JP3772021B2 - Pilot nozzle of gas turbine combustor - Google Patents

Description

[0001]
BACKGROUND OF THE INVENTION
The present invention relates to a pilot nozzle of a gas turbine combustor for igniting a gas turbine combustor.
[0002]
[Prior art]
The gas turbine combustor has a component called a pilot nozzle that first ignites the fuel. The fuel is supplied to the pilot nozzle to ignite the gas turbine combustor. In the following description, a part that mixes fuel and air is referred to as a pilot nozzle.
[0003]
Stainless steel is often used as the base material for the pilot nozzle, and ferritic stainless steel is employed particularly when considering the elongation of the base material due to the temperature rise of the combustion gas.
[0004]
FIG. 7 is a configuration diagram of a pilot nozzle of a conventional gas turbine combustor, in which the upper half of FIG. 7 is shown in a cross-sectional view and the lower half is partially cut away and shown in an external view. The pilot nozzle 1 includes a premixing nozzle 2 that mixes fuel and air and injects the mixed gas, a diffusion nozzle 3 to which fuel is separately supplied, an outer ring 4 provided outside the premixing nozzle 2, and the like. It is configured.
[0005]
The premixing nozzle 2 is provided with fins 5 for adjusting the flow rate of fuel, a fuel passage 6 to which fuel is supplied, a nozzle 7 for injecting fuel, and an air intake 8 for taking in air. The outer ring 4 and the premixing nozzle 2 are threaded, and the outer ring 4 can be removed by the threaded portion 9. That is, the outer ring 4 is removed and the nozzle 7 is inspected at the time of maintenance of the gas turbine combustor.
[0006]
In manufacturing such a pilot nozzle 1, first, a round bar is prepared, and the outer ring 4 is created by cutting out from the round bar. Since the outer ring 4 needs to be threaded for maintenance, the base material of the outer ring 4 needs to be thickened. Usually, a minimum thickness of 10 mm is maintained.
[0007]
The premixing nozzle 2 is also a round bar, the fuel passage 4 is formed as a long and thin round hole by machining, and the air intake 8 is drilled by machining. The fins 5 and nozzles 7 are two-dimensional blades formed by machining with separate members, and are attached to the premixing nozzle 2 by a fillet joint by TIG welding.
[0008]
In addition, the diffusion nozzle 3 is formed of a double pipe and has a welded portion between the sawara and the double pipe, and TIG welding has been performed.
[0009]
[Problems to be solved by the invention]
However, in such a pilot nozzle of the conventional gas turbine combustor, the main body of the outer ring 4 and the premixing nozzle 2 is first manufactured by cutting a round bar. It takes a long time. Furthermore, since the base material of the outer ring 4 and the premixing nozzle 2 is thick, the pilot nozzle 1 becomes heavy and it is difficult to remove it during maintenance.
[0010]
Further, since the fins 5 and the nozzles 7 are attached by TIG welding, thermal deformation is large, and further machining may be necessary after welding. Furthermore, since the fin 5 has a curvature, it is necessary to perform additional machining while rotating, which further increases the machining cost.
[0011]
Further, since the fuel passage 4 in which the premixing nozzle 2 is formed is long, the tool is easily damaged even in machining, and the work period is prolonged. The same applies to the diffusion nozzle, and the TIG welded portion between the double pipe and Sawara is greatly deformed and affects the amount of fuel supplied.
[0012]
Further, since the pilot nozzle 1 is heavy, the outer ring 4 is shortened for the convenience of maintenance. However, even if the outer ring 4 is removed, it is difficult to check the nozzle 7 for dirt and clogging. But there was.
[0013]
An object of the present invention is to obtain a pilot nozzle of a gas turbine combustor that can reduce thermal deformation, reduce weight, and increase efficiency during manufacturing.
[0014]
[Means for Solving the Problems]
A pilot nozzle of a gas turbine combustor according to the invention of claim 1 is constituted by connecting a plurality of sleeves by laser welding, and includes a premixing swirler having an air inlet and a fin for controlling the flow rate of the mixed gas; A plurality of sleeves are connected by laser welding, and are provided with a premixing nozzle that jets fuel supplied from a fuel passage in a mist form with a nozzle, and a diffusion nozzle to which fuel is separately supplied. .
[0015]
In the pilot nozzle of the gas turbine combustor according to the first aspect of the present invention, the premixing swirler is constituted by connecting a plurality of sleeves by laser welding. The premix swirler is provided with an air intake and fins for controlling the flow rate of the mixed gas. Similarly, the premix nozzle is configured by connecting a plurality of sleeves by laser welding. The premixing nozzle is provided with a fuel passage and a nozzle, and the fuel supplied from the fuel passage is ejected in a mist form by the nozzle. Separate fuel is supplied to the diffusion nozzle.
[0016]
A pilot nozzle of a gas turbine combustor according to a second aspect of the present invention is the pilot nozzle according to the first aspect of the present invention, wherein the premixing swirler is a frustoconical sleeve positioned on the fuel ejection side, the frustoconical sleeve, and laser welding. A fuel supply side sleeve having the fins and the air intake port, and a ring connected to the tip of the truncated cone sleeve by laser welding.
[0017]
In the pilot nozzle of the gas turbine combustor according to the invention of claim 2, in addition to the action of the invention of claim 1, the frustoconical sleep and the fuel supply side sleeve located on the fuel ejection side of the premixing swirler are laser welded. The fuel supply-side sleeve is provided with fins and air intakes. A ring is connected to the tip of the truncated cone sleeve by laser welding.
[0018]
A pilot nozzle of a gas turbine combustor according to a third aspect of the present invention is the pilot nozzle according to the second aspect, wherein the fin of the fuel supply side sleeve is attached to the fuel supply side sleeve by laser cutting. And the fins are inserted into the mounting holes and fixed by butt welding with a laser beam.
[0019]
In the pilot nozzle according to the invention of claim 3, in addition to the action of the invention of claim 2, a fin mounting hole is formed in the fuel supply side sleeve by laser cutting, and the fin is inserted into the mounting hole, and laser light is used. Fix by butt welding.
[0020]
According to a fourth aspect of the present invention, the pilot nozzle of the gas turbine combustor according to the second aspect of the invention is characterized in that the formation of the air intake port of the fuel supply side sleeve is performed by laser cutting with a laser beam. And
[0021]
In the pilot nozzle of the gas turbine combustor according to the invention of claim 4, in addition to the action of the invention of claim 2, the air intake port of the fuel supply side sleeve is formed by laser cutting with laser light.
[0022]
A pilot nozzle of a gas turbine combustor according to a fifth aspect of the present invention is the pilot nozzle according to the first aspect of the present invention, wherein the premixing nozzle comprises a truncated cone-shaped sleeve positioned on the fuel ejection side, the truncated cone-shaped sleeve and the ring. An inner sleeve connected by laser welding to form the fuel passage, an outer sleeve connected by laser welding via the frustoconical sleeve and the ring, and a tip of the frustoconical sleeve An injection side ring connected to the part by laser welding is provided.
[0023]
In the pilot nozzle of the gas turbine combustor according to the invention of claim 5, in addition to the action of the invention of claim 1, the frustoconical sleeve located on the fuel ejection side of the premixing nozzle and the ring are connected by laser welding. The ring and the inner sleeve forming the fuel passage are connected by laser welding. Similarly, the ring and the outer sleeve forming the fuel passage are connected by laser welding. Then, the injection side ring is connected to the tip of the truncated cone sleeve by laser welding.
[0024]
The pilot nozzle of a gas turbine combustor according to the invention of claim 6 is the pilot nozzle of claim 5, wherein the fuel passage of the premixing nozzle is formed by connecting the inner sleeve and the outer sleeve by laser welding using an outer access system. It is characterized by the fact that this is done.
[0025]
In the pilot nozzle of the gas turbine combustor according to the invention of claim 6, in addition to the action of the invention of claim 5, the inner sleeve and the outer sleeve are connected by laser welding by the outer access system to form the fuel passage of the premix nozzle. To do.
[0026]
A pilot nozzle of a gas turbine combustor according to a seventh aspect of the invention is the pilot nozzle according to the fifth aspect of the invention, wherein the nozzle of the premixing nozzle is attached by laser welding that enables partial penetration by penetration control. It is characterized by attaching.
[0027]
In the pilot nozzle of the gas turbine combustor according to the invention of claim 7, in addition to the action of the invention of claim 5, the nozzle is attached by laser welding that enables partial penetration by penetration control.
[0028]
The pilot nozzle of the gas turbine combustor according to the invention of claim 8 is the pilot nozzle according to claim 1, wherein the diffusion nozzle is a swirler provided on the fuel injection side, and a double pipe connected to the swirler by laser welding. It is characterized by comprising.
[0029]
In the pilot nozzle of the gas turbine combustor according to the invention of claim 8, in addition to the action of the invention of claim 1, the double pipe is connected by laser welding to the swirler provided on the fuel injection side of the diffusion nozzle. .
[0030]
DETAILED DESCRIPTION OF THE INVENTION
Hereinafter, an embodiment of a pilot nozzle of a gas turbine combustor according to the present invention will be described. FIG. 1 is a configuration diagram of a pilot nozzle of a gas turbine combustor according to an embodiment of the present invention. The upper half of FIG. 1 is shown in a sectional view, and the lower half is partly cut away and shown in an external view.
[0031]
The pilot nozzle 1 includes a premixing swirler 10 having an air intake 8 and fins 5 for controlling the flow rate and flow of the mixed gas, a nozzle 7 for injecting fuel in the form of a mist, and a premixing nozzle 2 having a fuel passage 6. And a diffusion nozzle 3 for supplying fuel separately.
[0032]
The premixing swirler 10 and the premixing nozzle 2 are formed in a sleeve shape to facilitate inspection during maintenance of the nozzle 7 that ejects fuel. That is, the premixing swirler 10 is configured by connecting a plurality of sleeves by laser welding, and the premixing swirler 10 is provided with an air intake 8 and fins 5 for controlling the flow rate of the mixed gas. Similarly, the premixing nozzle 2 is also configured by connecting a plurality of sleeves by laser welding. The premixing nozzle 2 is provided with a fuel passage 6 and a nozzle 7, and the fuel supplied from the fuel passage 6 is fed by the nozzle 7. It erupts in a mist form. The premix swirler 10 is fixed with bolts 11.
[0033]
The base material of the premixed swirler 10 in the pilot nozzle 1 is made of ferritic stainless steel such as SUS430, and has a smaller linear expansion coefficient than that of austenitic stainless steel and suppresses thermal stress during operation. The plate thickness is 5 mm, for example.
[0034]
The shapes of the premixing swirler 10 and the sleeve of the premixing nozzle 2 are secured by a molding method, and they are connected by laser welding. O marks a to k are attached to the laser welded portions connected by laser welding.
[0035]
FIG. 2 is an explanatory diagram of the premixing swirler 10 of the gas turbine combustor according to the embodiment of the present invention. The premixed swirler 10 includes a truncated cone sleeve 10a located on the fuel ejection side, a fuel supply side sleeve 10b connected to the truncated cone sleeve 10a by laser welding, and laser welding to the tip of the truncated cone sleeve 10a. It is comprised from the ring 10c connected by this. The fuel supply side sleeve 10b is provided with fins 5 and air intakes 8.
[0036]
The truncated cone type sleep 10a and the fuel supply side sleeve 10b are shaped by roll molding or press molding, and longitudinal welding is performed by laser welding. The laser welds are marked with O marks a, d, and h. Further, the mounting holes of the fins 5 and the air intake 8 are laser-cut, and the fins 5 are inserted into the mounting holes and fixed by butt welding using laser light. The laser beam used for laser welding employs a C02 laser, but a YAG laser may be employed.
[0037]
A method for forming the truncated cone sleeve 10a will be described. The developed shape of the frustoconical sleeve 10a is cut out from the flat base material by laser cutting, and the developed flat plate of the frustoconical sleeve 10a is used with three rolls 12 as shown in FIG. To mold. Further, as shown in FIG. 3B, a laser-cut flat plate is inserted into the lower die 13 of the press device and embossed with the upper die 14 to produce the shape of the truncated cone sleeve 10a. A press machine with a maximum of 1000 tons is sufficient. The longitudinal butt groove of the frustoconical sleeve 10a thus formed is laser welded.
[0038]
An example of cutting conditions and welding conditions for laser cutting in this forming process is shown below. (1) Laser cutting conditions Laser output: 1 to 6 kW
Cutting speed: 100 to 3000 mm / min
Focus setting position: -3 to 1 mm
Processing gas: Oxygen gas, Nitrogen gas, Ar gas Optical system focal length: 70-200 mm
(2) Laser welding conditions Laser output: 4 to 25 kW
Welding speed: 500 to 4000 mm / min
Focus setting position: -5 to 2 mm
Shielding gas: He, Ar, N2 gas focusing optical system focal length: 100-700 mm
Next, the fuel supply side sleeve 10b is similarly molded and manufactured. Then, each sleeve is laser welded to form the premixed swirler 10.
[0039]
Here, at the time of laser welding of the premixed swirler 10, it is possible to prevent the back bead from being oxidized by supplying the shielding gas to the inside. If necessary at the time of laser welding, the components of the weld metal may be adjusted using a filler wire.
[0040]
Furthermore, surplus after laser welding (both front and back beads) or adhering spatter may be finished with a grinder or the like, if necessary, at a portion related to the flow of fuel.
[0041]
Thus, in forming the pilot nozzle, the cutting of the round bar is stopped and the flat plate is formed and connected by laser welding. In other words, by forming a joint at the connection location, first, waste of the base material is eliminated and the weight can be reduced. Furthermore, since welding is performed by laser welding, welding thermal deformation can be suppressed, and a final processing finish is not required.
[0042]
Further, since the thickness of the product is realized by forming the sleeve, the handling at the time of maintenance becomes easy, and the premixed swirler 10 is fixed by the bolt 11, so that the detachment is easy. Further, the inspection of the nozzle 7 for ejecting fuel becomes easy, and the maintenance time can be shortened.
[0043]
The fin 5 is attached by piercing the main body of the fuel supply side sleeve 10b of the premixed swirler 10 by laser cutting to form a wing-shaped fin shape, inserting the fin 5 into the attachment hole, and butt welding by laser welding. To do. Therefore, unlike the case where fillet welding is performed on the premixing nozzle 2 side by conventional TIG welding, deformation is reduced, so that machining of the tips of the fins 5 is not required after welding. Further, since the air intake 8 of the premixed swirler 10 is formed by laser cutting, the air intake 8 having the design specifications can be easily formed even in the range where the base material is hardened or the residual stress is distributed, such as in the vicinity of the laser weld. be able to.
[0044]
Next, FIG. 4 is an explanatory diagram of the premixing nozzle 2 and shows a method of forming the premixing nozzle 2. First, as shown in FIG. 4A, the inner sleeve on the inner diameter side is welded. That is, laser welding is performed by irradiating the laser welding portion c with laser light. Next, as shown in FIG. 4B, laser welding is performed by irradiating the laser welding portion b of the outer sleeve 16 with laser light. Then, the ring 17 and the outer sleeve 16 are laser-welded by the laser welded part e, and the ring 17 and other parts 15 are laser welded by the laser welded part f. In this case, the laser welding portions e and f of the groove are formed with connection surfaces obliquely and irradiate the laser beam from the outside where light transmission is simple, not from the inside. Thereby, laser weldability is improved.
[0045]
Then, as shown in FIG. 4C, a frustoconical sleeve 18 is connected to the ring 17 by laser welding at a laser welded portion g, and a jet ring 19 is connected to the tip of the frustoconical sleep 18 with a laser. Laser welding is performed at the welded portion i to connect. Thereby, the premixing nozzle 2 is formed. Thereby, laser welding is easy and the fuel passage 6 can be formed.
[0046]
FIG. 5 is an explanatory diagram when the nozzle 7 is attached to the premixing nozzle 2. The nozzle 7 of the premixing nozzle 2 is provided with a fuel injection port 20 for injecting the fuel supplied through the fuel passage 6. The nozzle 7 is attached to an outer sleeve 16 that forms the fuel passage 6. The nozzle 7 is attached by laser welding that enables partial penetration by penetration control.
[0047]
That is, the nozzle 7 is disposed on the outer sleeve 16 of the premixing nozzle 2 and laser welding is performed. Partial penetration welding (non-penetrating welding) is performed without putting a splatter in the fuel passage 6. In the mounting of the nozzle 7 in this case, since the position of the fuel outlet 20 is important, the problem of thermal deformation due to conventional TIG welding can be solved by adopting laser welding.
[0048]
An example of laser welding conditions in this case is shown below.
(3) Laser welding conditions Laser output: 1 to 5 kW
Welding speed: 1000 to 3000 mm / min
Focus setting position: -2 to 0 mm
Shielding gas: He, Ar, N2 gas focusing optical system focal length: 100-200 mm
In this way, the nozzle 7 for injecting fuel into the premixing nozzle 2 in the form of a mist is attached by the laser welding method that enables partial penetration by penetration control, and the back bead splatter generated during penetration welding is sealed. The fuel passage is not left behind.
[0049]
Next, FIG. 6 is an explanatory view of the diffusion nozzle 3 of the gas turbine combustor according to the embodiment of the present invention. The diffusion nozzle 3 includes a swirler 21 provided on the fuel injection side, and a double pipe connected to the swirler 21 by laser welding. The inner pipe 22 of the double pipe is laser welded at the laser weld k, and the outer pipe 23 is laser welded at the laser weld j. FIG. 6 shows only the upper laser welds j and k across the center line.
[0050]
That is, in order to manufacture the diffusion nozzle 3, first, the inner pipe 22 is laser-welded to the swirler 21 by non-through welding. Next, the outer pipe 23 and the swirler 21 are welded. As the welding conditions, the parameters of the laser welding condition (3) described above are used. Thereby, the inclination of the inner pipe 22 and the outer pipe 23 and the deformation of the swirler 21 can be suppressed, and the fuel supply can be stabilized. Moreover, since the double pipes 22 and 23 and the swirler 21 which are components of the diffusion nozzle 3 are laser welded, the finishing process can be reduced by suppressing deformation.
[0051]
Further, by adopting laser welding or laser light drilling for welding or cooling hole drilling in the manufacture of the follow sleeve, deformation of the follow sleeve can be suppressed and the machining finishing process can be reduced. In this way, the nozzle cover can be manufactured efficiently because it employs laser welding.
[0052]
【The invention's effect】
As described above, according to the present invention, the pilot nozzle can be efficiently manufactured, and the pilot nozzle can be reduced in weight. Accordingly, maintainability can be improved, and manufacturing rationalization and process shortening can be realized.
[0053]
Further, since the pilot nozzle body is manufactured by roll forming, laser cutting, or laser welding, the thermal deformation of the body can be reduced and the processing cost can be reduced. Further, since the premixing swirler and the premixing nozzle are formed in a sleeve shape, the entire nozzle can be observed, and inspection and carrying during maintenance can be facilitated.
[Brief description of the drawings]
FIG. 1 is a configuration diagram of a pilot nozzle of a gas turbine combustor according to an embodiment of the present invention.
FIG. 2 is an explanatory diagram of a premixing swirler of the gas turbine combustor according to the embodiment of the present invention.
FIG. 3 is an explanatory view of molding of a truncated cone type sleeve according to the embodiment of the present invention.
FIG. 4 is an explanatory diagram of a premixing nozzle of a gas turbine combustor according to an embodiment of the present invention.
FIG. 5 is an explanatory diagram when a nozzle is attached to the premixing nozzle according to the embodiment of the present invention.
FIG. 6 is an explanatory view of a diffusion nozzle of the gas turbine combustor according to the embodiment of the present invention.
FIG. 7 is a configuration diagram of a pilot nozzle of a conventional gas turbine combustor.
[Explanation of symbols]
DESCRIPTION OF SYMBOLS 1 Pilot nozzle 2 Premix nozzle 3 Diffusion nozzle 4 Outer ring 5 Fin 6 Fuel passage 7 Nozzle 8 Air intake 9 Screw part 10 Premix swirler 11 Bolt 12 Roll 13 Lower mold 14 Upper mold 15 Inner sleeve 16 Outer sleeve 17 Ring 18 Frustum-shaped sleeve 19 Injection side sleeve 20 Fuel outlet 21 Swirler 22 Inner pipe 23 Outer pipe

Claims (8)

A premixed swirler having a plurality of sleeves connected by laser welding and having an air inlet and a fin for controlling the flow rate of the mixed gas; and a plurality of sleeves connected by laser welding and configured from a fuel passage A pilot nozzle for a gas turbine combustor, comprising: a premixing nozzle that ejects supplied fuel in a mist form through a nozzle; and a diffusion nozzle that is supplied with fuel separately. 2. The premix swirler according to claim 1, wherein the premix swirler includes a truncated cone sleeve located on a fuel ejection side, a fuel supply side sleeve connected to the truncated cone sleeve by laser welding and having the fin and the air intake port. And a pilot nozzle of a gas turbine combustor comprising: a ring connected to a tip portion of the frustoconical sleeve by laser welding. The fin of the fuel supply side sleeve may be attached to the fuel supply side sleeve by laser cutting to form a mounting hole for the fin, and the fin is inserted into the mounting hole. A pilot nozzle for a gas turbine combustor, wherein the pilot nozzle is fixed by butt welding using a gas turbine. 3. The pilot nozzle of a gas turbine combustor according to claim 2, wherein the air inlet of the fuel supply side sleeve is formed by laser cutting with a laser beam. In the invention of claim 1, the premixing nozzle includes a truncated cone-shaped sleeve positioned on a fuel ejection side, and an inner sleeve that is connected to the truncated cone-shaped sleeve by laser welding via a ring to form the fuel passage. An outer sleeve that is connected to the frustoconical sleeve by laser welding via the ring to form the fuel passage, and an injection-side ring that is connected to the tip of the frustoconical sleeve by laser welding. A pilot nozzle for a gas turbine combustor. 6. The gas turbine combustor according to claim 5, wherein the fuel passage of the premixing nozzle is formed by connecting the inner sleeve and the outer sleeve by laser welding using an outer access system. Pilot nozzle. 6. The gas turbine combustor pilot according to claim 5, wherein the nozzle of the premixing nozzle is attached by laser welding which enables partial penetration by penetration control. nozzle. 2. The gas turbine combustor pilot nozzle according to claim 1, wherein the diffusion nozzle includes a swirler provided on a fuel injection side and a double pipe connected to the swirler by laser welding. .

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