CN104456624A - Air inlet structure for fuel nozzle of gas turbine - Google Patents
Air inlet structure for fuel nozzle of gas turbine Download PDFInfo
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- CN104456624A CN104456624A CN201410642176.7A CN201410642176A CN104456624A CN 104456624 A CN104456624 A CN 104456624A CN 201410642176 A CN201410642176 A CN 201410642176A CN 104456624 A CN104456624 A CN 104456624A
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- air
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- air inlet
- gas turbine
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Abstract
The invention relates to the technical field of gas turbines, and provides an air inlet structure for a fuel nozzle of a gas turbine. The fuel nozzle comprises a center air channel and a fuel cavity which are communicated with each other, and the center air channel is used for connecting the air into the fuel cavity. A nozzle hanging flange is arranged at one end of the center air channel, and the nozzle hanging flange is provided with air inlet channels used for connecting the air into the center air channel. The nozzle hanging flange is movably sleeved with an adjusting sleeve, and the adjusting sleeve is used for limiting the sizes of openings of the air inlet channels through axial movement. By axially adjusting the adjusting sleeve, the flow of the air entering the center air channel can be adjusted, hence, it is guaranteed that fuel and air have a good pre-mixing effect, tempering can be prevented from happening to a nozzle outlet, and the reliability of the nozzle is improved; in addition, stepless speed change of the gas turbine can be achieved through the adjusting sleeve.
Description
Technical field
The present invention relates to gas turbine technology field, particularly a kind of air intake structure of air intake structure of gas turbine fuel nozzles.
Background technology
Traditional gas-turbine combustion chamber adopts diffusion combustion technology, and due to the localized hyperthermia in combustion chamber, cause its pollutant emission, especially discharged nitrous oxides is higher.Adopt the combustion chamber of premixed combustion to be used for the generation technology of gas turbine, belong to one of clean energy technology, while meeting generation load requirement, can effectively reduce the discharge of pollutant.This wherein gas-turbine combustion chamber nozzle design for tissue burning, reduce pollutant emission particularly important.
In the prior art of premixed fuel nozzle, easily there is tempering in nozzle rear, therefore needs featheriness air and protect nozzle rear.But the flow of featheriness air often has difference under varying environment and weather, meeting that featheriness air mass flow is on the low side causes the generation of tempering, causes head to be burnt, has a strong impact on the safety and reliability of gas turbine.
Summary of the invention
(1) technical problem that will solve
The object of this invention is to provide a kind of air intake structure that fuel and air have the gas turbine fuel nozzles of good premixing effect that can ensure.
(2) technical scheme
For achieving the above object, the invention provides a kind of air intake structure of gas turbine fuel nozzles, comprise the central air passage and fuel cavity that are interconnected, described central air passage is used for passing into air in described fuel cavity; One end of described central air passage is provided with nozzle and hangs flange, and described nozzle suspension flange is provided with the air inlet passage for passing into air in described central air passage; Described nozzle hangs the outer movable sleeve of flange and is provided with regulating sleeve, and described regulating sleeve is used for by moving axially the uncovered size limiting described air inlet passage.
Preferably, described nozzle hangs flange and comprises link and neck, and described air inlet passage is arranged on described neck.
Preferably, the sidewall thread that described regulating sleeve and described nozzle hang flange is connected.
Preferably, described regulating sleeve is by stepper motor driven rotary.
Preferably, described air inlet passage is perpendicular to the central axis of described central air passage.
Preferably, the cross section of described air inlet passage is rectangle.
Preferably, it is characterized in that, described air inlet passage is equally distributed multiple in the circumference that described nozzle hangs flange.
(3) beneficial effect
The air intake structure of a kind of gas turbine fuel nozzles provided by the invention, comprises the central air passage and fuel cavity that are interconnected, and central air passage is used for passing into air in fuel cavity; One end of central air passage is provided with nozzle and hangs flange, and nozzle suspension flange is provided with the air inlet passage for passing into air in central air passage; Nozzle hangs the outer movable sleeve of flange and is provided with regulating sleeve, and regulating sleeve is used for by moving axially the uncovered size limiting air inlet passage.By axially adjusting regulating sleeve, the flow of the air entering central air passage can be regulated, thus ensure that fuel and air have good premixing effect, prevent nozzle exit from producing tempering, improve the reliability of nozzle; In addition, the infinitely variable speeds of gas turbine also can be realized by regulating sleeve.
Accompanying drawing explanation
Fig. 1 is the sectional view of the air intake structure of a kind of gas turbine fuel nozzles of the embodiment of the present invention;
Fig. 2 is the zoomed-in view at A place in Fig. 1;
Fig. 3 is the 3-D view of the air intake structure of a kind of gas turbine fuel nozzles of the embodiment of the present invention.
Reference numeral:
1, central air passage; 2, fuel cavity; 3, air inlet passage; 4, interior pipe; 5, outer tube; 6, nozzle hangs flange; 7, regulating sleeve.
Detailed description of the invention
Below in conjunction with drawings and Examples, the specific embodiment of the present invention is described in further detail.Following examples for illustration of the present invention, but are not used for limiting the scope of the invention.
In describing the invention, it should be noted that, unless otherwise clearly defined and limited, term " connection " should be interpreted broadly, and such as, can be fixedly connected with, also can be removably connect, or connect integratedly; Can be directly be connected, also indirectly can be connected by intermediary.For the ordinary skill in the art, concrete condition above-mentioned term concrete meaning in the present invention can be understood.
Shown in composition graphs 1 and Fig. 3, the air intake structure of a kind of gas turbine fuel nozzles that the embodiment of the present invention provides, this fuel nozzle comprises interior pipe 4 and outer tube 5, interior pipe 4 plugs in outer tube 5 and is also relatively fixedly connected with, interior pipe 4 is defined as central air passage 1, fuel cavity 2 is defined as between interior pipe 4 and outer tube 5, central air passage 1 and fuel cavity 2 are interconnected, central air passage 1 for passing into air in fuel cavity 2, the fuel being premixed into air is more prone to realize Thorough combustion, effectively can prevent nozzle exit from producing tempering, improve the reliability of nozzle.
One end of central air passage 1 is provided with nozzle and hangs flange 6, nozzle hangs flange 6 for playing fixing effect to fuel nozzle, the nozzle suspension flange 6 of the present embodiment is provided with the air inlet passage 3 for passing into air in central air passage 1, air inlet passage 3 is preferably in the circumference that nozzle hangs flange 6 equally distributed multiple, namely air inflow is increased, make again the air-flow equilibrium entered, be beneficial to premixed that is follow-up and fuel; Nozzle hangs flange 6 outer movable sleeve and is provided with regulating sleeve 7, and the sidewall thread that the preferred and nozzle of regulating sleeve 7 hangs flange 6 is connected; Regulating sleeve 7 moves axially by rotating realization, and then by moving axially the uncovered size limiting air inlet passage 3; The cross section of air inlet passage 3 is preferably rectangle, rectangle near regulating sleeve 7 while be parallel to the end face of regulating sleeve 7, thus, make the uncovered area linear correlation moving axially distance and air inlet passage 3 of regulating sleeve 7, namely in the process moved axially at regulating sleeve 7, the uncovered area even variation of air inlet passage 3.
The environmentally change of factor, the inlet of air is regulated by regulating sleeve 7, and regulating sleeve 7 is preferably by stepper motor driven rotary, motor regulates by control system, control system be provided with can induced environment change sensor, as design temperature, humidity, the sensed conditions such as wind speed, control system regulates the uncovered size of air inlet passage 3 according to the change of sensed conditions.
Nozzle hangs flange 6 and comprises link and neck, and the diameter of link is greater than the diameter of neck, and air inlet passage 3 is preferably arranged on neck.During gas turbine running, by effects of air pressure, because link and neck have diameter difference, air flows through and produces inside eddy current herein, thus makes that air is easier enters into 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 peripheral vortex air more easily enter into air inlet passage 3.
Operation:
In gas turbine operation process, according to the change of external environment condition, by control system control step motor, regulating sleeve 7 changes axial location by the threaded engagement hanging flange 6 with nozzle, the uncovered area of air inlet passage 3 is adjusted, increases or reduce to enter into the air mass flow of central air passage 1, thus can ensure that fuel and air have good premixing effect, effectively can prevent nozzle exit from producing tempering, improve the reliability of nozzle; To the stepless changing of air mass flow, also can realize the infinitely variable speeds of gas turbine, finally realize the Thorough combustion of fuel.
The above is only the preferred embodiment of the present invention; it should be pointed out that for those skilled in the art, under the prerequisite not departing from the technology of the present invention principle; can also make some improvement and replacement, these improve and replace and also should be considered as protection scope of the present invention.
Claims (7)
1. the air intake structure of a gas turbine fuel nozzles, it is characterized in that, comprise the central air passage (1) and fuel cavity (2) that are interconnected, described central air passage (1) for passing into air in described fuel cavity (2); One end of described central air passage (1) is provided with nozzle and hangs flange (6), and described nozzle suspension flange (6) is provided with the air inlet passage (3) for passing into air in described central air passage (1); Described nozzle hangs flange (6) outer movable sleeve and is provided with regulating sleeve (7), and described regulating sleeve (7) is for the uncovered size by moving axially the described air inlet passage of restriction (3).
2. the air intake structure of gas turbine fuel nozzles according to claim 1, is characterized in that, described nozzle hangs flange (6) and comprises link and neck, and described air inlet passage (3) is arranged on described neck.
3. the air intake structure of gas turbine fuel nozzles according to claim 1, is characterized in that, described regulating sleeve (7) and described nozzle hang flange (6) threaded engagement and be connected.
4. the air intake structure of gas turbine fuel nozzles according to claim 3, is characterized in that, described regulating sleeve (7) is by stepper motor driven rotary.
5. form bracing structure according to claim 1, is characterized in that, described air inlet passage (3) is perpendicular to the central axis of described central air passage (1).
6. form bracing structure according to claim 1, is characterized in that, the cross section of described air inlet passage (3) is rectangle.
7. the air intake structure of the gas turbine fuel nozzles according to any one of claim 1-5, it is characterized in that, described air inlet passage (3) is for multiple, and multiple described air inlet passage (3) is hung in the circumference of flange (6) at described nozzle and is uniformly distributed.
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 |
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| CN104456624A true CN104456624A (en) | 2015-03-25 |
| CN104456624B CN104456624B (en) | 2017-08-04 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201410642176.7A Active CN104456624B (en) | 2014-11-11 | 2014-11-11 | The air intake structure of gas turbine fuel nozzles |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109099461A (en) * | 2018-08-03 | 2018-12-28 | 新奥能源动力科技（上海）有限公司 | Head device, combustion chamber and the gas turbine of combustion chamber |
| CN109185923A (en) * | 2018-08-03 | 2019-01-11 | 新奥能源动力科技（上海）有限公司 | A kind of chamber head part device, combustion chamber and gas turbine |
| CN109185924A (en) * | 2018-08-03 | 2019-01-11 | 新奥能源动力科技（上海）有限公司 | Head device, combustion chamber and the gas turbine of combustion chamber |
| CN110056905A (en) * | 2018-01-19 | 2019-07-26 | 中国科学院工程热物理研究所 | Dual Action for sparking plug and hot-end component covers positioning element and localization method |
| CN110285447A (en) * | 2019-06-06 | 2019-09-27 | 同济大学 | A kind of gas turbine low discharging burning chamber and varying duty air distribute adjusting method |
| CN112570394A (en) * | 2020-11-25 | 2021-03-30 | 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 |
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| CN103499097A (en) * | 2013-09-29 | 2014-01-08 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Combustion organizing method for combustion chamber for combusting fuel gas with low-medium calorific value and nozzle |
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| EP1156280B1 (en) * | 2000-05-15 | 2006-08-30 | 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 |
| CN103499097A (en) * | 2013-09-29 | 2014-01-08 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Combustion organizing method for combustion chamber for combusting fuel gas with low-medium calorific value and nozzle |
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110056905A (en) * | 2018-01-19 | 2019-07-26 | 中国科学院工程热物理研究所 | Dual Action for sparking plug and hot-end component covers positioning element and localization method |
| 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 |
| CN109099461A (en) * | 2018-08-03 | 2018-12-28 | 新奥能源动力科技（上海）有限公司 | Head device, combustion chamber and the gas turbine of combustion chamber |
| CN109185923A (en) * | 2018-08-03 | 2019-01-11 | 新奥能源动力科技（上海）有限公司 | A kind of chamber head part device, combustion chamber and gas turbine |
| CN109185924A (en) * | 2018-08-03 | 2019-01-11 | 新奥能源动力科技（上海）有限公司 | Head device, combustion chamber and the gas turbine of combustion chamber |
| 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 |
| 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 |
| 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 |
| CN110285447A (en) * | 2019-06-06 | 2019-09-27 | 同济大学 | A kind of gas turbine low discharging burning chamber and varying duty air distribute adjusting method |
| 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 |
| CN112570394A (en) * | 2020-11-25 | 2021-03-30 | 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 |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104456624B (en) | 2017-08-04 |
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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. |