CN100557318C - A kind of integral fuel jet axial swirler pre-mixing preevaporated low pollution combustion chamber - Google Patents
A kind of integral fuel jet axial swirler pre-mixing preevaporated low pollution combustion chamber Download PDFInfo
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- CN100557318C CN100557318C CNB2008101046863A CN200810104686A CN100557318C CN 100557318 C CN100557318 C CN 100557318C CN B2008101046863 A CNB2008101046863 A CN B2008101046863A CN 200810104686 A CN200810104686 A CN 200810104686A CN 100557318 C CN100557318 C CN 100557318C
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Abstract
A kind of integral fuel jet axial swirler pre-mixing preevaporated low pollution combustion chamber, combustion chamber are the monocycle cavity configuration, are made up of head of combustion chamber and burner inner liner, and head of combustion chamber comprises pre-combustion grade and the peripheral main combustion stage that is positioned at the center; Main combustion stage comprises direct-injection type air atomizer spray nozzle and main combustion stage axial swirler; Employing is with the injection and the main combustion stage axial swirler integrated technique scheme of main combustion stage fuel oil, the main combustion stage fuel oil of direct-injection type air atomizer spray nozzle ejection enters in the main combustion stage axial swirler blade path of main combustion stage axial swirler blade, and mix with the rotational flow air of main combustion stage axial swirler, the gas mixture of premix enters into the combustion zone through the main combustion stage hybrid chamber again and burns; This combustion system can effectively reduce the discharging of combustion chamber pollutant mistake; Can reduce simultaneously the length of combustion chamber; The present invention is mainly used in the aeroengine combustor buring chamber, also can be used in industry gas turbine and the naval vessel gas-turbine combustion chamber, to reduce the pollutant of row in atmosphere.
Description
Technical field
The present invention relates to a kind of low pollution emission combustion chamber, particularly a kind of integral fuel jet axial swirler pre-mixing preevaporated low pollution combustion chamber.
Background technology
The main development trend of aeroengine combustor buring chamber is combustion with reduced pollutants.The aero-engine emission standard of increasingly stringent must be satisfied in the aeroengine combustor buring chamber.The requirement of CAEP4 (the Committee on Aviation EnvironmentalProtection) standard that adopts at present is very strict, and is particularly to the NOx emission requirement, after 2008 that the CAEP6 standard that adopts is then more strict.The emission requirement of industry gas turbine reaches units---the requirement of ten thousand/concentration discharge.
In general, the aero-engine pollutant can be divided into two classes: because the pollutant that high flame temperature produces is nitrogen oxide (NOx); Because the pollutant that low flame temperature produces is carbon monoxide and unburned carbon hydrogen (CO and UHC).Mechanism that produces according to pollutant and experimental result as can be known, combustion chambers burn district equivalent proportion is in a very little scope (0.6～0.8), above-mentioned two big pollutants dischargings reach minimum.For conventional combustion chamber, when high power state, owing to adopt liquid mist diffusion combustion mode, the local equivalent proportion in combustion zone is always near 1, far away from the required equivalent proportion area requirement of above-mentioned combustion with reduced pollutants, so the discharging of CO and UHC is little, maximum but the discharging of NOx reaches.When low power state, the combustion zone equivalent proportion is very low again, far below the required equivalent proportion of above-mentioned combustion with reduced pollutants interval, the NOx discharging is low, but CO and UHC discharging are very high again, therefore for conventional combustion chamber, can't satisfy the low pollution requirement in whole engine operation scope.
GE engine company has proposed a kind of low pollution combustor-TAPS (Twin Annular Premixing Swirler), and head of combustion chamber comprises main combustion stage and pre-combustion grade, and main combustion stage and pre-combustion grade difference fuel feeding, realizes the subregion combustion system.According to this thinking, GE company has applied for several United States Patent (USP)s.Application number is that the main combustion stage scheme that 6418726 United States Patent (USP) proposes is: the main combustion stage fuel oil is injected to the rear portion of axial swirler, forms the premix and pre-evaporation gas mixture.In this organization plan, reach certain degree of mixing and evaporativity, mixing that needs and evaporation distance are longer, accompanying drawing as can be known from this patent, the fuel oil spray site approximately is half of head of combustion chamber structure height to porch, combustion zone distance, and for this fractional combustion chamber, the head construction height is greater than the head construction height of conventional combustion chamber, therefore the axial length of head of combustion chamber is oversize, thereby influences the length and the weight requirement of combustion chamber and even engine.Have this problem equally in application number is 6363726 United States Patent (USP), the fuel oil spray site is 1/3rd of a head of combustion chamber structure height approximately to porch, combustion zone distance.Above-mentioned several United States Patent (USP) has all been realized the low pollution requirement in the whole engine operation scope, but main combustion stage fuel oil spray site all has a segment distance from the cyclone outlet, and this segment distance has increased the head of combustion chamber axial length, thereby increases engine length and weight.
Summary of the invention
The technical problem to be solved in the present invention is: overcome above-mentioned prior art deficiency, adopt integrated fuel oil injection/axial swirler scheme, when I dye discharging in effective reduction combustion chamber, reduce the distance that the fuel oil spray site enters the mouth to the combustion zone, thereby reduce the axial length of head of combustion chamber structure, just effectively reduced the length and the weight of engine.
The technical solution adopted for the present invention to solve the technical problems is: a kind of integral fuel jet axial swirler pre-mixing preevaporated low pollution combustion chamber, form by head of combustion chamber 26 and burner inner liner, it is characterized in that: the combustion chamber is the monocycle cavity configuration, head of combustion chamber 26 comprises the pre-combustion grade 24 that is positioned at the center and the main combustion stage 25 of outer ring, and main combustion stage 25 has the direct-injection type of including air atomizer spray nozzle 33 and main combustion stage axial swirler 34; Employing is with the injection and the main combustion stage axial swirler 34 incorporate technical schemes of main combustion stage fuel oil 41, the main combustion stage fuel oil 41 of direct-injection type air atomizer spray nozzle 33 ejections enters in the main combustion stage axial swirler blade path 42 of main combustion stage axial swirler blade 37, and mix with the rotational flow air of main combustion stage axial swirler 34, the gas mixture of premix enters into combustion zone 16 burnings through main combustion stage hybrid chamber 36 again, realizes integrated fuel oil injection/axial swirler scheme.
Direct-injection type air atomizer spray nozzle 33 spray site 38 of described main combustion stage 25 are positioned on the main combustion stage axial swirler inwall 43, and spray site quantity is identical with blade quantity.
Direct-injection type air atomizer spray nozzle 33 spray site 39 of described main combustion stage 25 are positioned at optional position, main combustion stage axial swirler blade 37 both sides, and the spray site quantity on each blade can be 1, and perhaps 2, perhaps a plurality of combinations.
Direct-injection type air atomizer spray nozzle 33 spray site 40 of described main combustion stage 25 are positioned on the main combustion stage axial swirler outer wall 44, and spray site quantity is identical with blade quantity.
Direct-injection type air atomizer spray nozzle 33 positions of described main combustion stage 25 comprise spray site 38, any one in spray site 39 and the spray site 40, two or three s' combination.
Described main combustion stage fuel oil spray site to the porch, combustion zone apart from the relation between 49x and the head of combustion chamber structure height 48y is:
The tolerance of described main combustion stage 25 accounts for 65%～95% of head of combustion chamber tolerance, and the tolerance of pre-combustion grade 24 accounts for 5%～35%.
Described burning gas consumption all infeeds from head of combustion chamber 26, does not have primary holes on the burner inner liner, has only cooling hole, outer blending hole 21 and interior blending hole 22.
It is adjustable in 0 ° to 180 ° that described main combustion stage is received expansion part 35 contraction angles 47.
Operation principle of the present invention: the fuel oil in the main combustion stage axial swirler passage forms the premix and pre-evaporation gas mixture and enters into the combustion zone and burn under the effect of axial swirler air-flow, form the premixed combustion mode, pre-combustion grade adopts swirl atomizer and hydrocyclone structure, form diffusion combustion mode, take into account the performance requirement of flameholding and two contradictions of disposal of pollutants.This combustion system can be controlled the equivalent proportion of combustion chamber under different conditions, and this equivalent proportion is remained in the interval of low pollution emission, thereby helps controlling disposal of pollutants.Do not have primary holes on the combustion chamber flame drum, have only cooling hole and blending hole, the burning gas consumption all enters from head of combustion chamber.Main combustion stage and pre-combustion grade keep suitable tolerance to distribute, to adapt to different engine chamber working condition requirements.Control cooling air flows, and avoids producing too much CO and UHC.
Pre-combustion grade starts under low power 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 low power state, makes the good stability of burning, easily starting.When engine operation just starts main combustion stage during at high power state, the equivalent proportion of control combustion zone is in above-mentioned combustion with reduced pollutants equivalent proportion interval, and main combustion stage is the premix and pre-evaporation pattern, can guarantee the uniformity of local equivalent proportion in the combustion zone.Adopt this low pollution combustor head construction, can guarantee under all duties in aeroengine combustor buring chamber, the equivalent proportion of combustion zone is controlled in the interval of combustion with reduced pollutants, control the equivalent proportion uniformity of combustion zone simultaneously by the control main combustion stage mist of oil uniformity, degree of mixing and evaporativity, thereby it is low to reach disposal of pollutants, aeroengine combustor buring chamber performance requirements such as good stability.
Under a certain parameter (inlet velocity and temperature, pressure etc.) condition, fuel oil reaches that needed distance definition is L under a certain degree of mixing, consider from the disposal of pollutants angle, this length is the bigger the better, but consider that from tempering and spontaneous combustion angle this length again should not be too big, during therefore corresponding to a certain parameter, take all factors into consideration above-mentioned two factors, this length should be a definite value.For the TAPS scheme, the length of main combustion stage fuel oil spray site when fuel oil reaches a certain degree of mixing is L, and cyclone exports to the distance of spray site is Lsi, and cyclone length is Ls, and the length when reaching a certain degree of mixing like this from the cyclone inlets to the fuel oil is L+Lsi+Ls.The present invention adopts integrated fuel oil injection/axial swirler scheme, fuel oil injection and axial swirler are integrated, under identical axial swirler intake condition, length when reaching identical degree of mixing is L1+L, wherein L1 is not more than Ls, has not only removed axial swirler and has exported to the distance L si of spray site, but also made full use of the length L s of axial swirler, thereby shortened the axial length of head of combustion chamber greatly, reduced the length of combustion chamber and engine.
The present invention's advantage compared with prior art is as follows:
1. the injection of main combustion stage fuel oil of the present invention in the axial swirler passage, when reaching identical degree of mixing and evaporativity, the distance that needs shortens greatly, has reduced the length of combustion chamber.
2. combustion chambers burn tolerance of the present invention is all infeeded by head, and cooling and blending etc. then enter from burner inner liner with gas, simplifies the structure of combustion chamber when increasing the combustion chamber effect.
3. the compound combustion mode of pre-combustion grade diffusion combustion of the present invention and main combustion stage premix and pre-evaporation burning has realized performance requirements such as the wide stable operation range of aeroengine combustor buring chamber and low pollution emission.
Description of drawings
Fig. 1 is the engine structure schematic diagram;
Fig. 2 is the chamber structure schematic diagram;
Fig. 3 is the enlarged diagram in the zone 3 of combustion chamber;
Fig. 4 is the injection situation schematic diagram of first kind of main combustion stage fuel oil spray site; Wherein Fig. 4 a is a front view, and Fig. 4 b is a left view, and Fig. 4 c is the cutaway view in Fig. 4 b left view;
Fig. 5 is the injection situation schematic diagram of second kind of main combustion stage fuel oil spray site; Wherein Fig. 5 a is a front view, and Fig. 5 b is the cutaway view in Fig. 5 a front view, and Fig. 5 c is a left view for just second-class side figure (3-D view), Fig. 5 d, and Fig. 5 e is the cutaway view in Fig. 5 d left view;
Fig. 6 is the injection situation schematic diagram of the third main combustion stage fuel oil spray site; Wherein Fig. 6 a is a front view, and Fig. 6 b is the cutaway view in Fig. 6 a front view, and Fig. 6 c is the cutaway view among Fig. 6 b, and Fig. 6 d is just second-class side figure (3-D view);
Fig. 7 is a main combustion stage oil circuit collector ring schematic diagram, and wherein Fig. 7 a is the collector ring front view, and Fig. 7 b is the cutaway view in Fig. 7 a front view;
Fig. 8 is the fuel injection system schematic diagram, and wherein scheming A is that fuel oil is ejected into the schematic diagram in the transverse jet, and figure B is that TAPS main combustion stage fuel oil sprays schematic diagram, and figure C sprays schematic diagram for main combustion stage fuel oil of the present invention;
Among the figure: 10 engines, 11 low-pressure compressors, 12 high-pressure compressors, 13 combustion chambers, 14 high-pressure turbines, 15 low-pressure turbines, 16 combustion zones, 17 outer casings, 18 interior casings, 19 outer flame tube walls, flame tube wall in 20,21 outer blending hole, 22 interior blending hole, 23 head end wall, 24 pre-combustion grade, 25 main combustion stages, 26 head constructions, 27 pre-combustion grade swirl atomizers, 28 pre-combustion grade cyclones, 29 pre-combustion grade are received and are expanded part, 30 pre-combustion grade hybrid chambers, 31 pre-combustion grade swirl atomizer fuel oils, 32 pre-combustion grade swirler blades, 33 direct-injection type air atomizer spray nozzles, 34 main combustion stage axial swirlers, 35 main combustion stages are received and are expanded part, 36 main combustion stage hybrid chambers, 37 main combustion stage axial swirler blades, 38 spray site, be positioned on the main combustion stage axial swirler inwall, 39 spray site are positioned at arbitrary position, main combustion stage axial swirler blade both sides, 40 spray site, be positioned on the main combustion stage axial swirler outer wall, 41 main combustion stage fuel oils, 42 main combustion stage axial swirler blade paths, 43 main combustion stage axial swirler inwalls, 44 main combustion stage axial swirler outer walls, 45 main combustion stage nozzle entrances, 46 main combustion stage oil circuit collector rings, 47 main combustion stages are received and are expanded part contraction angle, 48 head of combustion chamber structure heights, the distance that 49 main combustion stage fuel oil spray site enter the mouth to the combustion zone.
The specific embodiment
Introduce the present invention in detail below in conjunction with the drawings and the specific embodiments.
Fig. 1 is the schematic diagram of an engine 10, and engine 10 comprises low-pressure compressor 11, high-pressure compressor 12, combustion chamber 13, high-pressure turbine 14 and low-pressure turbine 15.During engine 10 work, after air compresses through low-pressure compressor 11, enter high-pressure compressor 12 again, pressure-air enters into combustion chamber 13 burnings, fuel injection system is oil spout in high pressure draught, burns fully effectively in combustion chamber 13, and the burning back forms high-temperature high-pressure fuel gas, enter into high-pressure turbine 14 and low-pressure turbine 15, thereby promote the turbine acting.Fig. 2 is the schematic diagram of combustion chamber 13, and the combustion chamber is the monocycle cavity configuration.Fig. 3 is zone 3 zoomed-in views among Fig. 2, is the detailed structure of head of combustion chamber.Combustion chamber 13 comprises a combustion zone 16, and the external boundary of combustion zone 16 is outer flame tube walls 19, and inner boundary is interior flame tube wall 20, the interior flame tube wall 20 of annular and outer flame tube wall 19 the interior casing 18 of annular and outside between the casing 17.Blending hole 22 and outer blending hole 21 are used to adjust the combustor exit Temperature Distribution in arranging to have on inside and outside burner inner liner wall, also arrange on the inside and outside burner inner liner wall to cool off the hole (not shown), are used to cool off the burner inner liner wall, the life-span of assurance combustion chamber.16 upstream is a head construction 26 in the combustion zone, and head construction 26 is connected with the burner inner liner wall by head end wall 23.Head construction 26 comprises pre-combustion grade 24 and main combustion stage 25, because there is not primary holes, all burning tolerance all add from head of combustion chamber, head of combustion chamber is exactly an oil-poor head like this, help reducing the NOx disposal of pollutants, pre-combustion grade 24 tolerance account for 5%～35% of head of combustion chamber tolerance, and main combustion stage 25 tolerance account for 65%～95% of head of combustion chamber tolerance.
Center pre-combustion grade 24 comprises central nozzle 27, pre-combustion grade cyclone 28 and receives and expand part 29, receives expansion part 29 and has formed pre-combustion grade hybrid chamber 30.Central nozzle 27 adopts swirl atomizers, and the fuel oil 31 of swirl atomizer ejection burns with the combustion zone that enters into the combustion chamber in pre-combustion grade hybrid chamber 30 after the rotational flow air of pre-combustion grade cyclone 28 mixes again.
Outer ring main combustion stage 25 comprises direct-injection type air atomizer spray nozzle 33, main combustion stage axial swirler 34 and receives and expand part 35, receive the outside wall surface that expands part 35 and pre-combustion grade receipts expansion part 29 and formed main combustion stage hybrid chamber 36, it is adjustable in 0 ° to 180 ° to receive the contraction angle 47 that expands part 35, to adapt to different engine chamber working condition requirements.The main combustion stage fuel oil 41 of direct-injection type air atomizer spray nozzle 33 ejections enters in the main combustion stage axial swirler blade path 42 of main combustion stage axial swirler blade 37, and mix with the rotational flow air of main combustion stage axial swirler 34, the gas mixture of premix enters into combustion zone 16 burnings through main combustion stage hybrid chamber 36 again.Main combustion stage axial swirler 34 is the one-level axial swirler.The spray site 38 of main combustion stage air atomizer spray nozzle 33, spray site 39 and spray site 40 distributing position in main combustion stage axial swirler blade path 42 comprises: the spray site 39 of the spray site 38 on the main combustion stage axial swirler inwall 43, main combustion stage axial swirler blade 37 both sides and main combustion stage axial swirler outer wall 44 spray site 40, and respectively as Fig. 4, Fig. 5, shown in Figure 6.Corresponding three kinds of different spray site, main combustion stage fuel oil 41 all is to enter from main combustion stage nozzle entrance 45, and main combustion stage oil circuit collector ring 46 is used for the fuel oil of each spray site of mean allocation, and hole diameter on the collector ring and quantity are regulated according to main combustion stage atomizing situation.In Fig. 4, main combustion stage fuel oil 41 enters on the main combustion stage axial swirler inwall 43 through main combustion stage nozzle entrance 45, fuel oil is evenly distributed in the oil collecting ring at collector ring rear portion through main combustion stage oil circuit collector ring 46, be injected in the blade path 42 through spray site 38 again, wherein Fig. 4 a is the front view of spray site 38 positions, Fig. 4 b is a left view herein, and Fig. 4 c is the cutaway view in Fig. 4 b left view.In Fig. 5, main combustion stage fuel oil 41 enters on the main combustion stage axial swirler inwall 43 through main combustion stage nozzle entrance 45, fuel oil is evenly distributed in the oil collecting ring at collector ring rear portion through main combustion stage oil circuit collector ring 46, oil collecting ring communicates with the blade internal channel, fuel oil is injected in the blade path 42 in spray site 39 through this passage that communicates again, spray site 39 is any one position, blade both sides, wherein Fig. 5 a is the front view of spray site 39 positions, Fig. 5 b is the cutaway view in Fig. 5 a front view, Fig. 5 c is just second-class side figure (3-D view), Fig. 5 d is a left view, and Fig. 5 e is the cutaway view in Fig. 5 d left view.In Fig. 6, main combustion stage fuel oil 41 enters on the main combustion stage axial swirler inwall 43 through main combustion stage nozzle entrance 45, fuel oil is evenly distributed in the oil collecting ring at collector ring rear portion through main combustion stage oil circuit collector ring 46, the oil collecting ring of the oil collecting ring of main combustion stage axial swirler inwall 43 and main combustion stage axial swirler outer wall 44 communicates by the blade internal channel, fuel oil enters into the oil collecting ring of main combustion stage axial swirler outer wall 44 through this passage, be injected in the blade path 42 in spray site 40 again, wherein Fig. 6 a is the front view of spray site 40 positions, Fig. 6 b is the cutaway view in Fig. 6 a front view, Fig. 6 c is the cutaway view among Fig. 6 b, and Fig. 6 d is just second-class side figure (3-D view).Main combustion stage oil circuit collector ring schematic diagram as shown in Figure 7, wherein Fig. 7 a is the collector ring front view, Fig. 7 b is the cutaway view in Fig. 7 a front view; The quantity of main combustion stage axial swirler blade path 42 and main combustion stage fuel nozzle spray site 38, spray site 39 and spray site 40 is decided according to blade quantity.The spray site position of main combustion stage air atomizer spray nozzle 33 can be any one in spray site 38, spray site 39 and the spray site 40, two or three s' combination.Above-mentioned main combustion stage fuel oil spray site enters the mouth to the combustion zone and is 1/4th of head of combustion chamber structure height 48 apart from 49, these spray site are positioned at main combustion stage axial swirler blade path, made full use of the axial distance of axial swirler, removed the distance L si that axial swirler exports to spray site simultaneously, shown in Fig. 8 C, fuel oil shown in the comparison diagram 8A is ejected into the schematic diagram in the transverse jet, spray schematic diagram with the TAPS main combustion stage fuel oil shown in Fig. 8 B, can know that the present invention can shorten the axial length of head of combustion chamber structure greatly, thereby reduce the length and the weight of combustion chamber and engine.
When engine 10 is operated in low power state, the combustion chamber has only pre-combustion grade 24 fuel feeding, main combustion stage 25 have only air through and fuel feeding not, the swirl atomizer 27 of pre-combustion grade makes combustion chambers burn district 16 form diffusion combustion mode, thereby guaranteed reliable stability of engine chamber and starting characteristic, and reduced CO and UHC disposal of pollutants.When engine 10 is operated in high power state, main combustion stage 25 and pre-combustion grade 24 be fuel feeding simultaneously, main combustion stage fuel oil 41 is injected in the main combustion stage axial swirler blade path 42, the eddy flow of main combustion stage axial swirler 34 makes oil gas form the premix and pre-evaporation state, enter into combustion zone 16 burnings again, form the premixed combustion mode, can effectively reduce aero-engine NOx disposal of pollutants, guarantee performances such as high efficiency of combustion and uniform combustor exit Temperature Distribution simultaneously.The main combustion receipts expansion part 35 of main combustion stage 25 and pre-combustion grade 24 and pre-burning receipts expand part 29 and can well prevent nozzle carbon distribution and tempering.
The head of combustion chamber structure is installed and type of attachment: the blade 32 of pre-combustion grade cyclone 28 expands part 29 with receipts and is connected with pre-combustion grade cyclone inwall, forms an integral body.Main combustion stage axial swirler inwall 43 separated into two parts, forwardly divide the fuel hole of leaving oil collecting ring and main combustion stage nozzle entrance 45, again main combustion stage oil circuit collector ring 46 is connected the inside of oil collecting ring, then inwall rear section and forward part are linked into an integrated entity, last whole main combustion stage axial swirler inwall 43 is received expansion part 29 with pre-combustion grade and is linked into an integrated entity.Perforate on main combustion stage axial swirler inwall is convenient to fuel oil and is passed through.Main combustion stage axial swirler blade 37 is received expansion part 35 with main combustion stage axial swirler inwall 43 and main combustion stage respectively and is connected, pre-combustion grade and main combustion stage cyclone have formed an integral body like this, at last fuel nozzle 27 is inserted in the pre-combustion grade cyclone, and is connected with main combustion stage nozzle entrance 45.When engine chamber is installed, after burner inner liner and the casing installation, insert above-mentioned head construction (comprising fuel nozzle, main combustion stage and pre-combustion grade cyclone) from the nozzle mount pad of chamber front end, be connected with head end wall 23, head end wall 23 is connected by a loose collar with head construction 26, avoids the axial and thermal stress radially of combustion chamber.
Claims (9)
1, a kind of integral fuel jet axial swirler pre-mixing preevaporated low pollution combustion chamber, form by head of combustion chamber (26) and burner inner liner, it is characterized in that: the combustion chamber is the monocycle cavity configuration, head of combustion chamber (26) comprises the pre-combustion grade (24) that is positioned at the center and the main combustion stage (25) of outer ring, and main combustion stage (25) includes direct-injection type air atomizer spray nozzle (33) and main combustion stage axial swirler (34); Employing is with the injection and the incorporate technical scheme of main combustion stage axial swirler (34) of main combustion stage fuel oil (41), the main combustion stage fuel oil (41) of direct-injection type air atomizer spray nozzle (33) ejection enters in the main combustion stage axial swirler blade path (42) of main combustion stage axial swirler blade (37), and mix with the rotational flow air of main combustion stage axial swirler (34), main combustion stage axial swirler blade (37) is received expansion part (35) with main combustion stage axial swirler inwall (43) and main combustion stage respectively and is connected, the gas mixture of premix passes through main combustion stage hybrid chamber (36) again and enters into combustion zone (16) burning, realizes that integrated fuel oil sprays the axial swirler scheme.
2, a kind of integral fuel jet axial swirler pre-mixing preevaporated low pollution according to claim 1 combustion chamber, it is characterized in that: first spray site (38) of the direct-injection type air atomizer spray nozzle (33) of main combustion stage (25) is positioned on the main combustion stage axial swirler inwall (43), and spray site quantity is identical with blade quantity.
3, a kind of integral fuel jet axial swirler pre-mixing preevaporated low pollution according to claim 1 combustion chamber, it is characterized in that: second spray site (39) of the direct-injection type air atomizer spray nozzle (33) of main combustion stage (25) is positioned at main combustion stage axial swirler blade (37) optional position, both sides, spray site quantity on each blade can be 1, perhaps 2, perhaps more than 3 and 3.
4, a kind of integral fuel jet axial swirler pre-mixing preevaporated low pollution according to claim 1 combustion chamber, it is characterized in that: the 3rd spray site (40) of the direct-injection type air atomizer spray nozzle (33) of main combustion stage (25) is positioned on the main combustion stage axial swirler outer wall (44), and spray site quantity is identical with blade quantity.
5, according to each described a kind of integral fuel jet axial swirler pre-mixing preevaporated low pollution combustion chamber among the claim 1-4, it is characterized in that: direct-injection type air atomizer spray nozzle (33) position of main combustion stage (25) comprises first spray site (38), in second spray site (39) and the 3rd spray site (40) any one, two or three.
6, a kind of integral fuel jet axial swirler pre-mixing preevaporated low pollution according to claim 1 combustion chamber is characterized in that: main combustion stage fuel oil spray site to the relation between porch, combustion zone distance (49) x and head of combustion chamber structure height (48) y is:
7, a kind of integral fuel jet axial swirler pre-mixing preevaporated low pollution according to claim 1 combustion chamber, it is characterized in that: the tolerance of main combustion stage (25) accounts for 65%～95% of head of combustion chamber tolerance, and the tolerance of pre-combustion grade (24) accounts for 5%～35% of head of combustion chamber tolerance.
8, a kind of integral fuel jet axial swirler pre-mixing preevaporated low pollution according to claim 1 combustion chamber, it is characterized in that: the burning gas consumption all infeeds from head of combustion chamber (26), do not have primary holes on the burner inner liner, have only cooling hole, outer blending hole (21) and interior blending hole (22).
9, a kind of integral fuel jet axial swirler pre-mixing preevaporated low pollution according to claim 1 combustion chamber is characterized in that: main combustion stage is received and is expanded parts (35) to shrink angles (47) adjustable in 0 ° to 180 °.
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2008
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