CN103822231B - A kind of low swirl combustion chamber nozzle of gas turbine - Google Patents
A kind of low swirl combustion chamber nozzle of gas turbine Download PDFInfo
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- CN103822231B CN103822231B CN201410084641.XA CN201410084641A CN103822231B CN 103822231 B CN103822231 B CN 103822231B CN 201410084641 A CN201410084641 A CN 201410084641A CN 103822231 B CN103822231 B CN 103822231B
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Abstract
A kind of low swirl nozzle of gas-turbine combustion chamber, the combustion chamber burner includes nozzle center's runner, nozzle periphery runner and swirl-flow devices；The wall of nozzle center's runner is hollow ring cartridge.Multiple center flow channels fuel nozzles are provided with inside nozzle center's runner, multiple peripheral runner fuel nozzles are provided with nozzle periphery runner.Fuel enters from hollow ring cartridge, coaxially arranged nozzle center's runner and nozzle periphery runner is respectively enterd by center flow channels fuel nozzle and peripheral runner fuel nozzle, center flow channels air intlet pipe is set on hollow ring cartridge, by controlling the air capacity into nozzle center's runner, and then the air ratio of nozzle center and peripheral runner is controlled, adjust the swirling number of whole nozzle.The present invention is also provided with anti-backfire hollow ring cartridge in hollow ring cartridge endpiece.The present invention is simple in construction, reduces nozzle exit pressure loss, fuel blending ability is improved, while having the function of anti-backfire.
Description
Technical field
The present invention relates to a kind of low swirl nozzle of gas-turbine combustion chamber, belong to gas turbine structure design field.
Background technology
Prior art discloses a kind of low swirl nozzle applied to gas-turbine combustion chamber.As shown in figure 1, in low eddy flow
In nozzle 1, fuel is entered by fuel inlet tube 15, and air is entered by air intlet pipe 16, and fuel and air are in Venturi tube
Mixed in 171.The downstream of Venturi tube 171 is double-decker, and wherein nozzle center's runner 12 sets a restriction orifice 172, current limliting
Multiple metering holes 173 are evenly arranged on orifice plate 172；Nozzle periphery runner 13 sets swirl-flow devices 132, and swirl-flow devices 132 are by more
Individual swirl vane composition.Upstream homogeneous mixture produces low eddy flow mixing respectively by swirl-flow devices 132 and restriction orifice 172
Gas, burns into burning expansion regions 174.Flow into nozzle center's runner determines by the valid circulation area of restriction orifice,
Because the hole diameter and circulation area of restriction orifice are smaller, therefore it brings the larger pressure loss.To make fuel and air
Well mixed, the axial length L 1 of Venturi tube 171 is generally between 150mm~220mm, causes nozzle long, with other types
When nozzle is used cooperatively, installation is brought inconvenience；When tempering phenomenon occurs, the structure without corresponding automatic adjusument mode,
Easily the parts such as upstream swirl-flow devices, restriction orifice are caused to damage.
The content of the invention
In order to solve problems of the prior art, the present invention proposes a kind of low swirl nozzle of gas-turbine combustion chamber,
The pressure loss of nozzle can be effectively reduced, increases the mixing capacity of nozzle, nozzle length is rationally reduced, strengthened in nozzle
The heart, the control of peripheral runner fuel distribution, reduce the pollutant of combustion chamber, and with function of preventing back-fire.While the nozzle knot
Structure is simple, easy processing.
The technical solution adopted in the present invention is as follows：
A kind of low swirl combustion chamber nozzle of gas turbine, the combustion chamber burner includes coaxially arranged nozzle center and flowed
Road, nozzle periphery runner and swirl-flow devices, swirl-flow devices are arranged in the nozzle periphery runner, it is characterised in that：In nozzle
The wall of heart runner is hollow ring cartridge, and the top of the hollow ring cartridge is connected with train head lid, and fuel is from outside
Enter hollow ring cartridge through train head lid, the other end stretches into nozzle interior；At least one is set on hollow ring cartridge
Individual center flow channels air intlet pipe；Multiple center flow channels fuel nozzles, center stream are provided with inside nozzle center's runner
Road fuel nozzle one end is connected with hollow ring cartridge internal face, and the other end is arranged in nozzle center's runner, center stream
Road fuel nozzle sets center flow channels propellant spray hole；The center flow channels air intlet pipe is in train head lid and center flow channels
Between fuel nozzle；
Multiple peripheral runner fuel nozzles are set in described swirl-flow devices upstream, the peripheral runner fuel nozzle one end with
Outer nozzle wall face is connected, and the other end is connected with hollow ring cartridge；Peripheral runner is set on peripheral runner fuel nozzle
Propellant spray hole.
The technical characteristic of the present invention is also resided in：The tail end of the hollow ring cartridge provided with a segment length 3~8mm it
Between anti-backfire hollow ring cartridge；The distance of the end of the anti-backfire hollow ring cartridge away from hollow ring cartridge
L2For 5mm~15mm, the end of the hollow ring cartridge is away from swirl-flow devices apart from L3Between 100mm~150mm.
The wall thickness of anti-backfire hollow ring cartridge of the present invention is hollow ring fuel tube wall face thickness
0.2~0.5 times；Or the material of anti-backfire hollow ring cartridge is austenitic stainless steel.
In the above-mentioned technical proposal of the present invention, the number of the center flow channels air intlet pipe is preferably 4~8.
Center flow channels propellant spray hole of the present invention is evenly arranged or straggly along nozzle center's runner radial position
It is arranged in the center flow channels fuel nozzle wall both sides；The peripheral runner propellant spray hole is along the nozzle periphery runner footpath
It is evenly arranged to position or arranged crosswise is in the peripheral runner fuel nozzle wall both sides；The peripheral runner propellant spray hole
And the center line in center flow channels propellant spray hole and the combustion chamber burner center line are in 90 °.
Preferably, the quantity of peripheral runner fuel nozzle is consistent with swirl-flow devices blade quantity, or swirl-flow devices leaf
Piece quantity is the integral multiple of the quantity of peripheral runner fuel nozzle.
Preferably, peripheral runner fuel nozzle is arranged in swirl-flow devices, and integral structure is constituted with swirl vane.
Preferably：Center flow channels fuel nozzle is pipe, conical pipe or oval pipe, and its axial location fires with peripheral runner
Jet pipe relative distance is expected between 0~10mm, and its quantity is 4~8, and its top is connected by a ring pipe.
The present invention has the technique effect of advantages below and high-lighting compared with prior art：Combustion gas wheel of the present invention
The low swirl nozzle in machine combustion chamber, enters the air of nozzle center's runner by the effective area control of center flow channels air intlet pipe
Amount, and then the air ratio of nozzle center and peripheral runner is controlled, adjust the swirling number of whole nozzle；Fuel is from hollow ring fuel
Pipe enters, and flows through center flow channels air intlet pipe, respectively enters center flow channels fuel nozzle and peripheral runner fuel nozzle, and right
The air of runner is answered to mix；Hollow ring cartridge is deep into nozzle downstream, and its tail end is provided with anti-backfire hollow ring fuel
Pipe, when tempering occurs, burns the region, and premixed combustion is changed into diffusion combustion, protects the weight such as upstream swirl-flow devices, spray nozzle device
Want part；Using ring pipe connection in center flow channels fuel nozzle, the vibrations of center flow channels fuel nozzle are reduced, ring pipe is reduced
Bluff body eddyloss afterwards.
Brief description of the drawings
Fig. 1 is one low swirl nozzle sketch in the prior art.
Fig. 2 provides the structural representation of the low swirl combustion chamber nozzle embodiments of gas turbine for the present invention.
Fig. 3 is schematic perspective view of the invention.
Symbol description in figure：The low swirl combustion chamber nozzles of 1-；10- hollow ring cartridges；101- hollow ring cartridges
Tail end；102- anti-backfire hollow ring cartridges；The end of 103- hollow ring cartridges；111- center flow channels air intlets
Pipe；112- peripheries runner air intlet；12- nozzle center runner；121- center flow channels fuel nozzles；122- ring pipes；13- sprays
Mouth periphery runner；131- peripheries runner fuel nozzle；132- swirl-flow devices；14a- peripheries runner fuel jet hole；14b- centers
Runner fuel jet hole；15- fuel inlet tubes；16- air intlet pipes；171- Venturi tubes；172- restriction orifices；173- current limlitings
Hole；174- burning expansion segments；2- train head lids.
Embodiment
The present invention is elaborated with specific embodiment below in conjunction with the accompanying drawings：
Fig. 2 and Fig. 3 provides the structural representation of the low swirl combustion chamber nozzle embodiments of gas turbine for Fig. 2 for the present invention.
The low swirl combustion chamber nozzle 1 includes coaxially arranged nozzle center's runner 12, nozzle periphery runner 13 and swirl-flow devices 132,
Swirl-flow devices 132 are arranged in the nozzle periphery runner 13, and the wall of nozzle center's runner 12 is hollow ring cartridge 10,
The top of the hollow ring cartridge 10 is connected with train head lid 2, and fuel enters hollow ring fuel from the outside through train head lid 2
Pipe, the other end stretches into nozzle interior, separates nozzle center's runner 12 and nozzle periphery runner 13.
At least one center flow channels air intlet pipe 111 is set on hollow ring cartridge 10, (is provided with the present embodiment
Four center flow channels air intlet pipes)；Multiple center flow channels fuel nozzles 121 are provided with inside nozzle center's runner 12
(five are provided with the present embodiment, and is evenly arranged), each one end of center flow channels fuel nozzle 121 and hollow ring cartridge 10
Internal face is connected, and the other end is arranged in nozzle center's runner 12, sets center flow channels to fire in center flow channels fuel nozzle 121
Expect spray orifice 14b；The center flow channels air intlet pipe 111 is between train head lid 2 and center flow channels fuel nozzle 121.
Multiple peripheral runner fuel nozzles 131 are set in the described upstream of swirl-flow devices 132, and (embodiment is provided with 12 peripheral runner combustions
Expect jet pipe), peripheral one end of runner fuel nozzle 131 is connected with outer nozzle wall face, and the other end is connected with hollow ring cartridge 10
It is logical；Peripheral runner propellant spray hole 14a is set on peripheral runner fuel nozzle 131.
The center flow channels air intlet pipe 111 is arranged on hollow ring cartridge 10, and connection outside air enters spray
Mouth center flow channels 12, the position of center flow channels air intlet pipe 111 is in the downstream of end cap 2, center flow channels fuel nozzle 121
Upstream, can easily control to enter nozzle center's stream by the valid circulation area of control centre's runner air intlet pipe 111
The air capacity in road 12, and then the center of low swirl nozzle, peripheral runner air mass flow distribution are controlled, and then control whole nozzle
Swirling number；
The center flow channels fuel nozzle 121 is arranged in nozzle center's runner 12, one end and hollow ring cartridge 10
Internal face is connected, and center flow channels fuel nozzle 121 sets center flow channels fuel jet hole 14b.
The present invention another technical scheme be：The tail end 101 of the hollow ring cartridge 10 be provided with length 3~
Anti-backfire hollow ring cartridge 102 between 8mm；The anti-backfire hollow ring cartridge 102 is away from hollow ring cartridge
End 103 apart from L2For 5mm~15mm；The end 103 of hollow ring cartridge is away from swirl-flow devices 132 apart from L3
Between 100mm~150mm.During normal range of operation, hollow ring cartridge 10 and anti-backfire hollow ring cartridge 102 can be with
Local operating ambient temperature (being generally less than 700 DEG C) is born, it is described anti-when tempering (environment temperature is more than 1000 DEG C)
Tempering hollow ring cartridge 102 is burned first, protects nozzle upstream device especially swirl-flow devices 132, peripheral runner
Fuel nozzle 131 and center flow channels fuel nozzle 121.The wall thickness of anti-backfire hollow ring cartridge 102 is generally hollow
0.2~0.5 times of the wall thickness of annular fuel pipe 10, it is ensured that the region is easier to burn under high ambient temperatures than other regions
It is bad.Or, the material of anti-backfire hollow ring cartridge 102 uses austenitic stainless steel, other areas of hollow ring cartridge 10
The material in domain is hastelloy-X, and when tempering occurs, anti-backfire hollow ring cartridge 102 is easier to burn out than other regions,
Protect upstream structure.
The present invention another optimal technical scheme be：Center flow channels air intlet pipe 111 is 4~8, it is ensured that center flow channels
The uniformity of air intlet air-flow；The inner side of center flow channels fuel nozzle 121 is connected by a ring pipe 122, in can reducing
The vibrations of heart runner fuel nozzle, while air can pass through from ring pipe 122, the bluff body eddyloss after reduction ring pipe 122；
Center flow channels propellant spray hole 14b on center flow channels fuel nozzle 121 is evenly arranged along the radial position of nozzle center's runner 12
Or straggly it is arranged in the wall both sides of center flow channels fuel nozzle 121；Peripheral runner fuel spray on peripheral runner fuel nozzle 131
Orifice 14a is evenly arranged along the radial position of nozzle periphery runner 13 or arranged crosswise is in the peripheral wall two of runner fuel nozzle 131
Side, it is ensured that still there is good mixed performance when the fuel depth of penetration is not high；The peripheral runner propellant spray hole
14a and center flow channels propellant spray hole 14b center line are in 90 ° with the combustion chamber burner center line.
The another of the present invention is preferably that quantity and the blade quantity of swirl-flow devices 132 of peripheral runner fuel nozzle 131 are kept
Unanimously, or the blade quantity of swirl-flow devices 132 is the integral multiple of the quantity of peripheral runner fuel nozzle 131.
Peripheral runner fuel nozzle 131 can also be arranged in swirl-flow devices 132 by embodiments of the present invention, with eddy flow
Blade constitutes integral structure, i.e., the swirl vane in swirl-flow devices is made into hollow structure, and the both sides of swirl vane set combustion
Expect that spray orifice replaces peripheral runner fuel jet hole, swirl vane is connected with hollow ring cartridge.
Center flow channels fuel nozzle 121 is pipe, conical pipe or oval pipe, and its axial location sprays with peripheral runner fuel
The relative distance of pipe 131 is between 0~10mm, and its quantity is 4~8.
The course of work of the present invention is as follows：
Fuel enters from hollow ring cartridge 10, passes through the center flow channels fuel being connected with hollow ring cartridge 10
Jet pipe 121 and peripheral runner fuel nozzle 131, a part is entered by the fuel orifice 14 on center flow channels fuel nozzle 121
Enter nozzle center's runner 12；Another part enters nozzle periphery by the propellant spray hole 14 on peripheral runner fuel nozzle 131
Runner 13；An air part enters nozzle periphery runner 13 from peripheral runner air intlet 112, and another part passes through center flow channels
Air intlet pipe enters nozzle center's runner, when air is by center flow channels fuel nozzle 121 and peripheral runner fuel nozzle 131
The fuel-air mixture being mixed to form with the fuel of ejection in fuel-air mixture, nozzle periphery runner 13 flows through eddy flow dress
Put 132 to converge to form low vortex gas-flow in nozzle downstream with the gaseous mixture in nozzle center's runner, burnt in downstream.Pass through
The fuel-air ratio that control enters nozzle center's runner 12 is less than the fuel-air for entering the nozzle periphery runner 13
Ratio.Even if the recirculating zone of low swirl nozzle is smaller, the center of combustion zone still suffers from recirculating zone, and control enters in recirculating zone
Fuel quantity, can reduce the high-temperature region in recirculating zone, and then reduce the generation of nitrogen oxides, reduction pollution.
Claims (8)
1. a kind of low swirl combustion chamber nozzle of gas turbine, the combustion chamber burner includes coaxially arranged nozzle center's runner
(12), nozzle periphery runner (13) and swirl-flow devices (132), swirl-flow devices are arranged in the nozzle periphery runner (13), its
It is characterised by：The wall of nozzle center's runner (12) is hollow ring cartridge (10), the top of the hollow ring cartridge (10)
End is connected with train head lid (2), and the hollow ring cartridge other end stretches into nozzle interior, and fuel is from the outside through train head lid (2)
Into hollow ring cartridge；At least one center flow channels air intlet pipe (111) is set on hollow ring cartridge (10)；
Multiple center flow channels fuel nozzles (121), center flow channels fuel nozzle (121) are provided with inside nozzle center's runner (12)
One end is connected with hollow ring cartridge (10) internal face, and the other end is arranged in nozzle center's runner (12), in center stream
Road fuel nozzle (121) is provided with center flow channels propellant spray hole (14b)；The center flow channels air intlet pipe (111) is in
Between train head lid (2) and center flow channels fuel nozzle (121)；
In described swirl-flow devices (132) upstream, multiple peripheral runner fuel nozzles (131), peripheral runner fuel nozzle are set
(131) one end is connected with outer nozzle wall face, and the other end is connected with hollow ring cartridge (10)；In peripheral runner fuel nozzle
(131) provided with peripheral runner propellant spray hole (14a).
2. the low swirl combustion chamber nozzle of a kind of gas turbine according to claim 1, it is characterised in that：The hollow ring
The tail end (101) of cartridge is provided with anti-backfire hollow ring cartridge (102) of the segment length between 3~8mm；It is described to prevent back
End (103) of the fiery hollow ring cartridge (102) away from hollow ring cartridge apart from L2It is described hollow for 5mm~15mm
The end (103) of annular fuel pipe is away from swirl-flow devices apart from L3Between 100mm~150mm；Anti-backfire hollow ring fuel
The wall thickness for managing (102) is 0.2~0.5 times of hollow ring cartridge (10) wall thickness.
3. the low swirl combustion chamber nozzle of a kind of gas turbine according to claim 2, it is characterised in that：Anti-backfire hollow ring
The material of shape cartridge (102) is austenitic stainless steel.
4. a kind of low swirl combustion chamber nozzle of gas turbine according to claims 1 to 3 any claim, its feature exists
In：The number of the center flow channels air intlet pipe (111) is 4~8.
5. a kind of low swirl combustion chamber nozzle of gas turbine according to claims 1 to 3 any claim, its feature exists
In：The center flow channels propellant spray hole (14b) is evenly arranged or cloth straggly along nozzle center's runner (12) radial position
It is placed in center flow channels fuel nozzle (121) the wall both sides；The peripheral runner propellant spray hole (14a) is along outside the nozzle
Enclose that runner (13) radial position is evenly arranged or arranged crosswise is in peripheral runner fuel nozzle (131) the wall both sides；It is described
The center line in peripheral runner propellant spray hole (14a) and center flow channels propellant spray hole (14b) and the combustion chamber burner center
Line is in 90 °.
6. a kind of low swirl combustion chamber nozzle of gas turbine according to claims 1 to 3 any claim, its feature exists
In：The quantity of peripheral runner fuel nozzle (131) is consistent with swirl-flow devices (132) blade quantity, or swirl-flow devices (132)
Blade quantity is the integral multiple of the quantity of peripheral runner fuel nozzle (131).
7. a kind of low swirl combustion chamber nozzle of gas turbine according to claims 1 to 3 any claim, its feature exists
In：Peripheral runner fuel nozzle (131) is arranged in swirl-flow devices (132), and integral structure is constituted with swirl vane.
8. a kind of low swirl combustion chamber nozzle of gas turbine according to claims 1 to 3 any claim, its feature exists
In：Center flow channels fuel nozzle (121) is pipe, conical pipe or oval pipe, its axial location and peripheral runner fuel nozzle
(131) relative distance is between 0~10mm, and its quantity is 4~8, and its top is connected by a ring pipe (122).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410084641.XA CN103822231B (en) | 2014-03-10 | 2014-03-10 | A kind of low swirl combustion chamber nozzle of gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410084641.XA CN103822231B (en) | 2014-03-10 | 2014-03-10 | A kind of low swirl combustion chamber nozzle of gas turbine |
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| Publication Number | Publication Date |
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| CN103822231A CN103822231A (en) | 2014-05-28 |
| CN103822231B true CN103822231B (en) | 2017-11-03 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201410084641.XA Active CN103822231B (en) | 2014-03-10 | 2014-03-10 | A kind of low swirl combustion chamber nozzle of gas turbine |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104154566B (en) * | 2014-07-08 | 2018-03-23 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | gas turbine dual fuel nozzle structure |
| CN104373963B (en) * | 2014-10-28 | 2016-04-27 | 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 gas-turbine combustion chamber centerbody fluting swirl nozzle |
| CN104456624B (en) * | 2014-11-11 | 2017-08-04 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | The air intake structure of gas turbine fuel nozzles |
| CN104456625B (en) * | 2014-11-11 | 2017-11-07 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | The air intake structure of gas turbine fuel nozzles |
| 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 |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7028483B2 (en) * | 2003-07-14 | 2006-04-18 | Parker-Hannifin Corporation | Macrolaminate radial injector |
| EP2213938A2 (en) * | 2009-02-03 | 2010-08-04 | General Electric Company | Combustion system burner tube |
| WO2012141982A1 (en) * | 2011-04-13 | 2012-10-18 | The Regents Of The University Of California | Natural draft low swirl burner |
| CN103140715A (en) * | 2010-09-30 | 2013-06-05 | 西门子公司 | Burner for a gas turbine |
| CN204006116U (en) * | 2014-03-10 | 2014-12-10 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | The low swirl combustion chamber nozzle of a kind of gas turbine |
-
2014
- 2014-03-10 CN CN201410084641.XA patent/CN103822231B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7028483B2 (en) * | 2003-07-14 | 2006-04-18 | Parker-Hannifin Corporation | Macrolaminate radial injector |
| EP2213938A2 (en) * | 2009-02-03 | 2010-08-04 | General Electric Company | Combustion system burner tube |
| CN103140715A (en) * | 2010-09-30 | 2013-06-05 | 西门子公司 | Burner for a gas turbine |
| WO2012141982A1 (en) * | 2011-04-13 | 2012-10-18 | The Regents Of The University Of California | Natural draft low swirl burner |
| CN204006116U (en) * | 2014-03-10 | 2014-12-10 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | The low swirl combustion chamber nozzle of a kind of gas turbine |
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| CN103822231A (en) | 2014-05-28 |
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Effective date of registration: 20200122 Address after: 102209 Beijing Changping District in the future of the national electric investment group Park in the future science city south of Beijing Patentee after: China United heavy-duty gas turbine technology Co., Ltd. Address before: 100084 No. 8, building 1, No. 1001, Zhongguancun East Road, Beijing, Haidian District Patentee before: Beijing Huatsing Gas Turbine & IGCC Technology Co.,Ltd. |