CN203595143U - Double-fuel combustion chamber jet nozzle of combustion gas turbine - Google Patents
Double-fuel combustion chamber jet nozzle of combustion gas turbine Download PDFInfo
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- CN203595143U CN203595143U CN201320824703.7U CN201320824703U CN203595143U CN 203595143 U CN203595143 U CN 203595143U CN 201320824703 U CN201320824703 U CN 201320824703U CN 203595143 U CN203595143 U CN 203595143U
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- 239000000446 fuel Substances 0.000 title claims abstract description 81
- 238000002485 combustion reaction Methods 0.000 title abstract description 34
- 239000000567 combustion gas Substances 0.000 title abstract 3
- 239000003085 diluting agent Substances 0.000 claims abstract description 19
- 238000010790 dilution Methods 0.000 claims abstract description 18
- 239000012895 dilution Substances 0.000 claims abstract description 18
- 230000002093 peripheral effect Effects 0.000 claims description 26
- 238000000034 method Methods 0.000 claims description 7
- 239000007789 gas Substances 0.000 abstract description 22
- 238000005516 engineering process Methods 0.000 description 8
- 238000009792 diffusion process Methods 0.000 description 5
- 239000003344 environmental pollutant Substances 0.000 description 5
- 231100000719 pollutant Toxicity 0.000 description 5
- 230000015572 biosynthetic process Effects 0.000 description 3
- 239000003245 coal Substances 0.000 description 3
- 238000003786 synthesis reaction Methods 0.000 description 3
- CURLTUGMZLYLDI-UHFFFAOYSA-N Carbon dioxide Chemical compound O=C=O CURLTUGMZLYLDI-UHFFFAOYSA-N 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000002309 gasification Methods 0.000 description 2
- 238000002347 injection Methods 0.000 description 2
- 239000007924 injection Substances 0.000 description 2
- 238000002156 mixing Methods 0.000 description 2
- 238000010248 power generation Methods 0.000 description 2
- 230000006641 stabilisation Effects 0.000 description 2
- 238000011105 stabilization Methods 0.000 description 2
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 229910002092 carbon dioxide Inorganic materials 0.000 description 1
- 239000001569 carbon dioxide Substances 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 239000013505 freshwater Substances 0.000 description 1
- 239000011261 inert gas Substances 0.000 description 1
- 239000002075 main ingredient Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 239000003380 propellant Substances 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Images
Abstract
The utility model discloses a double-fuel combustion chamber jet nozzle of a combustion gas turbine and belongs to the technical field of combustion gas turbines. The jet nozzle comprises an axial center fuel channel, a periphery axial annular fuel channel, a periphery axial annular dilution gas channel and a periphery radial annular air channel, wherein the periphery axial annular fuel channel, the periphery axial annular dilution gas channel and the periphery radial annular air channel are arranged coaxial with the axial center fuel channel. A fuel dilution hole (7) is formed in the inner wall face of the periphery axial annular dilution gas channel and communicated with the periphery axial annular fuel channel. The jet nozzle structure has the advantages that the fuel dilution mode can not block air jet flows, so that it is guaranteed that sufficient air in the head of a combustion chamber participates in combustion; the mode that the jet nozzle is simple in structure and easy to implement is adopted, so that diluents and fuel are mixed in advance, addition of the diluents does not affect an internal flow field in the combustion chamber, and then stability of combustion 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, belongs to gas turbine technology field.
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.
Because main component in synthesis gas is CO and H2, 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, be injected into combustion zone, combustion zone peak flame temperature is significantly reduced, thereby reduce pollutant emission.
Dilution, diffusion and combustion technology enters engineering as one of technological means of early stage combustion with reduced pollutants and applies for many years, but its application in IGCC system combustion with reduced pollutants field still has two large problems to need to solve.That is: how in guaranteeing good dilution, keep flame stabilization; How to suppress fuel and the obstruction of diluent to air draught of large volume flow.
Utility model content
For solving problems of the prior art, the utility model provides a kind of gas turbine dual-fuel combustor nozzle, this combustion chamber burner not only can be in guaranteeing good dilution, keep flame stabilization, can also suppress fuel and the obstruction of diluent to air draught of large volume flow, 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 periphery axial annular fuel channel and the peripheral radial ringed air duct coaxially arranged with this axial centre fuel channel, it is characterized in that: described nozzle also comprises the axial annular diluent gas passage in the periphery coaxially arranged with described axial centre fuel channel, the axial annular diluent gas vias inner walls face in this periphery is provided with fuel dilution hole, and this fuel dilution hole is connected with peripheral axial annular fuel channel; 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; In the radial ringed air duct in described periphery, be provided with air swirl device.
In technique scheme, 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 8～16.
Described air swirl device adopts radial blade formula structure, and blade number is between 12～18.
This utility model compared with prior art, has the following advantages and beneficial effect:
(1) injection of diluent can obstruct airflow road, thereby has guaranteed sufficient combustion air amount, has overcome in prior art due to head of combustion chamber anoxic insufficient problem that causes burning.
(2) realize being pre-mixed of diluent and fuel by the mode of fuel dilution, thereby made the interior flow field that can not upset combustion chamber that adds of diluent, guaranteed the stability of burning and good combustor exit Temperature Distribution.
(3) this nozzle arrangements is simple, easy to process, is convenient to implement.
(4) the utility model is provided with intensive teasehole on the wall of the axial centre fuel channel port of export; this hole is in the time that gas turbine is worked; pass into separately fuel or pass into separately and blow clearly air; because the effect of extinguishing stops 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 the gas turbine dual-fuel combustor nozzle that Fig. 1 provides for the utility model.
Fig. 2 is the three-dimensional cutaway view that in dual-fuel combustor nozzle, peripheral fuel swirl device adopts axial cascade structure embodiment.
Fig. 3 is the three-dimensional cutaway view that dual-fuel combustor nozzle periphery fuel swirl device adopts axial blade formula structure 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 4-; 5-Process; The peripheral fuel swirl device of 6-; 7-fuel dilution hole; 8-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 the gas turbine dual-fuel combustor nozzle that Fig. 1 provides for the utility model, this nozzle comprises axial centre fuel channel 1 and periphery axial annular fuel channel 2, peripheral axial annular diluent gas passage 3 and the peripheral radial ringed air duct 4 coaxially arranged with this axial centre fuel channel 1; 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, and the amount that passes into diluent is guaranteed by fuel dilution hole 7 gross areas.On the wall of axial centre fuel channel 1 port of export, have Process 5; Peripheral axial annular fuel channel 2 exits are provided with peripheral fuel swirl device 6, and peripheral fuel swirl device 6 adopts axial blade formula structure or axial cascade type structure, and blade number or blade grid passage number are between 8～16; In peripheral radial ringed air duct 4, be provided with air swirl device 8, hole cyclonic current device 8 adopts radial blade formula structure, and blade number is between 12～18.
Operation principle of the present utility model is as follows:
Center fuel by axial centre fuel channel 1, enters combustion zone through Process 5 as starting fluid, with the rotational flow air mixing and burning entering by the radial ringed air duct 4 in periphery, is called startup combustion mode when nozzle supply center fuel; After nozzle starts, peripheral fuel participates in burning as base load fuel by peripheral axial annular fuel channel 2 flows into combustion regions, nozzle is called transition combustion mode when supply center's fuel and peripheral fuel simultaneously, meanwhile peripheral axial annular diluent gas passage 3 by fuel dilution hole 7 to the periphery axial annular fuel channel 2 supply diluent gas; 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 (3)
1. gas turbine dual-fuel combustor nozzle, this nozzle comprises axial centre fuel channel (1) and periphery axial annular fuel channel (2) and the peripheral radial ringed air duct (4) coaxially arranged with this axial centre fuel channel (1), it is characterized in that: described nozzle also comprises the periphery axial annular diluent gas passage (3) coaxially arranged with described axial centre fuel channel (1), the axial annular diluent gas passage in this periphery (3) internal face is provided with fuel dilution hole (7), this fuel dilution hole (7) is connected with peripheral axial annular fuel channel (2), on the wall of described axial centre fuel channel (1) port of export, have Process (5), the axial annular fuel channel in described periphery (2) exit is provided with peripheral fuel swirl device (6), in the radial ringed air duct in described periphery (4), be provided with air swirl device (8).
2. gas turbine dual-fuel combustor nozzle as claimed in claim 1, is characterized in that: described peripheral fuel swirl device (6) adopts axial blade formula structure or axial cascade type structure, and blade number or blade grid passage number are between 8～16.
3. gas turbine dual-fuel combustor nozzle as claimed in claim 1 or 2, is characterized in that: described air swirl device (8) adopts radial blade formula structure, and blade number is between 12～18.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320824703.7U CN203595143U (en) | 2013-12-13 | 2013-12-13 | Double-fuel combustion chamber jet nozzle of combustion gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320824703.7U CN203595143U (en) | 2013-12-13 | 2013-12-13 | Double-fuel combustion chamber jet nozzle of combustion gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203595143U true CN203595143U (en) | 2014-05-14 |
Family
ID=50676028
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320824703.7U Expired - Lifetime CN203595143U (en) | 2013-12-13 | 2013-12-13 | Double-fuel combustion chamber jet nozzle of combustion gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203595143U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106123030A (en) * | 2016-08-08 | 2016-11-16 | 华能国际电力股份有限公司 | A kind of hydrogen-rich combustion gas turbine burner |
| CN109737401A (en) * | 2018-12-28 | 2019-05-10 | 西安交通大学 | A kind of low NO being mixed and burned using lean gas/flammable cyclonic current |
-
2013
- 2013-12-13 CN CN201320824703.7U patent/CN203595143U/en not_active Expired - Lifetime
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106123030A (en) * | 2016-08-08 | 2016-11-16 | 华能国际电力股份有限公司 | A kind of hydrogen-rich combustion gas turbine burner |
| CN106123030B (en) * | 2016-08-08 | 2018-11-30 | 华能国际电力股份有限公司 | A kind of hydrogen-rich combustion gas turbine burner |
| CN109737401A (en) * | 2018-12-28 | 2019-05-10 | 西安交通大学 | A kind of low NO being mixed and burned using lean gas/flammable cyclonic current |
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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 | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Date of cancellation: 20191211 Granted publication date: 20140514 Pledgee: Tsinghua Holdings Co.,Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co.,Ltd. Registration number: 2016990000853 |
|
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20191231 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 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. |
|
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20140514 |