KR102703147B1 - Flange apparatus for assembling combuster and Combuster and Method for assembling combuster using the same - Google Patents

Abstract

The flange device for assembling a combustor of the present invention is a flange device for assembling a combustor to a combustor casing, comprising: a mounting base mounted on a flange portion of the combustor casing; a plurality of screw bars coupled to the mounting base; a liner coupling portion movably mounted to the plurality of screw bars; and a plurality of motor boxes coupled to the liner coupling portion and moving the liner coupling portion relative to the plurality of screw bars.

Description

{Flange apparatus for assembling combuster and combustor and method for assembling combuster using the same}

The present invention relates to a flange device for assembling a combustor, a combustor, and a method for assembling a combustor using the same, and more specifically, to a flange device for assembling a combustor, a combustor, and a method for assembling a combustor using the same, which enable easy assembly by combining and moving a liner to a flange device and fastening it, and then combining a nozzle casing to a flange portion of a combustor casing.

A turbine is a mechanical device that obtains rotational power through impulse or reaction force by utilizing the flow of compressible fluid such as steam or gas. Examples include steam turbines that use steam and gas turbines that use high-temperature combustion gas.

Among these, the gas turbine is largely composed of a compressor, a combustor, and a turbine. The compressor is equipped with an air inlet for introducing air, and a plurality of compressor vanes and compressor blades are arranged alternately within the compressor housing.

The combustor supplies fuel to the compressed air compressed in the compressor and ignites it with a burner, thereby generating high-temperature, high-pressure combustion gas.

The turbine has a plurality of turbine vanes and turbine blades arranged alternately within the turbine housing. In addition, the rotor is arranged to penetrate the center of the compressor, combustor, turbine, and exhaust chamber.

The above rotor is rotatably supported at both ends by bearings. In addition, a plurality of disks are fixed to the rotor, and each blade is connected, while a drive shaft of a generator or the like is connected to the end on the exhaust side.

Since these gas turbines do not have a reciprocating mechanism such as a piston in a four-stroke engine, there are no frictional parts such as pistons and cylinders, so they consume very little lubricating oil, and they have the advantage of greatly reducing the amplitude, which is a characteristic of reciprocating machines, and enabling high-speed operation.

Briefly explaining the operation of a gas turbine, compressed air from a compressor is mixed with fuel and combusted to create high-temperature combustion gas, which is then injected toward the turbine. The injected combustion gas generates rotational force as it passes through the turbine vanes and turbine blades, which in turn causes the rotor to rotate.

When assembling a combustor, there are cases where the parts assembled inside the combustor casing, such as a transition piece, are larger than the flange of the nozzle casing assembled outside the combustor casing. In such cases, the flange size of the nozzle casing must be increased or additional processing must be performed on the can hole flange of the combustor casing.

Patent Registration No. 10-1737715

The present invention aims to provide a flange device for assembling a combustor, which can be easily assembled by coupling and moving a liner to a flange device and then coupling a nozzle casing to a flange portion of a combustor casing, and a combustor and a method for assembling a combustor using the same.

In order to achieve the above object, the present invention provides a flange device for assembling a combustor to a combustor casing, the flange device comprising: a mounting base mounted on a flange portion of the combustor casing; a plurality of screw bars coupled to the mounting base; a liner coupling portion movably mounted to the plurality of screw bars; and a plurality of motor boxes coupled to the liner coupling portion and moving the liner coupling portion relative to the plurality of screw bars.

The above mounting base may include an outer flange portion that is fastened to a flange portion of the combustor casing, and an inner flange portion to which a liner of the combustor is fastened.

The outer flange portion may be formed to extend radially outward from an upper edge of the mounting base, and a plurality of fastening holes may be formed therethrough, while the inner flange portion may be formed to extend radially inward from a lower edge of the mounting base, and a plurality of fastening holes may be formed therethrough.

The above plurality of screw bars can be coupled to the inner flange portion.

The above liner joint can be moved inward along the plurality of screw bars while the liner of the combustor is temporarily coupled.

The above plurality of motor boxes are gear-coupled to the above plurality of screw bars and can be operated simultaneously to move the liner coupling part inward.

After the liner of the above combustor is fastened to the inner flange portion, the plurality of screw bars and the liner joint portion are separated, and then the nozzle casing of the combustor can be fastened to the flange portion of the combustor casing.

A combustor assembled using a flange device for assembling a combustor of the present invention comprises a nozzle casing having a fuel nozzle module mounted thereon, a liner connected to the nozzle casing and forming a combustion chamber therein and mounted on the flange device for assembling the combustor, a transition piece connected to the liner, and an ignition device for igniting a fuel-air mixture gas inside the combustion chamber, wherein the flange device for assembling the combustor comprises: a mounting base mounted on a flange portion of the combustor casing; a plurality of screw bars coupled to the mounting base; a liner coupling portion movably mounted to the plurality of screw bars; and a plurality of motor boxes coupled to the liner coupling portion and moving the liner coupling portion with respect to the plurality of screw bars.

The above mounting base may include an outer flange portion that is fastened to a flange portion of the combustor casing, and an inner flange portion to which a liner of the combustor is fastened.

The outer flange portion may be formed to extend radially outward from an upper edge of the mounting base, and a plurality of fastening holes may be formed therethrough, while the inner flange portion may be formed to extend radially inward from a lower edge of the mounting base, and a plurality of fastening holes may be formed therethrough.

The above plurality of screw bars can be coupled to the inner flange portion.

The above liner joint can be moved inward along the plurality of screw bars while the liner of the combustor is temporarily coupled.

The above plurality of motor boxes are gear-coupled to the above plurality of screw bars and can be operated simultaneously to move the liner coupling part inward.

After the liner of the above combustor is fastened to the inner flange portion, the plurality of screw bars and the liner joint portion are separated, and then the nozzle casing of the combustor can be fastened to the flange portion of the combustor casing.

A method for assembling a combustor using a flange device of the present invention comprises the steps of assembling a flange device for assembling a combustor by coupling a plurality of screw bars coupled with a plurality of motor boxes coupled with liner coupling portions to a mounting base; mounting the assembled flange device on a flange portion of the combustor casing; coupling a liner of the combustor to the liner coupling portion of the flange device; operating the plurality of motor boxes to move the liner inward; fastening the liner to the inner flange portion of the flange device; separating the plurality of screw bars and the liner coupling portion; and fastening a nozzle casing of the combustor to the flange portion of the combustor casing.

The above mounting base may include an outer flange portion that is fastened to a flange portion of the combustor casing, and an inner flange portion to which the liner of the combustor is fastened and to which the plurality of screw bars are coupled.

The outer flange portion is formed to extend radially outwardly from an upper edge of the mounting base, and a plurality of fastening holes are formed therethrough to be fastened to the flange portion of the combustor casing, and the inner flange portion is formed to extend radially inwardly from a lower edge of the mounting base, and a plurality of fastening holes are formed therethrough to allow the plurality of screw bars and the liner of the combustor to be coupled.

In the above liner moving step, the plurality of motor boxes are gear-coupled to the plurality of screw bars and can be operated simultaneously to move the liner coupling portion inward along the plurality of screw bars.

According to the above-described flange device for assembling a combustor of the present invention, the combustor, and the combustor assembly method using the same, a liner is coupled to the flange device, moved and fastened, and then the nozzle casing is coupled to the flange portion of the combustor casing, enabling easy assembly.

FIG. 1 is a partially cut-away perspective view of a gas turbine according to one embodiment of the present invention.
FIG. 2 is a cross-sectional view showing a schematic structure of a gas turbine according to one embodiment of the present invention.
Figure 3 is a partially enlarged perspective view showing the combustor section of the gas turbine of Figure 1.
FIG. 4 is a perspective view showing a combustor according to one embodiment of the present invention.
FIG. 5 is a perspective view showing a flange device for assembling a combustor according to one embodiment of the present invention.
Figure 6 is a partial perspective view showing the flange portion of the combustor casing.
Figure 7 is a partial perspective view showing a flange device for assembling a combustor mounted on a can hole flange portion of a combustor casing.
Figure 8 is a partial perspective view showing the attachment of a liner to a flange device for assembling a combustor.
Figure 9 is a partial perspective view showing the liner coupled to the flange device for assembling the combustor moved inward.
Figure 10 is a partial perspective view showing the liner attached to the inner flange portion of the flange device for assembling the combustor.
Fig. 11 is a partial perspective view showing the nozzle casing attached to the flange portion of the combustor casing.

The present invention can be modified in various ways and has various embodiments, and specific embodiments are illustrated and described in detail in the detailed description. However, this is not intended to limit the present invention to specific embodiments, but should be understood to include all modifications, equivalents, or substitutes included in the spirit and technical scope of the present invention.

The terminology used herein is only used to describe specific embodiments and is not intended to limit the present invention. The singular expression includes the plural expression unless the context clearly indicates otherwise. In the present invention, it should be understood that the terms "comprise" or "have" and the like are intended to specify that a feature, number, step, operation, component, part or combination thereof described in the specification is present, but do not exclude in advance the possibility of the presence or addition of one or more other features, numbers, steps, operations, components, parts or combinations thereof.

Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the attached drawings. At this time, it should be noted that the same components in the attached drawings are indicated by the same symbols as much as possible. In addition, detailed descriptions of well-known functions and configurations that may obscure the gist of the present invention will be omitted. For the same reason, some components in the attached drawings are exaggerated, omitted, or schematically illustrated.

FIG. 1 is a partially cut-away perspective view of a gas turbine according to one embodiment of the present invention, and FIG. 2 is a cross-sectional view showing a schematic structure of a gas turbine according to one embodiment of the present invention.

As illustrated in FIG. 1, a gas turbine (1000) according to one embodiment of the present invention includes a compressor (1100), a combustor (1200), and a turbine (1300). The compressor (1100) has a plurality of blades (1110) that are radially installed. The compressor (1100) rotates the blades (1110), and air moves while being compressed by the rotation of the blades (1110). The size and installation angle of the blades (1110) may vary depending on the installation location. In one embodiment, the compressor (1100) is directly or indirectly connected to the turbine (1300), and may receive a portion of the power generated in the turbine (1300) and use it to rotate the blades (1110).

Air compressed in the compressor (1100) moves to the combustor (1200). The combustor (1200) includes a plurality of combustion chambers (1210) arranged in an annular shape and a fuel nozzle module (1220).

As illustrated in FIG. 2, a gas turbine (1000) according to one embodiment of the present invention has a housing (1010), and a diffuser (1400) is provided at the rear side of the housing (1010) for discharging combustion gas passing through the turbine. In addition, a combustor (1200) is arranged in front of the diffuser (1400) to supply compressed air and combust it.

In terms of the direction of air flow, a compressor section (1100) is positioned on the upstream side of the housing (1010), and a turbine section (1300) is positioned on the downstream side. In addition, a torque tube unit (1500) is positioned between the compressor section (1100) and the turbine section (1300) as a torque transmission member that transmits rotational torque generated in the turbine section (1300) to the compressor section (1100).

The above compressor section (1100) is provided with a plurality (e.g., 14) of compressor rotor disks (1120), and each of the compressor rotor disks (1120) is connected by a tie rod (1600) so as not to be axially separated.

Specifically, each of the compressor rotor disks (1120) is aligned with each other along the axial direction with a tie rod (1600) forming a rotation axis passing through approximately the center. Here, the opposing surfaces of each of the neighboring compressor rotor disks (1120) are pressed by the tie rod (1600) so that relative rotation is impossible.

On the outer surface of the compressor rotor disk (1120), a plurality of blades (1110) are radially joined. Each blade (1110) has a dovetail portion (1112) and is fastened to the compressor rotor disk (1120).

Between each of the above rotor disks (1120), a vane (not shown) is positioned and fixed to the housing. Unlike the rotor disks, the vane is fixed so as not to rotate, and serves to align the flow of compressed air passing through the blades of the compressor rotor disk and guide the air to the blades of the rotor disk located on the downstream side.

The fastening method of the above dovetail portion (1112) includes a tangential type and an axial type. This can be selected according to the required structure of a commercially available gas turbine, and can have a commonly known dovetail or fir-tree shape. In some cases, the blade can be fastened to the rotor disk using a fastening device other than the above type, for example, a fixing device such as a key or bolt.

The tie rod (1600) is arranged to penetrate the center of the plurality of compressor rotor disks (1120) and turbine rotor disks (1320), and the tie rod (1600) may be composed of one or more tie rods. One end of the tie rod (1600) is fastened within the compressor rotor disk located on the uppermost side, and the other end of the tie rod (1600) is fastened by a fixing nut (1450).

The shape of the above tie rod (1600) may have various structures depending on the gas turbine, and is therefore not necessarily limited to the shape presented in Fig. 2. That is, as illustrated, one tie rod may have a shape penetrating the center of the rotor disk, or a plurality of tie rods may have a shape arranged in a circumferential manner, and a combination of these is also possible.

Although not shown, a vane that acts as a guide vane may be installed in the next position of the diffuser in the compressor of a gas turbine to increase the pressure of the fluid and then adjust the flow angle of the fluid entering the combustor inlet to the design flow angle. This is called a deswirler.

In the above combustor (1200), the introduced compressed air is mixed with fuel and combusted to create high-energy, high-temperature, high-pressure combustion gas, and the combustion gas temperature is increased to a heat-resistant limit that the combustor and turbine components can withstand through an isobaric combustion process.

The combustors constituting the combustion system of a gas turbine can be arranged in a plurality within a housing formed in a cell shape, and are configured to include a burner including a fuel injection nozzle, a combustor liner forming a combustion chamber, and a transition piece that serves as a connection between the combustor and the turbine.

Specifically, the liner provides a combustion space in which fuel injected by the fuel nozzle is mixed with compressed air of the compressor and combusted. The liner may include a flame tube providing a combustion space in which fuel mixed with air is combusted, and a flow sleeve forming an annular space while surrounding the flame tube. In addition, a fuel nozzle is coupled to the front end of the liner, and a spark plug is coupled to the side wall.

Meanwhile, at the rear end of the liner, a transition piece is connected so that combustion gas combusted by the ignition plug can be sent to the turbine side. This transition piece has an outer wall that is cooled by compressed air supplied from the compressor to prevent damage due to the high temperature of the combustion gas.

To this end, the above transition piece is provided with cooling holes so that air can be injected into the interior, and the compressed air cools the main body inside through the holes and then flows to the liner side.

In the annular space of the above liner, cooling air that cools the aforementioned transition piece flows, and on the outer wall of the liner, compressed air from the outside of the flow sleeve can collide with the cooling air by being provided through cooling holes provided in the flow sleeve.

Meanwhile, the high temperature and high pressure combustion gas from the above-described combustor is supplied to the turbine (1300) described above. As the supplied high temperature and high pressure combustion gas expands, it collides with the turbine's rotating blades, thereby providing a reaction force and causing a rotational torque. The rotational torque thus obtained is transmitted to the compressor through the torque tube described above, and power exceeding the power required to drive the compressor is used to drive a generator, etc.

The above turbine (1300) is basically similar in structure to a compressor. That is, the turbine (1300) is also provided with a plurality of turbine rotor disks (1320) similar to the compressor rotor disks of the compressor. Accordingly, the turbine rotor disk (1320) also includes a plurality of turbine blades (1340) that are arranged radially. The turbine blades (1340) may also be coupled to the turbine rotor disk (1320) in a dovetail or the like manner. In addition, a turbine vane (1330) fixed to a housing is also provided between the blades (1340) of the turbine rotor disk (1320) to guide the flow direction of combustion gas passing through the blades.

The above turbine rotor disk (1320) has a substantially circular plate shape, and a plurality of coupling slots are formed on its outer periphery. The coupling slots are formed to have a curved surface in the shape of a fir tree.

A turbine blade (1340) is fastened to the above-mentioned coupling slot. The turbine blade (1340) may have a flat-plate-shaped platform portion in the approximate center portion. The platform portion serves to maintain a gap between the blades by contacting the platform portion of an adjacent turbine blade with its side surface.

A root portion is formed on the bottom surface of the above platform portion. The root portion has an axial-type shape that is inserted along the axial direction of the rotor disk (1320) into the coupling slot of the above-described rotor disk (1320).

The above root portion has a curved portion having an approximate fir tree shape, which is formed to correspond to the shape of the curved portion formed in the joining slot. Here, the joining structure of the root portion does not necessarily have to have a fir tree shape, and may be formed to have a dovetail shape.

A blade section is formed on the upper surface of the above platform section. The blade section is formed to have an airfoil shape optimized according to the specifications of the gas turbine, and has a leading edge positioned on the upstream side and a trailing edge positioned on the downstream side based on the flow direction of the combustion gas.

Here, unlike the blades of the compressor, the blades of the turbine come into direct contact with the high-temperature, high-pressure combustion gas. Since the temperature of the combustion gas is so high that it can reach 1700℃, a cooling means is required. For this purpose, a cooling path is provided to extract compressed air from some parts of the compressor and supply it to the turbine blades.

The above cooling path may extend outside the housing (external path), may extend through the inside of the rotor disk (internal path), or may use both external and internal paths. A plurality of film cooling holes are formed on the surface of the blade portion, and the film cooling holes are connected to cooling paths (not shown) formed inside the blade portion to supply cooling air to the surface of the blade portion.

Meanwhile, the blade portion of the turbine rotates inside the housing by combustion gas, and a gap exists between the end of the blade portion and the inner surface of the housing so that the blade portion can rotate smoothly. However, as described above, combustion gas may leak through the gap, and therefore a sealing means is required to block this.

Turbine vanes and turbine blades are both airfoils, comprising a leading edge, a trailing edge, a suction surface, and a pressure surface. The interior of the turbine vanes and turbine blades comprises a complex labyrinth of structures that form a cooling system. Cooling circuits within the vanes and blades receive cooling fluid, for example air, from the compressor of the turbine engine, and the fluid passes through the ends of the vanes and blades, which are adapted to be coupled to the vane and blade carrier. The cooling circuits typically comprise a plurality of flow paths designed to maintain all surfaces of the turbine vanes and blades at a relatively uniform temperature, and at least a portion of the fluid passing through these cooling circuits is discharged through openings in the leading edge, trailing edge, suction surface, and pressure surface of the vanes.

The gas turbine (1000) of the present invention has a compressor (1100), a combustor (1200), and a turbine (1300) each having a casing on the outer surface. A plurality of casings can be connected to each other by a plurality of fastening members such as bolts and screws.

FIG. 3 is a partial perspective view showing an enlarged portion of a combustor section in the gas turbine of FIG. 1, FIG. 4 is a perspective view showing a combustor according to one embodiment of the present invention, FIG. 5 is a perspective view showing a flange device for assembling a combustor according to one embodiment of the present invention, and FIG. 6 is a partial perspective view showing a flange portion of a combustor casing.

In addition, FIGS. 7 to 11 are drawings showing the process of assembling a combustor to a can hole flange portion of a combustor casing using a flange device for assembling a combustor.

First, as illustrated in FIG. 3, a plurality of combustion chambers (1210) having fuel nozzle modules (1220) of a combustor (1200) may be mounted in a combustor casing (1230) in an annular arrangement. An ignition device (1240) may be mounted on a plurality of combustors (1200) in the combustor casing (1230).

Looking at the exterior of the combustor (1200) illustrated in FIG. 4, it may include a nozzle casing (1250) equipped with a fuel nozzle module (1220) inside and mounted on a combustor casing (1230), a liner (1260) coupled to the nozzle casing (1250), and a transition piece (1270) coupled to the liner (1260).

As illustrated in FIG. 5, a flange device (100) for assembling a combustor according to one embodiment of the present invention is a flange device for assembling a combustor (1200) to a combustor casing (1230). The flange device (100) may include a mounting base (110) mounted on a flange portion (1235) of a combustor casing (1230), a plurality of screw bars (140) coupled to the mounting base, a liner coupling portion (150) movably mounted to the plurality of screw bars, and a plurality of motor boxes (160) coupled to the liner coupling portion and moving the liner coupling portion relative to the plurality of screw bars.

The mounting base (110) is formed in a roughly circular pipe shape, and the upper part of the mounting base (110) can be mounted by being coupled to the flange part (1235) of the combustor casing (1230).

The mounting base (110) may include an outer flange portion (120) provided at its upper end and fastened to a flange portion (1235) of a combustor casing (1230), and an inner flange portion (130) provided at its lower end and fastened to a liner (1260) of a combustor (1200). Depending on the diameter of the liner (1260) fastened to the inner flange portion (130), the width of the inner flange portion (130) may be selected.

A plurality of screw bars (140) can be fastened and combined to the mounting base (110), particularly the inner flange portion (130). In FIG. 5, four screw bars (140) are fastened to the inner flange portion (130) and arranged in parallel in the longitudinal direction, but three to six screw bars (140) can be combined. The screw bars (140) have screw threads formed on the outer surface of a bar with a circular cross section, and can guide the movement of the liner coupling portion (150) like a lead screw.

The liner coupling portion (150) can be movably mounted on a plurality of screw bars (140). The liner coupling portion (150) has a circular disk band shape, and a plurality of reinforcing members passing through the center can be connected. A plurality of through holes through which a plurality of screw bars (140) can pass can be formed in the liner coupling portion (150). In addition, an upper flange portion of the liner (1260) can be fastened and fastened to the rear surface of the liner coupling portion (150) by a plurality of screws. Therefore, the liner (1260) can be moved along the plurality of screw bars (140) while being fastened to the liner coupling portion (150).

The motor box (160) is mounted to surround each screw bar (140) and is coupled to the liner coupling portion (150) so as to move the liner coupling portion (150) relative to a plurality of screw bars (140). Inside each motor box (160), an electric motor capable of forward and reverse rotation and gears such as a worm gear or a bevel gear can be mounted.

The outer flange portion (120) is formed to extend radially outward from the upper edge of the mounting base (110), and a plurality of fastening holes (122) can be formed through it. The outer flange portion (120) can be mounted to the flange portion (1235) of the combustor casing (1230) by fastening a plurality of bolts through the plurality of fastening holes (122).

The inner flange portion (130) is formed to extend radially inward from the lower edge of the mounting base (110), and a plurality of fastening holes (132) can be formed through it. The upper flange portion of the liner (1260) can be mounted on the inner flange portion (130) by fastening a plurality of bolts through the plurality of fastening holes (132).

The liner coupling portion (150) can be moved inward along the plurality of screw bars (140) while the liner (1260) of the combustor (1200) is temporarily coupled thereto. The liner coupling portion (150) can be coupled to the liner coupling portion (150) while the liner (1260) is positioned at the upper end of the plurality of screw bars (140). The liner (1260) is temporarily coupled to the liner coupling portion (150) and moved inward into the mounting base (110) by the operation of the plurality of motor boxes (160), and then the upper flange portion of the liner (1260) can be fastened to the inner flange portion (130).

A plurality of motor boxes (160) are gear-coupled to a plurality of screw bars (140) and can be operated simultaneously to move the liner coupling portion (150) inward.

After the liner (1260) of the combustor (1200) is fastened to the inner flange portion (130), the plurality of screw bars (140) and the liner coupling portion (150) are separated, and then the nozzle casing (1250) of the combustor (1200) can be fastened to the flange portion (1235) of the combustor casing (1230).

After the liner (1260) is fastened to the inner flange portion (130), the upper flange portion of the liner (1260) can be separated from the liner coupling portion (150), and the plurality of screw bars (140) can also be separated from the inner flange portion (130). When separating the plurality of screw bars (140), the plurality of motor boxes (160) can be operated in the reverse direction to move the liner coupling portion (150) to the upper portion of the plurality of screw bars (140), and then the plurality of screw bars (140) can be separated from the inner flange portion (130).

After that, the outer flange portion (120) of the mounting base (110) is mounted on the flange portion (1235) of the combustor casing (1230), and the liner (1260) is mounted on the inner flange portion (130), and the nozzle casing (1250) of the combustor (1200) can be mounted by fastening it to the flange portion (1235) of the combustor casing (1230). The rear end of the nozzle casing (1250) can be coupled with the upper flange portion of the liner (1260).

On the surface where the inner flange portion (130) and the liner (1260) are connected, a gasket (not shown) or the like may be provided for sealing.

Next, a method of assembling a combustor using a flange device for assembling a combustor is described with reference to the drawings.

The method for assembling a combustor (1200) using a flange device (100) of the present invention comprises the steps of assembling a flange device (100) for assembling a combustor by connecting a plurality of screw bars (140) coupled with a plurality of motor boxes (160) coupled with liner coupling portions (150) to a mounting base (110), mounting the assembled flange device (100) to a flange portion (1235) of a combustor casing (1230), connecting a liner (1260) of a combustor (1200) to the liner coupling portion (150) of the flange device (100), operating a plurality of motor boxes (160) to move the liner (1260) inward, fastening the liner (1260) to the inner flange portion (130) of the flange device (100), separating the plurality of screw bars (140) and the liner coupling portion (150), and It includes a step of fastening the nozzle casing (1250) of the combustor (1200) to the flange portion (1235) of the combustor casing (1230).

As illustrated in Fig. 6, the combustor casing (1230) has a flange portion (1235) formed on the outer edge of a plurality of combustor can holes capable of mounting a plurality of combustors (1200). A plurality of fastening holes are formed in the flange portion (1235).

As shown in Fig. 7, the flange device (100) for assembling the combustor can be assembled, and then the outer flange portion (120) of the assembled flange device (100) can be mounted by fastening a plurality of bolts to the flange portion (1235) of the combustor casing (1230).

As illustrated in FIG. 8, the liner (1260) of the combustor (1200) can be coupled from the inside to the liner coupling portion (150) of the flange device (100).

As illustrated in FIG. 9, multiple motor boxes (160) can be operated simultaneously to move the liner (1260) inward.

As illustrated in FIG. 10, the liner (1260) is fastened to the inner flange portion (130) of the flange device (100), and then the liner coupling portion (150) is separated, and the plurality of screw bars (140) are also separated. Then, the outer flange portion (120) of the flange device (100) is mounted to the flange portion (1235) of the combustor casing (1230), and the liner (1260) is mounted to the inner flange portion (120) of the flange device (100).

As illustrated in FIG. 11, the nozzle casing (1250) of the combustor (1200) can be fastened to the flange portion (1235) of the combustor casing (1230). At this time, the flange portion (1235) is equipped with an outer flange portion (120) of the flange device (100), and by fastening a plurality of bolts through the flange portion of the nozzle casing (1250) on the outer flange portion (120), the assembly of the combustor (1200) can be completed.

Above, one embodiment of the present invention has been described, but it will be apparent to those skilled in the art that various modifications and changes to the present invention can be made by adding, changing, deleting or adding components, without departing from the spirit of the present invention as described in the claims, and this is also included within the scope of the present invention.

1000: Gas turbine 1010: Housing
1100: Compressor 1110: Compressor Blade
1112: Dovetail 1120: Compressor rotor disc
1200: Combustor
1210: Combustion chamber 1220: Fuel nozzle module
1230: Combustor casing 1235: Casing flange
1240: Ignition 1250: Nozzle casing
1260: Liner 1270: Transition Piece
1300: Turbine 1320: Turbine rotor disc
1330: Turbine Vane 1340: Turbine Blade
1400: Diffuser 1450: Fixed nut
1500: Torque tube unit 1600: Tie rod
100: Flange device for combustion chamber assembly
110: Mounting base 120: Outer flange
122: Fastening hole 130: Inner flange part
132: Fastener 140: Screw bar
150: Liner joint 160: Motor box

Claims (18)

In a flange device for assembling a combustor to a combustor casing,
A mounting base mounted on the flange portion of the above combustor casing;
A plurality of screw bars coupled to the above mounting base;
A liner coupling member movably mounted on the plurality of screw bars; and
A plurality of motor boxes are coupled to the liner coupling portion and move the liner coupling portion relative to the plurality of screw bars,
The above mounting base
An outer flange portion formed by extending radially outward from the upper edge of the above mounting base and having a plurality of fastening holes formed therethrough, and fastened to the flange portion of the above combustion chamber casing;
It includes an inner flange portion formed by extending radially inwardly from the lower edge of the above-mentioned mounting base and having a plurality of fastening holes formed therethrough to which the liner of the above-mentioned combustor is fastened.
After the liner of the above combustor is attached to the inner flange portion,
After separating the above plurality of screw bars and the above liner joint,
A flange device for assembling a combustor, characterized in that the nozzle casing of the combustor is fastened to the flange portion of the combustor casing. delete delete In the first paragraph,
A flange device for assembling a combustor, characterized in that the plurality of screw bars are coupled to the inner flange portion. In paragraph 4,
A flange device for assembling a combustor, characterized in that the liner coupling member moves inward along the plurality of screw bars while the liner of the combustor is temporarily coupled. In paragraph 5,
A flange device for assembling a combustor, characterized in that the plurality of motor boxes are gear-coupled to the plurality of screw bars and operate simultaneously to move the liner coupling portion inward. delete A combustor comprising a nozzle casing equipped with a fuel nozzle module, a liner connected to the nozzle casing and forming a combustion chamber inside, and mounted on a flange device for assembling the combustor, a transition piece connected to the liner, and an ignition device for igniting a fuel-air mixture gas inside the combustion chamber,
The above flange device for assembling the combustor
A mounting base mounted on the flange portion of the combustor casing;
A plurality of screw bars coupled to the above mounting base;
A liner coupling member movably mounted on the plurality of screw bars; and
A plurality of motor boxes are coupled to the liner coupling portion and move the liner coupling portion relative to the plurality of screw bars,
The above mounting base
An outer flange portion formed by extending radially outward from the upper edge of the above mounting base and having a plurality of fastening holes formed therethrough, and fastened to the flange portion of the above combustion chamber casing;
It includes an inner flange portion formed by extending radially inwardly from the lower edge of the above-mentioned mounting base and having a plurality of fastening holes formed therethrough to which the liner of the above-mentioned combustor is fastened.
After the liner of the above combustor is attached to the inner flange portion,
After separating the above plurality of screw bars and the above liner joint,
A combustor characterized in that the nozzle casing of the combustor is fastened to the flange portion of the combustor casing. delete delete In Article 8,
A combustor characterized in that the plurality of screw bars are coupled to the inner flange portion. In Article 11,
A combustor characterized in that the liner coupling member moves inward along the plurality of screw bars while the liner of the combustor is temporarily coupled. In Article 12,
A combustor characterized in that the plurality of motor boxes are gear-coupled to the plurality of screw bars and operate simultaneously to move the liner coupling portion inward. delete A step of assembling a flange device for assembling a combustor by combining a plurality of screw bars combined with a plurality of motor boxes combined with liner coupling parts to a mounting base;
A step of mounting the assembled flange device on the flange portion of the combustor casing;
A step of joining a liner of a combustor to a liner joining portion of the above flange device;
A step of operating the plurality of motor boxes to move the liner inward;
A step of fastening the liner to the inner flange portion of the flange device;
a step of separating the plurality of screw bars and the liner joint; and
A method for assembling a combustor using a flange device, comprising the step of fastening a nozzle casing of the combustor to a flange portion of the combustor casing. In Article 15,
The above mounting base
An outer flange portion connected to the flange portion of the above combustion chamber casing,
A method for assembling a combustor using a flange device, characterized in that it includes an inner flange portion to which the liner of the combustor is fastened and to which the plurality of screw bars are coupled. In Article 16,
The above outer flange portion is formed to extend radially outward from the upper edge of the mounting base, and a plurality of fastening holes are formed through the flange portion to be fastened to the flange portion of the combustion chamber casing.
A method for assembling a combustor using a flange device, characterized in that the inner flange portion is formed to extend radially inward from the lower edge of the mounting base, and a plurality of fastening holes are formed through the flange portion to connect the plurality of screw bars and the liner of the combustor. In Article 17,
In the above liner movement step,
A method for assembling a combustor using a flange device, characterized in that the plurality of motor boxes are gear-coupled to the plurality of screw bars and operate simultaneously to move the liner coupling part inward along the plurality of screw bars.

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