CN106996579A - A kind of oil-poor direct jetstream whirl nozzle mould of low-pollution burning chamber of gas turbine - Google Patents
A kind of oil-poor direct jetstream whirl nozzle mould of low-pollution burning chamber of gas turbine Download PDFInfo
- Publication number
- CN106996579A CN106996579A CN201710342928.1A CN201710342928A CN106996579A CN 106996579 A CN106996579 A CN 106996579A CN 201710342928 A CN201710342928 A CN 201710342928A CN 106996579 A CN106996579 A CN 106996579A
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- Prior art keywords
- cyclone
- nozzle
- oil
- rotational flow
- air
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Classifications
-
- 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
Abstract
The invention discloses a kind of oil-poor direct jetstream whirl nozzle mould of low-pollution burning chamber of gas turbine, it is made up of axial-flow type cyclone, the straight runner of annular rotational flow air, annular rotational flow air astringent runner and nozzle.Using oil-poor lean direct injection technology, jet expansion and rotational flow air outlet are generally aligned in the same plane, and the taper mist of oil of nozzle formation quick crashing and is sufficiently mixed under rotational flow air effect with air.Nozzle mould is worked in non-premixed combustion mode, is effectively prevented from spontaneous combustion and the generation of tempering phenomenon, and reduce the risk of hugging appearance；Nozzle mould combustion equivalent ratio is between 0.6~0.8, it is ensured that combustion zone temperature is relatively low, so as to effectively reduce the generation of thermal NO.In actual gas-turbine combustion chamber, by the multiple swirl nozzle mould formation direct injection structures of multiple spot of reasonable Arrangement, subregion combustion function is realized, has both ensured steady operation under wide working condition, pollutant generation can be effectively reduced again.
Description
Technical field
The present invention relates to gas-turbine combustion chamber technical field, specifically, it is related to a kind of gas turbine combustion with reduced pollutants
The oil-poor direct jetstream whirl nozzle mould of room.
Background technology
In recent years, as people's environmental consciousness is more and more stronger, no matter for aero-engine or ground gas turbine, its
Pollutant emission requires increasingly strict.Such as the one of International Civil Aviation Organization (ICAO) the subordinate Environmental Protection Committee (CAEP) formulation
Series standard is made that strict regulations to carbon monoxide, unburned hydrocarbon and nitrogen oxides discharge, only meets emission request
Engine could obtain Certification.Therefore combustion with reduced pollutants technology must be greatly developed to reduce gas turbine pollutant emission
Level, so as to meet present and following higher emission request.
At present, gas turbine combustion with reduced pollutants technology mainly includes:Fuel-rich combustion-quick extinguishing-poor oil firing's technology
(Rich burn-Quick quench-Lean burn, RQL), lean premixed preevaporated combustion technology (Lean Premixed
Prevaporised, LPP), oil-poor lean direct injection technology (Lean Direct Injection, LDI).The low dirt of PW companies
Contaminate combustion chamber TALON II and use RQL technologies, its NOxEmission level can just meet CAEP6 requirement, but due in RQL technologies,
Extinguishing process is possible to produce the reaction condition close to stoichiometric ratio, so as to generate a large amount of NOx, therefore the reduction of RQL technologies is dirty
The limited potential of discharge is contaminated, it is difficult to meet following ICAO more strict discharge standards.LPP technologies are applied to TAPS by GE companies
In serial low pollution combustor, TAPS I and TAPS II NOxDischarge the regulation than CAEP6 reduces by 50% and 60% again, and is used for
GE9X TAPS III NOxThe regulation discharged than CAEP8 is also low by 30%.LDI technologies are that fuel oil is directly injected in combustion chamber
Generation diffusion combustion is mixed with air, due to no fuel oil and air pre-mixing, therefore the problem of spontaneous combustion and tempering, and its is not present
Combustion instability sex chromosome mosaicism is also serious like that without LPP.Thus many research institutions have carried out grinding on LDI technologies in recent years
Study carefully, under the NASA ERA project supports, Goodrich companies devise array LDI combustion chambers, the NO of the programxDischarge ratio
CAEP6 regulation is low by 75%.Parker companies are under the NASA UEET project supports, it is proposed that multistage subregion LDI combustion schemes,
Its pollutant emission level can meet reduction CAEP6 regulations NOxThe requirement of discharge 70%.Also there is many country on low stain
The research and development of combustion chamber.
Patent of invention 201510673156.0,201510674145.4 discloses two kinds of low pollution combustors, wherein pre-burning
Level using swirl stabilized diffusion combustion with it is swirl-flow premixed burning be combined by the way of, can under small state stably burn while
Reduce pollutant；Main combustion stage uses the combustion system of premix and pre-evaporation, can realize homogenous combustion under big state to reduce NOxRow
Put.Patent of invention 201410643105.9 discloses a kind of layered portion premix low pollution combustor of the poor premix of main combustion stage, value
Class uses diffusion combustion, and main combustion stage uses lean premixed burning；In big operating mode, level and main combustion stage on duty work simultaneously, main
Fire area and be in poor oil condition, NO can be significantly reducedxDischarge.But main combustion stage is possible to production by the way of premix and pre-evaporation
Raw combustion instability phenomenon, adversely affecting its combustion performance even results in structural destruction.
The content of the invention
In order to avoid the deficiency that prior art is present, the present invention proposes a kind of the oil-poor straight of low-pollution burning chamber of gas turbine
Jetstream whirl nozzle mould is connect, using oil-poor non-premixed combustion mode, it is to avoid the generation of spontaneous combustion and tempering, reduce combustion instability
The risk of appearance, pollutant emission is reduced while flameholding is ensured.
The technical solution adopted for the present invention to solve the technical problems is:Including swirler blades, cyclone inwall, eddy flow
Device outer wall, cyclone outlet flat segments, the annular straight runner of rotational flow air, cyclone outlet baffle plate, cyclone outlet converging portion,
Cooling Holes, annular rotational flow air convergent passage, rotational flow air outlet, nozzle, jet expansion, nozzle mounting seat, fuel filler pipe,
Eddy flow runner, the swirler blades are prismatic blade, and blade angle degree is 35~40 °, and swirler blades quantity is 8~16
Piece, swirler blades are circumferentially fixed on cyclone inwall, the swirler blades and cyclone inwall and cyclone outer wall
Form eddy flow runner；
The nozzle mounting seat is hollow cylindrical structure, and lug bosses at end part section has in internal thread, nozzle mounting seat and cyclone
Wall is connected, and fuel inlet is located at nozzle mounting seat front end, and the nozzle mounting seat forms annular rotation with cyclone outlet flat segments
Flow the straight runner of air；
The nozzle is threadedly coupled with nozzle mounting seat, and it is empty that the nozzle forms annular eddy flow with cyclone outlet converging portion
Gas astringent runner, rotational flow air exit is minimum flow area on air flow channel, is adjusted by changing rotational flow air outlet
Circumferential uniform some Cooling Holes, the cyclone outlet converging portion and cyclone on air capacity, cyclone outlet converging portion wall
Outlet damper horizontal direction angle α is 40~50 °；Jet expansion is concordant with cyclone convergence outlet, is sprayed from jet expansion
Taper mist of oil crushes under rotational flow air shear action and forms equally distributed droplet, and is mixed to form uniform oil with air
Qi leel cloth.
The swirl nozzle mould combustion equivalent ratio is 0.6~0.8.
The straight flow channel length h of annular rotational flow air1With internal diameter d1Ratio is 0.15~0.20.
Beneficial effect
The oil-poor direct jetstream whirl nozzle mould of a kind of low-pollution burning chamber of gas turbine proposed by the present invention, using oil-poor
Non- premixed combustion mode, it is to avoid the generation of spontaneous combustion and tempering, the risk that reduction combustion instability occurs is ensureing flameholding
While reduce pollutant emission.
The present invention compared with prior art, has the characteristics that:Swirl nozzle mould is poor oil firing's mode, and work equivalent proportion
Between 0.6~0.8, now flame temperature is relatively low, effectively the generation of reduction nitrogen oxides；Using non-premixed combustion mode, have
Avoid to effect the generation of spontaneous combustion and tempering, the risk that reduction hugging occurs；Rotation is eliminated using the straight runner of rotational flow air
Flow the influence of blade wake passing so that the air flow method of cyclone outlet is more uniform；Due to cyclone outlet be air flow circuit most
Small cross-sectional area position, therefore cyclone air mass flow can be adjusted by changing discharge area；Swirl nozzle mode structure is simply compact,
Easy to process and assembling, multiple spot direct injection combustion chamber head can be formed by rationally designing swirl nozzle mould arrangement mode.
Brief description of the drawings
A kind of the oil-poor of low-pollution burning chamber of gas turbine of the invention is directly sprayed with embodiment below in conjunction with the accompanying drawings
Swirl nozzle mould is described in further detail.
Fig. 1 is swirl nozzle mold shaft mapping of the present invention.
Fig. 2 is swirl nozzle mould sectional view of the present invention.
Fig. 3 a, Fig. 3 b are that swirl nozzle of embodiment of the present invention mould arranges schematic diagram.
In figure:
1. the cyclone of 5. cyclone outer wall of fuel inlet 2. cyclone inwall, 3. air intlet, 4. swirler blades 6.
The annular straight cyclone outlet converging portion 10. of 8. cyclone outlet baffle plate of runner 9. of rotational flow air of outlet flat segments 7. is cooled down
The annular rotational flow air of rotational flow air convergent passage 12. in hole 11. exports the nozzle mounting seat of 13. nozzle, 14. jet expansion 15.
16. the swirl nozzle mould of 19. streamline of fuel filler pipe 17. eddy flow runner, 18. taper mist of oil 20.
Embodiment
The present embodiment is a kind of oil-poor direct jetstream whirl nozzle mould of low-pollution burning chamber of gas turbine.
Refering to Fig. 1, Fig. 2, Fig. 3 a, Fig. 3 b, the oil-poor direct jetstream whirl of the present embodiment low-pollution burning chamber of gas turbine
Nozzle mould, is put down by fuel inlet 1, cyclone inwall 2, air intlet 3, swirler blades 4, cyclone outer wall 5, cyclone outlet
Straight section 6, the straight runner 7 of annular rotational flow air, cyclone outlet baffle plate 8, cyclone outlet converging portion 9, cooling aperture 10, annular
Rotational flow air convergent passage 11, rotational flow air outlet 12, nozzle 13, jet expansion 14, nozzle mounting seat 15, fuel filler pipe
16th, eddy flow runner 17 is constituted；Wherein, swirler blades are prismatic blade, and blade angle degree is 35~40 °, swirler blades number
Measure as 8~16, swirler blades are circumferentially fixed on cyclone inwall 2, the swirler blades 4 and cyclone inwall 2
With the formation eddy flow of cyclone outer wall 5 runner 17.Nozzle mounting seat 15 is hollow cylindrical structure, and lug bosses at end part section has internal thread, sprayed
Mouth mounting seat 15 is connected with cyclone inwall 2, and fuel inlet is located at nozzle mounting seat front end, the nozzle mounting seat 15 and eddy flow
Device outlet flat segments 6 form the straight runner 7 of annular rotational flow air.Nozzle 13 is threadedly coupled with nozzle mounting seat 15, the nozzle
13 form at annular rotational flow air astringent runner 11, rotational flow air outlet 12 as on air flow channel with cyclone outlet converging portion 9
Minimum flow area, adjusts circumferential uniform on air capacity, the wall of cyclone outlet converging portion 9 by changing rotational flow air outlet
Some Cooling Holes 10, the cyclone outlet converging portion is 40~50 ° with the horizontal direction angle α of cyclone outlet baffle plate 8；Nozzle
Outlet 14 is concordant with cyclone convergence outlet 12, and the taper mist of oil 18 from the ejection of jet expansion 14 is under rotational flow air shear action
It is broken to form equally distributed droplet, and it is mixed to form uniform petroleum distribution with air.The combustion equivalent of swirl nozzle mould 20
Than for 0.6~0.8.The annular straight flow channel length h of rotational flow air1With internal diameter d1Ratio is 0.15~0.20.
In the present embodiment, air enters eddy flow runner 17 by air intlet 3 and forms swirling motion, in annular rotational flow air
The influence of swirl vane tail is eliminated in straight runner 7, annular rotational flow air convergent passage 11 is then passed through and accelerates flowing, in rotation
Flow device outlet 12 and form the radially high VELOCITY DISTRIBUTION in the low outside in inner side, then form recirculating zone in the expansion of downstream streamline 19.Rotation
It is minimum flow area position on air flow circuit to flow air outlet slit 12, in Actual combustion room, can be gone out by changing rotational flow air
Mouthful 12 areas adjust air capacity.Cooling Holes 10 are evenly arranged in above cyclone outlet converging portion 9, fraction rotational flow air stream
Carry out coolant outlet converging portion 9 through Cooling Holes 10.Jet expansion 14 is concordant with cyclone convergence outlet 12, is sprayed from jet expansion 14
Taper mist of oil 18 under rotational flow air shear action quick crashing form equally distributed droplet, then mix shape with air
Into uniform petroleum distribution, it is ensured that burning is quickly carried out in oil-poor non-premix mode, combustion zone equivalent proportion is 0.6~0.8.
In actual gas-turbine combustion chamber, knot is directly sprayed by the multiple swirl nozzle mould formation multiple spots of reasonable Arrangement
Structure, realizes subregion combustion function, both can guarantee that steady operation under wide working condition, and pollutant generation can be effectively reduced again.Specifically
Nozzle modulus mesh and arrangement can be determined according to actual condition demand and combustion chamber arrowhead, the rotation in the present embodiment
Flow nozzle mould can organization center a bit, around 7 points of 6 points injection head constructions；Also can 4 points of organization center, around 8 points
Ten two points of injection head constructions.
The course of work:
In the present embodiment, fuel oil enters nozzle mounting seat from fuel inlet, then flow nozzle, and shape is sprayed from jet expansion
Tapered spraying.In downstream with oil-poor in stable condition burning after fuel oil spray cone and rotational flow air mixing.Annular rotational flow air
Astringent runner is surrounded by outer nozzle wall and cyclone outlet converging portion, and air produces eddy flow fortune by axial-flow type cyclone
It is dynamic, the influence of swirl vane tail is eliminated in straight runner, convergent passage is then passed through and accelerates flowing, in cyclone outlet shape
The high VELOCITY DISTRIBUTION in low outside on the inside of radially；Rotational flow air outlet is minimum flow area position on air flow circuit, in reality
Air capacity can be adjusted in the combustion chamber of border by changing rotational flow air outlet.Cyclone baffle plate is connected by welding with cyclone outer wall
It is connected together, plays assembling positioning action.Nozzle mounting seat is fixed by welding on cyclone wheel hub, and fuel inlet is located at spray
Mouth mounting seat upstream, nozzle, which is connected through a screw thread, to be fixed in nozzle mounting seat, and jet expansion is concordant with cyclone convergence outlet,
From nozzle spray taper mist of oil under rotational flow air shear action quick crashing form equally distributed droplet, then with sky
Gas is mixed to form uniform petroleum distribution, it is ensured that burning is quickly carried out in oil-poor non-premix mode.
Claims (3)
1. a kind of oil-poor direct jetstream whirl nozzle mould of low-pollution burning chamber of gas turbine, it is characterised in that:Including cyclone
Blade, cyclone inwall, cyclone outer wall, cyclone outlet flat segments, the straight runner of annular rotational flow air, cyclone outlet gear
Plate, cyclone outlet converging portion, Cooling Holes, annular rotational flow air convergent passage, rotational flow air outlet, nozzle, jet expansion, spray
Mouth mounting seat, fuel filler pipe, eddy flow runner, the swirler blades are prismatic blade, and blade angle degree is 35~40 °, rotation
It is 8~16 to flow device blade quantity, and swirler blades are circumferentially fixed on cyclone inwall, the swirler blades and eddy flow
Device inwall and cyclone outer wall formation eddy flow runner；
The nozzle mounting seat is hollow cylindrical structure, and lug bosses at end part section has internal thread, and nozzle mounting seat is consolidated with cyclone inwall
Even, fuel inlet is located at nozzle mounting seat front end, and it is empty that the nozzle mounting seat forms annular eddy flow with cyclone outlet flat segments
Gas is straight runner；
The nozzle is threadedly coupled with nozzle mounting seat, and the nozzle forms annular rotational flow air with cyclone outlet converging portion and received
Runner is held back, rotational flow air exit is minimum flow area on air flow channel, and air is adjusted by changing rotational flow air outlet
Circumferential uniform some Cooling Holes, the cyclone outlet converging portion and cyclone outlet on amount, cyclone outlet converging portion wall
Baffle plate horizontal direction angle α is 40~50 °；Jet expansion is concordant with cyclone convergence outlet, the taper sprayed from jet expansion
Mist of oil crushes under rotational flow air shear action and forms equally distributed droplet, and is mixed to form uniform oil gas point with air
Cloth.
2. the oil-poor direct jetstream whirl nozzle mould of low-pollution burning chamber of gas turbine according to claim 1, its feature
It is:The swirl nozzle mould combustion equivalent ratio is 0.6~0.8.
3. the oil-poor direct jetstream whirl nozzle mould of low-pollution burning chamber of gas turbine according to claim 1, its feature
It is:The straight flow channel length h of annular rotational flow air1With internal diameter d1Ratio is 0.15~0.20.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710342928.1A CN106996579B (en) | 2017-05-16 | 2017-05-16 | A kind of oil-poor direct jetstream whirl nozzle mould of low-pollution burning chamber of gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710342928.1A CN106996579B (en) | 2017-05-16 | 2017-05-16 | A kind of oil-poor direct jetstream whirl nozzle mould of low-pollution burning chamber of gas turbine |
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| Publication Number | Publication Date |
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| CN106996579A true CN106996579A (en) | 2017-08-01 |
| CN106996579B CN106996579B (en) | 2019-04-19 |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109539311A (en) * | 2018-11-13 | 2019-03-29 | 西北工业大学 | A kind of axial swirler structure with oil injection structure blade |
| CN112460631A (en) * | 2020-10-27 | 2021-03-09 | 中国船舶重工集团公司第七0三研究所 | Gas fuel and air mixing device for combustion chamber of gas turbine |
| 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 |
| CN114704853A (en) * | 2022-03-24 | 2022-07-05 | 西北工业大学 | High-efficient atomizing centrifugal nozzle |
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| CN105570932A (en) * | 2016-02-25 | 2016-05-11 | 上海电气燃气轮机有限公司 | Central nozzle structure having back-fire self-inhibition function |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109539311A (en) * | 2018-11-13 | 2019-03-29 | 西北工业大学 | A kind of axial swirler structure with oil injection structure blade |
| CN112460631A (en) * | 2020-10-27 | 2021-03-09 | 中国船舶重工集团公司第七0三研究所 | Gas fuel and air mixing device for combustion chamber of gas turbine |
| CN112460631B (en) * | 2020-10-27 | 2022-01-21 | 中国船舶重工集团公司第七0三研究所 | Gas fuel and air mixing device for combustion chamber of gas turbine |
| 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 |
| CN114704853A (en) * | 2022-03-24 | 2022-07-05 | 西北工业大学 | High-efficient atomizing centrifugal nozzle |
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| CN106996579B (en) | 2019-04-19 |
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