KR102162053B1 - Nozzle assembly and gas turbine including the same - Google Patents

Abstract

The present invention provides a nozzle assembly capable of improving mixing efficiency between fuel and air as a swirl vane is rotationally provided, and a gas turbine including the same. An embodiment of the present invention provides the nozzle assembly including: a nozzle body; a shroud surrounding the nozzle body; a plurality of swirl vanes provided to be spaced apart in a circumferential direction on a side surface of the nozzle body; a plurality of fuel injection holes which are provided on each side of the plurality of swirl vanes and through which fuel is injected; and a fuel supply unit for supplying fuel to the plurality of fuel injection holes from the inside of the nozzle body. The plurality of swirl vanes are rotationally provided in a circumferential direction with respect to the side surface of the nozzle body.

Description

Nozzle assembly and gas turbine including the same {NOZZLE ASSEMBLY AND GAS TURBINE INCLUDING THE SAME}

The present invention relates to a nozzle assembly and a gas turbine including the same, and more particularly, to a nozzle assembly capable of improving the mixing efficiency between fuel and air as the swirl vane is rotatably provided, and to a gas turbine including the same. .

In general, a turbine is a machine that converts the energy of a fluid such as water, gas, steam, etc. into mechanical work. Usually, several blades or blades are planted on the circumference of a rotating body and steam or gas is blown thereto at high speed with impulsive or reaction force. A turbo-type machine that rotates is called a turbine.

Types of such turbines include a hydro turbine that uses the energy of high water, a steam turbine that uses the energy of steam, an air turbine that uses the energy of high pressure compressed air, and a gas that uses the energy of high temperature and high pressure gas. And turbines.

In general, a gas turbine is a type of internal combustion engine that converts thermal energy into mechanical energy by injecting and rotating high-temperature and high-pressure combustion gas generated by combustion after mixing fuel with air compressed at high pressure in a compressor.

Since these gas turbines do not have a reciprocating mechanism such as a piston of a four-stroke engine, there is no mutual friction part such as a piston-cylinder, so the consumption of lubricating oil is extremely low. There is an advantage.

A gas turbine is a basic element, a compressor that compresses air, a combustor that generates combustion gas by combusting compressed air and fuel supplied from the compressor, and a turbine that generates power by rotating the blades through high-temperature and high-pressure gas emitted from the combustor. Includes.

As related to the combustor, US Patent No. US8220270 discloses a swozzle for mixing fuel and compressed air.

The conventional nozzle for a combustor having a swirler as described above allows compressed air to flow above the nozzle from which fuel is ejected, so that the ejected fuel and compressed air are mixed.

At this time, the guiding part included in the conventional nozzle for a combustor with a swirler is formed on the side of the swirler vane to guide the compressed air flowing along the side of the swirler vane, and uniform compressed air and fuel Mixing function has a limitation that it cannot be performed effectively.

As the fuel and compressed air are evenly mixed, nitrogen oxides or particulate matter are not generated, and the combustion efficiency of the fuel increases, thereby improving the operating efficiency of the gas turbine. Accordingly, there is a need for a nozzle for a combustor that enables fuel and compressed air to be efficiently mixed inside the gas turbine.

US Patent No. 8220270 (registered on July 17, 2012)

An object of the present invention is to provide a nozzle assembly capable of improving mixing efficiency between fuel and air as the swirl vane is rotatably provided and a gas turbine including the same.

The technical problem to be achieved by the present invention is not limited to the technical problems mentioned above, and other technical problems that are not mentioned can be clearly understood by those of ordinary skill in the technical field to which the present invention belongs from the following description. There will be.

An embodiment of the present invention for solving the above problems is a nozzle body, a shroud surrounding the nozzle body, a plurality of swirl vanes provided to be spaced apart in a circumferential direction on a side surface of the nozzle body, and the plurality of A plurality of fuel injection holes provided on each side of each swirl vane to inject fuel, and a fuel supply unit supplying fuel to the plurality of fuel injection holes from the inside of the nozzle body, wherein the plurality of swirl vanes It provides a nozzle assembly provided to be rotatable in the circumferential direction with respect to the side.

According to an embodiment of the present invention, the plurality of swirl vanes may be provided on a vane installation part rotatably coupled to a side surface of the nozzle body by a bearing.

According to an embodiment of the present invention, a groove is formed along a circumferential direction on a side surface of the nozzle body, and the vane installation part may be rotatably coupled to the groove by a bearing.

According to an embodiment of the present invention, the fuel supply unit includes a fuel chamber formed inside the vane installation unit, a first fuel supply passage extending along the inside of the nozzle body and communicating with the fuel chamber, and the fuel chamber. It may include a second fuel supply passage for supplying fuel to the plurality of fuel injection holes in communication with the plurality of fuel injection holes.

According to an embodiment of the present invention, a grid member may be provided between the nozzle body and the shroud.

According to an embodiment of the present invention, the grid member may be provided at the front end of the plurality of swirl vanes.

According to an embodiment of the present invention, each of the plurality of swirl vanes may be formed in an airfoil shape, and may be provided at a side of the nozzle body in a state that is twisted by a predetermined angle with respect to the axial direction of the nozzle body. .

According to an embodiment of the present invention, the plurality of fuel injection holes are provided on a pressure surface in each of the plurality of swirl vanes, and a trail forming a rear end along the direction of air flowing into the passage between the nozzle body and the shroud It may be provided closer to the leading edge forming the shear than the ring edge.

According to an embodiment of the present invention, each of the plurality of swirl vanes has a flat portion formed parallel to the direction of air flowing into the passage between the nozzle body and the shroud, and bends in one direction from the rear end of the flat portion. It may include a bent portion to be formed.

According to an embodiment of the present invention, the plurality of fuel injection holes may be provided on a side surface of the flat portion of each of the plurality of swirl vanes, and may be provided closer to a front end than to a rear end adjacent to the bent portion.

In addition, an embodiment of the present invention for solving the above problem is provided with a compressor for inhaling air and compressing it at high pressure, and a nozzle assembly for a combustor for mixing compressed air and fuel supplied from the compressor, It provides a gas turbine comprising a combustor for generating an electric power and a turbine generating electric power by obtaining rotational force by the combustion gas transmitted from the combustor. Here, the combustor may include the nozzle assembly according to the above embodiment.

According to the present invention, as the swirl vane is provided to be rotatable in a circumferential direction with respect to the side surface of the nozzle body, the mixing efficiency between fuel and air can be improved.

Ultimately, since the fuel and air can be uniformly mixed, nitrogen oxides or particulate matter are not generated, the combustion efficiency of the fuel is increased, and the operation efficiency of the gas turbine is improved.

The effects of the present invention are not limited to the above effects, and should be understood to include all effects that can be inferred from the configuration of the invention described in the detailed description or claims of the present invention.

1 is a cross-sectional view showing a gas turbine according to an embodiment of the present invention.
Figure 2 is a cross-sectional view showing a combustor included in the gas turbine of Figure 1;
3 is a cross-sectional view showing a separate nozzle assembly for a combustor included in the combustor of FIG. 2;
Figure 4 is a perspective view showing a nozzle assembly excluding the shroud in Figure 3;
5 is a perspective view showing one swirl vane separated from FIG. 4.
6 is a perspective view showing a separate swirl vane of the nozzle assembly according to another embodiment of the present invention.

Hereinafter, preferred embodiments of the nozzle assembly of the present invention and a gas turbine including the same will be described with reference to the accompanying drawings.

In addition, terms to be described later are terms defined in consideration of functions in the present invention, which may vary according to the intention or custom of users and operators, and the following examples do not limit the scope of the present invention, It is merely exemplary of the elements presented in the claims.

In order to clearly describe the present invention, parts irrelevant to the description have been omitted, and the same reference numerals are assigned to the same or similar components throughout the specification. Throughout the specification, when a certain part "includes" a certain component, it means that other components may be further provided without excluding other components unless otherwise stated.

First, a configuration of a gas turbine according to an embodiment of the present invention will be described with reference to FIGS. 1 and 2.

The gas turbine 1 according to an embodiment of the present invention comprises a casing 10, a compressor 20 for sucking air and compressing it to a high pressure, and the air compressed by the compressor 20 to fuel and It may include a combustor 30 for mixing and combusting, and a turbine 40 generating electric power by obtaining a rotational force by the combustion gas transmitted from the combustor 30.

The casing 10 includes a compressor casing 12 accommodating the compressor 20, a combustor casing 13 accommodating the combustor 30, and a turbine casing 14 accommodating the turbine 40 can do. Here, the compressor casing 12, the combustor casing 13, and the turbine casing 14 may be sequentially arranged from an upstream side in a fluid flow direction to a downstream side.

A rotor (center shaft) 50 is rotatably provided inside the casing 10, and a generator (not shown) is interlocked with the rotor 50 for power generation, and the turbine is located at the downstream side of the casing 10. A diffuser for discharging the combustion gas passing through 40 may be provided.

The rotor 50 is accommodated in a compressor rotor disk 52 accommodated in the compressor casing 12, a turbine rotor disk 54 accommodated in the turbine casing 14, and the combustor casing 13, and the compressor A torque tube 53 connecting the rotor disk 52 and the turbine rotor disk 54, the compressor rotor disk 52, the torque tube 53, and a tie rod fastening the turbine rotor disk 54 ( 55) and a fixing nut 56 may be included.

The compressor rotor disk 52 may be formed in a plurality (for example, 14 sheets), and the plurality of compressor rotor disks 52 may be arranged along the axial direction of the rotor 50. That is, the compressor rotor disk 52 may be formed in multiple stages. In addition, each of the compressor rotor disks 52 may be formed in a substantially disk shape, and a compressor blade coupling slot coupled to a compressor blade 22 to be described later may be formed at an outer circumference.

The turbine rotor disk 54 may be formed similar to the compressor rotor disk 52. That is, the turbine rotor disk 54 may be formed in plural, and the plurality of turbine rotor disks 54 may be arranged along the axial direction of the rotor 50. That is, the turbine rotor disk 54 may be formed in multiple stages. In addition, each of the turbine rotor disks 54 may be formed in a substantially disk shape, and a turbine blade coupling slot coupled to a turbine blade 42 to be described later may be formed at an outer peripheral portion.

The torque tube 53 is a torque transmission member that transmits the rotational force of the turbine rotor disk 54 to the compressor rotor disk 52, and one end is the highest in the flow direction of air among the plurality of compressor rotor disks 52. It is coupled to a compressor rotor disk positioned at a downstream end, and the other end may be coupled to a turbine rotor disk positioned at an uppermost end in the flow direction of the combustion gas among the plurality of turbine rotor disks 54. Here, a protrusion is formed in each of one end and the other end of the torque tube 53, and a groove engaging with the protrusion is formed in each of the compressor rotor disk 52 and the turbine rotor disk 54, and the torque tube Relative rotation of 53 to the compressor rotor disk 52 and the turbine rotor disk 54 can be prevented.

In addition, the torque tube 53 may be formed in a hollow cylinder shape so that air supplied from the compressor 20 can pass through the torque tube 53 and flow to the turbine 40. At this time, the torque tube 53 is strongly formed in deformation and distortion due to the characteristics of a gas turbine that is continuously operated for a long period of time, and can be easily assembled and disassembled for easy maintenance.

The tie rod 55 is formed to pass through the plurality of compressor rotor disks 52, the torque tube 53, and the plurality of turbine rotor disks 54, and one end of the plurality of compressor rotor disks 52 Based on the turbine rotor disk, which is fastened in the compressor rotor disk located at the uppermost end in the flow direction of the heavy air, and the other end is located at the lowest end in the flow direction of the combustion gas among the plurality of turbine rotor disks 54. It protrudes to the opposite side of the compressor 20 and may be fastened with the fixing nut 56.

Here, the fixing nut 56 pressurizes the turbine rotor disk 54 located at the lowermost end toward the compressor 20, and the compressor rotor disk 52 located at the uppermost end and the lowermost end As the distance between the positioned turbine rotor disks 54 decreases, a plurality of the compressor rotor disks 52, the torque tubes 53, and the plurality of turbine rotor disks 54 increase in the axial direction of the rotor 50 Can be compressed into Accordingly, the axial movement and relative rotation of the plurality of compressor rotor disks 52, the torque tube 53, and the plurality of turbine rotor disks 54 can be prevented.

Meanwhile, in the present embodiment, one tie rod is formed to pass through the centers of the plurality of compressor rotor disks, the torque tube, and the plurality of turbine rotor disks, but is not limited thereto. That is, separate tie rods may be provided on the compressor side and the turbine side, respectively, and a plurality of tie rods may be radially disposed along the circumferential direction, and a mixture thereof may be used.

The rotor 50 according to this configuration may have both ends rotatably supported by bearings, and one end may be connected to a drive shaft of the generator.

The compressor 20 includes a compressor blade 22 rotated together with the rotor 50 and a compressor vane 24 installed in the compressor casing 12 to align the flow of air introduced into the compressor blade 22. ) Can be included.

The compressor blade 22 is formed in plural, the plurality of compressor blades 22 are formed in a plurality of stages along the axial direction of the rotor 50, and the plurality of compressor blades 22 are formed in each stage. It may be formed radially along the rotation direction of the rotor 50.

That is, the root portion 22a of the compressor blade 22 is coupled to the compressor blade coupling slot of the compressor rotor disk 52, and the root portion 22a is the compressor blade 22 is the compressor blade coupling slot. It may be formed in a fir-tree shape to prevent the rotor 50 from being separated from the rotor in the radial direction of rotation. In this case, the compressor blade coupling slot may be formed in a fir shape so as to correspond to the root portion 22a of the compressor blade.

In the present embodiment, the compressor blade root portion 22a and the compressor blade coupling slot are formed in a fir shape, but are not limited thereto and may be formed in a dovetail shape. Alternatively, the compressor blade may be fastened to the compressor rotor disk by using a fastening device other than the above, for example, a fastener such as a key or a bolt.

Here, the compressor rotor disk 52 and the compressor blade 22 are typically combined in a tangential type or an axial type. In this embodiment, the compressor blade root portion 22a ) Is formed in a so-called axial type shape that is inserted in the compressor blade coupling slot along the axial direction of the rotor 50 as described above. Accordingly, a plurality of the compressor blade coupling slots according to the present embodiment may be formed, and the plurality of compressor blade coupling slots may be radially arranged along the circumferential direction of the compressor rotor disk 52.

The compressor vanes 24 may be formed in plural, and the plurality of compressor vanes 24 may be formed in a plurality of stages along the axial direction of the rotor 50. Here, the compressor vanes 24 and the compressor blades 22 may be alternately arranged along the air flow direction. In addition, the plurality of compressor vanes 24 may be radially formed in each stage along the rotation direction of the rotor 50.

The combustor 30 mixes and combusts the air introduced from the compressor 20 with fuel to produce a high-energy high-temperature and high-pressure combustion gas, and burns to a heat resistance limit that the combustor and the turbine can withstand through an isostatic combustion process. It may be formed to increase the gas temperature.

Specifically, the combustor 30 may be formed in plural, and the plurality of combustors 30 may be arranged in the combustor casing along the rotation direction of the rotor 50.

Each of the combustors 30 includes a liner 32 through which air compressed by the compressor 20 is introduced, and a transition piece 34 located at the rear of the liner 32 to guide the combustion gas to the turbine 40. ). The liner 32 and the transition piece 34 form a combustion chamber therein, and the sleeve 36 is disposed to surround the liner 32 and the transition piece 34 to form an annular flow space therebetween. do.

In addition, each of the combustors 30 includes a combustor nozzle assembly 1000 for mixing fuel with compressed air supplied from the compressor 20, and the nozzle assembly 1000 is in front of the liner 32 Can be combined. The nozzle assembly 1000 will be described in detail below.

As described above, compressed air introduced from the compressor 20 moves into the combustion chamber while being mixed with fuel through the nozzle assembly 1000, and combustion is ignited by a spark plug (not shown) in the combustion chamber. It happens. Thereafter, the burned gas is discharged to the turbine 40 to generate rotation.

At this time, cooling the liner 32 and the transition piece 34 exposed to the high temperature and high pressure combustion gas is an important part for increasing the durability of the combustor. To this end, a cooling hole is formed in the sleeve 36 so that compressed air flowing through the cooling hole vertically collides with the outer wall portion of the liner 32 and the transition piece 34, so that the liner 32 and the transition Let the piece 34 cool.

Specifically, compressed air introduced from the compressor 20 flows into the annular space through a cooling hole formed in the sleeve 36 to cool the liner 32 and the transition piece 34, and the liner along the annular space It flows to the front of (32), after reaching the end plate side and changing the direction, it may be introduced into the inlet of the nozzle assembly (100).

Next, the turbine 40 may be formed similar to the compressor 20. The turbine 40 includes a turbine blade 42 rotated together with the rotor 50 and a turbine vane fixedly installed on the turbine casing 14 to align the flow of air flowing into the turbine blade 42 ( 44) may be included.

The turbine blade 42 is formed in plural, the plurality of turbine blades 42 are formed in a plurality of stages along the axial direction of the rotor 50, and the plurality of turbine blades 42 are formed in each stage. It may be formed radially along the rotation direction of the rotor 50.

That is, the root portion (42a) of the turbine blade (42) is coupled to the turbine blade coupling slot of the turbine rotor disk (54), the root portion (42a), the turbine blade (42) is the turbine blade coupling slot It may be formed in a fir-tree shape to prevent the rotor 50 from being separated from the rotor in the radial direction of rotation. In this case, the turbine blade coupling slot may be formed in a fir shape so as to correspond to the root portion 42a of the turbine blade.

The turbine vanes 44 may be formed in plural, and the plurality of turbine vanes 44 may be formed in a plurality of stages along the axial direction of the rotor 50. Here, the turbine vanes 44 and the turbine blades 42 may be alternately arranged along the air flow direction. In addition, the plurality of turbine vanes 44 may be radially formed along the rotation direction of the rotor 50 for each stage.

Here, the turbine 40, unlike the compressor 20, is in contact with the high-temperature and high-pressure combustion gas, and thus requires a cooling means to prevent damage such as deterioration. To this end, a cooling passage for extracting compressed air from some portions of the compressor 20 and supplying it to the turbine 40 may be included.

The cooling flow path may extend outside the casing 10 (external flow path) or extend through the inside of the rotor 50 (internal flow path), and both the external flow path and the internal flow path may be You can also use it.

In this case, the cooling passage is in communication with a turbine blade cooling passage formed in the inside of the turbine blade 42, so that the turbine blade 42 may be cooled by cooling air. In addition, the turbine blade cooling passage is in communication with the turbine blade film cooling hole formed on the surface of the turbine blade 42, and cooling air is supplied to the surface of the turbine blade 42, so that the turbine blade 42 is The so-called membrane can be cooled by cooling air. The turbine vane 44 may also be formed to be cooled by receiving cooling air from the cooling passage, similar to the turbine blade 42.

Here, the gas turbine is only an embodiment of the present invention, and the nozzle assembly of the present invention, which will be described in detail below, can be widely applied not only to a general gas turbine but also to a jet engine in which air and fuel are combusted.

Hereinafter, a nozzle assembly 1000 according to an embodiment of the present invention will be described with reference to FIGS. 3 to 5. As described above, the combustion nozzle assembly 1000 provided in the combustor 30 mixes the fuel supplied from an external fuel tank (not shown) in which the fuel is stored with the compressed air supplied from the compressor 20. This is transmitted to the inside of the combustion chamber.

The nozzle assembly 1000 according to an embodiment of the present invention is largely composed of a nozzle body 100, a shroud 200, a plurality of swirl vanes 300, a plurality of fuel injection holes 320, and a fuel supply unit 400. ) Can be included. In the present invention, the plurality of swirl vanes 300 are provided to be rotatable in a circumferential direction with respect to the side surface of the nozzle body 100, which will be described in detail below.

The nozzle body 100 has a cylinder shape having a predetermined diameter, and a fuel supply hole 112 for receiving fuel from the outside so as to flow into the nozzle body 100 and an axial direction of the nozzle body 100. A plurality of air supply holes 114 for supplying compressed air of high pressure toward the air may be formed.

The plurality of air supply holes 114 are opened toward the plurality of swirl vanes 300, and a plurality of them are arranged along the circumferential direction to receive a large amount of compressed air from the compressor 20 to receive a plurality of swirl vanes 300 ) Can be supplied.

The shroud 200 has a cylindrical shape and is provided to surround the nozzle body 100, whereby the nozzle body 100 is located at the inner center of the shroud 200.

The plurality of swirl vanes 300 are spaced apart along the circumferential direction on the side of the nozzle body 100 and disposed in a radial form, and a plurality of fuel injections through which fuel is injected on each side of the plurality of swirl vanes 300 Hole 320 is formed.

At this time, in order to allow the plurality of swirl vanes 300 to be rotatable in a circumferential direction with respect to the side surface of the nozzle body 100, the plurality of swirl vanes 300 are disposed on the side surfaces of the nozzle body 100. It is provided on the vane installation portion 120 rotatably coupled to the bearing. That is, the plurality of swirl vanes 300 are disposed on the vane installation unit 120 in a radial form along the circumferential direction.

The vane installation part 120 is formed in a cylindrical shape and is installed to be rotatable in a circumferential direction with respect to the outer circumferential surface of the nozzle body 100. In this embodiment, a groove 102 is formed along the circumferential direction on the side of the nozzle body 100, and the vane installation part 120 is rotatably coupled to the groove 102 by a bearing 104 .

At this time, the plurality of swirl vanes 300 are provided in a state that is twisted by a predetermined angle with respect to the axial direction of the nozzle body 100 so that they can be rotated by compressed air supplied to the swirl vanes. That is, as shown in FIG. 4, as the plurality of swirl vanes 300 are not disposed parallel to the axial direction of the nozzle body 100 but are distorted by a certain angle, the plurality of swirl vanes 300 It can be rotated in the direction of the arrow by the force of compressed air passing through.

In this embodiment, each of the plurality of swirl vanes 300 may be formed in an airfoil shape. Specifically, as shown in FIG. 5, each of the plurality of swirl vanes 300 has a pressure surface 301, a suction surface 302, a leading edge 303, and a trailing edge ( 304), and the pressure surface 301 corresponds to an upper surface formed to be rounded toward the outside, and the suction surface 302 corresponds to a flat lower surface. In addition, the front portion facing the supplied compressed air corresponds to the leading edge 303, and the rear portion having the thinnest thickness corresponds to the trailing edge 304. However, it is not limited thereto, and the shape of the swirl vane can be variously modified.

At this time, the plurality of fuel injection holes 320 are provided on the pressure surface 301 in each of the plurality of swirl vanes 300, and are compressed to flow into the passage between the nozzle body 100 and the shroud 200. It is preferable to be provided closer to the leading edge 303 forming the front end than the trailing edge 304 forming the rear end along the direction of the air. That is, a plurality of fuel injection holes 320 are disposed on the pressure surface 301 to be spaced apart at predetermined intervals along the width direction of the swirl vane 300.

Accordingly, the compressed air supplied to the swirl vane 300 moves from the leading edge 303 to the trailing edge 304 along the pressure surface 301 and the suction surface 302 of the swirl vane 300. It is mixed with the fuel discharged from the fuel injection hole 320 and then moved downward in the axial direction of the nozzle body 100 in the form of a mixed gas.

In this way, the plurality of swirl vanes 300 are provided on the outer circumferential surface of the nozzle body 100 at a certain angle with respect to the axial direction of the nozzle body 100 so that compressed air is supplied to the swirl vanes 300 If so, it not only causes a flow of fluid that moves in a spiral shape along the axial direction of the nozzle body 100, but also causes a larger swirl flow (turbulence) because the plurality of swirl vanes 300 are rotated. The mixing efficiency of the liver can be improved.

Next, the inside of the nozzle body 100 by receiving fuel from the outside so that the fuel for mixing with compressed air can be discharged from the fuel injection hole 320 provided in each of the plurality of swirl vanes 300. The fuel supply unit 400 for supplying fuel to the plurality of fuel injection holes 320 will be described.

Referring to FIG. 3, the fuel supply unit 400 includes a fuel chamber 430 formed inside the vane installation unit 120 and the fuel chamber 430 by extending along the inside of the nozzle body 100. ) And a second fuel for supplying fuel to the plurality of fuel injection holes 320 by being in communication with the first fuel supply passage 410 and the fuel chamber 430 to the plurality of fuel injection holes 320 It may include a supply channel 420.

The first fuel supply passage 410 extends in a longitudinal direction from the fuel supply hole 112 for receiving fuel from the outside into the inside of the nozzle body 100 and communicates with the fuel chamber 430. The fuel chamber 430 is formed to have a space in the circumferential direction inside the vane installation unit 120, so that even if the vane installation unit 120 rotates, fuel continuously from the first fuel supply passage 410 Can be supplied. In addition, the second fuel supply passage 420 is in the inside of the swirl vane 300 along the plurality of fuel injection holes 320 so that all of the plurality of fuel injection holes 320 communicate with each other from the fuel chamber 430. Is formed to extend. In this case, the second fuel supply passage 420 may be designed such that the further away from the fuel chamber 430, the smaller the passage of the second fuel supply passage 420 is, considering that the supply pressure of the fuel decreases.

Moreover, a grid member 500 may be provided between the nozzle body 100 and the shroud 200. In particular, the grid member 500 may be provided at the front end of the plurality of swirl vanes 300.

The grid member 500 has both ends fixed to the nozzle body 100 and the shroud 200, respectively, to support the shroud 200 so as to be spaced apart from the nozzle body 100, and at the same time, the plurality of swirl vanes ( It distributes the compressed air supplied to 300) to be uniform.

Next, a nozzle assembly according to another embodiment of the present invention will be described with reference to FIG. 6. Here, only the shapes of the nozzle assembly 1000 and the swirl vane described above are different, and the remaining configurations are the same, so that only different parts will be described.

In this embodiment, each of the plurality of swirl vanes 1300 includes a flat portion 1301 formed parallel to the direction of air flowing into the passage between the nozzle body 100 and the shroud 200, and the flat portion 1301 It may include a bending portion 1302 formed to bend in one direction from the rear end of the portion 1301.

In this embodiment, a plurality of fuel injection holes 1320 formed in each of the plurality of swirl vanes 1300 may be formed on both sides of the flat portion 1301, and may be formed in front of the rear end adjacent to the bent portion 1302 It is preferable to be provided closer to.

Accordingly, the compressed air supplied to the swirl vane 1300 is mixed with the fuel discharged from the fuel injection hole 1320 while moving to the bent part 1302 along both sides of the flat part 1301 and then mixed. It is moved downward in the axial direction of the nozzle body 100 in the form of a gas.

At this time, the flat part 1301 is arranged in parallel with the axial direction of the nozzle body 100, but is twisted at a certain angle with respect to the axial direction of the nozzle body 100 by the bending part 1302 at the rear end. Accordingly, likewise, it may be rotated in the direction of the arrow by the force of compressed air passing through the plurality of swirl vanes 1300. However, the present invention is not limited thereto, and the flat portion may also be disposed to be distorted by a predetermined angle with respect to the axial direction of the nozzle body 100.

In this way, when compressed air is supplied to the swirl vane 1300, not only does it cause a flow of fluid that is helically moved along the axial direction of the nozzle body 100 by the bend part 1302, but also causes the plurality of swirls. Since the vane 1300 is rotated, a larger swirl flow (turbulence) can be induced, thereby improving the mixing efficiency between fuel and air.

According to the present invention, since the swirl vane 300 is provided to be rotatable in a circumferential direction with respect to the side surface of the nozzle body 100, the mixing efficiency between fuel and air may be improved.

Ultimately, since the fuel and air can be uniformly mixed, nitrogen oxides or particulate matter are not generated, the combustion efficiency of the fuel is increased, and the operation efficiency of the gas turbine is improved.

The present invention is not limited to the specific embodiments and description described above, and any person with ordinary knowledge in the technical field to which the present invention pertains without departing from the gist of the present invention claimed in the claims can implement various modifications And, such modifications are within the scope of the present invention.

1: gas turbine 10: casing
12: compressor casing 13: combustor casing
14: turbine casing 20: compressor
22: compressor blade 22a: compressor blade root portion
24: compressor vane 30: combustor
32: liner 34: transition piece
36: sleeve 40: turbine
42: turbine blade 42a: turbine blade root portion
44: turbine vane 50: rotor
52: compressor rotor disk 53: torque tube
54: turbine rotor disk 55: tie rod
56: fixing nut
100: nozzle body 102: groove
104: bearing 112: fuel supply hole
114: air supply hole 120: vane installation part
200: shroud 300: swirl vane
301: pressure surface 302: suction surface
303: leading edge 304: trailing edge
320: fuel injection hole 400: fuel supply unit
410: first fuel supply passage 420: second fuel supply passage
430: fuel chamber 500: grid member
1000: nozzle assembly
1300: swirl vane 1301: flat part
1302: bending part 1320: fuel injection hole

Claims (20)

Nozzle body;
A shroud surrounding the nozzle body;
A plurality of swirl vanes provided to be spaced apart in a circumferential direction on a side surface of the nozzle body;
A plurality of fuel injection holes provided on side surfaces of each of the plurality of swirl vanes to inject fuel; And
Includes; a fuel supply unit for supplying fuel to the plurality of fuel injection holes from the inside of the nozzle body,
The plurality of swirl vanes are provided to be rotatable in a circumferential direction with respect to the side surface of the nozzle body,
A grid member is provided between the nozzle body and the shroud, wherein the grid member is provided at a front end of the plurality of swirl vanes and uniformly distributes air supplied to the plurality of swirl vanes,
The plurality of swirl vanes are provided on a vane installation portion rotatably coupled to a side surface of the nozzle body by a bearing,
The fuel supply unit,
A fuel chamber formed inside the vane installation part;
A first fuel supply passage extending along the inside of the nozzle body and communicating with the fuel chamber; And
A second fuel supply passage communicating from the fuel chamber to the plurality of fuel injection holes to supply fuel to the plurality of fuel injection holes; and
A nozzle assembly, characterized in that the second fuel supply flow path becomes narrower as the second fuel supply flow path is further away from the fuel chamber. delete The method of claim 1,
A groove is formed along a circumferential direction on a side surface of the nozzle body, and the vane installation part is rotatably coupled to the groove by a bearing. delete delete delete The method of claim 1,
Each of the plurality of swirl vanes has an airfoil shape, and is provided on a side surface of the nozzle body in a state that is twisted by a predetermined angle with respect to the axial direction of the nozzle body. The method of claim 7,
The plurality of fuel injection holes are provided on a pressure surface in each of the plurality of swirl vanes, and at a leading edge forming a front end rather than a trailing edge forming a rear end along the direction of air flowing into the passage between the nozzle body and the shroud. Nozzle assembly provided closer. The method of claim 1,
Each of the plurality of swirl vanes includes a flat portion formed parallel to the direction of air flowing into the passage between the nozzle body and the shroud, and a bent portion formed to bend in one direction from the rear end of the flat portion. . The method of claim 9,
The plurality of fuel injection holes are provided on side surfaces of the flat portion in each of the plurality of swirl vanes, and are provided closer to a front end than to a rear end adjacent to the bent portion. A compressor that sucks air and compresses it at high pressure;
A combustor comprising a nozzle assembly for a combustor for mixing fuel and compressed air supplied from the compressor, and generating combustion gas; And
Includes; a turbine generating electric power by obtaining rotational force by the combustion gas transmitted from the combustor,
The combustion nozzle assembly,
Nozzle body;
A shroud surrounding the nozzle body;
A plurality of swirl vanes provided to be spaced apart in a circumferential direction on a side surface of the nozzle body;
A plurality of fuel injection holes provided on side surfaces of each of the plurality of swirl vanes to inject fuel; And
Includes; a fuel supply unit for supplying fuel to the plurality of fuel injection holes from the inside of the nozzle body,
The plurality of swirl vanes are provided to be rotatable in a circumferential direction with respect to the side surface of the nozzle body,
A grid member is provided between the nozzle body and the shroud, wherein the grid member is provided at a front end of the plurality of swirl vanes and uniformly distributes the compressed air supplied to the plurality of swirl vanes,
The plurality of swirl vanes are provided on a vane installation portion rotatably coupled to a side surface of the nozzle body by a bearing,
The fuel supply unit,
A fuel chamber formed inside the vane installation part;
A first fuel supply passage extending along the inside of the nozzle body and communicating with the fuel chamber; And
A second fuel supply passage communicating from the fuel chamber to the plurality of fuel injection holes to supply fuel to the plurality of fuel injection holes; and
The second fuel supply flow path, characterized in that the flow path narrows as the distance from the fuel chamber becomes narrower. delete The method of claim 11,
A groove is formed along a circumferential direction on a side surface of the nozzle body, and the vane installation portion is rotatably coupled to the groove by a bearing. delete delete delete The method of claim 11,
Each of the plurality of swirl vanes is formed in an airfoil shape, and is provided on a side surface of the nozzle body in a state that is twisted by a predetermined angle with respect to the axial direction of the nozzle body. The method of claim 17,
The plurality of fuel injection holes are provided on a pressure surface in each of the plurality of swirl vanes, and at a leading edge forming a front end rather than a trailing edge forming a rear end along the direction of air flowing into the passage between the nozzle body and the shroud. Gas turbines that are equipped closer together. The method of claim 11,
Each of the plurality of swirl vanes includes a flat portion formed parallel to the direction of air introduced into the passage between the nozzle body and the shroud, and a bend portion formed to bend in one direction from the rear end of the flat portion. . The method of claim 19,
The plurality of fuel injection holes are provided on side surfaces of the flat portion in each of the plurality of swirl vanes, and are provided closer to a front end than to a rear end adjacent to the bent portion.

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