CN103528094A - Dry-type low-nitrogen combustion device for gas fuel of gas turbine - Google Patents

Dry-type low-nitrogen combustion device for gas fuel of gas turbine Download PDF

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Publication number
CN103528094A
CN103528094A CN201310288860.5A CN201310288860A CN103528094A CN 103528094 A CN103528094 A CN 103528094A CN 201310288860 A CN201310288860 A CN 201310288860A CN 103528094 A CN103528094 A CN 103528094A
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fuel
burner
gas
liner
air
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CN201310288860.5A
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CN103528094B (en
Inventor
李振中
张宏涛
王岳
袁德
徐杨
于宗明
陈晓利
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Liaoning Combustion Engineering Technology Center (co Ltd)
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Liaoning Combustion Engineering Technology Center (co Ltd)
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Abstract

The invention discloses a dry-type low-nitrogen combustion device for gas fuel of a gas turbine. The combustion device comprises a plurality of circular-tube-shaped combustion units which are the same in structure and evenly arrayed in the peripheral direction. Each combustion unit comprises a combustion chamber end cover, a small combustion chamber casing, a fuel nozzle, an exhaust cylinder, a steel flame tube, a plurality of thermal insulation tiles, a top cover, an air guide bushing, a fuel gas guide tube outer shell, an air guide tube, a plurality of flow turbulence rings, a fuel gas guide tube inner shell and a fuel gas outlet. According to the combustion device, when the gas turbine operates, the gas fuel and air are evenly mixed to form lean premixed gas before combustion, so that spontaneous combustion and backfiring which possibly happen in the mixing process are avoided, and accordingly stable low-nitrogen combustion is realized; combustion heating is even in the whole working range of the gas turbine, and therefore flame turbulence is reduced; heat insulation, heat dissipation and combustion noise absorption are enhanced through combustion boundaries.

Description

A kind of gas fuel of gas turbine dry type low nitrogen combustion apparatus
Technical field
The present invention relates to thermodynamics technical field, especially a kind of gas fuel of gas turbine dry type low nitrogen combustion apparatus.
Background technology
Modern generating be take operating on gaseous fuel as main with heavy duty gas turbine, and its burner generally adopts multcan, and a plurality of identical cylindrical shape fuel elements are arranged on the compressor exhaust casing of gas turbine.
Fig. 1 illustrates the example that the gas turbine of generally applying in prior art divides a fuel element of cast dry type low nitrogen burning chamber, the sectional view that Figure 1A is fuel element, and Figure 1B is the structural representation of fuel nozzle group 40.As shown in Figure 1A, when fuel element is worked, the fuel nozzle group 40 communicating with its inside introduced and is assigned to by gaseous fuel from end cover of combustion chamber 1, described fuel nozzle group 40 comprise center fuel nozzle 2 and center fuel nozzle 2 peripheries arrange a circle a plurality of fuel nozzle 3(as shown in Figure 1B); Air enters exhaust casing 10 by external compressor 9, again from the gas conduct pipe cooling dome 6 inflow cooling domes 6 of porous and the circular passage between gas conduct pipe 5, gas conduct pipe 5 is being formed and impacting the cooling rear circular passage flowing between burner inner liner 4 and air conducting lining 7, the space of burner inner liner 4 being washed away to cooling rear flowing in combustion chamber end cap 1, combustion chamber casing 11, burner inner liner top cover 8 and surrounding, wherein, part air flows into burner inner liner 4 via the burner inner liner top cover 8 of porous, and most of air enters center fuel nozzle 2 and fuel nozzle 3; Gaseous fuel and air flow into burner inner liner 4 after center fuel nozzle 2 and the interior mixing of fuel nozzle 3, and in combustion zone, the 13 interior flames of setting up also burn, and the high-temperature fuel gas that burning produces flows to gas conduct pipe 5, is introduced gas outlets 12 output to turbine by gas conduct pipe 5.
Generating is high fuel gas temperature, low pollution, long-life with gas turbine to the requirement of chamber performance, and example is that the F level gas-turbine combustion chamber outlet fuel gas temperature as modern gas turbines power station main force equipment need reach 1400 ℃, nitrogen oxides in effluent concentration < 25ppm(and converts 15% oxygen concentration), maintenance interval > 8000 hours.
With reference to the fuel element shown in figure 1, in order to reach described performance indications, fuel element adopts dry type low nitrogen burning technology, be that gaseous fuel and air are before entering burner inner liner 4 burnings, in center fuel nozzle 2 and fuel nozzle 3, carry out blending, form fuel/air mixture than the poor premix gas lower than stoichiometric ratio, thereby reduce the maximum temperature of combustion zone, suppress the generation of nitrogen oxide.In order to realize the adjusting of combustion chamber load under the state at described poor premix gas low nitrogen burning, adopt the combustion control technology of fuel staging, it is the different range of respective combustion chamber load, adopt corresponding burning mode, for each burning mode, one in center fuel nozzle 2 and fuel nozzle 3 catches fire separately or several associated working.
Fuel element shown in Fig. 1 is in product development and the following problem of discovery in service: (1) center fuel nozzle 2 and fuel nozzle 3 fuels and air blending are even not, in order to keep flameholding, require to enter combustion zone premix gas overall fuel/air mixture than and the rare limit of burning between leave enough allowances (can with reference to figure 7); For strengthening fuel and air blending, the cyclone of center fuel nozzle 2 and fuel nozzle 3 premix gas passages is arranged on air intake one side, away from flame, has slackened flame stabilization mechanism; Fuel is responsive to fuel injection speed (associated with fuel Wobbe index) reaction with the uniformity coefficient of air blending and the disturbance of premixed flow; Fuel and air blending occur in the limited eddy flow flow process of circular passage, there is no other controlling mechanism, flow perturbation and intermittent large, and may there is spontaneous combustion and tempering.Above-mentioned limitation is brought the difficulty of coordinating between discharged nitrous oxides, combustion vibration and noise, makes these indexs be difficult to further reduction, and the difficulty that burning is adjusted and controlled increases, and fuel accommodation is narrow; (2), in the multi-jet configuration mode of fuel nozzle group 40, the distance between center fuel nozzle 2 and the outer rim of fuel nozzle 3 makes nozzle outer rim approach burner inner liner 4, has aggravated the calcination of nozzle flame to burner inner liner 4 internal faces; Center fuel nozzle 2 and peripheral fuel nozzle 3 have different structures, have increased the complexity that product development, burning are adjusted and controlled; (3) multiinjector configuration and combustion control mode make non-homogeneous the arranging of nozzle of catching fire under some burning mode, and burner inner liner 4 is burnt partially by nozzle flame; (4) burner inner liner 4 bears the stress of supporting construction when bearing high temperature, and the life-span is difficult to reach 8000 hours of F level gas turbine requirement; The air velocity that outer wall washes away cooling requirement is high, and requires burner inner liner 4 outer walls to be provided with flow-disturbing fin, and the flow resistance for this reason increasing reduces the efficiency of gas turbine; (5) the cooling air flow resistance causing of gas conduct pipe 5 outer walls impact is large, and in the position that approaches burner inner liner 4 because accelerate to impact cooling being weakened along wall direction flow velocity, can only rely on the thickness of the gas conduct pipe 5 made of thickening cobalt base superalloy to reach life requirements, further the possibility of improving performance is little.
Simultaneously, the development of gas turbine proposes again further requirement to chamber performance, exports fuel gas temperature and reaches 1500-1700 ℃, nitrogen oxides in effluent concentration < 10ppm(and convert 15% oxygen concentration), maintenance interval further extends on 8000 hours bases.The dry type low nitrogen burning chamber of described prior art and the existing problem of combustion control technology will be more sharp-pointed, can not meet the requirement further developing even completely.
Summary of the invention
In order to solve the existing problem of above-mentioned prior art, the present invention proposes a kind of gas fuel of gas turbine dry type low nitrogen combustion apparatus.
A kind of gas fuel of gas turbine dry type low nitrogen combustion apparatus that the present invention proposes comprises along the circumferential evenly distributed identical fuel element of a plurality of structures, described in each, fuel element comprises: end cover of combustion chamber 14, the little casing 41 in combustion chamber, fuel nozzle 15, exhaust casing 10, burner inner liner steel cylinder 16, a plurality of thermal insulation tile 18, top cover 17, air conducting lining 19, gas conduct pipe shell 20, air conduit 21, a plurality of flow-disturbing ring 22, gas conduct pipe inner casing 23, gas outlet 12, wherein:
Described end cover of combustion chamber 14 is positioned at one end of described fuel element, for the entrance as gaseous fuel;
Described gas outlet 12 is positioned at the other end of described fuel element, and communicates with the fuel gas inlet of turbine, for the combustion gas producing after gaseous fuel and air burning is input to described turbine;
Described end cover of combustion chamber 14, the little casing 41 in combustion chamber, air conducting lining 19, gas conduct pipe shell 20 connect successively, and the little casing 41 in described combustion chamber is connected by flange with one end of exhaust casing 10, and described gas conduct pipe shell 20 is connected with the periphery of described gas outlet 12;
Between the little casing 41 of burner inner liner steel cylinder 16 and described combustion chamber of described fuel element inside, be formed with the first circular passage, between described burner inner liner steel cylinder 16 and air conducting lining 19, be formed with the second circular passage, described gas conduct pipe shell 20 and be formed with the 3rd circular passage between the gas conduct pipe inner casing 23 of fuel element inside, above-mentioned three circular passages communicate;
Described a plurality of thermal insulation tile 18 divides row to be lifted on the internal face of burner inner liner steel cylinder 16 successively, together forms burner inner liner with burner inner liner steel cylinder 16;
The outer surface of described fuel nozzle 15 is connected with the inner surface of described burner inner liner near one end of described end cover of combustion chamber 14 by top cover 17;
The other end of described burner inner liner is connected with one end of gas conduct pipe inner casing 23, and the other end of gas conduct pipe inner casing 23 is connected with described gas outlet 12;
A plurality of flow-disturbing rings 22 are fixed on the outer surface of described gas conduct pipe inner casing 23;
Described air conduit 21 one end are fixed on described gas conduct pipe shell 20, and the other end is plugged on flow-disturbing ring 22, and communicate with described the 3rd circular passage;
Between described gas conduct pipe inner casing 23 and described gas conduct pipe shell 20, be welded with a plurality of joint pins with ripple buffer structure;
The other end of described exhaust casing 10 communicates with the outlet of compressor 9, the inner space of described exhaust casing 10 communicates with air conduit 21, the exhaust stream of described compressor 9, through the inside of air conduit 21, the 3rd circular passage, the second circular passage, the first circular passage, fuel nozzle 15, burner inner liner inside and gas conduct pipe inner casing 23, is input to described gas outlet 12.
During the work of described fuel element, gaseous fuel is introduced and is assigned to the fuel channel with the fuel nozzle 15 of array premixed device from end cover of combustion chamber 14, air enters exhaust casing 10 from compressor 9 simultaneously, the flow-disturbing ring 22 flowing into the 3rd circular passage from the air conduit 21 communicating with exhaust casing 10, after cooling to the outside wall surface formation impact of gas conduct pipe inner casing 23, flow to the second circular passage, to the outside wall surface of burner inner liner steel cylinder 16 wash away cooling after, most of air flows into end cover of combustion chamber 14, burner inner liner steel cylinder 16, the space that burner inner liner top cover 17 surrounds is by the air duct by fuel nozzle 15, after fuel nozzle 15 inside and fuel mix, flow into burner inner liner inside, it is inner that a small amount of air flows into burner inner liner via the gap between thermal insulation tile 18 and burner inner liner steel cylinder 16, the mist of fuel and air is set up flame burning in burner inner liner inside, the high-temperature fuel gas that burning produces flows to gas conduct pipe inner casing 23, by gas conduct pipe inner casing 23, introduced gas outlet 12 and enter turbine.
The present invention's low nitrogen burning stably when gas turbine turns round; Homogeneous heating at whole gas turbine working range internal combustion device, can reduce flame disturbance; And combustion boundary can be strengthened absorption heat insulation and to combustion noise.
Accompanying drawing explanation
Fig. 1 be in prior art generally the gas turbine of application divide the structural representation of a fuel element of cast dry type low nitrogen burning chamber.
Fig. 2 is the structural representation of a fuel element of dry type low nitrogen combustion apparatus according to an embodiment of the invention.
Fig. 3 is the burning mode schematic diagram of fuel element according to an embodiment of the invention.
Fig. 4 is according to an embodiment of the invention with the structural representation of the single fuel nozzle of array type premixed device.
Fig. 5 is the structural representation of thermal insulation tile according to an embodiment of the invention.
Fig. 6 is the structural representation of gas conduct pipe and flow-disturbing ring according to an embodiment of the invention.
Fig. 7 is that the overall fuel/air mixture of fuel nozzle-air mixing uniformity, premix gas is than the result of calculation of the relation with the rare limit of burning.
The specific embodiment
For making the object, technical solutions and advantages of the present invention clearer, below in conjunction with specific embodiment, and with reference to accompanying drawing, the present invention is described in more detail.
Gas fuel of gas turbine dry type low nitrogen combustion apparatus proposed by the invention is by forming along the identical tubular fuel element of circumferential evenly distributed a plurality of structures, Fig. 2 is the structural representation of a fuel element of dry type low nitrogen combustion apparatus according to an embodiment of the invention, Fig. 2 A is the sectional view of fuel element, and Fig. 2 B is the structural representation of fuel nozzle 15.As shown in Figure 2 A, described in each, fuel element comprises: end cover of combustion chamber 14, the little casing 41 in combustion chamber, fuel nozzle 15, exhaust casing 10, burner inner liner steel cylinder 16, a plurality of thermal insulation tile 18, top cover 17, air conducting lining 19, gas conduct pipe shell 20, air conduit 21, a plurality of flow-disturbing ring 22, gas conduct pipe inner casing 23, gas outlet 12, wherein:
Described end cover of combustion chamber 14 is positioned at one end of described fuel element, for the entrance as gaseous fuel;
Described gas outlet 12 is positioned at the other end of described fuel element, and communicates with the fuel gas inlet of turbine, for the combustion gas producing after gaseous fuel and air burning is input to described turbine;
Described end cover of combustion chamber 14, the little casing 41 in combustion chamber, air conducting lining 19, gas conduct pipe shell 20 connect successively, and the little casing 41 in described combustion chamber is connected by flange with one end of exhaust casing 10, and described gas conduct pipe shell 20 is connected with the periphery of described gas outlet 12;
Between the little casing 41 of burner inner liner steel cylinder 16 and described combustion chamber of described fuel element inside, be formed with the first circular passage, between described burner inner liner steel cylinder 16 and air conducting lining 19, be formed with the second circular passage, described gas conduct pipe shell 20 and be formed with the 3rd circular passage between the gas conduct pipe inner casing 23 of fuel element inside, above-mentioned three circular passages communicate;
Described a plurality of thermal insulation tile 18 divides row to be lifted on the internal face of burner inner liner steel cylinder 16 successively, together forms burner inner liner with burner inner liner steel cylinder 16;
The outer surface of described fuel nozzle 15 is connected with the inner surface of described burner inner liner near one end of described end cover of combustion chamber 14 by top cover 17;
Wherein, described fuel nozzle 15 comprises fuel channel and air duct, and one end of described fuel channel communicates by pipeline with described end cover of combustion chamber 14, and the other end communicates with the entrance of burner inner liner by array premixed device; The space that one end of described air duct surrounds via described end cover of combustion chamber 14, the little casing 41 in combustion chamber, burner inner liner top cover 17 communicates with the first circular passage, and the other end also communicates with the entrance of burner inner liner by array premixed device;
The other end of described burner inner liner is connected with one end of gas conduct pipe inner casing 23, and the other end of gas conduct pipe inner casing 23 is connected with described gas outlet 12;
A plurality of flow-disturbing rings 22 are fixed on the outer surface of described gas conduct pipe inner casing 23;
Described air conduit 21 one end are fixed on described gas conduct pipe shell 20, and the other end is plugged on flow-disturbing ring 22, and communicate with described the 3rd circular passage;
Between described gas conduct pipe inner casing 23 and described gas conduct pipe shell 20, be welded with a plurality of joint pins with ripple buffer structure;
The other end of described exhaust casing 10 communicates with the outlet of compressor 9, the inner space of described exhaust casing 10 communicates with air conduit 21, the exhaust stream of described compressor 9, through the inside of air conduit 21, the 3rd circular passage, the second circular passage, the first circular passage, fuel nozzle 15, burner inner liner inside and gas conduct pipe inner casing 23, is input to described gas outlet 12.
When the work of described fuel element, gaseous fuel is introduced and is assigned to the fuel channel with the fuel nozzle 15 of array premixed device (not shown) from end cover of combustion chamber 14, air enters exhaust casing 10 from compressor 9 simultaneously, the flow-disturbing ring 22 flowing into the 3rd circular passage from the air conduit 21 communicating with exhaust casing 10, after cooling to the outside wall surface formation impact of gas conduct pipe inner casing 23, flow to the second circular passage, to the outside wall surface of burner inner liner steel cylinder 16 wash away cooling after, most of air flows into end cover of combustion chamber 14, burner inner liner steel cylinder 16, the space that burner inner liner top cover 17 surrounds is by the air duct by fuel nozzle 15, after fuel nozzle 15 inside and fuel mix, flow into burner inner liner inside, it is inner that a small amount of air flows into burner inner liner via the gap between thermal insulation tile 18 and burner inner liner steel cylinder 16, the mist of fuel and air is set up flame burning in burner inner liner inside, the high-temperature fuel gas that burning produces flows to gas conduct pipe inner casing 23, by gas conduct pipe inner casing 23, introduced gas outlet 12 and enter turbine.
As shown in Figure 2 B, described fuel nozzle 15 comprises seven fuel nozzles that structure is identical, described fuel nozzle is all tubular, these seven fuel nozzles are arranged according to the tangent mode boundling of one, center, six, periphery and outer rim, and each fuel nozzle is interior all with array type fuel-air pre-mixing device and a cyclone that is positioned at air flow outlet.These a plurality of fuel nozzles can optionally be opened work according to the condition range of gas turbine.
Fig. 3 is illustrated in the whole working range of gas turbine the burning mode schematic diagram of a fuel element of dry type low nitrogen combustion apparatus according to an embodiment of the invention.When gas turbine starts to the condition range of unloaded full rotating speed, seven fuel nozzles are all worked, and each fuel nozzle is all in the identical diffusion combustion pattern of fuel duty, and this burning mode is labeled as D7, as shown in Figure 3A; When the unloaded full rotating speed of gas turbine is when exporting the condition range of 15% shaft work, seven fuel nozzles are all in the identical diffusion combustion pattern of fuel duty, three identical premixed combustion mode of peripheral fuel nozzle additional fuel supply that wherein distribute along even circumferential, this burning mode is labeled as D7+PM3, as shown in Figure 3 B; When the condition range Shi, center fuel nozzle of gas turbine output 15% to 40% shaft work is in diffusion combustion pattern, six peripheral fuel nozzles are in the identical premixed combustion mode of fuel duty, and this fuel mode is labeled as PM3+PM3 '+D1, as shown in Figure 3 C; When gas turbine is exported the condition range of 40% to 100% shaft work, seven fuel nozzles are all in the identical premixed combustion mode of fuel duty, and this combustion mode is labeled as PM3+PM3 '+PM1, as shown in Figure 3 D.
Mode is controlled in the arrangement mode of above-mentioned seven nozzles and burning thereof makes in whole gas turbine working range burner inner liner by homogeneous heating.
Fig. 4 is according to an embodiment of the invention with the structural representation of the single fuel nozzle of array type premixed device.As shown in Figure 4, described single fuel nozzle comprises: nozzle casing 31, centerbody 28, some row's fuel eject blades 34, fuel orifice 32, are arranged swirl vane 27, premixed fuel passage 30, diffused fuel passage 29, diffused fuel spray-hole 25, blow air duct 33 clearly, blown air jet hole 26 clearly, wherein:
Described centerbody 28 is positioned at the center of described fuel nozzle, nozzle casing 31 is positioned at the periphery of centerbody 28, between described nozzle casing 31 and centerbody 28, be formed with circular passage, in described circular passage, be disposed with vertically the some row's fuel eject blades 34 and the solid swirl vane 27 of a row that are connected with centerbody 28, other spaces of described circular passage form the air duct of described fuel nozzle, and described air duct communicates with burner inner liner inside;
Described fuel eject blade 34 is provided with inner passage, and the surface of described fuel eject blade 34 is provided with fuel orifice 32;
The end of described centerbody 28 is provided with the diffused fuel spray-hole 25 communicating with burner inner liner inside and blows clearly air jet hole 26;
In described centerbody 28, be radially provided with side by side premixed fuel passage 30, diffused fuel passage 29 and blow clearly air duct 33;
Described premixed fuel passage 30 communicates with the inner passage of fuel eject blade 34, for by gaseous fuel via being positioned at the fuel orifice 32 on fuel eject blade 34 surfaces, described air duct enters burner inner liner inside;
Described diffused fuel passage 29 sprays into burner inner liner inside by described diffused fuel spray-hole 25 by fuel;
The described air duct 33 that blows clearly will be blown clearly air and be sprayed into burner inner liner inside by the described air jet hole 26 that blows clearly, to protect centerbody, avoid high temperature to burn.
During work, it is inner that air flows into burner inner liner by the circular passage between nozzle casing 31 and centerbody 28.Under premixed combustion mode of operation, gaseous fuel flows into the inner passage of fuel eject blade 34 by the premixed fuel passage 30 in nozzle center's body 28, and flow into air duct from its surperficial fuel orifice 32, after mixing with air, enter burner inner liner inside and burn.Under diffusion combustion mode of operation, the diffused fuel spray-hole 25 of gaseous fuel by diffused fuel passage 29,Cong nozzle center body 28 ends directly sprays into that burner inner liner is inner to be contacted, burn with air.Blow clearly air by blowing clearly air duct 33, from blowing clearly air jet hole 26, spray into burner inner liner inside.
Fig. 5 is the structural representation of thermal insulation tile according to an embodiment of the invention, the perspective view that Fig. 5 A is thermal insulation tile, the partial sectional view that Fig. 5 B is thermal insulation tile.As shown in Figure 5, every block of thermal insulation tile 18 is provided with several in a side that deviates from flame knot 36 and some turbulence columns 37 is installed, and described installation knot 36 coordinates with floating ring 38 mounted thereto, thermal insulation tile 18 is installed on flexibly to the internal face place of burner inner liner steel cylinder 16.Thermal insulation tile 18 is coated with high-temperaure coating 35 on the side surface of flame.During work, high-temperature fuel gas directly washes away high-temperaure coating 35, the Cryogenic air in burner inner liner steel cylinder 16 outsides flows into the circumferential weld between thermal insulation tile 18 and burner inner liner steel cylinder 16 from the gap of knot 36 is installed, and after turbulence columns 37 arrays, flows into burner inner liner inner from the gap location between thermal insulation tile.
Fig. 6 is the structural representation of gas conduct pipe according to an embodiment of the invention, and Fig. 6 A is perspective view, and Fig. 6 B is partial sectional view.Described gas conduct pipe shell 20 and described gas conduct pipe Inner shell 23 have formed gas conduct pipe, and several air conduits 21 are installed on gas conduct pipe shell 20, are plugged in respectively on the some row's flow-disturbing rings 22 that are arranged on gas conduct pipe Inner shell 23 outer surfaces.Air in exhaust casing 10 flows in the circular passage between flow-disturbing ring 22 and Inner shell 23 from the inside of air conduit 21, with cooling gas conduct pipe Inner shell 23, then flows in the 3rd circular passage between gas conduct pipe inner casing 23 and shell 20.
With respect to prior art, there is following advantage in the present invention:
(1) fuel nozzle in the present invention is with array type premixed device, with this, can realize: mixture homogeneity (being the root mean square calculation result of nozzle premix gas channel outlet section concentration) doubles than the nozzle of the combustion chamber of the prior art shown in Fig. 12 and 3, enter combustion zone premix gas overall fuel/air mixture than and the rare limit of burning between allowance also can reduce approximately 1 times, specifically can be with reference to shown in figure 7, in Fig. 7, dashed curve is nozzle 2 and the 3 obtained fuel air ratios of the combustion chamber of prior art, block curve is the obtained fuel air ratio of fuel nozzle 15 of the present invention, mix and do not need eddy flow, thereby cyclone can be arranged on to jet expansion near a side of flame, thereby strengthened flame stabilization mechanism, array has suppressed the initial disturbance of inlet air flow, having eliminated large scale flows, exit flow perturbation amplitude is than the nozzle of the combustion chamber of the prior art shown in Fig. 12 and an order of magnitude of 3 declines, and mixture homogeneity and premixed flow disturbance are no longer responsive to fuel injection speed, in the passage of array premix gas, do not possess and catch fire and flame stabilization condition, thereby avoided the generation of spontaneous combustion and tempering,
(2) multiinjector of fuel nozzle 15 of the present invention is configured in the space that has maximally utilised geometrically burner inner liner cross section circle, under the prerequisite that keeps the cross-section area of nozzle, increase the distance between nozzle edge and burner inner liner, thereby alleviated the calcination to burner inner liner; And identical nozzle has reduced product development, burning is adjusted and the complexity of controlling; Other 7 nozzle arrangement coordinate method for controlling combustion, and the nozzle catching fire under each burning mode is uniformly distributed, thus the phenomenon of having avoided burner inner liner partially to burn;
(3) burner inner liner in the present invention adopts the structure of steel cylinder liner thermal insulation tile, under the condition of 1400 ℃ of outlet fuel gas temperatures, the temperature of burner inner liner load steel cylinder is below 800 ℃, cancel outside wall surface air and washed away cooling flow-disturbing fin, guarantee the burner inner liner life-span of F level gas turbine requirement, reduced the air flow resistance of combustion chamber;
(4) gas conduct pipe in the present invention adopts the duplex shell structure being connected by ripple post, has increased intensity; Between inside and outside shell, along air-flow direction, the flow-disturbing ring that multi-group has air conduit is installed, destroy the thermal boundary layer of inner casing outside wall surface, air introducing of the entrance on shell from air conduit, impact inner casing outside wall surface, avoided the cooling effect that slackens of adherent air-flow impact; The requirement of impact cooling-air flow velocity reduces, thereby reduces combustion chamber air flow resistance; The invention enables the potentiality that there is further lifting in the heat resistance of gas conduct pipe and life-span.
Above-described specific embodiment; object of the present invention, technical scheme and beneficial effect are further described; institute is understood that; the foregoing is only specific embodiments of the invention; be not limited to the present invention; within the spirit and principles in the present invention all, any modification of making, be equal to replacement, improvement etc., within all should being included in protection scope of the present invention.

Claims (10)

1. a gas fuel of gas turbine dry type low nitrogen combustion apparatus, is characterized in that, this burner comprises along the identical tubular fuel element of circumferential evenly distributed a plurality of structures; Described in each, fuel element comprises: end cover of combustion chamber (14), the little casing in combustion chamber (41), fuel nozzle (15), exhaust casing (10), burner inner liner steel cylinder (16), a plurality of thermal insulation tile (18), top cover (17), air conducting lining (19), gas conduct pipe shell (20), air conduit (21), a plurality of flow-disturbing ring (22), gas conduct pipe inner casing (23), gas outlet (12), wherein:
Described end cover of combustion chamber (14) is positioned at one end of described fuel element, for the entrance as gaseous fuel;
Described gas outlet (12) is positioned at the other end of described fuel element, and communicates with the fuel gas inlet of turbine, for the combustion gas producing after gaseous fuel and air burning is input to described turbine;
Described end cover of combustion chamber (14), the little casing in combustion chamber (41), air conducting lining (19), gas conduct pipe shell (20) connect successively, and the little casing in described combustion chamber (41) is connected by flange with one end of exhaust casing (10), described gas conduct pipe shell (20) is connected with the periphery of described gas outlet (12);
Be positioned between the little casing of burner inner liner steel cylinder (16) and described combustion chamber (41) of described fuel element inside and be formed with the first circular passage, between described burner inner liner steel cylinder (16) and air conducting lining (19), be formed with the second circular passage, described gas conduct pipe shell (20) and be positioned between the gas conduct pipe inner casing (23) of fuel element inside and be formed with the 3rd circular passage, above-mentioned three circular passages communicate;
Described a plurality of thermal insulation tile (18) divides row to be lifted on the internal face of burner inner liner steel cylinder (16) successively, together forms burner inner liner with burner inner liner steel cylinder (16);
The outer surface of described fuel nozzle (15) is connected with the inner surface of described burner inner liner near one end of described end cover of combustion chamber (14) by top cover (17);
The other end of described burner inner liner is connected with the one end of gas conduct pipe inner casing (23), and the other end of gas conduct pipe inner casing (23) is connected with described gas outlet (12);
A plurality of flow-disturbing rings (22) are fixed on the outer surface of described gas conduct pipe inner casing (23);
It is upper that described air conduit (21) one end is fixed in described gas conduct pipe shell (20), and it is upper that the other end is plugged in flow-disturbing ring (22), and communicate with described the 3rd circular passage;
Between described gas conduct pipe inner casing (23) and described gas conduct pipe shell (20), be welded with a plurality of joint pins with ripple buffer structure;
The other end of described exhaust casing (10) communicates with the outlet of compressor (9), the inner space of described exhaust casing (10) communicates with air conduit (21), the exhaust stream of described compressor (9), through the inside of air conduit (21), the 3rd circular passage, the second circular passage, the first circular passage, fuel nozzle (15), burner inner liner inside and gas conduct pipe inner casing (23), is input to described gas outlet (12);
During the work of described fuel element, gaseous fuel is introduced and is assigned to the fuel channel with the fuel nozzle (15) of array premixed device from end cover of combustion chamber (14), air enters exhaust casing (10) from compressor (9) simultaneously, from the air conduit (21) communicating with exhaust casing (10), flow into the flow-disturbing ring (22) the 3rd circular passage, after cooling to the outside wall surface formation impact of gas conduct pipe inner casing (23), flow to the second circular passage, to the outside wall surface of burner inner liner steel cylinder (16) wash away cooling after, most of air flows into end cover of combustion chamber (14), burner inner liner steel cylinder (16), the space that burner inner liner top cover (17) surrounds is by the air duct by fuel nozzle (15), after fuel nozzle (15) inside and fuel mix, flow into burner inner liner inside, it is inner that a small amount of air flows into burner inner liner via the gap between thermal insulation tile (18) and burner inner liner steel cylinder (16), the mist of fuel and air is set up flame burning in burner inner liner inside, the high-temperature fuel gas that burning produces flows to gas conduct pipe inner casing (23), by gas conduct pipe inner casing (23), introduced gas outlet (12) and enter turbine.
2. burner according to claim 1, it is characterized in that, described fuel nozzle (15) comprises fuel channel and air duct, and one end of described fuel channel communicates by pipeline with described end cover of combustion chamber (14), and the other end communicates with the entrance of burner inner liner by array premixed device; The space that one end of described air duct surrounds via described end cover of combustion chamber (14), the little casing in combustion chamber (41), burner inner liner top cover (17) communicates with the first circular passage, and the other end also communicates with the entrance of burner inner liner by array premixed device.
3. burner according to claim 1, it is characterized in that, described fuel nozzle (15) comprises seven fuel nozzles that structure is identical, and described fuel nozzle is all tubular, and these seven fuel nozzles are arranged according to the tangent mode boundling of one, center, six, periphery and outer rim.
4. burner according to claim 3, it is characterized in that, each of the fuel nozzle that described seven structures are identical comprises: nozzle casing (31), centerbody (28), some row's fuel eject blades (34), fuel orifice (32), are arranged swirl vane (27), premixed fuel passage (30), diffused fuel passage (29), diffused fuel spray-hole (25), blow air duct (33) clearly, blown air jet hole (26) clearly, wherein:
Described centerbody (28) is positioned at the center of described fuel nozzle, nozzle casing (31) is positioned at the periphery of centerbody (28), between described nozzle casing (31) and centerbody (28), be formed with circular passage, in described circular passage, be disposed with vertically the some row's fuel eject blades (34) and the solid swirl vane (27) of a row that are connected with centerbody (28), other spaces of described circular passage form the air duct of described fuel nozzle, and described air duct communicates with burner inner liner inside;
Described fuel eject blade (34) is provided with inner passage, and the surface of described fuel eject blade (34) is provided with fuel orifice (32);
The end of described centerbody (28) is provided with the diffused fuel spray-hole (25) communicating with burner inner liner inside and blows clearly air jet hole (26);
In described centerbody (28), be radially provided with side by side premixed fuel passage (30), diffused fuel passage (29) and blow clearly air duct (33);
Described premixed fuel passage (30) communicates with the inner passage of fuel eject blade (34), for gaseous fuel is entered to burner inner liner inside via the fuel orifice (32), the described air duct that are positioned at fuel eject blade (34) surface;
Described diffused fuel passage (29) sprays into burner inner liner inside by described diffused fuel spray-hole (25) by fuel;
The described air duct (33) that blows clearly will be blown clearly air and be sprayed into burner inner liner inside by the described air jet hole (26) that blows clearly, to protect centerbody, avoid high temperature to burn.
5. burner according to claim 4, is characterized in that, when each fuel nozzle of the fuel nozzle that described seven structures are identical is worked, it is inner that air flows into burner inner liner by the circular passage between nozzle casing (31) and centerbody (28); Under premixed combustion mode of operation, gaseous fuel flows into the inner passage of fuel eject blade (34) by the premixed fuel passage (30) in nozzle center's body (28), and flow into air duct from its surperficial fuel orifice (32), after mixing with air, enter burner inner liner inside and burn; Under diffusion combustion mode of operation, the diffused fuel spray-hole (25) of gaseous fuel by diffused fuel passage (29) ,Cong nozzle center body (28) end directly sprays into that burner inner liner is inner to be contacted, burn with air; Blow clearly air by blowing clearly air duct (33), from blowing clearly air jet hole (26), spray into burner inner liner inside.
6. burner according to claim 3, is characterized in that, the identical fuel nozzle of described seven structures is optionally opened work according to the condition range of gas turbine:
When gas turbine starts to the condition range of unloaded full rotating speed, seven fuel nozzles are all worked, and each fuel nozzle is all in the identical diffusion combustion pattern of fuel duty;
When the unloaded full rotating speed of gas turbine is when exporting the condition range of 15% shaft work, seven fuel nozzles are all in the identical diffusion combustion pattern of fuel duty, three identical premixed combustion mode of peripheral fuel nozzle additional fuel supply that wherein distribute along even circumferential;
When the condition range Shi, center fuel nozzle of gas turbine output 15% to 40% shaft work is in diffusion combustion pattern, six peripheral fuel nozzles are in the identical premixed combustion mode of fuel duty;
When gas turbine is exported the condition range of 40% to 100% shaft work, seven fuel nozzles are all in the identical premixed combustion mode of fuel duty.
7. burner according to claim 1, it is characterized in that, described thermal insulation tile (18) is provided with several in a side that deviates from flame knot (36) and some turbulence columns (37) is installed, described installation knot (36) coordinates with floating ring (38) mounted thereto, thermal insulation tile (18) is installed on flexibly to the internal face place of burner inner liner steel cylinder (16); Thermal insulation tile (18) is coated with high-temperaure coating (35) on the side surface of flame.
8. burner according to claim 7, it is characterized in that, during described thermal insulation tile work, high-temperature fuel gas directly washes away high-temperaure coating (35), the Cryogenic air in burner inner liner steel cylinder (16) outside flows into the circumferential weld between thermal insulation tile (18) and burner inner liner steel cylinder (16) from the gap of knot (36) is installed, after turbulence columns (37) array, from the gap location between thermal insulation tile, flow into burner inner liner inner.
9. burner according to claim 1, is characterized in that, described gas conduct pipe shell (20) and described gas conduct pipe Inner shell (23) have formed gas conduct pipe.
10. burner according to claim 9, it is characterized in that, air during described gas conduct pipe work in exhaust casing (10) flows in the circular passage between flow-disturbing ring (22) and Inner shell (23) from the inside of air conduit (21), with cooling gas conduct pipe Inner shell (23), then flow in the 3rd circular passage between gas conduct pipe inner casing (23) and shell (20).
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