CN101285591B - Integral fuel jet radial swirler pre-mixing preevaporated low pollution combustion-chamber - Google Patents

Integral fuel jet radial swirler pre-mixing preevaporated low pollution combustion-chamber Download PDF

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CN101285591B
CN101285591B CN2008101046844A CN200810104684A CN101285591B CN 101285591 B CN101285591 B CN 101285591B CN 2008101046844 A CN2008101046844 A CN 2008101046844A CN 200810104684 A CN200810104684 A CN 200810104684A CN 101285591 B CN101285591 B CN 101285591B
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main combustion
combustion stage
combustion
radial swirler
stage
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CN101285591A (en
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彭云晖
许全宏
张驰
林宇震
刘高恩
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Beihang University
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Beihang University
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Abstract

The invention discloses a combustion cavity for an integral fuel oil ejecting radial hydrocyclone with functions of premixing, pre-evaporation and low pollution. The combustion cavity has a single ring cavity structure, and consists of a combustion cavity head and a flame tube, wherein the combustion cavity head comprises a precombustion stage positioned at the center and a main combustion stage positioned at the peripheral. The main combustion stage comprises a direct jet type air atomizer spray nozzle and a main combustion stage radial hydrocyclone. The jetting of the main combustion stage fuel oil and the main combustion stage radial hydrocyclone are integrated. The main combustion stage fuel oil ejected by the direct jet type air atomizer spray nozzle enters into a main combustion stage radial hydrocyclone vane channel of a main combustion stage radial hydrocyclone vane, and the fuel oil is mixed with the rotary flow air of the main combustion stage radial hydrocyclone. A premixed oil-gas mixture enters into a combustion zone through a main combustion stage mixing cavity to be combusted. The combustion mode can effectively reduce pollutant emission in the combustion cavity and reduce the length of the combustion cavity. The combustion cavity is mainly used for an aerial engine combustion cavity, and also can be used for the combustion cavities of industrial gas turbines and ship gas turbines so as to reduce the pollutant discharged into atmosphere.

Description

A kind of integral fuel jet radial swirler pre-mixing preevaporated low pollution combustion chamber
Technical field
The present invention relates to a kind of low pollution emission combustion chamber, particularly a kind of integral fuel jet radial swirler pre-mixing preevaporated low pollution combustion chamber.
Background technology
The main development trend in 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 be fuel feeding respectively, realizes the subregion combustion system.According to this thinking, GE company has applied for several United States Patent (USP)s.Application number is respectively the main combustion stage scheme that 6389815,6354072,0178732 and 6381964 United States Patent (USP) proposes: a certain position after the main combustion stage fuel oil is injected to the radial swirler rear portion and turns round forms the premix and pre-evaporation gas mixture.From the accompanying drawing of these patents as can be known, the fuel oil spray site approximately is half of head of combustion chamber structure height to porch, combustion zone distance, 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.At application number is to have this problem in 6453660 United States Patent (USP)s equally, the fuel oil spray site is 1/3rd of a head of combustion chamber structure height approximately to porch, combustion zone distance, and the main combustion stage fuel injection system is very complicated, causes the head of combustion chamber structure very complicated.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 radial swirler outlet, and this segment distance has increased the head of combustion chamber axial length.
Summary of the invention
The technical problem to be solved in the present invention is: overcome above-mentioned the deficiencies in the prior art, adopt integrated fuel oil injection/radial swirler scheme, mobile by the gas mixture in fuel injection mode in the radial swirler blade path and the radial swirler passage turning round of radial swirler outlet, 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, can effectively reduce the combustion chamber disposal of pollutants simultaneously
The technical solution adopted for the present invention to solve the technical problems is: a kind of integral fuel jet radial 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, and 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; Main combustion stage 25 includes direct-injection type air atomizer spray nozzle 33 and main combustion stage radial swirler 34 again; Employing is integrated with the injection and the main combustion stage radial 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 ejections enters in the main combustion stage radial swirler blade path 42 of main combustion stage radial swirler blade 37, and mix with the rotational flow air of main combustion stage radial swirler 34, the gas mixture of premix enters into combustion zone 16 burnings through main combustion stage hybrid chamber 36 again, realizes that integrated fuel oil sprays the radial swirler scheme.
Described main combustion stage 25 direct-injection type air atomizer spray nozzles 33 first spray site 38 are positioned on the main combustion stage radial swirler left side wall 43, and spray site quantity is identical with blade quantity.
Described main combustion stage 25 direct-injection type air atomizer spray nozzles 33 second spray site 39 are positioned at optional position, main combustion stage radial swirler blade 37 both sides, and the spray site quantity on each blade is 1, and is perhaps 2, perhaps a plurality of.
Described main combustion stage 25 direct-injection type air atomizer spray nozzles 33 the 3rd spray site 40 is positioned on the main combustion stage radial swirler right side wall 44, and spray site quantity is identical with blade quantity.
Described main combustion stage 25 direct-injection type air atomizer spray nozzles 33 positions comprise any one in first spray site, 38, the second spray site 39 and the 3rd 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: x ≤ 1 5 y .
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.
Also include on the described main combustion stage (25) to receive and expand part (35), it is adjustable in 0 ° to 180 ° that 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 radial swirler passage forms the premix and pre-evaporation gas mixture and enters into the combustion zone and burn under the effect of cyclone 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 TAPS main combustion stage radial swirler 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, 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/radial swirler scheme, fuel oil injection and radial swirler are integrated, under identical radial swirler intake condition, length when reaching identical degree of mixing is L1+L, wherein L1 is not more than Ls, has not only removed cyclone and has exported to the distance L si of spray site, but also made full use of the length L s of cyclone, thereby shortened the length of head of combustion chamber greatly, reduced the length and the weight of combustion chamber.
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 radial swirler passage, when reaching identical degree of mixing and evaporativity, the distance that needs shortens greatly, has reduced the length of combustion chamber.
2. the gas mixture in the main combustion stage radial swirler of the present invention, because turning round of radial swirler downstream is mobile, when reaching identical degree of mixing and evaporativity, the distance that needs further shortens, thereby further reduces the length of combustion chamber.
3. 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.
4. 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 and Fig. 4 c are just second-class side figure (3-D 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 the cutaway view in Fig. 5 b front view, and Fig. 5 d is just second-class side figure (3-D 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 a cutaway view in the front view for Fig. 6 a, and Fig. 6 c is just second-class side figure (3-D view);
Fig. 7 is a main combustion stage oil circuit collector ring schematic diagram; 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 radial swirlers, 35 main combustion stages are received and are expanded part, 36 main combustion stage hybrid chambers, 37 main combustion stage radial swirler blades, 38 spray site, be positioned on the main combustion stage radial swirler left side wall, 39 spray site are positioned at arbitrary position, main combustion stage radial swirler blade both sides, 40 spray site, be positioned on the main combustion stage radial swirler right side wall, 41 main combustion stage fuel oils, 42 main combustion stage radial swirler blade paths, 43 main combustion stage radial swirler left side walls, 44 main combustion stage radial swirler right side 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, therefore all burning gas consumptions 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.Receive expansion part 29 and formed pre-combustion grade hybrid chamber 30.Central nozzle 27 adopts swirl atomizers, and the pre-combustion grade swirl atomizer fuel oil 31 of swirl atomizer ejection burns with the combustion zone that enters into the burning 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 radial 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 radial swirler blade path 42 of main combustion stage radial swirler blade 37, and mix with the rotational flow air of main combustion stage radial swirler 34, the gas mixture of premix enters into the combustion zone through main combustion stage hybrid chamber 36 again and burns.Main combustion stage radial swirler 34 is the one-level radial swirler.The spray site 38 of main combustion stage air atomizer spray nozzle 33, spray site 39 and spray site 40 distribute bits in main combustion stage radial swirler blade path 42 is equipped with three: the spray site 39 of the spray site 38 on the main combustion stage radial swirler left side wall 43, main combustion stage radial swirler blade 37 both sides and main combustion stage radial swirler right side wall 44 spray site 40, and respectively as Fig. 4, Fig. 5, shown in Figure 6.Corresponding to three kinds of different spray site 38, spray site 39 and spray site 40, main combustion stage fuel oil 41 inlets all are to enter from main combustion stage nozzle entrance 45, 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 radial swirler left side wall 43 through main combustion stage fuel filler 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 main combustion stage radial swirler blade path 42 through spray site 38 again, wherein Fig. 4 a is the front view of spray site 38 positions, and Fig. 4 b and Fig. 4 c are just second-class side figure (3-D view).In Fig. 5, main combustion stage fuel oil 41 enters on the main combustion stage radial swirler left side wall 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, and spray site 39 is any one position, blade both sides; Wherein Fig. 5 a is the front view of spray site 39 positions, and Fig. 5 b is the cutaway view in Fig. 5 a front view, and Fig. 5 c is the cutaway view in Fig. 5 b front view, and Fig. 5 d is just second-class side figure (3-D view).In Fig. 6, main combustion stage fuel oil 41 enters on the main combustion stage radial swirler left side wall 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 radial swirler left side wall 43 and main combustion stage radial swirler right side wall 44 communicates by the blade internal channel, fuel oil enters into the oil collecting ring of main combustion stage radial swirler right side 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 a cutaway view in the front view for Fig. 6 a, and Fig. 6 c is just second-class side figure (3-D view).Wherein main combustion stage oil circuit collector ring schematic diagram as shown in Figure 7, 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 radial 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 1/5th of head of combustion chamber structure height 48 apart from 49, these spray site are positioned at main combustion stage radial swirler blade path, removed the distance L si that radial swirler exports to spray site, 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, simultaneously because main combustion stage radial swirler downstream is turned round mobile, 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.
During low power states such as engine 10 startings or slow train, pre-combustion grade 24 fuel feeding of combuster, 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.Engine 10 is operated in when high power state such as taking off or climbing, main combustion stage 25 and pre-combustion grade 24 be fuel feeding simultaneously, and the fuel oil 41 of main combustion stage direct-injection type air atomizer spray nozzle 33 enters in the main combustion stage radial swirler blade path 42, the eddy flow of main combustion stage radial 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.And the main combustion stage of main combustion stage 25 and pre-combustion grade 24 is received expansion part 35 and pre-combustion grade receipts expansion part 29 can well prevent nozzle carbon distribution and tempering.
Combustion chamber installation and type of attachment are as follows: the blade 32 of pre-combustion grade cyclone 28 expands part 29 with receipts and pre-combustion grade cyclone inwall links into an integrated entity.Main combustion stage radial swirler left side wall 43 separated into two parts, the oilhole of left-hand component opener oil ring and main combustion stage nozzle entrance 45, again collector ring 46 is connected oil collecting ring inside, then the left side wall left side, right-hand component are linked into an integrated entity, last whole main combustion stage radial swirler left side wall 43 is received expansion part 29 with pre-combustion grade and is linked into an integrated entity.Perforate on the main combustion stage radial swirler left side wall is convenient to fuel oil and is passed through.Main combustion stage radial swirler blade 37 is received expansion part 35 with main combustion stage radial swirler left side wall 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, the above-mentioned head construction of nozzle mount pad insertion from chamber front end is 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. integral fuel jet radial 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, and 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; Main combustion stage (25) includes direct-injection type air atomizer spray nozzle (33) and main combustion stage radial swirler (34); Employing is integrated with the injection and the main combustion stage radial 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 radial swirler blade path (42) of main combustion stage radial swirler blade (37), and mix with the rotational flow air of main combustion stage radial swirler (34), 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 radial swirler scheme.
2. a kind of integral fuel jet radial swirler pre-mixing preevaporated low pollution according to claim 1 combustion chamber, it is characterized in that: main combustion stage (25) direct-injection type air atomizer spray nozzle (33) first spray site (38) are positioned on the main combustion stage radial swirler left side wall (43), and the quantity of first spray site (38) is identical with blade quantity.
3. a kind of integral fuel jet radial swirler pre-mixing preevaporated low pollution according to claim 1 combustion chamber, it is characterized in that: main combustion stage (25) direct-injection type air atomizer spray nozzle (33) second spray site (39) are positioned at main combustion stage radial swirler blade (37) optional position, both sides, spray site quantity on each blade is 1, perhaps 2, perhaps a plurality of.
4. a kind of integral fuel jet radial swirler pre-mixing preevaporated low pollution according to claim 1 combustion chamber, it is characterized in that: main combustion stage (25) direct-injection type air atomizer spray nozzle (33) the 3rd spray site (40) is positioned on the main combustion stage radial swirler right side wall (44), and the quantity of the 3rd spray site (40) is identical with blade quantity.
5. according to each described a kind of integral fuel jet radial swirler pre-mixing preevaporated low pollution combustion chamber among the claim 1-4, it is characterized in that: main combustion stage (25) direct-injection type air atomizer spray nozzle (33) position comprises first spray site (38), in second spray site (39) and the 3rd spray site (40) any one, two or three s' combination.
6. a kind of integral fuel jet radial 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 radial 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%.
8. a kind of integral fuel jet radial 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 radial swirler pre-mixing preevaporated low pollution according to claim 1 combustion chamber, it is characterized in that: also include on the main combustion stage (25) to receive and expand part (35), it is adjustable in 0 ° to 180 ° that main combustion stage is received expansion part (35) contraction angle (47).
CN2008101046844A 2008-04-22 2008-04-22 Integral fuel jet radial swirler pre-mixing preevaporated low pollution combustion-chamber Expired - Fee Related CN101285591B (en)

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CN102980204A (en) * 2012-11-27 2013-03-20 哈尔滨工程大学 Fuel-atomizing integrated igniter
CN107023855A (en) * 2017-05-25 2017-08-08 上海泛智能源装备有限公司 A kind of gas turbine
CN108679643B (en) * 2018-05-24 2020-06-02 中国科学院工程热物理研究所 Foaming air atomizing nozzle for burning high-density fuel oil
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