CN102878580B - Lean premixed combustion chamber for gas turbine - Google Patents
Lean premixed combustion chamber for gas turbine Download PDFInfo
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- CN102878580B CN102878580B CN201210337011.XA CN201210337011A CN102878580B CN 102878580 B CN102878580 B CN 102878580B CN 201210337011 A CN201210337011 A CN 201210337011A CN 102878580 B CN102878580 B CN 102878580B
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Abstract
The invention discloses a lean premixed combustion chamber for a gas turbine. The lean premixed combustion chamber for the gas turbine is characterized in that a flame tube is fixed in a cartridge receiver, and a plurality of round holes for feeding air are formed in a wall surface of a tail part of the cartridge receiver; an igniter mounting seat for mounting an igniter is arranged on a side surface of the cartridge receiver; a swirl cup with a variable diameter is arranged in the flame tube, and a nozzle swirler combined piece is connected to an inlet of the swirl cup through the cartridge receiver; an on-duty fuel introducing tube is arranged in the center of a nozzle body, and a premixed fuel introducing tube is arranged on an outer ring of the nozzle body; a back cover of a premixed fuel chamber of the swirler combined piece is connected with an inner side of a blade mounting base body to form the premixed fuel chamber; a plurality of blades are fixed on an outer side of the blade mounting base body, a blind hole is formed in every blade along the axial direction, and a plurality of premixed fuel jetting holes are formed in wall surfaces on two sides of every blade; and premixed fuel enters the premixed fuel chamber from the premixed fuel introducing tube, enters a swirler passage through the blind holes and the premixed fuel jetting holes in the blades and is mixed with air. By the lean premixed combustion chamber for the gas turbine, the fuel is uniformly mixed with the air, and the discharge of nitrogen oxide (NOX) of a combustion chamber can be reduced.
Description
Technical field
The invention belongs to gas turbine technology field, particularly relate to and be a kind ofly applied to the poor premixed combustion premixed fuel injection structure of gas-turbine combustion chamber and adopt the poor lean premixed combustor of this structure.
Background technology
The subject matter that current gas-turbine combustion chamber faces will reduce pollutant particularly NO exactly
xdischarge.Poor premixed combustion is as a kind of low NO of dry type of maturation
xtechnology is widely used.So-called poor premixed combustion be exactly by fuel and air in advance in combustion chamber combined upstream, avoid producing fuel and the AIR Proportional region close to stoichiometric ratio.Such combustion zone is in air excess state, and therefore flame temperature reduces, thus greatly reduces thermal NO
xgeneration.Poor premixed combustion technology reduces NO
xthe key of discharge is the even blending realizing fuel and air within the time short as far as possible., there is not local burnup high concentration region, district of localized hyperthermia would not be produced, thus a large amount of NO can be suppressed in fuel and air blending even
xgeneration.Fuel can not overstand in blending region in addition, otherwise tempering can occur and certainly light phenomenon, affects the safe operation of combustion chamber.Along with the development of gas turbine technology, combustion chamber inlet air temperature is more and more higher, and this problem is also more and more serious.In addition, because the ignition delay time of hydrogen at identical conditions will much smaller than the gas fuel of routine, therefore adopt for the fuel that hydrogen content is high that poor premixed combustion is easier to be occurred from lighting in premixed channel.
Gas-turbine combustion chamber adopts cyclone form Central backflow area thus stabilize the flame at head usually, and when adopting poor premixed combustion technology, fuel sprays in the upstream of cyclone usually, and fuel is realizing the blending with air in swirler passages process.The shortcoming of this kind of method is that fuel jet can cause fuel to accumulate in certain area under the impact of upstream incoming air, can not realize the even blending with air.The flow of incoming air and the fluctuation of flow direction also can have influence on the mixing effect of fuel and air.
Summary of the invention
The object of the present invention is to provide the poor lean premixed combustor of a kind of gas turbine, with the mixing effect of the premixed fuel and air that improve the poor lean premixed combustor of gas turbine, reduce NO
xdischarge.
For achieving the above object, the poor lean premixed combustor of gas turbine provided by the invention, its primary structure comprises:
One casing (1), this casing (1) internal fixtion has burner inner liner (2), forms two strands of passages of air between casing and burner inner liner;
This casing (1) afterbody wall offers some circular holes (11) passing into air; Casing (1) side is provided with the igniter mount pad (17) for mounting points firearm (5);
Be provided with the eddy flow cup (45) of reducing in this burner inner liner (2), the inlet diameter of this eddy flow cup (45) is less than outlet diameter; Nozzle a cluster cyclone component (3) is connected to the entrance of this eddy flow cup (45) by casing (1);
Rotating nozzle body (34) center in nozzle a cluster cyclone component (3) is fuel introduction tube on duty (38), the top of this fuel introduction tube on duty (38) is nozzle on duty (33), be the chamfering conical surface outside the port of export of nozzle on duty (33), the chamfering conical surface circumferentially processed multiple circular hole as fuel orifice (310); Fuel introduction tube on duty (38) outer ring is premixed fuel inlet tube (39), and one end of this premixed fuel inlet tube (39) connects a cluster cyclone component (35), and the side of this premixed fuel inlet tube (39) is provided with premixed fuel hole (303);
Premixed fuel chamber bonnet (304) of a cluster cyclone component (35) and the inner side of blades installation matrix (305) are connected to form premixed fuel chamber (307); The outside of blades installation matrix (305) is fixed with multiple blade (306), forms streamwise uiform section and become the swirler passages (31) of angle with radial direction between each blade (306); Each blade (306) has a blind hole (308) vertically, and each blind hole (308) is alignd with the perforate (309) on blades installation matrix (305); Each blade (306) two side walls is provided with multiple premixed fuel spray-hole (32), and the premixed fuel spray-hole (32) on each blade (306) communicates with the blind hole (308) of place blade (306); Premixed fuel enters premixed fuel chamber (307) from premixed fuel inlet tube (39), enter swirler passages (31) by the swirler blades blind hole (308) on blade (306) and the premixed fuel spray-hole (32) on blade (306), complete the blending with air.
The poor lean premixed combustor of described gas turbine, wherein, blades installation matrix (305) outside is provided with the shallow slot identical with swirler blades (306) shape of cross section, and blade (306) embeds in this shallow slot and is welded and fixed.
The poor lean premixed combustor of described gas turbine, wherein, the uiform section area of swirler passages (31) is determined by the air mass flow that swirler passages (31) enters burner inner liner (2); The size of the radial angle of swirler passages (31) depends on the swirl strength of needs.
The poor lean premixed combustor of described gas turbine, wherein, casing (1) middle part is provided with a ring flange (12), gas turbine body and the poor lean premixed combustor of gas turbine is linked together by this ring flange.
The poor lean premixed combustor of described gas turbine, wherein, circular hole (11) gross area of casing (1) afterbody is greater than the twice of the cross-sectional area (6) of two strands of passages.
The poor lean premixed combustor of described gas turbine, wherein, the outside of blades installation matrix (305) is provided with the notch identical with blade (306) shape of cross section, and each blade (306) embeds in a notch fixing.
The poor lean premixed combustor of described gas turbine, wherein, eddy flow cup (45) entrance is straight length, and transition is large diameter outlet.
The poor lean premixed combustor of described gas turbine, wherein, igniter (5) is fixed on the mount pad (17) of casing by screw thread, and successively through casing (1), burner inner liner (2) and eddy flow cup (45), igniter head of igniter (5) is located at inside eddy flow cup, fire fuel of discharging after energising.
Maximum feature of the present invention is that swirler passages arranges fuel orifice along sharf to having on surface more, and this some holes is connected with the premixed fuel passage of nozzle, forms the injection channel of premixed fuel.Premixed fuel completes and sprays and carry out blending with air in swirler passages.The advantage one of this premixed fuel spray regime ensure that the blending of fuel and air is even, is conducive to the NO reducing combustion chamber
xdischarge, two is impacts that the flowing of fuel is not easy to be subject to the fluctuation of incoming air flow field, upstream, ensures the stability of chamber fuel blending, can not cause combustion chamber NO
xthe change of discharge.
Accompanying drawing explanation
Fig. 1 is the longitudinal sectional view of the poor lean premixed combustor of gas turbine of the present invention.
Fig. 2 A is the enlarged diagram of case structure figure in Fig. 1, and Fig. 2 B is the side view front view of Fig. 2 A.
Fig. 3 A is the enlarged diagram of Fig. 1 Flame barrel structure figure, and Fig. 3 B is the side view of Fig. 3 A.
Fig. 4 is nozzle a cluster cyclone component three-dimensional view in Fig. 1.
Fig. 5 is nozzle a cluster cyclone component longitudinal sectional view in Fig. 1.
Fig. 6 is eddy flow cup sub-assembly longitudinal sectional view in Fig. 1.
Primary clustering symbol description in accompanying drawing:
1 casing;
2 burner inner liners, 20 burner inner liner top covers, 201 burner inner liner latter ends, cylindrical section outside 202 conical sections, 203 burner inner liner first paragraphs, igniter patchhole on 204 burner inner liners, 21 blending hole, 22 cylindrical shell film cooling holes, 23 burner inner liner top cover Cooling Holes, 24 burner inner liner outlets, the cylindrical shell of 25 burner inner liners, 26 burner inner liner top cap central macropores, aperture around 27 burner inner liner top cap central macropores, annulus inside 28 burner inner liners, 29 circular passages;
3 nozzle a cluster cyclone components, 31 swirler passages, the premixed fuel spray-hole of 32 blade walls, 33 nozzles on duty, 34 rotating nozzle body, 35 a cluster cyclone components, 36 cyclone mounting nuts, pad installed by 37 cyclones, 38 fuel nozzle inlet tubes on duty, 39 premixed fuel inlet tubes; 301 fuel road disrance sleeves, 302 premixed fuel road annulus access, 303 premixed fuel entrances, 304 premixed fuel chamber bonnets, 305 swirler blades install matrix, 306 swirler blades, 307 cyclone premixed fuel chambeies, 308 swirler blades blind holes, perforate on 309 blades installation matrixes, 310 fuel nozzle spray-holes on duty;
4 eddy flow cup sub-assemblies, 41 eddy flow cup entrances, 42 eddy flow cup outlets, 43 eddy flow cup mount pads, 44 eddy flow cup mount pad screw holes, 45 eddy flow cups, 46 igniter jacks;
5 igniters; 6 annulars, two strands of passages; 7 studs; 8 pads; 9 nuts; 10 packing rings; 11 circular holes; 12 ring flanges; 13 casing end cap central macropores; 14 screw holes; 15 blind holes; 16 through holes; 17 igniter mount pads; 18 screws.
Detailed description of the invention
Technical problem to be solved by this invention improves the premixed fuel of the poor lean premixed combustor of gas turbine and the mixing effect of air, reduces NO
xdischarge.
Technical scheme of the present invention is achieved in that
A tubular gas-turbine combustion chamber for operating on gaseous fuel, comprises casing, burner inner liner, nozzle a cluster cyclone component, eddy flow cup sub-assembly and igniter totally 5 parts.
Combustion chamber is divided into two-layer generally, and outside is casing, and inner side is burner inner liner.Form two strands of passages of air between casing and burner inner liner, casing afterbody wall has a large amount of circular hole, and the air from compressor enters two strands of passages by these circular holes.The gross area of circular hole is greater than the twice of the cross-sectional area of two strands of passages, to ensure that the pitot loss of combustion chamber mainly betides burner inner liner and cyclone, instead of these circular holes on casing.These circular holes play the effect air from compressor being carried out to rectification, eliminate the even property of circumferential asymmetry of incoming air and the disturbance of large whirlpool group, ensure the uniformity of burner inner liner air inlet, thus can improve the Exit temperature distribution of combustion chamber.Be welded with a ring flange in the middle part of casing, by this ring flange, combustion chamber and gas turbine body be assembled together.Casing end cap central has a macropore, for inserting nozzle.Four screw holes be uniformly distributed along the circumference outwards are had, for being screwed into the screw of fixed nozzle from center macropore.Outwards have four blind holes be uniformly distributed along the circumference again, outside is four through holes near blind hole, for inserting the studs connecting burner inner liner and casing.Studs through after end cap, is fixed with the nut with check washer, and is pounded into blind hole by check washer instrument, prevent nut loosening inside end cap.Casing side has a hole near end cap and is welded with an igniter mount pad, for mounting points firearm.
Burner inner liner is a tube-like thin-wall component, comprises top cover and cylindrical shell.Top cap central has a macropore, for installing eddy flow cup.Circumferentially having 4 apertures around macropore, fixing eddy flow cup sub-assembly for inserting studs; Remainder has a large amount of air admission hole, and portion of air enters burner inner liner for cooling eddy flow cup by this some holes.Cylindrical shell is welded by multistage, and wherein first paragraph side is having a hole, for insertion point firearm corresponding to casing igniter mount pad position.Except first paragraph, each section of upstream extremity circumferentially opens a large amount of aperture, and is welded with an annulus in inner side, and forms a circular passage between cylindrical shell, and the air entered by cylindrical shell wall aperture is flow through this circular passage and forms gaseous film control, reduces flame tube wall surface temperature.Circumferentially have 4 ~ 6 macropores at second from the bottom section of mid portion, the air entered by this round makes its temperature reduce with the high-temperature flue gas blending from head.Burner inner liner final stage is punctured into the less direct tube section of a diameter by direct tube section through a conical section, as the outlet of burner inner liner, inserts the spiral case for being connected combustion chamber and turbine when assembling with gas turbine.A cylindrical section is welded with, for increasing outlet section rigidity outside conical section.
Nozzle a cluster cyclone component is made up of nozzle body, a cluster cyclone component, nozzle on duty, mounting nuts and pad.
Nozzle body comprises fuel introduction tube on duty, premixed fuel inlet tube and fuel road disrance sleeve.
Fuel road disrance sleeve is the pipe fitting that one end machined step, and it first welds together with fuel introduction tube on duty, and then welds with premixed fuel inlet tube, and form an annulus access, premixed fuel perforate from the side enters this annular space, flows to a cluster cyclone component.
A cluster cyclone component comprises premixed fuel chamber bonnet, blades installation matrix and several swirler blades composition.Premixed fuel chamber bonnet and blades installation matrix are welded together to form premixed fuel chamber, and swirler blades is welded on blades installation matrix.The each Edge Blend angle of swirler blades, reduces flow losses.Swirler blades opens a blind hole vertically, the apertures in alignment on perforate and blades installation matrix, axially opens some apertures in blade both sides, as premixed fuel spray-hole along blade center hole.Premixed fuel spray-hole, along sharf to uniform, ensures the uniformity of fuel distribution.Premixed fuel after premixed fuel inlet tube enters annular space, premixed fuel chamber successively, then leads to the axial blind hole on blade, and the premixed fuel spray-hole finally by blade side enters swirler passages, completes the blending with air in swirler passages.
The screw-internal thread fit of premixed fuel chamber bonnet taper end threading and premixed fuel pipe taper end, nozzle body and a cluster cyclone component are threaded togather by this, the pad compressed between fuel road disrance sleeve and premixed fuel chamber bonnet by tightening this screw thread realizes sealing, and prevents premixed fuel from revealing.
Process the shallow slot that several (identical with blade quantity) are identical with leaf cross-section shape outside blades installation matrix, during welding, blade is embedded wherein, facilitate blade to locate, ensure leaf position precision.Blade is welded in after on matrix, forms streamwise uiform section and the passage formed an angle with radial direction.This passage passes through for the air entering head of combustion chamber, realizes the blending of premixed fuel and air, and forms eddy flow in downstream.
Nozzle on duty is positioned at nozzle assembly for fluid center, and one end machining internal thread matches with fuel introduction tube on duty.Chamfering outside the port of export, the chamfering conical surface is circumferentially processed some circular holes as fuel orifice, circle hole centreline and nozzle center form an angle.
Being threaded connection between nozzle body and cyclone, first being taken apart by two parts when assembling with casing, inserted by nozzle body by outside casing end cap, cyclone then loads and is assembled together with nozzle body inside end cap.
Insert outside end cover of combustion chamber after first mounting nuts, nozzle on duty and nozzle body being assembled when nozzle a cluster cyclone component and casing are assembled, and with four screws, mounting nuts is fixed on end cap, nozzle can be regulated to insert the degree of depth of combustion chamber by rotary nozzle body, convenience coordinates with burner inner liner.Then inside end cap, a cluster cyclone component is installed on nozzle body.
Eddy flow cup sub-assembly is made up of eddy flow cup and eddy flow cup mount pad, and both weld together.Four screwed holes are circumferentially had outside eddy flow cup mount pad.Eddy flow cup side is penetrating hole position corresponding to burner inner liner igniter has a hole, and igniter inserts and fire fuel of discharging in this position thus.Eddy flow cup sub-assembly loads top cap central macropore inside burner inner liner, a pad is placed outside top cover, eddy flow cup sub-assembly through the screwed hole of pad, burner inner liner top cover and eddy flow cup sub-assembly, is fixed on burner inner liner top cover by tightening studs by studs successively.
Igniter is fixed on the mount pad of casing by screw thread, and successively through casing, burner inner liner and eddy flow cup, igniter head leaks cruelly inside eddy flow cup, fire fuel of discharging after energising.
Described nozzle a cluster cyclone component comprises premix two-way fuel on duty injection channel.Fuel road on duty, in nozzle center, sprays into through nozzle on duty, and its effect is in cyclone, be formed centrally diffusion combustion flame, realizes the smooth combustion under underload.Premixed fuel road in outside, and is connected with radial swirler blade center hole.Open some premixed fuel spray-holes communicated with centre bore in blade two sides, premixed fuel sprays into swirler passages by described premixed fuel spray-hole.Premixed fuel spray-hole, along sharf to uniform, ensure that the uniformity of fuel distribution.Air flows acceleration after entering swirler passages, is not easy the impact of the air flow fluctuation being subject to upstream incoming flow, thus ensure that the stability of fuel and air blending.Radial swirler is uiform section area passage, and one end and described nozzle body pass through together with thread connection, and the other end and the eddy flow cup mount pad be arranged on burner inner liner top cover are fitted, and form the radial swirler passage closed.Premixed fuel realizes even blending with the air through cyclone in swirler passages in flow process, then enter the cyclone cup being arranged on burner inner liner head.Eddy flow cup entrance is straight length, and then transition is large diameter outlet.In the effect backspin flow cup expansion segment of cyclone, be formed centrally recirculating zone stabilize the flame.
Air from compressor enters two strands of passages from casing rear end, flows from back to front, enters burner inner liner successively by the cyclone of the blending hole on burner inner liner, film cooling holes and head, and cool burner inner liner wall with convection type in the process.The operating temperature allowed according to flame temperature and burner inner liner wall through the air capacity of film cooling holes is determined, determine through the air capacity primary zone mean temperature as required of cyclone and fuel quantity, remaining air is all entered by blending hole.
Burner inner liner and casing are linked together by 4 studs.The screw hole that a pad pad is passed in one end, burner inner liner top cover is screwed into eddy flow cup mount pad of studs.The other end stretches out outside casing, fixes with nut.Nozzle a cluster cyclone component is fixed on casing, and can regulate insertion depth by rotating nozzle body until the end face of swirler blades withstands on eddy flow cup mount pad.
Below in conjunction with accompanying drawing, the present invention is described in detail.The concrete structure of single cannular combustion chamber of the present invention as shown in Figure 1, mainly comprises five parts: casing 1, burner inner liner 2, nozzle a cluster cyclone component 3, eddy flow cup sub-assembly 4 and igniter 5.
(1) general structure
As shown in Figure 1, air from compressor enters annular two strands of passages 6 between casing 1 and burner inner liner 2 and to head flowing, the blending hole 21 successively on burner inner liner 2, cylindrical shell film cooling holes 22 and swirler passages 31 enter burner inner liner 2 from the circular hole 11 that casing 1 afterbody is offered.Fuel divides two-way to spray into.The fuel of about 90% sprays into swirler passages 31 by the perforate 32 of swirler blades wall, and carries out blending with air in swirler passages 31; The fuel of about 10% sprays into from the nozzle on duty 33 being positioned at cyclone center in addition, forms diffusion combustion, for stabilizing the flame.The gaseous mixture spin current device passage of fuel and air enters eddy flow cup entrance 41, and the eddy flow cup that arrives soon after outlet 42 forms sudden expansion, and forms central backflow in eddy flow cup outlet 42 under the cyclonic action of cyclone, ensures the stable of burning.The high-temperature flue gas that eddy flow cup outlet 42 produces export 24 from burner inner liner and flow out subsequently with after the air blending from burner inner liner top cover Cooling Holes 23, cylindrical shell film cooling holes 22 and blending hole 21.
Burner inner liner 2 and casing 1 are linked together by 4 studs 7.One end of studs, through pad 8, a burner inner liner top cover 20, is screwed into the screw hole 44 of eddy flow cup mount pad 43.The other end stretches out outside casing, fixes with nut 9 and packing ring 10.Nozzle a cluster cyclone component 3 to be fixed on casing 1, and can regulate insertion depth by rotating nozzle body 34 until the end face of swirler blades to withstand on eddy flow cup mount pad 43.
(2) casing
Fig. 2 A and Fig. 2 B is case structure figure.Casing (1) afterbody wall has a large amount of circular hole 11, and the air from compressor enters two strands of passages by these circular holes.Be welded with a ring flange 12 in the middle part of casing, by this ring flange, combustion chamber and gas turbine body be assembled together.Casing end cap central macropore 13 is for inserting nozzle.Four screw holes be uniformly distributed along the circumference 14 are outwards had, for being screwed into the screw 18 of fixed nozzle from center macropore.Outwards have four blind holes be uniformly distributed along the circumference 15 again, outside is four through holes 16 near blind hole, for inserting the studs 7 connecting burner inner liner 2 and casing 1.Studs 7 through after end cap, is fixed with the nut 9 with check washer 10, and is pounded check washer instrument into blind hole 15 inside end cap, prevents nut 9 from loosening.Casing side has a hole near end cap end and is welded with an igniter mount pad 17, for mounting points firearm 5.
(3) burner inner liner
Fig. 3 A and Fig. 3 B is flame tube structure figure.Burner inner liner is a tube-like thin-wall component, comprises top cover 20 and cylindrical shell 25.Top cover 20 center has a macropore 26, for installing eddy flow cup.Circumferentially having 4 apertures 27 around macropore, fixing eddy flow cup sub-assembly 4 for inserting studs 7.Remainder has a large amount of air admission hole 23, and portion of air enters burner inner liner for cooling eddy flow cup 45 by this some holes.The cylindrical shell 25 of burner inner liner is welded by multistage, and wherein first paragraph 203 side is having igniter patchhole 204 corresponding to casing igniter mount pad position.Except first paragraph, each section of upstream extremity circumferentially opens a large amount of aperture 22, and is welded with an annulus 28 in inner side, and forms a circular passage 29 between cylindrical shell, the air entered by cylindrical shell wall aperture 22 is flow through this circular passage 29 and forms gaseous film control, reduces flame tube wall surface temperature.Circumferentially have 6 blending hole 21 at second from the bottom section of mid portion, the air entered by this round makes its temperature reduce with the high-temperature flue gas blending from head.Burner inner liner final stage 201 is punctured into the less direct tube section of a diameter by direct tube section through a conical section, as the outlet of burner inner liner, inserts the spiral case for being connected combustion chamber and turbine when assembling with gas turbine.A cylindrical section 202 is welded with, for increasing outlet section rigidity outside conical section.
(4) nozzle a cluster cyclone component
Fig. 4, Fig. 5 are nozzle a cluster cyclone component front view and longitudinal sectional view respectively.Nozzle a cluster cyclone component is made up of with pad 37 nozzle body 34, a cluster cyclone component 35, nozzle on duty 33, mounting nuts 36.
Rotating nozzle body 34 comprises fuel introduction tube 38 on duty, premixed fuel inlet tube 39 and fuel road disrance sleeve 301.
Fuel road disrance sleeve 301 machined the pipe fitting of step for one end, it first welds together with fuel introduction tube 38 on duty, and then weld with premixed fuel inlet tube 39, form a premixed fuel annulus access 302, premixed fuel premixed fuel entrance 303 from the side enters this annulus access, flows to a cluster cyclone component 35.
A cluster cyclone component 35 comprises premixed fuel chamber bonnet 304, blades installation matrix 305 and 12 swirler blades 306.Premixed fuel chamber bonnet 304 and blades installation matrix 305 are welded together to form premixed fuel chamber 307.The shallow slot that outside blades installation matrix 305, processing 12 is identical with leaf cross-section shape, embeds wherein by blade 306 during welding, facilitates blade to locate, and ensures leaf position precision.Blade 306 is welded in after on matrix 305, forms streamwise uiform section and the passage 31 formed an angle with radial direction.This passage passes through for the air entering head of combustion chamber, realizes the blending of premixed fuel and air, and forms eddy flow in downstream.The each Edge Blend angle of swirler blades 306, reduces flow losses.Swirler blades 306 opens a blind hole 308 vertically, and blind hole 308 is alignd with the perforate 309 on blades installation matrix, axially respectively opens 5 apertures 32 in blade both sides, as premixed fuel spray-hole along blade center hole.Premixed fuel spray-hole 32, along sharf to uniform, ensures the uniformity of fuel distribution.Premixed fuel is after premixed fuel inlet tube 39 enters premixed fuel road annulus access 302, premixed fuel chamber 307 successively, lead to the axial blind hole 308 on blade again, premixed fuel spray-hole 32 finally by blade side enters swirler passages 31, completes the blending with air.
The screw-internal thread fit of premixed fuel chamber bonnet taper end threading and premixed fuel pipe taper end, nozzle body and a cluster cyclone component are threaded togather by this, the pad 37 compressed between fuel road disrance sleeve and premixed fuel chamber bonnet by tightening this screw thread realizes sealing, and prevents premixed fuel from revealing.
Nozzle 33 on duty is positioned at nozzle assembly for fluid 34 center, and one end machining internal thread matches with fuel introduction tube 38 on duty.Chamfering outside the port of export, the chamfering conical surface is circumferentially processed 12 circular holes as fuel orifice 310, circle hole centreline becomes 30 ~ 45 ° of angles with nozzle center.
(5) eddy flow cup sub-assembly
Fig. 6 is the longitudinal sectional view of eddy flow cup sub-assembly.Eddy flow cup sub-assembly 4 is made up of eddy flow cup 45 and eddy flow cup mount pad 43, and both weld together.4 screw holes 44 are circumferentially had outside eddy flow cup mount pad.Eddy flow cup side is penetrating hole position corresponding to burner inner liner igniter has a hole 46, and igniter 5 inserts and fire fuel of discharging in this position thus.
Eddy flow cup sub-assembly 4 loads top cap central macropore 26 inside burner inner liner 2, a pad 8 is placed outside top cover, eddy flow cup sub-assembly 7 through the screw hole 44 of pad 8, burner inner liner top cover 24 and eddy flow cup sub-assembly, is fixed on burner inner liner top cover 24 by tightening studs 7 by studs 7 successively.
(6) igniter
Igniter 5 is fixed on the mount pad 17 of casing by screw thread, and successively through casing 1, burner inner liner 2 and eddy flow cup 45, igniter head is exposed to inside eddy flow cup, electric discharge fire fuel (see figure 1) after energising.
Claims (7)
1. the poor lean premixed combustor of gas turbine, its primary structure comprises:
One casing (1), this casing (1) internal fixtion has burner inner liner (2), annular two strands of passages of air are formed between casing and burner inner liner, this casing (1) afterbody wall offers some circular holes (11) passing into air, air from compressor enters annular two strands of passages by those circular holes, those circular holes carry out rectification to the air from compressor, eliminate the even property of circumferential asymmetry of incoming air and the disturbance of large whirlpool group, improve the Exit temperature distribution of combustion chamber;
Casing (1) side is provided with the igniter mount pad (17) for mounting points firearm (5);
Be provided with the eddy flow cup (45) of reducing in this burner inner liner (2), the inlet diameter of this eddy flow cup (45) is less than outlet diameter; Nozzle a cluster cyclone component (3) is connected to the entrance of this eddy flow cup (45) by casing (1);
Nozzle body (34) center in nozzle a cluster cyclone component (3) is fuel introduction tube on duty (38), the top of this fuel introduction tube on duty (38) is nozzle on duty (33), be the chamfering conical surface outside the port of export of nozzle on duty (33), the chamfering conical surface circumferentially processed multiple circular hole as fuel nozzle spray-hole (310) on duty; Fuel introduction tube on duty (38) outer ring is premixed fuel inlet tube (39), one end of this premixed fuel inlet tube (39) connects a cluster cyclone component (35), and the side of this premixed fuel inlet tube (39) is provided with premixed fuel entrance (303);
Premixed fuel chamber bonnet (304) of a cluster cyclone component (35) and the inner side of blades installation matrix (305) are connected to form premixed fuel chamber (307); The outside of blades installation matrix (305) is fixed with multiple blade (306), forms streamwise uiform section and become the swirler passages (31) of angle with radial direction between each blade (306); Each blade (306) has a swirler blades blind hole (308) vertically, and each swirler blades blind hole (308) is alignd with the perforate (309) on blades installation matrix (305); Each blade (306) two side walls is provided with multiple premixed fuel spray-hole (32), and the premixed fuel spray-hole (32) on each blade (306) communicates with the swirler blades blind hole (308) of place blade (306); Premixed fuel enters premixed fuel chamber (307) from premixed fuel inlet tube (39), enter swirler passages (31) by the swirler blades blind hole (308) on blade (306) and the premixed fuel spray-hole (32) on blade (306), complete the blending with air.
2. the poor lean premixed combustor of gas turbine according to claim 1, wherein, blades installation matrix (305) outside is provided with the shallow slot identical with swirler blades (306) shape of cross section, and each blade (306) embeds in a shallow slot and is welded and fixed.
3. the poor lean premixed combustor of gas turbine according to claim 1, wherein, the uiform section area of swirler passages (31) is determined by the air mass flow that swirler passages (31) enters burner inner liner (2); The size of the radial angle of swirler passages (31) depends on the swirl strength of needs.
4. the poor lean premixed combustor of gas turbine according to claim 1, wherein, casing (1) middle part is provided with a ring flange (12), gas turbine body and the poor lean premixed combustor of gas turbine is linked together by this ring flange.
5. the poor lean premixed combustor of gas turbine according to claim 1, wherein, circular hole (11) gross area of casing (1) afterbody is greater than the twice of the cross-sectional area (6) of two strands of passages.
6. the poor lean premixed combustor of gas turbine according to claim 1, wherein, eddy flow cup (45) entrance is straight length, and transition is large diameter outlet.
7. the poor lean premixed combustor of gas turbine according to claim 1, wherein, igniter (5) is fixed on the mount pad (17) of casing by screw thread, and successively through casing (1), burner inner liner (2) and eddy flow cup (45), igniter head of igniter (5) is located at inside eddy flow cup, fire fuel of discharging after energising.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210337011.XA CN102878580B (en) | 2012-09-12 | 2012-09-12 | Lean premixed combustion chamber for gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210337011.XA CN102878580B (en) | 2012-09-12 | 2012-09-12 | Lean premixed combustion chamber for gas turbine |
Publications (2)
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| CN113091095B (en) * | 2021-05-13 | 2023-05-23 | 中国联合重型燃气轮机技术有限公司 | Gas turbine combustor nozzle and method for premixing fuel and air in nozzle |
| CN114659140B (en) * | 2022-03-21 | 2023-06-23 | 杭州汽轮动力集团有限公司 | Low-emission combustor for grading fuel of gas turbine |
| CN115595528A (en) * | 2022-09-07 | 2023-01-13 | 华能太原东山燃机热电有限责任公司（Cn） | Explosion spraying device suitable for hydrogen premixed combustion |
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