CN102889617A - 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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- CN102889617A CN102889617A CN2012103379256A CN201210337925A CN102889617A CN 102889617 A CN102889617 A CN 102889617A CN 2012103379256 A CN2012103379256 A CN 2012103379256A CN 201210337925 A CN201210337925 A CN 201210337925A CN 102889617 A CN102889617 A CN 102889617A
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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 the premixed combustion technology, adopt the pattern of fractional combustion, pre-combustion grade employing diffusion combustion organizational form, main combustion stage employing premixed combustion organizational form, main combustion stage adopt radially, and the mode of film forming feeds fuel oil.This invention can guarantee the wider stable operation range of combustion chamber, reduces simultaneously the combustion chamber disposal of pollutants.
Background technology
The key property of modern aeroengine combustion chamber and structure distribution have reached quite high level, but for the modern aeroengine combustion chamber, still have a large amount of difficult problems and challenge, the development and application of new material, new technology, new construction, new ideas is only and guarantees that it continues progressive source.
The Main Trends of The Development of modern civil aviation engine chamber is combustion with reduced pollutants.The civil aviation engine chamber must satisfy the aero-engine emission standard of increasingly stringent.The CAEP6(Committee on Aviation Environmental Protection that adopts at present) standard is very strict to the regulation of pollutant effulent, particularly to the NOx emission requirement; And up-to-date CAEP8 standard has proposed to reduce by 15% on the discharge standard that is emitted on CAEP6 with NOx, along with the fast development of aircraft industry and improving constantly of people's environmental consciousness, following gas-turbine combustion chamber disposal of pollutants meeting is proposed higher requirement.
Two GE of leading company of US Airways engine and PW set about research already to low pollution combustor, GE has has at first researched and developed dicyclo chamber combustion with reduced pollutants DAC(and has been used for GE90 and CFM56), PW company has adopted RQL(fuel-rich combustion-extinguishing-poor oil firing, Rich burn-Quench-Lean burn is called for short RQL) low pollution combustor TALON II(is used 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 the RQL mode to propose reduction NOx disposal of pollutants is TALON X, the head type that adopts is the air atomizer spray nozzle of PW development of company, the combustion chamber is the monocycle chamber, and the result of the test on V2500 engine fan type test section has reduced by 50% than CAEP2 standard.It is ANTLE that Rolls-Royce company adopts the low pollution combustor of LDM technical development, and this combustion chamber is fractional combustion chamber, a monocycle chamber, and its NOx disposal of pollutants has reduced by 50% than CAEP2 standard, is used for its engine rapids of new generation and reaches 1000.
And no matter be which kind of advanced person's low pollution combustor, its key technology reduces the NOx(nitrogen oxide exactly), the CO(carbon monoxide), the UHC(unburned hydrocarbons) and the combustion technology of smoldering, key problem is to reduce the temperature of combustion zone, make simultaneously the combustion zone temperature field even, 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.The mechanism that produces according to NOx and CO and result of the test be as can be known: the NOx that the primary zone equivalent proportion of combustion chamber produces in 0.6～0.8 scope and the discharging rule of CO(UHC and CO are similar) seldom.Based on this principle, the discharge capacity of taking into account NOx and CO, UHC all is in the low value scope, should consider two factors: the average equivalent ratio in first primary zone, it two is uniformities of primary zone average equivalent ratio, and all should be like this under the working condition of all aero-engines.And the uniformity of primary zone equivalent proportion depends primarily on the uniformity of fuel-oil atmozation and oil gas blending.This depends primarily on two aspects: the one, and the uniformity that the fuel particles diameter distributes, the i.e. distributing homogeneity of SMD; Second be the uniformity that the fuel oil oil mist concentration distributes.From combustion system, should adopt uniform premixed combustion, reach primary zone equivalent proportion uniformity requirement to reduce disposal of pollutants.
Present conventional combustion mode can't reduce NOx, CO and U HC.Reason is that the method for designing of current combustion chamber determines.For the conventional combustion chamber, when large operating mode, owing to adopting liquid mist diffusion combustion mode, the local equivalent proportion in combustion zone is always near 1, the required equivalent proportion area requirement of above-mentioned combustion with reduced pollutants that surpasses far away, although this moment CO and the discharging of UHC low, it is maximum that the discharging of NOx reaches.When unskilled labourer's condition, the combustion zone equivalent proportion is very low again, and is interval far below the required equivalent proportion of above-mentioned combustion with reduced pollutants, although this moment, the NOx discharging was low, CO and UHC discharging are very high again.In addition, because diffusion combustion mode is generally adopted in the conventional combustion chamber, local equivalent proportion is inhomogeneous, therefore for the conventional combustion chamber, can't satisfy the low pollution requirement in whole engine operation scope.Therefore, for the demand for development of civil aviation engine chamber, need a kind of combustion chamber that can the decrease disposal of pollutants of development, and can not make other performances poor than the 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, is satisfying under the condition of work of aero-engine this combustion chamber, can effectively reduce the disposal of pollutants of aeroengine combustor buring chamber burning, comprise NOx, smolder, CO and UHC, and simple in structure.
Technical solution of the present invention: a kind of employing is the premix and pre-evaporation combustion chamber of film forming main combustion stage radially, adopts the monocycle cavity configuration, consists of the combustion chamber outline by casing in outer combustion case and the combustion chamber, and outside air enters by diffuser; Burner inner liner outer wall, burner inner liner inwall and head of combustion chamber form the combustion zone, and combustion air all enters burner inner liner by head of combustion chamber, and dilution air is injected by the outer blending hole on the burner inner liner outer wall and the interior blending hole on the burner inner liner inwall; Described head of combustion chamber adopts the fractional combustion scheme, is divided into main combustion stage and pre-combustion grade; Described main combustion stage is connected and fixed by the whole end wall of head and burner inner liner outer wall and burner inner liner inwall, and described pre-combustion grade is passed through the 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 the pre-combustion grade head, the pre-combustion grade utilization enters the low speed recirculating zone retention flame that the rotational flow air of combustion chamber forms by the pre-combustion grade swirler assembly, and the pre-combustion grade swirler assembly is connected by encircling in pre-combustion grade head end wall and the main combustion stage premix and pre-evaporation section; The pre-combustion grade nozzle is positioned at the pre-combustion grade swirler assembly, and coaxial with the pre-combustion grade swirler assembly; 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 the 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 the 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 the water conservancy diversion support and form; The unsteady outer shroud of main combustion stage nozzle links to each other 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, the main combustion stage nozzle outer ring-shaped pressuring plate that floats is installed in main combustion stage nozzle outer shroud and outer shroud between the main combustion stage premix and pre-evaporation section front bulkhead slit of floating of floating, so the main combustion stage nozzle outer shroud pressure board that floats can float also in the unsteady slit of outer shroud; Encircle in ring and the main combustion stage premix and pre-evaporation section in the main combustion stage nozzle floats and link to each other, connected mode is screw thread or welding, before ring adopted nut or is welded to connect in ring and the main combustion stage premix and pre-evaporation section in the main combustion stage nozzle floated, in the main combustion stage nozzle floated ring-shaped pressuring plate be installed in the main combustion stage nozzle float in the slit of floating of the interior ring between the ring in ring and the main combustion stage premix and pre-evaporation section, so the main combustion stage nozzle float in ring-shaped pressuring plate be stuck in the interior ring slit of floating and also can float; Described main combustion stage outlet water conservancy diversion supports and is comprised of some blades, can be welded in the main combustion stage premix and pre-evaporation section ring upper or with main combustion stage premix and pre-evaporation section in ring is whole makes; The main combustion stage nozzle floats between outer shroud and main combustion stage nozzle encircle in floating at the main combustion stage nozzle, and coaxial with the pre-combustion grade nozzle; The main combustion stage nozzle is comprised 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; The main combustion stage nozzle body is comprised 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 consisted of 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 consisted of 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 consisted of fuel oil film forming district; Main combustion stage nozzle body ring cavity dividing wall links to each other with main combustion stage nozzle body outer wall, main combustion stage nozzle body inwall, and connected mode is made for welding or main combustion stage nozzle body ring cavity dividing wall and main combustion stage nozzle body outer wall are whole 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 manufacturing of main combustion stage nozzle body inwall integral body again again; Main combustion stage nozzle body oil-collecting ring cavity wall links to each other with main combustion stage nozzle body outer wall, main combustion stage nozzle body inwall, and connected mode is made for welding or main combustion stage nozzle body oil-collecting ring cavity wall and main combustion stage nozzle body outer wall are whole 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 manufacturing of main combustion stage nozzle body inwall integral body again again; Main combustion stage nozzle body outer wall, main combustion stage nozzle body inwall, main combustion stage nozzle body front bulkhead link to each other, and connected mode is welding or screw thread; Main combustion stage nozzle upstream cyclone ring links to each other with main combustion stage nozzle body outer wall in fuel oil film forming district, and connected mode is welding or whole the manufacturing; Main combustion stage nozzle downstream cyclone ring links to each other with main combustion stage nozzle body inwall in fuel oil film forming district, and connected mode is welding or whole the manufacturing; 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 whole the manufacturing; Main combustion stage nozzle downstream cyclone ring is connected with the unsteady interior ring-shaped pressuring plate of main combustion stage nozzle, and connected mode is welding or whole manufacturing; Therefore, after linking to each other with main combustion stage nozzle upstream cyclone ring, main combustion stage nozzle downstream cyclone ring, the main combustion stage nozzle body forms the main combustion stage nozzle, the main combustion stage nozzle upstream cyclone ring of main combustion stage nozzle, main combustion stage nozzle downstream cyclone ring link to each other with the unsteady outer ring-shaped pressuring plate of main combustion stage nozzle, the unsteady interior ring-shaped pressuring plate of main combustion stage nozzle respectively, the 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 slit, the interior ring slit of floating of floating, formation main combustion stage after the main combustion stage nozzle links to each other with main combustion stage premix and pre-evaporation section; Offer a main combustion stage fuel feed hole at main combustion stage nozzle body front bulkhead, the main combustion stage fuel oil enters main combustion stage oil-feed ring cavity by the main combustion stage fuel feed hole; Offer some main combustion stage oil-collecting ring cavity fuel feed holes at main combustion stage nozzle body ring cavity dividing wall, the main combustion stage fuel oil enters main combustion stage oil-collecting ring cavity by main combustion stage oil-collecting ring cavity fuel feed hole; Along circumferentially offering some tangential main combustion stage fuel jets, the main combustion stage fuel oil outwards sprays by the main combustion stage fuel jet at main combustion stage nozzle body oil-collecting ring cavity wall; The 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 in fuel oil film forming district and join, 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, fuel oil film forming district oil film is carried out shear action, oil film is at main combustion stage nozzle upstream cyclone ring, to occur broken under the aerodynamic force of main combustion stage nozzle downstream cyclone ring air-flow, be atomized into small fuel particles and blending occurs, fuel particles is being brought into main combustion stage premix and pre-evaporation section under the momentum of self and under the Aerodynamic force action of this strand eddy flow, have on the ring in main combustion stage premix and pre-evaporation section outer shroud and the main combustion stage premix and pre-evaporation section and have some main combustion stage front end wall air admission holes on some main combustion stage ring wall surface air admission holes and the main combustion stage premix and pre-evaporation section front bulkhead; Further atomizing and blending can occur in fuel particles 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, in main combustion stage premix and pre-evaporation section, evaporate simultaneously, the liquid fuel evaporite ratio is more complete in the exit of main combustion stage premix and pre-evaporation section, 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 that described main combustion stage outlet water conservancy diversion supports≤30, along encircling circumference uniform distribution in the main combustion stage premix and pre-evaporation section, the setting angle of blade is 0 °≤a＜90 °.
The geometry of described main combustion stage fuel jet is circle or rectangle, number 2＜the m of spray site≤300, each main combustion stage fuel jet is inclined hole, be arranged on the plane vertical with the main combustion stage nozzle-axis, the angle of inclination is 0 °＜b＜90 °, the 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.
The main combustion stage nozzle upstream cyclone ring of described combustion chamber, main combustion stage nozzle downstream cyclone ring adopt the radial blade formula structure around main combustion stage nozzle-axis circumference uniform distribution, blade quantity 20≤q≤50, and the setting angle of blade is 0 °＜c＜90 °.
The burning usefulness gas of described combustion chamber is all supplied fashionable by head of combustion chamber, the air distribution accounts for 40%～80% of combustion chamber inlet air flow; The cooling institute air demand of the whole end wall of pre-combustion grade head end wall and main combustion stage head 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 the air film cooling, disperse cooling or Compound cooling mode, wall surface temperature is controlled the life-span that prolongs 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 usefulness 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 mainly is exactly by two aspects, and the one, control the overall equivalent proportion scope in internal combustion zone, whole combustion chamber; 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 that causes because of local rich oil.According to above-mentioned principle and consider the work characteristics of aeroengine combustor buring chamber, the present invention adopts: the design philosophy of fractional combustion, make burning usefulness gas feed the combustion chamber from pre-combustion grade and main combustion stage respectively, and fuel oil is carried out classification feed, the control equivalent proportion of fuel oil in the combustion zone under aero-engine different operating state all in the combustion with reduced pollutants district, thereby reach the purpose that reduces the Air–pollution From Combustion emission.Pre-combustion grade starts under the little states such as slow train, and the equivalent proportion of combustion zone drops in the above-mentioned combustion with reduced pollutants equivalent proportion interval when keeping little state, and makes the good stability of burning, easily starts.When engine operation just starts main combustion stage during at large state, main combustion stage adopts the premix and pre-evaporation combustion method, and the equivalent proportion in control combustion district is interval in above-mentioned combustion with reduced pollutants equivalent proportion.Adopt above-mentioned low pollution combustor, can guarantee that the aeroengine combustor buring chamber is under all duties, the equivalent proportion of combustion zone all is controlled in the interval of combustion with reduced pollutants, can come the equivalent proportion uniformity in control combustion district by the control main combustion stage mist of oil uniformity, degree of mixing and evaporativity simultaneously, the disposal of pollutants of aero-engine low pollution combustor is low, the performance requirement of good stability thereby reach.
The present invention's advantage compared with prior art is 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 the 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 the inclined hole ejection, form circumferentially uniformly oil film in exit radially, under aerodynamic force, atomize, entering the premix and pre-evaporation section evaporates and blending, the oil film that circumferentially is evenly distributed is more easily realized uniform blending and good evaporation in the premix and pre-evaporation section, the gas mixture of good mixing enters in the burner inner liner can be in extremely short time internal combustion fully and uniform temperature fields, thereby reduce 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 the premix and pre-evaporation combustion method, this combined burning pattern can realize the work of aeroengine combustor buring chamber efficient stable in the working range of broadness, can realize the combustion chamber low pollution emission simultaneously.
Description of drawings
Fig. 1 is the 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;
Among the 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 the 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 stage, 15. pre-combustion grade, 16. pre-combustion grade swirler assembly, 17. pre-combustion grade one-level cyclone, 18. pre-combustion grade second cyclones, 19. pre-combustion grade inward eddy device installing rings, 20. pre-combustion grade Venturi tube, 21. the pre-combustion grade mounting edge, 22. pre-combustion grade nozzle installing holes, 23. pre-combustion grade nozzles, 24. pre-combustion grade head end wall, 25. pre-combustion grade head deflector, 26. main combustion stage premix and pre-evaporation sections, 27. main combustion stage premix and pre-evaporation section outer shrouds, 28. ring in the main combustion stage premix and pre-evaporation section, 29. main combustion stage premix and pre-evaporation section front bulkhead, 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 supports, the outer ring-shaped pressuring plate 33. the main combustion stage nozzle 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. the main combustion stage nozzle floats, the slit 37. outer shroud floats, the 38. interior rings slit of floating, 39. main combustion stage nozzles, 40. main combustion stage nozzle body, 41. main combustion stage nozzle body outer wall, 42. main combustion stage nozzle body inwalls, 43. main combustion stage nozzle body front bulkheads, 44. main combustion stage nozzle body ring cavity dividing wall, 45. main combustion stage nozzle body oil-collecting ring cavity wall, 46. main combustion stage oil-feed ring cavities, 47. main combustion stage oil-collecting ring cavities, 48. main combustion stage fuel feed hole, 49. main combustion stage oil-collecting ring cavity fuel feed hole, 50. main combustion stage fuel jets, 51. fuel oil film forming districts, 52. main combustion stage nozzle upstream cyclone ring, 53. main combustion stage nozzle downstream cyclone ring, 54. fuel oil film forming district outlet edges, the whole end wall of 55. heads, 56. the whole flow deflector of head, 57. main combustion stage nozzle-axis.
The specific embodiment
Fig. 1 is the engine structure schematic diagram, comprises low-pressure compressor 1, high-pressure compressor 2, combustion chamber 3, high-pressure turbine 4 and low-pressure turbine 5.During engine operation, after air compresses through low-pressure compressor 1, enter high-pressure compressor 2, pressure-air enters in the combustion chamber 3 and oil inflame again, the high-temperature high-pressure fuel gas that forms after the burning enters into high-pressure turbine 4 and low-pressure turbine 5, drives respectively high-pressure compressor 2 and low-pressure compressor 1 by the turbine acting;
As shown in Figure 2, the monocycle cavity configurations are adopted in combustion chamber 3, and casing 7 has consisted of the outline of combustion chamber in outer combustion case 6 and the combustion chamber, and are connected with high-pressure turbine with the high-pressure compressor 2 of front and back and are connected.The incoming flow air of high-pressure compressor 2 enters the combustion chamber behind diffuser 10 process reduction of speed diffusions, finish burning with fuel oil in the space that burner inner liner outer wall 8, burner inner liner inwall 9 and head of combustion chamber 13 surround.Zone before blending hole 11 and the interior blending hole 12 is the combustion zone outside, and dilution air enters burner inner liner from blending hole, and the high-temperature fuel gas blending with the combustion zone makes outlet temperature reach designing requirement.Head of combustion chamber 13 comprises main combustion stage 14, pre-combustion grade 15, and main combustion stage 14 is welded and fixed with burner inner liner outer wall 8 and burner inner liner inwall 9 by the whole end wall 55 of head, and pre-combustion grade 15 then is fixedly connected by pre-combustion grade head end wall 24 and main combustion stage 14.The whole flow deflector 56 of head and pre-combustion grade head flow deflector 25 are welded on respectively on the whole end wall 55 of head and the pre-combustion grade head end wall 24, with the high-temperature fuel gas in they and the burner inner liner separately, and with the protection structural intergrity;
Fig. 3 is the cutaway view of a head of combustion chamber structure, can find out clearly that main combustion stage 14 and pre-combustion grade 15 are arranged together according to concentric mode.In Fig. 4 and Fig. 5, pre-combustion grade 15 has adopted the double cyclones structure, mainly is comprised 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 18 welding of pre-combustion grade second cyclone, 17 of pre-combustion grade one-level cyclones pass through pre-combustion grade inward eddy device installing ring 19 and are connected with pre-combustion grade Venturi tube 20, can float simultaneously.21 of pre-combustion grade mounting edges are connected with pre-combustion grade head flow deflector with pre-combustion grade head end wall 24 and are connected, and 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 the 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 the 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 the main combustion stage premix and pre-evaporation section, opened the Multi-stage inlet hole on the main combustion stage premix and pre-evaporation section front bulkhead 29, 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 that mainly plays ejecting from main combustion stage nozzle 39 atomizes again, the effect of blending and promotion evaporation, 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 angle of ring 28 forms the recirculating zone in the main combustion stage premix and pre-evaporation section, and prevents 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 ring 28 circumference uniform distributions in the 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 the 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 blade quantity 2≤p of 32≤30, and along ring 28 circumference uniform distributions in the main combustion stage premix and pre-evaporation section, the setting angle of blade is 0 °≤a＜90 °, plays so on the one hand the effect of support and connection, is convenient to the processing installation; Blade plays the effect of water conservancy diversion on the other hand.Can select different blade constructions or adjust setting angle before implementing installation, to satisfy the requirement of various working, concrete adjustment blade is selected to look different requirement and is made a choice.Specific embodiments such as Fig. 6, Fig. 7 and shown in Figure 8, during installation, at first exports main combustion stage water conservancy diversion support 32 and is connected with ring 28 in the main combustion stage premix and pre-evaporation section, and adoptable connected mode is whole manufacturing or screw thread or bolt or welding; Then with both sub-assembly, insert in the main combustion stage premix and pre-evaporation section outer shroud 27, in guaranteeing main combustion stage premix and pre-evaporation section, under the coaxial prerequisite of ring 28 and main combustion stage premix and pre-evaporation section outer shroud 29, use the connected mode of whole manufacturing or screw thread or bolt or welding to connect; Then main combustion stage premix and pre-evaporation section front bulkhead 29 and the support 32 of main combustion stage outlet water conservancy diversion are linked to each other with sub-assembly and the main combustion stage premix and pre-evaporation section outer shroud 27 of ring 28 in the main combustion stage premix and pre-evaporation section, adoptable connected mode is whole manufacturing or screw thread or bolt or welding; Guarantee the main combustion stage nozzle float outside ring-shaped pressuring plate 33 and main combustion stage premix and pre-evaporation section outer shroud 27 coaxial in, the unsteady outer shroud 34 of main combustion stage nozzle is clipped in the main combustion stage nozzle to float between outer ring-shaped pressuring plate 33 and the 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; Guarantee the main combustion stage nozzle encircle in ring-shaped pressuring plate 35 and the main combustion stage premix and pre-evaporation section in floating 36 coaxial in, ring 36 was clipped in the unsteady interior ring-shaped pressuring plate 35 of main combustion stage nozzle and the main combustion stage premix and pre-evaporation section and encircles between 28 in the main combustion stage nozzle is unsteady, adopt welding or screw thread or bolted mode, main combustion stage nozzle 39 unsteady interior ring-shaped pressuring plates 35 are linked together with the interior ring 28 of main combustion stage premix and pre-evaporation section; After above-mentioned installation steps were finished, the assembling of main combustion stage premix and pre-evaporation section 26 was finished.
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, the radial blade formula structure that main combustion stage nozzle downstream cyclone ring 53 adopts around main combustion stage nozzle-axis 57 circumference uniform distributions, so that 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, is used for the atomizing 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 comprised 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 consisted of 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 consisted of 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 consisted of fuel oil film forming district 51; Main combustion stage nozzle body ring cavity dividing wall 44 links to each other 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 41 whole manufacturings of main combustion stage nozzle body outer wall 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 whole manufacturings again; Main combustion stage nozzle body oil-collecting ring cavity wall 45 links to each other 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 41 whole manufacturings of main combustion stage nozzle body outer wall 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 whole manufacturings again; Main combustion stage nozzle body outer wall 41, main combustion stage nozzle body inwall 42, main combustion stage nozzle body front bulkhead 43 link to each other, and connected mode is welding or screw thread; Main combustion stage nozzle upstream cyclone ring 52 links to each other with main combustion stage nozzle body outer wall 41 in fuel oil film forming district 51, and connected mode is welding or whole the manufacturing; Main combustion stage nozzle downstream cyclone ring 53 links to each other with main combustion stage nozzle body inwall 42 in fuel oil film forming district 51, and connected mode is welding or whole the manufacturing; 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 whole the manufacturing; Main combustion stage nozzle downstream cyclone ring 53 is connected with the unsteady interior ring-shaped pressuring plate 35 of main combustion stage nozzle, and connected mode is welding or whole manufacturing; Therefore, form main combustion stage nozzle 39 after main combustion stage nozzle body 40 links to each other with main combustion stage nozzle upstream cyclone ring 52, main combustion stage nozzle downstream cyclone ring 53, connected mode is screw thread or welding; The main combustion stage nozzle upstream cyclone ring 52 of main combustion stage nozzle 39, main combustion stage nozzle downstream cyclone ring 53 link to each other with the unsteady outer ring-shaped pressuring plate 33 of main combustion stage nozzle, the unsteady interior ring-shaped pressuring plate 34 of main combustion stage nozzle respectively, and connected mode is screw thread or welding; Main combustion stage nozzle upstream cyclone ring 52 and main combustion stage nozzle the float unsteady outer shroud 34 of main combustion stage nozzle that is stuck in main combustion stage premix and pre-evaporation section 26 after outer ring-shaped pressuring plate 33 is connected and the unsteady slit 37 of outer shroud between the main combustion stage premix and pre-evaporation section front bulkhead 29; In floating, the main combustion stage nozzle that is stuck in main combustion stage premix and pre-evaporation section 26 after ring-shaped pressuring plate 34 was connected in main combustion stage nozzle downstream cyclone ring 53 and main combustion stage nozzle floated encircles the unsteady slit 38 of interior ring between 28 in ring 36 and the main combustion stage premix and pre-evaporation section; After above-mentioned installation steps were finished, main combustion stage nozzle 39 just was connected as a body with main combustion stage premix and pre-evaporation section 26, has consisted of main combustion stage 14.As can be seen from Figure 10, offer a main combustion stage fuel feed hole 48 at main combustion stage nozzle body front bulkhead 43, the 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 at main combustion stage nozzle body ring cavity dividing wall 44, the 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; Along circumferentially offering some tangential main combustion stage fuel jets 50, the layout of main combustion stage fuel jet 50 such as Figure 12, main combustion stage fuel oil pass through main combustion stage fuel jet 50 and outwards spray at main combustion stage nozzle body oil-collecting ring cavity wall 45; 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 51 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 52 and main combustion stage nozzle downstream cyclone ring 53, at outlet edge 54 places, fuel oil film forming district oil film is carried out shear action, oil film is at main combustion stage nozzle upstream cyclone ring 52, to occur broken under the aerodynamic force of main combustion stage nozzle downstream cyclone ring 53 air-flows, be atomized into small fuel particles and blending occurs, fuel particles is being 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 eddy flow, have on the ring 28 in main combustion stage premix and pre-evaporation section outer shroud 27 and the main combustion stage premix and pre-evaporation section and have some main combustion stage front end wall air admission holes 30 on some main combustion stage ring wall surface air admission holes 31 and the main combustion stage premix and pre-evaporation section front bulkhead 29; Further atomizing and blending can occur in fuel particles 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, in main combustion stage premix and pre-evaporation section 26, evaporate simultaneously, the liquid fuel evaporite ratio is more complete in the exit of main combustion stage premix and pre-evaporation section 26, 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 main combustion stage nozzle 39 of main combustion stage 14 and the pre-combustion grade nozzle 23 of pre-combustion grade 15 are integrated on the structure, two benefits are arranged, the one, the installation of convenient 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, cooperates with pre-combustion grade one-level cyclone 17 by pre-combustion grade nozzle installing hole 22; Main combustion stage nozzle 39 adopts several main combustion stage fuel jet 50 outside fuel injected, the geometry of main combustion stage fuel jet 50 is circle or rectangle, number 2＜the m of spray site≤300, each spout is inclined hole, be arranged on the plane vertical with main combustion stage nozzle-axis 57, the angle of inclination is 0 °＜b＜90 °, fuel oil is from supplying after several main combustion stage fuel jets 50 eject, 51 launch to be connected into mutually oil film in fuel oil film forming district, be subject to main combustion stage nozzle upstream cyclone ring 52 at fuel oil film forming district outlet edge 54, then the Aerodynamic force action generation secondary-atomizing of main combustion stage nozzle downstream cyclone ring 53 swirling eddies enters main combustion stage premix and pre-evaporation section 26; Pre-combustion grade nozzle and main combustion stage nozzle provide the combustion chamber required whole fuel oils, and wherein to account for the ratio of total amount of fuel be 50%～90% to the 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 finish the installation of head of combustion chamber 13.
The non-elaborated part of the present invention belongs to techniques well known.
Claims (7)
1. one kind is adopted the radially premix and pre-evaporation combustion chamber of film forming main combustion stage, it is characterized in that: the monocycle cavity configuration is adopted in described combustion chamber, consist of the combustion chamber outline by casing (7) in outer combustion case (6) and the combustion chamber, outside air enters by diffuser (10); Burner inner liner outer wall (8), burner inner liner inwall (9) and head of combustion chamber (13) form the combustion zone, combustion air all enters burner inner liner by head of combustion chamber (13), and dilution air is injected by the outer blending hole (11) on the burner inner liner outer wall (8) and the interior blending hole (12) on the burner inner liner inwall (9); Described head of combustion chamber (13) adopts the fractional combustion scheme, is divided into main combustion stage (14) and pre-combustion grade (15); Described main combustion stage (14) is connected and fixed by the whole end wall of head (43) 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 the pre-combustion grade head, pre-combustion grade (15) is utilized by pre-combustion grade swirler assembly (16) and is entered the low speed recirculating zone retention flame that the rotational flow air of combustion chamber forms, 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 the 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), the 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 links to each other with main combustion stage premix and pre-evaporation section front bulkhead (29), float outer shroud (34) with before main combustion stage premix and pre-evaporation section front bulkhead (29) is connected at the main combustion stage nozzle, the main combustion stage nozzle outer ring-shaped pressuring plate (33) that floats is installed in main combustion stage nozzle outer shroud (34) and outer shroud between the main combustion stage premix and pre-evaporation section front bulkhead (29) slit (37) of floating of floating, and the main combustion stage nozzle outer ring-shaped pressuring plate (33) that floats is stuck in the unsteady slit (37) of outer shroud and also can floats; Ring (36) linked to each other with ring (28) in the main combustion stage premix and pre-evaporation section in the main combustion stage nozzle floated, before encircling (36) in the main combustion stage nozzle floats and ring (28) in the main combustion stage premix and pre-evaporation section being connected, ring-shaped pressuring plate (35) was installed in the unsteady interior unsteady slit (38) of interior ring of encircling between (36) and the interior ring of main combustion stage premix and pre-evaporation section (28) of main combustion stage nozzle in the main combustion stage nozzle is unsteady, and the unsteady interior ring-shaped pressuring plate (35) of main combustion stage nozzle is stuck in the unsteady slit (38) of interior ring and can floats; Described main combustion stage outlet water conservancy diversion supports (32) and is comprised of some blades, be welded in the main combustion stage premix and pre-evaporation section ring (28) upper or with main combustion stage premix and pre-evaporation section in ring (28) is whole makes; Main combustion stage nozzle (39) is positioned at the 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 comprised 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 comprised 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 consisted of 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 consisted of 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 consisted of fuel oil film forming district (51); Main combustion stage nozzle body ring cavity dividing wall (44) links to each other 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 whole manufacturing of main combustion stage nozzle body outer wall (41) 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 whole manufacturing of main combustion stage nozzle body inwall (42) again; Main combustion stage nozzle body oil-collecting ring cavity wall (45) links to each other 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 whole manufacturing of main combustion stage nozzle body outer wall (41) 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 whole manufacturing of main combustion stage nozzle body inwall (42) again; Main combustion stage nozzle body outer wall (41), main combustion stage nozzle body inwall (42), main combustion stage nozzle body front bulkhead (43) link to each other, and connected mode is welding or screw thread; Main combustion stage nozzle upstream cyclone ring (52) links to each other with main combustion stage nozzle body outer wall (41) in fuel oil film forming district (51), and connected mode is welding or whole the manufacturing; Main combustion stage nozzle downstream cyclone ring (53) links to each other with main combustion stage nozzle body inwall (42) in fuel oil film forming district (51), and connected mode is welding or whole the manufacturing; 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 whole the manufacturing; Main combustion stage nozzle downstream cyclone ring (53) is connected with the unsteady interior ring-shaped pressuring plate (35) of main combustion stage nozzle; Therefore, main combustion stage nozzle body (40) and main combustion stage nozzle upstream cyclone ring (52), after linking to each other, main combustion stage nozzle downstream cyclone ring (53) forms main combustion stage nozzle (39), the main combustion stage nozzle upstream cyclone ring (52) of main combustion stage nozzle (39), main combustion stage nozzle downstream cyclone ring (53) respectively with the main combustion stage nozzle outer ring-shaped pressuring plate (33) that floats, ring-shaped pressuring plate (34) linked to each other in the main combustion stage nozzle floated, the main combustion stage nozzle outer ring-shaped pressuring plate (33) that floats, ring-shaped pressuring plate (34) was stuck in the unsteady slit (37) of outer shroud in the main combustion stage nozzle floated, after linking to each other with main combustion stage premix and pre-evaporation section (26), the interior ring slit (38) of floating, main combustion stage nozzle (39) consist of main combustion stage (14); Offer a main combustion stage fuel feed hole (48) at main combustion stage nozzle body front bulkhead (43), the main combustion stage fuel oil enters main combustion stage oil-feed ring cavity (46) by main combustion stage fuel feed hole (48); Offer some main combustion stage oil-collecting ring cavity fuel feed holes (49) at main combustion stage nozzle body ring cavity dividing wall (44), the 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); Along circumferentially offering some tangential main combustion stage fuel jets (50), the main combustion stage fuel oil outwards sprays by main combustion stage fuel jet (50) at main combustion stage nozzle body oil-collecting ring cavity wall (45); 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 in fuel oil film forming district (51) and join, 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 is carried out shear action at fuel oil film forming district outlet edge (54), oil film is at main combustion stage nozzle upstream cyclone ring (52), to occur broken under the aerodynamic force of main combustion stage nozzle downstream cyclone ring (53) air-flow, be atomized into small fuel particles and blending occurs, fuel particles is being 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 eddy flow, have on some main combustion stage ring wall surface air admission holes (31) and the main combustion stage premix and pre-evaporation section front bulkhead (29) on the ring (28) in main combustion stage premix and pre-evaporation section outer shroud (27) and the main combustion stage premix and pre-evaporation section and have some main combustion stage front end wall air admission holes (30); Further atomizing and blending can occur in fuel particles 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, in main combustion stage premix and pre-evaporation section (26), evaporate simultaneously, the liquid fuel evaporite ratio is more complete in the exit of main combustion stage premix and pre-evaporation section (26), 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. a kind of employing according to claim 1 premix and pre-evaporation combustion chamber of film forming main combustion stage radially, it is characterized in that: the blade quantity 2≤p of described main combustion stage outlet water conservancy diversion support (32)≤30, along ring (28) circumference uniform distribution in the main combustion stage premix and pre-evaporation section, the setting angle of blade is 0 °≤a＜90 °.
3. a kind of employing according to claim 1 premix and pre-evaporation combustion chamber of film forming main combustion stage radially, it is characterized in that: the geometry of described main combustion stage fuel jet (50) is circle or rectangle, number 2＜m of spray site m≤300, each main combustion stage fuel jet (50) is inclined hole, be arranged on the plane vertical with main combustion stage nozzle-axis (57), angle of inclination b is 0 °＜b＜90 °, main combustion stage nozzle (39) has fuel oil film forming district (51), and fuel oil is connected into continuous oil film mutually in fuel oil film forming district (51).
4. a kind of employing according to claim 1 premix and pre-evaporation combustion chamber of film forming main combustion stage radially, 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 0 °＜c＜90 °.
5. a kind of employing according to claim 1 premix and pre-evaporation combustion chamber of film forming main combustion stage radially, it is characterized in that: the burning usefulness gas of described combustion chamber is all supplied fashionable by head of combustion chamber (13), the air distribution accounts for 40%～80% of combustion chamber inlet air flow; The cooling institute air demand of the whole end wall of pre-combustion grade head end wall (24) and main combustion stage head (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. a kind of employing according to claim 1 premix and pre-evaporation combustion chamber of film forming main combustion stage radially, 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 the air film cooling, disperse cooling or Compound cooling mode, wall surface temperature is controlled the life-span that prolongs burner inner liner.
7. a kind of employing according to claim 1 premix and pre-evaporation combustion chamber of film forming main combustion stage radially, 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 usefulness 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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| CN113137629A (en) * | 2021-04-19 | 2021-07-20 | 中国航发湖南动力机械研究所 | Double-stage integral swirler and flame tube head structure |
| CN115264534A (en) * | 2021-04-29 | 2022-11-01 | 中国航发商用航空发动机有限责任公司 | Swirler, flame tube and aeroengine |
| 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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| CN102889617B (en) | 2014-10-15 |
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