CN104456624B - The air intake structure of gas turbine fuel nozzles - Google Patents
The air intake structure of gas turbine fuel nozzles Download PDFInfo
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- CN104456624B CN104456624B CN201410642176.7A CN201410642176A CN104456624B CN 104456624 B CN104456624 B CN 104456624B CN 201410642176 A CN201410642176 A CN 201410642176A CN 104456624 B CN104456624 B CN 104456624B
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- air
- gas turbine
- nozzle
- passage
- regulating sleeve
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Abstract
The present invention relates to gas turbine technology field, there is provided a kind of air intake structure of gas turbine fuel nozzles.The fuel nozzle includes central air passage and the fuel cavity being interconnected, and central air passage is used to be passed through air into fuel cavity；One end of central air passage hangs flange provided with nozzle, and nozzle suspension flange is provided with the air inlet passage for being used for that air to be passed through into central air passage；The outer movable sleeve of nozzle suspension flange is provided with regulating sleeve, and regulating sleeve is used for the open size that air inlet passage is limited by moving axially.By axially adjustable regulating sleeve, the flow into the air of central air passage can be adjusted, so as to ensure that fuel and air have good premixing effect, prevents nozzle exit from producing tempering, improves the reliability of nozzle；In addition, can also realize the variable speed of gas turbine by regulating sleeve.
Description
Technical field
The present invention relates to gas turbine technology field, a kind of more particularly to air intake structure of gas turbine fuel nozzles enters
Depressed structure.
Background technology
Traditional gas-turbine combustion chamber uses diffusion combustion technology, due to the localized hyperthermia in combustion chamber, causes it dirty
Thing discharge is contaminated, especially discharged nitrous oxides are higher.The generation technology of gas turbine, category are used for using the combustion chamber of premixed combustion
In one of clean energy technology, the discharge of pollutant can be effectively reduced while generation load requirement is met.Among these
The design of gas-turbine combustion chamber nozzle is particularly important for tissue burning, reduction pollutant emission.
In premix fuel nozzle in the prior art, nozzle rear is easily tempered, it is therefore desirable to have featheriness air pair
Protected at nozzle rear.But the flow of featheriness air often has difference, featheriness air stream under varying environment and weather
Amount is relatively low to cause the generation of tempering, cause head to be burned out, have a strong impact on the safety and reliability of gas turbine.
The content of the invention
(1) technical problem to be solved
It ensure that fuel and air have the gas turbine of good premixing effect it is an object of the invention to provide a kind of
The air intake structure of fuel nozzle.
(2) technical scheme
To achieve the above object, the invention provides a kind of air intake structure of gas turbine fuel nozzles, including mutually interconnect
Logical central air passage and fuel cavity, the central air passage are used to be passed through air into the fuel cavity；The center
One end of air duct hangs flange provided with nozzle, and the nozzle suspension flange, which is provided with, to be used for into the central air passage
It is passed through the air inlet passage of air；The outer movable sleeve of nozzle suspension flange is provided with regulating sleeve, and the regulating sleeve is used for
The open size of the air inlet passage is limited by moving axially.
It is preferred that, the nozzle suspension flange includes connection end and neck, and the air inlet passage is arranged on the neck
Portion.
It is preferred that, the sidewall thread that the regulating sleeve hangs flange with the nozzle is connected.
It is preferred that, the regulating sleeve is driven by stepper motor to be rotated.
It is preferred that, central axis of the air inlet passage perpendicular to the central air passage.
It is preferred that, the rectangular cross-section of the air inlet passage.
It is preferred that, it is characterised in that the air inlet passage is to hang uniformly to divide in the circumference of flange in the nozzle
Cloth it is multiple.
(3) beneficial effect
A kind of air intake structure for gas turbine fuel nozzles that the present invention is provided, including interconnected central air passage
And fuel cavity, central air passage is for being passed through air into fuel cavity；One end of central air passage is provided with nozzle suspension method
Orchid, nozzle suspension flange is provided with the air inlet passage for being used for that air to be passed through into central air passage；Nozzle hangs flange
Outer movable sleeve is provided with regulating sleeve, and regulating sleeve is used for the open size that air inlet passage is limited by moving axially.Pass through
Axially adjustable regulating sleeve, can adjust the flow into the air of central air passage, so as to ensure that fuel has with air
Good premixing effect, prevents nozzle exit from producing tempering, improves the reliability of nozzle；In addition, by regulating sleeve also
The variable speed of gas turbine can be achieved.
Brief description of the drawings
Fig. 1 is a kind of sectional view of the air intake structure of gas turbine fuel nozzles of the embodiment of the present invention；
Fig. 2 is the zoomed-in view at A in Fig. 1；
Fig. 3 is a kind of 3-D view of the air intake structure of gas turbine fuel nozzles of the embodiment of the present invention.
Reference：
1st, central air passage；2nd, fuel cavity；3rd, air inlet passage；4th, inner tube；5th, outer tube；6th, nozzle suspension flange；
7th, regulating sleeve.
Embodiment
With reference to the accompanying drawings and examples, the embodiment to the present invention is described in further detail.Implement below
Example is used to illustrate the present invention, but is not limited to the scope of the present invention.
In the description of the invention, it is necessary to which explanation, unless otherwise clearly defined and limited, term " connection " should be done
It broadly understood, for example, it may be being fixedly connected or being detachably connected, or be integrally connected；Can be joined directly together,
It can also be indirectly connected to by intermediary.For the ordinary skill in the art, it can understand above-mentioned with concrete condition
The concrete meaning of term in the present invention.
With reference to shown in Fig. 1 and Fig. 3, a kind of air intake structure of gas turbine fuel nozzles provided in an embodiment of the present invention should
Fuel nozzle includes inner tube 4 and outer tube 5, and inner tube 4 plugs in outer tube 5 and is relatively fixed connection, and inner tube 4 is defined as center air
Passage 1, is defined as fuel cavity 2 between inner tube 4 and outer tube 5, central air passage 1 and fuel cavity 2 are interconnected, and center air leads to
Road 1 is used to be passed through air into fuel cavity 2, and the fuel for being premixed into air is more prone to realize abundant burning, can effectively prevent spray
Mouth exit produces tempering, improves the reliability of nozzle.
One end of central air passage 1 hangs flange 6 provided with nozzle, and nozzle suspension flange 6 is used to play fuel nozzle
Fixed effect, the nozzle suspension flange 6 of the present embodiment is provided with the air for being used to be passed through air into central air passage 1 and entered
Mouth passage 3, air inlet passage 3 is preferably to hang equally distributed multiple in the circumference of flange 6 in nozzle, that is, increases air inlet
Amount, makes the air-flow of entrance balanced, beneficial to premixing subsequently with fuel again；The outer movable sleeve of nozzle suspension flange 6 is provided with adjusting set
Cylinder 7, the sidewall thread that regulating sleeve 7 preferably hangs flange 6 with nozzle is connected；Regulating sleeve 7 is realized axially by rotating
It is mobile, and then by moving axially the open size of restriction air inlet passage 3；The section of air inlet passage 3 is preferably square
Shape, rectangle is close to end face of the one side of regulating sleeve 7 parallel to regulating sleeve 7, thus, make the axial movement of regulating sleeve 7 away from
From the open area linear correlation with air inlet passage 3, i.e., during regulating sleeve 7 is moved axially, air intake leads to
The open area even variation in road 3.
According to the change of environmental factor, the inlet of air is adjusted by regulating sleeve 7, and regulating sleeve 7 preferably passes through
Stepper motor drives rotation, and motor can be adjusted by control system, and control system is provided with the sensor for being capable of induced environment change,
Such as design temperature, humidity, the sensed conditions such as wind speed, control system adjusts air inlet passage 3 according to the change of sensed conditions
Open size.
Nozzle suspension flange 6 includes connection end and neck, and the diameter of connection end is more than the diameter of neck, air inlet passage
3 are preferably provided at neck.When gas turbine is operated, by effects of air pressure, because connection end and neck have diameter difference, air is flowed through
Inside vortex is produced herein, so that air is easier to enter in central air passage 1 from air inlet passage 3；In addition,
Air inlet passage 3 is preferably the central axis upright with central air passage 1, makes the vortex air of periphery be easier to enter
In air inlet passage 3.
Operation：
During gas turbine operation, according to the change of external environment condition, stepper motor, regulation are controlled by control system
Sleeve 7 coordinates change axial location by hanging the screw thread of flange 6 with nozzle, and the open area of air inlet passage 3 is carried out
Adjustment, increaseds or decreases the air mass flow for entering central air passage 1, so as to ensure that fuel and air have well pre-
Mixed effect, can effectively prevent nozzle exit from producing tempering, improve the reliability of nozzle；To the stepless changing of air mass flow,
Also the variable speed of gas turbine can be realized, the abundant burning of fuel is finally realized.
Described above is only the preferred embodiment of the present invention, it is noted that for the ordinary skill people of the art
For member, without departing from the technical principles of the invention, some improvement and replacement can also be made, these improve and replaced
Also it should be regarded as protection scope of the present invention.
Claims (6)
1. a kind of air intake structure of gas turbine fuel nozzles, it is characterised in that including interconnected central air passage (1)
With fuel cavity (2), the central air passage (1) is used to be passed through air into the fuel cavity (2)；The central air passage
(1) one end is provided with nozzle suspension flange (6), and the nozzle suspension flange (6), which is provided with, to be used for the central air passage
(1) air inlet passage (3) of air is passed through in；Described nozzle suspension flange (6) outer movable sleeve is provided with regulating sleeve (7), institute
State the rectangular cross-section of air inlet passage (3), the air inlet passage (3) close on one side of regulating sleeve (7) parallel to
The end face of regulating sleeve (7), the regulating sleeve (7) is used to limit the spacious of the air inlet passage (3) by moving axially
Mouth size.
2. the air intake structure of gas turbine fuel nozzles according to claim 1, it is characterised in that the nozzle suspension method
Blue (6) include connection end and neck, and the air inlet passage (3) is arranged on the neck.
3. the air intake structure of gas turbine fuel nozzles according to claim 1, it is characterised in that the regulating sleeve
(7) it is connected with nozzle suspension flange (6) screw thread.
4. the air intake structure of gas turbine fuel nozzles according to claim 3, it is characterised in that the regulating sleeve
(7) driven and rotated by stepper motor.
5. the air intake structure of gas turbine fuel nozzles according to claim 1, it is characterised in that the air intake leads to
Central axis of the road (3) perpendicular to the central air passage (1).
6. the air intake structure of the gas turbine fuel nozzles according to claim any one of 1-5, it is characterised in that the sky
Gas access road (3) is multiple, and multiple air inlet passages (3) hang uniform in the circumference of flange (6) in the nozzle
Distribution.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410642176.7A CN104456624B (en) | 2014-11-11 | 2014-11-11 | The air intake structure of gas turbine fuel nozzles |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410642176.7A CN104456624B (en) | 2014-11-11 | 2014-11-11 | The air intake structure of gas turbine fuel nozzles |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104456624A CN104456624A (en) | 2015-03-25 |
| CN104456624B true CN104456624B (en) | 2017-08-04 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410642176.7A Active CN104456624B (en) | 2014-11-11 | 2014-11-11 | The air intake structure of gas turbine fuel nozzles |
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Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110056905B (en) * | 2018-01-19 | 2023-12-05 | 中国科学院工程热物理研究所 | Double-movable-sleeve positioning component and positioning method for electric nozzle and hot end component |
| CN109185924B (en) * | 2018-08-03 | 2023-09-12 | 新奥能源动力科技（上海）有限公司 | Combustion chamber head device, combustion chamber and gas turbine |
| CN109099461B (en) * | 2018-08-03 | 2023-08-15 | 新奥能源动力科技（上海）有限公司 | Combustion chamber head device, combustion chamber and gas turbine |
| CN109185923B (en) * | 2018-08-03 | 2023-09-12 | 新奥能源动力科技（上海）有限公司 | Combustion chamber head device, combustion chamber and gas turbine |
| CN110285447B (en) * | 2019-06-06 | 2020-07-28 | 同济大学 | Low-emission combustion chamber of gas turbine and variable-load air distribution and adjustment method |
| CN112570394B (en) * | 2020-11-25 | 2022-07-22 | 哈尔滨汽轮机厂有限责任公司 | Method for cleaning nozzle of combustion chamber of heavy-duty gas turbine |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6418709B1 (en) * | 2000-05-15 | 2002-07-16 | United Technologies Corporation | Gas turbine engine liner |
| CN203464333U (en) * | 2013-06-27 | 2014-03-05 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Anti-backfire gas fuel injector used for gas turbine |
| CN103499097B (en) * | 2013-09-29 | 2016-05-11 | 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 combustion chambers burn method for organizing and nozzle that uses medium and low heat value fuel gas |
| CN103822231B (en) * | 2014-03-10 | 2017-11-03 | 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 low swirl combustion chamber nozzle of gas turbine |
| CN204313309U (en) * | 2014-11-11 | 2015-05-06 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | The air intake structure of gas turbine fuel nozzles |
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Effective date of registration: 20200123 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, Beijing, Haidian District science and Technology Park, Tsinghua Science and technology building, block C, 10 Patentee before: Beijing Huatsing Gas Turbine & IGCC Technology Co.,Ltd. |