CN103528094B - 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 PDFInfo
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- CN103528094B CN103528094B CN201310288860.5A CN201310288860A CN103528094B CN 103528094 B CN103528094 B CN 103528094B CN 201310288860 A CN201310288860 A CN 201310288860A CN 103528094 B CN103528094 B CN 103528094B
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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
Technical field
The present invention relates to Thermodynamic techniques field, especially a kind of gas fuel of gas turbine dry type low nitrogen combustion apparatus.
Background technology
Modern generating heavy duty gas turbine is based on operating on gaseous fuel, and its burner generally adopts multcan, and namely multiple identical cylindrical combustion cellular installation is on the compressor exhaust casing of gas turbine.
Fig. 1 illustrates that the gas turbine generally applied in prior art divides the example of a fuel element of cast dry type low nitrogen burning room, and Figure 1A is the sectional view of fuel element, and Figure 1B is the structural representation of fuel nozzle group 40.As shown in Figure 1A, when fuel element works, gaseous fuel is introduced from end cover of combustion chamber 1 and is assigned to the fuel nozzle group 40 communicated with its inside, and described fuel nozzle group 40 comprises center fuel nozzle 2 and arranges the multiple fuel nozzle 3(enclosed as shown in Figure 1B at center fuel nozzle 2 periphery); Air enters exhaust casing 10 by external compressor 9, the circular passage between cooling dome 6 and gas conduct pipe 5 is flowed into again from the gas conduct pipe cooling dome 6 of porous, the circular passage between burner inner liner 4 and air conducting lining 7 is flowed to after impinging cooling is formed to gas conduct pipe 5, the space that flowing in combustion chamber end cap 1, combustion chamber casing 11, burner inner liner top cover 8 surround after burner inner liner 4 being washed away to cooling, wherein, partial 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; Flow into burner inner liner 4 after gaseous fuel and air mix in center fuel nozzle 2 and fuel nozzle 3, set up flame and burn in combustion zone 13, the high-temperature fuel gas that burning produces flows to gas conduct pipe 5, is introduced gas outlet 12 output to turbine by gas conduct pipe 5.
The requirement of generating gas turbine to chamber performance is high fuel gas temperature, low stain, long-life, example be need reach 1400 DEG C as the F level gas-turbine combustion chamber outlet gas temperature of modern gas turbines power station main force equipment, nitrogen oxides in effluent concentration < 25ppm(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-NO_x combustion technology, namely gaseous fuel and air are before entering burner inner liner 4 and burning, blending is carried out in center fuel nozzle 2 and fuel nozzle 3, form fuel/air mixture than the poor premix gas lower than stoichiometric ratio, thus reduce the maximum temperature of combustion zone, suppress the generation of nitrogen oxide.In order to realize the adjustment of combustion chamber load under the state of described poor premix gas low nitrogen burning, adopt the combustion control technology of fuel staging, the i.e. different range of respective combustion chamber load, adopt mode of burning accordingly, 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 finds following problem in product development with in running: (1) center fuel nozzle 2 and fuel nozzle 3 fuel and air blending even not, in order to keep flameholding, the global fuel/air ratio and burning requiring to enter the premix gas of combustion zone to leave enough allowance (can with reference to figure 7) between rare limit; For strengthening fuel and air blending, the cyclone of center fuel nozzle 2 and fuel nozzle 3 premix gas passage is arranged on air intake side, away from flame, has slackened flame stabilization mechanism; Fuel reacts responsive with the disturbance of premixed flow to fuel injection speed (associating with fuel Wobbe index) with the uniformity coefficient of air blending; Fuel and air blending occur in the limited swirling two-phase flows process of circular passage, do not have other controlling mechanism, and flow perturbation and intermittence greatly, and spontaneous combustion and tempering may occur.The difficulty that above-mentioned limitation is brought discharged nitrous oxides, coordinated between combustion vibration and noise, makes these indexs be difficult to further reduction, and the difficulty of firing optimization and control increases, and fuel accommodation is narrow; (2) in the multi-jet configuration mode of fuel nozzle group 40, the distance between the outer rim of center fuel nozzle 2 and fuel nozzle 3 makes nozzle outer rim close to burner inner liner 4, exacerbates the calcination of nozzle flame to burner inner liner 4 internal face; Center fuel nozzle 2 and peripheral fuel nozzle 3 have different structures, add the complexity of product development, firing optimization and control; (3) multiinjector configuration and combustion control mode make some non-homogeneous arrangement of nozzle of catching fire under mode of burning, and burner inner liner 4 is burnt partially by nozzle flame; (4) burner inner liner 4 bears the stress of supporting construction while bearing high temperature, and the life-span is difficult to 8000 hours that reach the requirement of F level gas turbine; The air velocity that outer wall washes away cooling requirement is high, and requires that burner inner liner 4 outer wall is provided with flow-disturbing fin, and the flow resistance for this reason increased reduces the efficiency of gas turbine; (5) the air flow resistance that causes of gas conduct pipe 5 outer wall impinging cooling is large, and be weakened because accelerating impinging cooling along wall direction flow velocity in the position close to burner inner liner 4, the thickness thickening the gas conduct pipe 5 that cobalt base superalloy is made can only be relied on to reach life requirements, and the possibility of further improving performance is little.
Simultaneously, the development of gas turbine proposes again further requirement to chamber performance, and namely outlet gas temperature reaches 1500-1700 DEG C, nitrogen oxides in effluent concentration < 10ppm(converts 15% oxygen concentration), maintenance interval at 8000 hours, basis extends further.The dry type low nitrogen burning room of described prior art and the problem existing for combustion control technology will be more sharp-pointed, can not meet the requirement further developed even completely.
Summary of the invention
In order to solve the problem existing for 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 the identical fuel element of circumferentially evenly distributed multiple structures, each described 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, multiple thermal insulation tile 18, top cover 17, air conducting lining 19, gas conduct pipe shell 20, air conduit 21, multiple 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 being input in described turbine by the combustion gas produced after gaseous fuel and air burning;
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 passes through Flange joint with one end of exhaust casing 10, described gas conduct pipe shell 20 is connected with the periphery of described gas outlet 12;
The first circular passage is formed between the little casing 41 of burner inner liner steel cylinder 16 in described fuel element inside and described combustion chamber, the second circular passage is formed between described burner inner liner steel cylinder 16 and air conducting lining 19, 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 multiple 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;
Multiple flow-disturbing ring 22 is fixed on the outer surface of described gas conduct pipe inner casing 23;
Described air conduit 21 one end is fixed on described gas conduct pipe shell 20, and the other end is plugged on flow-disturbing ring 22, and communicates with described 3rd circular passage;
Multiple joint pin with ripple buffer structure is welded with between described gas conduct pipe inner casing 23 and described gas conduct pipe shell 20;
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 inside of the exhaust stream of described compressor 9 and gas conduct pipe inner casing 23 inner through air conduit 21, the 3rd circular passage, the second circular passage, the first circular passage, fuel nozzle 15, burner inner liner, is input to described gas outlet 12.
During described fuel element work, gaseous fuel is introduced from end cover of combustion chamber 14 and is assigned to the fuel channel with the fuel nozzle 15 of array premixed device, air enters exhaust casing 10 from compressor 9 simultaneously, the flow-disturbing ring 22 the 3rd circular passage is flowed into from the air conduit 21 communicated with exhaust casing 10, the second circular passage is flowed to after impinging cooling is formed to the outside wall surface of gas conduct pipe inner casing 23, after cooling is washed away to the outside wall surface of burner inner liner steel cylinder 16, major part air flowing in combustion chamber end cap 14, burner inner liner steel cylinder 16, through the air duct by fuel nozzle 15 behind the space that burner inner liner top cover 17 surrounds, burner inner liner inside is flowed into behind fuel nozzle 15 inside with fuel mix, 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 in burner inner liner inside and burns, the high-temperature fuel gas that burning produces flows to gas conduct pipe inner casing 23, introduced gas outlet 12 by gas conduct pipe inner casing 23 and enter turbine.
The present invention can stably low nitrogen burning when gas turbine operates; In the homogeneous heating of whole gas turbine working range combustion device, flame disturbance can be reduced; And combustion boundary can strengthen heat insulation and to combustion noise absorption.
Accompanying drawing explanation
Fig. 1 is the structural representation that the gas turbine generally applied in prior art divides a fuel element of cast dry type low nitrogen burning room.
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 the result of calculation of the relation of fuel nozzle-air mixing uniformity, premix gas global fuel/air ratio and the rare limit of burning.
Detailed description of the invention
For making the object, technical solutions and advantages of the present invention clearly understand, 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 made up of the tubular fuel element that circumferentially evenly distributed multiple structures are identical, 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, each described 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, multiple thermal insulation tile 18, top cover 17, air conducting lining 19, gas conduct pipe shell 20, air conduit 21, multiple 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 being input in described turbine by the combustion gas produced after gaseous fuel and air burning;
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 passes through Flange joint with one end of exhaust casing 10, described gas conduct pipe shell 20 is connected with the periphery of described gas outlet 12;
The first circular passage is formed between the little casing 41 of burner inner liner steel cylinder 16 in described fuel element inside and described combustion chamber, the second circular passage is formed between described burner inner liner steel cylinder 16 and air conducting lining 19, 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 multiple 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 is communicated by pipeline with described end cover of combustion chamber 14, and the other end is communicated 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 is also communicated 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;
Multiple flow-disturbing ring 22 is fixed on the outer surface of described gas conduct pipe inner casing 23;
Described air conduit 21 one end is fixed on described gas conduct pipe shell 20, and the other end is plugged on flow-disturbing ring 22, and communicates with described 3rd circular passage;
Multiple joint pin with ripple buffer structure is welded with between described gas conduct pipe inner casing 23 and described gas conduct pipe shell 20;
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 inside of the exhaust stream of described compressor 9 and gas conduct pipe inner casing 23 inner through air conduit 21, the 3rd circular passage, the second circular passage, the first circular passage, fuel nozzle 15, burner inner liner, is input to described gas outlet 12.
When described fuel element work, gaseous fuel is introduced from end cover of combustion chamber 14 and is assigned to the fuel channel with the fuel nozzle 15 of array premixed device (not shown), air enters exhaust casing 10 from compressor 9 simultaneously, the flow-disturbing ring 22 the 3rd circular passage is flowed into from the air conduit 21 communicated with exhaust casing 10, the second circular passage is flowed to after impinging cooling is formed to the outside wall surface of gas conduct pipe inner casing 23, after cooling is washed away to the outside wall surface of burner inner liner steel cylinder 16, major part air flowing in combustion chamber end cap 14, burner inner liner steel cylinder 16, through the air duct by fuel nozzle 15 behind the space that burner inner liner top cover 17 surrounds, burner inner liner inside is flowed into behind fuel nozzle 15 inside with fuel mix, 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 in burner inner liner inside and burns, the high-temperature fuel gas that burning produces flows to gas conduct pipe inner casing 23, introduced gas outlet 12 by gas conduct pipe inner casing 23 and enter turbine.
As shown in Figure 2 B, described fuel nozzle 15 comprises the identical fuel nozzle of seven structures, described fuel nozzle is all tubular, these seven fuel nozzles, according to one, center, six, periphery and the tangent mode boundling arrangement of outer rim, are all positioned at the cyclone of air flow outlet in each fuel nozzle with array type Fuel-air premixed device and one.This multiple fuel nozzle optionally can open work according to the condition range of gas turbine.
Fig. 3 illustrates the burning mode schematic diagram of a fuel element of dry type low nitrogen combustion apparatus according to an embodiment of the invention in the whole working range of gas turbine.When gas turbine starts to the condition range of unloaded full rotating speed, seven fuel nozzles all work, and each fuel nozzle is all in the identical diffusion combustion mode of fuel duty, and this burning multi-modal mark is D7, as shown in Figure 3A; When the unloaded full rotating speed of gas turbine is to the condition range of output 15% shaft work, seven fuel nozzles are all in the identical diffusion combustion mode of fuel duty, the premixed combustion mode that wherein circumferentially equally distributed three peripheral fuel nozzle additional fuel supplys are identical, this burning multi-modal mark is D7+PM3, as shown in Figure 3 B; When gas turbine exports the condition range of 15% to 40% shaft work, central fuel nozzle is in diffusion combustion mode, and six peripheral fuel nozzles are in the identical premixed combustion mode of fuel duty, and this fuel multi-modal mark is PM3+PM3 '+D1, as shown in Figure 3 C; When gas turbine exports 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.
The arrangement mode of above-mentioned seven nozzles and Combustion System mode thereof make to be heated properly at whole gas turbine working range flame cylinder.
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, circular passage is formed between described nozzle casing 31 and centerbody 28, be disposed with the some row's fuel eject blades 34 and be connected with centerbody 28 in described circular passage vertically and arrange solid swirl vane 27, 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 that communicates with burner inner liner inside and blows clearly air jet hole 26;
Radially be provided with premixed fuel passage 30, diffused fuel passage 29 in described centerbody 28 side by side 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 surface, described air duct enters burner inner liner inside;
Fuel is sprayed into burner inner liner inside by described diffused fuel spray-hole 25 by described diffused fuel passage 29;
The described air duct 33 that blows clearly sprays into burner inner liner inside by the described air jet hole 26 that blows clearly by blowing clearly air, to protect centerbody, avoids 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 the fuel orifice 32 on its surface, after mixing with air, enter burner inner liner inside and burn.Under diffusive combustion operation pattern, gaseous fuel, by diffused fuel passage 29, directly sprays into burner inner liner inside from the diffused fuel spray-hole 25 of nozzle center's body 28 end and carries out contacting, burning with air.Blowing clearly air by blowing air duct 33 clearly, spraying into burner inner liner inside from blowing clearly air jet hole 26.
Fig. 5 is the structural representation of thermal insulation tile according to an embodiment of the invention, and Fig. 5 A is the perspective view of thermal insulation tile, and Fig. 5 B is the partial sectional view of thermal insulation tile.As shown in Figure 5, every block thermal insulation tile 18 is provided with several and installs knot 36 and some turbulence columns 37 in the side deviating from flame, described installation knot 36 coordinates with floating ring 38 mounted thereto, thermal insulation tile 18 is installed on flexibly 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, Cryogenic air outside burner inner liner steel cylinder 16 flows into the circumferential weld between thermal insulation tile 18 and burner inner liner steel cylinder 16 from the gap of installing knot 36, after turbulence columns 37 array, 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 constitute gas conduct pipe, gas conduct pipe shell 20 are provided with several air conduits 21, are plugged in respectively and are arranged on some row's flow-disturbing rings 22 of gas conduct pipe Inner shell 23 outer surface.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, to cool gas conduct pipe Inner shell 23, then flows in the 3rd circular passage between gas conduct pipe inner casing 23 and shell 20.
Relative to prior art, there is following advantage in the present invention:
(1) fuel nozzle in the present invention is with array type premixed device, can realize with this: mixture homogeneity (i.e. the root mean square calculation result of nozzle premix gas channel outlet section concentration) doubles than the nozzle 2 and 3 of the combustion chamber of the prior art shown in Fig. 1, global fuel/the air ratio entering the premix gas of combustion zone and the allowance of burning between rare limit also can reduce about 1 times, specifically can with reference to shown in figure 7, in Fig. 7, the fuel air ratio acquired by nozzle 2 and 3 of the combustion chamber that dashed curve is prior art, the fuel air ratio of block curve acquired by the utility model fuel nozzle 15, mixing does not need eddy flow, thus cyclone can be arranged on the side of jet expansion near flame, thus enhances flame stabilization mechanism, array inhibits the initial disturbance of inlet air flow, eliminate large scale flowing, exit flow perturbation amplitude than the combustion chamber of the prior art shown in Fig. 1 nozzle 2 and 3 decline an order of magnitude, mixture homogeneity and premixed flow disturbance no longer responsive to fuel injection speed, do not possess in the passage of array premix gas and catch fire and flame stabilization condition, thus avoid the generation of spontaneous combustion and tempering,
(2) multiinjector of fuel nozzle 15 of the present invention is configured in the space having maximally utilised burner inner liner cross section circle geometrically, under the prerequisite keeping the cross-section area of nozzle, add the distance between nozzle edge and burner inner liner, thus alleviate the calcination to burner inner liner; And identical nozzle reduces the complexity of product development, firing optimization and control; Other 7 nozzle arrangement coordinate method for controlling combustion, and the nozzle caught fire under making each burning mode is uniformly distributed, thus avoid the phenomenon that burner inner liner burns partially;
(3) burner inner liner in the present invention adopts the structure of steel cylinder liner thermal insulation tile, under the condition of outlet gas temperature 1400 DEG C, the temperature of burner inner liner load steel cylinder is below 800 DEG C, eliminate the flow-disturbing fin that outside wall surface air washes away cooling, ensure that the burner inner liner life-span of F level gas turbine requirement, reduce the air flow resistance of combustion chamber;
(4) gas conduct pipe in the present invention adopts the duplex shell structure connected by ripple post, adds intensity; Along air-flow direction, the flow-disturbing ring that multi-group has air conduit is installed between inside and outside shell, destroy the thermal boundary layer of inner casing outside wall surface, air is introduced from the entrance of air conduit on shell, impact inner casing outside wall surface, avoids adherent air-flow and slackens effect to impinging cooling; The requirement impacting cooling-air flow velocity is reduced, thus reduces combustion air flow resistance; The heat resistance of gas conduct pipe and life-span is the invention enables to have the potentiality promoted further.
Above-described specific embodiment; object of the present invention, technical scheme and beneficial effect are further described; be 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 amendment made, equivalent replacement, improvement etc., all should be included within 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 the identical tubular fuel element of circumferentially evenly distributed multiple structures; Each described 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), multiple thermal insulation tile (18), top cover (17), air conducting lining (19), gas conduct pipe shell (20), air conduit (21), multiple 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 being input in described turbine by the combustion gas produced after gaseous fuel and air burning;
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 Flange joint is passed through with one end of exhaust casing (10) in the little casing in described combustion chamber (41), described gas conduct pipe shell (20) is connected with the periphery of described gas outlet (12);
What be positioned at described fuel element inside is formed with the first circular passage between burner inner liner steel cylinder (16) and described combustion chamber little casing (41), the second circular passage is formed between described burner inner liner steel cylinder (16) and air conducting lining (19), be formed with the 3rd circular passage between described gas conduct pipe shell (20) and the gas conduct pipe inner casing (23) being positioned at fuel element inside, above-mentioned three circular passages communicate;
On the internal face that described multiple thermal insulation tile (18) divides row to be lifted on burner inner liner steel cylinder (16) successively, together form 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);
Multiple flow-disturbing ring (22) is fixed on the outer surface of described gas conduct pipe inner casing (23);
Described air conduit (21) one end is fixed on described gas conduct pipe shell (20), and the other end is plugged on flow-disturbing ring (22), and communicates with described 3rd circular passage;
Multiple joint pin with ripple buffer structure is welded with between described gas conduct pipe inner casing (23) and described gas conduct pipe shell (20);
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 inside of the exhaust stream of described compressor (9) and gas conduct pipe inner casing (23) inner through air conduit (21), the 3rd circular passage, the second circular passage, the first circular passage, fuel nozzle (15), burner inner liner, is input to described gas outlet (12);
During described fuel element work, gaseous fuel is introduced from end cover of combustion chamber (14) and is assigned to the fuel channel with the fuel nozzle (15) of array premixed device, air enters exhaust casing (10) from compressor (9) simultaneously, the flow-disturbing ring (22) the 3rd circular passage is flowed into from the air conduit (21) communicated with exhaust casing (10), the second circular passage is flowed to after impinging cooling is formed to the outside wall surface of gas conduct pipe inner casing (23), after cooling is washed away to the outside wall surface of burner inner liner steel cylinder (16), major part air flowing in combustion chamber end cap (14), burner inner liner steel cylinder (16), through the air duct by fuel nozzle (15) behind the space that top cover (17) surrounds, burner inner liner inside is flowed into behind fuel nozzle (15) inside with fuel mix, 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 in burner inner liner inside and burns, the high-temperature fuel gas that burning produces flows to gas conduct pipe inner casing (23), introduced gas outlet (12) by gas conduct pipe inner casing (23) and enter turbine.
2. burner according to claim 1, it is characterized in that, described fuel nozzle (15) comprises fuel channel and air duct, one end of described fuel channel is communicated by pipeline with described end cover of combustion chamber (14), and the other end is communicated 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), top cover (17) communicates with the first circular passage, and the other end is also communicated 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 the identical fuel nozzle of seven structures, described fuel nozzle is all tubular, these seven fuel nozzles according to one, center, six, periphery and outer rim tangent mode boundling arrangement.
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), circular passage is formed between described nozzle casing (31) and centerbody (28), be disposed with the some row's fuel eject blades (34) and be connected with centerbody (28) in described circular passage vertically and arrange solid swirl vane (27), 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) that communicates with burner inner liner inside and blows clearly air jet hole (26);
Radially be provided with premixed fuel passage (30), diffused fuel passage (29) in described centerbody (28) side by side 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 burner inner liner inside via fuel orifice (32), the described air duct being positioned at fuel eject blade (34) surface;
Fuel is sprayed into burner inner liner inside by described diffused fuel spray-hole (25) by described diffused fuel passage (29);
The described air duct (33) that blows clearly sprays into burner inner liner inside by the described air jet hole (26) that blows clearly by blowing clearly air, to protect centerbody, avoids burn.
5. burner according to claim 4, it is characterized in that, when each fuel nozzle of the fuel nozzle that described seven structures are identical works, 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 the fuel orifice (32) on its surface, after mixing with air, enter burner inner liner inside and burn; Under diffusive combustion operation pattern, gaseous fuel, by diffused fuel passage (29), directly sprays into burner inner liner inside from the diffused fuel spray-hole (25) of nozzle center's body (28) end and carries out contacting, burning with air; Blowing clearly air by blowing air duct (33) clearly, spraying into burner inner liner inside from blowing clearly air jet hole (26).
6. burner according to claim 3, is characterized in that, the fuel nozzle that described seven structures are identical optionally opens 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 all work, and each fuel nozzle is all in the identical diffusion combustion mode of fuel duty;
When the unloaded full rotating speed of gas turbine is to the condition range of output 15% shaft work, seven fuel nozzles are all in the identical diffusion combustion mode of fuel duty, the premixed combustion mode that wherein circumferentially equally distributed three peripheral fuel nozzle additional fuel supplys are identical;
When gas turbine exports the condition range of 15% to 40% shaft work, central fuel nozzle is in diffusion combustion mode, and six peripheral fuel nozzles are in the identical premixed combustion mode of fuel duty;
When gas turbine exports 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 and installs knot (36) and some turbulence columns (37) in the side deviating from flame, described installation knot (36) coordinates with floating ring mounted thereto (38), thermal insulation tile (18) is installed on flexibly 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 installing knot (36), after turbulence columns (37) array, flow into burner inner liner from the gap location between thermal insulation tile 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) constitute 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 gas conduct pipe Inner shell (23) from the inside of air conduit (21), to cool gas conduct pipe Inner shell (23), then flow in the 3rd circular passage between gas conduct pipe inner casing (23) and gas conduct pipe shell (20).
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| Application Number | Priority Date | Filing Date | Title |
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| CN201310288860.5A CN103528094B (en) | 2013-07-10 | 2013-07-10 | Dry-type low-nitrogen combustion device for gas fuel of gas turbine |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201310288860.5A CN103528094B (en) | 2013-07-10 | 2013-07-10 | Dry-type low-nitrogen combustion device for gas fuel of gas turbine |
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| CN103528094A CN103528094A (en) | 2014-01-22 |
| CN103528094B true CN103528094B (en) | 2015-04-08 |
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| CN201310288860.5A Expired - Fee Related CN103528094B (en) | 2013-07-10 | 2013-07-10 | Dry-type low-nitrogen combustion device for gas fuel of gas turbine |
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Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104654358B (en) * | 2015-02-13 | 2017-09-15 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of combustion chamber premixer fuel nozzle with flow guiding structure |
| CN104654359B (en) * | 2015-02-13 | 2017-12-19 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of flow guiding structure of combustion chamber premixer fuel nozzle |
| CN106271007A (en) * | 2015-05-25 | 2017-01-04 | 西安航空动力股份有限公司 | A kind of electro-beam welding joint structure |
| CN108105802A (en) * | 2017-12-14 | 2018-06-01 | 天津成立航空技术有限公司 | A kind of flow path designs method of term durability gas turbine flame barrel combustion header |
| CN107975822B (en) * | 2017-12-19 | 2023-03-14 | 中国科学院工程热物理研究所 | Combustion chamber of gas turbine and gas turbine using combustion chamber |
| CN109519971A (en) * | 2018-12-28 | 2019-03-26 | 中国船舶重工集团公司第七0三研究所 | A kind of low emission gas turbine |
| CN112178691B (en) * | 2020-10-27 | 2022-05-13 | 西北工业大学 | Double-wall cooling structure with air film hole hyperbolic turbulence column |
| US11603799B2 (en) * | 2020-12-22 | 2023-03-14 | General Electric Company | Combustor for a gas turbine engine |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6361273B1 (en) * | 1999-04-01 | 2002-03-26 | Alstom (Switzerland) Ltd | Heat shield for a gas turbine |
| EP1503145A1 (en) * | 2003-07-31 | 2005-02-02 | General Electric Company | Thermal isolation device for liquid fuel components |
| CN102213425A (en) * | 2010-02-19 | 2011-10-12 | 通用电气公司 | Combustor liner for a turbine engine |
| CN102597631A (en) * | 2009-08-26 | 2012-07-18 | 西门子公司 | Burner, in particular for gas turbines |
| CN103134078A (en) * | 2011-11-25 | 2013-06-05 | 中国科学院工程热物理研究所 | Array standing vortex fuel-air premixer |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090235668A1 (en) * | 2008-03-18 | 2009-09-24 | General Electric Company | Insulator bushing for combustion liner |
-
2013
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Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6361273B1 (en) * | 1999-04-01 | 2002-03-26 | Alstom (Switzerland) Ltd | Heat shield for a gas turbine |
| EP1503145A1 (en) * | 2003-07-31 | 2005-02-02 | General Electric Company | Thermal isolation device for liquid fuel components |
| CN102597631A (en) * | 2009-08-26 | 2012-07-18 | 西门子公司 | Burner, in particular for gas turbines |
| CN102213425A (en) * | 2010-02-19 | 2011-10-12 | 通用电气公司 | Combustor liner for a turbine engine |
| CN103134078A (en) * | 2011-11-25 | 2013-06-05 | 中国科学院工程热物理研究所 | Array standing vortex fuel-air premixer |
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