CN105041539A - Multilevel rotational flow combined type air atomized fuel nozzle device and control method thereof - Google Patents
Multilevel rotational flow combined type air atomized fuel nozzle device and control method thereof Download PDFInfo
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Abstract
The invention relates to a multilevel rotational flow combined type air atomized fuel nozzle device and a control method thereof. The device is applied to a high temperature rise combustor. A head swirler comprises a central duty level unit and a peripheral primary combustion level unit, a two-level axial swirler structure is adopted by the central duty level unit, an oil membrane generated by duty level fuel oil is atomized under the shearing action of the rotational air of the inner level and the outer level of the duty level, an oil-rich diffusive combustion mode is formed in the duty level, and the problem that the combustion is unstable under small power due to the fact that the gas quantity is large in the head portion of the high temperature rise combustor is avoided; the primary combustion level is of a combined type swirler structure of two-level reverse rotation of weak swirl design, primary combustion fuel oil is sprayed toward the downstream of an axial swirler blade channel of the outer level of the primary combustion level through multiple fuel oil spraying holes, after being atomized and mixed by the rotational air of the inner level and the outer level, the fuel gas in a primary combustion level premix channel is distributed uniformly, and the problem of exhaust smoke at a combustor outlet under the high power of the high temperature rise combustor is avoided.
Description
Technical field
The present invention is applicable to aeroengine high temperature and raises oil-gas ratio firing chamber, relates to a kind of Multi-stage spiral combination type air atomizing fuel nozzle device.
Background technique
Military aero-engine thrust weight ratio is more and more higher, requires the temperature rise improving constantly firing chamber.High temperature rise is corresponding with high oil-gas ratio, under high oil-gas ratio environment, according to the cup type air-fuel mixture scheme of conventional eddy flow, due to primary holes and blending hole air inlet, the air quantity of actual participation head burning is less, making head equivalent proportion will considerably beyond 1, there is serious smoke event in high-power lower combustion chamber.But invisible the smoldering of aeroengine exhaust is the requirement of environmental protection, the operational requirements of ordnance engine especially.Because smoking of the exhaust means much red-hot trickle carbon particle, these red-hot carbon particles can trigger far infrared, and many air-to-air missiles are equipped with far infrared guidance device.Therefore, in high temperature rise combustor, being vented for solving problem of smoldering as seen, needing greatly to increase head air inflow, removing primary holes air inlet, reduce and even eliminate blending hole air inlet.When head tolerance is more, if still adopt conventional combustion room single channel fuel feeding scheme, there is combustion instability problem under low-power, the method solving this problem adopts the fuel feeding scheme being similar to low pollution combustor TAPS (TwinAnnualPremixingSwirler), namely under low-power, the requirement of combustion stability is only ensured by central value class fuel feeding, high-power lower level on duty and main combustion stage fuel feeding simultaneously, meets the invisible requirement of smoldering of high temperature rise combustor exhaust.
With reference to TAPS solution, BJ University of Aeronautics & Astronautics has applied for that several about integrated fuel-injected low pollution combustor patent, application number is respectively 200810104684.4,200810104686.3 and 200810105061.9, and the main feature of these patents is the difference on main combustion stage type hydrocyclone and fuel injection mode.As at application number be 200810104684.4 and 200810105061.9 patent in, main combustion stage adopts one-level radial swirler structure, and fuel oil sprays vertically in main combustion stage premixed channel, and difference is the position of main combustion stage direct-lighting type air atomizer spray nozzle.Application number be 200810104686.3 patent main combustion stage be one-level axial swirler, the position of main combustion stage oil burning jet exit point is positioned in the middle of main combustion stage inner ring, main combustion stage blade or main combustion stage outer shroud.These patents propose the designing requirement that head of combustion chamber structure and air-fuel mixture scheme can meet the relatively low low pollution combustor of the less oil-gas ratio of head air inflow, but for the high temperature rise combustor under enlarged head air inflow height oil-gas ratio environment, main combustion stage cyclone separator progression is less, eddy flow is organized comparatively single, is difficult to realize the efficient air-fuel mixture fast of head of combustion chamber.
In some patents of GE company application, adopt the weak eddy flow design of the strong eddy flow of main combustion stage level on duty, burning indoor return is dominated by main combustion stage, such mentality of designing is for the high temperature rise combustor under high oil-gas ratio environment, it is more weak that tolerance accounts for the many effect of peripheral main combustion stage air to fuel oil richer central value class, make level air-fuel mixture on duty uneven, be unfavorable for the improvement that combustor exit temperature distributes.
Summary of the invention
The technical problem to be solved in the present invention is: overcome above-mentioned the deficiencies in the prior art, adopts multistage combined hydrocyclone structure to strengthen mixing of head fuel oil and air, avoids combustor exit to smolder as seen; The mentality of designing of the weak eddy flow of adopted value class strong eddy flow main combustion stage, comes leading firing chamber by eddy flow on duty and refluxes, strengthen level air-fuel mixture on duty, thus improves combustor exit temperature distribution.
The technical solution adopted for the present invention to solve the technical problems is: a kind of Multi-stage spiral combination type air atomizing fuel nozzle device, be applied to high temperature and raise oil-gas ratio firing chamber, described firing chamber is once-through type monocycle cavity configuration, comprise head cyclone separator and burner inner liner, it is characterized in that: described head cyclone separator comprises central value class unit and peripheral main combustion stage unit, wherein:
--described central value class unit comprises from inside to outside and level axial swirler, level oil film nozzle on duty and not weight axial swirler on duty in coaxially arranged center guiding cone, level on duty, wherein,
Described center guiding cone comprises the conical section of cylindrical section and the close flow outlet side being positioned at airflow inlet side, and in described level on duty, level axial swirler is sheathed on the cylindrical section of described center guiding cone;
Described level oil film nozzle on duty is band annulus structure with dissection, and comprise the inducer, changeover portion and the outlet section that connect successively, wherein the size of inducer is greater than the size of outlet section;
Space between the internal face of described level oil film nozzle on duty and center guiding cone forms the first air-flow path, and the diameter of this air-flow path inducer is greater than the diameter of its outlet section;
Interlayer in described level oil film nozzle on duty forms level oil supply gallery on duty, described interlayer comprises generally within the level oil pocket on duty in described level oil film nozzle inlet section on duty and the level oil circuit on duty that is positioned on described level oil film nozzle changeover portion on duty and outlet section, this level oil circuit one end on duty and described level oil pocket UNICOM on duty, the other end and the slit UNICOM be arranged on described level oil film jet expansion section internal face on duty, this slit forms level oil film spout on duty;
Described not weight axial swirler on duty is sheathed on the outlet section of described level oil film nozzle on duty;
--described peripheral main combustion stage unit comprises transition annulus, annular main combustion stage for level axial swirler in oiled-plate method, peripheral annular sleeve, main combustion stage and the outer level radial swirler of main combustion stage, wherein,
Described transition annular jacket casing is located on the outlet section of described level oil film nozzle on duty, described not weight axial swirler on duty is set therebetween, described transition annular sleeve lining face forms the second air-flow path, space between the internal face of described transition annulus inducer and the outer wall of described level oil film jet expansion section on duty forms the inducer of the second air-flow path, and the outlet section of this air-flow path and central axis have certain angle; The described transition annulus internal face part exceeded outside described level oil film nozzle on duty forms the extending section of the second air-flow path;
Described annular main combustion stage comprises the main combustion stage layering dividing plate being arranged at its inner circumference place, the main combustion stage oil pocket being positioned at its dorsal part for oiled-plate method and is positioned at its outer surface and the main combustion stage fuel injection hole be communicated with described main combustion stage oil pocket; In described main combustion stage, level axial swirler is arranged in the 3rd air-flow path between described transition annulus inducer and described main combustion stage layering dividing plate; The outer level radial swirler of described main combustion stage is arranged at described annular main combustion stage in the 4th air-flow path between oiled-plate method and described peripheral annular sleeve;
Separated by described main combustion stage layering dividing plate between level axial swirler and the outer level radial swirler of main combustion stage in described main combustion stage; The internal face of described peripheral annular sleeve forms main combustion stage premixed channel.
In Multi-stage spiral combination type air atomizing fuel nozzle device of the present invention, central value class unit adopts two-stage cyclones structure, comprises level axial swirler and not weight axial swirler on duty in the level on duty coaxially arranged with center guiding cone; Level fuel oil on duty enters level oil pocket on duty, circumferential equally distributed oil film is formed after flowing through level oil circuit on duty, oil film is subject to level axial swirler and not weight axial swirler rotational-flow shearing on duty effect in level on duty, in level expanding channel on duty, form level mist of oil on duty.Peripheral main combustion stage unit adopts two-stage combined-type cyclone structure, comprises level axial swirler and the outer level radial swirler of main combustion stage in main combustion stage, separates between inside and outside level cyclone separator with main combustion stage layering dividing plate.Main combustion stage fuel oil enters main combustion stage oil pocket, fuel oil in main combustion stage oil pocket is directly sprayed to level radial swirler blade path downstream outside main combustion stage by main combustion stage fuel injection hole, form multiply main combustion stage fuel jet, successively be subject to the atomization mixed function of two-stage counterrotating rotational flow air inside and outside main combustion stage, equally distributed gas mixture is formed in main combustion stage premixed channel, last entering in zone of combustion is again burnt, and reaches the object improving air-fuel mixture in high temperature rise combustor.
Preferably, in described level on duty, the flow rotation direction of level axial swirler is identical or contrary with the flow rotation direction of not weight axial swirler on duty.
Preferably, in described main combustion stage, the flow rotation direction of level axial swirler is identical or contrary with the flow rotation direction of not weight axial swirler on duty, and the flow rotation direction of the outer level radial swirler of main combustion stage is vertical with the flow rotation direction of level axial swirler in main combustion stage.
Preferably, described main combustion stage fuel injection hole is positioned at the outer level radial swirler blade path downstream of main combustion stage, and the outer level radial swirler blade path number of main combustion stage is the integral multiple of main combustion stage fuel injection hole number, and main combustion stage fuel injection hole is circumferentially uniformly distributed.
Preferably, described main combustion stage fuel injection hole pore diameter range between 0.4mm ~ 1.2mm.
Preferably, the ratio of described main combustion stage fuel injection hole radial height and main combustion stage layering dividing plate radial height is in 1.1 ~ 1.3 scopes.
Preferably, the ratio of described main combustion stage layering septum plate length and main combustion stage fuel injection hole distance main combustion stage cyclone outlet is in 0 ~ 0.5 scope.
Preferably, the tolerance of described central value class unit accounts for the 10%-20% of the total air inflow in firing chamber, the tolerance of peripheral main combustion stage unit accounts for the 65%-75% of the total air inflow in firing chamber, in level on duty, level axial swirler tolerance accounts for the 30%-70% of central value class unit tolerance, and in main combustion stage, level axial swirler tolerance accounts for the 20%-80% of peripheral main combustion stage unit tolerance.
Preferably, for burning, air demand all enters from head cyclone separator, burner inner liner does not have primary holes and blending hole, only has Cooling Holes.
Working principle of the present invention: central value class unit adopts pre-diaphragll type air atomizing type, occurs broken, forms rich oil diffusive combustion under the rotational flow air effect of oil film two-stage friction speed inside and outside level on duty.The fuel jet that main combustion stage fuel oil is formed by multi-point injection carries out rapid mixing with air under the outer level radial vortex effect of main combustion stage, and then be subject to the effect of the axial oppositely rotational flow air of level in main combustion stage, fuel oil is mixed in main combustion stage premixed channel more even, realize main combustion stage premixed combustion.This combustion manner can take into account high temperature rise combustor combustion stability and high-power lower exhaust is invisible smolders under low-power.Combustion chamber flame drum does not offer primary holes and blending hole, only has Cooling Holes, object is to increase head air inflow, and reduce head equivalent proportion, further control combustion room exiting exhaust gas is smoldered.
Central value class unit starts under the low power states such as slow train, adopts the diffusion combustion mode of rich oil, avoids the combustion instability problem that high temperature rise combustor causes due to the increase of head air inflow.When engine power increases, start to start peripheral main combustion stage unit, what adopt due to peripheral main combustion stage unit is premixed combustion mode, and the total yield of combustor primary zone is than lower than 1.2, and the exhaust avoiding high temperature rise combustor may occur because oil-gas ratio is higher is smoldered problem as seen.
The contradiction under although level on duty adopts diffusive combustion, main combustion stage to adopt premixed combustion can solve the low-power and high-power operation state occurred in high temperature rise combustor from burning tissues, the uniformity of main combustion stage air-fuel mixture affects the direct factor whether high temperature rise combustor occur smoldering as seen under large operating mode.Main combustion stage adopts two-stage combined-type cyclone structure, can effectively avoid, because eddy flow organizes rich oil region, local in the single firing chamber caused, fuel oil being mixed more even with air.
Because high temperature rise combustor head air inflow is larger, burner inner liner does not offer primary holes and blending hole, the weak mentality of designing of revolving of adopted value class strong eddy flow main combustion stage, the backflow in leading firing chamber is carried out by level on duty, be conducive to main combustion stage inner air to be entrainmented in level recirculating zone on duty, reinforcement value class air-fuel mixture, decreasing value class peak value of temperature, thus improve without blending hole charge combustion room Exit temperature distribution.
The present invention's advantage is compared with prior art as follows:
1. main combustion stage of the present invention adopts two-stage combined-type cyclone structure, main combustion stage fuel oil is at the outer level radial swirler blade path downstream injection of main combustion stage, mix for the first time with radial vortex air, after layering dividing plate between main combustion stage two-stage cyclones, gas mixture mixes again with level axial rotational flow air in main combustion stage, strengthen mixing of fuel oil and air in main combustion stage premixed channel, effectively avoid the appearance in rich oil region, local.
2. the actual air-fuel mixture effect of the tolerance basic of distribution inside and outside main combustion stage of the present invention between two-stage cyclones is adjusted to optimal proportion.Main combustion stage fuel injection hole aperture, number and radial position also can according to actual air-fuel mixture effect adjustment.
3. level two-stage axial swirler flow rotation direction on duty of the present invention is identical or contrary, and the tolerance inside and outside adjusted value class between two-stage cyclones is distributed, and makes level on duty form strong eddy flow; In main combustion stage, level axial swirler is contrary with the flow rotation direction of outer level radial swirler, makes main combustion stage form weak eddy flow, realizes by level on duty leading burning indoor return.
4. combustion chambers burn required air of the present invention all enters from head, and burner inner liner does not offer primary holes and blending hole, to reduce main burning region average equivalent ratio, smolders under avoiding large operating mode.
5. the stratified combustion mode of level diffusive combustion on duty of the present invention and main combustion stage premixed combustion, has taken into account the stable operation under high temperature rise combustor low-power and the invisible smoking of the exhaust under high power.
Accompanying drawing explanation
Fig. 1 is high temperature rise combustor structural representation;
Fig. 2 is the enlarged diagram of head cyclone separator;
Fig. 3 is main combustion stage fuel injection hole radial position schematic diagram.
Embodiment
For making object of the present invention, technological scheme and advantage clearly understand, to develop simultaneously embodiment referring to accompanying drawing, the present invention is described in more detail.
Fig. 1 is the schematic diagram that a high temperature raises oil-gas ratio firing chamber 10, and this firing chamber is once-through type monocycle cavity configuration, and 10 comprise Diffuser 11, outer casing 12, interior casing 13, calotte 14, head end wall 15, outer burner inner liner 16, flame cylinder 17 and head cyclone separator 18.High-pressure air is divided into three tunnels after Diffuser 11 slows down diffusion, first via air is entered zone of combustion 19 and participates in burning after being mixed with fuel oil by head cyclone separator 18, two, three road air respectively flow through outer casing 12 and outer burner inner liner 16 and two ring cavities between interior casing 13 and flame cylinder 17, enter the Cooling Holes (meaning not shown in the figures) that outer burner inner liner 16 and flame 17 are offered, for cooling flame tube wall surface, ensure the firing chamber life-span.Inside and outside burner inner liner wall does not offer any primary holes and blending hole, only has Cooling Holes.First via tolerance accounts for 75% ~ 85% of combustion chamber charge amount, and object is the average equivalent ratio in order to reduce zone of combustion 19, occurs smoldering under avoiding large operating mode.Fig. 2 is the zoomed-in view of head cyclone separator 18 in Fig. 1, structure comprises central value class unit 20 and peripheral main combustion stage unit 21.Central value class unit 20 tolerance accounts for 10% ~ 20% of combustion chamber charge amount, and peripheral main combustion stage unit 21 tolerance accounts for 65% ~ 75% of combustion chamber charge amount.
Central value class unit 20 comprises from inside to outside and level axial swirler 22, level oil film nozzle 202 on duty and not weight axial swirler 23 on duty in coaxially arranged center guiding cone 201, level on duty, see Fig. 2, center guiding cone 201 comprises the conical section of cylindrical section and the close flow outlet side being positioned at airflow inlet side, and in level on duty, level axial swirler 22 is sheathed on the cylindrical section of center guiding cone 201; Level oil film nozzle 202 on duty is band annulus structure with dissection, and comprise the inducer, changeover portion and the outlet section that connect successively, wherein the size of inducer is greater than the size of outlet section; Space between the internal face of level oil film nozzle 202 on duty and center guiding cone 201 forms the first air-flow path, and the diameter of this air-flow path inducer is greater than the diameter of its outlet section; Interlayer in level oil film nozzle 202 on duty forms level oil supply gallery on duty, interlayer comprises generally within the level oil pocket 25 on duty in level oil film nozzle inlet section on duty and the level oil circuit 26 on duty that is positioned on level oil film nozzle changeover portion on duty and outlet section, this level oil circuit 26 one end on duty and level oil pocket 25 UNICOM on duty, the other end and the slit UNICOM be arranged on level oil film nozzle 202 outlet section internal face on duty, this slit forms level oil film spout on duty.Not weight axial swirler 23 on duty is sheathed on the outlet section of level oil film nozzle 202 on duty.
Peripheral main combustion stage unit 21 comprises transition annulus 211, annular main combustion stage is for oiled-plate method 212, peripheral annular sleeve 213, level axial swirler 20 and the outer level radial swirler 31 of main combustion stage in main combustion stage, transition annulus 211 is set on the outlet section of level oil film nozzle 202 on duty, therebetween settings class not weight axial swirler 23, transition annulus 211 internal face forms the second air-flow path, space between the internal face of transition annulus 211 inducer and the outer wall of level oil film nozzle 202 outlet section on duty forms the inducer of the second air-flow path, the outlet section of this air-flow path and central axis have certain angle, the transition annulus 211 internal face part exceeded outside level oil film nozzle 202 on duty forms the extending section of the second air-flow path.
Annular main combustion stage comprises the main combustion stage layering dividing plate 30 being arranged at its inner circumference place, the main combustion stage oil pocket 33 being positioned at its dorsal part for oiled-plate method 212 and is positioned at its outer surface and the main combustion stage fuel injection hole 34 be communicated with main combustion stage oil pocket; In main combustion stage, level axial swirler 29 is arranged in the 3rd air-flow path between transition annulus 211 inducer and main combustion stage layering dividing plate 30; The outer level radial swirler 31 of main combustion stage is arranged at annular main combustion stage in the 4th air-flow path between oiled-plate method 212 and peripheral annular sleeve 213.Separated by main combustion stage layering dividing plate 30 between level axial swirler 29 and the outer level radial swirler 31 of main combustion stage in main combustion stage; The internal face of peripheral annular sleeve 30 forms main combustion stage premixed channel 36.
Level fuel oil 24 on duty enters level oil pocket 25 on duty, circumferentially oil film is formed after flowing through longer level oil circuit 26 on duty, there is fragmentation under level axial swirler 22 and not weight axial swirler 23 rotational-flow shearing on duty effect in oil film, and form the level mist of oil on duty of certain cone angle in level expanding channel 28 on duty in level on duty.Along with the strong cyclonic action of level on duty, mist of oil diffuses to zone of combustion 19 and burns.
Peripheral main combustion stage 21 comprises level axial swirler 29 in main combustion stage, main combustion stage layering dividing plate 30, the outer level radial swirler 31 of main combustion stage.Main combustion stage fuel oil 32 enters main combustion stage oil pocket 34, fuel oil penetrates from multiple main combustion stage fuel injection hole 34, multiply main combustion stage fuel jet 35 is formed in outer level radial swirler blade path 40 downstream of main combustion stage, under the outer level radial swirler 31 rotational flow air effect of main combustion stage, fuel oil mixes for the first time with air, after gas mixture flows through main combustion stage layering dividing plate, in main combustion stage, level axial swirler 23 rotational flow air participates in the air-fuel mixture in main combustion stage 21, make the fuel distribution in main combustion stage premixed channel 36 more even, effectively prevent the smoking of the exhaust because local rich oil causes.
For both without primary holes also without blending hole firing chamber for, the weak eddy flow design of adopted value class strong eddy flow main combustion stage, object be in order to by level eddy flow on duty to form the backflow in firing chamber, be conducive to main combustion stage partial air being entrainmented to fuel-rich combustion region, center, strengthen air-fuel mixture in this region, decreasing value class peak value of temperature, thus improve combustor exit temperature distribution.Therefore, in level on duty, level axial swirler 22 can be identical or contrary with the flow rotation direction of not weight axial swirler 23 on duty, distributed, make level 20 on duty reach strong eddy flow by the tolerance inside and outside adjusted value class 20 between two-stage cyclones; In main combustion stage, level axial swirler 29 is contrary with the flow rotation direction of the outer level radial swirler 31 of main combustion stage, and object is to weaken main combustion stage 21 swirl strength, strengthens the air-fuel mixture in main combustion stage premixed channel 36 simultaneously; Not weight axial swirler 23 on duty can be identical or contrary with the flow rotation direction in main combustion stage between level axial swirler 29, and this is determined by the service behaviour of Actual combustion room, as the parameter such as some flame failure limit of firing chamber.
Consider the atomizing effect of main combustion stage fuel jet 35 in outer level radial swirler 31 tranverse air flow of main combustion stage, need choose reasonable main combustion stage fuel injection hole aperture 41 and main combustion stage fuel injection hole 34 number, general main combustion stage fuel injection hole aperture 41 is between 0.4 ~ 1.2mm, and outer level radial swirler blade path 40 number of main combustion stage is the integral multiple of main combustion stage fuel injection hole 34 number.In order to make the air-fuel mixture of in main combustion stage premixed channel 36 more even, need the position of reasonable Arrangement main combustion stage fuel injection hole 34, Fig. 3 represents the radial position of main combustion stage fuel injection hole, the ratio of general selection main combustion stage fuel injection hole radial height 42 and main combustion stage layering dividing plate radial height, in 1.1 ~ 1.3 scopes, makes the fuel oil radially reasonable layout of main combustion stage cyclone outlet 37.
In adjustment Fig. 1, the length 38 of main combustion stage layering dividing plate 30 can control the mixing length again of level axial swirler 29 pairs of main combustion stage fuel jets 35 in the first atomization mixing length of the outer level radial swirler 31 pairs of main combustion stage fuel jets 35 of main combustion stage and main combustion stage, main combustion stage layering dividing plate 30 is shorter, the outer level radial swirler 31 initial mixing length of main combustion stage will shorter and in main combustion stage the mixing length again of level axial swirler 29 longer, select main combustion stage layering septum plate length 38 and the main combustion stage fuel injection hole distance main combustion stage cyclone outlet ratio apart from 39 in 0 ~ 0.5 scope, to obtain the main combustion stage gas mixture of uniformity the best.
When engine start or when being operated in low power state, central value class unit 20 fuel feeding, peripheral main combustion stage unit 21 only has air to enter and not fuel feeding, level mist of oil 27 on duty forms diffusion combustion mode in zone of combustion 19, thus ensure that high temperature rise combustor is due to the combustion stability in the larger situation of head air inflow.When engine operation is when the high power state such as climbing or cruise, level 20 on duty and main combustion stage 21 fuel feeding simultaneously, main combustion stage fuel oil 32 is subject to the transverse jet atomization of two-stage rotational flow air inside and outside main combustion stage 21 through the multiply fuel jet 35 that main combustion stage fuel injection hole 34 penetrates, premix oil gas is formed in main combustion stage premixed channel 36, enter into zone of combustion 19 and form premixed combustion mode, make main burning region equivalent proportion lower than 1.2, thus ensure that high temperature rise combustor exports invisible smoking of the exhaust at high power.
The foregoing is only preferred embodiment of the present invention, not in order to limit the present invention, within the spirit and principles in the present invention all, any amendment made, equivalent replacement, improvement etc., all should be included within the scope of the present invention.
Claims (10)
1. a Multi-stage spiral combination type air atomizing fuel nozzle device, be applied to high temperature rise combustor, described firing chamber is once-through type monocycle cavity configuration, comprises head cyclone separator and burner inner liner, it is characterized in that: described head cyclone separator comprises central value class unit and peripheral main combustion stage unit, wherein:
--described central value class unit comprises from inside to outside and level axial swirler, level oil film nozzle on duty and not weight axial swirler on duty in coaxially arranged center guiding cone, level on duty, wherein,
Described center guiding cone comprises the conical section of cylindrical section and the close flow outlet side being positioned at airflow inlet side, and in described level on duty, level axial swirler is sheathed on the cylindrical section of described center guiding cone;
Described level oil film nozzle on duty is band annulus structure with dissection, comprises the inducer, changeover portion and the outlet section that connect successively; Space between the internal face of described level oil film nozzle on duty and center guiding cone forms the first air-flow path;
Interlayer in described level oil film nozzle on duty forms level oil supply gallery on duty, described interlayer comprises generally within the level oil pocket on duty in described level oil film nozzle inlet section on duty and the level oil circuit on duty that is positioned on described level oil film nozzle changeover portion on duty and outlet section, this level oil circuit one end on duty and described level oil pocket UNICOM on duty, the other end and the slit UNICOM be arranged on described level oil film jet expansion section internal face on duty, this slit forms level oil film spout on duty;
--described peripheral main combustion stage unit comprises transition annulus, annular main combustion stage for level axial swirler in oiled-plate method, peripheral annular sleeve, main combustion stage and the outer level radial swirler of main combustion stage, wherein,
Described transition annular jacket casing is located on the outlet section of described level oil film nozzle on duty, described not weight axial swirler on duty is set therebetween, described transition annular sleeve lining face forms the second air-flow path, space between the internal face of described transition annulus inducer and the outer wall of described level oil film jet expansion section on duty forms the inducer of the second air-flow path, and the outlet section of this air-flow path and central axis have certain angle; The described transition annulus internal face part exceeded outside described level oil film nozzle on duty forms the extending section of the second air-flow path;
Described annular main combustion stage comprises the main combustion stage layering dividing plate being arranged at its inner circumference place, the main combustion stage oil pocket being positioned at its dorsal part for oiled-plate method and is positioned at its outer surface and the main combustion stage fuel injection hole be communicated with described main combustion stage oil pocket; In described main combustion stage, level axial swirler is arranged in the 3rd air-flow path between described transition annulus inducer and described main combustion stage layering dividing plate; The outer level radial swirler of described main combustion stage is arranged at described annular main combustion stage in the 4th air-flow path between oiled-plate method and described peripheral annular sleeve;
Separated by described main combustion stage layering dividing plate between level axial swirler and the outer level radial swirler of main combustion stage in described main combustion stage; The internal face of described peripheral annular sleeve forms main combustion stage premixed channel.
2. Air Blast Fuel-oil Atomizer device according to claim 1, is characterized in that: in described level on duty, the flow rotation direction of level axial swirler keeps identical or contrary with the flow rotation direction of not weight axial swirler on duty.
3. Air Blast Fuel-oil Atomizer device according to claim 1, it is characterized in that: in described main combustion stage, the flow rotation direction of level axial swirler is identical or contrary with the flow rotation direction of not weight axial swirler on duty, the flow rotation direction of the outer level radial swirler of main combustion stage is contrary with the flow rotation direction of level axial swirler in main combustion stage.
4. Air Blast Fuel-oil Atomizer device according to claim 1, it is characterized in that: main combustion stage fuel injection hole is positioned at the outer level radial swirler blade path downstream of main combustion stage, the outer level radial swirler blade path number of main combustion stage is the integral multiple of main combustion stage fuel injection hole number, and main combustion stage fuel injection hole is circumferentially uniformly distributed.
5. Air Blast Fuel-oil Atomizer device according to claim 1, is characterized in that: main combustion stage fuel injection hole pore diameter range is between 0.4mm ~ 1.2mm.
6. Air Blast Fuel-oil Atomizer device according to claim 1, is characterized in that: the ratio d2/d3 of main combustion stage fuel injection hole radial height and main combustion stage layering dividing plate radial height is in 1.1 ~ 1.3 scopes.
7. Air Blast Fuel-oil Atomizer device according to claim 1, is characterized in that: the ratio L1/L2 of main combustion stage layering septum plate length and main combustion stage fuel injection hole distance main combustion stage cyclone outlet is in 0 ~ 0.5 scope.
8. an Air Blast Fuel-oil Atomizer device according to claim 1, it is characterized in that: central value class unit tolerance accounts for the 10%-20% of the total air inflow in firing chamber, peripheral main combustion stage unit tolerance accounts for the 65%-75% of the total air inflow in firing chamber, in level on duty, level axial swirler tolerance accounts for the 30%-70% of level tolerance on duty, and in main combustion stage, level axial swirler tolerance accounts for the 20%-80% of main combustion stage tolerance.
9. Air Blast Fuel-oil Atomizer device according to claim 1, is characterized in that: air demand all enters from head cyclone separator for burning, burner inner liner not having primary holes and blending hole, only having Cooling Holes.
10. the controlling method of the Air Blast Fuel-oil Atomizer device described in any one of claim 1 to 9, it is characterized in that: central value class unit starts under the low power states such as slow train, adopt the diffusion combustion mode of rich oil, avoid the combustion instability problem that high temperature rise combustor causes due to the increase of head air inflow; When engine power increases, start to start peripheral main combustion stage unit, peripheral main combustion stage unit adopts premixed combustion mode, and the total yield of combustor primary zone is than lower than 1.2, and the exhaust avoiding high temperature rise combustor may occur because oil-gas ratio is higher is smoldered problem as seen.
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| CN201510397172.1A CN105041539B (en) | 2015-07-08 | 2015-07-08 | A kind of Multi-stage spiral combination type air atomizing fuel nozzle device and its control method |
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| CN201510397172.1A CN105041539B (en) | 2015-07-08 | 2015-07-08 | A kind of Multi-stage spiral combination type air atomizing fuel nozzle device and its control method |
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| CN105937774A (en) * | 2016-06-17 | 2016-09-14 | 南京航空航天大学 | Multi-point lean oil direct injection classified combustion chamber system and work method thereof |
| CN106091013A (en) * | 2016-06-07 | 2016-11-09 | 中国科学院工程热物理研究所 | A kind of high temperature rise combustor structure of three stage layered burnings |
| CN106500130A (en) * | 2016-10-08 | 2017-03-15 | 中国科学院工程热物理研究所 | A kind of three-level layered portion lean premixed combustor of main combustion stage fuel-firing preheating prevapourising |
| 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 |
| CN110131065A (en) * | 2019-05-15 | 2019-08-16 | 燕山大学 | A kind of novel tangential combined internal combustion engine cylinder based on eddy flow secondary injection |
| CN110686274A (en) * | 2019-09-25 | 2020-01-14 | 中国科学院工程热物理研究所 | Air atomization device for main combustion stage of layered premixed combustion chamber |
| CN111215015A (en) * | 2019-12-26 | 2020-06-02 | 浙江长城搅拌设备股份有限公司 | Special stirring device for viscous fluid mixing and gas dispersing |
| CN111482772A (en) * | 2020-04-21 | 2020-08-04 | 四川航天中天动力装备有限责任公司 | Processing technology of combined fuel nozzle |
| CN111765032A (en) * | 2020-06-12 | 2020-10-13 | 沈阳航空航天大学 | Sliding arc plasma-high disturbance cross structure fuel oil atomizing nozzle |
| CN113932253A (en) * | 2020-06-29 | 2022-01-14 | 中国航发商用航空发动机有限责任公司 | Combustion chamber head, combustion chamber, gas turbine engine, and combustion control method |
| CN114413284A (en) * | 2021-12-28 | 2022-04-29 | 北京动力机械研究所 | Special-shaped swirler matched with head of annular combustion chamber |
| CN115234942A (en) * | 2022-06-28 | 2022-10-25 | 北京航空航天大学 | Combustion chamber for injecting fuel by venturi |
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| CN106091013A (en) * | 2016-06-07 | 2016-11-09 | 中国科学院工程热物理研究所 | A kind of high temperature rise combustor structure of three stage layered burnings |
| CN105937774A (en) * | 2016-06-17 | 2016-09-14 | 南京航空航天大学 | Multi-point lean oil direct injection classified combustion chamber system and work method thereof |
| CN105937774B (en) * | 2016-06-17 | 2018-03-02 | 南京航空航天大学 | A kind of oil-poor direct-injection fractional combustion chamber system of multiple spot and its method of work |
| CN106500130A (en) * | 2016-10-08 | 2017-03-15 | 中国科学院工程热物理研究所 | A kind of three-level layered portion lean premixed combustor of main combustion stage fuel-firing preheating prevapourising |
| 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 |
| CN110131065A (en) * | 2019-05-15 | 2019-08-16 | 燕山大学 | A kind of novel tangential combined internal combustion engine cylinder based on eddy flow secondary injection |
| CN110686274A (en) * | 2019-09-25 | 2020-01-14 | 中国科学院工程热物理研究所 | Air atomization device for main combustion stage of layered premixed combustion chamber |
| CN111215015A (en) * | 2019-12-26 | 2020-06-02 | 浙江长城搅拌设备股份有限公司 | Special stirring device for viscous fluid mixing and gas dispersing |
| CN111215015B (en) * | 2019-12-26 | 2022-07-12 | 浙江长城搅拌设备股份有限公司 | Special stirring device for viscous fluid mixing and gas dispersing |
| CN111482772A (en) * | 2020-04-21 | 2020-08-04 | 四川航天中天动力装备有限责任公司 | Processing technology of combined fuel nozzle |
| CN111482772B (en) * | 2020-04-21 | 2021-04-20 | 四川航天中天动力装备有限责任公司 | Processing technology of combined fuel nozzle |
| CN111765032A (en) * | 2020-06-12 | 2020-10-13 | 沈阳航空航天大学 | Sliding arc plasma-high disturbance cross structure fuel oil atomizing nozzle |
| CN113932253A (en) * | 2020-06-29 | 2022-01-14 | 中国航发商用航空发动机有限责任公司 | Combustion chamber head, combustion chamber, gas turbine engine, and combustion control method |
| CN114413284A (en) * | 2021-12-28 | 2022-04-29 | 北京动力机械研究所 | Special-shaped swirler matched with head of annular combustion chamber |
| CN115234942A (en) * | 2022-06-28 | 2022-10-25 | 北京航空航天大学 | Combustion chamber for injecting fuel by venturi |
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