CN102878580A - Lean premixed combustion chamber for gas turbine - Google Patents
Lean premixed combustion chamber for gas turbine Download PDFInfo
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- CN102878580A CN102878580A CN201210337011XA CN201210337011A CN102878580A CN 102878580 A CN102878580 A CN 102878580A CN 201210337011X A CN201210337011X A CN 201210337011XA CN 201210337011 A CN201210337011 A CN 201210337011A CN 102878580 A CN102878580 A CN 102878580A
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- gas turbine
- premixed fuel
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 38
- 239000000446 fuel Substances 0.000 claims abstract description 149
- 238000002156 mixing Methods 0.000 claims description 29
- 239000011159 matrix material Substances 0.000 claims description 21
- 238000009434 installation Methods 0.000 claims description 19
- 238000000034 method Methods 0.000 claims description 7
- 230000008569 process Effects 0.000 claims description 5
- 230000007704 transition Effects 0.000 claims description 3
- 239000007789 gas Substances 0.000 abstract description 25
- MWUXSHHQAYIFBG-UHFFFAOYSA-N Nitric oxide Chemical compound O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 abstract 6
- 238000001816 cooling Methods 0.000 description 11
- 210000003660 reticulum Anatomy 0.000 description 10
- 239000007921 spray Substances 0.000 description 7
- 238000011144 upstream manufacturing Methods 0.000 description 7
- 238000007599 discharging Methods 0.000 description 6
- 230000000694 effects Effects 0.000 description 6
- 238000005516 engineering process Methods 0.000 description 5
- 238000002347 injection Methods 0.000 description 4
- 239000007924 injection Substances 0.000 description 4
- 238000012856 packing Methods 0.000 description 4
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 description 3
- 230000015572 biosynthetic process Effects 0.000 description 3
- 239000003546 flue gas Substances 0.000 description 3
- 238000003780 insertion Methods 0.000 description 3
- 230000037431 insertion Effects 0.000 description 3
- 230000014759 maintenance of location Effects 0.000 description 3
- 238000012545 processing Methods 0.000 description 3
- 238000007789 sealing Methods 0.000 description 3
- 238000003466 welding Methods 0.000 description 3
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 2
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000009792 diffusion process Methods 0.000 description 2
- 239000001257 hydrogen Substances 0.000 description 2
- 229910052739 hydrogen Inorganic materials 0.000 description 2
- 238000003754 machining Methods 0.000 description 2
- 230000003134 recirculating effect Effects 0.000 description 2
- 206010020843 Hyperthermia Diseases 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 235000019628 coolness Nutrition 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 239000003344 environmental pollutant Substances 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 239000008246 gaseous mixture Substances 0.000 description 1
- 230000036031 hyperthermia Effects 0.000 description 1
- 230000035800 maturation Effects 0.000 description 1
- JTJMJGYZQZDUJJ-UHFFFAOYSA-N phencyclidine Chemical class C1CCCCN1C1(C=2C=CC=CC=2)CCCCC1 JTJMJGYZQZDUJJ-UHFFFAOYSA-N 0.000 description 1
- 231100000719 pollutant Toxicity 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 238000005496 tempering Methods 0.000 description 1
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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 the gas turbine technology field, relate in particular to a kind of poor premixed combustion premixed fuel injection structure of gas-turbine combustion chamber and poor lean premixed combustor that adopts this structure of being applied to.
Background technology
The subject matter that present gas-turbine combustion chamber faces will reduce particularly NO of pollutant exactly
XDischarging.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 with fuel and air in advance in the combustion chamber combined upstream, avoid producing fuel and AIR Proportional near the zone of stoichiometric ratio.The combustion zone is in the air excess state like this, so the flame temperature reduction, thereby has greatly reduced thermal NO
XGeneration.Poor premixed combustion Techniques For Reducing NO
XThe key of discharging is to realize the even blending of fuel and air within the short as far as possible time.Fuel and air blending evenly, do not have local burnup's high concentration region, just can not produce the localized hyperthermia district, thereby can suppress a large amount of NO
XGeneration.The overstand that fuel can not be in the blending zone in addition, otherwise tempering can occur and certainly light phenomenon, the safe operation of combustion chamber affected.Along with the development of gas turbine technology, the combustion chamber inlet air temperature is more and more higher, and this problem is also more and more serious.In addition, the ignition delay time owing to hydrogen under identical condition will much smaller than the gas fuel of routine, therefore adopt easier the generation in premixed channel of poor premixed combustion certainly to light for the high fuel of hydrogen content.
Thereby gas-turbine combustion chamber adopts cyclone to form recirculating zone, the center retention flame at head usually, and fuel sprays in the upstream of cyclone usually when adopting poor premixed combustion technology, and fuel is realized the blending with air in through the swirler passages process.The shortcoming of this kind method is that fuel jet can cause fuel to accumulate in certain area, can not realize the even blending with air under the impact of upstream incoming flow air.The flow of incoming flow 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 premixed fuel of the poor lean premixed combustor of raising gas turbine and the mixing effect of air, reduce NO
XDischarging.
For achieving the above object, the poor lean premixed combustor of gas turbine provided by the invention, its primary structure comprises:
One casing (1) is fixed with burner inner liner (2) in this casing (1), form two strands of passages of air between casing and the burner inner liner;
This casing (1) afterbody wall offers some circular holes (11) that pass into air; Casing (1) side is provided with the igniter mount pad (17) for mounting points firearm (5);
The eddy flow cup (45) of reducing is installed in this burner inner liner (2), and 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 the nozzle a cluster cyclone component (3) is fuel inlet tube on duty (38), the top of this fuel inlet tube on duty (38) is nozzle on duty (33), the port of export of nozzle on duty (33) outside is the chamfering conical surface, processes a plurality of circular holes spray-hole (310) that acts as a fuel along circumference on the chamfering conical surface; Fuel inlet 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 hole (303);
The premixed fuel chamber bonnet (304) of a cluster cyclone component (35) is connected to form premixed fuel chamber (307) with the inboard of blades installation matrix (305); The outside of blades installation matrix (305) is fixed with a plurality of blades (306), form between each blade (306) the streamwise uiform section and with the swirler passages that radially becomes angle (31); Each blade (306) has a blind hole (308) vertically, and each blind hole (308) is alignd with the perforate (309) on the blades installation matrix (305); Each blade (306) two side walls is provided with a plurality of premixed fuel spray-holes (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 blind hole (308) on the blade (306) and the premixed fuel spray-hole (32) on the blade (306), finish 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) depends on the air mass flow that enters burner inner liner (2) by swirler passages (31); The size of the radially 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), by this ring flange gas turbine body and the poor lean premixed combustor of gas turbine is linked together.
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 the notch fixing.
The poor lean premixed combustor of described gas turbine, wherein, eddy flow cup (45) entrance is straight length, 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 pass successively casing (1), burner inner liner (2) and eddy flow cup (45), it is inboard that igniter head of igniter (5) is located at the eddy flow cup, discharge fire fuel after the energising.
Maximum characteristics of the present invention are swirler passages along sharf to have many row's fuel orifices on the surface, and these holes link to each other with the premixed fuel passage of nozzle, form the injection channel of premixed fuel.Premixed fuel is finished injection and is carried out blending with air in swirler passages.The advantage one of this premixed fuel spray regime is to have guaranteed that the blending of fuel and air is even, is conducive to reduce the NO of combustion chamber
XDischarging, the 2nd, the mobile impact that is not easy to be subject to upstream incoming flow air flow field fluctuation of fuel, the stability of assurance combustion chamber fuel blending can not cause combustion chamber NO
XThe variation of discharging.
Description of drawings
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 among 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 among Fig. 1.
Fig. 5 is nozzle a cluster cyclone component longitudinal sectional view among Fig. 1.
Fig. 6 is eddy flow cup sub-assembly longitudinal sectional view among Fig. 1.
Primary clustering symbol description in the accompanying drawing:
1 casing;
2 burner inner liners, 20 burner inner liner top covers, 201 burner inner liner latter ends, the cylindrical section in the 202 conical sections outside, 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, the outlet of 24 burner inner liners, the cylindrical shell of 25 burner inner liners, aperture around the 26 burner inner liner top cover center macropores, 27 burner inner liner top cover center macropores, the inboard annulus of 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 swivel nozzle bodies, 35 a cluster cyclone components, 36 cyclone mounting nuts, 37 cyclones are installed pad, 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 are installed matrix, 306 swirler blades, 307 cyclone premixed fuel chambeies, 308 swirler blades blind holes, perforate on the 309 blades installation matrixes, 310 fuel nozzle spray-holes on duty;
4 eddy flow cup sub-assemblies, 41 eddy flow cup entrances, the outlet of 42 eddy flow cups, 43 eddy flow cup mount pads, 44 eddy flow cup mount pad screw holes, 45 eddy flow cups, 46 igniter jacks;
5 igniters; Two strands of passages of 6 annulars; 7 studs; 8 pads; 9 nuts; 10 packing rings; 11 circular holes; 12 ring flanges; 13 casing end cap center macropores; 14 screw holes; 15 blind holes; 16 through holes; 17 igniter mount pads; 18 screws.
The specific embodiment
Technical problem to be solved by this invention is to improve the premixed fuel of the poor lean premixed combustor of gas turbine and the mixing effect of air, reduces NO
XDischarging.
Technical scheme of the present invention is achieved in that
A kind of tubular gas-turbine combustion chamber of operating on gaseous fuel comprises casing, burner inner liner, nozzle a cluster cyclone component, eddy flow cup sub-assembly and igniter totally 5 parts.
The combustion chamber is divided into two-layer generally, and the outside is casing, and the inboard is burner inner liner.Form two strands of passages of air between casing and the burner inner liner, casing afterbody wall has a large amount of circular holes, enters two strands of passages from the air of compressor 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, mainly betides burner inner liner and cyclone with the pitot loss that guarantees the combustion chamber, rather than these circular holes on casing.These circular holes play carry out the effect of rectification from the air of compressor, eliminate the even property of circumferential asymmetry of incoming flow air and the disturbance that roll into a ball in large whirlpool, guarantee the uniformity of burner inner liner air inlet, thereby the outlet temperature that can improve the combustion chamber distribute.The casing middle part is welded with a ring flange, by this ring flange combustion chamber and gas turbine body is assembled together.Casing end cap center has a macropore, is used for inserting nozzle.From the center macropore four screw holes that are uniformly distributed along the circumference are outwards arranged, be used for being screwed into the screw of fixed nozzle.Four blind holes that are uniformly distributed along the circumference are outwards arranged again, and the outside is four through holes near blind hole, is used for inserting the studs that connects burner inner liner and casing.Studs is used with the nut of check washer and is fixed after passing end cap from the end cap inboard, and check washer is pounded into blind hole with instrument, prevents nut loosening.The casing side has a hole and is welded with an igniter mount pad near end cap, is used for the mounting points firearm.
Burner inner liner is a tube-like thin-wall component, comprises top cover and cylindrical shell.The top cover center has a macropore, is used for installing the eddy flow cup.Have 4 apertures along circumference around the macropore, be used for inserting studs and fix eddy flow cup sub-assembly; Remainder has a large amount of air admission holes, and portion of air enters burner inner liner by these holes and is used for cooling eddy flow cup.Cylindrical shell is welded by multistage, and wherein the first paragraph side is having a hole corresponding to casing igniter mount pad position, is used for the insertion point firearm.Except first paragraph, each section upstream extremity is opened a large amount of apertures along circumference, and is welded with an annulus in the inboard, and forms a circular passage between the cylindrical shell, and the air that enters by cylindrical shell wall aperture flows through this circular passage formation air film cooling, reduces the flame tube wall surface temperature.Have 4～6 macropores at second from the bottom section mid portion along circumference, the air that is entered by this round reduces its temperature with high-temperature flue gas blending from head.The burner inner liner final stage is punctured into a direct tube section that diameter is less by direct tube section through a conical section, as the outlet of burner inner liner, inserts the spiral case that is used for being connected combustion chamber and turbine when assembling with gas turbine.The conical section outside is welded with a cylindrical section, for increasing the outlet section rigidity.
Nozzle a cluster cyclone component is comprised of nozzle body, a cluster cyclone component, nozzle on duty, mounting nuts and pad.
Nozzle body comprises fuel inlet tube on duty, premixed fuel inlet tube and fuel road disrance sleeve.
Fuel road disrance sleeve is the pipe fitting that an end has been processed step, and it welds together with fuel inlet tube on duty first, and then welds with the premixed fuel inlet tube, forms an annulus access, and from the side perforate of premixed fuel enters this annular space, flows to a cluster cyclone component.
The a cluster cyclone component comprises that premixed fuel chamber bonnet, blades installation matrix and several swirler blades form.Premixed fuel chamber bonnet and blades installation matrix are welded together to form the premixed fuel chamber, and swirler blades is welded on the blades installation matrix.Flow losses are reduced at each Edge Blend angle of swirler blades.Swirler blades is opened a blind hole vertically, and perforate is alignd with the perforate on the blades installation matrix, axially opens some apertures in the blade both sides along blade center hole, as the premixed fuel spray-hole.The premixed fuel spray-hole guarantees the uniformity of fuel distribution along sharf to uniform.Premixed fuel leads to the axial blind hole on the blade again after the premixed fuel inlet tube enters annular space, premixed fuel chamber successively, the premixed fuel spray-hole by blade side enters swirler passages at last, finishes 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, realize sealing by the pad of tightening between this screw thread compression fuel road disrance sleeve and the premixed fuel chamber bonnet, prevent the premixed fuel leakage.
Processing several (identical with blade quantity) shallow slot identical with the leaf cross-section shape in the blades installation matrix outside embeds blade wherein during welding, makes things convenient for the blade location, guarantees the leaf position precision.After blade is welded on the matrix, form the streamwise uiform section and with the passage that radially forms an angle.This passage passes through for the air that enters head of combustion chamber, realizes the blending of premixed fuel and air, and forms eddy flow in the downstream.
Nozzle on duty is positioned at the nozzle assembly for fluid center, and an end machining internal thread matches with fuel inlet tube on duty.Port of export outside chamfering is processed some circular holes spray-hole that acts as a fuel along circumference on the chamfering conical surface, circle hole centreline and nozzle center form an angle.
Be threaded connection between nozzle body and the cyclone, first two parts taken apart when assembling with casing, nozzle body is inserted by the casing end cap outside, cyclone is then packed into from the end cap inboard and is assembled together with nozzle body.
Insert from the end cover of combustion chamber outside after first mounting nuts, nozzle on duty and nozzle body being assembled during with nozzle a cluster cyclone component and casing assembling, and with four screws mounting nuts is fixed on the end cap, can regulate the degree of depth that nozzle inserts the combustion chamber by the rotary nozzle body, convenience cooperates with burner inner liner.Then in the end cap inboard a cluster cyclone component is installed on the nozzle body.
Eddy flow cup sub-assembly is comprised of eddy flow cup and eddy flow cup mount pad, and both weld together.The eddy flow cup mount pad outside has four screwed holes along circumference.Eddy flow cup side has a hole in the position that penetrates the hole corresponding to the burner inner liner igniter, and igniter inserts and thus in this position discharge fire fuel.The eddy flow cup sub-assembly top cover center macropore of packing in the burner inner liner inboard, place a pad in the top cover outside, studs passes the screwed hole of pad, burner inner liner top cover and eddy flow cup sub-assembly successively, by tightening studs eddy flow cup sub-assembly is fixed on the burner inner liner top cover.
Igniter is fixed on the mount pad of casing by screw thread, and passes successively casing, burner inner liner and eddy flow cup, and igniter head is sudden and violent to leak in eddy flow cup inboard discharge fire fuel after the energising.
Described nozzle a cluster cyclone component comprises premix two-way fuel on duty injection channel.Fuel on duty road sprays into through nozzle on duty in nozzle center, and its effect is to be formed centrally diffusion combustion flame in cyclone, realizes the smooth combustion under the underload.The premixed fuel road is in the outside, and links to each other with the radial swirler blade center hole.Open some premixed fuel spray-holes that communicate with centre bore in the blade two sides, premixed fuel sprays into swirler passages by described premixed fuel spray-hole.The premixed fuel spray-hole has guaranteed the uniformity of fuel distribution along sharf to uniform.Air flow to accelerate after entering swirler passages, is not easy to be subject to the impact of the Air Flow fluctuation of upstream incoming flow, thereby has guaranteed the stability of fuel and air blending.Radial swirler is uiform section area passage, and an end and described nozzle body pass through thread connection together, and the other end is fitted with the eddy flow cup mount pad that is installed on the burner inner liner top cover, forms the radial swirler passage of sealing.Premixed fuel is realized even blending with the air through cyclone in the flow process in swirler passages, then enter the cyclone cup that is installed in the 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 the recirculating zone retention flame.
Air from compressor enters two strands of passages from the casing rear end, flow from back to front, and the cyclone by the blending hole on the burner inner liner, film cooling holes and head enters burner inner liner successively, and with convection type the burner inner liner wall is cooled off in this process.Air capacity through film cooling holes is determined according to the operating temperature of flame temperature and the permission of burner inner liner wall, determines that through air capacity primary zone mean temperature and the fuel quantity as required of cyclone remaining air all enters by blending hole.
Burner inner liner and casing are linked together by 4 studs.One end of studs passes the screw hole that a pad pad, burner inner liner top cover are screwed into eddy flow cup mount pad.The other end stretches out the casing outside, fixes with nut.Nozzle a cluster cyclone component is fixed on the casing, and can regulate insertion depth until the end face of swirler blades withstands on the eddy flow cup mount pad by the swivel nozzle body.
Below in conjunction with accompanying drawing the present invention is described in detail.The concrete structure of monotubular shape of the present invention combustion chamber mainly comprises five parts as shown in Figure 1: 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, the circular hole 11 of offering from casing 1 afterbody from the air of compressor enters the two strands of passages 6 of annular between casing 1 and the burner inner liner 2 and flows to head, enters burner inner liner 2 through blending hole 21, cylindrical shell film cooling holes 22 and swirler passages 31 on the burner inner liner 2 successively.Fuel divides two-way to spray into.About 90% fuel sprays into swirler passages 31 by the perforate 32 of swirler blades wall, and carries out blending with air in swirler passages 31; About 10% fuel sprays into from the nozzle on duty 33 that is positioned at the cyclone center in addition, forms diffusion combustion, is used for the retention 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 exports the backflow of 42 formation centers at the eddy flow cup under the cyclonic action of cyclone, guarantees the stable of burning.The high-temperature flue gas that eddy flow cup outlet 42 produces flows out subsequently with from exporting 24 from burner inner liner after the air blending of 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 passes a pad 8, 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 the casing outside, and is fixing with nut 9 and packing ring 10.Nozzle a cluster cyclone component 3 is fixed on the casing 1, and can regulate insertion depths until the end face of swirler blades withstands on the eddy flow cup mount pad 43 by swivel nozzle body 34.
(2) casing
Fig. 2 A and Fig. 2 B are case structure figure.Casing (1) afterbody wall has a large amount of circular holes 11, enters two strands of passages from the air of compressor by these circular holes.The casing middle part is welded with a ring flange 12, by this ring flange combustion chamber and gas turbine body is assembled together.Casing end cap center macropore 13 is used for inserting nozzle.From the center macropore four screw holes that are uniformly distributed along the circumference 14 are outwards arranged, be used for being screwed into the screw 18 of fixed nozzle.Four blind holes that are uniformly distributed along the circumference 15 are outwards arranged again, and the outside is four through holes 16 near blind hole, is used for inserting the studs 7 that connects burner inner liner 2 and casing 1.After studs 7 passes end cap from the end cap inboard, use with the nut 9 of check washer 10 and fix, and check washer is pounded into blind hole 15 with instrument, prevent that nut 9 is loosening.The casing side has a hole and is welded with an igniter mount pad 17 near the end cap end, is used for mounting points firearm 5.
(3) burner inner liner
Fig. 3 A and Fig. 3 B are the burner inner liner structure charts.Burner inner liner is a tube-like thin-wall component, comprises top cover 20 and cylindrical shell 25.Top cover 20 centers have a macropore 26, are used for installing the eddy flow cup.Have 4 apertures 27 along circumference around the macropore, be used for inserting studs 7 and fix eddy flow cup sub-assembly 4.Remainder has a large amount of air admission holes 23, and portion of air enters burner inner liner by these holes and is used for cooling eddy flow cup 45.The cylindrical shell 25 of burner inner liner is welded by multistage, and wherein first paragraph 203 sides are having igniter patchhole 204 corresponding to casing igniter mount pad position.Except first paragraph, each section upstream extremity is opened a large amount of apertures 22 along circumference, and is welded with an annulus 28 in the inboard, and forms a circular passage 29 between the cylindrical shell, the air that enters by cylindrical shell wall aperture 22 flows through this circular passage 29 formation air film coolings, reduces the flame tube wall surface temperature.Have 6 blending hole 21 at second from the bottom section mid portion along circumference, the air that is entered by this round reduces its temperature with high-temperature flue gas blending from head.Burner inner liner final stage 201 is punctured into a direct tube section that diameter is less by direct tube section through a conical section, as the outlet of burner inner liner, inserts the spiral case that is used for being connected combustion chamber and turbine when assembling with gas turbine.The conical section outside is welded with a cylindrical section 202, for increasing the outlet section rigidity.
(4) nozzle a cluster cyclone component
Fig. 4, Fig. 5 are respectively nozzle a cluster cyclone component front view and longitudinal sectional view.Nozzle a cluster cyclone component is comprised of with pad 37 nozzle body 34, a cluster cyclone component 35, nozzle on duty 33, mounting nuts 36.
Fuel road disrance sleeve 301 is the pipe fitting that an end has been processed step, it welds together with fuel inlet tube 38 on duty first, and then with premixed fuel inlet tube 39 welding, 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 is welded together to form premixed fuel chamber 307 with blades installation matrix 305.Processing 12 shallow slots identical with the leaf cross-section shape in blades installation matrix 305 outsides embed blade 306 wherein during welding, make things convenient for the blade location, guarantee the leaf position precision.After blade 306 is welded on the matrix 305, form the streamwise uiform section and with the passage 31 that radially forms an angle.This passage passes through for the air that enters head of combustion chamber, realizes the blending of premixed fuel and air, and forms eddy flow in the downstream.Flow losses are reduced at swirler blades 306 each Edge Blend angle.Swirler blades 306 is opened a blind hole 308 vertically, and blind hole 308 is alignd with the perforate 309 on the blades installation matrix, axially respectively opens 5 apertures 32 in the blade both sides along blade center hole, as the premixed fuel spray-hole.Premixed fuel spray-hole 32 guarantees the uniformity of fuel distribution along sharf to uniform.Premixed fuel is after premixed fuel inlet tube 34 enters premixed fuel road annulus access 302, premixed fuel chamber 307 successively, lead to again the axial blind hole 308 on the blade, premixed fuel spray-hole 32 by blade side enters swirler passages 31 at last, finishes 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, realize sealing by the pad 37 of tightening between this screw thread compression fuel road disrance sleeve and the premixed fuel chamber bonnet, prevent the premixed fuel leakage.
(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 comprised of eddy flow cup 45 and eddy flow cup mount pad 43, and both weld together.The eddy flow cup mount pad outside has 4 screw holes 44 along circumference.Eddy flow cup side has a hole 46 in the position that penetrates the hole corresponding to the burner inner liner igniter, and igniter 5 inserts and thus in this position discharge fire fuel.
The eddy flow cup sub-assembly 4 top cover center macropore 26 of packing in burner inner liner 2 inboards, place a pad 8 in the top cover outside, studs 7 passes the screw hole 44 of pad 8, burner inner liner top cover 24 and eddy flow cup sub-assembly successively, by tightening studs 7 eddy flow cup sub-assembly 7 is fixed on the burner inner liner top cover 24.
(6) igniter
Igniter 5 is fixed on the mount pad 17 of casing by screw thread, and passes successively casing 1, burner inner liner 2 and eddy flow cup 45, and it is inboard that igniter head is exposed to the eddy flow cup, discharge fire fuel (seeing Fig. 1) after the energising.
Claims (7)
1. poor lean premixed combustor of gas turbine, its primary structure comprises:
One casing (1), be fixed with burner inner liner (2) in this casing (1), form two strands of passages of air between casing and the burner inner liner, this casing (1) afterbody wall offers some circular holes (11) that pass into air, air from compressor enters 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 flow air and the disturbance that roll into a ball in large whirlpool, and the outlet temperature of improving the combustion chamber distributes;
Casing (1) side is provided with the igniter mount pad (17) for mounting points firearm (5);
The eddy flow cup (45) of reducing is installed in this burner inner liner (2), and 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 the nozzle a cluster cyclone component (3) is fuel inlet tube on duty (38), the top of this fuel inlet tube on duty (38) is nozzle on duty (33), the port of export of nozzle on duty (33) outside is the chamfering conical surface, processes a plurality of circular holes spray-hole (310) that acts as a fuel along circumference on the chamfering conical surface; Fuel inlet 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 hole (303);
The premixed fuel chamber bonnet (304) of a cluster cyclone component (35) is connected to form premixed fuel chamber (307) with the inboard of blades installation matrix (305); The outside of blades installation matrix (305) is fixed with a plurality of blades (306), form between each blade (306) the streamwise uiform section and with the swirler passages that radially becomes angle (31); Each blade (306) has a blind hole (308) vertically, and each blind hole (308) is alignd with the perforate (309) on the blades installation matrix (305); Each blade (306) two side walls is provided with a plurality of premixed fuel spray-holes (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 blind hole (308) on the blade (306) and the premixed fuel spray-hole (32) on the blade (306), finish 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) depends on the air mass flow that enters burner inner liner (2) by swirler passages (31); The size of the radially 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, is provided with a ring flange (12) in the middle part of the casing (1), by this ring flange gas turbine body and the poor lean premixed combustor of gas turbine is linked together.
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, 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 pass successively casing (1), burner inner liner (2) and eddy flow cup (45), it is inboard that igniter head of igniter (5) is located at the eddy flow cup, discharge fire fuel after the energising.
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| CN201210337011.XA CN102878580B (en) | 2012-09-12 | 2012-09-12 | Lean premixed combustion chamber for gas turbine |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201210337011.XA CN102878580B (en) | 2012-09-12 | 2012-09-12 | Lean premixed combustion chamber for gas turbine |
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| CN102878580A true CN102878580A (en) | 2013-01-16 |
| CN102878580B CN102878580B (en) | 2015-04-22 |
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| CN107576502A (en) * | 2017-08-10 | 2018-01-12 | 中国北方发动机研究所(天津) | A kind of turbocharger test platform combustion chamber with mixing section |
| CN107620982A (en) * | 2017-09-25 | 2018-01-23 | 上海泛智能源装备有限公司 | A kind of pre-mixing apparatus and miniature gas turbine |
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| CN114659140A (en) * | 2022-03-21 | 2022-06-24 | 杭州汽轮动力集团有限公司 | Low-emission combustor for fuel classification of gas turbine |
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| CN107576502B (en) * | 2017-08-10 | 2019-11-12 | 中国北方发动机研究所(天津) | A kind of turbocharger test platform combustion chamber with mixing section |
| CN107576502A (en) * | 2017-08-10 | 2018-01-12 | 中国北方发动机研究所(天津) | A kind of turbocharger test platform combustion chamber with mixing section |
| CN107620982A (en) * | 2017-09-25 | 2018-01-23 | 上海泛智能源装备有限公司 | A kind of pre-mixing apparatus and miniature gas turbine |
| CN108317542A (en) * | 2018-01-03 | 2018-07-24 | 南方科技大学 | Cooling structure of aeroengine combustion chamber and aeroengine combustion chamber |
| CN108987765A (en) * | 2018-06-29 | 2018-12-11 | 张家港氢云新能源研究院有限公司 | Heating device in proton exchange film fuel cell electric piling |
| CN108987765B (en) * | 2018-06-29 | 2023-12-15 | 张家港氢云新能源研究院有限公司 | Heating device in proton exchange membrane fuel cell stack |
| CN111911960A (en) * | 2020-08-11 | 2020-11-10 | 新奥能源动力科技（上海）有限公司 | Low nitrogen oxide emission combustion chamber for gas turbine and gas turbine |
| CN112128761A (en) * | 2020-09-21 | 2020-12-25 | 上海齐耀热能工程有限公司 | Immersed low-nitrogen gas combustion device |
| TWI807525B (en) * | 2020-12-11 | 2023-07-01 | 加拿大商迪 梅遜股份有限公司 | burner with fixed blades |
| CN113074367A (en) * | 2021-04-07 | 2021-07-06 | 上海交通大学 | Burner with a burner head |
| CN113091095A (en) * | 2021-05-13 | 2021-07-09 | 中国联合重型燃气轮机技术有限公司 | Gas turbine combustor nozzle and method of premixing fuel and air in the nozzle |
| CN113091094A (en) * | 2021-05-13 | 2021-07-09 | 中国联合重型燃气轮机技术有限公司 | Gas turbine combustor nozzle and method of premixing fuel and air in the 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 |
| CN114659140A (en) * | 2022-03-21 | 2022-06-24 | 杭州汽轮动力集团有限公司 | Low-emission combustor for fuel classification 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 |
| CN115727354A (en) * | 2022-11-11 | 2023-03-03 | 中国航发哈尔滨东安发动机有限公司 | Turbofan engine flame tube structure for aircraft |
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