CN204006116U - The low swirl combustion chamber nozzle of a kind of gas turbine - Google Patents
The low swirl combustion chamber nozzle of a kind of gas turbine Download PDFInfo
- Publication number
- CN204006116U CN204006116U CN201420105251.1U CN201420105251U CN204006116U CN 204006116 U CN204006116 U CN 204006116U CN 201420105251 U CN201420105251 U CN 201420105251U CN 204006116 U CN204006116 U CN 204006116U
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- nozzle
- runner
- center
- hollow ring
- flow channels
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Abstract
The low swirl combustion chamber nozzle of gas turbine, this combustion chamber burner comprises nozzle center's runner, nozzle periphery runner and swirl-flow devices; The wall of nozzle center's runner is hollow ring cartridge.In nozzle center's runner inside, be provided with a plurality of center flow channels fuel nozzles, in nozzle periphery runner, be provided with a plurality of peripheral runner fuel nozzles.Fuel enters from hollow ring cartridge, by center flow channels fuel nozzle and peripheral runner fuel nozzle, enter respectively coaxially arranged nozzle center's runner and nozzle periphery runner, center flow channels air intlet pipe is set on hollow ring cartridge, by control, enter the air capacity of nozzle center's runner, and then the air ratio of Control Nozzle center and peripheral runner, adjust the swirling number of whole nozzle.The utility model is also provided with anti-backfire hollow ring cartridge at hollow ring cartridge rear.The utility model is simple in structure, has reduced nozzle exit pressure loss, has improved fuel blending ability, has anti-backfire function simultaneously.
Description
Technical field
The utility model relates to the low swirl nozzle of a kind of gas-turbine combustion chamber, belongs to gas turbine structure design field.
Background technology
Patent WO2012141982A1 has described the low swirl nozzle that is applied to gas-turbine combustion chamber.As shown in Figure 1, in low swirl nozzle 1, fuel enters by fuel inlet tube 15, and air enters by air intlet pipe 16, and fuel and air are in the interior mixing of Venturi tube 171.Venturi tube 171 downstreams are double-decker, and wherein nozzle center's runner 12 arranges a restriction orifice 172, are evenly arranged a plurality of metering holes 173 on restriction orifice 172; Nozzle periphery runner 13 arranges swirl-flow devices 132, and swirl-flow devices 132 is comprised of a plurality of swirl vanes.The even gaseous mixture in upstream by swirl-flow devices 132 and restriction orifice 172, produces low eddy flow gaseous mixture respectively, enters 174 burnings of burning expansion regions.The flow that enters nozzle center's runner determines by the valid circulation area of restriction orifice, and because hole diameter and the circulation area of restriction orifice are less, so it brings the larger pressure loss.For fuel and air are mixed, Venturi tube 171 axial length L 1 are generally between 150mm～220mm, cause nozzle long, when being used in conjunction with other types nozzle, to installing, bring inconvenience; When tempering phenomenon occurs, this structure, without corresponding self adaptation regulative mode, easily causes damage to parts such as upstream swirl-flow devices, restriction orifices.
Utility model content
In order to solve problems of the prior art, the utility model proposes the low swirl nozzle of a kind of gas-turbine combustion chamber, can effectively reduce the pressure loss of nozzle, increase the mixing capacity of nozzle, rationally reduce nozzle length, the control that reinforcement distributes nozzle center, peripheral runner fuel, reduces the pollutant of combustion chamber, and has function of preventing back-fire.This nozzle arrangements is simple simultaneously, easily processing.
The technical scheme that the utility model adopts is as follows:
The low swirl combustion chamber nozzle of a kind of gas turbine, described combustion chamber burner comprises coaxially arranged nozzle center's runner, nozzle periphery runner and swirl-flow devices, swirl-flow devices is arranged in described nozzle periphery runner, it is characterized in that: the wall of nozzle center's runner is hollow ring cartridge, the top of this hollow ring cartridge is connected with train head lid, fuel enters hollow ring cartridge from outside through train head lid, and the other end stretches into nozzle interior; At least one center flow channels air intlet pipe is set on hollow ring cartridge; In described nozzle center's runner inside, be provided with a plurality of center flow channels fuel nozzles, this center flow channels fuel nozzle one end is connected with hollow ring cartridge internal face, the other end is arranged in nozzle center's runner, and center flow channels fuel nozzle arranges center flow channels propellant spray hole; Described center flow channels air intlet pipe is between train head lid and center flow channels fuel nozzle;
A plurality of peripheral runner fuel nozzles are set in described swirl-flow devices upstream, and this runner fuel nozzle one end, periphery is connected with nozzle outside wall surface, and the other end is connected with hollow ring cartridge; Peripheral runner propellant spray hole is set on peripheral runner fuel nozzle.
Technical characterictic of the present utility model is also: the tail end of described hollow ring cartridge is provided with the anti-backfire hollow ring cartridge of a segment length between 3～8mm; Described anti-backfire hollow ring cartridge is apart from the distance L of the end of hollow ring cartridge
2for 5mm～15mm, the distance L of the end-to-end distance swirl-flow devices of described hollow ring cartridge
3between 100mm～150mm.
The wall thickness of anti-backfire hollow ring cartridge described in the utility model is 0.2～0.5 times of hollow ring fuel tube wall face thickness.
In technique scheme of the present utility model, the number of described center flow channels air intlet pipe is preferably 4～8.
Center flow channels propellant spray described in the utility model hole is evenly arranged or the described center flow channels fuel nozzle wall both sides that are arranged in straggly along the runner radial position of described nozzle center; Described peripheral runner propellant spray hole along the radial position of described nozzle periphery runner be evenly arranged or arranged crosswise in described peripheral runner fuel nozzle wall both sides; Center line and the described combustion chamber burner center line in described peripheral runner propellant spray hole and center flow channels propellant spray hole are 90 °.
Preferably, the quantity of peripheral runner fuel nozzle and swirl-flow devices blade quantity are consistent, or swirl-flow devices blade quantity is the integral multiple of the quantity of peripheral runner fuel nozzle.
Preferably, peripheral runner fuel nozzle is arranged in swirl-flow devices, forms integral structure with swirl vane.
Preferably: center flow channels fuel nozzle is pipe, conical pipe or oval pipe, its axial location and peripheral runner fuel nozzle relative distance are between 0～10mm, and its quantity is 4～8, and its top is connected by a ring pipe.
The utility model compared with prior art has the following advantages and the technique effect of high-lighting: the low swirl nozzle of gas-turbine combustion chamber that the utility model relates to, effective area by center flow channels air intlet pipe is controlled the air capacity that enters nozzle center's runner, and then the air ratio of Control Nozzle center and peripheral runner, adjust the swirling number of whole nozzle; Fuel enters from hollow ring cartridge, flows through center flow channels air intlet pipe, enters respectively center flow channels fuel nozzle and peripheral runner fuel nozzle, mixes with the air of corresponding runner; Hollow ring cartridge is deep into nozzle downstream, and its tail end is provided with anti-backfire hollow ring cartridge, when tempering occurs, burns this region, and premixed combustion is become to diffusion combustion, the vitals such as protection upstream swirl-flow devices, spray nozzle device; In center flow channels fuel nozzle, adopt ring pipe to connect, reduce the vibrations of center flow channels fuel nozzle, reduce the bluff body eddyloss after ring pipe.
Accompanying drawing explanation
Fig. 1 is a low swirl nozzle sketch in prior art.
Fig. 2 provides the structural representation of the low swirl combustion chamber nozzle of gas turbine embodiment for the utility model.
Fig. 3 is schematic perspective view of the present utility model.
The low swirl combustion chamber nozzle of symbol description in figure: 1-; 10-hollow ring cartridge; The tail end of 101-hollow ring cartridge; 102-anti-backfire hollow ring cartridge; The end of 103-hollow ring cartridge; 111-center flow channels air intlet pipe; The peripheral runner air intlet of 112-; 12-nozzle center runner; 121-center flow channels fuel nozzle; 122-ring pipe; 13-nozzle periphery runner; The peripheral runner fuel nozzle of 131-; 132-swirl-flow devices; The peripheral runner fuel jet of 14a-hole; 14b-center flow channels fuel jet hole; 15-fuel inlet tube; 16-air intlet pipe; 171-Venturi tube; 172-restriction orifice; 173-metering hole; The 174-expansion segment that burns; 2-train head lid.
The specific embodiment
Below in conjunction with the drawings and specific embodiments, the utility model is elaborated:
Fig. 2 and Fig. 3 provide the structural representation of the low swirl combustion chamber nozzle of gas turbine embodiment for the utility model.This low swirl combustion chamber nozzle 1 comprises coaxially arranged nozzle center's runner 12, nozzle periphery runner 13 and swirl-flow devices 132, swirl-flow devices 132 is arranged in described nozzle periphery runner 13, the wall of nozzle center's runner 12 is hollow ring cartridge 10, the top of this hollow ring cartridge 10 is connected with train head lid 2, fuel enters hollow ring cartridge from outside through train head lid 2, 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, (in the present embodiment, being provided with four center flow channels air intlet pipes); In described nozzle center runner 12 inside, be provided with a plurality of center flow channels fuel nozzles 121 and (in the present embodiment, be provided with five, and be evenly arranged), each center flow channels fuel nozzle 121 one end is connected with hollow ring cartridge 10 internal faces, the other end is arranged in nozzle center's runner 12, at center flow channels fuel nozzle 121, center flow channels propellant spray hole 14b is set; Described center flow channels air intlet pipe 111 is between train head lid 2 and center flow channels fuel nozzle 121.A plurality of peripheral runner fuel nozzles 131 (embodiment is provided with 12 peripheral runner fuel nozzles) are set in described swirl-flow devices 132 upstreams, peripheral runner fuel nozzle 131 one end are connected with nozzle outside wall surface, and the other end is connected with hollow ring cartridge 10; Peripheral runner propellant spray hole 14a is set on peripheral runner fuel nozzle 131.
Described center flow channels air intlet pipe 111 is arranged on hollow ring cartridge 10, be communicated with outside air and enter nozzle center's runner 12, described center flow channels air intlet pipe 111 positions are in end cap 2 downstreams, the upstream of center flow channels fuel nozzle 121, valid circulation area by control centre's runner air intlet pipe 111 can be controlled the air capacity that enters nozzle center's runner 12 easily, and then control the center of low swirl nozzle, the distribution of peripheral runner air mass flow, and then control the swirling number of whole nozzle;
Described center flow channels fuel nozzle 121 is arranged in nozzle center's runner 12, and one end is connected with hollow ring cartridge 10 internal faces, and center flow channels fuel nozzle 121 arranges center flow channels fuel jet hole 14b.
Another technical scheme of the present utility model is: the tail end 101 of described hollow ring cartridge 10 is provided with the anti-backfire hollow ring cartridge 102 of length between 3～8mm; Described anti-backfire hollow ring cartridge 102 is apart from the distance L of the end 103 of hollow ring cartridge
2for 5mm～15mm; The end 103 of hollow ring cartridge is apart from the distance L of swirl-flow devices 132
3between 100mm～150mm.During normal range of operation; hollow ring cartridge 10 and anti-backfire hollow ring cartridge 102 can bear local operating ambient temperature (being generally less than 700 ℃); when there is tempering (environment temperature is over 1000 ℃); first described anti-backfire hollow ring cartridge 102 is burned, and has protected 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 0.2～0.5 times of hollow ring cartridge 10 wall thickness, guarantees that this region more easily burns out than other regions at hot environment temperature.Or; the material of anti-backfire hollow ring cartridge 102 adopts austenitic stainless steel, and the material in hollow ring cartridge 10 other regions is hastelloy-X, when tempering occurs; anti-backfire hollow ring cartridge 102 more easily burns out than other regions, protection upstream structure.
Another optimal technical scheme of the present utility model is: center flow channels air intlet pipe 111 is 4～8, guarantees the uniformity of center flow channels air intlet air-flow; The inner side of center flow channels fuel nozzle 121 is connected by a ring pipe 122, can reduce the vibrations of center flow channels fuel nozzle, and air can pass through from ring pipe 122 simultaneously, reduces the bluff body eddyloss after ring pipe 122; Center flow channels propellant spray Kong14bYan nozzle center runner 12 radial positions on center flow channels fuel nozzle 121 are evenly arranged or the center flow channels fuel nozzle 121 wall both sides that are arranged in straggly; Peripheral runner propellant spray hole 14a on peripheral runner fuel nozzle 131 along 13 radial positions of nozzle periphery runner be evenly arranged or arranged crosswise in peripheral runner fuel nozzle 131 wall both sides, guarantee when the fuel depth of penetration is not high, still to there is good mixed performance; Center line and the described combustion chamber burner center line of described peripheral runner propellant spray hole 14a and center flow channels propellant spray hole 14b are 90 °.
Another being preferably of the present utility model, the quantity of peripheral runner fuel nozzle 131 and swirl-flow devices 132 blade quantities are consistent, or swirl-flow devices 132 blade quantities are integral multiples of the quantity of peripheral runner fuel nozzle 131.
Embodiment of the present utility model can also be arranged at peripheral runner fuel nozzle 131 in swirl-flow devices 132, form integral structure with swirl vane, the swirl vane being about in swirl-flow devices is made hollow structure, the both sides of swirl vane arrange propellant spray hole and replace outer peripheral runner fuel jet hole, and 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 and peripheral runner fuel nozzle 131 relative distances are between 0～10mm, and its quantity is 4～8.
The course of work of the present utility model is as follows:
Fuel enters from hollow ring cartridge 10, by the center flow channels fuel nozzle 121 and the peripheral runner fuel nozzle 131 that are connected with hollow ring cartridge 10, a part enters nozzle center's runner 12 by the fuel orifice 14 on center flow channels fuel nozzle 121; Another part enters nozzle periphery runner 13 by the propellant spray hole 14 on peripheral runner fuel nozzle 131; An air part enters nozzle periphery runner 13 from peripheral runner air intlet 112, another part enters nozzle center's runner by center flow channels air intlet pipe, air through center flow channels fuel nozzle 121 during with peripheral runner fuel nozzle 131 with the fuel mix formation fuel-air mixture of ejection, the gaseous mixture that fuel-air mixture in nozzle periphery runner 13 is flowed through in swirl-flow devices 132Yu nozzle center runner converges in nozzle downstream and forms low vortex gas-flow, in downstream, burns.By control, enter the fuel-air ratio of described nozzle center runner 12 lower than the fuel-air ratio that enters described nozzle periphery runner 13.Even if the recirculating zone of low swirl nozzle is less, still there is recirculating zone in the center of combustion zone, controls and enter the fuel quantity in recirculating zone, can reduce the high-temperature region in recirculating zone, and then reduce the generation of nitrogen oxide, reduces and pollute.
Claims (8)
1. the low swirl combustion chamber nozzle of gas turbine, described combustion chamber burner comprises coaxially arranged nozzle center's runner (12), nozzle periphery runner (13) and swirl-flow devices (132), swirl-flow devices is arranged in described nozzle periphery runner (13), it is characterized in that: the wall of nozzle center's runner (12) is hollow ring cartridge (10), the top of this hollow ring cartridge (10) is connected with train head lid (2), fuel enters hollow ring cartridge from outside through train head lid (2), and the other end stretches into nozzle interior; At least one center flow channels air intlet pipe (111) is set on hollow ring cartridge (10); In described nozzle center runner (12) inside, be provided with a plurality of center flow channels fuel nozzles (121), center flow channels fuel nozzle (121) one end is connected with hollow ring cartridge (10) internal face, the other end is arranged in nozzle center's runner (12), is provided with center flow channels propellant spray hole (14b) on center flow channels fuel nozzle (121); Described center flow channels air intlet pipe (111) is between train head lid (2) and center flow channels fuel nozzle (121);
In described swirl-flow devices (132) upstream, a plurality of peripheral runner fuel nozzles (131) are set, peripheral runner fuel nozzle (131) one end is connected with nozzle outside wall surface, and the other end is connected with hollow ring cartridge (10); On peripheral runner fuel nozzle (131), be 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, is characterized in that: the tail end of described hollow ring cartridge (101) is provided with the anti-backfire hollow ring cartridge (102) of a segment length between 3～8mm; Described anti-backfire hollow ring cartridge (102) is apart from the distance L of the end (103) of hollow ring cartridge
2for 5mm～15mm, the end of described hollow ring cartridge (103) is apart from the distance L of swirl-flow devices
3between 100mm～150mm.
3. the low swirl combustion chamber nozzle of a kind of gas turbine according to claim 2, is characterized in that: the wall thickness of anti-backfire hollow ring cartridge (102) is 0.2～0.5 times of hollow ring cartridge (10) wall thickness.
4. according to the low swirl combustion chamber nozzle of a kind of gas turbine described in the arbitrary claim of claim 1～3, it is characterized in that: the number of described center flow channels air intlet pipe (111) is 4～8.
5. according to the low swirl combustion chamber nozzle of a kind of gas turbine described in the arbitrary claim of claim 1～3, it is characterized in that: described center flow channels propellant spray hole (14b) is evenly arranged or described center flow channels fuel nozzle (121) the wall both sides that are arranged in straggly along described nozzle center runner (12) radial position; Described peripheral runner propellant spray hole (14a) along described nozzle periphery runner (13) radial position be evenly arranged or arranged crosswise in described peripheral runner fuel nozzle (131) wall both sides; The center line in described peripheral runner propellant spray hole (14a) and center flow channels propellant spray hole (14b) and described combustion chamber burner center line are 90 °.
6. according to the low swirl combustion chamber nozzle of a kind of gas turbine described in the arbitrary claim of claim 1～3, it is characterized in that: the quantity of peripheral runner fuel nozzle (131) and swirl-flow devices (132) blade quantity are consistent, or swirl-flow devices (132) blade quantity is the integral multiple of the quantity of peripheral runner fuel nozzle (131).
7. according to the low swirl combustion chamber nozzle of a kind of gas turbine described in the arbitrary claim of claim 1～3, it is characterized in that: peripheral runner fuel nozzle (131) is arranged in swirl-flow devices (132), form integral structure with swirl vane.
8. according to the low swirl combustion chamber nozzle of a kind of gas turbine described in the arbitrary claim of claim 1～3, it is characterized in that: center flow channels fuel nozzle (121) is pipe, conical pipe or oval pipe, its axial location and peripheral runner fuel nozzle (131) relative distance are between 0～10mm, 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 |
|---|---|---|---|
| CN201420105251.1U CN204006116U (en) | 2014-03-10 | 2014-03-10 | The low swirl combustion chamber nozzle of a kind of gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420105251.1U CN204006116U (en) | 2014-03-10 | 2014-03-10 | The low swirl combustion chamber nozzle of a kind of gas turbine |
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| CN204006116U true CN204006116U (en) | 2014-12-10 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420105251.1U Withdrawn - After Issue CN204006116U (en) | 2014-03-10 | 2014-03-10 | The low swirl combustion chamber nozzle of a kind of gas turbine |
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| CN (1) | CN204006116U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103822231A (en) * | 2014-03-10 | 2014-05-28 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Low-rotational flow combustor nozzle of combustion gas turbine |
| CN107676817A (en) * | 2017-11-16 | 2018-02-09 | 中国航空发动机研究院 | A kind of combustion chamber radial multi-stage swirl nozzle for using fuel gas |
| CN112902227A (en) * | 2021-03-04 | 2021-06-04 | 西北工业大学 | Multi-channel evaporating pipe of combustion chamber of micro engine |
-
2014
- 2014-03-10 CN CN201420105251.1U patent/CN204006116U/en not_active Withdrawn - After Issue
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103822231A (en) * | 2014-03-10 | 2014-05-28 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Low-rotational flow combustor nozzle of combustion gas turbine |
| CN103822231B (en) * | 2014-03-10 | 2017-11-03 | 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 low swirl combustion chamber nozzle of gas turbine |
| CN107676817A (en) * | 2017-11-16 | 2018-02-09 | 中国航空发动机研究院 | A kind of combustion chamber radial multi-stage swirl nozzle for using fuel gas |
| CN107676817B (en) * | 2017-11-16 | 2023-02-28 | 中国航空发动机研究院 | Radial multistage swirl nozzle of combustion chamber for burning gaseous fuel |
| CN112902227A (en) * | 2021-03-04 | 2021-06-04 | 西北工业大学 | Multi-channel evaporating pipe of combustion chamber of micro engine |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: Low-rotational flow combustor nozzle of combustion gas turbine Effective date of registration: 20161104 Granted publication date: 20141210 Pledgee: Tsinghua Holdings Co., Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. Registration number: 2016990000853 |
|
| PLDC | Enforcement, change and cancellation of contracts on pledge of patent right or utility model | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20141210 Effective date of abandoning: 20171103 |
|
| AV01 | Patent right actively abandoned |
Granted publication date: 20141210 Effective date of abandoning: 20171103 |
|
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Date of cancellation: 20191211 Granted publication date: 20141210 Pledgee: Tsinghua Holdings Co., Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. Registration number: 2016990000853 |
|
| PC01 | Cancellation of the registration of the contract for pledge of patent right |