CN108278634A - A kind of gas turbine and its burner - Google Patents
A kind of gas turbine and its burner Download PDFInfo
- Publication number
- CN108278634A CN108278634A CN201711279240.XA CN201711279240A CN108278634A CN 108278634 A CN108278634 A CN 108278634A CN 201711279240 A CN201711279240 A CN 201711279240A CN 108278634 A CN108278634 A CN 108278634A
- Authority
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- China
- Prior art keywords
- burner
- injection pipe
- fuel injection
- gas turbine
- along
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 239000000446 fuel Substances 0.000 claims abstract description 202
- 238000002347 injection Methods 0.000 claims abstract description 113
- 239000007924 injection Substances 0.000 claims abstract description 113
- 239000007921 spray Substances 0.000 claims abstract description 65
- 238000002156 mixing Methods 0.000 claims abstract description 49
- 239000000203 mixture Substances 0.000 claims abstract description 13
- 230000002093 peripheral effect Effects 0.000 claims description 25
- 230000008676 import Effects 0.000 claims description 14
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 claims description 13
- 238000002485 combustion reaction Methods 0.000 claims description 11
- 239000011148 porous material Substances 0.000 claims description 8
- 238000009434 installation Methods 0.000 claims description 2
- 230000000694 effects Effects 0.000 abstract description 6
- 239000007789 gas Substances 0.000 description 30
- 238000001816 cooling Methods 0.000 description 9
- 238000010586 diagram Methods 0.000 description 5
- 238000005516 engineering process Methods 0.000 description 4
- 230000008602 contraction Effects 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 3
- 230000010339 dilation Effects 0.000 description 2
- 238000006073 displacement reaction Methods 0.000 description 2
- 230000001914 calming effect Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
Abstract
The invention discloses a kind of gas turbine and its burner, the burner includes burner inner liner, guide bushing and rear flame fuel injection pipe；The guide bushing is set on the burner inner liner, and circular passage is formed between the guide bushing and the burner inner liner；The outer end of flame fuel injection pipe is fixed in the guide bushing after described, the inner end of flame fuel injection pipe extends to the burner inner liner after described, it is axial successively equipped with air orifice plate and spray plate along it in flame fuel injection pipe after described, the air orifice plate is equipped with multiple air admission holes, the spray plate is equipped with multiple squit holes, and the spray plate is used to fuel and air mixing resulting mixture and is sprayed into the mixture in the rear flame fuel injection pipe by the squit hole.The present invention improves the mixing effect of fuel and air, and the structure of the burner is simple, reduces the cost of system.
Description
Technical field
The present invention relates to gas turbine technology fields, a kind of burner more particularly to gas turbine and have the combustion
The gas turbine of burner.
Background technology
In the thermodynamic cycle of gas turbine, the indoor fuel gas temperature that burns is higher, is more conducive to the raising of efficiency and power.
But excessive air is easy to form oxynitrides NO at high temperatureX, and in order to reduce the thermal NOXDischarge, then need
Reduce indoor maximum temperature of burning.It on the one hand needs to improve temperature as a result, to meet the needs of power, on the other hand then needs to drop
Low maximum temperature is to reach emission request.
In the related technology, fractional combustion is used in the combustion chamber of gas turbine, for a kind of classification combustion in gas turbine
It is " late lean injection " to burn, and in the fractional combustion of this type, late lean injection device is located at the downstream of main burning nozzle, herein
Downstream position increases fuel, can not only increase power, but also is avoided that burning indoor temperature is excessively high.However, the poor spray of current delay
Emitter is complicated, has both increased the cost of system, also brings excessively high heat structure load, there is also the risks of leakage；And
And fuel inlet is located on annular fuel passage, fuel and air mixing is undesirable.
Invention content
The present invention is directed to solve at least some of the technical problems in related technologies.
For this purpose, one aspect of the present invention proposes that a kind of burner of gas turbine, the burner improve fuel and sky
The mixing effect of gas, and it is simple in structure, reduce the cost of system.
The invention also provides a kind of gas turbines with said burner.
The burner of the gas turbine of embodiment according to the first aspect of the invention includes burner inner liner；Guide bushing, institute
It states guide bushing to be set on the burner inner liner, circular passage is formed between the guide bushing and the burner inner liner；Flame afterwards
The outer end of fuel injection pipe, the rear flame fuel injection pipe is fixed in the guide bushing, the rear flame fuel spray
The inner end for penetrating pipe extends to the burner inner liner, and the rear flame fuel injection pipe is interior axial successively equipped with air orifice plate and spray along it
Plate is noted, the air orifice plate is equipped with multiple air admission holes, and the spray plate is equipped with multiple squit holes, and the spray plate is used for will
Fuel and air mix resulting mixture and are sprayed into the mixture in the rear flame fuel injection pipe by the squit hole.
The burner of gas turbine according to the ... of the embodiment of the present invention, by rear flame fuel injection pipe along its axial direction according to
It is secondary to be equipped with air orifice plate and spray plate, the mixing effect of fuel and air is improved, and the structure of the burner is simple, reduced
The cost of system.
In some embodiments, the air orifice plate has air inlet side surface and outlet side surface, the outlet side surface
It is equipped with the distributing trough of multiple connections corresponding with the air admission hole.
In some embodiments, the distributing trough is the arc groove of the circumferentially extending along the air orifice plate.
In some embodiments, the air admission hole is arranged to the evenly spaced radial multi-turn opened along the air orifice plate,
The air admission hole on each circle is along the circumferential array of the air orifice plate and evenly-spaced.
In some embodiments, the circumferential lengths for the distributing trough being connected with the air admission hole on same circle
It is identical.
In some embodiments, along the radial direction of the air orifice plate, the two neighboring distributing trough, it is located inside
Distributing trough circumferential lengths be less than positioned at outside distributing trough circumferential lengths.
In some embodiments, the air admission hole is arranged to evenly spaced radial four circles opened along the air orifice plate,
There are four the evenly-spaced air admission holes of circumferential direction along the air orifice plate for tool on each circle, so as to the air orifice plate
All the air admission holes are divided into four groups, the air admission hole in each group along the air orifice plate radially aligned, with each group
The circumferential lengths for the distributing trough that interior air admission hole is connected are gradually reduced along the radial ecto-entad of the air orifice plate.
In some embodiments, the spray plate has import side surface and exports side surface, on the import side surface
With mixing cavity groove, it is described mixing cavity groove side wall on have fuel inlet, the squit hole from it is described mixing cavity groove bottom surface
Extend to the outlet side surface of the spray plate.
In some embodiments, the mixing cavity groove is multiple and along the circumferentially-spaced arrangement of the spray plate, each
There are multiple squit holes on the bottom surface of the mixing cavity groove.
In some embodiments, the mixing cavity groove is four, and the center of the import side surface of the spray plate has
There are square protruding, the adjacent mixing cavity groove to be opened by substantially fan-shaped bulge clearance, the inner end of each fan-shaped protrusion and institute
The corresponding corner for stating square protruding connects, and the side of the outer end of each fan-shaped protrusion is connected with the week along the spray plate
To the arc convex of extension, the other end of the arc convex is opened with the adjacent fan-shaped bulge clearance to form the fuel
Import.
In some embodiments, it is equipped with cowling panel between the air orifice plate and the spray plate, is set on the cowling panel
There are multiple rectification holes.
In some embodiments, the air orifice plate and the cowling panel after described flame fuel injection pipe it is axial that
This is directly fitted, and axial direction of the cowling panel with the spray plate along the rear flame fuel injection pipe is bonded directly with one another.
In some embodiments, the burner of the gas turbine further includes floating lantern ring, and the floating lantern ring is mounted on
On the burner inner liner and removable relative to the burner inner liner, the inner end of the rear flame fuel injection pipe passes through the floating bushing
Ring extends to the burner inner liner.
In some embodiments, the burner inner liner is equipped with mounting hole, and bearing, the floating are equipped in the mounting hole
Lantern ring is mounted on the bearing and removable relative to the bearing.
In some embodiments, the bearing includes pedestal and annular cover plate, and the pedestal includes cylinder, from the cylinder
Upper end periphery along the cylinder the flange to extend radially outwardly and from the outer peripheral edge of the flange along the cylinder axially outward
The cofferdam of extension, the outer peripheral edge of the annular cover plate are connected with the cofferdam so as to the annular cover plate, the cofferdam and described
Flange forms annular groove, and a part for the floating lantern ring movably coordinates in the annular groove.
In some embodiments, the floating lantern ring include tubular section and from the inner end of the tubular section along the tubular section
The peripheral part to extend radially outwardly, the peripheral part movably coordinate in the annular groove, and the tubular section is sleeved on described
Afterwards on flame fuel injection pipe and with it is described after flame fuel injection pipe tight fit.
In some embodiments, the outer end of the rear flame fuel injection pipe has flange, the rear flame fuel injection
Pipe is mounted on by the flange in the guide bushing.
In some embodiments, the guide bushing is equipped with mounting hole, and outer shroud is equipped in the mounting hole, described outer
Ring has along the annular outer groove of the outer shroud being radially outward open and along the annular trough of the outer shroud being radially-inwardly open, described
Annular outboard is connected to the annular outer groove by intercommunicating pore；Inner ring is installed, the inner ring has interior along this in the outer shroud
The inner ring annular groove of ring being radially outward open, the inner ring annular groove dock logical to form annular fuel with the annular trough
Road, the flange are mounted on the outer shroud, and the rear flame fuel injection pipe passes through the inner ring, the annular fuel passage
It is connected to the teasehole on the rear flame fuel injection pipe by the fuel through-hole in the inner ring.
In some embodiments, it is equipped with cyclone in the rear flame fuel injection pipe.
The gas turbine of embodiment according to the second aspect of the invention includes the burner of above-described embodiment.
Description of the drawings
Fig. 1 is the overall structure diagram of the burner of gas turbine according to an embodiment of the invention.
Fig. 2 is the section view at the rear flame fuel injection pipe of the burner of gas turbine according to an embodiment of the invention
Figure.
Fig. 3 is the section at the rear flame fuel injection pipe of the burner of gas turbine according to an embodiment of the invention
Figure.
Fig. 4 is the air inlet side schematic diagram of the air orifice plate of the burner of gas turbine according to an embodiment of the invention.
Fig. 5 is that the air orifice plate of the burner of gas turbine according to an embodiment of the invention goes out gas side schematic diagram.
Fig. 6 is the schematic diagram of the spray plate of the burner of gas turbine according to an embodiment of the invention.
Fig. 7 is the schematic diagram of the cowling panel of the burner of gas turbine according to an embodiment of the invention.
Reference numeral：
Burner inner liner 1, guide bushing 2, floating lantern ring 3, cylindrical portion 31, direct tube section 311, loudspeaker section 312, peripheral part 32, after
Flame fuel injection pipe 4, air orifice plate 5, air inlet side surface 51, outlet side surface 52, bearing 6, pedestal 61, cylinder 611, flange
612, cofferdam 613, annular cover plate 62, spray plate 7, mixing cavity groove 71, fuel inlet 72, square protruding 73, fan-shaped protrusion 74, arc
Shape protrusion 75, cooling hole 8, flange 9, outer shroud 10, annular outer groove 101, annular trough 102, intercommunicating pore 103, inner ring 11, inner ring ring
Shape slot 111, annular fuel passage 12, fuel through-hole 13, circular passage 14, annular groove 15, fuel channel 16, fuel cover board 17,
Cyclone 18, air admission hole 19, squit hole 20, distributing trough 21, cowling panel 22, rectification hole 23.
Specific implementation mode
The embodiment of the present invention is described below in detail, examples of the embodiments are shown in the accompanying drawings.Below with reference to
The embodiment of attached drawing description is exemplary, it is intended to for explaining the present invention, and is not considered as limiting the invention.
As shown in figs. 1-7, the burner of gas turbine according to the ... of the embodiment of the present invention includes burner inner liner 1,2 and of guide bushing
Flame fuel injection pipe 4 afterwards, the front end (left end shown in Fig. 1) of burner inner liner 1 are equipped with primary fuel nozzles, so as to burner inner liner
Fuel is sprayed in 1.
Guide bushing 2 is set on burner inner liner 1, and circular passage 14 is formed between guide bushing 2 and burner inner liner 1.Through calming the anger
The pressure-air of machine compression enters the front end of burner inner liner 1 through the circular passage 14, and the fuel sprayed with primary fuel nozzles exists
The mixing of burner inner liner 1, burning.
The outer end of flame fuel injection pipe 4 is fixed in guide bushing 2 afterwards, and the inner end of rear flame fuel injection pipe 4 extends
To burner inner liner 1.Specifically, the opening of the inner end of rear flame fuel injection pipe 4 is concordant with the internal face of burner inner liner 1.It can manage
It solves, it is multiple, multiple teasehole edges to have the teasehole for being suitable for fuel entrance and teasehole on rear flame fuel injection pipe 4
The circumferential uniform intervals arrangement of flame fuel injection pipe 4 afterwards.Herein, " outer end " refers to one end of neighbouring guide bushing 2, i.e. Fig. 2
Shown in upper end；" inner end " refers to one end of neighbouring burner inner liner 1, i.e., lower end shown in Fig. 2.
Afterwards flame fuel injection pipe 4 be suitable for fuel at the downstream (right side shown in FIG. 1) of primary fuel nozzles and
The mixture of air is ejected into working fluid.Flame fuel injection pipe 4 is more specifically for the mixing of fuel and air afterwards
Object is ejected into the rear end (right end shown in FIG. 1) of the primary combustion chamber of the restriction of burner inner liner 1.Flame fuel injection pipe 4 is first afterwards
The mixing of fuel and air, burning are realized in grade combustion zone downstream, to improve NOXDischarge.
Axial successively equipped with air orifice plate 5 and spray plate 7 along it in flame fuel injection pipe 4 afterwards, air orifice plate 5 is equipped with
Multiple air admission holes 19, air are entered the air orifice plate in rear flame fuel injection pipe 4 from the outer end of air orifice plate 5 by air admission hole 19
Space between 5 and spray plate 7, meanwhile, teasehole of the fuel after on flame fuel injection pipe 4 enters air orifice plate 5 and spray
It notes the space between plate 7 and the space fuel between air orifice plate 5 and spray plate 7 and air mixes.Spray plate 7 is equipped with
Multiple squit holes 20, after spray plate 7 is sprayed into the mixture of fuel and air by squit hole 20 in flame fuel injection pipe 4.
It is understood that external air enters the air orifice plate in rear flame fuel injection pipe 4 by air orifice plate 5
Space between 5 and spray plate 7, meanwhile, teasehole of the fuel after on flame fuel injection pipe 4 enters 5 He of air orifice plate
Space between spray plate 7, fuel are sprayed by the squit hole 20 on spray plate 7 again after being mixed in the space with air
Into rear flame fuel injection pipe 4, the mixture of the fuel and air of ejection further mixes in rear flame fuel injection pipe 4
And by the injection to burner inner liner 1 of rear flame fuel injection pipe 4.
The burner of gas turbine according to the ... of the embodiment of the present invention, by rear flame fuel injection pipe along its axial direction according to
It is secondary to be equipped with air orifice plate and spray plate, air orifice plate 5 and spray plate of the fuel and air first in rear flame fuel injection pipe 4
It is pre-mixed in space between 7, improves the mixing effect of fuel and air, and the structure of the burner is simple, reduces
The cost of system.
In some embodiments, as shown in Fig. 2,4,5, air orifice plate 5 have air inlet side surface 51 (Fig. 2, shown in 3 on
Surface) and outlet side surface 52 (Fig. 2,3 shown in lower surface), outlet side surface 52 be equipped with multiple companies corresponding with air admission hole 19
Logical distributing trough 21.In other words, each air admission hole 19 is corresponded on outlet side surface 52 is designed with one and 19 phase of air admission hole
The distributing trough 21 of connection, when external air enters outlet side surface 52 by air inlet side surface 51 by air admission hole 19, air
It can be flowed along the distributing trough 21, to improve the mobility of air, be conducive to the blending of air and fuel.
In some embodiments, distributing trough 21 is the arc groove of the circumferentially extending along air orifice plate 5.In other words, correspond to
Each air admission hole 19 is all provided with that there are one the arc grooves of the circumferentially extending along air orifice plate 5 on outlet side surface 52.
In some embodiments, air admission hole 19 is arranged to the evenly spaced radial multi-turn opened along air orifice plate 5, each circle
On air admission hole 19 along the circumferential array of air orifice plate 5 and evenly-spaced.
In some embodiments, the circumferential lengths phase for the distributing trough 21 being connected with the air admission hole 19 on same circle
Together.In other words, the circumferential lengths of the 19 corresponding distributing trough 21 of multiple air admission holes on same circle are identical.
In some embodiments, along the radial direction of air orifice plate 5, two neighboring distributing trough 21, it is located at point of inside
The circumferential lengths of slot allocation 21 are less than the circumferential lengths of the distributing trough 21 positioned at outside.In other words, on the small circle of radial dimension into
The circumferential lengths of 19 corresponding distributing trough 21 of stomata are less than the 19 corresponding distributing trough 21 of air admission hole on the big circle of radial dimension
Circumferential lengths.
In some embodiments, air admission hole 19 is arranged to evenly spaced radial four circles opened along air orifice plate 5, each circle
Upper tool divides there are four the evenly-spaced air admission hole 19 of circumferential direction along air orifice plate 5 so as to whole air admission holes 19 of air orifice plate 5
At the air admission hole 19 in four groups, each group along the radially aligned of air orifice plate 5, what is be connected with the air admission hole 19 in each group divides
The circumferential lengths of slot allocation 21 are gradually reduced along the radial ecto-entad of air orifice plate 5.
In some embodiments, as shown in Figure 2,6, spray plate 7 has import side surface (upper surface shown in FIG. 1) and goes out
Mouthful side surface (lower surface shown in FIG. 1) has mixing cavity groove 71 on import side surface, and mixing has combustion on the side wall of cavity groove 71
Expect that import 72, squit hole 20 extend to the outlet side surface of spray plate 7 from the bottom surface of mixing cavity groove 71.It is understood that combustion
Material is entered by fuel inlet 72 in mixing cavity groove, and the air entered by air orifice plate 5 enters in mixing cavity groove 71 with fuel
Mixing, mixed mixture are sprayed by squit hole 20 by the outlet side surface of spray plate 7.
In some embodiments, mixing cavity groove 71 is multiple, multiple mixing cavity grooves 71 and the circumferentially-spaced cloth along spray plate 7
It sets, there are multiple squit holes 20 on the bottom surface of each mixing cavity groove 71.
In some embodiments, as shown in fig. 6, mixing cavity groove 71 is four, the center of the import side surface of spray plate 7 has
There is square protruding 73, adjacent mixing cavity groove 71 is spaced apart by substantially fan-shaped protrusion 74, inner end (the i.e. edge of each fan-shaped protrusion 74
Radially inward one end of spray plate 7) corresponding with square protruding 73 corner connects, i.e., and each corner of square protruding 72 connects
A fan-shaped protrusion 74 is connect, the side of the outer end of each fan-shaped protrusion 74 is connected with arc convex 75, and the arc convex 75 is along spray
The circumferentially extending of plate 7 is noted, and the other end of arc convex 75 is spaced apart with adjacent sector protrusion 74 to form fuel inlet 72.
In some embodiments, as shown in Fig. 2,3,7, cowling panel 22, rectification are equipped between air orifice plate 5 and spray plate 7
Plate 22 is equipped with multiple rectification holes 23.The burner of gas turbine according to the ... of the embodiment of the present invention, can be by cowling panel 22
The flowing that one step improves the air for entering the air orifice plate 5 in rear flame fuel injection pipe 4 and the space between spray plate 7 is uniform
Property, to the mixing conducive to air and fuel.
In some embodiments, axial direction of the air orifice plate 5 with cowling panel 22 along rear flame fuel injection pipe 4 is pasted directly with one another
It closes, axial direction of the cowling panel 22 with spray plate 7 along rear flame fuel injection pipe 4 is bonded directly with one another.In other words, as shown in Figure 2,3,
It is equipped with air orifice plate 5, cowling panel 22 and spray plate 7 in flame fuel injection pipe 4 successively from top to bottom afterwards, and air orifice plate 5, whole
Flowing plate 22 and spray plate 7 are all plectanes, and the axis of three plectanes is consistent, and the upper surface of cowling panel 22 and air orifice plate 5
Lower surface directly fits, and the lower surface of cowling panel 22 and the upper surface of the arc convex 75 of nozzle plate 7 directly fit.
In some embodiments, the burner of the gas turbine of the embodiment of the present invention further includes floating lantern ring 3, floating lantern ring
3 are mounted on burner inner liner 1 and are moved relative to burner inner liner 1, and the inner end of rear flame fuel injection pipe 4 is prolonged across floating lantern ring 2
Reach burner inner liner 1.Herein, " removable " refers to that floating lantern ring 3 is located on burner inner liner 1, but burner inner liner 1 does not limit floating bushing ring
3 movements, the movement can include mainly the global displacement radially of floating lantern ring 3 or due to generation of expanding with heat and contract with cold contraction or
Expansion also includes the axial contraction or expansion due to generation of expanding with heat and contract with cold along floating lantern ring 3 certainly.
It is understood that floating lantern ring 3 is set on rear flame fuel injection pipe 4, rear flame fuel injection pipe 4 and fire
Flame cylinder 1 generates thermal expansion at high temperature, and floating lantern ring 3 can with the expansion or shrinkage of rear flame fuel injection pipe 4 and correspondingly
Expansion or shrinkage (generates displacement), since there are thermal dilation differences between rear flame fuel injection pipe 4 and burner inner liner 1, passes through
Floating lantern ring 3, flame fuel injection pipe 4 and flame after can compensating are set between rear flame fuel injection pipe 4 and burner inner liner 1
There are thermal dilation difference between cylinder 1, avoids thermally expanding unbalanced problem, reduce the generation of thermal stress.
In some embodiments, burner inner liner 1 is equipped with mounting hole, and bearing 6 is equipped in mounting hole, and floating lantern ring 3 is opposite
It is movably arranged on bearing 6 in bearing 6.In other words, bearing 6 is installed on burner inner liner 1, floating lantern ring is installed on bearing 6
3, and floating lantern ring 3 on bearing 6 can the integrally radial dilatation along floating lantern ring 3 or contraction, as shown in Figure 2,3, floating bushing
Ring 3 can be expanded or be shunk in the lateral direction on bearing 6.
In some embodiments, bearing 6 includes pedestal 61 and annular cover plate 62, and pedestal 61 includes cylinder 611, flange 612
With cofferdam 613, wherein flange 612 is from outer end (upper end of cylinder 611 shown in Fig. 3) periphery of cylinder 611 along the cylinder 611
Extend radially outwardly, the extending axially outward along cylinder 611 from the outer peripheral edge of flange 612 of cofferdam 613.In other words, cofferdam 613
It is connected with cylinder 611 by flange 612, and the internal diameter in cofferdam 613 is more than the internal diameter of cylinder 611.
The outer peripheral edge of annular cover plate 62 is connected with cofferdam 613 so that annular cover plate 62, cofferdam 613 and flange 612 form ring
Shape slot 15.Such as shown in Fig. 3, annular cover plate 62 is connected with the inner wall in cofferdam 613 and positioned at the upper end of flange 612, ring cover
There are gaps between plate 62 and flange 612, so that annular cover plate 62, cofferdam 613 and flange 612 form annular groove 15.
A part for floating lantern ring 3 movably coordinates in the annular groove 15.In other words, a part for floating lantern ring 3
In the annular groove 15, the part of floating lantern ring 3 can be in the annular groove 15 radially whole is displaced outwardly or whole for cooperation
Body moves inward.
In some embodiments, floating lantern ring 3 includes cylindrical portion 31 and peripheral part 32, and peripheral part 32 is out of cylindrical portion 31
Hold (lower end shown in Fig. 2) extending radially outwardly along the cylindrical portion 31.In other words, as shown in Fig. 2, floating lantern ring 3 includes upper
The cylindrical portion 31 in portion and the peripheral part 32 of lower part, the upper end of peripheral part 32 are connected with cylindrical portion 31, and peripheral part 32 is along cylindrical portion 31
Extend radially outwardly.
The peripheral part 32 of floating lantern ring 3 movably coordinates in annular groove 15.In other words, as shown in figure 3, peripheral part 32
It expands or shrinks in the annular groove 15 and along the upper surface of flange 612.
Cylindrical portion 31 be sleeved on rear flame fuel injection pipe 4 and with rear 4 tight fit of flame fuel injection pipe.
In some embodiments, outer end of the cylindrical portion 31 including direct tube section 311 and with direct tube section 311 is (on shown in Fig. 3
End) connected loudspeaker section 312.In other words, as shown in Fig. 2, cylindrical portion 31 includes the loudspeaker section of the direct tube section 311 and top of lower part
312, the upper end of direct tube section 311 is connect with loudspeaker section 312, and the radial dimension of loudspeaker section 312 gradually increases from top to bottom.
Flame fuel injection pipe 4 sequentially passes through the loudspeaker section 312 of cylindrical portion 31, direct tube section 311 and stretches into pedestal 61 afterwards
In cylinder 611, the direct tube section 311 of cylindrical portion 31 and rear 4 tight fit of flame fuel injection pipe.Specifically, as shown in Fig. 2, cylinder
The internal face flush of 611 lower face, the lower face of rear flame fuel injection pipe 4 and burner inner liner 1.
In some embodiments, the wall of cylinder 611 is equipped with the cooling hole 8 that is connected to circular passage 5, and cooling air can be with
Entered in pedestal 61 by cooling hole 8, with flame fuel injection pipe 4 after cooling and featheriness.
In some embodiments, the outer end (upper end shown in Fig. 2) of rear flame fuel injection pipe 4 has flange 9, rear flame
Fuel injection pipe 4 is mounted on by flange 9 in guide bushing 2.Specifically, flange 9 is mounted on water conservancy diversion by fasteners such as bolts
On bushing 2.
In some embodiments, guide bushing 2 is equipped with mounting hole, is equipped with outer shroud 10 in mounting hole, outer shroud 10 has
Annular outer groove 101, annular trough 102 and intercommunicating pore 103.
Annular outer groove 101 along the radially outward opening of the outer shroud 10, along the outer shroud 10 radially-inwardly open by annular trough 102
Mouthful, intercommunicating pore 103 is for being connected to annular outer groove 101 and annular trough 102.Specifically, as shown in figure 3, outer shroud 10 includes on flat
Cover board, connecting plate and lower cover and section in an axial direction are in substantially I-shaped, and upper cover plate is parallel with lower cover and arranged for interval, even
Fishplate bar is axially extending along outer shroud 10, and connecting plate is equipped with intercommunicating pore 103, and the middle position of upper cover plate 10 is connected by connecting plate
Lower cover is connect, lower cover includes along the radial outside portion and inside portion being sequentially arranged from outside to inside of outer shroud 10, the radial direction of outside portion
Size is shorter than the radial dimension of inside portion.
Inner ring 11 is installed, inner ring 11 has inner ring annular groove 111, and inner ring annular groove 111 is along the inner ring 11 in outer shroud 10
Radially outward opening.
The inner ring annular groove 111 of inner ring 11 is docked with the annular trough 102 of outer shroud 10 to form annular fuel passage 12.
The flange 9 of 4 outer end of flame fuel injection pipe is mounted on outer shroud 10 afterwards, and rear flame fuel injection pipe 4 passes through inner ring
11.In other words, as shown in Figure 2,3, flange 9 is fastened by bolts on outer shroud 10, and outer shroud 10 is fixed in guide bushing 2, from
And flange 9 is mounted in guide bushing 2 indirectly.
Annular fuel passage 12 is connected by the fuel through-hole 13 in inner ring 11 with the teasehole on rear flame fuel injection pipe 4
It is logical, so that the fuel in annular fuel passage 12 passes sequentially through fuel through-hole 13 and teasehole into rear flame fuel injection pipe 4
It is interior.It is understood that the fuel in annular fuel passage 12 enters rear flame after passing sequentially through fuel through-hole 13 and teasehole
In fuel injection pipe 4, the fuel in rear flame fuel injection pipe 4 enters spray plate 7 using the fuel inlet 72 on spray plate 7
On mixing cavity groove 71 in, with mixing cavity groove 7 in realize air and fuel mixing.
In some embodiments, 2 inside of guide bushing is equipped with fuel channel 16, and fuel channel 16 connects with annular outer groove 101
It is logical, that is, be connected with annular fuel passage 12.As shown in Figure 1,3, fuel is by the fuel channel 16 on the inside of guide bushing 2
Left end receives, and is passed through in annular fuel passage 12 by the right end of fuel channel 16, so as to the mixing chamber in time on spray plate 7
Fuel is supplied in slot 71.
In some optional embodiments, fuel channel 16 is formed in the inner wall of guide bushing 2.In other embodiments
In, fuel cover board 17 is equipped in guide bushing 2, fuel channel 16 is formed between the inner wall of guide bushing 2 and fuel cover board 17.
In some embodiments, cyclone 18 is equipped in rear flame fuel injection pipe 4.Flame after cyclone 18 can enhance
The mixing effect of fuel and air in fuel injection pipe 4, to stablize flame.Specifically, as shown in Figure 2,3, rear flame fuel
Cyclone 18 in injection pipe 4 is arranged adjacent to the lower face of rear flame fuel injection pipe 4.
In some embodiments, rear flame fuel injection pipe 4 is multiple, and multiple rear flame fuel injection pipes 4 are served as a contrast along water conservancy diversion
The circumferential uniform intervals arrangement of set 2.The burner of the gas turbine of the embodiment of the present invention, by under primary fuel nozzles
The rear flame fuel injection pipe 4 that multiple circumferential uniform intervals along guide bushing 2 are arranged is arranged in trip position, can further improve
NOXDischarge improves overall performance.
Below with reference to the accompanying drawings 1-7 describes the burner of the gas turbine according to the specific embodiment of the invention.
As shown in figs. 1-7, the burner of gas turbine according to the ... of the embodiment of the present invention include burner inner liner 1, guide bushing 2,
Floating lantern ring 3, rear flame fuel injection pipe 4, air orifice plate 5, bearing 6, spray plate 7, outer shroud 10, inner ring 11, fuel cover board 17,
Cyclone 18 and cowling panel 22.
Guide bushing 2 is set on burner inner liner 1 to form circular passage 14, water conservancy diversion between guide bushing 2 and burner inner liner 1
It is equipped with fuel cover board 17 in bushing 2, forms fuel channel 16 between fuel cover board 17 and guide bushing 2.
The upper end of flame fuel injection pipe 4 is fixed in guide bushing 2 afterwards, and the lower end of rear flame fuel injection pipe 4 extends
To burner inner liner 1.Flame fuel injection pipe 4 is multiple afterwards, and multiple rear flame fuel injection pipes 4 are along the circumferential uniform of guide bushing 2
Arranged for interval.There are multiple teaseholes, multiple teaseholes are along rear flame fuel injection pipe 4 after each on flame fuel injection pipe 4
Circumferential uniform intervals arrangement.
It is axial successively equipped with the air orifice plate 5, cowling panel 22 and spray for being plectane along it in flame fuel injection pipe 4 afterwards
Plate 7, air orifice plate 5, cowling panel 22 are consistent with the axial direction of spray plate 7, and cowling panel 22 is equipped with multiple rectification holes 23, rectification
The upper surface of plate 22 is directly fitted with air orifice plate 5, and lower surface and the spray plate 7 of cowling panel 22 directly fit：
Air orifice plate 5 is equipped with 16 air admission holes 19, and air admission hole 19 is arranged to open along the evenly spaced radial of air orifice plate 5
Four circles, there are four the evenly-spaced air admission holes 19 of circumferential direction along air orifice plate 5 for tool on each circle, so as to air orifice plate 5
Whole air admission holes 19 are divided into four groups, radially aligned of the air admission hole 19 in each group along air orifice plate 5.
There is air orifice plate 5 air inlet side surface 51 and outlet side surface 52, outlet side surface 52 to be equipped with multiple and air inlet
Hole 19 corresponds to the distributing trough 21 of connection, and distributing trough 21 is the arc groove of the circumferentially extending along air orifice plate 5.It is multiple on same circle
The circumferential lengths of 19 corresponding distributing trough 21 of air admission hole are identical, the distributing trough 21 being connected with the air admission hole 19 in each group
Circumferential lengths be gradually reduced along the radial ecto-entad of air orifice plate 5.
Spray plate 7 has import side surface and outlet side surface, has 4 mixing cavity grooves 71 on import side surface, each
The fuel inlet 72 for having on the side wall of cavity groove 71 and being connected to the teasehole on rear flame fuel injection pipe 4 is mixed, by teasehole
The fuel of entrance is entered by fuel inlet in mixing cavity groove 71.
The center of the import side surface of spray plate 7 has square protruding 73, and adjacent mixing cavity groove 71 is by substantially fan-shaped convex
It plays 74 to be spaced apart, pair of inner end (i.e. along radially inward one end of spray plate 7) and square protruding 73 of each fan-shaped protrusion 74
The corner answered connects, i.e., each corner of square protruding 72 connects a fan-shaped protrusion 74, the outer end of each fan-shaped protrusion 74
Side is connected with arc convex 75, and the arc convex 75 is along the circumferentially extending of spray plate 7, and the other end of arc convex 75 and phase
Adjacent sector protrusion 74 is spaced apart to form fuel inlet 72.
Multiple squit holes 20 are additionally provided on spray plate 7, squit hole 20 extends to spray plate 7 from the bottom surface of mixing cavity groove 71
Side surface is exported, after spray plate 7 is sprayed into the mixture of fuel and air by squit hole 20 in flame fuel injection pipe 4.
Guide bushing 2 is equipped with mounting hole, and outer shroud 10, outer peripheral edge and the guide bushing 2 of outer shroud 10 are equipped in mounting hole
Welding.
Outer shroud 10 has annular outer groove 101, annular trough 102 and intercommunicating pore 103.Annular outer groove 101 is along the outer shroud 10
It is radially outward open, annular trough 102 is along the radially-inwardly opening of the outer shroud 10, and intercommunicating pore 103 is for being connected to annular outer groove 101
With annular trough 102.
Inner ring 11 is installed, inner ring 11 has inner ring annular groove 111, and inner ring annular groove 111 is along the inner ring 11 in outer shroud 10
Radially outward opening, also there is in inner ring 11 fuel through-hole 13.
The inner ring annular groove 111 of inner ring 11 is docked with the annular trough 102 of outer shroud 10 to form annular fuel passage 12, ring
Shape fuel channel 12 is connected with fuel channel 16.
It is understood that the fuel in fuel channel 16 passes through the fuel through-hole on annular fuel passage 12 and inner ring 11
13 and rear flame fuel injection pipe 4 teasehole by fuel inlet 72 enter mixing cavity groove 71 in.
Floating lantern ring 3 is mounted on by bearing 6 on burner inner liner 1.Bearing 6 is mounted in the mounting hole on burner inner liner 6, is floated
Lantern ring 3 is mounted on bearing 6, and is displaced outwardly or whole is inwardly moved in the radially whole of floating lantern ring 3 relative to bearing 6
It is dynamic.
Bearing 6 includes pedestal 61 and annular cover plate 62, and pedestal 61 includes cylinder 611, flange 612 and cofferdam 613, flange
612 from upper end periphery the extending radially outwardly along the cylinder 611 of cylinder 611, and cofferdam 613 is from the outer peripheral edge of flange 612 along cylinder
Body 611 extends axially outward.
Annular cover plate 62 is connected with the inner wall in cofferdam 613 and positioned at the upper end of flange 612, annular cover plate 62 and flange 612
Between there are gap, so that annular cover plate 62, cofferdam 613 and flange 612 form annular groove 15.
Floating lantern ring 3 includes the peripheral part 32 of the cylindrical portion 31 and lower part on top, upper end and the cylindrical portion 31 of peripheral part 32
It is connected, peripheral part 32 extends radially outwardly along cylindrical portion 31.The peripheral part 32 of floating lantern ring 3 coordinates in annular groove 15 and edge
The upper surface of flange 612 is displaced outwardly in the radially entirety of floating lantern ring 3 or entirety moves inward.
Cylindrical portion 31 includes the loudspeaker section 312 of the direct tube section 311 and top of lower part, upper end and the loudspeaker section of direct tube section 311
312 connections, the radial dimension of loudspeaker section 312 gradually increase from top to bottom.
The upper end of flame fuel injection pipe 4 has flange 9 afterwards, and flange 9 is located at the upper surface of outer shroud 10, and flange 9 passes through spiral shell
Bolt is fastened on outer shroud 10, and rear flame fuel injection pipe 4 is passed through out of inner ring 11, and the lower end of rear flame fuel injection pipe 4 according to
It is secondary to be stretched into the cylinder 611 of pedestal 61 across the cylindrical portion 31 of floating lantern ring 3 and peripheral part 32, the cylindrical portion 31 of floating lantern ring 3
Direct tube section 311 and rear 4 tight fit of flame fuel injection pipe, the lower face of rear flame fuel injection pipe 4, the lower face of bearing 6
With the internal face flush of burner inner liner 1, sprayed by the lower end of rear flame fuel injection pipe 4 so as to the mixture of fuel and air
In burner inner liner 1.
The position of its neighbouring lower face is equipped with cyclone 18 in flame fuel injection pipe 4 afterwards, to further enhance rear flame
The mixing effect of fuel and air in fuel injection pipe 4 stablizes flame.
The wall of cylinder 611 is equipped with the cooling hole 8 that is connected to circular passage 14, cooling air can by cooling hole 8 into
Enter in pedestal 61, with flame fuel injection pipe 4 after cooling and featheriness.
The gas turbine of embodiment according to another aspect of the present invention includes the burner of above-described embodiment.
In the description of the present invention, it is to be understood that, term "center", " longitudinal direction ", " transverse direction ", " length ", " width ",
" thickness ", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom" "inner", "outside", " up time
The orientation or positional relationship of the instructions such as needle ", " counterclockwise ", " axial direction ", " radial direction ", " circumferential direction " be orientation based on ... shown in the drawings or
Position relationship is merely for convenience of description of the present invention and simplification of the description, and does not indicate or imply the indicated device or element must
There must be specific orientation, with specific azimuth configuration and operation, therefore be not considered as limiting the invention.
In addition, term " first ", " second " are used for description purposes only, it is not understood to indicate or imply relative importance
Or implicitly indicate the quantity of indicated technical characteristic.Define " first " as a result, the feature of " second " can be expressed or
Implicitly include at least one this feature.In the description of the present invention, the meaning of " plurality " is at least two, such as two, three
It is a etc., unless otherwise specifically defined.
In the present invention unless specifically defined or limited otherwise, term " installation ", " connected ", " connection ", " fixation " etc.
Term shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or integral；Can be that machinery connects
It connects, can also be to be electrically connected or can communicate each other；It can be directly connected, can also indirectly connected through an intermediary, it can be with
It is the interaction relationship of the connection or two elements inside two elements, unless otherwise restricted clearly.For this field
For those of ordinary skill, the specific meanings of the above terms in the present invention can be understood according to specific conditions.
In the present invention unless specifically defined or limited otherwise, fisrt feature can be with "above" or "below" second feature
It is that the first and second features are in direct contact or the first and second features pass through intermediary mediate contact.Moreover, fisrt feature exists
Second feature " on ", " top " and " above " but fisrt feature be directly above or diagonally above the second feature, or be merely representative of
Fisrt feature level height is higher than second feature.Fisrt feature second feature " under ", " lower section " and " below " can be
One feature is directly under or diagonally below the second feature, or is merely representative of fisrt feature level height and is less than second feature.
In the description of this specification, reference term " one embodiment ", " some embodiments ", " example ", " specifically show
The description of example " or " some examples " etc. means specific features, structure, material or spy described in conjunction with this embodiment or example
Point is included at least one embodiment or example of the invention.In the present specification, schematic expression of the above terms are not
It must be directed to identical embodiment or example.Moreover, particular features, structures, materials, or characteristics described can be in office
It can be combined in any suitable manner in one or more embodiments or example.In addition, without conflicting with each other, the skill of this field
Art personnel can tie the feature of different embodiments or examples described in this specification and different embodiments or examples
It closes and combines.
Although the embodiments of the present invention has been shown and described above, it is to be understood that above-described embodiment is example
Property, it is not considered as limiting the invention, those skilled in the art within the scope of the invention can be to above-mentioned
Embodiment is changed, changes, replacing and modification.
Claims (20)
1. a kind of burner of gas turbine, which is characterized in that including：
Burner inner liner；
Guide bushing, the guide bushing are set on the burner inner liner, are formed between the guide bushing and the burner inner liner
Circular passage；
The outer end of flame fuel injection pipe afterwards, the rear flame fuel injection pipe is fixed in the guide bushing, after described
The inner end of flame fuel injection pipe extends to the burner inner liner, is axially equipped with successively along it in the rear flame fuel injection pipe empty
Spiracular plate and spray plate, the air orifice plate are equipped with multiple air admission holes, and the spray plate is equipped with multiple squit holes, the spray
Plate is noted to be used to fuel and air mixing resulting mixture and the mixture is sprayed into the rear flame combustion by the squit hole
Expect in injection pipe.
2. the burner of gas turbine according to claim 1, which is characterized in that the air orifice plate has air inlet side table
Face and outlet side surface, the outlet side surface are equipped with the distributing trough of multiple connections corresponding with the air admission hole.
3. the burner of gas turbine according to claim 2, which is characterized in that the distributing trough is along the airport
The arc groove of the circumferentially extending of plate.
4. the burner of gas turbine according to claim 3, which is characterized in that the air admission hole is arranged to along the sky
The evenly spaced radial multi-turn opened of spiracular plate, the circumferential array and of the air admission hole on each circle along the air orifice plate
It is even to be spaced apart.
5. the burner of gas turbine according to claim 4, which is characterized in that with the air inlet on same circle
The circumferential lengths for the distributing trough that hole is connected are identical.
6. the burner of gas turbine according to claim 5, which is characterized in that along the radial direction side of the air orifice plate
To in the two neighboring distributing trough, the circumferential lengths for being located at the distributing trough of inside are less than the circumferential direction of the distributing trough positioned at outside
Length.
7. the burner of gas turbine according to claim 4, which is characterized in that the air admission hole is arranged to along the sky
Evenly spaced radial four circles opened of spiracular plate, there are four the circumferential direction along the air orifice plate is evenly-spaced for tool on each circle
The air admission hole is divided into four groups so as to the whole air admission hole of the air orifice plate, and the air admission hole in each group is along institute
The radially aligned for stating air orifice plate, the circumferential lengths for the distributing trough being connected with the air admission hole in each group are along the air
The radial ecto-entad of orifice plate is gradually reduced.
8. the burner of gas turbine according to claim 1, which is characterized in that the spray plate has import side surface
With outlet side surface, there is on the import side surface mixing cavity groove, there is fuel inlet, institute on the side wall of the mixing cavity groove
State the outlet side surface that squit hole extends to the spray plate from the bottom surface of the mixing cavity groove.
9. the burner of gas turbine according to claim 8, which is characterized in that the mixing cavity groove is multiple and along institute
The circumferentially-spaced arrangement of spray plate is stated, there are multiple squit holes on the bottom surface of each mixing cavity groove.
10. the burner of gas turbine according to claim 9, which is characterized in that the mixing cavity groove is four, described
There is square protruding, the adjacent mixing cavity groove to pass through substantially fan-shaped bulge clearance at the center of the import side surface of spray plate
It opens, the inner end corner corresponding with the square protruding of each fan-shaped protrusion connects, and each the fan-shaped protrusion is outer
The side at end is connected with the arc convex of the circumferentially extending along the spray plate, the other end of the arc convex and adjacent institute
Fan-shaped bulge clearance is stated to open to form the fuel inlet.
11. the burner of the gas turbine according to any one of claim 1-10, which is characterized in that the air orifice plate
Cowling panel is equipped between the spray plate, the cowling panel is equipped with multiple rectification holes.
12. the burner of gas turbine according to claim 11, which is characterized in that the air orifice plate and the rectification
Plate is bonded directly with one another along the axial direction of the rear flame fuel injection pipe, and the cowling panel is with the spray plate along the rear flame
The axial direction of fuel injection pipe is bonded directly with one another.
13. the burner of the gas turbine according to any one of claim 1-10, which is characterized in that further include floating bushing
Ring, the floating lantern ring are mounted on the burner inner liner and removable relative to the burner inner liner, the rear flame fuel injection
The inner end of pipe extends to the burner inner liner across the floating lantern ring.
14. the burner of gas turbine according to claim 13, which is characterized in that the burner inner liner is equipped with installation
Hole, bearing is equipped in the mounting hole, and the floating lantern ring is mounted on the bearing and removable relative to the bearing.
15. the burner of gas turbine according to claim 14, which is characterized in that the bearing includes pedestal and annular
Cover board, the pedestal includes cylinder, from the upper end periphery of the cylinder along the flange of the cylinder to extend radially outwardly and from institute
The axially outwardly extending cofferdam of the outer peripheral edge along the cylinder of flange is stated,
The outer peripheral edge of the annular cover plate is connected with the cofferdam so that the annular cover plate, the cofferdam and the flange are formed
Annular groove,
A part for the floating lantern ring movably coordinates in the annular groove.
16. the burner of gas turbine according to claim 15, which is characterized in that the floating lantern ring includes tubular section
With from the inner end of the tubular section, along the peripheral part of the tubular section to extend radially outwardly, the peripheral part movably coordinates
In the annular groove, tubular section set in the rear on flame fuel injection pipe and with it is described after flame fuel injection pipe close-fitting
It closes.
17. the burner of gas turbine according to claim 13, which is characterized in that flame fuel injection pipe after described
There is flange, the rear flame fuel injection pipe to be mounted in the guide bushing by the flange for outer end.
18. the burner of gas turbine according to claim 17, which is characterized in that the guide bushing, which is equipped with, fixes
Hole, outer shroud is equipped in the mounting hole, and the outer shroud has along the annular outer groove of the outer shroud being radially outward open and along this
The annular trough of outer shroud being radially-inwardly open, the annular outboard are connected to the annular outer groove by intercommunicating pore；
Inner ring is installed, the inner ring has the inner ring annular groove being radially outward open along the inner ring, described in the outer shroud
Inner ring annular groove is docked with the annular trough to form annular fuel passage,
The flange is mounted on the outer shroud, and the rear flame fuel injection pipe passes through the inner ring, the annular fuel logical
Road is connected to by the fuel through-hole in the inner ring with the teasehole on the rear flame fuel injection pipe.
19. the burner of the gas turbine according to any one of claim 1-10, which is characterized in that flame combustion after described
Expect to be equipped with cyclone in injection pipe.
20. a kind of gas turbine, which is characterized in that including the burner as described in any one of claim 1-19.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711279240.XA CN108278634B (en) | 2017-12-06 | 2017-12-06 | Gas turbine and combustor thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711279240.XA CN108278634B (en) | 2017-12-06 | 2017-12-06 | Gas turbine and combustor thereof |
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| Publication Number | Publication Date |
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| CN108278634A true CN108278634A (en) | 2018-07-13 |
| CN108278634B CN108278634B (en) | 2020-07-14 |
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ID=62801343
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| Application Number | Title | Priority Date | Filing Date |
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| CN201711279240.XA Active CN108278634B (en) | 2017-12-06 | 2017-12-06 | Gas turbine and combustor thereof |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110979685A (en) * | 2019-12-11 | 2020-04-10 | 贵州理工学院 | A dibble seeding system for unmanned aerial vehicle seeding |
| CN113738777A (en) * | 2021-09-13 | 2021-12-03 | 中国联合重型燃气轮机技术有限公司 | Shaft coupling |
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| US5881756A (en) * | 1995-12-22 | 1999-03-16 | Institute Of Gas Technology | Process and apparatus for homogeneous mixing of gaseous fluids |
| CN101818908A (en) * | 2009-02-02 | 2010-09-01 | 通用电气公司 | The apparatus for fuel injection that is used for turbogenerator |
| CN102954469A (en) * | 2011-08-05 | 2013-03-06 | 通用电气公司 | Assembly and apparatus related to integrating late lean injection into combustion turbine engine |
| CN103189619A (en) * | 2010-10-29 | 2013-07-03 | 索拉透平公司 | Gas turbine combustor with mounting for helmholtz resonators |
| CN203893228U (en) * | 2012-11-06 | 2014-10-22 | 通用电气公司 | Micro mixer spray nozzle |
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Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5881756A (en) * | 1995-12-22 | 1999-03-16 | Institute Of Gas Technology | Process and apparatus for homogeneous mixing of gaseous fluids |
| CN101818908A (en) * | 2009-02-02 | 2010-09-01 | 通用电气公司 | The apparatus for fuel injection that is used for turbogenerator |
| CN103189619A (en) * | 2010-10-29 | 2013-07-03 | 索拉透平公司 | Gas turbine combustor with mounting for helmholtz resonators |
| CN102954469A (en) * | 2011-08-05 | 2013-03-06 | 通用电气公司 | Assembly and apparatus related to integrating late lean injection into combustion turbine engine |
| CN203893228U (en) * | 2012-11-06 | 2014-10-22 | 通用电气公司 | Micro mixer spray nozzle |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110979685A (en) * | 2019-12-11 | 2020-04-10 | 贵州理工学院 | A dibble seeding system for unmanned aerial vehicle seeding |
| CN113738777A (en) * | 2021-09-13 | 2021-12-03 | 中国联合重型燃气轮机技术有限公司 | Shaft coupling |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108278634B (en) | 2020-07-14 |
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