CN109489070A - A kind of gas-turbine combustion chamber cyclone and component - Google Patents
A kind of gas-turbine combustion chamber cyclone and component Download PDFInfo
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- CN109489070A CN109489070A CN201811404515.2A CN201811404515A CN109489070A CN 109489070 A CN109489070 A CN 109489070A CN 201811404515 A CN201811404515 A CN 201811404515A CN 109489070 A CN109489070 A CN 109489070A
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- cyclone
- guide ring
- gas
- swirl vane
- component
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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
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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 belongs to technical field of gas turbine, a kind of gas-turbine combustion chamber cyclone and component are disclosed, including cyclone, guide ring and premix chamber, cyclone are connected to guide ring, guide ring is connected to premix chamber；Cyclone is radial swirler, multiple swirl vanes including arranging lopping, swirl vane bottom are bolted with combustor endcover, are fixedly connected at the top of swirl vane with circular end plate, combustor endcover is arranged concentrically with circular end plate, and circular end plate is equipped with concentric centre bore；Swirl vane radially extends, and eddy flow conduit is formed between adjacent swirl vane, and eddy flow conduit is equipped with fuel nozzle；Guide ring is connected to the fixation of the centre bore of circular end plate, and guide ring is in the shape of a trumpet；Premix chamber is tube structure.The present invention is sufficiently mixed air and fuel uniformly, reduces disposal of pollutants, realizes and stablizes burning, prevents from being tempered, inhibit the advantageous effects of combustion oscillation.
Description
Technical field
The present invention relates to a kind of gas turbine components, especially a kind of gas-turbine combustion chamber cyclone and component belong to
In technical field of gas turbine.
Background technique
Dry low NOx (DLN) combustion technology (DLN) is the current control that heavy duty gas turbine generallys use in the world pollution
The mature technology of object discharge.In dry-low NOx combustion technology, it is crucial that realize fuel and air it is uniform mix and
Dilute phase premixed combustion.The most substantive advantage of dilute phase premixed combustion is exactly that its flame temperature is low, directly affects the generation of NOx.But
Other than the ratio of control fuel and air, the horizontal fuel-air mixture homogeneity that also system can be reached of NOx generation
It is very sensitive.Air and fuel are mixed uniformly by cyclone, are most common methods in practice.
Compared to traditional diffusion burner, DLN technology has incomparable advantage in terms of contamination control.But meanwhile
Due to the transformation of combustion system, series of challenges also is brought to designed combustion device, such as poor combustion stability, tempering, Load Regulation
The problems such as range becomes smaller, combustion oscillation.
Summary of the invention
Goal of the invention of the invention is: in view of the above problems, providing a kind of stable burning, prevents from being tempered, press down
The gas-turbine combustion chamber cyclone and component of combustion oscillation processed.
The technical solution adopted by the invention is as follows:
A kind of gas-turbine combustion chamber cyclone and component, including cyclone and be set to cyclone airflow downstream guide ring and
Premix chamber, the cyclone are connected to guide ring, and guide ring is connected to premix chamber.
Further, the cyclone is radial swirler, multiple swirl vanes including arranging lopping, swirl vane top
Portion is fixedly connected with circular end plate, and swirl vane bottom is detachably connected with combustor endcover, combustor endcover and circular end plate
It is arranged concentrically, circular end plate is equipped with concentric centre bore；Swirl vane radially extends, and forms edge between adjacent swirl vane
The eddy flow conduit that centre bore tangential direction extends, eddy flow conduit are equipped with fuel nozzle, and fuel nozzle is installed on combustor end and covers,
Fuel nozzle is equipped with multiple fuel jet orifices.
Further, the outer end width of the swirl vane is greater than inner end width, and there are chamfering in the outer end two sides of swirl vane.
Further, the quantity of the swirl vane is 4-24 piece.
Further, 30-60 ° of the setting angle of the swirl vane.
Further, the fuel nozzle is located at the swirl vane chamfering of eddy flow conduit inlet end two sides, fuel jet orifice
Fuel is sprayed to eddy flow channel entrance.
Further, the fuel nozzle is located among eddy flow conduit inlet end, and fuel jet orifice is sprayed to two sides swirl vane
Fuel out.
Further, the centre bore fixation of the guide ring and circular end plate be connected to, the diameter of the air inlet of guide ring and
The diameter of circular end plate centre bore is identical.
Further, the guide ring is in the shape of a trumpet.
Further, the diameter of the air inlet of the guide ring be greater than guide ring gas outlet diameter, guide ring into
The diameter of port to the gas outlet of guide ring gradually successively decreases.
Further, the premix chamber is tube structure.
Further, the cyclone, guide ring and premix chamber are integrally formed.
The course of work of of the invention a kind of gas-turbine combustion chamber cyclone and component is as follows: pressure-air is through radial rotation
The eddy flow channel entrance end for flowing device flows into, and strong eddy flow is generated under the action of swirl vane, with eddy flow channel entrance end fuel
The fuel that spray orifice sprays is uniformly mixed, and is flowed out from eddy flow channel outlet end, then fuel combination is come at guide ring, and guide ring can
To prevent fuel combination to be detached from wall surface, stable next goes to burner inner liner into premix chamber.
It should be noted that exhaust gas nozzle is there are two types of set-up mode, one is the centre for being set to eddy flow channel entrance end,
Fuel jet orifice sprays fuel to two sides swirl vane；Another kind is to be set to eddy flow channel entrance end two sides swirl vane chamfering
, there are two fuel nozzles at place, and fuel jet orifice sprays fuel to eddy flow channel entrance end.Two kinds of technical solutions are all to both direction
Fuel is sprayed, compared with one direction sprays the technical solution of fuel, technical solution of the present invention can make fuel and air mixing more
Uniformly, reach stable burning, reduce local flame temperature, reduce NOx emission.
In conclusion by adopting the above-described technical solution, the beneficial effects of the present invention are: radial swirler make combustion gas with
Air is sufficiently mixed uniformly, and wall surface will not be separated when guide ring makes fuel combination turn, prevents fuel combination from being formed at turning
Vortex keeps steady air current, can stablize burning, inhibits combustion oscillation；Premix chamber increases the mixing distance of combustion gas and air,
Keep fuel and air more fully mixed, by changing the diameter control air-flow velocity of premix chamber, prevents tempering phenomenon, adjust
The length of premix chamber can inhibit the generation of combustion oscillation.The present invention makes air and fuel be sufficiently mixed uniform, stable to be transmitted to fire
Flame cylinder is realized and stablizes burning, prevents from being tempered, inhibit the advantageous effects of combustion oscillation.
Detailed description of the invention
Examples of the present invention will be described by way of reference to the accompanying drawings, in which:
Fig. 1 is gas engine combustion chamber cyclone and component diagrammatic cross-section；
Fig. 2 is guide ring and end plate connection schematic diagram；
Fig. 3 is the schematic diagram that jet pipe is located among eddy flow conduit；
Fig. 4 is that the fuel and air that jet pipe is located among eddy flow conduit flow to schematic diagram；
Fig. 5 is the schematic diagram that jet pipe is located at the chamfering of eddy flow conduit two sides；
Fig. 6 is that the fuel and air that jet pipe is located at the chamfering of eddy flow conduit two sides flow to schematic diagram；
Marked in the figure: 1- swirl vane, 2- combustor endcover, 3- circular end plate, 4- guide ring, 5- premix chamber, 6- fuel nozzle,
The gas outlet of 7- eddy flow conduit, the air inlet of 8- guide ring, 9- guide ring.
Specific embodiment
All features disclosed in this specification or disclosed all methods or in the process the step of, in addition to mutually exclusive
Feature and/or step other than, can combine in any way.
Any feature disclosed in this specification unless specifically stated can be equivalent or with similar purpose by other
Alternative features are replaced.That is, unless specifically stated, each feature is an example in a series of equivalent or similar characteristics
?.
Embodiment 1
As shown in Fig. 1-4, a kind of gas-turbine combustion chamber cyclone and component of the present embodiment, including cyclone and be set to
The guide ring 4 and premix chamber 5 of cyclone airflow downstream, guide ring 4 is between cyclone and premix chamber 5, cyclone, guide ring
4 are integrally formed with premix chamber 5；The cyclone is radial swirler, multiple swirl vanes 1 including arranging lopping, eddy flow leaf
1 top of piece is fixedly connected with circular end plate 3, and 1 bottom of swirl vane is bolted with combustor endcover 2, is set on combustor endcover 2
There is fuel nozzle pilot hole, combustor endcover 2 is arranged concentrically with circular end plate 3, and circular end plate 3 is equipped with concentric centre bore；
Swirl vane 1 radially extends, and the eddy flow conduit 7 extended along centre bore direction, eddy flow conduit 7 are formed between adjacent swirl vane
Equipped with fuel nozzle 6, fuel nozzle 6 is installed on pilot hole, and fuel nozzle 6 is equipped with multiple fuel jet orifices, swirl vane 1
Outer end width is greater than inner end width, and the quantity of swirl vane is 4, and 30 ° of the setting angle of swirl vane, fuel nozzle 6 is located at
Among 7 inlet end of eddy flow conduit, fuel jet orifice sprays fuel to two sides swirl vane 1.
The guide ring 4 is connected to the fixation of the centre bore of circular end plate 3, the diameter and round nose of the air inlet 8 of guide ring
The diameter of 3 centre bore of plate is identical, and guide ring 4 is in the shape of a trumpet, and the diameter of the air inlet 8 of guide ring is greater than the gas outlet of guide ring
The diameter of 9 diameter, air inlet 8 to the gas outlet of guide ring 9 of guide ring gradually successively decreases；Premix chamber 5 and the fixed company of guide ring 4
Logical, premix chamber 5 is cylindrical structure, and the diameter of premix chamber 5 and the diameter of gas outlet 9 of guide ring are identical.
Embodiment 2
As shown in Fig. 1-2 and Fig. 5-6, a kind of gas-turbine combustion chamber cyclone and component of the present embodiment, including cyclone and
Be set to the guide ring 4 and premix chamber 5 of cyclone airflow downstream, guide ring 4 between cyclone and premix chamber 5, cyclone,
Guide ring 4 and premix chamber 5 are integrally formed；The cyclone is radial swirler, multiple swirl vanes 1 including arranging lopping,
1 top of swirl vane is fixedly connected with circular end plate 3, and 1 bottom of swirl vane is bolted with combustor endcover 2, combustor end
Lid 2 is equipped with fuel nozzle pilot hole, and combustor endcover 2 is arranged concentrically with circular end plate 3, and circular end plate 3 is equipped with concentric
Centre bore；Swirl vane 1 radially extends, and the eddy flow conduit 7 extended along centre bore direction, rotation are formed between adjacent swirl vane
Chute road 7 is equipped with fuel nozzle 6, and fuel nozzle 6 is installed on pilot hole, and fuel nozzle 6 is equipped with multiple fuel jet orifices, eddy flow
The outer end width of blade 1 is greater than inner end width, and the quantity of swirl vane is 24,60 ° of the setting angle of swirl vane, fuel spray
Pipe 6 is located at 1 chamfering of swirl vane of 7 inlet end two sides of eddy flow conduit, and fuel jet orifice is sprayed to 7 inlet of eddy flow conduit and fired
Material.
The guide ring 4 is connected to the fixation of the centre bore of circular end plate 3, the diameter and round nose of the air inlet 8 of guide ring
The diameter of 3 centre bore of plate is identical, and guide ring 4 is in the shape of a trumpet, and the diameter of the air inlet 8 of guide ring is greater than the gas outlet of guide ring
The diameter of 9 diameter, air inlet 8 to the gas outlet of guide ring 9 of guide ring gradually successively decreases；Premix chamber 5 and the fixed company of guide ring 4
Logical, premix chamber 5 is cylindrical structure, and the diameter of premix chamber 5 and the diameter of gas outlet 9 of guide ring are identical.
Embodiment 3
As shown in Fig. 1-4, a kind of gas-turbine combustion chamber cyclone and component of the present embodiment, including cyclone and be set to
The guide ring 4 and premix chamber 5 of cyclone airflow downstream, guide ring 4 is between cyclone and premix chamber 5, cyclone, guide ring
4 are integrally formed with premix chamber 5；The cyclone is radial swirler, multiple swirl vanes 1 including arranging lopping, eddy flow leaf
1 top of piece is fixedly connected with circular end plate 3, and 1 bottom of swirl vane is bolted with combustor endcover 2, is set on combustor endcover 2
There is fuel nozzle pilot hole, combustor endcover 2 is arranged concentrically with circular end plate 3, and circular end plate 3 is equipped with concentric centre bore；
Swirl vane 1 radially extends, and the eddy flow conduit 7 extended along centre bore direction, eddy flow conduit 7 are formed between adjacent swirl vane
Equipped with fuel nozzle 6, fuel nozzle 6 is installed on pilot hole, and fuel nozzle 6 is equipped with multiple fuel jet orifices, swirl vane 1
Outer end width is greater than inner end width, and the quantity of swirl vane is 16, and 45 ° of the setting angle of swirl vane, fuel nozzle 6 is located at
Among 7 inlet end of eddy flow conduit, fuel jet orifice sprays fuel to two sides swirl vane 1.
The guide ring 4 is connected to the fixation of the centre bore of circular end plate 3, the diameter and round nose of the air inlet 8 of guide ring
The diameter of 3 centre bore of plate is identical, and guide ring 4 is in the shape of a trumpet, and the diameter of the air inlet 8 of guide ring is greater than the gas outlet of guide ring
The diameter of 9 diameter, air inlet 8 to the gas outlet of guide ring 9 of guide ring gradually successively decreases；Premix chamber 5 and the fixed company of guide ring 4
Logical, premix chamber 5 is cylindrical structure, and the diameter of premix chamber 5 and the diameter of gas outlet 9 of guide ring are identical.
Embodiment 4
As shown in Fig. 1-2 and Fig. 5-6, a kind of gas-turbine combustion chamber cyclone and component of the present embodiment, including cyclone and
Be set to the guide ring 4 and premix chamber 5 of cyclone airflow downstream, guide ring 4 between cyclone and premix chamber 5, cyclone,
Guide ring 4 and premix chamber 5 are integrally formed；The cyclone is radial swirler, multiple swirl vanes 1 including arranging lopping,
1 top of swirl vane is fixedly connected with circular end plate 3, and 1 bottom of swirl vane is bolted with combustor endcover 2, combustor end
Lid 2 is equipped with fuel nozzle pilot hole, and combustor endcover 2 is arranged concentrically with circular end plate 3, and circular end plate 3 is equipped with concentric
Centre bore；Swirl vane 1 radially extends, and the eddy flow conduit 7 extended along centre bore direction, rotation are formed between adjacent swirl vane
Chute road 7 is equipped with fuel nozzle 6, and fuel nozzle 6 is installed on pilot hole, and fuel nozzle 6 is equipped with multiple fuel jet orifices, eddy flow
The outer end width of blade 1 is greater than inner end width, and the quantity of swirl vane is 8,50 ° of the setting angle of swirl vane, fuel spray
Pipe 6 is located at 1 chamfering of swirl vane of 7 inlet end two sides of eddy flow conduit, and fuel jet orifice is sprayed to 7 inlet of eddy flow conduit and fired
Material.
The guide ring 4 is connected to the fixation of the centre bore of circular end plate 3, the diameter and round nose of the air inlet 8 of guide ring
The diameter of 3 centre bore of plate is identical, and guide ring 4 is in the shape of a trumpet, and the diameter of the air inlet 8 of guide ring is greater than the gas outlet of guide ring
The diameter of 9 diameter, air inlet 8 to the gas outlet of guide ring 9 of guide ring gradually successively decreases；Premix chamber 5 and the fixed company of guide ring 4
Logical, premix chamber 5 is cylindrical structure, and the diameter of premix chamber 5 and the diameter of gas outlet 9 of guide ring are identical.
Swirl vane quantity is 4-24 piece, and when setting angle is 30-60 °, the mixed effect of fuel and air is best.
In conclusion keeping air and fuel abundant using a kind of gas-turbine combustion chamber cyclone of the invention and component
It is uniformly mixed and stablizes and be transmitted to burner inner liner, realize and stablize burning, prevent from being tempered, inhibit the advantageous effects of combustion oscillation.
The invention is not limited to specific embodiments above-mentioned.The present invention, which expands to, any in the present specification to be disclosed
New feature or any new combination, and disclose any new method or process the step of or any new combination.
Claims (10)
1. a kind of gas-turbine combustion chamber cyclone and component, it is characterised in that: including cyclone and be set to cyclone air-flow
The guide ring (4) and premix chamber (5), the cyclone in downstream are connected to guide ring (4), and guide ring (4) and premix chamber (5) are even
It is logical.
2. gas-turbine combustion chamber cyclone as described in claim 1 and component, it is characterised in that: the cyclone is radial
Cyclone, multiple swirl vanes (1) including arranging lopping, swirl vane (1) top are fixedly connected with circular end plate (3), revolve
Stream blade (1) bottom is detachably connected with combustor endcover (2), and combustor endcover (2) is arranged concentrically with circular end plate (3), circle
Shape end plate (3) is equipped with concentric centre bore；Swirl vane (1) radially extends, and is formed between adjacent swirl vane (1)
The eddy flow conduit (7) that heart hole tangential direction extends, eddy flow conduit (7) are equipped with fuel nozzle (6), which is installed on
On combustor endcover (2), fuel nozzle (6) is equipped with multiple fuel jet orifices.
3. gas-turbine combustion chamber cyclone as claimed in claim 2 and component, it is characterised in that: the swirl vane (1)
Outer end width be greater than inner end width, there are chamfering in the outer end two sides of swirl vane (1).
4. gas-turbine combustion chamber cyclone as claimed in claim 3 and component, it is characterised in that: the fuel nozzle (6)
At swirl vane (1) chamfering of eddy flow conduit (7) inlet end two sides, fuel jet orifice is sprayed to eddy flow conduit (7) inlet
Fuel.
5. gas-turbine combustion chamber cyclone as claimed in claim 2 and component, it is characterised in that: the fuel nozzle (6)
Among eddy flow conduit (7) inlet end, fuel jet orifice sprays fuel to two sides swirl vane (1).
6. gas-turbine combustion chamber cyclone as claimed in claim 2 and component, it is characterised in that: the guide ring (4) with
The fixed connection of the centre bore of circular end plate (3), the diameter of the air inlet (8) of guide ring and the diameter of circular end plate (3) centre bore
It is identical.
7. gas-turbine combustion chamber cyclone as described in claim 1 and component, it is characterised in that: the guide ring (4) is in
Bell mouth shape.
8. gas-turbine combustion chamber cyclone as claimed in claim 7 and component, it is characterised in that: the air inlet of the guide ring
The diameter of mouth (8) is greater than the diameter of the gas outlet (9) of guide ring, and the air inlet (8) of guide ring arrives the gas outlet (9) of guide ring
Diameter gradually successively decreases.
9. gas-turbine combustion chamber cyclone as described in claim 1 and component, it is characterised in that: the premix chamber (5) is
Cylindrical structure.
10. gas-turbine combustion chamber cyclone as described in claim 1 and component, it is characterised in that: the cyclone, water conservancy diversion
Ring (4) and premix chamber (5) are integrally formed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811404515.2A CN109489070A (en) | 2018-11-23 | 2018-11-23 | A kind of gas-turbine combustion chamber cyclone and component |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811404515.2A CN109489070A (en) | 2018-11-23 | 2018-11-23 | A kind of gas-turbine combustion chamber cyclone and component |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109489070A true CN109489070A (en) | 2019-03-19 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811404515.2A Pending CN109489070A (en) | 2018-11-23 | 2018-11-23 | A kind of gas-turbine combustion chamber cyclone and component |
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| CN (1) | CN109489070A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111947144A (en) * | 2019-05-14 | 2020-11-17 | 芜湖美的厨卫电器制造有限公司 | Full-premix combustion assembly, manufacturing process thereof and full-premix combustor |
| CN112097260A (en) * | 2020-07-08 | 2020-12-18 | 成都航利航空科技有限责任公司 | Novel high-precision air swirler and manufacturing method thereof |
| CN114427689A (en) * | 2022-01-20 | 2022-05-03 | 中国空气动力研究与发展中心空天技术研究所 | Disc-shaped rotary detonation combustion chamber capable of realizing supersonic flow field observation |
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| CN103776058A (en) * | 2012-10-22 | 2014-05-07 | 阿尔斯通技术有限公司 | Burner |
| CN205825113U (en) * | 2016-06-16 | 2016-12-21 | 上海和兰动力科技有限公司 | The radial swirler of gas-turbine combustion chamber |
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| CN207006235U (en) * | 2017-07-03 | 2018-02-13 | 上海泛智能源装备有限公司 | A kind of pre-mixing apparatus of gas turbine and combustion chamber |
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| DE4124491C1 (en) * | 1991-07-24 | 1992-10-15 | Erno Raumfahrttechnik Gmbh, 2800 Bremen, De | Drive set with gaseous and/or liq. fuel delivery - has annular chamber, whose middle section is divided into several narrow chambers |
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| CN103776058A (en) * | 2012-10-22 | 2014-05-07 | 阿尔斯通技术有限公司 | Burner |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111947144A (en) * | 2019-05-14 | 2020-11-17 | 芜湖美的厨卫电器制造有限公司 | Full-premix combustion assembly, manufacturing process thereof and full-premix combustor |
| CN111947144B (en) * | 2019-05-14 | 2022-09-27 | 芜湖美的厨卫电器制造有限公司 | Full-premix combustion assembly, manufacturing process thereof and full-premix combustor |
| CN112097260A (en) * | 2020-07-08 | 2020-12-18 | 成都航利航空科技有限责任公司 | Novel high-precision air swirler and manufacturing method thereof |
| CN112097260B (en) * | 2020-07-08 | 2022-09-09 | 成都航利航空科技有限责任公司 | High-precision air swirler and manufacturing method thereof |
| CN114427689A (en) * | 2022-01-20 | 2022-05-03 | 中国空气动力研究与发展中心空天技术研究所 | Disc-shaped rotary detonation combustion chamber capable of realizing supersonic flow field observation |
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