CN105318355B - Gas turbine burner - Google Patents
Gas turbine burner Download PDFInfo
- Publication number
- CN105318355B CN105318355B CN201510455129.6A CN201510455129A CN105318355B CN 105318355 B CN105318355 B CN 105318355B CN 201510455129 A CN201510455129 A CN 201510455129A CN 105318355 B CN105318355 B CN 105318355B
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- China
- Prior art keywords
- fuel nozzle
- fuel
- gas turbine
- turbine burner
- erection opening
- 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.)
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Classifications
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- 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
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- 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
- F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
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- 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
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/00018—Manufacturing combustion chamber liners or subparts
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Gas Burners (AREA)
- Nozzles For Spraying Of Liquid Fuel (AREA)
Abstract
The present invention provides a kind of gas turbine burner, even if the narrow space around fuel nozzle, the gas turbine burner also can easily carry out the engagement of fuel nozzle and fuel nozzle plate, the raising of the precision engaged to fuel nozzle with fuel nozzle plate is realized, so as to improve the stability of structure.Gas turbine burner possesses pulverizing jet (18), and the pulverizing jet includes：Multiple fuel nozzles (15), it supplies fuel；Fuel nozzle plate (14), it structurally supports the end of the fuel nozzle, and plays a part of to distribute from the fuel that upstream side flows into the fuel nozzle；And air orifice plate (13), it has multiple airports (21) of supply combustion air, gas turbine burner formed with the fuel nozzle erection opening (44) for inserting fuel nozzle (15), engages from the upstream side of fuel nozzle plate (14) on fuel nozzle plate (14) to the fuel nozzle plate (14) with the fuel nozzle (15) inserted to fuel nozzle erection opening (44).
Description
Technical field
The present invention relates to a kind of gas turbine burner, more particularly to a kind of combustion gas for the fuel nozzle for possessing spray fuel
Turbine combustion device.
Background technology
In gas turbine burner, for the purpose of the load applied by reducing waste gas to environment, to gas turbine burner
The NOx discharged during operating is set with strict environmental criteria.
NOx discharge rate increases with the high temperature of flame temperature, thus needs to suppress in gas turbine burner
It is formed locally the flame of high temperature and realizes and equably burn.
In order to uniformly be burnt in gas turbine burner, the dispersiveness for improving fuel is effective, such as
In the technology of gas turbine burner described in the Japanese Unexamined Patent Publication 2013-108667 publications of known example, by combustion gas wheel
Multiple fuel nozzles are set respectively in the circumference and radial direction of the air orifice plate of machine burner, so as to improve the scattered of fuel
Property.
In addition, in gas turbine burner described in Japanese Unexamined Patent Publication 2013-053814 publications in known example, pass through
Set located at formed combustion chamber combustion barrel head give mixed type guide's pulverizing jet and its periphery configuration give mixing
The main jet burner of type, so as to realize sufficiently giving hybridization and realizing low NOxization for air and fuel.
Citation
Patent document
Patent document 1：Japanese Unexamined Patent Publication 2013-108667 publications
Patent document 2：Japanese Unexamined Patent Publication 2013-053814 publications
In the gas turbine burner of the technology described in patent document 1, if for the purpose of the dispersiveness for improving fuel
And increase the radical of fuel nozzle, then there is between the distance between fuel nozzle or fuel nozzle and neighbouring wall
The problem that distance shortens.
Moreover, if the distance between distance or fuel nozzle between fuel nozzle and neighbouring wall shorten, fire
Space around material nozzle becomes narrow, in the gas turbine burner of the technology described in patent document 2, if relative to
The fuel nozzle plate of supporting fuel nozzle is from the end of the downstream side engagement fuel nozzle in structure, then there is cannot ensure
Problem for the sufficient space of engagement.
The content of the invention
Invent problem to be solved
It is an object of the invention to provide a kind of following gas turbine burner, even if the space around fuel nozzle
Narrow, the gas turbine burner also can easily carry out the engagement of fuel nozzle and fuel nozzle plate, realize to fuel nozzle
The raising of the precision engaged with fuel nozzle plate, so as to improve the stability of structure.
For solving the scheme of problem
The gas turbine burner of the present invention possesses pulverizing jet, and the pulverizing jet includes：Multiple fuel nozzles, it supplies combustion
Material；Fuel nozzle plate, it structurally supports the end of the fuel nozzle, and play by from the fuel that upstream side flows into this
The effect of fuel nozzle distribution；And air orifice plate, it has multiple airports of supply combustion air, the gas turbine
Burner is configured to, and formed with the fuel nozzle erection opening for inserting fuel nozzle on fuel nozzle plate, is sprayed from fuel
The upstream side of mouth plate is engaged by melting welding to the fuel nozzle plate with the fuel nozzle inserted to fuel nozzle erection opening,
Also, in the appearance of the fuel nozzle inserted into the fuel nozzle erection opening than the position downstream of the engagement
Formed with gap between the inner surface of face and the fuel nozzle erection opening, moreover, from the position of the engagement to the fuel
The end of downstream side of nozzle, the outer surface of the fuel nozzle do not contact with other components.
Invention effect
According to invention, following gas turbine burner can be realized, should even if the narrow space around fuel nozzle
Gas turbine burner also can easily carry out the engagement of fuel nozzle and fuel nozzle plate, realize and fuel nozzle and fuel are sprayed
The raising for the precision that mouth plate is engaged, so as to improve the stability of structure.
Brief description of the drawings
Fig. 1 is the flowing and burning of the fuel and air in the gas turbine burner for represent embodiments of the invention 1
The sectional view of the gas turbine burner of the summary of process.
Fig. 2 is the constituting portion in the pulverizing jet portion in the gas turbine burner for represent the embodiments of the invention 1 shown in Fig. 1
Part partial sectional view.
Fig. 3 is that the fuel nozzle in the gas turbine burner for represent the embodiments of the invention 1 shown in Fig. 1 sprays with fuel
The partial sectional view of the joint method of mouth plate.
Fig. 4 is the fuel nozzle for forming pulverizing jet portion and fuel nozzle plate for the gas turbine burner for representing comparative example
The partial sectional view of joint method.
Fig. 5 is fuel nozzle in the gas turbine burner for represent embodiments of the invention 2 and fuel nozzle plate connects
The partial sectional view of conjunction method.
Fig. 6 is fuel nozzle in the gas turbine burner for represent embodiments of the invention 3 and fuel nozzle plate connects
The partial sectional view of conjunction method.
Fig. 7 is fuel nozzle in the gas turbine burner for represent embodiments of the invention 4 and fuel nozzle plate connects
The partial sectional view of conjunction method.
Fig. 8 is fuel nozzle in the gas turbine burner for represent embodiments of the invention 5 and fuel nozzle plate connects
The partial sectional view of conjunction method.
Fig. 9 is fuel nozzle in the gas turbine burner for represent embodiments of the invention 6 and fuel nozzle plate connects
The partial sectional view of conjunction method.
Figure 10 is fuel nozzle in the gas turbine burner for represent embodiments of the invention 7 and fuel nozzle plate connects
The partial sectional view of conjunction method.
Description of reference numerals：
1：Gas-turbine plant, 2：Air, 3：Compressor, 4：Compressed air, 5：Fuel, 6：Burning gases, 7：Combustion gas wheel
Machine burner, 8：Gas turbine, 9：Generator, 10：End cap, 11：Front side outer barrel, 12：Rear side outer barrel, 13：Air orifice plate, 14：
Fuel nozzle plate, 15：Fuel nozzle, 16：Bushing, 17：Stream between rear side outer barrel and bushing, 18：Pulverizing jet, 19：For
The cooling air of cooling, 20：Fuel feed pipe, 21：The airport of air orifice plate, 22：Fuel and the gaseous mixture of compressed air,
23：Combustion chamber, 24：Flame, 30：The end of downstream side of fuel nozzle, 40：The upstream-side-end of fuel nozzle, 40b：Fuel sprays
Side near the upstream side of mouth, 41：The upstream-side-end of fuel nozzle plate, 41b：The end of downstream side of fuel nozzle plate, 43：
Space around fuel nozzle, 44：Fuel nozzle erection opening, 42,45：Junction surface, 50：The stage portion of fuel nozzle, 51：Combustion
The stage portion of material nozzle erection opening, 52：The axial direction of fuel nozzle, 60：Profile decrescence shape portion, 70,71：Tapering, 71：Fuel
The radial direction of nozzle, 80：The flange part of the upstream-side-end of fuel nozzle, 81：The flange part and fuel nozzle of fuel nozzle
Contact site between plate, 90：Throttle hole portion.
Embodiment
Hereinafter, the embodiment of the gas turbine burner of the present invention is illustrated using accompanying drawing.
【Embodiment 1】
The structure for applying the gas-turbine plant of the gas turbine burner of embodiments of the invention 1 is entered using Fig. 1
Row explanation.
In the gas-turbine plant 1 for the gas turbine burner for applying the embodiment 1 shown in Fig. 1, gas turbine is set
Standby 1 includes：Compressor 3, it is from air introduction air 2 and is compressed；Gas turbine burner 7, it makes to press in compressor 3
Compressed air 4 and fuel 5 after contracting are burnt, so as to generate the burning gases 6 of HTHP；Turbine 8, it passes through by the combustion gas wheel
Burning gases 6 drive caused by machine burner 7, obtain the energy of burning gases 6 as rotary power；And generator 9, it makes
Generated electricity with the rotary power of turbine 8.
The gas turbine burner 7 possess the end set of gas turbine burner 7 end cap 10, be installed on end cap
10 cylindric front side outer barrel 11 and front side outer barrel 11 rear side install longer cylindric rear side outer barrel 12.
It is provided with the inner side of the front side outer barrel 11 and rear side outer barrel 12 and forms the discoid of multiple airports 21
Air orifice plate 13, the upstream side of the air orifice plate 13 is provided with fuel nozzle plate 14, is provided with the fuel nozzle plate 14
Multiple fuel nozzles 15 that fuel is sprayed towards the airport 21 formed on air orifice plate 13, under the air orifice plate 13
Trip side is provided with longer cylindric bushing 16, and the bushing 16 forms the combustion for making fuel mix combining combustion with air on the inside of it
Burn room 23.
Moreover, compressed air 4 after being compressed by the compressor 3 between rear side outer barrel 12 and bushing 16 by forming
Circular stream 17, is flowed into the pulverizing jet 18 formed in gas turbine burner 7.
The pulverizing jet 18 includes：Multiple fuel nozzles 15, its spray fuel；Fuel nozzle plate 14, it is supported in structure
The end of fuel nozzle 15, and play a part of to distribute from the fuel that upstream side flows into the fuel nozzle 15；It is and empty
Spiracular plate 13, it is in sky of the downstream for the fuel nozzle plate 14 for possessing the multiple fuel nozzle 15 formed with supply burning
Multiple airports 21 of gas.
In addition, a part for compressed air 4 flows into from multiple Cooling Holes located at the bushing 16 into bushing 16, as
Cooling air 19 for cooling bushing 16.
To the fuel 5 that gas turbine burner 7 supplies by the fuel feed pipe 20 located at end cap 10 and to fuel nozzle
Plate 14 flows into, the multiple airports 21 formed from fuel nozzle plate 14 by each fuel nozzle 15 and direction on air orifice plate 13
Injection.
Then, at the fuel nozzle side entrance of the airport 21 of air orifice plate 13, the combustion next from the injection of fuel nozzle 15
The compressed air 4 that material 5 is supplied with the circular stream 17 by being formed between rear side outer barrel 12 and bushing 16 mixes
And turning into gaseous mixture 22, the fuel 5 and the gaseous mixture 22 of compressed air 4 spray and burnt towards combustion chamber 23, so as to form height
The flame 24 of temperature.
The gas turbine burner 7 of the present embodiment can not only use natural gas, can also use oven gas, oil refinery waste
The fuel such as gas, coal gasification gas are as fuel 5.
Next, figure 2 illustrates the structure of the pulverizing jet 18 of the gas turbine burner 7 of embodiment 1.As shown in Fig. 2
The pulverizing jet 18 set in the gas turbine burner 7 of the present embodiment includes air orifice plate 13, fuel nozzle plate 14 and combustion
Expect nozzle 15.
The upstream-side-end 40 of the fuel nozzle 15 of spray fuel is engaged with fuel nozzle plate 14, and its junction surface is sealed
To cause fuel 5 not leak.
The end of downstream side 30 of fuel nozzle 15 is configured to the airport 21 of air orifice plate 13, does not engage or contacts, pressure
Contracting air 4 is free to flow into relative to the airport 21 formed on air orifice plate 13.
Moreover, the upstream-side-end 40 of fuel nozzle 15 and the joint method of fuel nozzle plate 14 are tight generally using bolt
Gu, melting welding, soldering etc..
Next, using Fig. 3 and Fig. 4 partial enlarged drawing to the composition torch firing of the gas turbine burner 7 of embodiment 1
The joint method of the fuel nozzle 15 and fuel nozzle plate 14 of device 18 illustrates.
Fig. 3 partial enlarged drawing shows the composition pulverizing jet to the gas turbine burner 7 of the present embodiment by melting welding
Joint method when 18 fuel nozzle 15 is engaged with fuel nozzle plate 14.
But in the present embodiment, fuel nozzle 15 and combustion on the composition pulverizing jet 18 to gas turbine burner 7
The joint method that material nozzle plate 14 is engaged, is not limited to the engagement using melting welding, can also utilize the engagement side beyond melting welding
Method.
As shown in Fig. 3 partial enlarged drawing, in the fuel of the composition pulverizing jet 18 of the gas turbine burner 7 of the present embodiment
Nozzle 15 on fuel nozzle plate 14 with the joint method of fuel nozzle plate 14, being formed there through for inserting fuel nozzle 15
Fuel nozzle erection opening 44, to the He of upstream-side-end 40 of the fuel nozzle 15 inserted to the fuel nozzle erection opening 44
This both sides of the upstream-side-end 41 of fuel nozzle plate 14, implement melting welding from upstream side relative to fuel nozzle plate 14 and form engagement
Portion 45, so as to the upstream-side-end 41 to the upstream-side-end 40 of fuel nozzle 15 and fuel nozzle plate 14, both connects
Close.
Fig. 4 shows to carry out the fuel nozzle 15 of the composition pulverizing jet 18 of gas turbine burner 7 with fuel nozzle plate 14
The joint method of the comparative example of engagement, it is attached to the upstream side of fuel nozzle 15 in the joint method of the comparative example shown in the Fig. 4
Near side 40b and the end of downstream side 41b of fuel nozzle plate 14 this both sides, form relative to fuel nozzle plate 14 from downstream
Junction surface 42 and engaged.
However, in the joint method of the comparative example engaged to fuel nozzle 15 with fuel nozzle plate 14 shown in Fig. 4
In, cause the sky around fuel nozzle 15 when being closely equipped with multiple fuel nozzles 15 in the downstream of fuel nozzle plate 14
Between 43 it is narrow in the case of, exist can not ensure in the downstream of fuel nozzle plate 14 be used for carry out engage fuel nozzle 15 with combustion
Expect this problem of enough working spaces of joining process of nozzle plate 14.
In addition, in the joint method of the comparative example engaged to fuel nozzle 15 with fuel nozzle plate 14 shown in Fig. 4
In, structure as shown in Figure 4 can be clear and definite, is not present in the upstream side of fuel nozzle plate 14 and is used to carry out fuel nozzle 15 and combustion
Expect the working space of the engagement of nozzle plate 14.
Then, in the gas turbine burner 7 of the present embodiment shown in Fig. 3, sprayed in the composition of gas turbine burner 7
In the fuel nozzle 15 of burner 18 and the joint method of fuel nozzle plate 14, even if being closely equipped with multiple fuel nozzles 15
In the case of, the joint method of fuel nozzle 15 and fuel nozzle plate 14 in the gas turbine burner of the present embodiment,
It is formed there through the fuel nozzle erection opening 44 for inserting fuel nozzle 15 on fuel nozzle plate 14, and to the fuel nozzle
The fuel nozzle 15 that erection opening 44 inserts, which is matched somebody with somebody, is set to prominent to the downstream of fuel nozzle plate 14.
Moreover, the upstream-side-end 40 of the fuel nozzle 15 to being inserted to the fuel nozzle erection opening 44 and described
This both sides of the upstream-side-end 41 of fuel nozzle plate 14, implement melting welding from upstream side relative to fuel nozzle plate 14 and form engagement
Portion 45, so as to the upstream-side-end 41 to the upstream-side-end 40 of fuel nozzle 15 and fuel nozzle plate 14, both connects
Close.
That is, in the gas turbine burner 7 of the present embodiment, do not arranged using in the upstream side of fuel nozzle plate 14
The structure of fuel nozzle 15 is stated, therefore ensure that in the upstream side of fuel nozzle plate 14 and implement fuel nozzle 15 and fuel nozzle plate
Working space broad enough needed for 14 engagement, so as to which the joining accuracy of fuel nozzle 15 and fuel nozzle plate 14 improves,
And improved along with the joining accuracy, fuel nozzle 15 and the structural reliability at the junction surface of fuel nozzle plate 14 improve.
In addition, the fuel nozzle 15 and fuel nozzle of the composition pulverizing jet 18 in the gas turbine burner 7 of the present embodiment
In the joint method of plate 14, fuel 5 and compressed air 4 gaseous mixture 22 gas turbine burner 7 the internal combustion of combustion chamber 23
Combustion vibration is produced during burning, causes fuel nozzle 15 to situation about being vibrated with the rectangular direction of the central shaft of the fuel nozzle 15
Under, the side of the fuel nozzle 15 is pacified with the fuel nozzle formed for the insertion fuel nozzle 15 into fuel nozzle plate 14
Dress suppresses vibration with the inner surface contact in hole 44, it is thus possible to reduces to for the junction surface formed to the two progress melting welding
The load of 45 effects.
Also, pass through the inner surface in the side of fuel nozzle 15 and the fuel nozzle erection opening 44 of fuel nozzle plate 14
Between design small gap, so as in the fuel nozzle erection opening 44 of the side of fuel nozzle 15 and fuel nozzle plate 14
Between inner surface, frictional force can be produced along with the contact of the two, therefore can obtain making to act on combustion by frictional force
Expect the effect of the vibration decay of nozzle 15.
According to the present embodiment, following gas turbine burner can be realized, even if the space around fuel nozzle is narrow
Narrow, the gas turbine burner also can easily carry out the engagement of fuel nozzle and fuel nozzle plate, realize that the precision of engagement carries
Height, so as to improve the stability of structure.
【Embodiment 2】
Next, the composition of the gas turbine burner 7 of embodiments of the invention 2 is sprayed using Fig. 5 partial enlarged drawing
The joint method of the fuel nozzle 15 and fuel nozzle plate 14 of burner 18 illustrates.
Fig. 5 partial enlargement illustrates the structure of the pulverizing jet 18 set on the gas turbine burner 7 of embodiment 2
Details, sprayed with the fuel of the composition pulverizing jet 18 to gas turbine burner 7 of the embodiments of the invention 1 illustrated before
Mouth 15 is similar with the basic structure for the joint method that fuel nozzle plate 14 is engaged, therefore omits to the two identical structure
Illustrate, different parts is illustrated below.
Fig. 5 partial enlarged drawing shown in the pulverizing jet 18 of the gas turbine burner 7 of embodiment 2, fuel nozzle
15 situations about being engaged by its upstream-side-end 40 with the upstream-side-end 41 of fuel nozzle plate 14.
In the pulverizing jet 18 of the gas turbine burner 7 of the embodiment 2 shown in Fig. 5, through fuel nozzle plate 14 and
The upstream side of the fuel nozzle erection opening 44 of formation is provided with stage portion 51, the stage portion 51 and fuel nozzle erection opening 44
Downstream hole diameter compared to being formed as big footpath, and in the combustion inserted to the inside of the fuel nozzle erection opening 44
The upstream-side-end 40 of material nozzle 15 is provided with stage portion 50, and the stage portion 50 is straight with the part in the downstream of fuel nozzle 15
Used compared to big footpath is formed as in the stage portion 50 that the upstream-side-end 40 of the fuel nozzle 15 is set with being installed in fuel nozzle in footpath
The stage portion 51 that the upstream side in hole 44 is set abuts.
Moreover, upstream-side-end 40 to the stage portion 50 located at the big footpath of fuel nozzle 15 and with being formed at fuel
The upstream-side-end of the fuel nozzle plate 14 of the upstream side pair of the stage portion 51 in the big footpath of nozzle erection opening 44
41 this both sides, implement melting welding from upstream side relative to fuel nozzle plate 14 and form junction surface 45, so as to fuel nozzle 15
Both upstream-side-ends 41 of upstream-side-end 40 and fuel nozzle plate 14 are engaged.
In the pulverizing jet 18 of the gas turbine burner 7 of the embodiment 2 shown in Fig. 5, using in the upper of fuel nozzle 15
The external diameter for the stage portion 50 that trip side end 40 is set has the structure of the big diameter of the external diameter in the downstream than fuel nozzle 15, and
The internal diameter of the stage portion 51 formed using the upstream side of the fuel nozzle erection opening 44 in fuel nozzle plate 14 is had than fuel
The structure of the big diameter of the internal diameter in the downstream of nozzle erection opening 44, thus, the institute in the big footpath set on fuel nozzle 15
The lower surface for stating stage portion 50 abuts with the lower surface of the stage portion 51 in the big footpath set in fuel nozzle erection opening 44, from
And prevent fuel nozzle 15 downstream side comes off from fuel nozzle erection opening 44.
By using above-mentioned structure, even if fuel nozzle 15 upstream-side-end 40 with through fuel nozzle plate 14 and
At the junction surface 45 of the upstream-side-end of the fuel nozzle erection opening 44 of formation produce damage and in the case of breakage, in fuel
The lower surface of the stage portion 50 in the big footpath that the upstream-side-end 40 of nozzle 15 is set in fuel nozzle erection opening 44 also with setting
That puts is formed at the lower surface abutting of the stage portion 51 in the big footpath of fuel nozzle erection opening 44, so as to prevent the fuel nozzle
15 movement, therefore prevent fuel nozzle 15 downstream side comes off and led from the fuel nozzle erection opening 44 of fuel nozzle plate 14
Cause the miscellaneous part damage of gas turbine burner.
In addition, the stage portion 50,51 can also carry out the positioning of the axial direction 52 of fuel nozzle 15.
According to the present embodiment, following gas turbine burner can be realized, even if the space around fuel nozzle is narrow
Narrow, the gas turbine burner also can easily carry out the engagement of fuel nozzle and fuel nozzle plate, realize that the precision of engagement carries
Height, so as to improve the stability of structure.
【Embodiment 3】
Next, the composition of the gas turbine burner 7 of embodiments of the invention 3 is sprayed using Fig. 6 partial enlarged drawing
The joint method of the fuel nozzle 15 and fuel nozzle plate 14 of burner 18 illustrates.
Fig. 6 partial enlargement illustrates the detailed feelings of the structure of the pulverizing jet 18 in the gas turbine burner of embodiment 3
Condition, with the fuel nozzle 15 of the composition pulverizing jet 18 to gas turbine burner 7 of the embodiments of the invention 1 that show before
Upstream-side-end 40 is similar with the basic structure for the joint method that the upstream-side-end 41 of fuel nozzle plate 14 is engaged, therefore
The explanation to the two identical structure is omitted, different parts is illustrated below.
Fig. 6 shows the details of the structure of the pulverizing jet 18 in the gas turbine burner 7 of embodiment 3.
In the pulverizing jet 18 of the gas turbine burner 7 of the embodiment 3 shown in Fig. 6, show to insertion fuel nozzle
The upstream-side-end 40 and fuel nozzle plate 14 of plate 14 and fuel nozzle 15 that the fuel nozzle erection opening 44 that is formed inserts
Upstream-side-end 41, implement melting welding from the upstream side of fuel nozzle plate 14 and form junction surface 45, the upstream side of fuel nozzle 15
The situation that end 40 is engaged by the junction surface 45 and the upstream-side-end 41 with fuel nozzle plate 14.
In the pulverizing jet 18 of the gas turbine burner 7 of embodiment 3, from the fuel for penetrating fuel nozzle plate 14 and being formed
Downstream the external diameter of the part for the fuel nozzle 15 that side protrudes is formed as having from root towards downstream nozzle erection opening 44
End 30 and profile decrescence shape portion 60 that external diameter tapers into.
In the pulverizing jet 18 of the gas turbine burner 7 of embodiment 3, due to from fuel nozzle erection opening 44 downstream
The external diameter for the fuel nozzle 15 that side protrudes is formed as with towards end of downstream side 30 and profile decrescence shape that external diameter tapers into
Shape portion 60, therefore the amount tapered into the external diameter of fuel nozzle 15 is correspondingly, makes the lightweight of fuel nozzle 15, as a result,
It can reduce along with combustion vibration and act on the upstream of the upstream-side-end 40 and fuel nozzle plate 14 to fuel nozzle 15
The load at the junction surface 45 that side end 41 is engaged.
According to the present embodiment, following gas turbine burner can be realized, even if the space around fuel nozzle is narrow
Narrow, the gas turbine burner also can easily carry out the engagement of fuel nozzle and fuel nozzle plate, realize that the precision of engagement carries
Height, so as to improve the stability of structure.
【Embodiment 4】
Next, the composition of the gas turbine burner 7 of embodiments of the invention 4 is sprayed using Fig. 7 partial enlarged drawing
The joint method of the fuel nozzle 15 and fuel nozzle plate 14 of burner 18 illustrates.
Fig. 7 partial enlargement illustrates the detailed feelings of the structure of the pulverizing jet 18 in the gas turbine burner 7 of embodiment 4
Condition, with the fuel nozzle 15 of the composition pulverizing jet 18 to gas turbine burner 7 of the embodiments of the invention 2 that show before
Upstream-side-end 40 is similar with the basic structure for the joint method that the upstream-side-end 41 of fuel nozzle plate 14 is engaged, therefore
The explanation to the two identical structure is omitted, different parts is illustrated below.
In the pulverizing jet 18 of the gas turbine burner 7 of the embodiment 4 shown in Fig. 7, using in the upper of fuel nozzle 15
The profile for the stage portion 50 that trip side end 40 is set has the structure of the big diameter of the external diameter in the downstream than fuel nozzle 15, and
Be formed as having than combustion in the internal diameter of the stage portion 51 of the upstream side of the fuel nozzle erection opening 44 of fuel nozzle plate 14 formation
Expect the structure of the big diameter of the internal diameter in the downstream of nozzle erection opening 44, thus, the big footpath set on fuel nozzle 15
The lower surface of the stage portion 50 abuts with the lower surface of the stage portion 51 in the big footpath set in fuel nozzle erection opening 44,
So as to prevent fuel nozzle 15, from fuel nozzle erection opening 44, downstream side comes off.
By using above-mentioned structure, even if upstream-side-end 40 and the upstream of fuel nozzle plate 14 in fuel nozzle 15
Damage is produced at the junction surface 45 of side end 41 in the case of breakage, is formed as the stage portion 50 in big footpath on fuel nozzle 15
Lower surface also with being formed as the step in big footpath in the upstream side for the fuel nozzle erection opening 44 for being arranged at fuel nozzle plate 14
The lower surface in portion 51 abuts, and so as to prevent the movement of the fuel nozzle 15, therefore prevents fuel nozzle 15 from fuel nozzle plate
Downstream side comes off and causes the miscellaneous part of gas turbine burner to damage 14 fuel nozzle erection opening 44.
Also, fuel nozzle 15 is in the same manner as the shape of the fuel nozzle 15 described in embodiment 3, in fuel nozzle 15 from passing through
At the fuel nozzle erection opening 44 worn fuel nozzle plate 14 and the formed part that downstream side protrudes, outside the fuel nozzle 15
Shape is formed as with the profile decrescence shape portion 60 from root towards end of downstream side 30 and shape that external diameter tapers into.
In the pulverizing jet 18 of the gas turbine burner 7 of embodiment 4, due to from the fuel for being formed at fuel nozzle plate 14
Downstream the profile for the fuel nozzle 15 that side protrudes is formed as having from root towards end of downstream side 30 nozzle erection opening 44
And the profile for the shape that external diameter tapers into decrescence shape portion 60, therefore it is corresponding to the amount that the external diameter of fuel nozzle 15 tapers into
Ground, make the lightweight of fuel nozzle 15, as a result, can reduce along with combustion vibration and act on to the upper of fuel nozzle 15
The load at the junction surface 45 that trip side end 40 is engaged with the upstream-side-end 41 of fuel nozzle plate 14.
, can be while intensity be maintained in the pulverizing jet 18 of the gas turbine burner 7 of the embodiment 4 shown in Fig. 7
Make the lightweight of fuel nozzle 15, acted on so as to reduce along with combustion vibration to fuel nozzle 15 and fuel nozzle plate
The load at 14 junction surfaces 45 engaged.
According to the present embodiment, following gas turbine burner can be realized, even if the space around fuel nozzle is narrow
Narrow, the gas turbine burner also can easily carry out the engagement of fuel nozzle and fuel nozzle plate, realize that the precision of engagement carries
Height, so as to improve the stability of structure.
【Embodiment 5】
Next, the composition of the gas turbine burner 7 of embodiments of the invention 5 is sprayed using Fig. 8 partial enlarged drawing
The joint method of the fuel nozzle 15 and fuel nozzle plate 14 of burner 18 illustrates.
Fig. 8 partial enlargement illustrates the detailed feelings of the structure of the pulverizing jet 18 in the gas turbine burner of embodiment 5
Condition, with the fuel nozzle 15 of the composition pulverizing jet 18 to gas turbine burner 7 of the embodiments of the invention 1 that show before
Upstream-side-end 40 is similar with the basic structure for the joint method that the upstream-side-end 41 of fuel nozzle plate 14 is engaged, therefore
The explanation to the two identical structure is omitted, different parts is illustrated below.
In the pulverizing jet 18 of the gas turbine burner 7 of the embodiment 5 shown in Fig. 8, in the gas turbine of the present embodiment
In the pulverizing jet 18 of burner 7, the fuel nozzle erection opening 44 formed through fuel nozzle plate 14 is formed as having therefrom
Way towards upstream side and tapering 70 that external diameter becomes larger internal face, in the tapering 70 of the fuel nozzle erection opening 44
Accordingly, the outside wall surface of the fuel nozzle 15 inserted to the fuel nozzle erection opening 44 is again formed as having the shape of wall
There is the outside wall surface in the tapering 72 that from midway towards upstream side and external diameter becomes larger.
Moreover, Fig. 8 shows following situation, i.e. to what is formed near the upstream-side-end 41 of fuel nozzle plate 14
The internal face in tapering 70 and the shape near the upstream-side-end 40 of the fuel nozzle 15 inserted to fuel nozzle erection opening 44
Into tapering 72 outside wall surface, implement melting welding from the upstream side of fuel nozzle plate 14 and form junction surface 45, fuel nozzle 15 is logical
Cross the junction surface 45 and engaged with fuel nozzle plate 14.
By be formed as with fuel nozzle 15 the external diameter that is formed about of upstream-side-end 40 than downstream part
The outside wall surface in the big tapering 72 of external diameter, and be formed as with the fuel near the upstream-side-end 41 as fuel nozzle plate 14
The internal face in the internal diameter formed in nozzle erection opening 44 the tapering 70 bigger than the internal diameter of downstream part, therefore sprayed located at fuel
The outside wall surface in the tapering 72 of mouth 15 abuts with the internal face in the tapering 70 located at fuel nozzle erection opening 44, so as to prevent
From fuel nozzle erection opening 44, downstream side comes off fuel nozzle 15.
By using above-mentioned structure, even if upstream-side-end 40 and the upstream of fuel nozzle plate 14 in fuel nozzle 15
At the junction surface 45 of side end 41 produce damage and in the case of breakage, the shape near the upstream-side-end 40 of fuel nozzle 15
Into tapering 72 outside wall surface also with the fuel nozzle erection opening 44 near the upstream-side-end 41 of fuel nozzle plate 14
The internal face in the tapering 70 of middle formation abuts, and so as to prevent the movement of the fuel nozzle 15, therefore prevents fuel nozzle 15 certainly
Downstream side comes off and causes the miscellaneous part of gas turbine burner to damage the fuel nozzle erection opening 44 of fuel nozzle plate 14.
In addition, by setting tapering 72 on fuel nozzle 15, so as to be formed relative on fuel nozzle plate 14
Fuel nozzle erection opening 44 tapering 70, carry out fuel nozzle 15 axially 52 and radial direction 71 positioning.
According to the present embodiment, following gas turbine burner can be realized, even if the space around fuel nozzle is narrow
Narrow, the gas turbine burner also can easily carry out the engagement of fuel nozzle and fuel nozzle plate, realize that the precision of engagement carries
Height, so as to improve the stability of structure.
【Embodiment 6】
Next, the composition of the gas turbine burner 7 of embodiments of the invention 6 is sprayed using Fig. 9 partial enlarged drawing
The joint method of the fuel nozzle 15 and fuel nozzle plate 14 of burner 18 illustrates.
Fig. 9 partial enlargement illustrates the detailed feelings of the structure of the pulverizing jet 18 in the gas turbine burner of embodiment 6
Condition, with the fuel nozzle 15 of the composition pulverizing jet 18 to gas turbine burner 7 of the embodiments of the invention 1 that show before with
The basic structure for the joint method that fuel nozzle plate 14 is engaged is similar, therefore omits the explanation to the two identical structure,
Different parts is illustrated below.
In the structure of the pulverizing jet 18 of the gas turbine burner 7 of the embodiment 6 shown in Fig. 9, in the combustion of the present embodiment
In the pulverizing jet 18 of gas-turbine burner 7, inserted to the fuel nozzle erection opening 44 formed through fuel nozzle plate 14
Fuel nozzle 15 upstream-side-end 40, set and be formed as the convex of big footpath compared with the external diameter in the downstream of the fuel nozzle 15
Edge 80.
Moreover, Fig. 9 shows following situation, i.e. the upstream-side-end 41 of fuel nozzle plate 14 is sprayed with fuel is arranged on
The flange part 80 in the big footpath of the upstream-side-end 40 of mouth 15, implement melting welding from the upstream side of fuel nozzle plate 14 and form junction surface
45, the lower surface of the upstream-side-end 40 of fuel nozzle 15 is by the junction surface 45 and the upstream-side-end with fuel nozzle plate 14
41 engagements.
In the present embodiment, by the way that the external diameter of the flange part 80 set in the upstream-side-end 40 of fuel nozzle 15 is formed
Internal diameter for the fuel nozzle erection opening 44 than fuel nozzle plate 14 is big, even if so as in the upstream side to fuel nozzle 15
In the case of damage being produced at the junction surface 45 that the lower surface in portion 40 is engaged with the upstream-side-end 41 of fuel nozzle plate 14,
Being also prevented from fuel nozzle 15, downstream side comes off and causes gas turbine to fire from the fuel nozzle erection opening 44 of fuel nozzle plate 14
The miscellaneous part damage of burner.
In addition, the fuel nozzle 15 of the flange part 80 as fuel nozzle 15 upstream-side-end 40 lower surface with
At the contact site 81 that the upstream-side-end 41 of fuel nozzle plate 14 contacts, the positioning of the axial direction 52 of fuel nozzle 15 can be carried out.
According to the present embodiment, following gas turbine burner can be realized, even if the space around fuel nozzle is narrow
Narrow, the gas turbine burner also can easily carry out the engagement of fuel nozzle and fuel nozzle plate, realize that the precision of engagement carries
Height, so as to improve the stability of structure.
【Embodiment 7】
Next, the composition of the gas turbine burner 7 of embodiments of the invention 7 is sprayed using Figure 10 partial enlarged drawing
The joint method of the fuel nozzle 15 and fuel nozzle plate 14 of burner 18 illustrates.
Figure 10 partial enlargement illustrates the detailed feelings of the structure of the pulverizing jet 18 in the gas turbine burner of embodiment 7
Condition, with the fuel nozzle 15 of the composition pulverizing jet 18 to gas turbine burner 7 of the embodiments of the invention 2 that show before
Upstream-side-end 40 is similar with the basic structure for the joint method that the upstream-side-end 41 of fuel nozzle plate 14 is engaged, therefore
The explanation to the two identical structure is omitted, different parts is illustrated below.
In the structure of the pulverizing jet 18 of the gas turbine burner 7 of the embodiment 7 shown in Figure 10, in the combustion of the present embodiment
In the pulverizing jet 18 of gas-turbine burner 7, throttling hole portion 90 is set in the midway of the fuel flow path of fuel nozzle 15, moreover, right
The upstream-side-end 40 of the stage portion 50 in the big footpath set on fuel nozzle 15 and it is being formed at fuel nozzle plate 14
The fuel nozzle plate 14 of the upstream side of the stage portion 51 as big footpath set in fuel nozzle erection opening 44
This both sides of upstream-side-end 41, implement melting welding from the upstream side of fuel nozzle plate 14 and form junction surface 45, so as to the combustion
Expect that both the upstream-side-end 40 of nozzle 15 and the upstream-side-end 41 of the fuel nozzle plate 14 are engaged.
In the case where being engaged by melting welding to fuel nozzle 15 with fuel nozzle plate 14, the ratio according to Fig. 4
Compared with the joint method of example, thermal deformation caused by melting welding can be produced and cause what is set in the midway of the fuel flow path of fuel nozzle 15
The internal diameter of throttling hole portion 90 changes, and in the structure of the pulverizing jet 18 in the gas turbine burner 7 of embodiment 7, melt
The direction of thermal deformation caused by weldering be not the radial direction 71 of fuel nozzle 15 but axially 52, therefore can will be in fuel nozzle
Deformation is suppressed to smaller caused by 15 throttling hole portion 90, so as to control fuel flow rate with high accuracy.
According to the present embodiment, following gas turbine burner can be realized, even if the space around fuel nozzle is narrow
Narrow, the gas turbine burner also can easily carry out the engagement of fuel nozzle and fuel nozzle plate, realize that the precision of engagement carries
Height, so as to improve the stability of structure.
Claims (8)
1. a kind of gas turbine burner, it possesses pulverizing jet, and the pulverizing jet includes：Multiple fuel nozzles, it supplies fuel；
Fuel nozzle plate, it structurally supports the end of the fuel nozzle, and plays from the fuel that upstream side flows into the combustion
Expect the effect of nozzle distribution；And air orifice plate, it has multiple airports of supply combustion air,
The gas turbine burner is characterised by,
Formed with the fuel nozzle erection opening for inserting fuel nozzle on fuel nozzle plate,
From the upstream side of fuel nozzle plate by melting welding to the fuel nozzle plate and the fuel to the insertion of fuel nozzle erection opening
Nozzle is engaged, also, described in inserted than the position downstream of the engagement into the fuel nozzle erection opening
Formed with gap between the inner surface of the outer surface of fuel nozzle and the fuel nozzle erection opening, moreover, from the engagement
To the end of downstream side of the fuel nozzle, the outer surface of the fuel nozzle does not contact with other components at position.
2. gas turbine burner according to claim 1, it is characterised in that
Into the fuel nozzle inserted located at the fuel nozzle erection opening of fuel nozzle plate, positioned at the fuel of fuel nozzle plate
The external diameter of the upstream part of the fuel nozzle of the inside of nozzle erection opening is formed as the downstream than the fuel nozzle
The external diameter of side part is big.
3. gas turbine burner according to claim 2, it is characterised in that
Located at fuel nozzle plate and for inserting in the fuel nozzle erection opening of fuel nozzle, the fuel nozzle installation is used
The internal diameter of the upstream part in hole is formed as bigger than the internal diameter of the downstream part of the fuel nozzle erection opening.
4. gas turbine burner according to claim 1, it is characterised in that
The upstream-side-end of fuel nozzle is provided with flange, the flange has than located at fuel nozzle plate and for inserting combustion
Expect the big external diameter of the internal diameter of the fuel nozzle erection opening of nozzle.
5. gas turbine burner according to claim 3, it is characterised in that
Located at fuel nozzle plate and for inserting in the fuel nozzle erection opening of fuel nozzle, first step portion is provided with simultaneously
And be provided with second step portion, the first step portion is configured to, the upstream part of the fuel nozzle erection opening it is interior
Footpath is bigger than the internal diameter of the downstream part of the fuel nozzle erection opening, and the second step portion is configured to, to fuel nozzle
External diameter of the external diameter of the upstream part of the fuel nozzle of erection opening insertion than the downstream part of the fuel nozzle
Greatly,
The second step portion of the fuel nozzle abuts with the first step portion of the fuel nozzle erection opening.
6. gas turbine burner according to claim 3, it is characterised in that
The gas turbine burner is provided with the first tapering and is provided with the second tapering, and first tapering is formed as, shape
Into the upstream part of the fuel nozzle erection opening in fuel nozzle plate internal diameter than the fuel nozzle erection opening
Downstream part internal diameter it is big, second tapering is formed as, to fuel nozzle erection opening insert the fuel nozzle
Upstream part external diameter it is bigger than the external diameter of the downstream part of the fuel nozzle,
The outer surface in the second tapering of the fuel nozzle abuts with the first tapering of the fuel nozzle erection opening.
7. gas turbine burner according to any one of claim 1 to 6, it is characterised in that
Be formed as court from the external diameter of the fuel nozzle erection opening of the fuel nozzle plate downstream part for the fuel nozzle that side protrudes
Turn into path to the end of downstream side of the fuel nozzle.
8. gas turbine burner according to any one of claim 1 to 6, it is characterised in that
Possesses the throttle orifice of constriction stream in the fuel flow path of inside for being formed at fuel nozzle.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2014-157350 | 2014-08-01 | ||
| JP2014157350A JP6301774B2 (en) | 2014-08-01 | 2014-08-01 | Gas turbine combustor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105318355A CN105318355A (en) | 2016-02-10 |
| CN105318355B true CN105318355B (en) | 2018-03-16 |
Family
ID=53773318
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510455129.6A Active CN105318355B (en) | 2014-08-01 | 2015-07-29 | Gas turbine burner |
Country Status (4)
| Country | Link |
|---|---|
| US (1) | US20160033136A1 (en) |
| EP (1) | EP2980483B1 (en) |
| JP (1) | JP6301774B2 (en) |
| CN (1) | CN105318355B (en) |
Families Citing this family (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP6423760B2 (en) * | 2015-06-24 | 2018-11-14 | 三菱日立パワーシステムズ株式会社 | Fuel nozzle structure of gas turbine combustor |
| JP6633982B2 (en) * | 2016-07-01 | 2020-01-22 | 三菱日立パワーシステムズ株式会社 | Gas turbine combustor and method for manufacturing fuel nozzle of gas turbine combustor |
| JP6863718B2 (en) * | 2016-11-21 | 2021-04-21 | 三菱パワー株式会社 | Gas turbine combustor |
| FR3059047B1 (en) * | 2016-11-21 | 2020-08-28 | Safran Helicopter Engines | COMBUSTION CHAMBER INJECTOR FOR A TURBOMACHINE AND ITS MANUFACTURING PROCESS |
| US10920673B2 (en) * | 2017-03-16 | 2021-02-16 | General Electric Company | Gas turbine with extraction-air conditioner |
| CN107023830B (en) * | 2017-05-26 | 2023-11-07 | 泉州市明燃厨房设备有限公司 | Burner nozzle base |
| CN107477611B (en) * | 2017-07-20 | 2019-08-09 | 中国科学院工程热物理研究所 | Burner |
| KR102049042B1 (en) * | 2017-10-27 | 2019-11-26 | 두산중공업 주식회사 | Fuel nozzle assembly, combustor and gas turbine having the same |
| JP7287811B2 (en) * | 2019-03-25 | 2023-06-06 | 三菱重工業株式会社 | Combustor and gas turbine |
| CN111237087B (en) * | 2020-01-19 | 2024-03-22 | 西北工业大学 | Micro-pore plate active and passive composite cooling structure for aerospace power and cooling method |
| JP7257350B2 (en) * | 2020-03-16 | 2023-04-13 | 三菱重工業株式会社 | gas turbine combustor |
| JP2021162184A (en) * | 2020-03-31 | 2021-10-11 | 三菱パワー株式会社 | Gas turbine combustor and method for manufacturing fuel nozzle |
| JP2023131352A (en) * | 2022-03-09 | 2023-09-22 | 三菱重工業株式会社 | Burner, and gas turbine |
| JP2024141648A (en) * | 2023-03-29 | 2024-10-10 | 三菱重工業株式会社 | Burner assembly, gas turbine combustor and gas turbine |
Family Cites Families (24)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3975141A (en) * | 1974-06-25 | 1976-08-17 | The United States Of America As Represented By The Secretary Of The Army | Combustion liner swirler |
| JPS5469537A (en) * | 1977-11-15 | 1979-06-04 | Hitachi Zosen Corp | Joining method for tube and tube plate in heat exchanger or the like |
| JPS5496537A (en) * | 1978-01-17 | 1979-07-31 | Nissan Motor Co Ltd | Coating method |
| JPS5671595A (en) * | 1979-11-19 | 1981-06-15 | Toshiba Corp | Welding method for tube and tube plate in heat exchanger |
| US5575153A (en) * | 1993-04-07 | 1996-11-19 | Hitachi, Ltd. | Stabilizer for gas turbine combustors and gas turbine combustor equipped with the stabilizer |
| US7360363B2 (en) * | 2001-07-10 | 2008-04-22 | Mitsubishi Heavy Industries, Ltd. | Premixing nozzle, combustor, and gas turbine |
| US6813889B2 (en) * | 2001-08-29 | 2004-11-09 | Hitachi, Ltd. | Gas turbine combustor and operating method thereof |
| US6857271B2 (en) * | 2002-12-16 | 2005-02-22 | Power Systems Mfg., Llc | Secondary fuel nozzle with readily customizable pilot fuel flow rate |
| US8122721B2 (en) * | 2006-01-04 | 2012-02-28 | General Electric Company | Combustion turbine engine and methods of assembly |
| JP2009014297A (en) * | 2007-07-06 | 2009-01-22 | Hitachi Ltd | Gas turbine combustor |
| JP4906689B2 (en) * | 2007-11-29 | 2012-03-28 | 株式会社日立製作所 | Burner, combustion device, and method for modifying combustion device |
| US8061142B2 (en) * | 2008-04-11 | 2011-11-22 | General Electric Company | Mixer for a combustor |
| US8230687B2 (en) * | 2008-09-02 | 2012-07-31 | General Electric Company | Multi-tube arrangement for combustor and method of making the multi-tube arrangement |
| US20100071377A1 (en) * | 2008-09-19 | 2010-03-25 | Fox Timothy A | Combustor Apparatus for Use in a Gas Turbine Engine |
| EP2189720A1 (en) * | 2008-11-21 | 2010-05-26 | Siemens Aktiengesellschaft | Burner assembly |
| JP2011058775A (en) * | 2009-09-14 | 2011-03-24 | Hitachi Ltd | Gas turbine combustor |
| JP5470662B2 (en) * | 2011-01-27 | 2014-04-16 | 株式会社日立製作所 | Gas turbine combustor |
| JP5393745B2 (en) * | 2011-09-05 | 2014-01-22 | 川崎重工業株式会社 | Gas turbine combustor |
| JP5630424B2 (en) * | 2011-11-21 | 2014-11-26 | 三菱日立パワーシステムズ株式会社 | Gas turbine combustor |
| US9296038B2 (en) * | 2011-12-29 | 2016-03-29 | Solar Turbines Incorporated | Method and apparatus for swaged liquid injector spoke |
| US9267690B2 (en) * | 2012-05-29 | 2016-02-23 | General Electric Company | Turbomachine combustor nozzle including a monolithic nozzle component and method of forming the same |
| JP5926635B2 (en) * | 2012-07-04 | 2016-05-25 | 三菱日立パワーシステムズ株式会社 | Gas turbine combustor |
| JP5908361B2 (en) * | 2012-07-24 | 2016-04-26 | 三菱日立パワーシステムズ株式会社 | Gas turbine combustor |
| DE102012216080A1 (en) * | 2012-08-17 | 2014-02-20 | Dürr Systems GmbH | burner |
-
2014
- 2014-08-01 JP JP2014157350A patent/JP6301774B2/en active Active
-
2015
- 2015-07-29 CN CN201510455129.6A patent/CN105318355B/en active Active
- 2015-07-30 US US14/813,987 patent/US20160033136A1/en not_active Abandoned
- 2015-07-31 EP EP15179363.5A patent/EP2980483B1/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN105318355A (en) | 2016-02-10 |
| JP6301774B2 (en) | 2018-03-28 |
| JP2016035336A (en) | 2016-03-17 |
| EP2980483B1 (en) | 2018-09-19 |
| US20160033136A1 (en) | 2016-02-04 |
| EP2980483A1 (en) | 2016-02-03 |
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Address after: Kanagawa Prefecture, Japan Patentee after: Mitsubishi Power Co., Ltd Address before: Kanagawa Prefecture, Japan Patentee before: MITSUBISHI HITACHI POWER SYSTEMS, Ltd. |