CN204084467U - The swirl nozzle that the axial two-stage direction of gas-turbine combustion chamber is contrary - Google Patents
The swirl nozzle that the axial two-stage direction of gas-turbine combustion chamber is contrary Download PDFInfo
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- CN204084467U CN204084467U CN201420547162.2U CN201420547162U CN204084467U CN 204084467 U CN204084467 U CN 204084467U CN 201420547162 U CN201420547162 U CN 201420547162U CN 204084467 U CN204084467 U CN 204084467U
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- axial
- flow device
- rotational flow
- swirl
- contrary
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Abstract
The swirl nozzle that the axial two-stage direction of gas-turbine combustion chamber is contrary, is characterized in axial direction arranging in peripheral axial annular air duct and is separately fixed on conical inner body by the swirl-flow devices that two-stage eddy flow direction is contrary; First order swirl-flow devices adopts hollow blade and is connected with center fuel passage, and hollow blade both sides have fuel orifice; First order swirl-flow devices air outlet slit is close to by the air intake of second level swirl-flow devices, and the flow inlet angle of second level swirl-flow devices is identical with the flow angle that first order swirl-flow devices exports, and the blade of two-stage axial rotational flow device is staggered in arrangement.The utility model effectively can increase the air velocity of air duct inner circumferential side, the mixing of enhanced fuel gas and air, ensures that nozzle exit velocity distribution is reasonable, fuel-air blending is even, and then promotes combustion stability.Reduce conical inner body boundary-layer to the impact of nozzle exit velocity type simultaneously, make conical inner body downstream not produce recirculating zone, improve burning reliability.
Description
Technical field
The utility model relates to the contrary swirl nozzle in the axial two-stage direction of gas-turbine combustion chamber, particularly relates to the low-pollution burning chamber of gas turbine nozzle using gas fuel.
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 gas and air realize the change of premix velocity profile by nozzle, reach rational VELOCITY DISTRIBUTION at jet expansion, and mate rational fuel-air mixture example, enter combustion chamber tissue burning.Current, to the design form of gas-turbine combustion chamber nozzle, such as patent document CN 100567823C, adopts the notched air swirling vanes in bottom, improves 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, 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 swirl nozzle that the utility model provides the axial two-stage direction of a kind of gas-turbine combustion chamber contrary, make it on the one hand can while maintenance flame stabilization, increase the air velocity of air duct inner circumferential side, ensure that nozzle exit velocity reasonable layout, fuel-air blending are even; Can also mate on the other hand the mixing effect of nozzle exit velocity distribution, fuel and air, conservative control combustion zone, maintains combustion chamber flow field structure, thus ensures the stability of burning and good Exit temperature distribution.
The technical scheme that the utility model adopts is as follows:
The swirl nozzle that the axial two-stage direction of a kind of gas-turbine combustion chamber is contrary, the peripheral annular air duct that this nozzle comprises center fuel passage, arrange with this center fuel channel coaxial and conical inner body, it is characterized in that: in peripheral axial annular air duct, arrange the swirl-flow devices that two-stage eddy flow direction is contrary successively vertically, be separately fixed on described conical inner body; First order axial rotational flow device is positioned at the front end of peripheral axial annular air duct, and first order axial rotational flow device adopts hollow blade and is connected with center fuel passage, and hollow blade both sides have fuel orifice; First order swirl-flow devices air outlet slit is close to by the air intake of second level axial rotational flow device, and the flow inlet angle of second level axial rotational flow device is identical with the flow angle that first order axial rotational flow device exports, and the blade of two-stage axial rotational flow device is staggered in arrangement.
In technique scheme, the radial height of first order axial rotational flow device is identical with the radial height of peripheral annular air duct, and the radial height of second level axial rotational flow device is 0.1 ~ 0.5 of first order axial rotational flow device radial height.
Preferably, first order axial rotational flow device described in the utility model adopts axial blade formula structure, and blade annularly air duct is evenly arranged, and blade number is between 6 ~ 12; Second level axial rotational flow device adopts axial blade formula structure or axial cascade type structure, and annularly air duct is evenly arranged, blade number or blade grid passage number identical with first order axial rotational flow device.
The swirl nozzle that the axial two-stage direction of gas-turbine combustion chamber described in the utility model is contrary, is characterized in that: the flow-deviation angle α that first order axial rotational flow device produces is equal with the flow-deviation angle that second level axial rotational flow device produces.
Preferably, the pore size of fuel orifice described in the utility model is Φ 0.1 ~ Φ 0.5.Described peripheral axial annular air duct is divided into straight section and contraction section successively along airflow direction, and described first order axial rotational flow device and second level axial rotational flow device are arranged in described straight section.
This utility model compared with prior art, has the following advantages and high-lighting effect:
(1) the utility model adopts the contrary swirl-flow devices in two-stage direction can the mixing of enhanced fuel gas and air, ensure nozzle exit velocity distribution rationally, fuel-air blending is even, and then promotes combustion stability.
(2) the rotational flow air axial velocity of air duct inner circumferential side can increase by the second level of the present utility model swirl-flow devices, reduce conical inner body boundary-layer to the impact of nozzle exit velocity type, ensure air duct inner circumferential side velocity profile and fuel-air blending coupling, conical inner body downstream does not produce recirculating zone, improves burning reliability.
(3) second level of the present utility model swirl-flow devices can provide wider design space for first order swirl-flow devices by the adjustment of blade height, angle, meet the needs of different fuel and air blending, improve the VELOCITY DISTRIBUTION of nozzle center's cone to nozzle outlet portion.
Accompanying drawing explanation
The structural principle schematic diagram of the swirl nozzle that the axial two-stage eddy flow direction of the gas-turbine combustion chamber that Fig. 1 provides for the utility model is contrary.
Fig. 2 is the structure three-dimensional sectional view of axial two-stage swirl nozzle.
Fig. 3 is the principle schematic in the flow rotation direction of two-stage axial rotational flow nozzle.
In figure, symbol description is as follows: 1-center fuel passage; 2-peripheral annular air duct; 3-fuel orifice; 4-first order axial rotational flow device; 5-second level axial rotational flow device; 6-conical inner body; 7-nozzle contraction section; 8-jet expansion.
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 swirl nozzle that the axial two-stage direction of the gas-turbine combustion chamber that Fig. 1 provides for the utility model is contrary, this nozzle comprises center fuel passage 1, and the peripheral annular air duct 2 arranged with this center fuel channel coaxial and conical inner body 6; Conical inner body 6 in peripheral axial annular air duct 2 arranges the swirl-flow devices that two-stage eddy flow direction is contrary vertically successively; First order axial rotational flow device 4 is positioned at the front end of peripheral axial annular air duct 2, and this axial rotational flow device adopts hollow blade and is connected with center fuel passage, and hollow blade both sides have fuel orifice 3; First order axial rotational flow device 4 air outlet slit is close to by the air intake of second level axial rotational flow device 5, the flow inlet angle of second level axial rotational flow device is identical with the flow angle that first order axial rotational flow device exports, and the blade of two-stage axial rotational flow device is staggered in arrangement (see Fig. 2).
The radial height of first order axial rotational flow device is higher than second level axial rotational flow device 5; The radial height of first order axial rotational flow device 4 is identical with the radial height of peripheral annular air duct 2, and the radial height of second level axial rotational flow device is 0.1 ~ 0.5 of first order axial rotational flow device radial height.
First order axial rotational flow device 4 adopts axial blade formula structure, and blade annularly air duct is evenly arranged, and blade number is between 6 ~ 12.Second level axial rotational flow device 5 adopts axial blade formula structure or axial cascade type structure, and annularly air duct is evenly arranged, blade number or blade grid passage number identical with first order axial rotational flow device.
First order axial rotational flow device 4 makes approach airflow direction deflect; Second level axial rotational flow device 5 makes approach air-flow deflect, the flow-deviation angle α equal (as shown in Figure 3) that two-stage axial rotational flow device produces.
Peripheral axial annular air duct of the present utility model can be divided into straight section and contraction section 7 successively along airflow direction, and described first order axial rotational flow device and second level axial rotational flow device are arranged in described straight section.
Operation principle of the present utility model is as follows:
Gas fuel enters axial centre fuel channel 1, first order axial rotational flow device 4 is entered by the perforate of conical inner body 6 wall, spray from blade both sides fuel orifice 3, the pore size of fuel orifice is generally Φ 0.1 ~ Φ 0.5, and spray-hole height can regulate.Air enters peripheral axial annular air duct 2, mixes with fuel in first order axial rotational flow device 4 front end, and deflects through first order axial rotational flow blade speed of action direction, and mixed effect strengthens.After fuel and air Mixture flow out first order axial rotational flow device 4, press close to the effect of air duct inner circumferential side gaseous mixture by second level axial rotational flow device 5 of conical inner body 6, velocity attitude deflects back axially.Away from air duct outer circumferential side fuel and the swirl strength of air Mixture maintenance after first order axial rotational flow device 4 of conical inner body 6, continue the outlet of blending to second level swirl-flow devices 5, with air duct inner circumferential side fuel and air Mixture blending, through nozzle contraction section 7 until jet expansion.Thus form the nozzle exit velocity distribution of coupling and good fuel-air mixing effect, ensure the stability of burning and good Exit temperature distribution.
Claims (7)
1. the swirl nozzle that the axial two-stage direction of gas-turbine combustion chamber is contrary, this nozzle comprises center fuel passage (1), the peripheral annular air duct (2) coaxially arranged with this center fuel passage (1) and conical inner body (6), it is characterized in that: in peripheral axial annular air duct (2), arrange the swirl-flow devices that two-stage eddy flow direction is contrary successively vertically, be separately fixed on described conical inner body (6); First order axial rotational flow device (4) is positioned at the front end of peripheral axial annular air duct (2), first order axial rotational flow device (4) adopts hollow blade and is connected with center fuel passage (1), and hollow blade both sides have fuel orifice (3); First order swirl-flow devices (4) air outlet slit is close to by the air intake of second level axial rotational flow device (5), the flow inlet angle of second level axial rotational flow device (5) is identical with the flow angle that first order axial rotational flow device (4) exports, and the blade of two-stage axial rotational flow device is staggered in arrangement.
2. the swirl nozzle that the axial two-stage direction of gas-turbine combustion chamber as claimed in claim 1 is contrary, it is characterized in that: the radial height of first order axial rotational flow device (4) is identical with the radial height of peripheral annular air duct (2), the radial height (5) of second level axial rotational flow device is 0.1 ~ 0.5 of first order axial rotational flow device radial height.
3. the swirl nozzle that the axial two-stage direction of gas-turbine combustion chamber as claimed in claim 1 or 2 is contrary, it is characterized in that: first order axial rotational flow device (4) adopts axial blade formula structure, blade annularly air duct is evenly arranged, and blade number is between 6 ~ 12.
4. the swirl nozzle that the axial two-stage direction of gas-turbine combustion chamber as claimed in claim 1 or 2 is contrary, it is characterized in that: second level axial rotational flow device (5) adopts axial blade formula structure or axial cascade type structure, annularly air duct is evenly arranged, blade number or blade grid passage number identical with first order axial rotational flow device.
5. the swirl nozzle that the axial two-stage direction of gas-turbine combustion chamber as claimed in claim 1 is contrary, is characterized in that: the flow-deviation angle α that first order axial rotational flow device (4) produces is equal with the flow-deviation angle that second level axial rotational flow device (5) produces.
6. the swirl nozzle that the axial two-stage direction of gas-turbine combustion chamber as claimed in claim 1 is contrary, is characterized in that: the pore size of fuel orifice (3) is Φ 0.1 ~ Φ 0.5.
7. the swirl nozzle that the axial two-stage direction of gas-turbine combustion chamber as claimed in claim 1 is contrary, it is characterized in that: described peripheral axial annular air duct (2) is divided into straight section and contraction section (7) successively along airflow direction, and described first order axial rotational flow device (4) and second level axial rotational flow device (5) are arranged in described straight section.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420547162.2U CN204084467U (en) | 2014-09-22 | 2014-09-22 | The swirl nozzle that the axial two-stage direction of gas-turbine combustion chamber is contrary |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420547162.2U CN204084467U (en) | 2014-09-22 | 2014-09-22 | The swirl nozzle that the axial two-stage direction of gas-turbine combustion chamber is contrary |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204084467U true CN204084467U (en) | 2015-01-07 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420547162.2U Withdrawn - After Issue CN204084467U (en) | 2014-09-22 | 2014-09-22 | The swirl nozzle that the axial two-stage direction of gas-turbine combustion chamber is contrary |
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| CN (1) | CN204084467U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104266228B (en) * | 2014-09-22 | 2018-02-09 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Gas-turbine combustion chamber axial direction two-stage swirl nozzle in opposite direction |
| CN109073224A (en) * | 2016-04-28 | 2018-12-21 | 赛峰飞机发动机公司 | For turbine spraying system, in inlet include the air inlet swirler of pneumatic deflector |
| CN111536555A (en) * | 2020-05-08 | 2020-08-14 | 中国航发湖南动力机械研究所 | Engine and engine combustion chamber thereof |
| US11396888B1 (en) | 2017-11-09 | 2022-07-26 | Williams International Co., L.L.C. | System and method for guiding compressible gas flowing through a duct |
-
2014
- 2014-09-22 CN CN201420547162.2U patent/CN204084467U/en not_active Withdrawn - After Issue
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104266228B (en) * | 2014-09-22 | 2018-02-09 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Gas-turbine combustion chamber axial direction two-stage swirl nozzle in opposite direction |
| CN109073224A (en) * | 2016-04-28 | 2018-12-21 | 赛峰飞机发动机公司 | For turbine spraying system, in inlet include the air inlet swirler of pneumatic deflector |
| CN109073224B (en) * | 2016-04-28 | 2021-02-05 | 赛峰飞机发动机公司 | Intake swirler for a turbomachine injection system comprising an aerodynamic deflector at the inlet |
| US11396888B1 (en) | 2017-11-09 | 2022-07-26 | Williams International Co., L.L.C. | System and method for guiding compressible gas flowing through a duct |
| CN111536555A (en) * | 2020-05-08 | 2020-08-14 | 中国航发湖南动力机械研究所 | Engine and engine combustion chamber thereof |
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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: Axial two-level direction inverse rotational flow nozzle of combustor of gas turbine Effective date of registration: 20161104 Granted publication date: 20150107 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 | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20150107 Effective date of abandoning: 20180209 |
|
| AV01 | Patent right actively abandoned |
Granted publication date: 20150107 Effective date of abandoning: 20180209 |
|
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Date of cancellation: 20191211 Granted publication date: 20150107 Pledgee: Tsinghua Holdings Co., Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. Registration number: 2016990000853 |
|
| PC01 | Cancellation of the registration of the contract for pledge of patent right |