CN104456625B - 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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- CN104456625B CN104456625B CN201410643780.1A CN201410643780A CN104456625B CN 104456625 B CN104456625 B CN 104456625B CN 201410643780 A CN201410643780 A CN 201410643780A CN 104456625 B CN104456625 B CN 104456625B
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- air
- gas turbine
- air inlet
- passage
- nozzle
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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, 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 hangs flange provided with nozzle, nozzle suspension flange is provided with multiple air inlet passages for being used to be passed through air into central air passage, multiple air inlet passages hang in nozzle and are uniformly distributed in the circumference of flange, each air inlet passage is equipped with an adjustment mechanism, and adjustment mechanism is used for the size for limiting the minimum flow area of air inlet passage.Each adjusting lever carries out that independent regulation can be done, and is effectively improved 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 variable speed of gas turbine can be also realized, the abundant burning of fuel is finally realized.
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 reach above-mentioned purpose, 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 is provided with multiple for logical to the center air
The air inlet passage of air is passed through in road, multiple air inlet passages hang uniform in the circumference of flange in the nozzle
Distribution, each air inlet passage is equipped with an adjustment mechanism, and the adjustment mechanism is used to limit the air intake
The size of the minimum flow area of passage.
It is preferred that, locating slot is offered on the inwall of the air inlet passage, the bottom of the locating slot, which is provided with, to be run through
Axis hole；The adjustment mechanism includes adjusting lever and limiting block, and the limiting block activity is plugged in the locating slot, described to adjust
Whole bar is plugged in the axis hole and is connected with the limiting block, and the adjusting lever is used to drive the limiting block along the positioning
Groove is moved.
It is preferred that, the adjusting lever is relatively fixed with the axis hole in the axial direction；The adjusting lever and the current limliting
Block screw thread is connected.
It is preferred that, one end of the adjusting lever is connected with the axis hole screw thread, and the other end of the adjusting lever is against
Elastic component is provided between the side wall of the side of the limiting block, the opposite side of the limiting block and the air inlet passage.
It is preferred that, the elastic component is spring.
It is preferred that, the air inlet passage is tilted to the side where the combustion chamber of gas turbine.
It is preferred that, the axis of the air inlet passage and gas turbine is into 40~90 degree of angle.
It is preferred that, the rectangular cross-section of the air inlet passage.
It is preferred that, the quantity of the air inlet passage is 4~8.
(3) beneficial effect
The invention provides a kind of air intake structure of gas turbine fuel nozzles, 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 multiple air inlet passages for being used to be passed through air into central air passage, multiple air
Access road hangs in nozzle and is uniformly distributed in the circumference of flange, and each air inlet passage is equipped with an adjustment mechanism, adjusts
Complete machine structure is used for the size for limiting the minimum flow area of air inlet passage.Each adjustment mechanism can be adjusted individually,
So as to be effectively improved the VELOCITY DISTRIBUTION of head of combustion chamber air, the mixing effect of fuel and air is improved, and then can effectively be prevented
Only nozzle exit produces tempering, improves the reliability of nozzle；To the stepless changing of air mass flow, gas turbine can be also realized
Variable speed.
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 one；
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 one；
Fig. 4 is a kind of signal of the adjustment mechanism of the air intake structure of gas turbine fuel nozzles of the embodiment of the present invention two
Figure；
Fig. 5 is a kind of 3-D view of the air intake structure of gas turbine fuel nozzles of the embodiment of the present invention two.
Reference：
1st, central air passage；2nd, fuel cavity；3rd, air inlet passage；4th, inner tube；5th, outer tube；6th, nozzle suspension flange；
7th, locating slot；8th, limiting block；9th, adjusting lever；10th, elastic component.
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, unless otherwise indicated, term " on ", " under ", " top ", " bottom ", " longitudinal direction " etc. refer to
The orientation or state relation shown is, based on orientation shown in the drawings or state relation, to be for only for ease of the description present invention and simplify
Description, rather than indicate or imply that the device or element of meaning must have specific orientation, with specific azimuth configuration and behaviour
Make, therefore be not considered as limiting the 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.
Embodiment one
With reference to shown in Fig. 1 to Fig. 3, a kind of air intake structure for gas turbine fuel nozzles that the embodiment of the present invention one is provided,
Including inner tube 4 and outer tube 5, inner tube 4 plugs in outer tube 5 and is relatively fixed connection, and inner tube 4 is defined as central air passage 1, interior
Fuel cavity 2 is defined as between pipe 4 and outer tube 5, central air passage 1 and fuel cavity 2 are interconnected, and central air passage 1 is used for
Air is passed through into fuel cavity 2, the fuel for being premixed into air can be made to be more prone to realize abundant burning, and then 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 fixation to inner tube 4
Effect, the present embodiment nozzle suspension flange 6 be provided be used for be passed through into central air passage 1 air air intake lead to
Equally distributed multiple, air inlet passage 3 in road 3, circumference of the air inlet passage 3 preferably to hang flange 6 in nozzle
Quantity be preferably 4~8, that is, increase air inflow, make the air-flow of entrance balanced again, beneficial to premixing subsequently with fuel.
Each air inlet passage 3 is equipped with an adjustment mechanism, and adjustment mechanism is used to limit air inlet passage 3 most
The size of small circulation area, so as to limit the flow that each air inlet passage 3 is passed through air, each adjustment mechanism can make list
Solely regulation, can be effectively improved the VELOCITY DISTRIBUTION of head of combustion chamber air, improve the mixing effect of fuel and air.
Locating slot 7 is offered on the inwall of air inlet passage 3, the bottom of locating slot 7 is provided with the axis hole run through, axis hole
Insertion delivery nozzle hangs the end face of flange 6；Adjustment mechanism includes adjusting lever 9 and limiting block 8, and the activity of limiting block 8 is plugged in positioning
In groove 7, adjusting lever 9 is plugged in axis hole and is connected with limiting block 8, and one end of adjusting lever 9 wears out the end face that mouth hangs flange,
In order to be operated from the outside of end face to adjusting lever 9, drive limiting block 8 to be moved along locating slot 7 by adjusting lever 9, realize
Restriction to the minimum flow area of air inlet passage 3.It is preferred that, the rectangular cross-section of air inlet passage 3, corresponding limit
The horizontal cross-section for flowing block 8 is also rectangle, makes the minimum flow area of the displacement and air inlet passage 3 of limiting block 8 linear
Correlation, that is, limit during stream block movement, the minimum flow area even variation of the air inlet passage 3 limited.
Adjusting lever 9 can take bolt arrangement, and axial limiting is formed between the bolt head and axis hole of one end of adjusting lever 9, adjust
The other end of whole bar 9 is connected with the screw thread of limiting block 8, so as to make limiting block 8 be moved in locating slot 7 by rotating adjusting lever 9
Dynamic, screw thread, which coordinates, can improve the feed accuracy of limiting block 8；It should be noted that the structure of adjusting lever 9 is not only limited in spiral shell
Bolt, as long as making have axial limit structure between adjusting lever 9 and axis hole, and makes adjusting lever 9 be connected i.e. with the screw thread of limiting block 8
Can.
It is preferred that, air inlet passage 3 is tilted to the side where the combustion chamber of gas turbine, using produced by combustion chamber
Air-flow, make air be easier to enter in air inlet passage 3, through experimental results demonstrate, air inlet passage 3 and combustion gas wheel
When the axis of machine is into 40~90 degree, air enters best results.In addition, nozzle suspension flange 6 generally comprise it is larger-diameter
Connection end, and small diameter neck, preferably make neck be obliquely installed with connection end junction, and air inlet passage 3 is opened up
At the inclination of neck, so, on the airflow direction along produced by combustion chamber, the distal edge of the opening of air inlet passage 3
Edge is higher than the proximal edge of opening, air is easier entrance.
Operation：
During gas turbine operation, according to the change of external environment condition, it is determined that the air inflow of individual air inlet passage 3,
Rotate each adjusting lever 9 accordingly, the minimum flow area to each air inlet passage 3 is adjusted, increased or decrease into
Enter the air mass flow to each central air passage 1, and be adjusted into the vortex form of air；It can be adjusted during this to each
Whole bar 9 carries out that independent regulation can be done, so as to be effectively improved the VELOCITY DISTRIBUTION of head of combustion chamber air, improves mixing for fuel and air
Mixed effect, and then can effectively prevent nozzle exit from producing tempering, improve the reliability of nozzle；To the stepless-adjustment of air mass flow
It is whole, it can also realize the variable speed of gas turbine.
Embodiment two
A kind of air intake structure for gas turbine fuel nozzles that the present embodiment two is provided, the basic phase of structure with embodiment one
Together, something in common is repeated no more, and difference is：
With reference to shown in Fig. 4 and Fig. 5, one end and the axis hole screw thread of adjusting lever 9 are connected, and the other end of adjusting lever 9 is against
The side of limiting block 8, is provided with elastic component between the opposite side of limiting block 8 and the side wall of air inlet passage 3, elastic component can be
Spring, adjusting lever 9 is by the cooperation with axis hole by the jacking forward of limiting block 8, and limiting block 8 is moved back by the elastic force effect of elastic component
Return；If taking other elastic components, the width of elastic component should be less than the width of air inlet passage 3, in order to avoid air inlet is produced excessive
Influence；Compared to embodiment one, position-limit mechanism need not be set in the axial direction, in adjustment block between adjusting lever 9 and axis hole
Without the screw coaxial with axis hole is set, so as to reduce difficulty of processing, operation is also convenient for.
In addition, can also the side of limiting block 8 towards air inlet passage 3 be set to inclined-plane, the inclined-plane is parallel to air intake
The side side wall on the other side of passage 3, and the groove of locating slot 7 to parallel to nozzle hang flange 6 axial direction, the side of axis hole
To the end face that flange 6 is hung perpendicular to nozzle, the side that can either so make limiting block 8 and the air inlet passage being obliquely installed
3 are adapted, and current limitation effect is good；In addition, axis of the direction of locating slot 7 and axis hole still parallel to nozzle, so easy to process,
Operation to adjusting lever 9 is also convenient for.And, although the glide direction of limiting block 8 and non-perpendicular to side wall of the air such as empty passage,
The changing of the relative positions occurs for the mobile two ends that can make elastic component of limiting block 8, but the two ends of elastic component can adapt to this to a certain extent
The one relative changing of the relative positions, hardly influences its elastic effect.
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 (7)
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 used for the center air provided with nozzle suspension flange (6), the nozzle suspension flange (6) provided with multiple
The air inlet passage (3) of air is passed through in passage (1), multiple air inlet passages (3) hang flange in the nozzle
(6) it is uniformly distributed in circumference, each air inlet passage (3) is equipped with an adjustment mechanism, the adjustment mechanism is used
In the size for the minimum flow area for limiting the air inlet passage (3)；
Locating slot (7) is offered on the inwall of the air inlet passage (3), the bottom of the locating slot (7) is provided with what is run through
Axis hole；The adjustment mechanism includes adjusting lever (9) and limiting block (8), and limiting block (8) activity is plugged in the locating slot
(7) in, the adjusting lever (9) is plugged in the axis hole and is connected with the limiting block (8), and the adjusting lever (9) is used to drive
Move the limiting block (8) mobile along the locating slot (7)；
The air inlet passage (3) tilts to the side where the combustion chamber of gas turbine.
2. the air intake structure of gas turbine fuel nozzles according to claim 1, it is characterised in that the adjusting lever (9)
There is axial limit structure between the axis hole；The adjusting lever (9) is connected with the limiting block (8) screw thread.
3. the air intake structure of gas turbine fuel nozzles according to claim 1, it is characterised in that the adjusting lever (9)
One end and the axis hole screw thread be connected, the other end of the adjusting lever (9) is against the side of the limiting block (8), institute
State and elastic component is provided between the opposite side of limiting block (8) and the side wall of the air inlet passage (3).
4. the air intake structure of gas turbine fuel nozzles according to claim 3, it is characterised in that the elastic component is bullet
Spring.
5. the air intake structure of gas turbine fuel nozzles according to claim 1, it is characterised in that the air intake leads to
The axis of road (3) and gas turbine is into 40~90 degree of angle.
6. the air intake structure of gas turbine fuel nozzles according to claim 1, it is characterised in that the air intake leads to
The rectangular cross-section in road (3).
7. the air intake structure of the gas turbine fuel nozzles according to claim any one of 1-6, it is characterised in that the sky
The quantity of gas access road (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 |
|---|---|
| CN104456625A CN104456625A (en) | 2015-03-25 |
| CN104456625B true CN104456625B (en) | 2017-11-07 |
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Families Citing this family (5)
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| CN105627317B (en) * | 2015-12-31 | 2018-07-10 | 北京理工大学 | Rapidly mixing tubulose flame burner with axial jet |
| CN105423285A (en) * | 2015-12-31 | 2016-03-23 | 北京理工大学 | Tangential inlet hybrid-tube-shaped flame burner |
| CN109099460B (en) * | 2017-06-20 | 2020-07-17 | 中国航发商用航空发动机有限责任公司 | Intake area adjusting device and combustion chamber |
| CN112325333B (en) * | 2021-01-04 | 2021-04-06 | 成都裕鸢航空智能制造股份有限公司 | 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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| EP1564462B1 (en) * | 2004-02-11 | 2008-08-06 | WEBER, Gisela | Pipe-fracture valve |
| CN1880807A (en) * | 2005-06-17 | 2006-12-20 | 中国石油化工股份有限公司 | Current limit control valve |
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