CN102889617B - Premixing and pre-evaporation combustor for main combustion stage using radial film formation - Google Patents
Premixing and pre-evaporation combustor for main combustion stage using radial film formation Download PDFInfo
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- CN102889617B CN102889617B CN201210337925.6A CN201210337925A CN102889617B CN 102889617 B CN102889617 B CN 102889617B CN 201210337925 A CN201210337925 A CN 201210337925A CN 102889617 B CN102889617 B CN 102889617B
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Abstract
A premixing and pre-evaporation combustor for a main combustion stage using radial film formation consists of a diffuser, an outer combustor case, an inner combustor case, a pre-combustion stage, the main-combustion stage, a flame barrel outer wall and a flame barrel inner wall, wherein the flame of the pre-combustion stage is stabilized by a low-speed return flow zone formed by cyclone generated when a pre-combustion stage cyclone assembly enters the combustor; after being sprayed out by a plurality of tangential spraying openings of a main combustion stage nozzle, fuel oil of the main combustion stage spreads in a fuel oil film formation region and realizes connection, so that a peripheral continuous oil film is formed; the cyclone of an upstream cyclone ring of the main combustion stage nozzle and the cyclone of a downstream cyclone ring of the main combustion stage nozzle secondarily atomize the fuel oil, the fuel oil is brought to a premixing and pre-evaporation section to evaporate and is mixed with air, and uniform oil-gas mixtures are formed at an outlet of the premixing and pre-evaporation section, are jetted into a flame barrel, are ignited by the flame of the pre-combustion stage and then are combusted. The premixing and pre-evaporation combustor is simple in structure; and pollutant discharge can be effectively reduced while a normal working state of an aerial engine is guaranteed.
Description
Technical field
The present invention relates to a kind of aero-gas turbine low pollution combustor that utilizes premixed combustion technology, adopt the pattern of fractional combustion, pre-combustion grade adopts diffusion combustion organizational form, and main combustion stage adopts premixed combustion organizational form, and main combustion stage adopts the radially mode of film forming to feed fuel oil.This invention can ensure the wider stable operation range of combustion chamber, reduces combustion chamber disposal of pollutants simultaneously.
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 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 ensures that it continues progressive source.
The Main Trends of The Development of modern civil aviation engine chamber is combustion with reduced pollutants.Civil aviation engine chamber must meet the aero-engine emission standard of increasingly stringent.The CAEP6(Committee on Aviation Environmental Protection adopting at present) standard is very strict to the regulation of pollutant effulent, particularly to NOx emission requirement; And up-to-date CAEP8 standard has proposed to reduce by 15% in the discharge standard that is emitted on CAEP6 of NOx, along with the fast development of aircraft industry and improving constantly of people's environmental consciousness, following to the higher requirement of gas-turbine combustion chamber disposal of pollutants meeting proposition.
The GE of Liang Ge leading company of US Airways engine and PW set about research already to low pollution combustor, first GE has researched and developed dicyclo chamber combustion with reduced pollutants DAC(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(is for PW4000 and 6000 series).Aspect low pollution combustor of future generation, GE company adopts LDM(Lean Direct Mixing Combustion, oil-poor direct hybrid combustor) technology is the TAPS(Twin Annular Premixing Swirler of its GEnx reseach of engine) low pollution combustor.In stand loopful verification experimental verification, the NOx disposal of pollutants of TAPS low pollution combustor has reduced by 50% than CAEP2 discharge standard.The low pollution combustor that PW company continues to adopt RQL mode to propose reduction NOx disposal of pollutants is TALON X, the head type adopting 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 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, reaches 1000 for its engine rapids of new generation.
And no matter be which kind of advanced person's low pollution combustor, its key technology reduces NOx(nitrogen oxide exactly), CO(carbon monoxide), UHC(unburned hydrocarbons) and the combustion technology of smoldering, key problem is to reduce the temperature of combustion zone, make combustion zone temperature field even simultaneously, be the equivalent proportion control of whole and part, and the uniformity of primary zone equivalent proportion depend 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.Known according to mechanism and the result of the test of NOx and CO generation: the NOx that the primary zone equivalent proportion of combustion chamber produces in 0.6～0.8 scope and the discharge rule of CO(UHC and CO are similar) seldom.Based on this principle, take into account the discharge capacity of NOx and CO, UHC 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: the one, and the uniformity that fuel particles diameter distributes, the i.e. distributing homogeneity of SMD; Second be the uniformity that 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.
Current conventional combustion mode cannot reduce NOx, CO and U HC.Reason is that the method for designing of current combustion chamber determines.For conventional combustion chamber, in the time of large operating mode, owing to adopting liquid mist diffusion combustion mode, the local equivalent proportion in combustion zone is always near 1, far exceed the required equivalent proportion area requirement of above-mentioned combustion with reduced pollutants, although now the discharge of CO and UHC is low, it is maximum that the discharge of NOx reaches.In the time of unskilled labourer's condition, combustion zone equivalent proportion is very low again, and far below the required equivalent proportion of above-mentioned combustion with reduced pollutants interval, although now NOx discharge is low, CO and UHC discharge are very high again.In addition, because conventional combustion chamber generally adopts diffusion combustion mode, local equivalent proportion is inhomogeneous, therefore for conventional combustion chamber, cannot meet the low pollution requirement within the scope of whole engine operation.Therefore, for the demand for development of civil aviation engine chamber, need to develop a kind of combustion chamber that can significantly reduce disposal of pollutants, and can not make other performances poor compared with conventional combustion chamber simultaneously.
Summary of the invention
Technology of the present invention is dealt with problems: overcome the deficiencies in the prior art, the radially premix and pre-evaporation combustion chamber of film forming main combustion stage of a kind of employing is provided, this combustion chamber is under the condition of work that meets aero-engine, can effectively reduce the disposal of pollutants of aeroengine combustor buring chamber burning, comprise NOx, smolder, CO and UHC, and simple in structure.
Technical solution of the present invention: a kind of employing is the premix and pre-evaporation combustion chamber of film forming main combustion stage radially, adopts monocycle cavity configuration, forms combustion chamber outline by casing in outer combustion case and combustion chamber, and outside air enters by diffuser, burner inner liner outer wall, burner inner liner inwall and head of combustion chamber composition combustion zone, combustion air all enters burner inner liner by head of combustion chamber, and dilution air is injected by the interior blending hole on outer blending hole and burner inner liner inwall on burner inner liner outer wall, described head of combustion chamber adopts fractional combustion scheme, is divided into main combustion stage and pre-combustion grade, described main combustion stage is connected and fixed by head entirety end wall and burner inner liner outer wall and burner inner liner inwall, and described pre-combustion grade is passed through pre-combustion grade head end wall and connected with main combustion stage, and concentric with main combustion stage, described pre-combustion grade comprises deflector in pre-combustion grade swirler assembly, pre-combustion grade nozzle, pre-combustion grade head end wall and pre-combustion grade head, pre-combustion grade utilization enters by pre-combustion grade swirler assembly the low speed recirculating zone that the rotational flow air of combustion chamber forms and stabilizes the flame, and pre-combustion grade swirler assembly is connected with encircling in main combustion stage premix and pre-evaporation section by pre-combustion grade head end wall, pre-combustion grade nozzle is positioned at pre-combustion grade swirler assembly, and coaxial with pre-combustion grade swirler assembly, described main combustion stage comprises main combustion stage nozzle, main combustion stage premix and pre-evaporation section, described main combustion stage premix and pre-evaporation section by main combustion stage nozzle float outer ring-shaped pressuring plate, main combustion stage nozzle float outer shroud, main combustion stage nozzle float in ring-shaped pressuring plate, main combustion stage nozzle float in ring, main combustion stage premix and pre-evaporation section outer shroud, main combustion stage premix and pre-evaporation section ring, main combustion stage premix and pre-evaporation section front bulkhead and main combustion stage export water conservancy diversion support and form, the unsteady outer shroud of main combustion stage nozzle is connected with main combustion stage premix and pre-evaporation section front bulkhead, connected mode is screw thread or welding, at the unsteady outer shroud of main combustion stage nozzle and main combustion stage premix and pre-evaporation section front bulkhead employing nut or before being welded to connect, unsteady main combustion stage nozzle outer ring-shaped pressuring plate is arranged on to the unsteady gap of outer shroud that main combustion stage nozzle floats between outer shroud and main combustion stage premix and pre-evaporation section front bulkhead, and therefore the unsteady outer shroud pressure board of main combustion stage nozzle also can float in the unsteady gap of outer shroud, in main combustion stage nozzle floats, ring is connected with encircling in main combustion stage premix and pre-evaporation section, connected mode is screw thread or welding, main combustion stage nozzle float in ring with main combustion stage premix and pre-evaporation section in ring adopt nut or be welded to connect before, in main combustion stage nozzle is floated ring-shaped pressuring plate be arranged on main combustion stage nozzle float in the gap of floating of the interior ring between ring in ring and main combustion stage premix and pre-evaporation section, therefore main combustion stage nozzle float in ring-shaped pressuring plate be stuck in the interior ring gap of floating and also can float, described main combustion stage outlet water conservancy diversion supports and is made up of some blades, can be welded in main combustion stage premix and pre-evaporation section ring upper or with main combustion stage premix and pre-evaporation section in ring entirety manufacture, main combustion stage nozzle floats between outer shroud and main combustion stage nozzle encircle in floating at main combustion stage nozzle, and coaxial with pre-combustion grade nozzle, main combustion stage nozzle is made up of main combustion stage nozzle body, main combustion stage fuel jet, fuel oil film forming district, main combustion stage nozzle upstream cyclone ring and main combustion stage nozzle downstream cyclone ring, main combustion stage nozzle body is made up of main combustion stage nozzle body outer wall, main combustion stage nozzle body inwall, main combustion stage nozzle body front bulkhead, main combustion stage nozzle body ring cavity dividing wall, main combustion stage nozzle body oil-collecting ring cavity wall, main combustion stage nozzle body outer wall, main combustion stage nozzle body inwall, main combustion stage nozzle body front bulkhead and main combustion stage nozzle body ring cavity dividing wall have formed main combustion stage oil-feed ring cavity, main combustion stage nozzle body outer wall, main combustion stage nozzle body inwall, main combustion stage nozzle body ring cavity dividing wall and main combustion stage nozzle body oil-collecting ring cavity wall have formed main combustion stage oil-collecting ring cavity, main combustion stage nozzle body outer wall, main combustion stage nozzle body inwall and main combustion stage nozzle body oil-collecting ring cavity wall have formed fuel oil film forming district, main combustion stage nozzle body ring cavity dividing wall is connected with main combustion stage nozzle body outer wall, main combustion stage nozzle body inwall, and connected mode is manufactured and is weldingly connected with main combustion stage nozzle body inwall or main combustion stage nozzle body ring cavity dividing wall is weldingly connected with main combustion stage nozzle body outer wall with the overall manufacture of main combustion stage nozzle body inwall again again for welding or main combustion stage nozzle body ring cavity dividing wall and main combustion stage nozzle body outer wall entirety, main combustion stage nozzle body oil-collecting ring cavity wall is connected with main combustion stage nozzle body outer wall, main combustion stage nozzle body inwall, and connected mode is manufactured and is weldingly connected with main combustion stage nozzle body inwall or main combustion stage nozzle body oil-collecting ring cavity wall is weldingly connected with main combustion stage nozzle body outer wall with the overall manufacture of main combustion stage nozzle body inwall again again for welding or main combustion stage nozzle body oil-collecting ring cavity wall and main combustion stage nozzle body outer wall entirety, main combustion stage nozzle body outer wall, main combustion stage nozzle body inwall, main combustion stage nozzle body front bulkhead are connected, and connected mode is welding or screw thread, main combustion stage nozzle upstream cyclone ring is connected with main combustion stage nozzle body outer wall in fuel oil film forming district, and connected mode is welding or entirety manufacture, main combustion stage nozzle downstream cyclone ring is connected with main combustion stage nozzle body inwall in fuel oil film forming district, and connected mode is welding or entirety manufacture, main combustion stage nozzle upstream cyclone ring is connected with the unsteady outer ring-shaped pressuring plate of main combustion stage nozzle, and connected mode is welding or screw thread or entirety manufacture, in main combustion stage nozzle downstream cyclone ring floats with main combustion stage nozzle, ring-shaped pressuring plate is connected, and connected mode is welding or overall manufacture, therefore, composition main combustion stage nozzle after main combustion stage nozzle body is connected with main combustion stage nozzle upstream cyclone ring, main combustion stage nozzle downstream cyclone ring, in the main combustion stage nozzle upstream cyclone ring of main combustion stage nozzle, main combustion stage nozzle downstream cyclone ring float with the unsteady outer ring-shaped pressuring plate of main combustion stage nozzle, main combustion stage nozzle respectively, ring-shaped pressuring plate is connected, main combustion stage nozzle float outer ring-shaped pressuring plate, main combustion stage nozzle float in ring-shaped pressuring plate be stuck in outer shroud gap, the interior ring gap of floating of floating, formation main combustion stage after main combustion stage nozzle is connected with main combustion stage premix and pre-evaporation section, on main combustion stage nozzle body front bulkhead, offer a main combustion stage fuel feed hole, main combustion stage fuel oil enters main combustion stage oil-feed ring cavity by main combustion stage fuel feed hole, on main combustion stage nozzle body ring cavity dividing wall, offer some main combustion stage oil-collecting ring cavity fuel feed holes, main combustion stage fuel oil enters main combustion stage oil-collecting ring cavity by main combustion stage oil-collecting ring cavity fuel feed hole, at main combustion stage nozzle body oil-collecting ring cavity wall, along circumferentially offering some tangential main combustion stage fuel jets, main combustion stage fuel oil outwards sprays by main combustion stage fuel jet, main combustion stage fuel jet is inclined hole, the oil burning jet of main combustion stage shoots out has certain tangential velocity, some strands of fuel oils launch and join in fuel oil film forming district, form circumferentially continuous oil film, under the cyclonic action of main combustion stage nozzle upstream cyclone ring and main combustion stage nozzle downstream cyclone ring, at outlet edge place of fuel oil film forming district, oil film is carried out to shear action, oil film is at main combustion stage nozzle upstream cyclone ring, under the aerodynamic force of main combustion stage nozzle downstream cyclone ring air-flow, will occur broken, be atomized into small fuel particles and blending occurs, fuel particles is brought into main combustion stage premix and pre-evaporation section under the momentum of self and under the Aerodynamic force action of this strand of eddy flow, on ring, have in main combustion stage premix and pre-evaporation section outer shroud and main combustion stage premix and pre-evaporation section and on some main combustion stage ring wall surface air admission holes and main combustion stage premix and pre-evaporation section front bulkhead, have some main combustion stage front end wall air admission holes, under the effect of main combustion stage ring wall surface air admission hole, the air inlet of main combustion stage front end wall air admission hole, can there is further atomization and blending in fuel particles, in main combustion stage premix and pre-evaporation section, evaporate simultaneously, in the exit of main combustion stage premix and pre-evaporation section, liquid fuel evaporite ratio is more complete, gaseous fuel and air blending are good, form uniform gas mixture and enter burner inner liner, under the igniting of pre-combustion grade flame, carry out premixed combustion.
Blade quantity 2≤p≤30 that described main combustion stage outlet water conservancy diversion supports, along encircling circumference uniform distribution in main combustion stage premix and pre-evaporation section, the setting angle of blade is 90 ° of 0 °≤a <.
The geometry of described main combustion stage fuel jet is circle or rectangle, number 2 < m≤300 of spray site, each main combustion stage fuel jet is inclined hole, be arranged in the plane vertical with main combustion stage nozzle-axis, angle of inclination is 90 ° of 0 ° of < b <, main combustion stage nozzle has fuel oil film forming district, and fuel oil is connected into continuous oil film mutually in fuel oil film forming district.
Main combustion stage nozzle upstream cyclone ring, the main combustion stage nozzle downstream cyclone ring of described combustion chamber adopt the radial blade formula structure around main combustion stage nozzle-axis circumference uniform distribution, blade quantity 20≤q≤50, the setting angle of blade is 90 ° of 0 ° of < c <.
The burning use gas of described combustion chamber is all supplied fashionable by head of combustion chamber, air distribution accounts for 40%～80% of combustion chamber inlet air flow; The cooling institute air demand of pre-combustion grade head end wall and main combustion stage head entirety end wall accounts for 5%～10% of whole burning tolerance, pre-combustion grade institute air demand accounts for 5%～25% of whole burning tolerance, and all the other main combustion stage nozzle upstream cyclone rings by main combustion stage, main combustion stage nozzle downstream cyclone ring and main combustion stage premix and pre-evaporation section feed.
The burner inner liner outer wall of described combustion chamber and the type of cooling of burner inner liner inwall adopt air film cooling, disperse cooling or Compound cooling mode, wall surface temperature is controlled to the life-span of prolongation burner inner liner.
Be provided with outer blending hole in described burner inner liner external rear wall, be provided with interior blending hole at described burner inner liner inwall rear portion, blending use gas enters burner inner liner from outer blending hole and interior blending hole respectively, distributes with control combustion chamber outlet temperature.
Principle of the present invention is: generally speaking, the realization of aeroengine combustor buring chamber low pollution emission is exactly mainly by two aspects, the one, control the overall equivalent proportion scope in whole burning Indoor Combustion region; Second be the burning uniformity of the indoor whole combustion zone of control combustion, i.e. equivalent proportion uniformity, the excessive disposal of pollutants that also can greatly increase engine of local equivalent proportion causing because of local rich oil.According to above-mentioned principle and consider the work characteristics of aeroengine combustor buring chamber, the present invention adopts: the design philosophy of fractional combustion, the use gas that makes to burn feeds combustion chamber from pre-combustion grade and main combustion stage respectively, and fuel oil is carried out to classification infeed, control the equivalent proportion of fuel oil in combustion zone under aero-engine different operating state all in combustion with reduced pollutants district, thereby reach the object that reduces Air-pollution From Combustion emission.Pre-combustion grade starts under the little states such as slow train, and while keeping little state, the equivalent proportion of combustion zone drops in above-mentioned combustion with reduced pollutants equivalent proportion interval, and makes the good stability of burning, easily starts.When engine operation just starts main combustion stage during at large state, main combustion stage employing premix and pre-evaporation combustion method, the equivalent proportion in control combustion district is in above-mentioned combustion with reduced pollutants equivalent proportion interval.Adopt above-mentioned low pollution combustor, can guarantee that aeroengine combustor buring chamber is under all duties, the equivalent proportion of combustion zone is all controlled in the interval of combustion with reduced pollutants, can carry out the equivalent proportion uniformity in control combustion district by controlling the main combustion stage mist of oil uniformity, degree of mixing and evaporativity, thereby reach, the disposal of pollutants of aero-engine low pollution combustor is low, the performance requirement of good stability simultaneously.
The present invention's advantage is compared with prior art as follows:
(1) the present invention adopts monocycle cavity combustion chamber structure, and combustion air is all fed by head, only has Cooling Holes and necessary blending hole on burner inner liner, has modular characteristics, has simplified chamber structure, and premix and pre-evaporation endless tube structure is also simpler, is easy to processing;
(2) main combustion stage of the present invention adopts the combustion method of premix and pre-evaporation.The fuel oil of main combustion stage is through inclined hole ejection, form circumferentially oil film uniformly in exit radially, atomization under aerodynamic force, entering premix and pre-evaporation section evaporates and blending, the oil film being circumferentially evenly distributed is more easily realized uniform blending and good evaporation in premix and pre-evaporation section, the gas mixture of good mixing enters in burner inner liner can burn down complete and uniform temperature fields at extremely short time internal combustion, thereby reduces the disposal of pollutants of combustion chamber;
(3) pre-combustion grade of the present invention adopts swirl stabilized diffusion flame combustion method, main combustion stage adopts premix and pre-evaporation combustion method, this combined burning pattern can realize the work of aeroengine combustor buring chamber efficient stable in broad working range, can realize combustion chamber low pollution emission simultaneously.
Brief description of the drawings
Fig. 1 is engine structure schematic diagram;
Fig. 2 is chamber structure cutaway view of the present invention;
Fig. 3 is head of combustion chamber structure cutaway view of the present invention;
Fig. 4 is pre-combustion grade swirler assembly structure cutaway view of the present invention;
Fig. 5 is pre-combustion grade swirler assembly structural perspective of the present invention;
Fig. 6 is main combustion stage structure cutaway view of the present invention;
Fig. 7 is main combustion stage premix and pre-evaporation segment structure schematic diagram of the present invention;
Fig. 8 is main combustion stage outlet water conservancy diversion supporting construction schematic diagram of the present invention;
Fig. 9 is main combustion stage nozzle arrangements cutaway view of the present invention;
Figure 10 is main combustion stage nozzle body structure chart of the present invention;
Figure 11 is main combustion stage nozzle body structure cutaway view of the present invention;
Figure 12 is that main combustion stage nozzle ejection point of the present invention is arranged schematic diagram;
Figure 13 is pre-combustion grade nozzle of the present invention and main combustion stage nozzle assembly for fluid structural perspective;
In figure: 1. low-pressure compressor, 2. high-pressure compressor, 3. combustion chamber, 4. high-pressure turbine, 5. low-pressure turbine, 6. outer combustion case, 7. casing in combustion chamber, 8. burner inner liner outer wall, 9. burner inner liner inwall, 10. diffuser, 11. outer blending hole, 12. interior blending hole, 13. head of combustion chamber, 14. main combustion stages, 15. pre-combustion grade, 16. pre-combustion grade swirler assemblies, 17. pre-combustion grade one-level cyclones, 18. pre-combustion grade second cyclones, 19. pre-combustion grade inward eddy device installing rings, 20. pre-combustion grade Venturi tubes, 21. pre-combustion grade mounting edges, 22. pre-combustion grade nozzle installing holes, 23. pre-combustion grade nozzles, 24. pre-combustion grade head end wall, 25. pre-combustion grade head deflectors, 26. main combustion stage premix and pre-evaporation sections, 27. main combustion stage premix and pre-evaporation section outer shrouds, ring in 28. main combustion stage premix and pre-evaporation sections, 29. main combustion stage premix and pre-evaporation section front bulkheads, 30. main combustion stage front end wall air admission holes, 31. main combustion stage ring wall surface air admission holes, 32. main combustion stage outlet water conservancy diversion support, the 33. main combustion stage nozzles outer ring-shaped pressuring plate that floats, the 34. main combustion stage nozzles outer shroud that floats, ring-shaped pressuring plate in 35. main combustion stage nozzles float, ring in 36. main combustion stage nozzles float, the 37. outer shrouds gap of floating, the 38. interior rings gap of floating, 39. main combustion stage nozzles, 40. main combustion stage nozzle bodies, 41. main combustion stage nozzle body outer walls, 42. main combustion stage nozzle body inwalls, 43. main combustion stage nozzle body front bulkheads, 44. main combustion stage nozzle body ring cavity dividing walls, 45. main combustion stage nozzle body oil-collecting ring cavity walls, 46. main combustion stage oil-feed ring cavities, 47. main combustion stage oil-collecting ring cavities, 48. main combustion stage fuel feed holes, 49. main combustion stage oil-collecting ring cavity fuel feed holes, 50. main combustion stage fuel jets, 51. fuel oil film forming districts, 52. main combustion stage nozzle upstream cyclone rings, 53. main combustion stage nozzle downstream cyclone rings, 54. fuel oil film forming district outlet edges, 55. head entirety end walls, 56. head entirety flow deflectors, 57. main combustion stage nozzle-axis.
Detailed description of the invention
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.When engine operation, air is after low-pressure compressor 1 compression, enter high-pressure compressor 2, pressure-air enters in combustion chamber 3 and oil inflame again, the high-temperature high-pressure fuel gas forming after burning enters into high-pressure turbine 4 and low-pressure turbine 5, is done work and is driven respectively high-pressure compressor 2 and low-pressure compressor 1 by turbine;
As shown in Figure 2, combustion chamber 3 adopts monocycle cavity configuration, and in outer combustion case 6 and combustion chamber, casing 7 has formed the outline of combustion chamber, and is connected with high-pressure compressor 2 and the high-pressure turbine 4 of front and back.The incoming flow air of high-pressure compressor 2 enters combustion chamber from diffuser 10 after reduction of speed diffusion, in the space surrounding, completes burning with fuel oil at burner inner liner outer wall 8, burner inner liner inwall 9 and head of combustion chamber 13.Region before blending hole 11 and interior blending hole 12 is 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 main combustion stage 14 is welded and fixed with burner inner liner outer wall 8 and burner inner liner inwall 9 by head entirety end wall 55, and pre-combustion grade 15 is fixedly connected by pre-combustion grade head end wall 24 and main combustion stage 14.The overall flow deflector 56 of head is welded on respectively in head entirety end wall 55 and pre-combustion grade head end wall 24 with pre-combustion grade head flow deflector 25, they and the high-temperature fuel gas in burner inner liner is separated, to protect structural intergrity;
Fig. 3 is the cutaway view of a head of combustion chamber structure, can clearly find out that main combustion stage 14 and pre-combustion grade 15 are arranged together according to concentric mode.In Fig. 4 and Fig. 5, pre-combustion grade 15 has adopted double cyclones structure, is mainly made up of pre-combustion grade one-level cyclone 17, pre-combustion grade second cyclone 18 and pre-combustion grade Venturi tube 20.Pre-combustion grade Venturi tube 20 and pre-combustion grade second cyclone 18 weld, and 17 of pre-combustion grade one-level cyclones are connected with pre-combustion grade Venturi tube 20 by pre-combustion grade inward eddy device installing ring 19, can float simultaneously.21 of pre-combustion grade mounting edges are connected with pre-combustion grade head end wall 24 and pre-combustion grade head flow deflector 25, can adopt welding or screw thread to add the mode of locking.In Fig. 6, main combustion stage 14 comprises main combustion stage nozzle 39, main combustion stage premix and pre-evaporation section 26, wherein main combustion stage nozzle float outer ring-shaped pressuring plate 33, main combustion stage nozzle float outer shroud 34, main combustion stage nozzle float in ring-shaped pressuring plate 35, main combustion stage nozzle float in ring 36, main combustion stage premix and pre-evaporation section outer shroud 27, main combustion stage premix and pre-evaporation section ring 28, main combustion stage premix and pre-evaporation section front bulkhead 29 and main combustion stage outlet water conservancy diversion support 32 formed main combustion stage premix and pre-evaporation section 26, from Fig. 7 and Fig. 8, can see, main combustion stage premix and pre-evaporation section outer shroud 27, ring 28 in main combustion stage premix and pre-evaporation section, on main combustion stage premix and pre-evaporation section front bulkhead 29, open Multi-stage inlet hole, main combustion stage front end wall air admission hole 30 and main combustion stage ring wall surface air admission hole 31 are straight hole or inclined hole, the oil film mainly playing ejecting from main combustion stage nozzle 39 carries out atomization again, blending also promotes the effect of evaporating, in addition, main combustion stage front end wall air inlet 30 is also played to main combustion stage premix and pre-evaporation section 26 effect with axial initial velocity air inlet is provided, can prevent main combustion stage premix and pre-evaporation section front bulkhead 29 and main combustion stage premix and pre-evaporation section outer shroud 27, the formation recirculating zone, angle of ring 28 in main combustion stage premix and pre-evaporation section, and prevent that main combustion stage nozzle 39 from injecting fuel on the internal face of main combustion stage premix and pre-evaporation section outer shroud 27, as can see from Figure 8, main combustion stage outlet water conservancy diversion supports 32 along encircling 28 circumference uniform distributions in main combustion stage premix and pre-evaporation section, main combustion stage outlet water conservancy diversion supports 32 to be play a part to connect ring 28 in main combustion stage premix and pre-evaporation section outer shroud 27 and main combustion stage premix and pre-evaporation section on the one hand, plays a part on the other hand to adjust through main combustion stage premix and pre-evaporation section 26 air stream outlet angles, main combustion stage outlet water conservancy diversion supports 32 blade quantity 2≤p≤30, along encircling 28 circumference uniform distributions in main combustion stage premix and pre-evaporation section, the setting angle of blade is 90 ° of 0 °≤a <, plays so on the one hand the effect of support and connection, is convenient to processing and installs, blade plays the effect of water conservancy diversion on the other hand.Before implementing installation, can select different blade constructions or adjust setting angle, to meet the requirement of various working, concrete adjustment blade is selected to make a choice depending on different requirements.Specific embodiments, as shown in Fig. 6, Fig. 7 and Fig. 8, when installation, first main combustion stage is exported water conservancy diversion support 32 with in main combustion stage premix and pre-evaporation section, encircle 28 and be connected, adoptable connected mode is overall manufacture or screw thread or bolt or welding; Then by both sub-assemblies, insert in main combustion stage premix and pre-evaporation section outer shroud 27, ensure to encircle in main combustion stage premix and pre-evaporation section 28 with the coaxial prerequisite of main combustion stage premix and pre-evaporation section outer shroud 29 under, use the connected mode of overall manufacture or screw thread or bolt or welding to connect; Then main combustion stage premix and pre-evaporation section front bulkhead 29 is supported to 32 with main combustion stage outlet water conservancy diversion and be connected with the sub-assembly and the main combustion stage premix and pre-evaporation section outer shroud 27 that encircle 28 in main combustion stage premix and pre-evaporation section, adoptable connected mode is overall manufacture or screw thread or bolt or welding; Ensure main combustion stage nozzle float outside ring-shaped pressuring plate 33 coaxial with main combustion stage premix and pre-evaporation section outer shroud 27 in, unsteady main combustion stage nozzle outer shroud 34 is clipped in to main combustion stage nozzle to float between outer ring-shaped pressuring plate 33 and main combustion stage premix and pre-evaporation section outer shroud 27, adopt welding or screw thread or bolted mode, the unsteady outer ring-shaped pressuring plate 33 of main combustion stage nozzle is linked together with main combustion stage premix and pre-evaporation section outer shroud 27; Ensure main combustion stage nozzle encircle in ring-shaped pressuring plate 35 and main combustion stage premix and pre-evaporation section in floating 36 coaxial in, in main combustion stage nozzle is floated, ring 36 is clipped in the unsteady interior ring-shaped pressuring plate 35 of main combustion stage nozzle and main combustion stage premix and pre-evaporation section and encircles between 28, adopt welding or screw thread or bolted mode, the unsteady interior ring-shaped pressuring plate 35 of main combustion stage nozzle 39 and the interior ring 28 of main combustion stage premix and pre-evaporation section are linked together; After above-mentioned installation steps complete, the assembling of main combustion stage premix and pre-evaporation section 26 completes.
Fig. 9 is main combustion stage nozzle arrangements cutaway view of the present invention, main combustion stage nozzle 39 is by main combustion stage nozzle body 40, main combustion stage fuel jet 50, fuel oil film forming district 51, main combustion stage nozzle upstream cyclone ring 52 and main combustion stage nozzle downstream cyclone ring 53 form, main combustion stage nozzle upstream cyclone ring 52, main combustion stage nozzle downstream cyclone ring 53 adopts the radial blade formula structure around main combustion stage nozzle-axis 57 circumference uniform distributions, make by main combustion stage nozzle upstream cyclone ring 52, the air inlet of main combustion stage nozzle downstream cyclone ring 53 has swirling flow characteristic and has certain shear effect, for the atomization of mist of oil, Figure 10 is main combustion stage nozzle body structure chart of the present invention, Figure 11 is main combustion stage nozzle body structure cutaway view of the present invention, and main combustion stage nozzle body 40 is made up of main combustion stage nozzle body outer wall 41, main combustion stage nozzle body inwall 42, main combustion stage nozzle body front bulkhead 43, main combustion stage nozzle body ring cavity dividing wall 44, main combustion stage nozzle body oil-collecting ring cavity wall 45, main combustion stage nozzle body outer wall 41, main combustion stage nozzle body inwall 42, main combustion stage nozzle body front bulkhead 43 and main combustion stage nozzle body ring cavity dividing wall 44 have formed main combustion stage oil-feed ring cavity 46, main combustion stage nozzle body outer wall 41, main combustion stage nozzle body inwall 42, main combustion stage nozzle body ring cavity dividing wall 44 and main combustion stage nozzle body oil-collecting ring cavity wall 45 have formed main combustion stage oil-collecting ring cavity 47, main combustion stage nozzle body outer wall 41, main combustion stage nozzle body inwall 42 and main combustion stage nozzle body oil-collecting ring cavity wall 45 have formed fuel oil film forming district 51, main combustion stage nozzle body ring cavity dividing wall 44 is connected with main combustion stage nozzle body outer wall 41, main combustion stage nozzle body inwall 42, and connected mode is for welding or main combustion stage nozzle body ring cavity dividing wall 44 is weldingly connected with main combustion stage nozzle body inwall 42 with main combustion stage nozzle body outer wall 41 entirety manufactures again or main combustion stage nozzle body ring cavity dividing wall 44 is weldingly connected with main combustion stage nozzle body outer wall 41 with main combustion stage nozzle body inwall 42 entirety manufactures again, main combustion stage nozzle body oil-collecting ring cavity wall 45 is connected with main combustion stage nozzle body outer wall 41, main combustion stage nozzle body inwall 42, and connected mode is for welding or main combustion stage nozzle body oil-collecting ring cavity wall 45 is weldingly connected with main combustion stage nozzle body inwall 42 with main combustion stage nozzle body outer wall 41 entirety manufactures again or main combustion stage nozzle body oil-collecting ring cavity wall 45 is weldingly connected with main combustion stage nozzle body outer wall 41 with main combustion stage nozzle body inwall 42 entirety manufactures again, main combustion stage nozzle body outer wall 41, main combustion stage nozzle body inwall 42, main combustion stage nozzle body front bulkhead 43 are connected, and connected mode is welding or screw thread, main combustion stage nozzle upstream cyclone ring 52 is connected with main combustion stage nozzle body outer wall 41 in fuel oil film forming district 51, and connected mode is welding or entirety manufacture, main combustion stage nozzle downstream cyclone ring 53 is connected with main combustion stage nozzle body inwall 42 in fuel oil film forming district 51, and connected mode is welding or entirety manufacture, main combustion stage nozzle upstream cyclone ring 52 is connected with the unsteady outer ring-shaped pressuring plate 33 of main combustion stage nozzle, and connected mode is welding or screw thread or entirety manufacture, in main combustion stage nozzle downstream cyclone ring 53 floats with main combustion stage nozzle, ring-shaped pressuring plate 35 is connected, and connected mode is welding or overall manufacture, therefore, composition main combustion stage nozzle 39 after main combustion stage nozzle body 40 is connected with main combustion stage nozzle upstream cyclone ring 52, main combustion stage nozzle downstream cyclone ring 53, connected mode is screw thread or welding, in the main combustion stage nozzle upstream cyclone ring 52 of main combustion stage nozzle 39, main combustion stage nozzle downstream cyclone ring 53 float with the unsteady outer ring-shaped pressuring plate 33 of main combustion stage nozzle, main combustion stage nozzle respectively, ring-shaped pressuring plate 34 is connected, and connected mode is screw thread or welding, main combustion stage nozzle upstream cyclone ring 52 and main combustion stage nozzle float and after outer ring-shaped pressuring plate 33 is connected, are stuck in the unsteady gap 37 of outer shroud between the unsteady outer shroud 34 of main combustion stage nozzle and the main combustion stage premix and pre-evaporation section front bulkhead 29 of main combustion stage premix and pre-evaporation section 26, main combustion stage nozzle downstream cyclone ring 53 is stuck in the unsteady interior ring 36 of main combustion stage nozzle and the interior unsteady gap 38 of interior ring of encircling between 28 of main combustion stage premix and pre-evaporation section of main combustion stage premix and pre-evaporation section 26 after being connected with the unsteady interior ring-shaped pressuring plate 34 of main combustion stage nozzle, after above-mentioned installation steps complete, main combustion stage nozzle 39 is just connected as a body with main combustion stage premix and pre-evaporation section 26, has formed main combustion stage 14.As can be seen from Figure 10, offer a main combustion stage fuel feed hole 48 on main combustion stage nozzle body front bulkhead 43, main combustion stage fuel oil enters main combustion stage oil-feed ring cavity 46 by main combustion stage fuel feed hole 48, as can be seen from Figure 11, offer some main combustion stage oil-collecting ring cavity fuel feed holes 49 on main combustion stage nozzle body ring cavity dividing wall 44, main combustion stage fuel oil enters main combustion stage oil-collecting ring cavity 47 by main combustion stage oil-collecting ring cavity fuel feed hole 49, at main combustion stage nozzle body oil-collecting ring cavity wall 45, along circumferentially offering some tangential main combustion stage fuel jets 50, the layout of main combustion stage fuel jet 50 is as Figure 12, and main combustion stage fuel oil outwards sprays by main combustion stage fuel jet 50, main combustion stage fuel jet 50 is inclined hole, the oil burning jet of main combustion stage shoots out has certain tangential velocity, some strands of fuel oils launch and join in fuel oil film forming district 51, form circumferentially continuous oil film, under the cyclonic action of main combustion stage nozzle upstream cyclone ring 52 and main combustion stage nozzle downstream cyclone ring 53, at outlet edge 54 places of fuel oil film forming district, oil film is carried out to shear action, oil film is at main combustion stage nozzle upstream cyclone ring 52, under the aerodynamic force of main combustion stage nozzle downstream cyclone ring 53 air-flows, will occur broken, be atomized into small fuel particles and blending occurs, fuel particles is brought into main combustion stage premix and pre-evaporation section 26 under the momentum of self and under the Aerodynamic force action of this strand of eddy flow, on ring 28, have in main combustion stage premix and pre-evaporation section outer shroud 27 and main combustion stage premix and pre-evaporation section and on some main combustion stage ring wall surface air admission holes 31 and main combustion stage premix and pre-evaporation section front bulkhead 29, have some main combustion stage front end wall air admission holes 30, under the effect of main combustion stage ring wall surface air admission hole 31,30 air inlets of main combustion stage front end wall air admission hole, can there is further atomization and blending in fuel particles, in main combustion stage premix and pre-evaporation section 26, evaporate simultaneously, in the exit of main combustion stage premix and pre-evaporation section 26, liquid fuel evaporite ratio is more complete, gaseous fuel and air blending are good, form uniform gas mixture and enter burner inner liner, under the igniting of pre-combustion grade flame, carry out premixed combustion.
Figure 13 is pre-combustion grade nozzle of the present invention and main combustion stage nozzle assembly for fluid structural perspective, the pre-combustion grade nozzle 23 of the main combustion stage nozzle 39 of main combustion stage 14 and pre-combustion grade 15 is integrated in a structure, there are two benefits, the one, facilitate the installation of whole head, the 2nd, can strict guarantee main combustion stage nozzle 39 and the concentricity of pre-combustion grade nozzle 23, pre-combustion grade nozzle 23 adopts a rotarytype injector, by independent fuel pipe fuel feeding, coordinates with pre-combustion grade one-level cyclone 17 by pre-combustion grade nozzle installing hole 22, main combustion stage nozzle 39 adopts the outside fuel injected of several main combustion stage fuel jets 50, the geometry of main combustion stage fuel jet 50 is circle or rectangle, number 2 < m≤300 of spray site, each spout is inclined hole, be arranged in the plane vertical with main combustion stage nozzle-axis 57, angle of inclination is 90 ° of 0 ° of < b <, fuel oil is from supplying after several main combustion stage fuel jets 50 eject, launch to be connected into mutually oil film in fuel oil film forming district 51, be subject to main combustion stage nozzle upstream cyclone ring 52 at fuel oil film forming district outlet edge 54, the Aerodynamic force action generation secondary-atomizing of main combustion stage nozzle downstream cyclone ring 53 swirling eddies, then enter main combustion stage premix and pre-evaporation section 26, pre-combustion grade nozzle and main combustion stage nozzle provide combustion chamber required whole fuel oils, and wherein to account for the ratio of total amount of fuel be 50%～90% to main combustion stage fuel oil.
After main combustion stage premix and pre-evaporation section 26 and 16 installations of pre-combustion grade swirler assembly, insert the sub-assembly of main combustion stage nozzle 39 and pre-combustion grade nozzle 23 at correspondence position, thereby complete the installation of head of combustion chamber 13.
Non-elaborated part of the present invention belongs to techniques well known.
Claims (7)
1. one kind adopts the radially premix and pre-evaporation combustion chamber of film forming main combustion stage, it is characterized in that: described combustion chamber adopts monocycle cavity configuration, form combustion chamber outline by casing (7) in outer combustion case (6) and 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) composition combustion zone, combustion air all enters burner inner liner by head of combustion chamber (13), and dilution air is injected by the interior blending hole (12) on outer blending hole (11) and burner inner liner inwall (9) on burner inner liner outer wall (8), described head of combustion chamber (13) adopts fractional combustion scheme, is divided into main combustion stage (14) and pre-combustion grade (15), described main combustion stage (14) is connected and fixed by head entirety end wall (55) and burner inner liner outer wall (8) and burner inner liner inwall (9), described pre-combustion grade (15) connects with main combustion stage (14) by pre-combustion grade head end wall (24), and concentric with main combustion stage (14), described pre-combustion grade (15) comprises deflector (25) in pre-combustion grade swirler assembly (16), pre-combustion grade nozzle (23), pre-combustion grade head end wall (24) and pre-combustion grade head, pre-combustion grade (15) is utilized and is entered by pre-combustion grade swirler assembly (16) the low speed recirculating zone that the rotational flow air of combustion chamber forms and stabilize the flame, and pre-combustion grade swirler assembly (16) is connected by pre-combustion grade head end wall (24) and interior encircle (28) of main combustion stage premix and pre-evaporation section, pre-combustion grade nozzle (23) is positioned at pre-combustion grade swirler assembly (16), and coaxial with pre-combustion grade swirler assembly (16), described main combustion stage (14) comprises main combustion stage nozzle (39), main combustion stage premix and pre-evaporation section (26), described main combustion stage premix and pre-evaporation section (26) by main combustion stage nozzle float outer ring-shaped pressuring plate (33), main combustion stage nozzle float outer shroud (34), main combustion stage nozzle float in ring-shaped pressuring plate (35), main combustion stage nozzle float in ring (36), main combustion stage premix and pre-evaporation section outer shroud (27), main combustion stage premix and pre-evaporation section ring (28), main combustion stage premix and pre-evaporation section front bulkhead (29) and main combustion stage export water conservancy diversion support (32) and form, the main combustion stage nozzle outer shroud (34) that floats is connected with main combustion stage premix and pre-evaporation section front bulkhead (29), before the unsteady outer shroud (34) of main combustion stage nozzle is connected with main combustion stage premix and pre-evaporation section front bulkhead (29), unsteady main combustion stage nozzle outer ring-shaped pressuring plate (33) is arranged on to the unsteady gap (37) of outer shroud that main combustion stage nozzle floats between outer shroud (34) and main combustion stage premix and pre-evaporation section front bulkhead (29), and the unsteady outer ring-shaped pressuring plate (33) of main combustion stage nozzle is stuck in the unsteady gap (37) of outer shroud and also can floats, in main combustion stage nozzle floats, ring (36) is connected with ring (28) in main combustion stage premix and pre-evaporation section, before in main combustion stage nozzle floats, ring (36) is connected with the interior ring of main combustion stage premix and pre-evaporation section (28), in main combustion stage nozzle is unsteady, ring-shaped pressuring plate (35) is arranged on the unsteady gap (38) of interior ring between the unsteady interior ring of main combustion stage nozzle (36) and the interior ring of main combustion stage premix and pre-evaporation section (28), and in main combustion stage nozzle is unsteady, ring-shaped pressuring plate (35) is stuck in the unsteady gap (38) of interior ring and can floats, described main combustion stage outlet water conservancy diversion supports (32) and is made up of some blades, be welded in main combustion stage premix and pre-evaporation section ring (28) upper or with main combustion stage premix and pre-evaporation section in ring (28) entirety manufacture, main combustion stage nozzle (39) is positioned at main combustion stage nozzle and floats between outer shroud (34) and the unsteady ring of main combustion stage nozzle (36), and coaxial with pre-combustion grade nozzle (23), main combustion stage nozzle (39) is made up of main combustion stage nozzle body (40), main combustion stage fuel jet (50), fuel oil film forming district (51), main combustion stage nozzle upstream cyclone ring (52) and main combustion stage nozzle downstream cyclone ring (53), main combustion stage nozzle body (40) is made up of main combustion stage nozzle body outer wall (41), main combustion stage nozzle body inwall (42), main combustion stage nozzle body front bulkhead (43), main combustion stage nozzle body ring cavity dividing wall (44), main combustion stage nozzle body oil-collecting ring cavity wall (45), main combustion stage nozzle body outer wall (41), main combustion stage nozzle body inwall (42), main combustion stage nozzle body front bulkhead (43) and main combustion stage nozzle body ring cavity dividing wall (44) have formed main combustion stage oil-feed ring cavity (46), main combustion stage nozzle body outer wall (41), main combustion stage nozzle body inwall (42), main combustion stage nozzle body ring cavity dividing wall (44) and main combustion stage nozzle body oil-collecting ring cavity wall (45) have formed main combustion stage oil-collecting ring cavity (47), main combustion stage nozzle body outer wall (41), main combustion stage nozzle body inwall (42) and main combustion stage nozzle body oil-collecting ring cavity wall (45) have formed fuel oil film forming district (51), main combustion stage nozzle body ring cavity dividing wall (44) is connected with main combustion stage nozzle body outer wall (41), main combustion stage nozzle body inwall (42), and connected mode is for welding or main combustion stage nozzle body ring cavity dividing wall (44) is weldingly connected with main combustion stage nozzle body inwall (42) with the manufacture of main combustion stage nozzle body outer wall (41) entirety again or main combustion stage nozzle body ring cavity dividing wall (44) is manufactured and is weldingly connected with main combustion stage nozzle body outer wall (41) with main combustion stage nozzle body inwall (42) entirety, main combustion stage nozzle body oil-collecting ring cavity wall (45) is connected with main combustion stage nozzle body outer wall (41), main combustion stage nozzle body inwall (42), and connected mode is for welding or main combustion stage nozzle body oil-collecting ring cavity wall (45) is weldingly connected with main combustion stage nozzle body inwall (42) with the manufacture of main combustion stage nozzle body outer wall (41) entirety again or main combustion stage nozzle body oil-collecting ring cavity wall (45) is manufactured and is weldingly connected with main combustion stage nozzle body outer wall (41) with main combustion stage nozzle body inwall (42) entirety, main combustion stage nozzle body outer wall (41), main combustion stage nozzle body inwall (42), main combustion stage nozzle body front bulkhead (43) are connected, and connected mode is welding or screw thread, main combustion stage nozzle upstream cyclone ring (52) is connected with main combustion stage nozzle body outer wall (41) in fuel oil film forming district (51), and connected mode is welding or entirety manufacture, main combustion stage nozzle downstream cyclone ring (53) is connected with main combustion stage nozzle body inwall (42) in fuel oil film forming district (51), and connected mode is welding or entirety manufacture, main combustion stage nozzle upstream cyclone ring (52) is connected with the unsteady outer ring-shaped pressuring plate (33) of main combustion stage nozzle, and connected mode is welding or screw thread or entirety manufacture, in main combustion stage nozzle downstream cyclone ring (53) floats with main combustion stage nozzle, ring-shaped pressuring plate (35) is connected, therefore, composition main combustion stage nozzle (39) after main combustion stage nozzle body (40) is connected with main combustion stage nozzle upstream cyclone ring (52), main combustion stage nozzle downstream cyclone ring (53), forms main combustion stage (14) after main combustion stage nozzle (39) is connected with main combustion stage premix and pre-evaporation section (26), on main combustion stage nozzle body front bulkhead (43), offer a main combustion stage fuel feed hole (48), main combustion stage fuel oil enters main combustion stage oil-feed ring cavity (46) by main combustion stage fuel feed hole (48), on main combustion stage nozzle body ring cavity dividing wall (44), offer some main combustion stage oil-collecting ring cavity fuel feed holes (49), main combustion stage fuel oil enters main combustion stage oil-collecting ring cavity (47) by main combustion stage oil-collecting ring cavity fuel feed hole (49), at main combustion stage nozzle body oil-collecting ring cavity wall (45), along circumferentially offering some tangential main combustion stage fuel jets (50), main combustion stage fuel oil outwards sprays by main combustion stage fuel jet (50), main combustion stage fuel jet (50) is inclined hole, the oil burning jet of main combustion stage shoots out has certain tangential velocity, some strands of fuel oils launch and join in fuel oil film forming district (51), form circumferentially continuous oil film, under the cyclonic action of main combustion stage nozzle upstream cyclone ring (52) and main combustion stage nozzle downstream cyclone ring (53), locate oil film to carry out shear action at fuel oil film forming district outlet edge (54), oil film is at main combustion stage nozzle upstream cyclone ring (52), under the aerodynamic force of main combustion stage nozzle downstream cyclone ring (53) air-flow, will occur broken, be atomized into small fuel particles and blending occurs, fuel particles is brought into main combustion stage premix and pre-evaporation section (26) under the momentum of self and under the Aerodynamic force action of this strand of eddy flow, in main combustion stage premix and pre-evaporation section outer shroud (27) and main combustion stage premix and pre-evaporation section, on ring (28), have on some main combustion stage ring wall surface air admission holes (31) and main combustion stage premix and pre-evaporation section front bulkhead (29) and have some main combustion stage front end wall air admission holes (30), under the effect of main combustion stage ring wall surface air admission hole (31), main combustion stage front end wall air admission hole (30) air inlet, can there is further atomization and blending in fuel particles, in main combustion stage premix and pre-evaporation section (26), evaporate simultaneously, in the exit of main combustion stage premix and pre-evaporation section (26), liquid fuel evaporite ratio is more complete, gaseous fuel and air blending are good, form uniform gas mixture and enter burner inner liner, under the igniting of pre-combustion grade flame, carry out premixed combustion.
2. the radially premix and pre-evaporation combustion chamber of film forming main combustion stage of a kind of employing according to claim 1, it is characterized in that: described main combustion stage outlet water conservancy diversion supports blade quantity 2≤p≤30 of (32), along ring (28) circumference uniform distribution in main combustion stage premix and pre-evaporation section, the setting angle of blade is 90 ° of 0 °≤a <.
3. the radially premix and pre-evaporation combustion chamber of film forming main combustion stage of a kind of employing according to claim 1, it is characterized in that: the geometry of described main combustion stage fuel jet (50) is circle or rectangle, number 2 < m≤300 of spray site m, each main combustion stage fuel jet (50) is inclined hole, be arranged in the plane vertical with main combustion stage nozzle-axis (57), angle of inclination b is 90 ° of 0 ° of < b <, main combustion stage nozzle (39) has fuel oil film forming district (51), fuel oil is connected into continuous oil film mutually in fuel oil film forming district (51).
4. the radially premix and pre-evaporation combustion chamber of film forming main combustion stage of a kind of employing according to claim 1, it is characterized in that: described main combustion stage nozzle upstream cyclone ring (52), main combustion stage nozzle downstream cyclone ring (53) adopt the radial blade formula structure around main combustion stage nozzle-axis (57) circumference uniform distribution, blade quantity q is 20≤q≤50, and the setting angle c of blade is 90 ° of 0 ° of < c <.
5. the radially premix and pre-evaporation combustion chamber of film forming main combustion stage of a kind of employing according to claim 1, it is characterized in that: the burning use gas of described combustion chamber is all supplied fashionable by head of combustion chamber (13), air distribution accounts for 40%～80% of combustion chamber inlet air flow; The cooling institute air demand of pre-combustion grade head end wall (24) and main combustion stage head entirety end wall (55) accounts for 5%～10% of whole burning tolerance, pre-combustion grade (14) institute air demand accounts for 5%～25% of whole burning tolerance, and all the other main combustion stage nozzle upstream cyclone rings (52) by main combustion stage (15), main combustion stage nozzle downstream cyclone ring (53) and main combustion stage premix and pre-evaporation section (26) feed.
6. the radially premix and pre-evaporation combustion chamber of film forming main combustion stage of a kind of employing according to claim 1, 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 air film cooling, disperse cooling or Compound cooling mode, wall surface temperature is controlled to the life-span of prolongation burner inner liner.
7. the radially premix and pre-evaporation combustion chamber of film forming main combustion stage of a kind of employing according to claim 1, it is characterized in that: be provided with outer blending hole (11) at described burner inner liner outer wall (8) rear portion, be provided with interior blending hole (12) at described burner inner liner inwall (9) rear portion, blending use gas enters burner inner liner from outer blending hole (11) and interior blending hole (12) respectively, distributes with control combustion chamber outlet temperature.
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| JP6028578B2 (en) * | 2013-01-15 | 2016-11-16 | 株式会社Ihi | Combustor |
| CN103185355B (en) * | 2013-02-28 | 2015-07-15 | 北京航空航天大学 | Premixing pre-evaporation low-pollution combustion chamber with multi-point axial double-stage air auxiliary atomizing nozzle main combustion stage |
| EP2927598B1 (en) * | 2014-03-31 | 2018-12-19 | Siemens Aktiengesellschaft | Method for replacing a swirler |
| US9927126B2 (en) * | 2015-06-10 | 2018-03-27 | General Electric Company | Prefilming air blast (PAB) pilot for low emissions combustors |
| CN109340823A (en) * | 2018-09-17 | 2019-02-15 | 北京石油化工学院 | A kind of head of combustion chamber oil gas mixing machine |
| CN109945233B (en) * | 2019-03-20 | 2021-01-29 | 中国航发湖南动力机械研究所 | Combustion chamber, atomization device thereof and aviation gas turbine engine |
| CN113932253B (en) * | 2020-06-29 | 2022-10-18 | 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 |
| CN113137629B (en) * | 2021-04-19 | 2022-11-04 | 中国航发湖南动力机械研究所 | Double-stage integral swirler and flame tube head structure |
| CN115264534B (en) * | 2021-04-29 | 2023-09-26 | 中国航发商用航空发动机有限责任公司 | Cyclone, flame tube and aeroengine |
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