CN104456625A - 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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- CN104456625A CN104456625A CN201410643780.1A CN201410643780A CN104456625A CN 104456625 A CN104456625 A CN 104456625A CN 201410643780 A CN201410643780 A CN 201410643780A CN 104456625 A CN104456625 A CN 104456625A
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- air
- air inlet
- gas turbine
- inlet passage
- nozzle
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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 air inlet structure 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, the nozzle hanging flange is provided with a plurality of air inlet channels used for connecting the air into the center air channel, and the air inlet channels are evenly distributed in the circumferential direction of the nozzle hanging flange. Each air inlet channel is provided with an adjusting mechanism, and each adjusting mechanism is used for limiting the size of the minimum flow area of the corresponding air inlet channel. Each adjusting rod can be adjusted independently, the speed distribution of the air on the head portion of a combustion chamber is effectively improved, the mixing effect of fuel and the air is improved, hence, tempering can be effectively prevented from happening at a nozzle outlet, and the reliability of the nozzle is improved. The air flow can be steplessly adjusted, stepless speed change of the air turbine can also be achieved, and the fuel can be fully burnt ultimately.
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, comprising 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, described nozzle hangs flange and is provided with multiple air inlet passage for passing into air in described central air passage, multiple described air inlet passage hangs in the circumference of flange at described nozzle and is uniformly distributed, each described air inlet passage is equipped with a guiding mechanism, and described guiding mechanism is for limiting the size of the minimum flow area of described air inlet passage.
Preferably, the inwall of described air inlet passage offers locating slot, the bottom of described locating slot is provided with the axis hole run through; Described guiding mechanism comprises adjusting lever and current limliting block, and the activity of described current limliting block is plugged in described locating slot, and described adjusting lever to be plugged in described axis hole and to be connected with described current limliting block, and described adjusting lever moves along described locating slot for driving described current limliting block.
Preferably, described adjusting lever is relative with described axis hole fixing in the axial direction; Described adjusting lever is connected with described current limliting block threaded engagement.
Preferably, one end of described adjusting lever is connected with described axis hole threaded engagement, and the other end of described adjusting lever is against the side of described current limliting block, is provided with elastic component between the opposite side of described current limliting block and the sidewall of described air inlet passage.
Preferably, described elastic component is spring.
Preferably, described air inlet passage is to the lopsidedness at the place, combustion chamber of gas turbine.
Preferably, described air inlet passage becomes the angle of 40 ~ 90 degree with the axis of gas turbine.
Preferably, the cross section of described air inlet passage is rectangle.
Preferably, the quantity of described air inlet passage is 4 ~ 8.
(3) beneficial effect
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, 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, nozzle hangs flange and is provided with multiple air inlet passage for passing into air in central air passage, multiple air inlet passage hangs in the circumference of flange at nozzle and is uniformly distributed, each air inlet passage is equipped with a guiding mechanism, and guiding mechanism is for limiting the size of the minimum flow area of air inlet passage.Each guiding mechanism all can adjust separately, thus effectively can improve the VELOCITY DISTRIBUTION of head of combustion chamber air, improves the mixing effect of fuel and air, and then can effectively prevent nozzle exit from producing tempering, improves the reliability of nozzle; To the stepless changing of air mass flow, the infinitely variable speeds of gas turbine also can be realized.
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 one;
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 one;
Fig. 4 is the schematic diagram of the guiding mechanism of the air intake structure of a kind of gas turbine fuel nozzles of the embodiment of the present invention two;
Fig. 5 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 two.
Reference numeral:
1, central air passage; 2, fuel cavity; 3, air inlet passage; 4, interior pipe; 5, outer tube; 6, nozzle hangs flange; 7, locating slot; 8, current limliting block; 9, adjusting lever; 10, elastic component.
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, except as otherwise noted, term " on ", D score, " top ", " bottom ", the orientation of the instruction such as " longitudinal direction " or state relation be based on orientation shown in the drawings or state relation, only the present invention for convenience of description and simplified characterization, instead of indicate or imply that the device of indication or element must have specific orientation, with specific azimuth configuration and operation, therefore can not be interpreted as limitation of the present 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.
Embodiment one
Shown in composition graphs 1 to Fig. 3, the air intake structure of a kind of gas turbine fuel nozzles that the embodiment of the present invention one provides, comprise 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 can be made to be more prone to realize Thorough combustion, and then can effectively 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 and plays fixing effect for internal pipe 4, 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 equally distributed multiple in the circumference that nozzle hangs flange 6, the quantity of air inlet passage 3 is preferably 4 ~ 8, namely increase air inflow, make again the air-flow equilibrium entered, be beneficial to premixed that is follow-up and fuel.
Each air inlet passage 3 is equipped with a guiding mechanism, guiding mechanism is for limiting the size of the minimum flow area of air inlet passage 3, thus limit the flow that each air inlet passage 3 passes into air, each guiding mechanism all can do independent adjustment, effectively can improve the VELOCITY DISTRIBUTION of head of combustion chamber air, improve the mixing effect of fuel and air.
The inwall of air inlet passage 3 offers locating slot 7, and the bottom of locating slot 7 is provided with the axis hole run through, and the through delivery nozzle of axis hole hangs the end face of flange 6; Guiding mechanism comprises adjusting lever 9 and current limliting block 8, current limliting block 8 activity is plugged in locating slot 7, adjusting lever 9 to be plugged in axis hole and to be connected with current limliting block 8, one end of adjusting lever 9 wears out the end face that mouth hangs flange, so that operate from the outside of end face adjusting lever 9, drive current limliting block 8 to move along locating slot 7 by adjusting lever 9, realize the restriction of the minimum flow area to air inlet passage 3.Preferably, the cross section of air inlet passage 3 is rectangle, the horizontal cross-section of corresponding current limliting block 8 is also rectangle, make the displacement of current limliting block 8 and the minimum flow area linear correlation of air inlet passage 3, namely limit in the process of stream block movement, the minimum flow area even variation of the air inlet passage 3 limited.
Adjusting lever 9 can take bolt arrangement, axial limiting is formed between the bolt head of one end of adjusting lever 9 and axis hole, the other end of adjusting lever 9 is connected with current limliting block 8 threaded engagement, thus by rotating adjusting lever 9, current limliting block 8 being moved in locating slot 7, threaded engagement can improve the feed accuracy of current limliting block 8; It should be noted that the structure of adjusting lever 9 has more than and be limited to bolt, as long as make to have axial limit structure between adjusting lever 9 and axis hole, and adjusting lever 9 is connected with current limliting block 8 threaded engagement.
Preferably, air inlet passage 3 is to the lopsidedness at the place, combustion chamber of gas turbine, utilize the air-flow that combustion chamber produces, air is made more easily to enter into air inlet passage 3, through experimental results demonstrate, air inlet passage 3 becomes 40 ~ 90 degree during with the axis of gas turbine, air enters best results.In addition, nozzle hangs flange 6 and generally comprises larger-diameter link, with small diameter neck, neck and link junction is preferably made to be obliquely installed, and air inlet passage 3 is opened in inclination place of neck, like this, on the airflow direction produced along combustion chamber, the remote edge of the opening of air inlet passage 3, higher than the proximal edge of opening, makes air more easily enter like this.
Operation:
In gas turbine operation process, according to the change of external environment condition, determine the air inflow of an air inlet passage 3, each adjusting lever 9 of corresponding rotation, the minimum flow area of each air inlet passage 3 is adjusted, increase or reduce to enter into the air mass flow of each central air passage 1, and adjustment enters the eddy current form of air; Can carry out doing independent adjustment to each adjusting lever 9 in this process, thus effectively improve the VELOCITY DISTRIBUTION of head of combustion chamber air, improve the mixing effect of fuel and air, and then can effectively prevent nozzle exit from producing tempering, improve the reliability of nozzle; To the stepless changing of air mass flow, the infinitely variable speeds of gas turbine also can be realized.
Embodiment two
The air intake structure of a kind of gas turbine fuel nozzles that the present embodiment two provides, substantially identical with the structure of embodiment one, something in common repeats no more, and difference is:
Shown in composition graphs 4 and Fig. 5, one end of adjusting lever 9 is connected with axis hole threaded engagement, the other end of adjusting lever 9 is against the side of current limliting block 8, elastic component is provided with between the opposite side of current limliting block 8 and the sidewall of air inlet passage 3, elastic component can be spring, adjusting lever 9 by with axis hole coordinate current limliting block 8 jacking forward, current limliting block 8 is return by the elastic force effect of elastic component; If take other elastic components, the width of elastic component should be less than the width of air inlet passage 3, in order to avoid produce excessive impact to air inlet; Compare embodiment one, in the axial direction without the need to arranging position-limit mechanism between adjusting lever 9 and axis hole, also without the need to arranging the screw coaxial with axis hole in adjustment block, thus reduce difficulty of processing, operation also facilitates.
In addition, also can be set to inclined-plane towards the side of air inlet passage 3 by current limliting block 8, this inclined-plane is parallel to air inlet passage 3 side on the other side sidewall, and the groove of locating slot 7 is to the axial direction being parallel to nozzle suspension flange 6, the direction of axis hole hangs the end face of flange 6 perpendicular to nozzle, the side of current limliting block 8 can either be made like this to adapt with the air inlet passage 3 be obliquely installed, and current limitation effect is good; In addition, the direction of locating slot 7 and axis hole is still parallel to the axis of nozzle, is easy to processing like this, also facilitates the operation of adjusting lever 9.And, although the glide direction of current limliting block 8 non-perpendicular to the sidewall of air as empty passage, the movement of current limliting block 8 can make the two ends of elastic component that the changing of the relative positions occurs, but the two ends of elastic component can adapt to this relative changing of the relative positions to a certain extent, affect its elastic effect hardly.
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 (9)
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), described nozzle hangs flange (6) and is provided with multiple air inlet passage (3) for passing into air in described central air passage (1), multiple described air inlet passage (3) is hung in the circumference of flange (6) at described nozzle and is uniformly distributed, each described air inlet passage (3) is equipped with a guiding mechanism, and described guiding mechanism is for limiting the size of the minimum flow area of described air inlet passage (3).
2. the air intake structure of gas turbine fuel nozzles according to claim 1, it is characterized in that, the inwall of described air inlet passage (3) offers locating slot (7), the bottom of described locating slot (7) is provided with the axis hole run through; Described guiding mechanism comprises adjusting lever (9) and current limliting block (8), the activity of described current limliting block (8) is plugged in described locating slot (7), described adjusting lever (9) to be plugged in described axis hole and to be connected with described current limliting block (8), and described adjusting lever (9) is for driving described current limliting block (8) mobile along described locating slot (7).
3. the air intake structure of gas turbine fuel nozzles according to claim 2, is characterized in that, has axial limit structure between described adjusting lever (9) and described axis hole; Described adjusting lever (9) is connected with described current limliting block (8) threaded engagement.
4. the air intake structure of gas turbine fuel nozzles according to claim 2, it is characterized in that, one end of described adjusting lever (9) is connected with described axis hole threaded engagement, the other end of described adjusting lever (9) is against the side of described current limliting block (8), is provided with elastic component between the opposite side of described current limliting block (8) and the sidewall of described air inlet passage (3).
5. the air intake structure of gas turbine fuel nozzles according to claim 4, is characterized in that, described elastic component is spring.
6. the air intake structure of gas turbine fuel nozzles according to claim 1, is characterized in that, described air inlet passage (3) is to the lopsidedness at the place, combustion chamber of gas turbine.
7. the air intake structure of gas turbine fuel nozzles according to claim 6, is characterized in that, described air inlet passage (3) becomes the angle of 40 ~ 90 degree with the axis of gas turbine.
8. the air intake structure of gas turbine fuel nozzles according to claim 1, is characterized in that, the cross section of described air inlet passage (3) is rectangle.
9. the air intake structure of the gas turbine fuel nozzles according to any one of claim 1-8, is characterized in that, the quantity of described air inlet passage (3) is 4 ~ 8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410643780.1A CN104456625B (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 |
|---|---|---|---|
| CN201410643780.1A CN104456625B (en) | 2014-11-11 | 2014-11-11 | The air intake structure of gas turbine fuel nozzles |
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| Publication Number | Publication Date |
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| CN104456625A true CN104456625A (en) | 2015-03-25 |
| CN104456625B CN104456625B (en) | 2017-11-07 |
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| CN201410643780.1A Active CN104456625B (en) | 2014-11-11 | 2014-11-11 | The air intake structure of gas turbine fuel nozzles |
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Cited By (5)
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| CN105423285A (en) * | 2015-12-31 | 2016-03-23 | 北京理工大学 | Tangential inlet hybrid-tube-shaped flame burner |
| CN105627317A (en) * | 2015-12-31 | 2016-06-01 | 北京理工大学 | Rapid-mixing tubular flame burner with axial jet function |
| CN109099460A (en) * | 2017-06-20 | 2018-12-28 | 中国航发商用航空发动机有限责任公司 | A kind of air inlet area regulating device and combustion chamber |
| CN112325333A (en) * | 2021-01-04 | 2021-02-05 | 成都裕鸢航空零部件制造有限公司 | Aeroengine oil-gas mixing method and mixing cavity structure |
| CN114704853A (en) * | 2022-03-24 | 2022-07-05 | 西北工业大学 | High-efficient atomizing centrifugal nozzle |
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| CN105423285A (en) * | 2015-12-31 | 2016-03-23 | 北京理工大学 | Tangential inlet hybrid-tube-shaped flame burner |
| CN105627317A (en) * | 2015-12-31 | 2016-06-01 | 北京理工大学 | Rapid-mixing tubular flame burner with axial jet function |
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| CN112325333A (en) * | 2021-01-04 | 2021-02-05 | 成都裕鸢航空零部件制造有限公司 | Aeroengine oil-gas mixing method and mixing cavity structure |
| CN114704853A (en) * | 2022-03-24 | 2022-07-05 | 西北工业大学 | High-efficient atomizing centrifugal nozzle |
Also Published As
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| CN104456625B (en) | 2017-11-07 |
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