CN203595144U - Nozzle of dual-fuel combustion chamber of combustion gas turbine - Google Patents
Nozzle of dual-fuel combustion chamber of combustion gas turbine Download PDFInfo
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- CN203595144U CN203595144U CN201320824748.4U CN201320824748U CN203595144U CN 203595144 U CN203595144 U CN 203595144U CN 201320824748 U CN201320824748 U CN 201320824748U CN 203595144 U CN203595144 U CN 203595144U
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Abstract
The utility model provides a nozzle of a dual-fuel combustion chamber of a combustion gas turbine, and belongs to the technical field of combustion gas turbines. The nozzle comprises an axial center fuel channel, a peripheral axial annular fuel channel, a peripheral axial annular diluent gas channel, a first level peripheral radial annular air channel and a second level peripheral radial annular air channel, wherein the peripheral axial annular fuel channel is coaxial with the axial center fuel channel. The nozzle is divided into two levels to supply fresh air to the head of the combustion chamber, a diluent is divided into three paths, one path is supplied to fuel, one path is supplied to first level air, and another path is supplied to second level air, the proportion of the three paths of the diluent can be adjusted according to the performance optimized result of the combustion chamber, the fuel has enough air for combustion supporting, and therefore good balance of efficient combustion and reduction of the temperature of flames is achieved; after being well mixed with the fuel and the air, the diluent flows into a flame tube to participate in combustion, and therefore the internal flow field of the combustion chamber can not be disturbed due to the addition of the diluent, and combustion stability and good outlet temperature distribution are guaranteed.
Description
Technical field
The utility model relates to a kind of gas-turbine combustion chamber nozzle, relates in particular to and can use dual-fuel low-pollution burning chamber of gas turbine nozzle.
Background technology
In the current energy resource structure of China, adopt the thermal power generation of traditional coal combustion technology to occupy most shares.But this traditional generation technology exists generating efficiency low, pollutant emission high (especially NOx discharge), expends the shortcomings such as freshwater resources are many.IGCC (integrated gasification combined cycle for power generation system) is as a kind of novel " green " coal combustion technology, for the clean and effective utilization of coal provides a kind of new approach.
Gas turbine in IGCC system, the medium-Btu syngas that adopts gasification furnace to produce is fuel, and the pressure-air transporting with compressor carries out rapid mixing and burning in combustion chamber, and the air-flow of HTHP does work through turbine, and then drive motor generating.Due to synthesis gas, (Main Ingredients and Appearance is CO and H
2) be different from conventional fuel, so in gas-turbine combustion chamber common adopted as diffusion combustion and premixed combustion technology all no longer applicable.Therefore, need, according to the feature of IGCC system and synthesis gas propellant composition, develop more applicable combustion with reduced pollutants technology.
In synthesis gas, main component is CO and H
2, the flame propagation velocity that it is too high, too high adiabatic flame temperature and wide Flammability limits and blast border, making diffusion combustion mode is best combustion strategy.But, while adopting diffusion combustion mode, also bring the intrinsic shortcoming of diffusion combustion mode, in combustion zone, forever there is the flame front of stoichiometric ratio, too high peak flame temperature, will greatly impel NOx to generate fast.For head it off, people attempt diluent, as nitrogen (N
2), steam (H
2and carbon dioxide (CO O)
2) etc. inert gas, this significantly reduces combustion zone peak flame temperature to be injected into combustion zone, thus reduce pollutant emission.For injecting diluent, one of method is to adopt outside fuel dilution in advance, but this need to purchase extras, therefore in engineering and be of little use; And while adopting air steam dilution, diluent on the one hand can obstruct airflow road, can reduce the concentration of oxidant simultaneously, and then be difficult to maintain efficient combustion; And while adopting fuel steam dilution, this can significantly reduce unit volume fuel value, can cause equally efficiency of combustion to be difficult to improve; Diluent is directly sprayed into combustion zone and can upset combustion chamber flow field, be unfavorable for flame stabilization, can worsen outlet temperature simultaneously and distribute.
Utility model content
For solving problems of the prior art, the utility model provides a kind of gas turbine dual-fuel combustor nozzle, and this technical scheme can, in guaranteeing good dilution, keep flame stabilization; In addition, this technical scheme can also suppress fuel and the obstruction of diluent to air draught of large volume flow, and the injection of diluent simultaneously can not upset combustion chamber interior flow field structure, thereby guarantees that the stability of burning and good outlet temperature distribute.
The technical scheme that the utility model adopts is as follows: a kind of gas turbine dual-fuel combustor nozzle, this nozzle comprises axial centre fuel channel and the periphery axial annular fuel channel coaxially arranged with this axial centre fuel channel, it is characterized in that: peripheral axial annular fuel channel is also provided with the axial annular diluent gas passage in the periphery coaxially arranged with axial centre fuel channel outward; The air duct of nozzle is also coaxially arranged with axial centre fuel channel, and is divided into the peripheral radial ringed air duct of the peripheral radial ringed air duct of the first order and the second level; On the wall of the described axial centre fuel channel port of export, have Process; Axial annular fuel channel exit, described periphery is provided with peripheral fuel swirl device; The axial annular diluent gas vias inner walls face in described periphery is provided with fuel dilution hole, and fuel dilution hole is communicated with peripheral axial annular fuel channel; On the wall of the axial annular diluent gas channel outlet in described periphery, be respectively equipped with first order Dilution air hole and Dilution air hole, the second level, first order Dilution air hole is connected with the peripheral radial ringed air duct of the first order, and Dilution air hole, the second level is connected with the peripheral radial ringed air duct in the second level; In the peripheral radial ringed air duct of the described first order, be provided with first order air swirl device, in the peripheral radial ringed air duct in the second level, be provided with second level air swirl device.
In technique scheme, described first order air swirl device adopts the hole of cutting sth. askew, this hole of cutting sth. askew penetrates in the peripheral radial ringed air duct of the first order from the outside wall surface of nozzle, and is evenly arranged along the wall of the peripheral radial ringed air duct of the first order, and the number in hole is between 6～12.
Described peripheral fuel swirl device adopts axial blade formula structure or axial cascade type structure, and blade number or blade grid passage number are between 6～12.
This utility model compared with prior art, has the following advantages and high-lighting effect:
(1) diluent infeed mode of the present utility model is different from prior art, diluent can carry out multiply fuel dilution and multiply Dilution air, diluent can recently be optimized adjustment by the area that changes each dilution holes to the infeed ratio of each fuel channel and air duct, and the dilution of having avoided prior art to adopt single dilution method to bring is inhomogeneous existing.
(2) diluent of the present utility model adopts multiple spray-holes to feed, can strengthen mixing of diluent and fuel or air, strengthen on the one hand diluent and fuel and air mixing effect, the blocking action of the diluent air-flow that also can lower on the other hand large volume flow to air-spray, thereby guarantee the air supply of head of combustion chamber, and then promote combustion stability.
(3) the diluent carrying method that the utility model adopts can not upset the interior flow field of combustion chamber, thus guarantee diluent injection can not be distributed with harmful effect to combustion stability and outlet temperature.
(4) end of the utility model fuel transmission component has intensive teasehole; while work at combustion machine in this hole; or pass into separately fuel or pass into separately featheriness air; this makes nozzle end wall place; the factors such as gas flow temperature is lower, air-flow velocity is higher, fuel-air ratio are all unsuitable for flame stabilization; and then stop flame in the adhering to of end wall, thereby protection nozzle end wall can not be burned.
Accompanying drawing explanation
The structural principle schematic diagram of a kind of gas turbine dual-fuel combustor nozzle that Fig. 1 provides for the utility model.
Fig. 2 is the structure three-dimensional cutaway view of dual-fuel combustor nozzle embodiment.
In figure, symbol description is as follows: 1-axial centre fuel channel; The peripheral axial annular fuel channel of 2-; The peripheral axial annular diluent gas passage of 3-; The peripheral radial ringed air duct of the 4-first order; The peripheral radial ringed air duct in the 5-second level; 6-Process; 7-fuel dilution hole; 8-first order Dilution air hole; Dilution air hole, the 9-second level; The peripheral fuel swirl device of 10-; 11-first order air swirl device; 12-second level air swirl device.
The specific embodiment
Below in conjunction with accompanying drawing, principle of the present utility model, structure and the specific embodiment are described further.
The structural principle schematic diagram of a kind of gas turbine dual-fuel combustor nozzle that Fig. 1 provides for the utility model, this nozzle comprises axial centre fuel channel 1 and the periphery axial annular fuel channel 2 coaxially arranged with this axial centre fuel channel 1, it is characterized in that: the outer axial annular diluent gas passage 3 in the periphery coaxially arranged with axial centre fuel channel 1 that is also provided with of peripheral axial annular fuel channel 2; The air duct of nozzle is also coaxially arranged with axial centre fuel channel 1, and is divided into the peripheral radial ringed air duct 4 of the first order and the peripheral radial ringed air duct 5 in the second level.
On the wall of axial centre fuel channel 1 port of export, have Process 6; Peripheral axial annular fuel channel 2 exits are provided with peripheral fuel swirl device 10, and peripheral fuel swirl device 10 adopts axial blade formula structure or axial cascade type structure, blade number or blade grid passage number between 6～12 (referring to Fig. 2).
Peripheral axial annular diluent gas passage 3 internal faces are provided with fuel dilution hole 7, and fuel dilution hole 7 is communicated with peripheral axial annular fuel channel 2; On the wall of axial annular diluent gas passage 3 ports of export in described periphery, be respectively equipped with first order Dilution air hole 8 and Dilution air hole, the second level 9, first order Dilution air hole 8 is connected with the peripheral radial ringed air duct 4 of the first order, and Dilution air hole 9, the second level is connected with the peripheral radial ringed air duct 5 in the second level.
First order air swirl device 11 adopts the hole of cutting sth. askew, and this hole of cutting sth. askew penetrates in the peripheral radial ringed air duct 4 of the first order from the outside wall surface of nozzle, and is evenly arranged along the wall of the peripheral radial ringed air duct 4 of the first order, and the number in hole is between 6～12.
In the peripheral radial ringed air duct 5 in the second level, be provided with second level air swirl device 12, second level air swirl device 12 adopts radial blade formula structure, and blade number is (referring to Fig. 2) between 6～16.
Peripheral axial annular diluent gas passage 3 ends are provided with the fuel dilution hole 7 that is communicated with peripheral axial annular fuel channel 2, be communicated with the first order Dilution air hole 8 of peripheral radial ringed first order air duct 4, and Dilution air hole, the second level 9(that is communicated with peripheral radial ringed second level air duct 5 is referring to Fig. 2), diluent mass flow proportion by fuel dilution hole 7, first order Dilution air hole 8 and Dilution air hole, the second level 9 is 1:0.1～0.5:0.4～1, and flow-rate ratio is guaranteed from the different of perforated area by the number in hole.
Operation principle of the present utility model is as follows:
Center fuel passes through axial centre fuel channel 1 as starting fluid, enter combustion zone through Process 6, with the rotational flow air mixing and burning entering by the peripheral radial ringed air duct 5 of the peripheral radial ringed air duct 4 of the first order and the second level, when nozzle supply center fuel, be called startup combustion mode; After nozzle starts, peripheral fuel enters combustion zone as base load fuel by axial annular fuel channel 2 eddy flows in periphery and participates in burning, when nozzle while supply center's fuel and peripheral fuel, be called transition combustion mode, meanwhile peripheral axial annular diluent gas passage 3 is supplied eddy flow diluent gas to combustion zone by fuel dilution hole 7, first order Dilution air hole 8 and Dilution air hole 9, the second level; Reach after burden requirement, the center Fuel switching Cheng Qing that axial centre fuel channel 1 is supplied blows air, and nozzle is called normal combustion mode while only supplying peripheral fuel.
Claims (4)
1. a gas turbine dual-fuel combustor nozzle, this nozzle comprises axial centre fuel channel (1) and the periphery axial annular fuel channel (2) coaxially arranged with this axial centre fuel channel (1), it is characterized in that: outside peripheral axial annular fuel channel (2), be also provided with the periphery axial annular diluent gas passage (3) coaxially arranged with axial centre fuel channel (1); The air duct of nozzle is also coaxially arranged with axial centre fuel channel (1), and is divided into the peripheral radial ringed air duct of the first order (4) and the peripheral radial ringed air duct in the second level (5); On the wall of described axial centre fuel channel (1) port of export, have Process (6); The axial annular fuel channel in described periphery (2) exit is provided with peripheral fuel swirl device (10); The axial annular diluent gas passage in described periphery (3) internal face is provided with fuel dilution hole (7), and this fuel dilution hole (7) is communicated with peripheral axial annular fuel channel (2); On the wall of the axial annular diluent gas passage in described periphery (3) port of export, be respectively equipped with first order Dilution air hole (8) and Dilution air hole, the second level (9), first order Dilution air hole (8) is connected with the peripheral radial ringed air duct of the first order (4), and Dilution air hole, the second level (9) is connected with the peripheral radial ringed air duct in the second level (5); In the peripheral radial ringed air duct of the described first order (4), be provided with first order air swirl device (11), in the peripheral radial ringed air duct in the second level (5), be provided with second level air swirl device (12).
2. a kind of gas turbine dual-fuel combustor nozzle as claimed in claim 1, it is characterized in that: described first order air swirl device (11) adopts the hole of cutting sth. askew, this hole of cutting sth. askew penetrates in the peripheral radial ringed air duct of the first order (4) from the outside wall surface of nozzle, and the wall along the peripheral radial ringed air duct of the first order (4) is evenly arranged, and the number in hole is between 6～12.
3. a kind of gas turbine dual-fuel combustor nozzle as claimed in claim 1, is characterized in that: described second level air swirl device (12) adopts radial blade formula structure, and blade number is between 6～16.
4. a kind of gas turbine dual-fuel combustor nozzle as claimed in claim 1, is characterized in that: described peripheral fuel swirl device (10) adopts axial blade formula structure or axial cascade type structure, and blade number or blade grid passage number are between 6～12.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320824748.4U CN203595144U (en) | 2013-12-13 | 2013-12-13 | Nozzle of dual-fuel combustion chamber of combustion gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320824748.4U CN203595144U (en) | 2013-12-13 | 2013-12-13 | Nozzle of dual-fuel combustion chamber of combustion gas turbine |
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| Publication Number | Publication Date |
|---|---|
| CN203595144U true CN203595144U (en) | 2014-05-14 |
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ID=50676029
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320824748.4U Withdrawn - After Issue CN203595144U (en) | 2013-12-13 | 2013-12-13 | Nozzle of dual-fuel combustion chamber of combustion gas turbine |
Country Status (1)
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|---|---|
| CN (1) | CN203595144U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103672969B (en) * | 2013-12-13 | 2017-09-15 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of gas turbine dual-fuel combustion chamber nozzle of combustion |
| CN111520760A (en) * | 2020-04-10 | 2020-08-11 | 西北工业大学 | Combustion chamber flame tube wall surface structure adopting impact/gas film double-wall composite cooling mode |
-
2013
- 2013-12-13 CN CN201320824748.4U patent/CN203595144U/en not_active Withdrawn - After Issue
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103672969B (en) * | 2013-12-13 | 2017-09-15 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of gas turbine dual-fuel combustion chamber nozzle of combustion |
| CN111520760A (en) * | 2020-04-10 | 2020-08-11 | 西北工业大学 | Combustion chamber flame tube wall surface structure adopting impact/gas film double-wall composite cooling mode |
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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: Dual-fuel combustion chamber nozzle of combustion gas turbine Effective date of registration: 20161104 Granted publication date: 20140514 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 | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20140514 Effective date of abandoning: 20170915 |