CN204513457U - A kind of gas-turbine combustion chamber classification nozzle of air supply - Google Patents
A kind of gas-turbine combustion chamber classification nozzle of air supply Download PDFInfo
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- CN204513457U CN204513457U CN201420766661.0U CN201420766661U CN204513457U CN 204513457 U CN204513457 U CN 204513457U CN 201420766661 U CN201420766661 U CN 201420766661U CN 204513457 U CN204513457 U CN 204513457U
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Abstract
A kind of gas-turbine combustion chamber classification nozzle of air supply, belongs to gas turbine technology field.This nozzle comprises conical inner body and peripheral annular air duct, is provided with center fuel passage in conical inner body; Be furnished with fuel injection device and axial rotational flow device successively vertically in peripheral annular air channel, be furnished with air intake guiding unit in peripheral annular air channel front end, this air intake guiding unit comprises radial guiding flow structure and axial diversion structure; Radial guiding flow structure contains at least two-layer horn-like annular guide shell arranged vertically, and axial diversion structure is made up of the axial support plate be arranged between the horn-like annular guide shell of every two-stage.The utility model, by changing the air intake structure of nozzle, carries out rectification and layering to the air entering nozzle, realizes adjusting the air flowing in nozzle in the charging stage.While guarantee air-flow axial velocity, the needing of based on fuel blending adjusts air-distribution, thus ensures good Exit temperature distribution.
Description
Technical field
The utility model relates to a kind of gas-turbine combustion chamber classification nozzle of air supply, 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 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.Current, such as, to the design form of gas-turbine combustion chamber nozzle, Chinese patent literature CN100567823C, adopt 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 utility model provides a kind of gas-turbine combustion chamber classification nozzle of air supply, be intended to the air intake structure by changing nozzle, rectification and layering are carried out to the air entering nozzle, realize adjusting the air flowing in nozzle in the charging stage, while guarantee air-flow axial velocity, the needing of based on fuel blending adjusts air-distribution, thus ensures good outlet fuel distribution.
The technical scheme that the utility model adopts is as follows: a kind of gas-turbine combustion chamber classification nozzle of air supply, and this nozzle comprises conical inner body and the peripheral annular air duct coaxially arranged with this conical inner body, is provided with center fuel passage in conical inner body; Described peripheral annular air duct is furnished with fuel injection device and axial rotational flow device vertically successively, fuel injection device both sides are provided with fuel orifice, it is characterized in that: be furnished with air intake guiding unit in peripheral annular air channel front end, this air intake guiding unit comprises radial guiding flow structure and axial diversion structure; Described radial guiding flow structure contains at least two-layer horn-like annular guide shell arranged vertically, and the bottom of each horn-like annular guide shell is all connected with the front end of fuel injection device; Each horn-like annular guide shell at least has a discharge capacity dispensing orifice vertically, and flow distributing hole is circumferentially evenly arranged; Described axial diversion structure is made up of axial support plate circumferentially, and axial support plate is connected between the horn-like annular guide shell of every two-stage.
Preferably, the molded line of described horn-like annular guide shell is hyperbola; The number of horn-like annular guide shell is between 2 ~ 5.
Preferably, the axial support plate quantity between every two-layer horn-like annular guide shell props up is identical, and axial support plate is circumferentially evenly arranged, and number is between 6 ~ 12.
Preferably, described flow distributing hole row is vertically 2 ~ 5 rows, and often equidistantly arranges between row, and pore size is Φ 0.1mm ~ Φ 2mm.
In technique scheme, described axial rotational flow device adopts axial blade formula structure, and blade peripherally annular air channel (2) is evenly arranged, and blade number is between 4 ~ 6; The pore size of described fuel orifice is Φ 0.1mm ~ Φ 0.5mm; Described peripheral annular air duct has a nozzle contraction section vertically after axial rotational flow device.
This utility model compared with prior art, have the following advantages and beneficial effect: 1. radial air inlet structure of the present utility model carries out radially layered to air, and adjusted by the flow of flow distributing hole to each interlayer, effectively improve the air inlet effect of nozzle, have positive role to adjustment nozzle interior flow field.2. axial admission structure of the present utility model carries out axially staged and rectification to each layer of air, coordinate fuel injection device to distribute the air mass flow be applicable to and blending is carried out to fuel gas, the mixing effect of effective guarantee fuel gas, and eliminate the air inlet problem of non-uniform caused owing to carrying out flow disturbance.
Accompanying drawing explanation
The structural principle schematic diagram of a kind of gas-turbine combustion chamber classification nozzle of air supply that Fig. 1 provides for the utility model.
Fig. 2 is the structure three-dimensional sectional view of Fig. 1.
Fig. 3 is the air intake structure principle schematic of classification nozzle of air supply.
Fig. 4 is the central cross-section sectional view of Fig. 3.
Fig. 5 is the three dimensional sectional view of Fig. 3.
In figure, symbol description is as follows: 1-conical inner body; 2-peripheral annular air duct; The horn-like annular guide shell of 3-; The axial support plate of 4-; 6-flow distributing hole; 7-center fuel passage; 8-fuel injection device; 9-fuel orifice; 10-axial rotational flow device; 11-nozzle contraction section.
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 a kind of gas-turbine combustion chamber classification nozzle of air supply that Fig. 1, Fig. 2 provide for the utility model, this nozzle comprises conical inner body 1 and the peripheral annular air duct 2 coaxially arranged with this conical inner body 1, center fuel passage 7 is provided with in conical inner body 1, in peripheral annular air channel 2, be axially furnished with fuel injection device 8 and axial rotational flow device 10 successively, fuel injection device 8 both sides are provided with fuel orifice 9.Fuel gas enters nozzle from conical inner body 1, enters fuel injection device 8 by wall perforate, sprays from the fuel orifice 9 of both sides.
See Fig. 3, Fig. 4 and Fig. 5, be furnished with air intake guiding unit in the front end of peripheral annular air channel 2, this air intake guiding unit comprises radial guiding flow structure and axial diversion structure; Described radial guiding flow structure contains at least two-layer horn-like annular guide shell 3 arranged vertically, and the bottom of each horn-like annular guide shell is all connected with the front end of fuel injection device 8; The wall of each horn-like annular guide shell 3 at least has a discharge capacity dispensing orifice 6 vertically, and flow distributing hole 6 circumferentially; Flow distributing hole 6 vertically row is between 2 ~ 5, preferably evenly distributed, and pore size is Φ 0.1mm ~ Φ 2mm.Horn-like annular guide shell 3 molded line is preferably hyperbola, and import is radial direction, exports as axial direction; Horn-like annular guide shell 3 number is preferably between 2 ~ 5.
Described axial diversion structure is made up of axial support plate 4 circumferentially, and axial support plate 4 is connected between the horn-like annular guide shell 3 of every two-stage.Axial support plate 4 quantity between every two-layer horn-like annular guide shell props up is identical, and is circumferentially evenly arranged, and number is between 6 ~ 12.
Axial rotational flow device 10 adopts axial blade formula structure, and blade annularly air duct is evenly arranged, and blade number is between 4 ~ 6.Fuel orifice 9 pore size is Φ 0.1mm ~ Φ 0.5mm, fuel orifice 9 height adjustable.Peripheral annular air duct 2 has a nozzle contraction section 11 vertically after axial rotational flow device 10.
Air-flow eliminates disturbance in the radial direction through radial guiding flow structure, eliminates the disturbance on axial direction, enter nozzle interior afterwards with fuel gas generation blending through axial diversion structure.
Operation principle of the present utility model is as follows:
Gas fuel enters nozzle from center fuel channel 7, enters fuel injection device 8, spray from the fuel orifice 9 of both sides by the perforate of conical inner body 1 wall.Air is divided into radial direction vertically through air intake structure and multistagely enters nozzle, and carry out first time layering through radial guiding flow structure air, by the flow distributing hole 6 on radial guiding flow structure, air carries out the assignment of traffic of interlayer.Air carries out axially staged and rectification through axial diversion structure after entering the region between radial guiding flow structure again.Air eliminates disturbance in the radial direction through radial guiding flow structure, eliminates the disturbance on axial direction through axial diversion structure.Afterwards, the fuel gas blending that sprays with fuel orifice 9 in fuel injection device 8 front end of air.Gaseous mixture produces deflection through axial rotational flow device 10, accelerates to jet expansion through nozzle contraction section 11 gaseous mixture.By air intake structure to the classification of air and rectification, realize adjusting the air flowing in nozzle in the charging stage.While guarantee air-flow axial velocity, the needing of based on fuel blending adjusts air-distribution, thus ensures good outlet fuel distribution.
Claims (7)
1. a gas-turbine combustion chamber classification nozzle of air supply, this nozzle comprises conical inner body (1) and the peripheral annular air duct (2) coaxially arranged with this conical inner body (1), is provided with center fuel passage (7) in conical inner body; Described peripheral annular air duct (2) is furnished with fuel injection device (8) and axial rotational flow device (10) vertically successively, fuel injection device (8) both sides are provided with fuel orifice (9), it is characterized in that: be furnished with air intake guiding unit in peripheral annular air channel (2) front end, this air intake guiding unit comprises radial guiding flow structure and axial diversion structure; Described radial guiding flow structure contains at least two-layer horn-like annular guide shell (3) arranged vertically, and the bottom of each horn-like annular guide shell is all connected with the front end of fuel injection device (8); Each horn-like annular guide shell (3) at least has a discharge capacity dispensing orifice (6) vertically, and flow distributing hole (6) is circumferentially evenly arranged; Described axial diversion structure is made up of axial support plate (4) circumferentially, and axial support plate (4) is connected between the horn-like annular guide shell (3) of every two-stage.
2. a kind of gas-turbine combustion chamber classification nozzle of air supply as claimed in claim 1, is characterized in that: the molded line of described horn-like annular guide shell (3) is hyperbola; The number of horn-like annular guide shell (3) is between 2 ~ 5.
3. a kind of gas-turbine combustion chamber classification nozzle of air supply as claimed in claim 1, it is characterized in that: axial support plate (4) quantity between every two-layer horn-like annular guide shell (3) is identical, axial support plate (4) is circumferentially evenly arranged, and number is between 6 ~ 12.
4. a kind of gas-turbine combustion chamber classification nozzle of air supply as described in claim 1,2 or 3, it is characterized in that: described flow distributing hole (6) row is vertically 2 ~ 5 rows, and often equidistantly arrange between row, pore size is Φ 0.1mm ~ Φ 2mm.
5. as claim asks a kind of gas-turbine combustion chamber classification nozzle of air supply as described in 1,2 or 3, it is characterized in that: described axial rotational flow device (10) adopts axial blade formula structure, blade peripherally annular air channel (2) is evenly arranged, and blade number is between 4 ~ 6.
6. as claim asks a kind of gas-turbine combustion chamber classification nozzle of air supply as described in 1,2 or 3, it is characterized in that: the pore size of described fuel orifice (9) is Φ 0.1mm ~ Φ 0.5mm.
7., as claim asks a kind of gas-turbine combustion chamber classification nozzle of air supply as described in 1,2 or 3, it is characterized in that: described peripheral annular air duct (2) has a nozzle contraction section (11) vertically after axial rotational flow device (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420766661.0U CN204513457U (en) | 2014-12-08 | 2014-12-08 | A kind of gas-turbine combustion chamber classification nozzle of air supply |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420766661.0U CN204513457U (en) | 2014-12-08 | 2014-12-08 | A kind of gas-turbine combustion chamber classification nozzle of air supply |
Publications (1)
| Publication Number | Publication Date |
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| CN204513457U true CN204513457U (en) | 2015-07-29 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420766661.0U Withdrawn - After Issue CN204513457U (en) | 2014-12-08 | 2014-12-08 | A kind of gas-turbine combustion chamber classification nozzle of air supply |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104566459A (en) * | 2014-12-08 | 2015-04-29 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Grading air intake nozzle of combustor of gas turbine |
| CN107575889A (en) * | 2017-09-05 | 2018-01-12 | 中国联合重型燃气轮机技术有限公司 | The fuel nozzle of gas turbine |
| CN107620980A (en) * | 2017-09-05 | 2018-01-23 | 中国联合重型燃气轮机技术有限公司 | The rectifier of gas turbine |
| CN107620983A (en) * | 2017-09-05 | 2018-01-23 | 中国联合重型燃气轮机技术有限公司 | Fuel nozzle |
| CN107655033A (en) * | 2017-09-05 | 2018-02-02 | 中国联合重型燃气轮机技术有限公司 | fuel nozzle and rectifier |
| CN107702147A (en) * | 2017-09-05 | 2018-02-16 | 中国联合重型燃气轮机技术有限公司 | The fuel nozzle of gas turbine |
| CN108954381A (en) * | 2017-04-27 | 2018-12-07 | 斗山重工业建设有限公司 | Fuel injector assembly, fuel nozzle module and gas turbine |
| CN113048513A (en) * | 2021-04-14 | 2021-06-29 | 西北工业大学 | Multistage oil spout hole center cone integration afterburner |
| 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
- 2014-12-08 CN CN201420766661.0U patent/CN204513457U/en not_active Withdrawn - After Issue
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104566459B (en) * | 2014-12-08 | 2017-12-12 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of gas-turbine combustion chamber is classified nozzle of air supply |
| CN104566459A (en) * | 2014-12-08 | 2015-04-29 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Grading air intake nozzle of combustor of gas turbine |
| CN108954381A (en) * | 2017-04-27 | 2018-12-07 | 斗山重工业建设有限公司 | Fuel injector assembly, fuel nozzle module and gas turbine |
| US10955139B2 (en) | 2017-04-27 | 2021-03-23 | Doosan Heavy Industries & Construction Co., Ltd. | Fuel nozzle assembly, and fuel nozzle module and gas turbine having the same |
| CN107655033B (en) * | 2017-09-05 | 2020-07-14 | 中国联合重型燃气轮机技术有限公司 | Fuel nozzle and flow straightener |
| CN107655033A (en) * | 2017-09-05 | 2018-02-02 | 中国联合重型燃气轮机技术有限公司 | fuel nozzle and rectifier |
| CN107702147A (en) * | 2017-09-05 | 2018-02-16 | 中国联合重型燃气轮机技术有限公司 | The fuel nozzle of gas turbine |
| CN107620983A (en) * | 2017-09-05 | 2018-01-23 | 中国联合重型燃气轮机技术有限公司 | Fuel nozzle |
| CN107620980A (en) * | 2017-09-05 | 2018-01-23 | 中国联合重型燃气轮机技术有限公司 | The rectifier of gas turbine |
| CN107702147B (en) * | 2017-09-05 | 2020-07-14 | 中国联合重型燃气轮机技术有限公司 | Fuel nozzle for gas turbine |
| CN107575889A (en) * | 2017-09-05 | 2018-01-12 | 中国联合重型燃气轮机技术有限公司 | The fuel nozzle of gas turbine |
| CN107620983B (en) * | 2017-09-05 | 2023-04-25 | 中国联合重型燃气轮机技术有限公司 | Fuel nozzle |
| CN107620980B (en) * | 2017-09-05 | 2023-04-25 | 中国联合重型燃气轮机技术有限公司 | Rectifier of gas turbine |
| 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 |
| CN113048513A (en) * | 2021-04-14 | 2021-06-29 | 西北工业大学 | Multistage oil spout hole center cone integration afterburner |
| CN113048513B (en) * | 2021-04-14 | 2022-07-01 | 西北工业大学 | Multistage oil spout hole center cone integration afterburner |
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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: Grading air intake nozzle of combustor of gas turbine 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 | ||
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20150729 Effective date of abandoning: 20171212 |
|
| AV01 | Patent right actively abandoned |
Granted publication date: 20150729 Effective date of abandoning: 20171212 |
|
| 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 |