CN204513459U - The double-deck nozzle of air supply of a kind of gas-turbine combustion chamber blade - Google Patents
The double-deck nozzle of air supply of a kind of gas-turbine combustion chamber blade Download PDFInfo
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- CN204513459U CN204513459U CN201520095216.0U CN201520095216U CN204513459U CN 204513459 U CN204513459 U CN 204513459U CN 201520095216 U CN201520095216 U CN 201520095216U CN 204513459 U CN204513459 U CN 204513459U
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Abstract
The double-deck nozzle of air supply of a kind of gas-turbine combustion chamber blade, this nozzle comprises conical inner body, internal layer gas channel, outer gas flow passage, inner air swirl-flow devices and outer air swirl-flow devices; The front end of each blade of air swirling device is provided with radial fuel gas hollow channel, and conical inner body internal placement has annular fuel gas passage.The hollow clapboard of band circumferential weld is provided with between inside and outside layer gas channel, radial air hollow channel is also provided with at the vane nose of outer air swirl-flow devices, this radial air hollow channel is positioned at the below of radial fuel gas hollow channel, and is connected with the circumferential weld in described hollow clapboard.The utility model is by arranging the central dividing plate of radial air hollow channel and band circumferential weld, air swirling device and fuel supply are cooperatively interacted, the low regime in central dividing plate downstream can be eliminated, be conducive to forming the recirculating zone stabilized the flame in nozzle downstream, and then achieve good Exit temperature distribution, ensure that stable combustion field.
Description
Technical field
The utility model relates to the double-deck nozzle of air supply of a kind of gas-turbine combustion chamber blade, particularly relates to the structural design using dual-fuel gas-turbine combustion chamber nozzle.
Background technology
In the energy resource structure that China is current, the thermal power generation of traditional coal combustion technology is adopted to occupy most share.But it is low that this traditional generation technology exists generating efficiency, pollutant emission high (especially NOx emission), expends the shortcomings such as freshwater resources are many.Be that the gas turbine power generation technology of fuel is as one of clean energy technology with natural gas, can while meeting generation load requirement, effectively reduce the discharge of pollutant, this wherein gas-turbine combustion chamber nozzle design for tissue burning, reduce pollutant emission particularly important.
In gas-turbine combustion chamber, fuel and air realize the change of premixed and velocity profile by nozzle, reach rational VELOCITY DISTRIBUTION at jet expansion, and mate rational fuel-air mixture example, enter combustion chamber tissue burning, form stable flow field and combustion field.The double-deck nozzle of air supply of blade requires under different loads, adopt different fuel to burn, and ensures flame stabilization and good combustibility.Current, to the design form of the double-deck nozzle of air supply of gas-turbine combustion chamber blade, the open CN 100567823C of such as Chinese patent, adopts the notched air swirling vanes in bottom, improve the speed of air duct inner circumferential side, coupling nozzle exit velocity type and fuel-air mixture example.
But owing to there is breach bottom air swirling vanes, the air flow deflector angle of passage inner circumferential side is little, and swirl strength is weak, the mixing effect of this side fuel and air is caused to be deteriorated; Fuel gas is in the spray of hollow blade two STH simultaneously, and the blending distance of fuel gas and air is shorter, and adds the difficulty of blade processing, the tissue of impact burning and the generation of pollutant.Therefore, more rationally effective gas-turbine combustion chamber form of nozzle is still needed to organize burning and control polluted articles discharge.
Utility model content
For solving problems of the prior art, the purpose of this utility model is to provide the double-deck nozzle of air supply of a kind of gas-turbine combustion chamber blade, be intended to air swirling device and fuel supply are cooperatively interacted, prevent the appearance of nozzle interior low regime, be conducive to forming the recirculating zone stabilized the flame in nozzle downstream, and then realize good Exit temperature distribution, ensure stable combustion field.
The technical scheme that the utility model adopts is as follows:
The double-deck nozzle of air supply of a kind of gas-turbine combustion chamber blade, this nozzle comprises conical inner body, internal layer gas channel and outer gas flow passage; Conical inner body internal placement has annular fuel gas passage, internal layer gas channel and outer gas flow passage are furnished with inner air swirl-flow devices and outer air swirl-flow devices respectively, inside and outside layer of air swirl-flow devices is positioned 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 communicated with center annular fuel gas passageway; The wall of radial fuel gas hollow channel has fuel gas spray-hole, it is characterized in that: the hollow clapboard being provided with band circumferential weld between internal layer gas channel and outer gas flow passage, radial air hollow channel is also provided with at the vane nose of outer air swirl-flow devices, this radial air hollow channel is positioned at the below of radial fuel gas hollow channel, and is connected with the circumferential weld in described hollow clapboard.
Technical characteristic of the present utility model is also: the radial height of described circumferential weld is 0.2 ~ 1.5mm; The outlet of the hollow clapboard of described band circumferential weld is jet orifice structure; The diameter of described fuel gas spray-hole is 0.1 ~ 1mm.
In technique scheme, the double-deck nozzle of air supply of described a kind of gas-turbine combustion chamber blade, is characterized in that: described inner air swirl-flow devices adopts axial blade formula structure, and blade is evenly arranged along internal layer gas channel, eddy flow angle is 0 ~ 5 degree, and blade number is between 6 ~ 8.Outer air swirl-flow devices adopts axial blade formula structure, and blade is evenly arranged along outer gas flow passage, and eddy flow angle is 5 ~ 45 degree, and blade number is identical with inner air swirl-flow devices.
This utility model compared with prior art, have the following advantages and beneficial effect: 1. the blade of outer air swirl-flow devices rear end of the present utility model is provided with radial air hollow channel at the vane nose of outer air swirl-flow devices, air is introduced central dividing plate by this hollow channel outside nozzle, and from the circumferential weld of central dividing plate or jet orifice ejection, effectively eliminate low regime, central dividing plate downstream.The radial air hollow channel of outer air swirl-flow devices vane nose can also make air swirling device and fuel supply cooperatively interact simultaneously, reach better mixing effect, prevent the appearance of nozzle interior low regime, be conducive to forming the recirculating zone stabilized the flame in nozzle downstream, realize good Exit temperature distribution, ensure stable combustion field.
Accompanying drawing explanation
The structural principle schematic diagram of the double-deck nozzle of air supply embodiment of a kind of gas-turbine combustion chamber blade that Fig. 1 provides for the utility model.
Fig. 2 is the three-dimensional structure sectional view of Fig. 1.
Fig. 3 is the three-dimensional structure schematic diagram of the double-deck nozzle of air supply of blade of the outlet employing jet orifice structure of hollow clapboard.
In figure, symbol description is as follows: 1-conical inner body; 3-center annular fuel gas passageway; 4-circumferential weld; 5-internal layer gas channel; 6-outer gas flow passage; 7-inner air swirl-flow devices; 8-outer air swirl-flow devices; 9-is with the hollow clapboard of circumferential weld; 10-radial fuel gas hollow channel; 11-fuel gas spray-hole; 12-radial air hollow channel; 13-jet orifice structure.
Detailed description of the invention
Below in conjunction with accompanying drawing, principle of the present utility model, structure and detailed description of the invention are described further.
The structural principle schematic diagram of the double-deck nozzle of air supply embodiment of a kind of gas-turbine combustion chamber blade that Fig. 1 provides for the utility model, this nozzle comprises conical inner body 1, internal layer gas channel 5 and outer gas flow passage 6; Conical inner body 1 internal placement has annular fuel gas passage 3, internal layer gas channel 5 and outer gas flow passage 6 are furnished with inner air swirl-flow devices 7 and outer air swirl-flow devices 8 respectively, described inside and outside layer of air swirl-flow devices is positioned at same axial location, and the front end of each blade is provided with radial fuel gas hollow channel 10, radial fuel gas hollow channel 10 is communicated with center annular fuel gas passageway 3; The wall of radial fuel gas hollow channel has fuel gas spray-hole 11; The hollow clapboard 9 of band circumferential weld 4 is provided with between internal layer gas channel 5 and outer gas flow passage 6, radial air hollow channel 12 is also provided with at the vane nose of outer air swirl-flow devices 8, this radial air hollow channel is positioned at the below of radial fuel gas hollow channel, and is connected with the circumferential weld 4 in described hollow clapboard.
Enter the fuel gas of gas channel, with inside and outside two-layer rotational flow air, violent blending effect occurs, when arriving jet expansion, form the VELOCITY DISTRIBUTION of fuel distribution and the coupling be applicable to.The air entered outside nozzle, the radial air hollow channel 12 on outer air swirl-flow devices 8 blade enters in the circumferential weld 4 of hollow clapboard, the circumferential weld ejection in central partition plate 9 exit, or sprays through jet orifice structure 13.
In the technical solution of the utility model, the radial height of the circumferential weld 4 in hollow clapboard is 0.2 ~ 1.5mm; The outlet of hollow clapboard 9 is preferably jet orifice structure 13 (as shown in Figure 3).The diameter of described fuel gas spray-hole 11 is 0.1 ~ 1mm.Described inner air swirl-flow devices 7 adopts axial blade formula structure, and blade is evenly arranged along internal layer gas channel 5, and eddy flow angle is 0 ~ 5 degree, and blade number is between 6 ~ 8.Outer air swirl-flow devices 8 adopts axial blade formula structure, and blade is evenly arranged along outer gas flow passage 6, and eddy flow angle is 5 ~ 45 degree, and blade number is identical with inner air swirl-flow devices 7.
Operation principle of the present utility model is as follows:
Fuel gas enters nozzle interior by center annular fuel gas passageway 3, enter the radial fuel gas hollow channel 10 of the vane nose of inside and outside layer of air swirl-flow devices through the fuel pore of conical inner body 1 wall, the fuel gas spray-hole 11 offered by blade wall is sprayed in double-layer air-flow passage.Air divides three grades to enter nozzle, and outer air is carried out blending through the outer air swirl-flow devices 8 of outer gas flow passage 6 with the fuel gas sprayed into and forms strong eddy flow; Inner air is carried out blending through the inner air swirl-flow devices 7 of internal layer gas channel 5 with the fuel gas sprayed into and forms weak eddy flow.Two layer of air converge after central dividing plate 9.Another strand of air is introduced outside nozzle, and the radial air hollow channel 12 offered through outer air swirl-flow devices 8 vane nose passes in circumferential weld 4, penetrates from circumferential weld in central partition plate 9 exit, or adopts jet orifice structure 13 to spray.Fuel gas and inside and outside layer of air swirl-flow devices complement each other to form suitable nozzle exit velocity distribution and fuel-air mixing effect, ensure the stability of burning and good Exit temperature distribution.
Claims (6)
1. the double-deck nozzle of air supply of gas-turbine combustion chamber blade, this nozzle comprises conical inner body (1), internal layer gas channel (5) and outer gas flow passage (6); Conical inner body (1) internal placement has annular fuel gas passage (3), internal layer gas channel (5) and outer gas flow passage (6) are furnished with inner air swirl-flow devices (7) and outer air swirl-flow devices (8) respectively, inside and outside layer of air swirl-flow devices is positioned at same axial location, and the front end of each blade is provided with radial fuel gas hollow channel (10), radial fuel gas hollow channel (10) is communicated with center annular fuel gas passageway (3); The wall of radial fuel gas hollow channel (10) has fuel gas spray-hole (11), it is characterized in that: the hollow clapboard (9) being provided with band circumferential weld between internal layer gas channel (5) and outer gas flow passage (6), radial air hollow channel (12) is also provided with at the vane nose of outer air swirl-flow devices (8), this radial air hollow channel is positioned at the below of radial fuel gas hollow channel, and is connected with the circumferential weld (4) in described hollow clapboard.
2. the double-deck nozzle of air supply of a kind of gas-turbine combustion chamber blade as claimed in claim 1, is characterized in that: the radial height of described circumferential weld (4) is 0.2 ~ 1.5mm.
3. the double-deck nozzle of air supply of a kind of gas-turbine combustion chamber blade as claimed in claim 1 or 2, is characterized in that: the outlet of the hollow clapboard (9) of described band circumferential weld is jet orifice structure (13).
4. the double-deck nozzle of air supply of a kind of gas-turbine combustion chamber blade as claimed in claim 1 or 2, is characterized in that: the diameter of described fuel gas spray-hole (11) is 0.1 ~ 1mm.
5. the double-deck nozzle of air supply of a kind of gas-turbine combustion chamber blade as claimed in claim 1, it is characterized in that: described inner air swirl-flow devices (7) adopts axial blade formula structure, blade is evenly arranged along internal layer gas channel (5), eddy flow angle is 0 ~ 5 degree, and blade number is between 6 ~ 8.
6. the double-deck nozzle of air supply of a kind of gas-turbine combustion chamber blade as claimed in claim 1, it is characterized in that: outer air swirl-flow devices (8) adopts axial blade formula structure, blade is evenly arranged along outer gas flow passage (6), eddy flow angle is 5 ~ 45 degree, and blade number is identical with inner air swirl-flow devices (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520095216.0U CN204513459U (en) | 2015-02-10 | 2015-02-10 | The double-deck nozzle of air supply of a kind of gas-turbine combustion chamber blade |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520095216.0U CN204513459U (en) | 2015-02-10 | 2015-02-10 | The double-deck nozzle of air supply of a kind of gas-turbine combustion chamber blade |
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| CN204513459U true CN204513459U (en) | 2015-07-29 |
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| CN201520095216.0U Active CN204513459U (en) | 2015-02-10 | 2015-02-10 | The double-deck nozzle of air supply of a kind of gas-turbine combustion chamber blade |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112096346A (en) * | 2020-11-02 | 2020-12-18 | 黄石市博汇科技有限公司 | Multistage composite rotational flow and turbulent flow sound wave ultra-strong viscosity reduction, paraffin control and oil increasing device |
-
2015
- 2015-02-10 CN CN201520095216.0U patent/CN204513459U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112096346A (en) * | 2020-11-02 | 2020-12-18 | 黄石市博汇科技有限公司 | Multistage composite rotational flow and turbulent flow sound wave ultra-strong viscosity reduction, paraffin control and oil increasing device |
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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: The double-deck nozzle of air supply of combustion chamber blade Effective date of registration: 20161104 Granted publication date: 20150729 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: 20150729 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: 20191227 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. |