre-film radial two-grade reverse rotational flow Download PDFInfo
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Abstract
The invention discloses a low-pollution combustion chamber with a main combustion stage adopting single-layer pre-film radial two-grade reverse rotational flow. The low-pollution combustion chamber adopts a single annular cavity structure, and comprises a diffuser, a combustion outdoor box, a combustion indoor box, a flame cylinder outer wall, a flame cylinder inner wall and a combustion chamber head part; the combustion chamber adopts a classification combustion scheme; the combustion head part is divided into a pre-combustion stage and the main combustion stage; the pre-combustion stage adopts a mode of combining rotational flow-stable diffusion combustion with rotational flow premixing combustion; the combustion mode reduces the pollutant discharge under small working conditions when not influencing stable combustion; and the main combustion stage adopts a premixing pre-evaporation combustion mode to be in favor of uniform combustion. The combustion chamber adopts a center classification structure; the pre-combustion stage is simple in structure; the main combustion grade adopts a two-grade reverse cyclone distributed in the radial direction; and two parts of reverse rotational flows shear an oil film, so that the atomization effect is greatly improved, the atomization of fuel of the main combustion stage and the mixing with air are enhanced, the premixing pre-evaporation of the fuel is reinforced, and the pollution discharge of whole landing and taking-off circulation of an aero-engine combustion chamber is further reduced.
Description
Technical field
The present invention relates to the technical field of aero-gas turbine, be specifically related to the aero-gas turbine low pollution combustor that a kind of main combustion stage adopts the reverse eddy flow of the radial two-stage of the pre-film of individual layer, this combustion chamber adopts the pattern of fractional combustion, pre-combustion grade is at center, adopt the mode that diffusion combustion and premixed combustion combine, while guarantee combustion chamber smooth combustion, reduce the disposal of pollutants under little operating mode; Main combustion stage is peripheral in pre-combustion grade, adopts the mode of premix and pre-evaporation burning, is mainly used in reducing the disposal of pollutants under large operating mode, thus reduces the whole landing of aero-engine and to take off the disposal of pollutants that circulation (LandingandTake-off, LTO) circulates.
Background technology
The key property of modern aeroengine combustion chamber and structure distribution have reached quite high level, but for modern aeroengine combustion chamber, still there is a large amount of difficult problems and challenge, the development and application of new material, new technology, new construction, new ideas is only the source ensureing its continuous advancement.
The Main Trends of The Development of modern civil engine combustion chamber is combustion with reduced pollutants.Civil engine combustion chamber must meet the aero-engine emission standard of increasingly stringent.CAEP6 (CommitteeonAviationEnvironmentalProtection) standard of current employing is very strict to the regulation of pollutant effulent, particularly to NOx emission requirement; And the discharge standard being emitted on CAEP6 that up-to-date CAEP8 standard proposes NOx reduces by 15%, along with the fast development of aircraft industry and improving constantly of people's environmental consciousness, followingly to gas-turbine combustion chamber disposal of pollutants, higher requirement can be proposed.
Liang Ge leading company GE and PW of US Airways engine sets about research already to low pollution combustor, first GE have developed dicyclo chamber combustion with reduced pollutants DAC (for GE90 and CFM56), PW company have employed RQL (fuel-rich combustion-extinguishing-poor oil firing, Richburn-Quench-Leanburn, is called for short RQL) low pollution combustor TALONII (for PW4000 and 6000 series).In low pollution combustor of future generation, GE company employing LDM (LeanDirectMixingCombustion, oil-poor direct hybrid combustor) technology is TAPS (TwinAnnularPremixingSwirler) low pollution combustor of its GEnx reseach of engine.This combustion chamber is in stand loopful verification experimental verification, and NOx disposal of pollutants reduces 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 are all that pre-combustion grade adopts diffusion combustion, main combustion stage to adopt the combustion method of premixed combustion, and object is the NOx emission reduced under the maximum large operating mode of pollution index.It is TALONX that PW company continues to adopt RQL mode to propose the low pollution combustor reducing NOx disposal of pollutants, the head type adopted is the air atomizer spray nozzle of PW development of company, combustion chamber is monocycle chamber, and the result of the test on V2500 engine fan test section reduces 50% than CAEP2 standard.Rolls-Royce company adopts the low pollution combustor of LDM technical development to be ANTLE, and this combustion chamber is fractional combustion room, a monocycle chamber, and its NOx disposal of pollutants reduces 50% than CAEP2 standard, reaches 1000 for its engine rapids of new generation.
Aero-Space university of BeiJing, China has also applied for 200910238793.X to low pollution combustor, 201010101574.X, 201010034141.7, 201010277014.X etc. multinomial patent, the scheme adopted is that pre-combustion grade adopts diffusion combustion mode, main combustion stage adopts premixed combustion mode, main combustion stage is loop configuration, axial or radial fuel feeding, adopt multi-point injection or pre-film atomizing type, object is the NOx emission under the large operating mode of reduction, thus the discharge of the NOx making whole LTO circulate is reduced, but the emission level difficulty that will reduce the NOx that whole LTO circulates further is larger.
Above-described patent, all at large operating mode decline low pollution emission, and according to International Civil Aviation Organization (InternationalCivilAviationOrganization, ICAO) the emission index under the standard cycle specified, express this parameter with LTOEmission, be calculated as follows formula:
From above formula, LTOEmission is relevant, namely both relevant with the NOx emission under large operating mode, also relevant with the NOx emission under little operating mode with the NOx discharge under four operating modes.
Operational mode in standard LTO circulation, the thrust under each operational mode and running time, as shown in the table.
Operational mode in the LTO circulation that table 1ICAO specifies and time
| Operational mode | Thrust is arranged | Running time (min) |
| Take off (Take-off) | 100％F oo | 0.7 |
| Climb (Climb) | 85％F oo | 2.2 |
| March into the arena (Approach) | 30％F oo | 4.0 |
| Slide/ground idle speed (Taxi/ground idle) | 7％F oo | 26.0 |
The thrust of conventional or active service in the NOx emission of the CFM56-5B/3 engine of 140KN as following table, data from ICAOEmissiondatabank.
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 |
Combustion chamber adopts fractional combustion, and pre-combustion grade is diffusion combustion mode, and main combustion stage is premixed combustion mode, reduces the NOx emission under large operating mode, and the NOx emission that can reach 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), although NOx emission index is lower, according to the running time under the known little operating mode of table 1 far away higher than other large operating modes, known according to table 3, when main combustion stage adopts premixed combustion mode, the NOx emission index under large operating mode can be made significantly to be reduced, the proportion accounted in the disposal of pollutants discharge that now the NOx emission total amount of pre-combustion grade circulates at whole LTO is maximum, therefore want the NOx emission reducing whole LTO circulation further, just need the NOx emission considering to reduce pre-combustion grade.
And be no matter the low pollution combustor of which kind of advanced person, the combustion technology that its key technology reduces NOx (nitrogen oxide), CO (carbon monoxide), UHC (unburned hydrocarbons) exactly and smolders, key problem reduces the temperature of combustion zone, make combustion zone temperature field even simultaneously, namely the equivalent proportion of whole and part controls, 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.The mechanism produced according to NOx and CO and result of the test: NOx and the CO (emission equivalent of UHC and CO is similar) that the primary zone equivalent proportion of combustion chamber produces in 0.6 ~ 0.8 scope is little.Based on this principle, take into account NOx and CO, the discharge capacity of UHC is all in 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: one is the uniformity that fuel particles diameter distributes, i.e. the distributing homogeneity of SMD; Second be the uniformity of fuel oil oil mist concentration distribution.From combustion system, uniform premixed combustion should be adopted, reach primary zone equivalent proportion uniformity requirement to reduce disposal of pollutants.
Current conventional combustion manner cannot reduce NOx, CO and UHC.Reason is that the method for designing of current combustion room determines.For conventional combustion room, when large state, owing to adopting liquid mist diffusion combustion mode, local, combustion zone equivalent proportion is always near 1, far exceed equivalence ratio range requirement needed for above-mentioned combustion with reduced pollutants, although now the discharge of CO and UHC is low, the discharge of NOx reaches maximum.When little state, combustion zone equivalent proportion is very low again, interval far below equivalent proportion needed for above-mentioned combustion with reduced pollutants, although now NOx emission is low, CO and UHC discharge is very high again.In addition, because conventional combustion room generally adopts diffusion combustion mode, local equivalent proportion is uneven, therefore for conventional combustion room, cannot meet the low stain requirement in whole engine working range.
Summary of the invention
The technical problem to be solved in the present invention is: overcome prior art deficiency, use premix and pre-evaporation combustion technology, provide the low pollution combustor that a kind of main combustion stage adopts the reverse eddy flow of the radial two-stage of the pre-film of individual layer, combustion chamber adopts the pattern of fractional combustion, pre-combustion grade is at center, adopt the mode that diffusion combustion and premixed combustion combine, while guarantee combustion chamber smooth combustion, reduce the disposal of pollutants under little operating mode; Main combustion stage is peripheral in pre-combustion grade, adopts the mode of premix and pre-evaporation burning, is mainly used in reducing the disposal of pollutants under large operating mode, thus reduces the disposal of pollutants of the whole LTO circulation of aero-engine.
The technical solution adopted for the present invention to solve the technical problems is: a kind of main combustion stage adopts the low pollution combustor of the reverse eddy flow of the radial two-stage of the pre-film of individual layer, this low pollution combustor adopts monocycle cavity configuration, is made up of casing, burner inner liner outer wall, burner inner liner inwall and head of combustion chamber in diffuser, outer combustion case, combustion chamber, combustion air all enters burner inner liner by head of combustion chamber, and dilution air is injected by blending hole, adopt fractional combustion scheme, be divided into pre-combustion grade and main combustion stage, fuel nozzle supply combustion chamber all fuel oils, main combustion stage is fixed by the overall end wall of head and burner inner liner outer wall and burner inner liner inwall, pre-combustion grade is then connected with main combustion stage by inter-stage section, and concentric with main combustion stage, described main combustion stage is made up of main combustion stage inward eddy device, main combustion stage contour stealth device, the pre-lamina membranacea of main combustion stage, the overall end wall of head and the overall flow deflector of head, main combustion stage fuel oil enters main combustion stage fuel oil collection chamber by main combustion stage fuel pipe, enter main combustion stage fuel oil oil transportation hole subsequently, the pre-lamina membranacea internal channel of main combustion stage is sprayed into by main combustion stage fuel oil spray orifice, part fuel oil forms the straight oil spray of main combustion stage, part fuel oil is got on pre-lamina membranacea and is formed even oil film, under two bursts of reverse rotational-flow shearing effects of main combustion stage pre-lamina membranacea internal channel and pre-lamina membranacea internal channel, broken atomization forms main combustion stage pneumatic nebulization mist of oil, two strands of mist of oils and air carry out blending and form more uniform gas mixture, uniform gas mixture enters burner inner liner and carries out premixed combustion.
Further, the progression of the cyclone of described pre-combustion grade employing is 1≤n≤5; Every grade of cyclone adopts the structure of cyclone to be axial swirler, or radial swirler, or tangential cyclones; As the progression n=1 of pre-combustion grade, cyclone is directly connected with inter-stage section; When progression 1<n≤5 of pre-combustion grade, cyclone at different levels first connects into an entirety, then is connected with combustion level head end wall.
Further, described main combustion stage adopts the reverse hydrocyclone structure of two-stage, and every grade of cyclone adopts the structure of cyclone to be axial swirler, or radial swirler, or tangential cyclones, and two-stage cyclones radial arrangement, greatly strengthen oil gas blending uniformity.
Further, described main combustion stage fuel oil adopts the discrete horizontal spray of circumference, part fuel oil forms straight oil spray, part fuel oil is beaten and form oil film on the pre-lamina membranacea of main combustion stage, add circumferential uniformity, under main combustion stage pre-lamina membranacea internal channel and the reverse rotational-flow shearing effect of pre-lamina membranacea internal channel, broken atomization forms main combustion stage pneumatic nebulization mist of oil.
Further, the described whole fuel oils of fuel nozzle supply needed for combustion chamber, the ratio that main combustion stage fuel oil accounts for total amount of fuel is 50% ~ 90%.
Further, described head of combustion chamber is circumferentially evenly arranged, and number is 10 ~ 60, and the air capacity of head of combustion chamber accounts for 20% ~ 80% of combustion chamber total air, wherein main combustion stage accounts for 60% ~ 90% of head air capacity, and pre-combustion grade accounts for 10% ~ 40% of head air capacity.
Further, the burner inner liner outer wall of described combustion chamber and the type of cooling of burner inner liner inwall adopt gaseous film control, disperse cooling or Compound cooling mode, to carry out the life-span controlling to extend burner inner liner to wall surface temperature.
Further, described burner inner liner external rear wall is provided with burner inner liner outer wall blending hole, described burner inner liner inwall rear portion is provided with burner inner liner inwall blending hole, blending gas enters burner inner liner, with control combustion room Exit temperature distribution from burner inner liner outer wall blending hole and burner inner liner inwall blending hole respectively.
Principle of the present invention is as follows: reach by the equivalent proportion and the uniformity that control aeroengine combustor buring Indoor Combustion district the object reducing disposal of pollutants.Combustion air all enters burner inner liner from head of combustion chamber, enters burner inner liner burning after making most fuel oil and air blending evenly again, reduces disposal of pollutants favourable to control combustion district equivalent proportion.Employing center hierarchy and fractional combustion scheme, pre-combustion grade, at center, is the mode that diffusion combustion combines with swirl-flow premixed burning, for ensureing the combustion stability of whole combustion chamber and main combustion stage of igniting; Main combustion stage is peripheral in pre-combustion grade, is premixed combustion mode, liquid fuel evaporate in premix and pre-evaporation section and with air blending, form uniform combustible gas and enter combustion chamber and participate in burning.Main combustion stage part fuel oil forms the straight oil spray of main combustion stage by nozzle opening ejection, another part fuel oil is got on pre-lamina membranacea and is formed even oil film, under two bursts of reverse rotational-flow shearing effects of main combustion stage pre-lamina membranacea internal channel and pre-lamina membranacea internal channel, broken atomization forms main combustion stage pneumatic nebulization mist of oil, two strands of mist of oils and air carry out blending and form more uniform gas mixture, and uniform gas mixture enters burner inner liner and carries out premixed combustion.
The advantage that the present invention is compared with prior art had is as follows:
(1), main combustion stage of the present invention adopts the pre-film of individual layer, add the circumferential uniformity of fuel oil, the cyclone eddy flow direction of two-stage radial arrangement is contrary, the eddy flow reversely rotated is stronger to the shear action of oil film, better to fuel oil mixing diffusion effect, air-fuel mixture is more even, prevapourising better effects if, is conducive to homogenous combustion, reduces the disposal of pollutants of combustion chamber;
(2), the present invention adopts monocycle cavity combustion chamber structure, and combustion air is all fed by head, burner inner liner only has blending hole and necessary Cooling Holes, there is modular characteristics, simplify chamber structure, premix and pre-evaporation circular tube structure is simple, is easy to processing; Main combustion stage structure is simple, is easy to assembling;
(3), the present invention adopts fractional combustion concept, and pre-combustion grade provides steady burning things which may cause a fire disaster, and main combustion stage realizes combustion with reduced pollutants, can guarantee the stability of aeroengine combustor buring room while reducing disposal of pollutants.
Accompanying drawing explanation
Fig. 1 is engine structure schematic diagram;
Fig. 2 is chamber structure sectional view of the present invention;
Fig. 3 is head of combustion chamber structure sectional view of the present invention;
Fig. 4 is pre-combustion grade structure sectional view of the present invention;
Fig. 5 is main combustion stage structure sectional view of the present invention;
Wherein the implication of Reference numeral is: 1 is low-pressure compressor, 2 is high-pressure compressors, 3 is combustion chambers, 4 is high-pressure turbines, 5 is low-pressure turbines, 6 is outer combustion cases, 7 is casings in combustion chamber, 8 is burner inner liner outer walls, 9 is burner inner liner inwalls, 10 is diffusers, 11 is burner inner liner outer wall blending hole, 12 is burner inner liner inwall blending hole, 13 is head of combustion chamber, 14 is main combustion stages, 15 is pre-combustion grade, 16 is fuel nozzles, 17 is pre-combustion grade mist of oils, 18 is the straight oil spraies of main combustion stage, 19 is main combustion stage pneumatic nebulization mist of oils, 20 is pre-combustion grade inward eddy devices, 21 is pre-combustion grade contour stealth devices, 22 is main combustion stage outer walls, 23 is the pre-sections of premix, 24 is main combustion stage inward eddy devices, 25 is main combustion stage contour stealth devices, 26 is the pre-lamina membranaceas of main combustion stage, 27 is pre-combustion grade atomizer installing holes, 28 is pre-combustion grade inward eddy Venturi tubes, 29 is pre-combustion grade mounting edges, 30 is inter-stage sections, 31 is main combustion stage atomizer fuel feed holes, 32 is main combustion stage fuel oil collection chambers, 33 is main combustion stage fuel oil oil transportation holes, 34 is main combustion stage fuel oil spray orifices, 35 is pre-combustion grade atomizers, 36 is main combustion stage fuel pipes, 37 is pre-combustion grade fuel pipes, 38 is the pre-lamina membranacea internal channels of main combustion stage, 39 is the pre-lamina membranacea outer tunnels of main combustion stage, 40 is the overall end walls of head, 41 is the overall flow deflectors of head.
Detailed description of the invention
The present invention is further illustrated below in conjunction with the drawings and specific embodiments.
Fig. 1 is 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, air is after low-pressure compressor 1 compresses, enter high-pressure compressor 2, pressure-air enter again in combustion chamber 3 with oil inflame, the high-temperature high-pressure fuel gas formed after burning enters into high-pressure turbine 4 and low-pressure turbine 5, and being done work by turbine drives high-pressure compressor 2 and low-pressure compressor 1 respectively.
As shown in Figure 2, head of combustion chamber adopts center hierarchy, and pre-combustion grade is at center, and main combustion stage is peripheral in pre-combustion grade.Combustion chamber 3 adopts monocycle cavity configuration, and in outer combustion case 6 and combustion chamber, casing 7 constitutes the outline of combustion chamber, and is connected with the high-pressure compressor 2 of front and back and high-pressure turbine 4.The incoming air of high-pressure compressor 2 enters combustion chamber from diffuser 10 after reduction of speed diffusion, in the space that burner inner liner outer wall 8, burner inner liner inwall 9 and head of combustion chamber 13 surround, complete burning with fuel oil.Blending hole 11 and interior blending hole 12 region are in the past combustion zone outside, and dilution air enters burner inner liner from blending hole, and the high-temperature fuel gas blending with 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 welded and fixed with burner inner liner outer wall 8 and burner inner liner inwall 9 by the overall end wall 40 of head, and pre-combustion grade 15 is fixedly connected by inter-stage section 30 and main combustion stage 14, fuel nozzle 16 supplies whole fuel oil.The overall flow deflector 41 of head is welded on the overall end wall 40 of head, makes it separate with the high-temperature fuel gas in burner inner liner, with operator guards integrality.
Fig. 3 is the sectional view of head of combustion chamber 13 structure, and main combustion stage 14 and pre-combustion grade 15 are arranged together according to concentric mode, and pre-combustion grade is at center, and main combustion stage is arranged in pre-combustion grade periphery.Head of combustion chamber 13 is circumferentially evenly arranged, and number is 10 ~ 60, and its air capacity 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.Pre-combustion grade atomizer 40 is pressure atomized fog jet, pneumatic nozzle or combined nozzle.
In the diagram, pre-combustion grade 15 have employed double cyclones structure, and be made up of pre-combustion grade inward eddy device 20, pre-combustion grade contour stealth 21, pre-combustion grade inward eddy Venturi tube 28 and inter-stage section 30, four weld together.Pre-combustion grade mist of oil 17 utilizes pre-combustion grade inward eddy Venturi tube 28 to be atomized further.
Main combustion stage 14 is made up of main combustion stage inward eddy device 24, main combustion stage contour stealth device 25, the pre-lamina membranacea 26 of main combustion stage, the overall end wall 40 of head and the overall flow deflector 41 of head, and all parts all weld together.Main combustion stage fuel oil, the pre-lamina membranacea internal channel 38 of main combustion stage is sprayed into by main combustion stage fuel oil spray orifice 34, part fuel oil forms the straight oil spray 18 of main combustion stage, part fuel oil is got on pre-lamina membranacea 23 and is formed even oil film, under the rotational-flow shearing effect that main combustion stage pre-lamina membranacea internal channel 38 and pre-lamina membranacea internal channel 39 two strands reversely rotate, broken atomization formation main combustion stage pneumatic nebulization mist of oil 19, two strands of mist of oils and air carry out blending and form more uniform gas mixture.
The above; be only the detailed description of the invention in the present invention; but protection scope of the present invention is not limited thereto; any people being familiar with this technology is in the technical scope disclosed by the present invention; the conversion or replacement expected can be understood; all should be encompassed in and of the present inventionly comprise within scope, therefore, protection scope of the present invention should be as the criterion with the protection domain of claims.
Claims (8)
1. the low pollution combustor of the reverse eddy flow of the radial two-stage of the pre-film of main combustion stage employing individual layer, it is characterized in that: this low pollution combustor adopts monocycle cavity configuration, is made up of casing (7), burner inner liner outer wall (8), burner inner liner inwall (9) and head of combustion chamber (13) in diffuser (10), outer combustion case (6), combustion chamber, combustion air all enters burner inner liner by head of combustion chamber (13), and dilution air is injected by blending hole, adopt fractional combustion scheme, be divided into pre-combustion grade (15) and main combustion stage (14), the all fuel oils in fuel nozzle (16) supply combustion chamber, main combustion stage (14) is fixed with burner inner liner outer wall (8) and burner inner liner inwall (9) by the overall end wall (40) of head, pre-combustion grade (15) is then connected with main combustion stage (14) by inter-stage section (30), and concentric with main combustion stage (14), described main combustion stage (14) is made up of main combustion stage inward eddy device (24), main combustion stage contour stealth device (25), the pre-lamina membranacea of main combustion stage (26), the overall end wall (40) of head and the overall flow deflector (41) of head, main combustion stage fuel oil enters main combustion stage fuel oil collection chamber (32) by main combustion stage fuel pipe (36), enter main combustion stage fuel oil oil transportation hole (33) subsequently, the pre-lamina membranacea internal channel (38) of main combustion stage is sprayed into by main combustion stage fuel oil spray orifice (34), part fuel oil forms the straight oil spray of main combustion stage (18), the even oil film of the upper formation of pre-lamina membranacea (23) got to by part fuel oil, under two bursts of reverse rotational-flow shearing effects of main combustion stage pre-lamina membranacea internal channel (38) and pre-lamina membranacea internal channel (39), broken atomization forms main combustion stage pneumatic nebulization mist of oil (19), two strands of mist of oils and air carry out blending and form more uniform gas mixture, uniform gas mixture enters burner inner liner and carries out premixed combustion.
2. a kind of main combustion stage according to claim 1 adopts the low pollution combustor of the reverse eddy flow of the radial two-stage of the pre-film of individual layer, it is characterized in that: the progression of the cyclone that described pre-combustion grade (15) adopts is 1≤n≤5; Every grade of cyclone adopts the structure of cyclone to be axial swirler, or radial swirler, or tangential cyclones; As the progression n=1 of pre-combustion grade (15), cyclone is directly connected with inter-stage section (30); When progression 1<n≤5 of pre-combustion grade (15), cyclone at different levels first connects into an entirety, then is connected with combustion level head end wall (30).
3. a kind of main combustion stage according to claim 1 adopts the low pollution combustor of the reverse eddy flow of the radial two-stage of the pre-film of individual layer, it is characterized in that: described main combustion stage (14) adopts the hydrocyclone structure that two-stage rotation direction is contrary, two-stage cyclones radial arrangement, every grade of cyclone adopts the structure of cyclone to be axial swirler, or radial swirler, or tangential cyclones, two-stage cyclones radial distribution, greatly strengthen oil gas blending uniformity.
4. a kind of main combustion stage according to claim 1 adopts the low pollution combustor of the reverse eddy flow of the radial two-stage of the pre-film of individual layer, it is characterized in that: described main combustion stage (14) fuel oil adopts the discrete horizontal spray of circumference, part fuel oil forms straight oil spray, part fuel oil is beaten and form oil film on the pre-lamina membranacea of main combustion stage (26), add circumferential uniformity, under main combustion stage pre-lamina membranacea internal channel (38) and (39) the two bursts of reverse rotational-flow shearing effects of pre-lamina membranacea internal channel, broken atomization forms main combustion stage pneumatic nebulization mist of oil (19).
5. a kind of main combustion stage according to claim 1 adopts the low pollution combustor of the reverse eddy flow of the radial two-stage of the pre-film of individual layer, it is characterized in that: the described whole fuel oils of fuel nozzle (16) supply needed for combustion chamber, the ratio that main combustion stage fuel oil accounts for total amount of fuel is 50% ~ 90%.
6. a kind of main combustion stage according to claim 1 adopts the low pollution combustor of the reverse eddy flow of the radial two-stage of the pre-film of individual layer, it is characterized in that: described head of combustion chamber (13) is circumferentially evenly arranged, 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.
7. a kind of main combustion stage according to claim 1 adopts the low pollution combustor of the reverse eddy flow of the radial two-stage of the pre-film of individual layer, it is characterized in that: the burner inner liner outer wall (8) of described combustion chamber and the type of cooling of burner inner liner inwall (9) adopt gaseous film control, disperse cooling or Compound cooling mode, to carry out the life-span controlling to extend burner inner liner to wall surface temperature.
8. a kind of main combustion stage according to claim 1 adopts the low pollution combustor of the reverse eddy flow of the radial two-stage of the pre-film of individual layer, it is characterized in that: described burner inner liner outer wall (8) rear portion is provided with burner inner liner outer wall blending hole (11), described burner inner liner inwall (9) rear portion is provided with burner inner liner inwall blending hole (12), blending gas enters burner inner liner, with control combustion room Exit temperature distribution from burner inner liner outer wall blending hole (11) and burner inner liner inwall blending hole (12) respectively.
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| CN201621089663.6U CN206281002U (en) | 2015-10-16 | 2016-09-28 | Main combustion stage uses the low pollution combustor of the pre- reverse eddy flow of film radial direction two-stage of individual layer |
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| CN201621089663.6U Active CN206281002U (en) | 2015-10-16 | 2016-09-28 | Main combustion stage uses the low pollution combustor of the pre- reverse eddy flow of film radial direction two-stage of individual layer |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105733730A (en) * | 2016-02-04 | 2016-07-06 | 黑龙江泰昇农业科技开发有限公司 | Biomass micron carbonized power high-temperature combustion method |
| CN108592084A (en) * | 2018-05-17 | 2018-09-28 | 北京航空航天大学 | A kind of main combustion stage matches the low emission combustor head of blade injection structure using the pre- diaphragm plate of axial rotational flow |
| CN109737451A (en) * | 2019-01-23 | 2019-05-10 | 南方科技大学 | A kind of fuel gas is prewhirled the low emission combustor of injection |
| WO2020001606A1 (en) * | 2018-06-29 | 2020-01-02 | 中国航发商用航空发动机有限责任公司 | Low pollution combustor and combustion control method therefor |
| CN111520757A (en) * | 2020-03-31 | 2020-08-11 | 西北工业大学 | Direct injection type concave cavity swirl nozzle |
| CN111623375A (en) * | 2019-02-28 | 2020-09-04 | 中国航发商用航空发动机有限责任公司 | Device for cooling fuel nozzle and aircraft engine comprising same |
| CN113464982A (en) * | 2021-07-02 | 2021-10-01 | 中国航空发动机研究院 | Center staged combustion chamber based on self-excitation sweep oscillation fuel nozzle |
| CN115218217A (en) * | 2022-06-16 | 2022-10-21 | 北京航空航天大学 | Main combustion stage head of central staged combustion chamber adopting porous multi-angle oil injection ring structure |
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| CN108252811A (en) * | 2017-12-27 | 2018-07-06 | 中国航发四川燃气涡轮研究院 | A kind of multi-point spraying apparatus for strengthening atomization |
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| CN113280367B (en) * | 2021-05-31 | 2022-08-02 | 中国航空发动机研究院 | Staged combustion chamber head with swirl pre-membrane plate structure |
-
2015
- 2015-10-16 CN CN201510674145.4A patent/CN105180215A/en not_active Withdrawn
-
2016
- 2016-09-28 CN CN201621089663.6U patent/CN206281002U/en active Active
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105733730A (en) * | 2016-02-04 | 2016-07-06 | 黑龙江泰昇农业科技开发有限公司 | Biomass micron carbonized power high-temperature combustion method |
| CN108592084A (en) * | 2018-05-17 | 2018-09-28 | 北京航空航天大学 | A kind of main combustion stage matches the low emission combustor head of blade injection structure using the pre- diaphragm plate of axial rotational flow |
| CN110657452B (en) * | 2018-06-29 | 2020-10-27 | 中国航发商用航空发动机有限责任公司 | Low-pollution combustion chamber and combustion control method thereof |
| WO2020001606A1 (en) * | 2018-06-29 | 2020-01-02 | 中国航发商用航空发动机有限责任公司 | Low pollution combustor and combustion control method therefor |
| CN110657452A (en) * | 2018-06-29 | 2020-01-07 | 中国航发商用航空发动机有限责任公司 | Low-pollution combustion chamber and combustion control method thereof |
| US11506387B2 (en) | 2018-06-29 | 2022-11-22 | Aecc Commercial Aircraft Engine Co., Ltd. | Low-pollution combustor and combustion control method therefor |
| CN109737451A (en) * | 2019-01-23 | 2019-05-10 | 南方科技大学 | A kind of fuel gas is prewhirled the low emission combustor of injection |
| CN111623375A (en) * | 2019-02-28 | 2020-09-04 | 中国航发商用航空发动机有限责任公司 | Device for cooling fuel nozzle and aircraft engine comprising same |
| CN111520757B (en) * | 2020-03-31 | 2022-06-10 | 西北工业大学 | Direct injection type concave cavity swirl nozzle |
| CN111520757A (en) * | 2020-03-31 | 2020-08-11 | 西北工业大学 | Direct injection type concave cavity swirl nozzle |
| CN113464982A (en) * | 2021-07-02 | 2021-10-01 | 中国航空发动机研究院 | Center staged combustion chamber based on self-excitation sweep oscillation fuel nozzle |
| WO2023273305A1 (en) * | 2021-07-02 | 2023-01-05 | 中国航空发动机研究院 | Center-staged combustion chamber based on self-excitation sweep oscillation fuel nozzles |
| CN115218217A (en) * | 2022-06-16 | 2022-10-21 | 北京航空航天大学 | Main combustion stage head of central staged combustion chamber adopting porous multi-angle oil injection ring structure |
| CN115218217B (en) * | 2022-06-16 | 2023-06-16 | 北京航空航天大学 | Main combustion stage head of central staged combustion chamber adopting porous multi-angle oil injection ring structure |
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