CN107143881A - A kind of direct injection nozzle structure of multiple spot for low-pollution burning chamber of gas turbine - Google Patents
A kind of direct injection nozzle structure of multiple spot for low-pollution burning chamber of gas turbine Download PDFInfo
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- CN107143881A CN107143881A CN201710342914.XA CN201710342914A CN107143881A CN 107143881 A CN107143881 A CN 107143881A CN 201710342914 A CN201710342914 A CN 201710342914A CN 107143881 A CN107143881 A CN 107143881A
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- Prior art keywords
- swirl
- combustion
- nozzle
- rotational flow
- mould
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
- F23R3/12—Air inlet arrangements for primary air inducing a vortex
- F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Abstract
The invention discloses a kind of direct injection nozzle structure of the multiple spot for low-pollution burning chamber of gas turbine, circumferential uniform connected using multiple mutually isostructural secondary combustion level swirl nozzle moulds and main combustion stage swirl nozzle Mo Yi head of combustion chamber flange center, main combustion stage swirl nozzle mould is circumferentially located at secondary combustion level swirl nozzle mould periphery；Air intlet, swirl channel, annular rotational flow air straight channel, annular rotational flow air convergent passage and rotational flow air outlet constitute the air flow circuit of swirl nozzle mould, export to form the radially high VELOCITY DISTRIBUTION in the low outside in inner side in rotational flow air.Fuel inlet, nozzle and jet expansion composition fuel flow path；Jet expansion is concordant with rotational flow air outlet, and nozzle mould is worked in non-premixed combustion mode, it is to avoid spontaneous combustion and the generation of tempering phenomenon, reduces the risk of hugging；Combustion zone temperature is relatively low, flameholding, effectively the generation of reduction thermal NO.Pollutant emission is few, it is adaptable to low-pollution burning chamber of gas turbine.
Description
Technical field
The present invention relates to gas-turbine combustion chamber technical field, specifically, it is related to a kind of for gas turbine low stain
The direct injection nozzle structure of multiple spot of combustion chamber.
Background technology
The source of gas turbine pollutant emission comes from combustion chamber, therefore development combustion with reduced pollutants technology is reduction combustion gas wheel
The key of machine disposal of pollutants.The major pollutants of combustion chamber include nitrogen oxides, carbon monoxide and unburned hydrocarbon, wherein most important
Be reduce nitrogen oxides growing amount.In a combustion chamber, thermal NO formation mechanism plays leading role, therefore drop
Low combustion zone ignition temperature is to reduce one of effective means of formation of nitrogen oxides.Poor oil firing's technology can effectively reduce burning
Area's ignition temperature, so as to reduce the growing amount of nitrogen oxides.
For poor oil firing's technology, foreign study persons propose lean premixed preevaporated combustion technology, and it is carried out
Widely studied, the technology can effectively control primary zone ignition temperature, have very big potentiality in terms of nitrogen oxides is reduced.But
It is that the technology barriers such as spontaneous combustion, tempering and serious combustion instability are run into during the technical research, these problems are seriously made
The about practical application of the technology.The problem of being run into for premixed combustion, has also been proposed oil-poor lean direct injection technology, the skill
Art intermediate fuel oil is without premix but is directly injected in primary zone and quickly mixes and fully burn with air, equally can be effective
The growing amount of nitrogen oxides is reduced, and completely avoid the problem of spontaneous combustion and tempering, while reducing combustion instability
Degree.Therefore oil-poor lean direct injection technology is one of important directions of combustion with reduced pollutants technology development.
The country also has many documents on low pollution combustor to deliver in recent years.Patent 201510673156.0,
201510674145.4 disclose two kinds of low pollution combustors, wherein secondary combustion level is pre- using swirl stabilized diffusion combustion and eddy flow
The mixed mode being combined of burning, can reduce pollutant under small state while stable burning；Main combustion stage uses premix and pre-evaporation
Combustion system, homogenous combustion can be realized under big state to reduce NOxDischarge.Patent 201410643105.9 discloses one kind
The layered portion premix low pollution combustor of the poor premix of main combustion stage, level on duty uses diffusion combustion, and main combustion stage is using lean premixed
Burning, in big operating mode, level and main combustion stage on duty work simultaneously, and primary zone is in poor oil condition, can significantly reduce NOx row
Put.But main combustion stage be possible to by the way of premix and pre-evaporation produce combustion instability phenomenon, adversely affecting its combustion performance, very
To causing structural destruction.Patent CN104791847A proposes " a kind of suitable for the low of low-pollution burning chamber of gas turbine
Eddy flow multiinjector chamber structure ", the combustion chamber is made up of six low swirl nozzles in outside and a low swirl nozzle in center, is adopted
With fuel gas and premixed combustion mode, pollutant emission can be effectively reduced.Fuel gas directly can be mixed quickly with air, but
Be liquid fuel have to pass through good atomization and and air mix after could form flammable mixed gas, therefore the burner is not suitable for
Liquid fuel, it is impossible to solve the problems, such as the combustion with reduced pollutants using liquid fuel gas turbine.
The content of the invention
In order to avoid the deficiency that prior art is present, the present invention proposes a kind of for many of low-pollution burning chamber of gas turbine
The direct injection nozzle structure of point, the injection nozzle structure can make combustion chamber stability and high efficiency in the range of full working scope work, and effectively suppress combustion
Instable generation is burnt, while reducing pollutant emission.
The technical solution adopted for the present invention to solve the technical problems is:Including head of combustion chamber flange, four secondary combustion levels
Swirl nozzle mould, eight main combustion stage swirl nozzle moulds, air intlet, swirl channel, annular rotational flow air straight channel, annular rotations
Flow air convergent passage, rotational flow air outlet, fuel inlet, nozzle, jet expansion, the secondary combustion level swirl nozzle mould and main combustion
Level swirl nozzle Mo Yi head of combustion chamber flange center is circumferential uniform connected, and main combustion stage swirl nozzle mould is evenly distributed in pair combustion
Level swirl nozzle mould periphery, air intlet, swirl channel, annular rotational flow air straight channel, annular rotational flow air convergent passage
Exported with rotational flow air in the air flow circuit of composition swirl nozzle mould, swirl channel and swirl vane is installed, air flows through eddy flow
Passage formation rotational flow, exports to form the radially high VELOCITY DISTRIBUTION in the low outside in inner side in rotational flow air；The fuel inlet,
Nozzle and jet expansion composition fuel flow path, the jet expansion are concordant with rotational flow air outlet, the oil sprayed from jet expansion
Mist is crushed under rotational flow air shear action to be formed equally distributed droplet and is mixed to form uniform flammable mixed gas with air, with
Non- premix mode combustion reaction；Main combustion stage swirl nozzle mould and secondary combustion level swirl nozzle mould can work independently or while work.
The circumferentially-adjacent nozzle mould centre-to-centre spacing S of the secondary combustion level swirl nozzle mould1For 1.5~2.0d.
The circumferentially-adjacent nozzle mould centre-to-centre spacing S of main combustion stage swirl nozzle mould2For 1.5~2.0d.
The swirl nozzle mould combustion equivalent ratio is 0.6~0.8.
Swirl vane quantity in the swirl channel is 8~16, and swirl vane setting angle is 35~40 °.
Beneficial effect
The direct injection nozzle structure of multiple spot proposed by the present invention for low-pollution burning chamber of gas turbine, combustion zone is using poor
Oil design, work equivalent proportion is between 0.6~0.8, and now flame temperature is relatively low, can effectively suppress what is generated by heating power type mechanism
Nitrogen oxides.Fuel spray is rapid under rotational flow air effect to be atomized and is well mixed with air, it is ensured that combustion even is fully not
Produce hot localised points.
Combustion chamber is under identical entry condition, for the more conventional combustion chamber single point injection of multi-point injection, each nozzle
Flow reduces, therefore can select the less nozzle of flow number, so as to ensure higher charge oil pressure, reaches more preferable atomized water
It is flat, faster carry out combustion reaction evenly.Meanwhile, multi-point injection results in more uniform outlet temperature compared with single point injection
.
Oil-poor multiple spot is directly sprayed using non-premixed combustion, greatly reduces the probability for occurring combustion instability, and
Interference effect between each nozzle can be controlled by adjusting injector spacing, effectively suppress combustion noise.
The present invention uses grading combustion technology, burning is divided into main combustion stage and secondary combustion level, its purpose is to widen burning
Room steady operation border.Under small-power state, it is only necessary to pair combustion level fuel feeding burning, main combustion stage not fuel feeding, pair combustion level work is worked as
Ratio is measured between 0.6~0.8, it is ensured that combustion chamber steady operation, with the increase of power rating, main combustion stage can be gradually opened and closed
Close secondary combustion level；Same main combustion stage works equivalent proportion between 0.6~0.8, under maximum power state, and main combustion stage and secondary combustion level are same
When work still keep combustion equivalent ratio between 0.6~0.8.It can ensure under all working state, combustion chamber can stable work
Make and effectively reduce pollutant emission level.
Brief description of the drawings
It is direct to a kind of multiple spot for low-pollution burning chamber of gas turbine of the invention with embodiment below in conjunction with the accompanying drawings
Injection nozzle structure is described in further detail.
Fig. 1 is the direct injection nozzle structure schematic diagram of multiple spot of the present invention.
Fig. 2 is the direct injection nozzle structure arrangement schematic diagram of multiple spot of the present invention.
Fig. 3 is swirl nozzle mold shaft mapping of the invention.
Fig. 4 is swirl nozzle mould sectional view of the invention.
Fig. 5 is applied to ring-pipe type combustion chamber schematic diagram for the present invention.
In figure:
1. the secondary main combustion stage swirl nozzle mould of combustion level swirl nozzle mould 4. of 2. head of combustion chamber flange of head of combustion chamber 3.
5. the annular eddy flow of rotational flow air convergent passage 9. of the annular rotational flow air straight channel 8. of 6. swirl channel of air intlet 7. is empty
The streamline of gas outlet 10. fuel inlet, 11. nozzle, 12. jet expansion, 13. taper mist of oil 14.
3a, 3b, 3c, 3d are secondary combustion level swirl nozzle mould
4a, 4b, 4c, 4d, 4e, 4f, 4g, 4h are main combustion stage swirl nozzle mould
Embodiment
The present embodiment is a kind of direct injection nozzle structure of the multiple spot for low-pollution burning chamber of gas turbine.
Such as Fig. 1~Fig. 4, the present embodiment is used for the direct injection nozzle structure of multiple spot of low-pollution burning chamber of gas turbine, by firing
Burning chamber-head portion 1, head of combustion chamber flange 2, four secondary combustion level swirl nozzle moulds 3, eight main combustion stage swirl nozzle moulds 4, air enter
Mouth 5, swirl channel 6, annular rotational flow air straight channel 7, annular rotational flow air convergent passage 8, rotational flow air outlet 9, fuel oil
Import 10, nozzle 11, jet expansion 12 are constituted；Wherein, secondary combustion level swirl nozzle mould 3 includes swirl nozzle mould 3a, swirl nozzle
Mould 3b, swirl nozzle mould 3c, swirl nozzle mould 3d；Main combustion stage swirl nozzle mould 4 includes swirl nozzle mould 4a, swirl nozzle mould
4b, swirl nozzle mould 4c, swirl nozzle mould 4d, swirl nozzle mould 4e, swirl nozzle mould 4f, swirl nozzle mould 4g, swirl nozzle
Mould 4h；Pair combustion level swirl nozzle mould 3 and main combustion stage swirl nozzle mould 4 are all according to the head of combustion chamber flange center of head of combustion chamber 1
It is connected to uniform, main combustion stage swirl nozzle mould 4 is evenly distributed in the periphery of pair combustion level swirl nozzle mould 3；Main combustion stage swirl nozzle
Mould 4 and secondary combustion level swirl nozzle mould 3 can work independently or while work.The circumferentially-adjacent nozzle mould center of pair combustion level swirl nozzle mould
Away from S1For 1.5~2.0d.The circumferentially-adjacent nozzle mould centre-to-centre spacing S of main combustion stage swirl nozzle mould2For 1.5~2.0d.
In the present embodiment, air intlet 5, swirl channel 6, annular rotational flow air straight channel 7, annular rotational flow air convergence
Passage 8 and rotational flow air outlet 9 constitute the air flow circuit of swirl nozzle mould；Swirl vane is installed, eddy flow leads in swirl channel 6
Swirl vane quantity in road 6 is 8~16, and swirl vane setting angle is 35 °~40 °；Air flows through swirl channel 6 and formed
Rotational flow, exports 9 in rotational flow air and forms the radially high VELOCITY DISTRIBUTION in the low outside in inner side.Fuel inlet 10, the and of nozzle 11
Jet expansion 12 constitutes fuel flow path；Jet expansion 12 is concordant with rotational flow air outlet 9, and the mist of oil sprayed from jet expansion 12 exists
Crushed under rotational flow air shear action and form equally distributed droplet and be mixed to form uniform flammable mixed gas with air, with non-pre-
Mixed mode combustion reaction.
Combustion chamber operational process:
During combustion chamber ignition, the only secondary combustion level swirl nozzle mould burning in four, center, with the increase of working condition, fuel delivery
Also gradually increase, when reaching that four secondary combustion level swirl nozzle die workers make the upper limit, open peripheral eight main combustion stage swirl nozzle moulds,
Flame of centre ignites rapidly the flammable mixed gas in periphery, then keeps secondary combustion level swirl nozzle mould and main combustion stage swirl nozzle mould work simultaneously
Make.
The swirl nozzle mould course of work:
Air enters the formation eddy flow flowing of swirl channel 6 from air intlet 5, then passes through annular rotational flow air straight channel
7 to eliminate the influence of swirl vane tail；Annular rotational flow air convergent passage 8 is again passed through, is formed in rotational flow air outlet 9 along footpath
To the high VELOCITY DISTRIBUTION in the low outside in inner side, the expansion of final cyclone downstream streamline 14 forms recirculating zone.Fuel oil is from fuel inlet 10
Into nozzle 11, from jet expansion 12 spray after spray cone 13, fuel oil spray cone 13 and rotational flow air mixing downstream with
Oil-poor in stable condition burning.Swirl nozzle mould combustion equivalent ratio is 0.6~0.8.
Fig. 5 is the layout applied to ring-pipe type combustion chamber, in practical application, according to the concrete structure and chi of gas turbine
Very little adjustment can burner quantity.
Claims (5)
1. a kind of direct injection nozzle structure of multiple spot for low-pollution burning chamber of gas turbine, it is characterised in that:Including combustion chamber
Head flanges, four secondary combustion level swirl nozzle moulds, eight main combustion stage swirl nozzle moulds, air intlet, swirl channel, annular eddy flows
Air straight channel, annular rotational flow air convergent passage, rotational flow air outlet, fuel inlet, nozzle, jet expansion, the pair
Fire level swirl nozzle mould and main combustion stage swirl nozzle Mo Yi head of combustion chamber flange center is circumferential uniform connected, the spray of main combustion stage eddy flow
Mouth mould is evenly distributed in pair combustion level swirl nozzle mould periphery, air intlet, swirl channel, annular rotational flow air straight channel,
Rotation is installed in the air flow circuit of annular rotational flow air convergent passage and rotational flow air outlet composition swirl nozzle mould, swirl channel
Blade is flowed, air flows through swirl channel formation rotational flow, exports to form the radially high speed in the low outside in inner side in rotational flow air
Degree distribution；The fuel inlet, nozzle and jet expansion composition fuel flow path, the jet expansion and rotational flow air outlet are flat
Together, the mist of oil sprayed from jet expansion is crushed under rotational flow air shear action forms equally distributed droplet and mixed with air
Close and form uniform flammable mixed gas, with non-premix mode combustion reaction；Main combustion stage swirl nozzle mould and secondary combustion level swirl nozzle mould can
Work independently or work simultaneously.
2. the direct injection nozzle structure of the multiple spot according to claim 1 for low-pollution burning chamber of gas turbine, its feature
It is:The circumferentially-adjacent nozzle mould centre-to-centre spacing S of the secondary combustion level swirl nozzle mould1For 1.5~2.0d.
3. the direct injection nozzle structure of the multiple spot according to claim 1 for low-pollution burning chamber of gas turbine, its feature
It is:The circumferentially-adjacent nozzle mould centre-to-centre spacing S of main combustion stage swirl nozzle mould2For 1.5~2.0d.
4. the direct injection nozzle structure of the multiple spot according to claim 1 for low-pollution burning chamber of gas turbine, its feature
It is:The swirl nozzle mould combustion equivalent ratio is 0.6~0.8.
5. the direct injection nozzle structure of the multiple spot according to claim 1 for low-pollution burning chamber of gas turbine, its feature
It is:Swirl vane quantity in the swirl channel is 8~16, and swirl vane setting angle is 35 °~40 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710342914.XA CN107143881B (en) | 2017-05-16 | 2017-05-16 | Multi-point direct injection head structure for low-pollution combustion chamber of gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710342914.XA CN107143881B (en) | 2017-05-16 | 2017-05-16 | Multi-point direct injection head structure for low-pollution combustion chamber of gas turbine |
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| CN107143881A true CN107143881A (en) | 2017-09-08 |
| CN107143881B CN107143881B (en) | 2020-02-14 |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109084329A (en) * | 2018-07-05 | 2018-12-25 | 西北工业大学 | A kind of multiple spot direct injection combustion chamber head construction |
| CN110081417A (en) * | 2019-04-11 | 2019-08-02 | 西安航天源动力工程有限公司 | A kind of combustion head and alcohol radical low nitrogen combustion apparatus |
| CN110131065A (en) * | 2019-05-15 | 2019-08-16 | 燕山大学 | A kind of novel tangential combined internal combustion engine cylinder based on eddy flow secondary injection |
| CN113834095A (en) * | 2021-11-02 | 2021-12-24 | 西安热工研究院有限公司 | Gas turbine annular tube type combustion chamber based on detonation combustion |
| CN114440261A (en) * | 2022-01-11 | 2022-05-06 | 中国人民解放军国防科技大学 | Supersonic partial premixing combustion device with low turbulence |
| CN115338050A (en) * | 2021-05-12 | 2022-11-15 | 马丁有限公司 | Nozzle, flue gas discharge device with nozzle and use method of nozzle |
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| CN104791847A (en) * | 2015-03-17 | 2015-07-22 | 上海交通大学 | Low-rotational-flow multi-nozzle combustor structure applicable to low-pollution combustion chamber of gas turbine |
| EP2933560A1 (en) * | 2014-04-17 | 2015-10-21 | Alstom Technology Ltd | Method for premixing air with a gaseous fuel and burner arrangement for conducting said method |
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| US9027349B2 (en) * | 2011-01-27 | 2015-05-12 | Mitsubishi Hitachi Power Systems, Ltd. | Gas turbine gaseous fuel injection system |
| CN203586283U (en) * | 2013-07-10 | 2014-05-07 | 辽宁省燃烧工程技术中心（有限公司） | Dry-type low-nitrogen combustion device of combustion gas turbine employing gas fuel |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109084329A (en) * | 2018-07-05 | 2018-12-25 | 西北工业大学 | A kind of multiple spot direct injection combustion chamber head construction |
| CN110081417A (en) * | 2019-04-11 | 2019-08-02 | 西安航天源动力工程有限公司 | A kind of combustion head and alcohol radical low nitrogen combustion apparatus |
| CN110081417B (en) * | 2019-04-11 | 2024-04-30 | 西安航天源动力工程有限公司 | Combustion head and alcohol group low-nitrogen combustion device |
| CN110131065A (en) * | 2019-05-15 | 2019-08-16 | 燕山大学 | A kind of novel tangential combined internal combustion engine cylinder based on eddy flow secondary injection |
| CN115338050A (en) * | 2021-05-12 | 2022-11-15 | 马丁有限公司 | Nozzle, flue gas discharge device with nozzle and use method of nozzle |
| CN113834095A (en) * | 2021-11-02 | 2021-12-24 | 西安热工研究院有限公司 | Gas turbine annular tube type combustion chamber based on detonation combustion |
| CN113834095B (en) * | 2021-11-02 | 2023-02-07 | 西安热工研究院有限公司 | Gas turbine annular tube type combustion chamber based on detonation combustion |
| CN114440261A (en) * | 2022-01-11 | 2022-05-06 | 中国人民解放军国防科技大学 | Supersonic partial premixing combustion device with low turbulence |
| CN114440261B (en) * | 2022-01-11 | 2023-09-01 | 中国人民解放军国防科技大学 | Supersonic part premixed combustion device with low turbulence |
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