CN105318355A - Gas turbine combustor - Google Patents
Gas turbine combustor Download PDFInfo
- Publication number
- CN105318355A CN105318355A CN201510455129.6A CN201510455129A CN105318355A CN 105318355 A CN105318355 A CN 105318355A CN 201510455129 A CN201510455129 A CN 201510455129A CN 105318355 A CN105318355 A CN 105318355A
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- CN
- China
- Prior art keywords
- fuel nozzle
- gas turbine
- turbine burner
- erection opening
- nozzle plate
- 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 invention provides a gas turbine combustor which can easily perform welding of fuel nozzles and a fuel nozzle plate and realize improvement of precision of welding of the fuel nozzles and the fuel nozzle plate even if the space around the fuel nozzles is narrow, thereby improving structural stability. The gas turbine combustor comprises a burner (18) including: a plurality of fuel nozzles (15) to supply a fuel (5); a fuel nozzle plate (14) to supports end portions of the fuel nozzles structurally and being configured to distribute the fuel flowing from an upstream side to the fuel nozzles; and a swirler (13) including a plurality of air holes (21) to supply combustion air, wherein the fuel nozzle plate is provided with a fuel nozzle receiving hole to receive the fuel nozzle, and the fuel nozzle plate and the fuel nozzle inserted in the fuel nozzle receiving hole are connected to each other from an upstream side of the fuel nozzle plate by welding.
Description
Technical field
The present invention relates to a kind of gas turbine burner, particularly relate to a kind of gas turbine burner possessing the fuel nozzle of burner oil.
Background technology
In gas turbine burner, to reduce for the purpose of the load that waste gas applies environment, the NOx discharged when operating to gas turbine burner is set with strict environmental criteria.
The discharge rate of NOx increases along with the high temperature of flame temperature, thus needs suppression in gas turbine burner be formed locally the flame of high temperature and realize burning equably.
In order to burn uniformly in gas turbine burner, the dispersiveness improving fuel is effective, such as, in the technology of the gas turbine burner recorded in the Japanese Unexamined Patent Publication 2013-108667 publication of known case, by the circumference of the air orifice plate at gas turbine burner and radial direction arrange multiple fuel nozzle respectively, thus improve the dispersiveness of fuel.
In addition, in the gas turbine burner recorded in the Japanese Unexamined Patent Publication 2013-053814 publication of known case, by being located at the guide's pulverizing jet giving mixed type of head of the combustion barrel forming combustion chamber and the main jet burner of giving mixed type configured in its periphery, thus realizing air and the giving hybridization fully of fuel and realize low NOxization.
At first technical literature
Patent document
Patent document 1: Japanese Unexamined Patent Publication 2013-108667 publication
Patent document 2: Japanese Unexamined Patent Publication 2013-053814 publication
In the gas turbine burner of the technology described in patent document 1, if increase the radical of fuel nozzle for the purpose of the dispersiveness improving fuel, then there is the problem that fuel nozzle distance each other or the distance between fuel nozzle and neighbouring wall shorten.
And, if fuel nozzle distance each other or the distance between fuel nozzle and neighbouring wall shorten, then the space of the surrounding of fuel nozzle becomes narrow, in the gas turbine burner of the technology described in patent document 2, if engage the end of this fuel nozzle from downstream relative to the fuel nozzle plate of structurally supporting fuel nozzle, then there is the problem can not guaranteed for the sufficient space engaged.
Summary of the invention
Invent problem to be solved
The object of the present invention is to provide a kind of following gas turbine burner, even if the narrow space of the surrounding of fuel nozzle, this gas turbine burner also easily can carry out the joint of fuel nozzle and fuel nozzle plate, realize the raising to the precision that fuel nozzle engages with fuel nozzle plate, thus improve the stability of structure.
For solving the scheme of problem
Gas turbine burner of the present invention possesses pulverizing jet, and described pulverizing jet comprises: multiple fuel nozzle, and it supplies fuel; Fuel nozzle plate, it structurally supports the end of described fuel nozzle, and plays the effect distributed to this fuel nozzle by the fuel flowed into from upstream side; And air orifice plate, it has multiple airports of supply combustion air, described gas turbine burner is configured to, fuel nozzle plate being formed the fuel nozzle erection opening for inserting fuel nozzle, from the upstream side of fuel nozzle plate, this fuel nozzle plate being engaged with the fuel nozzle inserted to fuel nozzle erection opening.
Invention effect
According to invention, following gas turbine burner can be realized, even if the narrow space of the surrounding of fuel nozzle, this gas turbine burner also easily can carry out the joint of fuel nozzle and fuel nozzle plate, realize the raising to the precision that fuel nozzle engages with fuel nozzle plate, thus improve the stability of structure.
Accompanying drawing explanation
Fig. 1 is the sectional view of the gas turbine burner representing fuel in the gas turbine burner of embodiments of the invention 1 and the flowing of air and the summary of combustion process.
Fig. 2 is the component parts partial sectional view in the pulverizing jet portion represented in the gas turbine burner of the embodiments of the invention 1 shown in Fig. 1.
Fig. 3 is the partial sectional view of the joint method representing fuel nozzle in the gas turbine burner of the embodiments of the invention 1 shown in Fig. 1 and fuel nozzle plate.
Fig. 4 is the fuel nozzle in formation pulverizing jet portion of the gas turbine burner representing comparative example and the partial sectional view of the joint method of fuel nozzle plate.
Fig. 5 is the partial sectional view of the joint method representing fuel nozzle in the gas turbine burner of embodiments of the invention 2 and fuel nozzle plate.
Fig. 6 is the partial sectional view of the joint method representing fuel nozzle in the gas turbine burner of embodiments of the invention 3 and fuel nozzle plate.
Fig. 7 is the partial sectional view of the joint method representing fuel nozzle in the gas turbine burner of embodiments of the invention 4 and fuel nozzle plate.
Fig. 8 is the partial sectional view of the joint method representing fuel nozzle in the gas turbine burner of embodiments of the invention 5 and fuel nozzle plate.
Fig. 9 is the partial sectional view of the joint method representing fuel nozzle in the gas turbine burner of embodiments of the invention 6 and fuel nozzle plate.
Figure 10 is the partial sectional view of the joint method representing fuel nozzle in the gas turbine burner of embodiments of the invention 7 and fuel nozzle plate.
Description of reference numerals:
1: gas-turbine plant, 2: air, 3: compressor, 4: compressed air, 5: fuel, 6: burning gases, 7: gas turbine burner, 8: gas turbine, 9: generator, 10: end cap, 11: front side urceolus, 12: rear side urceolus, 13: air orifice plate, 14: fuel nozzle plate, 15: fuel nozzle, 16: lining, 17: the stream between rear side urceolus and lining, 18: pulverizing jet, 19: for the cooling-air cooled, 20: fuel feed pipe, 21: the airport of air orifice plate, 22: fuel and compressed-air actuated gaseous mixture, 23: combustion chamber, 24: flame, 30: the end of downstream side of fuel nozzle, 40: the upstream-side-end of fuel nozzle, 40b: the side near the upstream side of fuel nozzle, 41: the upstream-side-end of fuel nozzle plate, 41b: the end of downstream side of fuel nozzle plate, 43: the space around fuel nozzle, 44: fuel nozzle erection opening, 42, 45: junction surface, 50: the stage portion of fuel nozzle, 51: the stage portion of fuel nozzle erection opening, 52: the axis of fuel nozzle, 60: profile is shape portion decrescence, 70, 71: tapering, 71: the radial direction of fuel nozzle, 80: the flange part of the upstream-side-end of fuel nozzle, 81: the contact site between the flange part of fuel nozzle and fuel nozzle plate, 90: throttle orifice portion.
Detailed description of the invention
Below, the embodiment of accompanying drawing to gas turbine burner of the present invention is utilized to be described.
[embodiment 1]
The structure of gas-turbine plant of Fig. 1 to the gas turbine burner applying embodiments of the invention 1 is utilized to be described.
In the gas-turbine plant 1 of the gas turbine burner of the embodiment 1 applied shown in Fig. 1, gas-turbine plant 1 comprises: compressor 3, and it is from air introduction air 2 and compress; Gas turbine burner 7, it makes the compressed air 4 in compressor 3 after compression and fuel 5 burn, thus generates the burning gases 6 of HTHP; Turbine 8, it is driven by the burning gases 6 produced by this gas turbine burner 7, obtains the energy of burning gases 6 as rotary power; And generator 9, it uses the rotary power of turbine 8 to generate electricity.
The rear side urceolus 12 of longer cylindrical shape that described gas turbine burner 7 possesses the end cap 10 arranged in the end of gas turbine burner 7, the front side urceolus 11 being installed on the cylindrical shape of end cap 10 and installs at the rear side of front side urceolus 11.
The inner side of described front side urceolus 11 and rear side urceolus 12 is provided with the discoid air orifice plate 13 defining multiple airport 21, the upstream side of this air orifice plate 13 is provided with fuel nozzle plate 14, this fuel nozzle plate 14 is provided with the multiple fuel nozzles 15 sprayed towards the airport 21 formed on air orifice plate 13 by fuel, be provided with the lining 16 of longer cylindrical shape in the downstream of this air orifice plate 13, this lining 16 forms the combustion chamber 23 making fuel and air mix combining combustion within it.
And the circular stream 17 of compressed air 4 by being formed between rear side urceolus 12 and lining 16 after being compressed by described compressor 3, flows into the pulverizing jet 18 formed in gas turbine burner 7.
This pulverizing jet 18 comprises: multiple fuel nozzle 15, its burner oil; Fuel nozzle plate 14, the end of its structurally supporting fuel nozzle 15, and play the effect distributed to described fuel nozzle 15 by the fuel flowed into from upstream side; And air orifice plate 13, it is formed with multiple airports 21 of the air of supply burning in the downstream of the fuel nozzle plate 14 possessing described multiple fuel nozzle 15.
In addition, a part for compressed air 4 flows into, as the cooling-air 19 for cooling bushing 16 from the multiple Cooling Holes being located at described lining 16 in lining 16.
The fuel 5 supplied to gas turbine burner 7 flows into fuel nozzle plate 14 by being located at the fuel feed pipe 20 of end cap 10, is sprayed from fuel nozzle plate 14 by each fuel nozzle 15 towards the multiple airports 21 formed at air orifice plate 13.
Then, at the fuel nozzle side entrance place of the airport 21 of air orifice plate 13, spray next fuel 5 from fuel nozzle 15 and be mixed to gaseous mixture 22 by the compressed air 4 that the circular stream 17 formed between rear side urceolus 12 and lining 16 carries out supplying, this fuel 5 sprays towards combustion chamber 23 with the gaseous mixture 22 of compressed air 4 and burns, thus forms the flame 24 of high temperature.
The gas turbine burner 7 of the present embodiment can not only use natural gas, and the fuel such as oven gas, refinery flares, coal gasification gas also can be used as fuel 5.
Next, the structure of the pulverizing jet 18 of the gas turbine burner 7 of embodiment 1 shown in Figure 2.As shown in Figure 2, the pulverizing jet 18 arranged in the gas turbine burner 7 of the present embodiment comprises air orifice plate 13, fuel nozzle plate 14 and fuel nozzle 15.
The upstream-side-end 40 of the fuel nozzle 15 of burner oil engages with fuel nozzle plate 14, and its junction surface is sealed to make fuel 5 to 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, and compressed air 4 can freely flow into relative to the airport 21 formed on air orifice plate 13.
And the upstream-side-end 40 of fuel nozzle 15 utilizes bolted, melting welding, soldering etc. usually with the joint method of fuel nozzle plate 14.
Next, the partial enlarged drawing of Fig. 3 and Fig. 4 is utilized to be described the fuel nozzle 15 of the formation pulverizing jet 18 of the gas turbine burner 7 of embodiment 1 and the joint method of fuel nozzle plate 14.
The partial enlargement of Fig. 3 illustrates joint method when being engaged with fuel nozzle plate 14 by the fuel nozzle 15 of melting welding to the formation pulverizing jet 18 of the gas turbine burner 7 of the present embodiment.
But in the present embodiment, the joint method that the fuel nozzle 15 about the formation pulverizing jet 18 to gas turbine burner 7 engages with fuel nozzle plate 14, is not limited to the joint utilizing melting welding, also can utilize the joint method beyond melting welding.
As shown in the partial enlarged drawing of Fig. 3, in the fuel nozzle 15 of the formation pulverizing jet 18 of the gas turbine burner 7 of the present embodiment and the joint method of fuel nozzle plate 14, fuel nozzle plate 14 runs through the fuel nozzle erection opening 44 formed for inserting fuel nozzle 15, the upstream-side-end 40 of fuel nozzle 15 that fuel nozzle erection opening 44 described in subtend inserts and these both sides of upstream-side-end 41 of fuel nozzle plate 14, implement melting welding relative to fuel nozzle plate 14 from upstream side and form junction surface 45, thus the upstream-side-end 40 of fuel nozzle 15 is engaged with both upstream-side-end 41 of fuel nozzle plate 14.
Fig. 4 illustrates the joint method to the comparative example that the fuel nozzle 15 of the formation pulverizing jet 18 of gas turbine burner 7 engages with fuel nozzle plate 14, in the joint method of the comparative example shown in this Fig. 4, to these both sides of end of downstream side 41b of the side 40b near the upstream side of fuel nozzle 15 and fuel nozzle plate 14, engage from formation junction surface, downstream 42 relative to fuel nozzle plate 14.
But, in the joint method to the comparative example that fuel nozzle 15 engages with fuel nozzle plate 14 shown in Fig. 4, when being closely equipped with multiple fuel nozzle 15 in the downstream of fuel nozzle plate 14 and making the space 43 around fuel nozzle 15 narrow, there is this problem of enough working spaces can not guaranteed in the downstream of fuel nozzle plate 14 for carrying out the joining process engaging fuel nozzle 15 and fuel nozzle plate 14.
In addition, in the joint method to the comparative example that fuel nozzle 15 engages with fuel nozzle plate 14 shown in Fig. 4, structure as shown in Figure 4 can be clear and definite, there is not the working space of the joint for carrying out fuel nozzle 15 and fuel nozzle plate 14 at the upstream side of fuel nozzle plate 14.
So, in the gas turbine burner 7 of the present embodiment shown in Fig. 3, in the fuel nozzle 15 of the formation pulverizing jet 18 of gas turbine burner 7 and the joint method of fuel nozzle plate 14, even if when being closely equipped with multiple fuel nozzle 15, according to the joint method of the fuel nozzle 15 in the gas turbine burner of the present embodiment with fuel nozzle plate 14, fuel nozzle plate 14 runs through the fuel nozzle erection opening 44 formed for inserting fuel nozzle 15, and arrange as the downstream to fuel nozzle plate 14 is outstanding to the fuel nozzle 15 that this fuel nozzle erection opening 44 inserts.
And, the upstream-side-end 40 of described fuel nozzle 15 that this fuel nozzle erection opening 44 of subtend inserts and these both sides of upstream-side-end 41 of described fuel nozzle plate 14, implement melting welding relative to fuel nozzle plate 14 from upstream side and form junction surface 45, thus the upstream-side-end 40 of fuel nozzle 15 is engaged with both upstream-side-end 41 of fuel nozzle plate 14.
Namely, in the gas turbine burner 7 of the present embodiment, adopt the structure not being equipped with described fuel nozzle 15 at the upstream side of fuel nozzle plate 14, therefore ensure that the enough broad working space needed for the joint implementing fuel nozzle 15 and fuel nozzle plate 14 at the upstream side of fuel nozzle plate 14, thus fuel nozzle 15 improves with the joining accuracy of fuel nozzle plate 14, and improve along with this joining accuracy, fuel nozzle 15 improves with the structural reliability at the junction surface of fuel nozzle plate 14.
In addition, in the fuel nozzle 15 of the formation pulverizing jet 18 of the gas turbine burner 7 of the present embodiment and the joint method of fuel nozzle plate 14, combustion vibration is produced when combustion chamber 23 combustion at gas turbine burner 7 of the gaseous mixture 22 of fuel 5 and compressed air 4, when causing fuel nozzle 15 to vibrate to the direction rectangular with the central shaft of this fuel nozzle 15, the side of described fuel nozzle 15 contacts with the inner surface of the fuel nozzle erection opening 44 formed to insert fuel nozzle 15 in fuel nozzle plate 14 and suppresses to vibrate, thus the load acted on to the junction surface 45 formed to carry out melting welding to the two can be reduced.
And, by designing small gap between the inner surface of the fuel nozzle erection opening 44 of the side of fuel nozzle 15 and fuel nozzle plate 14, thus between the inner surface of the fuel nozzle erection opening 44 of the side of fuel nozzle 15 and fuel nozzle plate 14, frictional force can be produced along with the contact of the two, therefore can obtain by frictional force the effect making the vibration attenuation acting on fuel nozzle 15.
According to the present embodiment, can realize following gas turbine burner, even if the narrow space of the surrounding of fuel nozzle, this gas turbine burner also easily can carry out the joint of fuel nozzle and fuel nozzle plate, the precision realizing engaging improves, thus improves the stability of structure.
[embodiment 2]
Next, the partial enlarged drawing of Fig. 5 is utilized to be described the fuel nozzle 15 of the formation pulverizing jet 18 of the gas turbine burner 7 of embodiments of the invention 2 and the joint method of fuel nozzle plate 14.
The partial enlargement of Fig. 5 illustrates the details of the structure of the pulverizing jet 18 arranged on the gas turbine burner 7 of embodiment 2, the basic structure of the joint method engaged with fuel nozzle plate 14 with the fuel nozzle 15 of the formation pulverizing jet 18 to gas turbine burner 7 of the embodiments of the invention 1 illustrated before is similar, therefore omit the explanation to the two identical structure, below different parts is described.
The partial enlargement of Fig. 5 illustrates in the pulverizing jet 18 of the gas turbine burner 7 of embodiment 2, the situation that fuel nozzle 15 is engaged with the upstream-side-end 41 of fuel nozzle plate 14 by its upstream-side-end 40.
In the pulverizing jet 18 of the gas turbine burner 7 of the embodiment 2 shown in Fig. 5, the upstream side of the fuel nozzle erection opening 44 formed running through fuel nozzle plate 14 is provided with stage portion 51, this stage portion 51 is formed as large footpath compared with the diameter in the hole in the downstream of fuel nozzle erection opening 44, and the upstream-side-end 40 of the fuel nozzle 15 inserted to the inside of described fuel nozzle erection opening 44 is provided with stage portion 50, this stage portion 50 is formed as large footpath compared with the diameter of the part in the downstream of fuel nozzle 15, the stage portion 50 arranged in the upstream-side-end 40 of this fuel nozzle 15 abuts with the stage portion 51 that the upstream side at fuel nozzle erection opening 44 is arranged.
And, to the upstream-side-end 40 of described stage portion 50 in large footpath and these both sides of upstream-side-end 41 of the described fuel nozzle plate 14 right with the upstream side of described stage portion 51 in the large footpath being formed at fuel nozzle erection opening 44 of being located at fuel nozzle 15, implement melting welding relative to fuel nozzle plate 14 from upstream side and form junction surface 45, thus the upstream-side-end 40 of fuel nozzle 15 is engaged with both 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, the external diameter of the stage portion 50 arranged in the upstream-side-end 40 of fuel nozzle 15 is adopted to have the structure of the diameter larger than the external diameter in the downstream of fuel nozzle 15, and adopt the internal diameter of the stage portion 51 formed at the upstream side of the fuel nozzle erection opening 44 of fuel nozzle plate 14 to have the structure of the diameter larger than the internal diameter in the downstream of fuel nozzle erection opening 44, thus, the lower surface of the described stage portion 50 in the large footpath that fuel nozzle 15 is arranged abuts with the lower surface of the stage portion 51 in the large footpath arranged in fuel nozzle erection opening 44, thus stop fuel nozzle 15 to come off to downstream from fuel nozzle erection opening 44.
By adopting above-mentioned structure, even if when fuel nozzle 15 upstream-side-end 40 with run through fuel nozzle plate 14 and junction surface 45 place of the upstream-side-end of fuel nozzle erection opening 44 that formed produce damage and breakage, the lower surface of the stage portion 50 in the large footpath that the upstream-side-end 40 of fuel nozzle 15 is arranged also abuts with the lower surface being formed at the stage portion 51 in the large footpath of fuel nozzle erection opening 44 arranged in fuel nozzle erection opening 44, thus stop the movement of described fuel nozzle 15, therefore prevent fuel nozzle 15 from coming off to downstream from the fuel nozzle erection opening 44 of fuel nozzle plate 14 and causing the miscellaneous part of gas turbine burner to damage.
In addition, described stage portion 50,51 also can carry out the location of axial 52 of fuel nozzle 15.
According to the present embodiment, can realize following gas turbine burner, even if the narrow space of the surrounding of fuel nozzle, this gas turbine burner also easily can carry out the joint of fuel nozzle and fuel nozzle plate, the precision realizing engaging improves, thus improves the stability of structure.
[embodiment 3]
Next, the partial enlarged drawing of Fig. 6 is utilized to be described the fuel nozzle 15 of the formation pulverizing jet 18 of the gas turbine burner 7 of embodiments of the invention 3 and the joint method of fuel nozzle plate 14.
The partial enlargement of Fig. 6 illustrates the details of the structure of the pulverizing jet 18 in the gas turbine burner of embodiment 3, the basic structure of the joint method engaged with the upstream-side-end 41 of fuel nozzle plate 14 with the upstream-side-end 40 of fuel nozzle 15 of the formation pulverizing jet 18 to gas turbine burner 7 of the embodiments of the invention 1 illustrated before is similar, therefore omit the explanation to the two identical structure, below different parts is described.
Fig. 6 illustrates 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, illustrate the through fuel nozzle plate 14 of subtend and formed fuel nozzle erection opening 44 insert the upstream-side-end 40 of fuel nozzle 15 and the upstream-side-end 41 of fuel nozzle plate 14, implement melting welding from the upstream side of fuel nozzle plate 14 and form junction surface 45, the situation that the upstream-side-end 40 of fuel nozzle 15 is passed through this junction surface 45 and engaged with the upstream-side-end 41 of fuel nozzle plate 14.
In the pulverizing jet 18 of the gas turbine burner 7 of embodiment 3, the external diameter of the part of the fuel nozzle 15 that the fuel nozzle erection opening 44 formed from through fuel nozzle plate 14 is outstanding to side, downstream is formed as to be had from the root profile that external diameter diminishes gradually towards end of downstream side 30 decrescence shape portion 60.
In the pulverizing jet 18 of the gas turbine burner 7 of embodiment 3, owing to being formed as that there is the profile decrescence shape portion 60 that external diameter diminishes gradually towards end of downstream side 30 from the external diameter of fuel nozzle erection opening 44 fuel nozzle 15 outstanding to side, downstream, therefore the amount diminished gradually with the external diameter of fuel nozzle 15 correspondingly, make fuel nozzle 15 lightweight, consequently, the load acted on along with combustion vibration the junction surface 45 that the upstream-side-end 40 of fuel nozzle 15 engages with the upstream-side-end 41 of fuel nozzle plate 14 can be reduced.
According to the present embodiment, can realize following gas turbine burner, even if the narrow space of the surrounding of fuel nozzle, this gas turbine burner also easily can carry out the joint of fuel nozzle and fuel nozzle plate, the precision realizing engaging improves, thus improves the stability of structure.
[embodiment 4]
Next, the partial enlarged drawing of Fig. 7 is utilized to be described the fuel nozzle 15 of the formation pulverizing jet 18 of the gas turbine burner 7 of embodiments of the invention 4 and the joint method of fuel nozzle plate 14.
The partial enlargement of Fig. 7 illustrates the details of the structure of the pulverizing jet 18 in the gas turbine burner 7 of embodiment 4, the basic structure of the joint method engaged with the upstream-side-end 41 of fuel nozzle plate 14 with the upstream-side-end 40 of fuel nozzle 15 of the formation pulverizing jet 18 to gas turbine burner 7 of the embodiments of the invention 2 illustrated before is similar, therefore omit the explanation to the two identical structure, below different parts is described.
In the pulverizing jet 18 of the gas turbine burner 7 of the embodiment 4 shown in Fig. 7, the profile of the stage portion 50 arranged in the upstream-side-end 40 of fuel nozzle 15 is adopted to have the structure of the diameter larger than the external diameter in the downstream of fuel nozzle 15, and the internal diameter being formed as the stage portion 51 formed at the upstream side of the fuel nozzle erection opening 44 of fuel nozzle plate 14 has the structure of the diameter larger than the internal diameter in the downstream of fuel nozzle erection opening 44, thus, the lower surface of the described stage portion 50 in the large footpath that fuel nozzle 15 is arranged abuts with the lower surface of the stage portion 51 in the large footpath arranged in fuel nozzle erection opening 44, thus stop fuel nozzle 15 to come off to downstream from fuel nozzle erection opening 44.
By adopting above-mentioned structure, even if when the upstream-side-end 40 of fuel nozzle 15 and junction surface 45 place of the upstream-side-end 41 of fuel nozzle plate 14 produce damage and breakage, the lower surface that the lower surface that fuel nozzle 15 is formed as the stage portion 50 in large footpath is also formed as the stage portion 51 in large footpath with the upstream side at the fuel nozzle erection opening 44 being arranged at fuel nozzle plate 14 abuts, thus stop the movement of described fuel nozzle 15, therefore prevent fuel nozzle 15 from coming off to downstream from the fuel nozzle erection opening 44 of fuel nozzle plate 14 and causing the miscellaneous part of gas turbine burner to damage.
And, fuel nozzle 15 is in the same manner as the shape of the fuel nozzle 15 described in embodiment 3, in fuel nozzle erection opening 44 part outstanding to side, downstream that fuel nozzle 15 is formed from running through fuel nozzle plate 14, the profile of this fuel nozzle 15 is formed as having the profile decrescence shape portion 60 from root shape that external diameter diminishes gradually towards end of downstream side 30.
In the pulverizing jet 18 of the gas turbine burner 7 of embodiment 4, owing to being formed as that there is the profile decrescence shape portion 60 from root shape that external diameter diminishes gradually towards end of downstream side 30 from the profile of the fuel nozzle erection opening 44 being formed at fuel nozzle plate 14 fuel nozzle 15 outstanding to side, downstream, therefore the amount diminished gradually with the external diameter of fuel nozzle 15 correspondingly, make fuel nozzle 15 lightweight, consequently, the load acted on along with combustion vibration the junction surface 45 that the upstream-side-end 40 of fuel nozzle 15 engages with the upstream-side-end 41 of fuel nozzle plate 14 can be reduced.
In the pulverizing jet 18 of the gas turbine burner 7 of the embodiment 4 shown in Fig. 7, fuel nozzle 15 lightweight can be made while maintenance intensity, thus the load acted on along with combustion vibration the junction surface 45 that fuel nozzle 15 engages with fuel nozzle plate 14 can be reduced.
According to the present embodiment, can realize following gas turbine burner, even if the narrow space of the surrounding of fuel nozzle, this gas turbine burner also easily can carry out the joint of fuel nozzle and fuel nozzle plate, the precision realizing engaging improves, thus improves the stability of structure.
[embodiment 5]
Next, the partial enlarged drawing of Fig. 8 is utilized to be described the fuel nozzle 15 of the formation pulverizing jet 18 of the gas turbine burner 7 of embodiments of the invention 5 and the joint method of fuel nozzle plate 14.
The partial enlargement of Fig. 8 illustrates the details of the structure of the pulverizing jet 18 in the gas turbine burner of embodiment 5, the basic structure of the joint method engaged with the upstream-side-end 41 of fuel nozzle plate 14 with the upstream-side-end 40 of fuel nozzle 15 of the formation pulverizing jet 18 to gas turbine burner 7 of the embodiments of the invention 1 illustrated before is similar, therefore omit the explanation to the two identical structure, below different parts is described.
In the pulverizing jet 18 of the gas turbine burner 7 of the embodiment 5 shown in Fig. 8, in the pulverizing jet 18 of the gas turbine burner 7 of the present embodiment, run through fuel nozzle plate 14 and the fuel nozzle erection opening 44 that formed is formed as having from midway that external diameter becomes the internal face in large tapering 70 gradually towards upstream side, with the shape of the internal face in the tapering 70 of this fuel nozzle erection opening 44 accordingly, outside wall surface to the fuel nozzle 15 of described fuel nozzle erection opening 44 insertion is also formed as to be had from towards upstream side, external diameter becomes the outside wall surface in large tapering 72 gradually halfway.
And, Fig. 8 shows following situation, namely, to the outside wall surface in tapering 72 of the internal face in the tapering 70 formed near the upstream-side-end 41 of fuel nozzle plate 14 and formation near the upstream-side-end 40 of the fuel nozzle 15 inserted to fuel nozzle erection opening 44, implement melting welding from the upstream side of fuel nozzle plate 14 and form junction surface 45, fuel nozzle 15 is engaged with fuel nozzle plate 14 by this junction surface 45.
By being formed as having the outside wall surface in the external diameter tapering 72 larger than the external diameter of downstream part formed near the upstream-side-end 40 of fuel nozzle 15, and be formed as that there is the internal face in the internal diameter becoming formation in the fuel nozzle erection opening 44 near the upstream-side-end 41 of fuel nozzle plate 14 tapering 70 larger than the internal diameter of downstream part, therefore the outside wall surface being located at the described tapering 72 of fuel nozzle 15 abuts with the internal face in the tapering 70 being located at fuel nozzle erection opening 44, thus stops fuel nozzle 15 to come off to downstream from fuel nozzle erection opening 44.
By adopting above-mentioned structure, even if when the upstream-side-end 40 of fuel nozzle 15 and junction surface 45 place of the upstream-side-end 41 of fuel nozzle plate 14 produce damage and breakage, the outside wall surface in the tapering 72 formed near the upstream-side-end 40 of fuel nozzle 15 also abuts with the internal face in the tapering 70 formed in the fuel nozzle erection opening 44 near the upstream-side-end 41 of fuel nozzle plate 14, thus stop the movement of described fuel nozzle 15, therefore preventing fuel nozzle 15 to come off to downstream from the fuel nozzle erection opening 44 of fuel nozzle plate 14 causes the miscellaneous part of gas turbine burner to damage.
In addition, by arranging tapering 72 on fuel nozzle 15, thus relative to the tapering 70 of the fuel nozzle erection opening 44 formed on fuel nozzle plate 14, axial 52 of fuel nozzle 15 and the location of radial direction 71 can be carried out.
According to the present embodiment, can realize following gas turbine burner, even if the narrow space of the surrounding of fuel nozzle, this gas turbine burner also easily can carry out the joint of fuel nozzle and fuel nozzle plate, the precision realizing engaging improves, thus improves the stability of structure.
[embodiment 6]
Next, the partial enlarged drawing of Fig. 9 is utilized to be described the fuel nozzle 15 of the formation pulverizing jet 18 of the gas turbine burner 7 of embodiments of the invention 6 and the joint method of fuel nozzle plate 14.
The partial enlargement of Fig. 9 illustrates the details of the structure of the pulverizing jet 18 in the gas turbine burner of embodiment 6, the basic structure of the joint method engaged with fuel nozzle plate 14 with the fuel nozzle 15 of the formation pulverizing jet 18 to gas turbine burner 7 of the embodiments of the invention 1 illustrated before is similar, therefore omit the explanation to the two identical structure, below different parts is described.
In the structure of the pulverizing jet 18 of the gas turbine burner 7 of the embodiment 6 shown in Fig. 9, in the pulverizing jet 18 of the gas turbine burner 7 of the present embodiment, in the upstream-side-end 40 of the fuel nozzle 15 that the fuel nozzle erection opening 44 formed to running through fuel nozzle plate 14 inserts, the flange part 80 being formed as large footpath compared with the external diameter in the downstream of this fuel nozzle 15 is set.
And, Fig. 9 shows following situation, namely, to the upstream-side-end 41 of fuel nozzle plate 14 and the flange part 80 in large footpath of upstream-side-end 40 being arranged on fuel nozzle 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 engaged with the upstream-side-end 41 of fuel nozzle plate 14 by this junction surface 45.
In the present embodiment, be formed as larger than the internal diameter of the fuel nozzle erection opening 44 of fuel nozzle plate 14 by the external diameter of the flange part 80 upstream-side-end 40 at fuel nozzle 15 arranged, even if thus when junction surface 45 place that the lower surface of the upstream-side-end 40 to fuel nozzle 15 engages with the upstream-side-end 41 of fuel nozzle plate 14 produce damage, also prevent fuel nozzle 15 to come off to downstream from the fuel nozzle erection opening 44 of fuel nozzle plate 14 and cause the miscellaneous part of gas turbine burner to damage.
In addition, at contact site 81 place that the lower surface of the upstream-side-end 40 of this fuel nozzle 15 of the flange part 80 as fuel nozzle 15 contacts with the upstream-side-end 41 of fuel nozzle plate 14, the location of axial 52 of fuel nozzle 15 can be carried out.
According to the present embodiment, can realize following gas turbine burner, even if the narrow space of the surrounding of fuel nozzle, this gas turbine burner also easily can carry out the joint of fuel nozzle and fuel nozzle plate, the precision realizing engaging improves, thus improves the stability of structure.
[embodiment 7]
Next, the partial enlarged drawing of Figure 10 is utilized to be described the fuel nozzle 15 of the formation pulverizing jet 18 of the gas turbine burner 7 of embodiments of the invention 7 and the joint method of fuel nozzle plate 14.
The partial enlargement of Figure 10 illustrates the details of the structure of the pulverizing jet 18 in the gas turbine burner of embodiment 7, the basic structure of the joint method engaged with the upstream-side-end 41 of fuel nozzle plate 14 with the upstream-side-end 40 of fuel nozzle 15 of the formation pulverizing jet 18 to gas turbine burner 7 of the embodiments of the invention 2 illustrated before is similar, therefore omit the explanation to the two identical structure, below different parts is described.
In the structure of the pulverizing jet 18 of the gas turbine burner 7 of the embodiment 7 shown in Figure 10, in the pulverizing jet 18 of the gas turbine burner 7 of the present embodiment, in the midway of the fuel flow path of fuel nozzle 15, throttle orifice portion 90 is set, and, to the upstream-side-end 40 of the described stage portion 50 in the large footpath arranged on fuel nozzle 15, with these both sides of upstream-side-end 41 becoming the described fuel nozzle plate 14 of the upstream side of the described stage portion 51 in large footpath arranged in the fuel nozzle erection opening 44 being formed at fuel nozzle plate 14, implement melting welding from the upstream side of fuel nozzle plate 14 and form junction surface 45, thus the upstream-side-end 40 of described fuel nozzle 15 is engaged with both upstream-side-end 41 of described fuel nozzle plate 14.
When being engaged with fuel nozzle plate 14 fuel nozzle 15 by melting welding, the joint method of the comparative example according to Fig. 4, thermal deformation that melting welding causes can be produced and the internal diameter in the throttle orifice portion 90 arranged in the midway of the fuel flow path of fuel nozzle 15 is changed, and in the structure of pulverizing jet 18 in the gas turbine burner 7 of embodiment 7, the direction of the thermal deformation that melting welding causes be not fuel nozzle 15 radial direction 71 but axially 52, therefore, it is possible to the distortion produced in the throttle orifice portion 90 at fuel nozzle 15 suppresses for less, thus fuel flow rate can be controlled with high accuracy.
According to the present embodiment, can realize following gas turbine burner, even if the narrow space of the surrounding of fuel nozzle, this gas turbine burner also easily can carry out the joint of fuel nozzle and fuel nozzle plate, the precision realizing engaging improves, thus improves the stability of structure.
Claims (9)
1. a gas turbine burner, it possesses pulverizing jet, and described pulverizing jet comprises: multiple fuel nozzle, and it supplies fuel; Fuel nozzle plate, it structurally supports the end of described fuel nozzle, and plays the effect distributed to this fuel nozzle by the fuel flowed into from upstream side; And air orifice plate, it has multiple airports of supply combustion air,
The feature of described gas turbine burner is,
Fuel nozzle plate is formed the fuel nozzle erection opening for inserting fuel nozzle,
This fuel nozzle plate is engaged with the fuel nozzle inserted to fuel nozzle erection opening from the upstream side of fuel nozzle plate by melting welding.
2. gas turbine burner according to claim 1, is characterized in that,
In the fuel nozzle inserted to the fuel nozzle erection opening being located at fuel nozzle plate, the external diameter being positioned at the upstream side part of the described fuel nozzle of the inside of the fuel nozzle erection opening of fuel nozzle plate is formed as larger than the external diameter of the downstream part of described fuel nozzle.
3. gas turbine burner according to claim 2, is characterized in that,
Be located at fuel nozzle plate and for inserting in the fuel nozzle erection opening of fuel nozzle, the internal diameter of the upstream side part of described fuel nozzle erection opening is formed as larger than the internal diameter of the downstream part of described fuel nozzle erection opening.
4. gas turbine burner according to claim 1, is characterized in that,
The upstream-side-end of fuel nozzle is provided with flange, and described flange has than being located at fuel nozzle plate and for the large external diameter of the internal diameter of the fuel nozzle erection opening inserting fuel nozzle.
5. gas turbine burner according to claim 3, is characterized in that,
Be located at fuel nozzle plate and for inserting in the fuel nozzle erection opening of fuel nozzle, be provided with first step portion and be provided with second step portion, described first step portion is configured to, the internal diameter of the upstream side part of described fuel nozzle erection opening is larger than the internal diameter of the downstream part of described fuel nozzle erection opening, described second step portion is configured to, external diameter to the upstream side part of the described fuel nozzle of fuel nozzle erection opening insertion is larger than the external diameter of the downstream part of described fuel nozzle
The second step portion of described fuel nozzle abuts with the first step portion of described fuel nozzle erection opening.
6. gas turbine burner according to claim 3, is characterized in that,
Described gas turbine burner is provided with the first tapering and is provided with the second tapering, described first tapering is formed as, the internal diameter being formed at the upstream side part of the described fuel nozzle erection opening of fuel nozzle plate is larger than the internal diameter of the downstream part of described fuel nozzle erection opening, described second tapering is formed as, external diameter to the upstream side part of the described fuel nozzle of fuel nozzle erection opening insertion is larger than the external diameter of the downstream part of described fuel nozzle
The outer surface in the second tapering of described fuel nozzle abuts with the first tapering of described fuel nozzle erection opening.
7. gas turbine burner according to any one of claim 1 to 6, is characterized in that,
Be formed at fuel nozzle plate and for being formed with gap between the inner surface of the fuel nozzle erection opening that inserts fuel nozzle and the outer surface of described fuel nozzle inserted to described fuel nozzle erection opening.
8. gas turbine burner according to any one of claim 1 to 6, is characterized in that,
Be formed as towards the end of downstream side of described fuel nozzle from the external diameter of the part of the fuel nozzle erection opening of the fuel nozzle plate fuel nozzle outstanding to side, downstream and become path.
9. gas turbine burner according to any one of claim 1 to 6, is characterized in that,
The throttle orifice of constriction stream is possessed in the fuel flow path of inside 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 true CN105318355A (en) | 2016-02-10 |
| CN105318355B 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) |
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| CN107023830A (en) * | 2017-05-26 | 2017-08-08 | 泉州市明燃厨房设备有限公司 | A kind of burner nozzle base |
| CN107477611A (en) * | 2017-07-20 | 2017-12-15 | 中国科学院工程热物理研究所 | Burner |
| CN107559880A (en) * | 2016-07-01 | 2018-01-09 | 三菱日立电力系统株式会社 | Fuel nozzle and its manufacture method, the gas turbine burner of gas turbine burner |
| CN113483356A (en) * | 2020-03-16 | 2021-10-08 | 三菱动力株式会社 | Gas turbine combustor |
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| JP7287811B2 (en) * | 2019-03-25 | 2023-06-06 | 三菱重工業株式会社 | Combustor and gas turbine |
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| 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 |
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Also Published As
| Publication number | Publication date |
|---|---|
| EP2980483B1 (en) | 2018-09-19 |
| US20160033136A1 (en) | 2016-02-04 |
| JP6301774B2 (en) | 2018-03-28 |
| EP2980483A1 (en) | 2016-02-03 |
| JP2016035336A (en) | 2016-03-17 |
| CN105318355B (en) | 2018-03-16 |
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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. |