CN104654360B - A kind of gas-turbine combustion chamber centerbody fuel feeding dual fuel nozzle - Google Patents
A kind of gas-turbine combustion chamber centerbody fuel feeding dual fuel nozzle Download PDFInfo
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- CN104654360B CN104654360B CN201510070054.XA CN201510070054A CN104654360B CN 104654360 B CN104654360 B CN 104654360B CN 201510070054 A CN201510070054 A CN 201510070054A CN 104654360 B CN104654360 B CN 104654360B
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Abstract
A kind of gas-turbine combustion chamber centerbody fuel feeding dual fuel nozzle, is directed to use with the structure design of the combustion chamber burner of double fuel.The dual fuel nozzle includes conical inner body and double-layer air-flow passage；Annular fuel gas passage and central fuel passage are disposed with inside conical inner body, internal layer gas channel and outer gas flow passage are respectively disposed with inner air swirl-flow devices and outer air swirl-flow devices, and in the inside of conical inner body tract provided with the annular straight channel of fuel oil, and at least arrange two row's fuel injection holes vertically on the wall of conical inner body tract, fuel oil annular straight channel is connected with central fuel passage and fuel injection hole.The parameters such as angle of the technical scheme by adjusting fuel injection hole aperture, the annular straight channel radial height of fuel oil and fuel injection hole and conical inner body central axis, the requirement being distributed under the conditions of different load to fuel type and fuel can be met, realize that double fuel is supplied, it is ensured that stable combustion field and good Exit temperature distribution.
Description
Technical field
Fired the present invention relates to a kind of gas-turbine combustion chamber dual fuel nozzle, more particularly to using the gas turbine of double fuel
Burn the structure design of room nozzle.
Background technology
In the current energy resource structure of China, most shares are occupied using the thermal power generation of traditional coal combustion technology.
But to there is generating efficiency low for this traditional generation technology, pollutant emission height (especially NOx emission) expends freshwater resources
Many the shortcomings of.Gas turbine power generation technology by fuel of natural gas can generate electricity as one of clean energy technology meeting
While burden requirement, the discharge of pollutant is effectively reduced, the design of gas-turbine combustion chamber nozzle is for tissue among these
Burning, reduction pollutant emission are particularly important.
In gas-turbine combustion chamber, fuel and air realize premixing and the change of velocity profile by nozzle, go out in nozzle
Mouth reaches rational VELOCITY DISTRIBUTION, and matches rational fuel-air mixture example, organizes to burn into combustion chamber, forms stable
Flow field and combustion field.The requirement of centerbody fuel feeding dual fuel nozzle is burnt under different loads using different fuel,
Ensure flame stabilization and good combustibility.Currently, to the design of gas-turbine combustion chamber centerbody fuel feeding dual fuel nozzle
Form, such as patent CN102261673A, centrifuging temperature nozzle is installed using nozzle center, and atomizing air enters to fuel oil to be fired
Burn before the burning of room be atomized and ensure good combustibility.
But, fuel distribution effect of the centrifuging temperature nozzle under some loading condictions is not enough managed compared to pre- membrane type nozzle
Think, the distribution of centrifuging temperature port fuel is spread, it is necessary to coordinate atomizing air to make centered on nozzle center region to surrounding
Fuel oil reaches suitable droplet size and distribution before combustion, adds the difficulty to nozzle center's bleed.Therefore, there is still a need for
Gas-turbine combustion chamber dual fuel nozzle reasonable in design, so that effectively tissue burning and control pollutant emission.
The content of the invention
To solve problems of the prior art, the present invention provides a kind of gas-turbine combustion chamber centerbody fuel feeding double combustions
Expect nozzle, supply air swirling device and double fuel and cooperate, so that the recirculating zone of stable flame is formed in nozzle downstream,
Ensure stable combustion field, realize good Exit temperature distribution.
The technical solution adopted in the present invention is as follows：
A kind of gas-turbine combustion chamber centerbody fuel feeding dual fuel nozzle, the nozzle includes conical inner body and double-layer air-flow is logical
Road, the double-layer air-flow passage is divided into internal layer gas channel and outer gas flow passage；Annular fuel gas is disposed with inside conical inner body
Passage and central fuel passage, internal layer gas channel and outer gas flow passage are respectively disposed with inner air swirl-flow devices and outer layer
Air swirling device, inside and outside layer of air swirl-flow devices are located at same axial location, and the front end of each blade is provided with radial fuel
Gas hollow channel, radial fuel gas hollow channel is connected with center annular fuel gas passageway；The wall of radial fuel gas hollow channel
Fuel gas jet straight hole is provided with face, it is characterised in that：The inside of conical inner body tract provided with the annular straight channel of fuel oil, and
Two row's fuel injection holes, fuel oil annular straight channel and described center are at least arranged on the wall of conical inner body tract vertically
Fuel gallery is connected with fuel injection hole.
The technical characteristic of the present invention is also resided in：The radial height of the annular straight channel of described fuel oil is preferably 0.1~
1.5mm.The diameter of described fuel injection hole is preferably 0.1~0.5mm.Often row's fuel injection hole is uniformly distributed circumferentially, and
The axial spacing of adjacent two rows fuel injection hole is 2~10 times of fuel injection hole diameter.The perforate direction of fuel injection hole with
The centerlines of conical inner body are 0~45 degree.
In above-mentioned technical proposal, a diameter of 0.1~1mm of fuel gas jet straight hole.Inner air swirl-flow devices use axle
To leaf structure, blade is evenly arranged along internal layer gas channel, and eddy flow angle is 0~5 degree, and blade number is between 6~8.
Outer air swirl-flow devices use axial blade formula structure, and blade is evenly arranged along outer gas flow passage, and eddy flow angle is 5~45
Degree, blade number is identical with inner air swirl-flow devices.
The invention compared with prior art, with advantages below and beneficial effect：1. fuel oil of the invention passes through at center
The annular straight channel of fuel oil and fuel injection hole that cone tract is opened up enter gas channel, coordinate inside and outside layer of air eddy flow dress
Fuel oil is set into reaching suitable droplet size and distribution offer condition behind combustion zone.2. fuel oil of the invention, fuel gas are double
Fuel is supplied, and coordinates inside and outside layer of air swirl-flow devices, can be met and fuel type and fuel distribution be wanted under the conditions of different load
Ask.3. by adjusting fuel injection hole and the angle of conical inner body central axis, fuel injection hole aperture, the annular straight channel of fuel oil
The variables such as radial height, can be the design Widening Design space of inside and outside layer of air swirl-flow devices, reach preferably blending effect
Really.
Brief description of the drawings
Fig. 1 is the structural representation of the embodiment of the present invention.
Fig. 2 is Fig. 1 structure three-dimensional sectional view.
Fig. 3 is Fig. 2 three dimensional sectional view.
The sectional drawing of cone tract centered on Fig. 4.
Symbol description is as follows in figure：1- conical inner bodies；2- double-layer air-flow passages；3- annular fuel gas passages；Fire at 4- centers
Oily passage；5- internal layer gas channels；6- outer gas flow passages；7- inner air swirl-flow devices；8- outer air swirl-flow devices；9-
Central dividing plate；10- fuel gas jet straight holes；11- fuel oils annular straight channel；12- fuel injection holes.
Embodiment
Principle, structure and the embodiment to the present invention are described further below in conjunction with the accompanying drawings.
A kind of structural principle signal for gas-turbine combustion chamber centerbody fuel feeding dual fuel nozzle that Fig. 1 provides for the present invention
Figure, the nozzle includes conical inner body 1 and double-layer air-flow passage 2, and the double-layer air-flow passage is divided into internal layer air-flow by central dividing plate 9
Passage 5 and outer gas flow passage 6；Annular fuel gas passage 3 and central fuel passage 4, internal layer gas are disposed with inside conical inner body 1
Circulation road 5 and outer gas flow passage 6 are respectively disposed with inner air swirl-flow devices 7 and outer air swirl-flow devices 8, inside and outside layer
Air swirling device is located at same axial location, and the front end of each blade is provided with radial fuel gas hollow channel, radial fuel
Gas hollow channel is connected with center annular fuel gas passageway 3；Fuel gas jet is provided with the wall of radial fuel gas hollow channel
Straight hole 10；The inside of the tract of conical inner body 1 is provided with the annular straight channel 11 of fuel oil, and on the wall of the tract of conical inner body 1
Two row's fuel injection holes 12 are at least arranged vertically, and fuel oil annular straight channel 11 is sprayed with described central fuel passage 4 and fuel oil
Perforation is connected.Into the fuel gas and fuel oil of gas channel, occur violent blending effect with inside and outside two layers rotational flow air,
Fuel oil reaches suitable droplet size and distribution, when reaching jet expansion, two kinds of fuel can reach suitable fuel distribution and
The VELOCITY DISTRIBUTION of matching.
In technical scheme, the radial height of the annular straight channel of described fuel oil is preferably 0.1~1.5mm.Institute
The diameter for the fuel injection hole stated is preferably 0.1~0.5mm.Often row's fuel injection hole should be uniformly distributed circumferentially, and adjacent two
The axial spacing for arranging fuel injection hole is 2~10 times of fuel injection hole diameter.The perforate direction of fuel injection hole and center cone
The centerlines of body are 0~45 degree.
In technical scheme, a diameter of 0.1~1mm of fuel gas jet straight hole.Inner air swirl-flow devices are adopted
With axial blade formula structure, blade is evenly arranged along internal layer gas channel, eddy flow angle be 0~5 degree, blade number 6~8 it
Between.Outer air swirl-flow devices use axial blade formula structure, and blade is evenly arranged along outer gas flow passage, and eddy flow angle is 5
~45 degree, blade number is identical with inner air swirl-flow devices.
The operation principle of the present invention is as follows：
Fuel gas enters nozzle by annular fuel gas passage 3, by the fuel stomata of the wall of conical inner body 1 enter it is interior,
The blade hollow channel of outer air swirl-flow devices, the fuel gas jet straight hole 10 opened up by blade wall sprays into double-layer air-flow
In passage 2.Fuel oil enters nozzle, the fuel oil that a part of fuel oil is opened up through conical inner body downstream inner by central fuel passage 4
Annular straight channel 11 sprays into gas channel；Another part fuel oil sprays into air-flow through the fuel injection hole 12 on the wall of centerbody downstream
Passage.Air point two-stage enters nozzle, and outer air is by the outer air swirl-flow devices 8 of outer gas flow passage 6 with penetrating
Fuel gas is blended and forms strong eddy flow；Inner air is by the inner air swirl-flow devices 7 of internal layer gas channel 5 with penetrating
Fuel gas blended and form weak eddy flow.Two layer of air converge after central dividing plate 9, and with the annular He of straight channel 11 of fuel oil
The fuel oil that fuel injection hole 12 sprays is atomized and blended, and forms the jet expansion speed of matching two kinds of fuel of fuel gas and fuel oil
Degree distribution and fuel-air mixing effect, it is ensured that the stability of burning and good Exit temperature distribution.
Claims (8)
1. a kind of gas-turbine combustion chamber centerbody fuel feeding dual fuel nozzle, the nozzle includes conical inner body (1) and double-layer air-flow
Passage (2), the double-layer air-flow passage is divided into internal layer gas channel (5) and outer gas flow passage (6)；The internal cloth of conical inner body (1)
It is equipped with annular fuel gas passage (3) and central fuel passage (4), internal layer gas channel (5) and outer gas flow passage (6) difference cloth
Inner air swirl-flow devices (7) and outer air swirl-flow devices (8) are equipped with, inside and outside layer of air swirl-flow devices are located at same axial direction
Position, and the front end of each blade is provided with radial fuel gas hollow channel, radial fuel gas hollow channel and center annular fuel
Gas passage (3) is connected；Fuel gas jet straight hole (10) is provided with the wall of radial fuel gas hollow channel, it is characterised in that：In
The inside of heart cone (1) tract is provided with the annular straight channel (11) of fuel oil, and along axle on the wall of conical inner body (1) tract
To at least arranging two row's fuel injection holes (12), fuel oil annular straight channel (11) and described central fuel passage (4) and fuel oil
Spray-hole is connected.
2. a kind of gas-turbine combustion chamber centerbody fuel feeding dual fuel nozzle as claimed in claim 1, it is characterised in that：Fuel oil
The radial height of annular straight channel (11) is 0.1~1.5mm.
3. a kind of gas-turbine combustion chamber centerbody fuel feeding dual fuel nozzle as claimed in claim 1, it is characterised in that：It is described
Fuel injection hole a diameter of 0.1~0.5mm.
4. a kind of gas-turbine combustion chamber centerbody fuel feeding dual fuel nozzle as described in claim 1,2 or 3, its feature exists
In：Often row's fuel injection hole is uniformly distributed circumferentially, and the axial spacing of adjacent two rows fuel injection hole is fuel injection hole
(12) 2~10 times of diameter.
5. a kind of gas-turbine combustion chamber centerbody fuel feeding dual fuel nozzle as claimed in claim 4, it is characterised in that：Fuel oil
The centerlines of spray-hole (12) perforate direction and conical inner body are 0~45 degree.
6. a kind of gas-turbine combustion chamber centerbody fuel feeding dual fuel nozzle as claimed in claim 1, it is characterised in that：Fuel
A diameter of 0.1~1mm of gas jet straight hole (10).
7. a kind of gas-turbine combustion chamber centerbody fuel feeding dual fuel nozzle as claimed in claim 1, it is characterised in that：Internal layer
Air swirling device (7) uses axial blade formula structure, and blade is evenly arranged along internal layer gas channel (5), and eddy flow angle is 0~
5 degree, blade number is between 6~8.
8. a kind of gas-turbine combustion chamber centerbody fuel feeding dual fuel nozzle as claimed in claim 1, it is characterised in that：Outer layer
Air swirling device (8) uses axial blade formula structure, and blade is evenly arranged along outer gas flow passage (6), and eddy flow angle is 5~
45 degree, blade number is identical with inner air swirl-flow devices (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510070054.XA CN104654360B (en) | 2015-02-10 | 2015-02-10 | A kind of gas-turbine combustion chamber centerbody fuel feeding dual fuel nozzle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510070054.XA CN104654360B (en) | 2015-02-10 | 2015-02-10 | A kind of gas-turbine combustion chamber centerbody fuel feeding dual fuel nozzle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104654360A CN104654360A (en) | 2015-05-27 |
| CN104654360B true CN104654360B (en) | 2017-09-15 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201510070054.XA Active CN104654360B (en) | 2015-02-10 | 2015-02-10 | A kind of gas-turbine combustion chamber centerbody fuel feeding dual fuel nozzle |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107796016A (en) * | 2017-09-29 | 2018-03-13 | 哈尔滨理工大学 | A kind of gas-turbine combustion chamber double fuel integrated spray nozzle device |
| CN114857622B (en) * | 2022-05-12 | 2023-08-22 | 中国人民解放军空军工程大学 | Quick adjustable device of rotatory knocking combustion chamber fuel injection area |
| CN114811656A (en) * | 2022-05-19 | 2022-07-29 | 上海和兰透平动力技术有限公司 | Fuel nozzle |
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| PB01 | Publication | ||
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| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of invention: Gas turbine combustor centrebody oil supply dual fuel nozzle Effective date of registration: 20171115 Granted publication date: 20170915 Pledgee: Tsinghua Holdings Co., Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. Registration number: 2016990000853 |
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| 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: 20170915 Pledgee: Tsinghua Holdings Co., Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. Registration number: 2016990000853 |
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| TR01 | Transfer of patent right |
Effective date of registration: 20191225 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-duty 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. |