KR102189499B1 - Combustor and gas turbine including center body formed with end portion of cone shape - Google Patents

Abstract

The present invention relates to a combustor and a gas turbine. The combustor includes: a fuel nozzle disposed in a nozzle tube and having a hollow unit; a center body connected to a nozzle base and disposed in the hollow unit of the fuel nozzle; and a swirler disposed between the inner surface of the fuel nozzle and the outer circumferential surface of the center body. The front end of the center body can be formed in a cone shape of which the cross-sectional area decreases toward the direction of a combustion chamber. According to the present invention, a fuel-air mixing degree can be increased and, at the same time, the front end surface of the center body can be cooled and protected.

Description

Combustor and gas turbine including center body formed with end portion of cone shape}

The present invention relates to a combustor and a gas turbine including a center body in which a cone-shaped end is formed, and more particularly, a front end of the center body of the combustor is formed in a cone shape, and a cooling fluid such as compressed air is sprayed in a diffusion form. It relates to a combustor and a gas turbine capable of cooling and protecting an end surface of a center body while increasing fuel-air mixing by injecting through a hole.

In general, a turbine is a power generating device that converts thermal energy of a fluid such as gas and steam into rotational force, which is mechanical energy, and a rotor including a plurality of rotor blades so as to be axially rotated by the fluid ( It includes a rotor and a casing installed around the rotor and provided with a plurality of diaphragms.

Here, the gas turbine includes a compressor section, a combustor, and a turbine section, and external air is sucked and compressed by the rotation of the compressor section and then sent to the combustor, and combustion is performed by mixing compressed air and fuel in the combustor. The high-temperature and high-pressure gas generated from the combustor passes through the turbine section and rotates the rotor of the turbine to drive the generator.

Among the gas turbine configurations, the combustor injects and mixes fuel with compressed air in the compressor section to cause combustion in the combustion chamber. When supplying fuel mixed with air to the combustion chamber, it is important to increase the air-fuel mixture. When the air-fuel mixing degree is improved, combustion vibration is reduced during combustion in the combustion chamber, and the overall power generation efficiency of the gas turbine is improved.

There is also something as important as improving the fuel-air mix. Since the combustor is operated in a high temperature/high temperature environment, it is necessary to stably cool the combustor parts. Therefore, in the art, structural studies that can effectively cool the combustor parts while increasing the fuel-air mixing degree are continuously underway. have.

US Patent Publication No.: US 2019-0137102 A1

The present invention was conceived to solve the problems in the related art as described above, and an object of the present invention is to form a cone-shaped front end of a center body of a combustor, and to form a diffusion-type injection hole for cooling fluid such as compressed air It is to provide a combustor and a gas turbine capable of cooling and protecting the end surface of the center body while increasing the fuel-air mixing degree by injection through.

The present invention for achieving the above objects relates to a combustor, and further, in an embodiment of the present invention, a fuel nozzle disposed on a nozzle tube and formed with a hollow portion; A center body connected to the nozzle base and disposed in the hollow portion of the fuel nozzle; And a swirler disposed between the inner surface of the fuel nozzle and the outer circumferential surface of the center body, wherein the front end portion of the center body may have a cone shape whose cross-sectional area decreases toward the combustion chamber.

In addition, in an embodiment of the present invention, the center body includes a body frame connected to the nozzle base; A central flow path formed inside the body frame and through which compressed air flows; A cone-shaped portion disposed at the front end of the body frame; And an air injection hole disposed on the cone-shaped portion, connected to the central flow channel, and spraying compressed air.

In addition, in the embodiment of the present invention, the air injection hole may be inclined with respect to the direction of the combustion chamber.

In addition, in an embodiment of the present invention, the center body includes: a partition wall connected to the nozzle base and defining a central flow path through which compressed air flows; And a guide block inserted into the partition wall and configured to guide the flow direction of compressed air flowing through the central flow path.

In addition, in an embodiment of the present invention, a cone-shaped portion is formed at the front end of the guide block, and a protruding block is disposed along the outer circumference adjacent to the cone-shaped portion, and the outer circumference of the protruding block flows in the central passage. One or more air injection slots for injecting compressed air; may be disposed.

In addition, in an embodiment of the present invention, the air injection slot may be formed on the protruding block in the longitudinal direction of the guide block.

Further, in an exemplary embodiment of the present invention, a plurality of air injection slots may be formed on the protruding block along a radial direction, and the air injection slots may be formed to be inclined with respect to the direction of the combustion chamber.

In addition, in an embodiment of the present invention, the mixing degree is increased by increasing turbulence in the compressed air supplied to the combustion chamber by rotating the fuel-air mixture fluid supplied to the combustion chamber and the fuel-air mixture fluid supplied to the combustion chamber and the compressed air supplied to the combustion chamber. Thus, the inclined direction of the air injection slot and the curved direction of the swirler may be formed in opposite directions.

In addition, in an embodiment of the present invention, an inclined portion whose inclination increases from the top to the bottom of the protruding block is formed on the inner surface of the air injection slot so that compressed air is diffused and sprayed outward based on the center of the cone-shaped portion. Can be.

In addition, in an embodiment of the present invention, a curved portion having a curvature increasing from the top to the bottom of the protruding block is formed on the inner surface of the air injection slot so that fuel is diffused and injected in an outward direction based on the center of the cone-shaped portion. I can.

In addition, in an embodiment of the present invention, one or more air injection holes may be disposed around the inner periphery of the protruding block to inject compressed air flowing in the central passage.

In addition, in an embodiment of the present invention, a spiral portion for rotating air may be formed in the air injection hole to rotate and inject compressed air to increase an additional degree of mixing with the fuel-air mixed fluid.

In addition, the gas turbine of the present invention, a casing; A compressor section disposed inside the casing and compressing the introduced air; A combustor connected to the compressor section in the casing and disposed to burn compressed air; A turbine section connected to the combustor in the casing and arranged to generate power using the combusted air; And a diffuser connected to the turbine section inside the casing and disposed to discharge air to the outside.

According to the present invention, the front end portion of the center body of the combustor is formed in a cone shape, and the injection hole for injecting compressed air is disposed in the direction in which it is diffused, so that the degree of fuel-air mixing before entering the combustion chamber can be effectively increased.

In addition, by injecting compressed air with a relatively low temperature to the front end of the center body due to the characteristics of the combustor operating in a high temperature/high temperature environment, it is possible to cool and protect the combustor components.

This ultimately has the effect of increasing the combustion efficiency and extending the service life of the combustor.

1 is a side cross-sectional view showing the general structure of a gas turbine.
2 is a perspective cross-sectional view showing the general structure of a combustor.
Figure 3 is a side cross-sectional view showing a first embodiment of the center body of the present inventors combustor.
Figure 4 is a perspective view of the center body posted in Figure 3;
Figure 5 is a side cross-sectional view showing a second embodiment of the center body of the present inventors combustor.
6 is a perspective view showing one form of the center body posted in FIG. 5.
7 is a perspective view showing another form of the center body posted in FIG. 5.
Figure 8 is a perspective view showing another form of the center body posted in Figure 5;
9 is a perspective view showing another form of the center body posted in FIG. 5.

Hereinafter, preferred embodiments of the combustor and gas turbine according to the present invention will be described in detail with reference to the accompanying drawings.

Prior to the description of the present invention, the configuration of the gas turbine 1 will be described with reference to the drawings.

1, the gas turbine is basically a casing 2 forming the exterior, a compressor section 4 for compressing air, a combuster 10 for burning air, and A turbine section 6 for generating electricity using gas, a diffuser 7 for discharging exhaust gas, and a rotor for transmitting rotational power by connecting the compressor section 4 and the turbine section 6; It can be configured including 3).

Thermodynamically, external air is introduced into the compressor section corresponding to the upstream side of the gas turbine and undergoes adiabatic compression process. Compressed air is introduced into the combustor section and mixed with fuel to undergo an isostatic combustion process, and the combustion gas is introduced into the turbine section corresponding to the downstream side of the gas turbine and undergoes adiabatic expansion process. .

Referring to the air flow direction, the compressor section 4 is positioned in front of the casing 10, and the turbine section 6 is provided in the rear.

Between the compressor section 4 and the turbine section 6, a torque tube 3b for transmitting the rotational torque generated in the turbine section 6 to the compressor section 4 is provided.

The compressor section 4 is provided with a plurality of (for example, 14) compressor rotor disks 4a, and each of the compressor rotor disks 4a is fastened so as not to be spaced apart in the axial direction by a tie rod 3a. do.

The tie rods 3a penetrate the center of each of the compressor rotor disks 4a and are aligned along the axial direction with each other. A flange (not shown) coupled to an adjacent rotor disk to prevent relative rotation is formed in the vicinity of the outer peripheral portion of the compressor rotor disk 4a to protrude in the axial direction.

A plurality of blades 4b (or referred to as buckets) are radially coupled to the outer peripheral surface of the compressor rotor disk 4a. Each of the blades 4b has a dove tail portion (not shown) and is fastened to the compressor rotor disk 4a.

There are two types of fastening methods of the dove tail part: a tangential type and an axial type. This can be selected according to the required structure of a commercial gas turbine. In some cases, the compressor blade 4b may be fastened to the compressor rotor disk 4a by using a fastening device other than the dovetail.

At this time, on the inner circumferential surface of the compressor section 4 of the casing 2, a vane (not shown) (or referred to as a nozzle) for the relative rotational motion of the compressor blade 4b is mounted and disposed on the diaphragm (not shown). I can.

The tie rod (3a) is arranged to pass through the center of the plurality of compressor rotor disks (4a), one end is fastened in the compressor rotor disk (4a) located on the uppermost side, the other end is the torque tube (3b) ) Is fixed.

The shape of the tie rod 3a may have various structures depending on the gas turbine, so it is not necessarily limited to the shape shown in the drawings.

One tie rod (3a) may have a form penetrating the central portion of the compressor rotor disk (4a), a plurality of tie rods (3a) may have a form arranged in a circumferential shape, and a mixture of them is also possible. .

Although not shown, in the compressor of the gas turbine, a vane serving as a guide blade may be installed at the next position of the diffuser in order to adjust the flow angle of the fluid entering the inlet of the combustor to the design flow angle after increasing the pressure of the fluid. It is called desworler.

The combustor 10 mixes and combusts the introduced compressed air with fuel to produce high-energy high-temperature, high-pressure combustion gas, and heat-resistant components of the combustor 10 and the turbine section 6 can withstand through an isostatic combustion process. The combustion gas temperature is raised to the limit.

A number of combustors 10 constituting the combustion system of the gas turbine may be arranged in a casing 2 formed in a cell shape.

The structure of the combustor 10 will be described in detail below with reference to FIG. 2.

On the other hand, in general, in the turbine section 6, the high-temperature and high-pressure combustion gas from the combustor 10 expands, and impulses and reaction forces are applied to the rotor blades of the turbine section 6 to convert them into mechanical energy.

The mechanical energy obtained from the turbine section 6 is supplied as the energy required to compress the air in the compressor section 4 and the rest is used to drive the generator to produce power.

The turbine section 6 is configured by alternately arranging and forming a plurality of stator blades and rotor blades in a vehicle cabin, and drives the rotor blades by combustion gas to rotate the output shaft to which the generator is connected.

For this purpose, the turbine section 6 is equipped with a plurality of turbine rotor disks 6a. Each of the turbine rotor disks 6a basically has a shape similar to that of the compressor rotor disk 4a.

The turbine rotor disk 6a also includes a flange (not shown) provided for coupling with the adjacent turbine rotor disk 6a, and includes a plurality of turbine blades 6b (or referred to as buckets) arranged radially. do. The turbine blade 6b may also be coupled to the turbine rotor disk 6a in a dovetail manner.

At this time, on the inner circumferential surface of the turbine section 6 of the casing 2, a vane (not shown) (or referred to as a nozzle) for the relative rotational motion of the turbine blade 6b is mounted and disposed on the diaphragm (not shown). I can.

In the gas turbine having the structure as described above, the introduced air is compressed in the compressor section 4, burned in the combustor 10, and then moved to the turbine section 6 to generate power and drive the diffuser 7 It is discharged into the atmosphere through.

Here, the torque tube 3b, the compressor rotor disk 4a, the compressor blade 4b, the turbine rotor disk 6a, the turbine blade 6b, the tie rod 3a, etc. are integrally rotated as rotating components. 3) or may be referred to as a rotating body. In addition, the casing 2, vanes (not shown), diaphragms (not shown), etc. are non-rotating components and may be integrally referred to as a stator or a fixture.

A general type of structure for a gas turbine is as described above, and the present invention applied to such a gas turbine will be described below.

2 is a longitudinal cut perspective view of the combustor. The combustor 10 surrounds the burner casing 11 surrounding the fuel nozzles 15 and 17 constituting the burner 10a, the liner 31 forming the combustion chamber 31a, and the liner 31 in an annular shape. An inexpensive flow sleeve 35, and a transition piece 33, which is a connection portion between the combustor 10 and the turbine section 6, and a flow sleeve 35 surrounding the transition piece 33 in an annular shape are constituted.

The liner 31 provides a combustion chamber 31a in which fuel injected by the fuel nozzles 15 and 17 is mixed and combusted with compressed air introduced therein. The liner 31 may cool the liner 31 through the compressed air flow path 32 by the flow sleeve 35 forming an annular space on the outer periphery. Fuel nozzles 15 and 17 are coupled to the front end of the liner 31.

On the other hand, at the rear end of the liner 31, a transition piece 33 is connected to send the combustion gas burned by the spark plug to the turbine section. The liner 31 and the transition piece 33 are annular space formed by the liner 31 and the flow sleeve 35 wrapped around the transition piece 33, that is, a compressed air flow path ( It is cooled by compressed air supplied to 32,34).

The plurality of fuel nozzles 18 are annularly enclosed in a burner casing 11 functioning as a housing, and are connected to the liner 31. A cylindrical member having a plurality of openings may be inserted into the portion where the plurality of fuel nozzles 18 are connected to the liner 31, and the cylindrical member includes a nozzle tube ( 13). A plurality of openings formed in the nozzle tube 13 functions as a fuel nozzle 18, and the fuel nozzle 18 may be composed of a central nozzle 17 and a plurality of peripheral nozzles 15 surrounding the nozzle tube. .

The fuel nozzle 18 is configured to surround the center body 100 extending from the center of the cylindrical space in the front-rear direction of the combustor. One end of the center body 100 is connected to the nozzle base 12 to receive fuel therefrom, and this fuel is a fuel injection opening formed around the swirler 19 and/or the center body 100 (not shown). Si) can be sprayed and mixed with compressed air. In the present invention, a fuel injection opening (not shown) is formed on the swirler 19. It should be noted that the location and shape of the fuel nozzle to which fuel is supplied are not limited to the shape shown in FIG. 2, and the drawings are only examples.

The nozzle base 12 is connected to the end cover 22, and the end cover 22 may include a configuration for at least partially receiving fuel.

Hereinafter, features of the present invention will be described in detail.

3 is a side cross-sectional view showing a first embodiment of the center body 100 of the combustor 10 according to the present invention.

Referring to FIG. 3, in the first embodiment of the combustor 10 according to the present invention, a fuel nozzle 18, a center body 100, and a swirler 19 may be included.

First, a plurality of fuel nozzles 18 may be arranged in the nozzle tube 13 and may be in the form of a tube in which a hollow part is formed. In addition, the center body 100 may be connected to the nozzle base 12 and disposed in a form extending into the hollow portion of the fuel nozzle 18. The center body 100 may be provided with a number corresponding to the number of fuel nozzles 18.

The swirler 19 may be disposed between the inner surface of the fuel nozzle 18 and the outer surface of the center body 100. The swirler 19 may have a curve formed in a specific direction so that compressed air rotates and flows into the combustion chamber 31a through the hollow portion of the fuel nozzle 18, and a fuel injection hole (not shown) in the swirler 19 In this arrangement, fuel is injected into compressed air to form a fuel-air mixed fluid (A).

Here, the front end of the center body 100 may be formed in a cone shape whose cross-sectional area is reduced toward the combustion chamber 31a. The fuel-air mixed fluid (A) that is swirled and flows through the swirler (19) gradually expands along the cone shape at the front end of the center body (100) and is supplied to the combustion chamber (31a). In other words, the turbulence of the mixed fluid (A) increases, and the fuel-air mixing degree increases.

The center body 100 may include a body frame 110, a central passage 112, a cone-shaped portion 116, and an air injection hole 114.

First, the body frame 110 may be configured in the shape of a tube connected to the nozzle base 12, and the central flow path 112 may be formed inside the body frame 110 and provided to allow air to flow. At this time, on the body frame 110, a compressed air inlet (not shown) is provided at a portion adjacent to the nozzle base 12 so that a part of the compressed air introduced from the compressor section 10 can flow into the interior of the central flow channel 112. Can be formed.

Next, the cone-shaped part 116 may be formed at the front end of the body frame 110, and as described above, it functions to diffuse the mixed fluid A that passes through the swirler 19 and rotates.

At this time, the air injection hole 114 is disposed in the cone-shaped portion 116 and is connected to the central passage 112, and may be provided to inject compressed air (B) in the mixed fluid (A) direction. In addition, since the air injection hole 114 is disposed inclined with respect to the direction of the combustion chamber 31a, it is injected in the flow direction of the mixed fluid A, so that the mixed fluid A can be naturally mixed while minimizing flow disturbance.

Here, since the cone-shaped part 116 is adjacent to the combustion chamber 31a, it is exposed to a high temperature/high temperature environment during combustion, and the compressed air B injected from the air injection hole 114 is relatively low temperature. It serves to cool the surface of the cone-shaped portion 116.

This allows the mixed fluid (A) to diffuse from the periphery of the cone-shaped portion 116, so that the compressed air (B) injected from the air injection hole 114 along the flow flows along the surface of the cone-shaped portion 116 to cool It will work.

On the other hand, although the fluid supplied from the central flow path 112 is limited to compressed air, it may be changed to supply a mixed fluid in which air and fuel are mixed according to design purposes. In this case, although not shown in the drawing, fuel is supplied through the nozzle base 12, and part of the compressed air is supplied in a mixed state by being introduced through the inlet (not shown) formed on the body frame 110. Can be.

In the first embodiment of the combustor 10 according to the present invention, the fuel-air mixing degree is increased through the above structure and the effect of cooling and protecting the front end surface of the center body 100 is achieved.

5 is a side cross-sectional view showing a second embodiment of the center body 100 of the combustor 10 according to the present invention.

Referring to FIG. 5, in the second embodiment of the combustor 10 according to the present invention, a fuel nozzle 18, a center body 100, and a swirler 19 may be included. Since the basic description of the fuel nozzle 18, the center body 100 and the swirler 19 is the same as in the first embodiment. It will be omitted below.

In the second embodiment of the combustor 10 according to the present invention, the center body 100 may include a partition wall 120, a guide block 130, a protrusion block 132, and an air injection slot 140.

First, the partition wall 120 is connected to the nozzle base 12, and a central flow path 122 through which compressed air B flows may be formed. Here, in the partition wall 120, a compressed air inlet (not shown) may be formed in a portion adjacent to the nozzle base 12 so that a part of the compressed air supplied from the compressor section may flow into the central passage 122.

Next, the guide block 130 may be inserted and disposed inside the partition wall 120 and provided to guide the flow direction of the compressed air B flowing through the central passage 122. At this time, a cone-shaped portion 134 may be formed at a front end of the guide block 130, and the protruding block 132 may be disposed along an outer circumference at a portion adjacent to the cone-shaped portion 134.

In addition, one or more air injection slots 140 for injecting compressed air (B) flowing in the central flow path 122 in the direction of the fuel-air mixed fluid (A) may be disposed around the outer periphery of the protruding block 132. .

The cone-shaped part 134 is formed at the front end of the guide block 130, is rotated through the swirler 19 and diffuses when the flowing fuel-air mixed fluid A flows into the combustion chamber 31a. It functions to increase the range.

At this time, a plurality of the air injection slots 140 are arranged at predetermined intervals along the outer periphery of the protruding block 132, so that the compressed air (B) supplied through the central flow channel 122 is directed toward the mixed fluid (A). Will be sprayed. In FIG. 5, since the air injection slots 140 are arranged side by side in the flow direction of the mixed fluid A, they are naturally mixed without interfering with the flow of the mixed fluid A.

Here, since the cone-shaped part 134 is adjacent to the combustion chamber 31a, it is exposed to a high temperature/high temperature environment during combustion, and the compressed air B injected from the air injection slot 140 is at a relatively low temperature. This serves to cool the surface of the cone-shaped portion 134.

Of course, since the mixed fluid (A) is diffused from the periphery of the cone-shaped portion 134, the compressed air (B) injected from the air injection slot 140 along the flow flows along the surface of the cone-shaped portion to function as a cooling. will be.

6 and 7, in the second embodiment of the present invention, the protrusion block 132 may be provided in a cylindrical shape, and the air injection slot 140 is along the outer periphery of the protrusion block 132. It may be formed in a structure in which a plurality of are disposed at predetermined intervals.

First, in FIG. 6, the air injection slot 140 is formed in the longitudinal direction of the guide block 130 on the protruding block 132, and may be disposed in parallel along the flow direction of compressed air (B). In this case, compressed air Since (B) is sprayed in the same direction as the mixed fluid (A) while passing through the air injection slot 140, it can be naturally mixed without interfering with the flow of the mixed fluid (A).

Alternatively, as shown in FIG. 7, a plurality of air injection slots 140 may be formed on the protruding block 132 along a radial direction, and in this case, the air injection slot 140 is formed to be inclined with respect to the direction of the combustion chamber 31a. Can be. In this case, the compressed air (B) supplied from the central flow path 122 is sprayed while turning while passing through the air injection slot 140.

Here, the fuel-air mixed fluid (A) is also being rotated and introduced into the combustion chamber (31a).Since the compressed air (B) passing through the air injection slot (140) is also rotated and injected, the mixed fluid (A) and compressed air ( As turbulence occurs between B), the degree of mixing increases more.

In this case, the inclined direction of the air injection slot 140 may be set to a direction opposite to the curved direction of the swirler 19. In this case, the direction in which the mixed fluid (A) is rotated and the direction in which the compressed air (B) is rotated are opposite to each other, so that the generation of turbulence increases and the degree of mixing may be further significantly increased.

Of course, the inclined direction of the air injection slot 140 may be set in the same direction as the curved direction of the swirler 19. In this case, there is no significant increase in the occurrence of turbulence, but since it is rotated in the same direction, natural mixing can be achieved.

Next, referring to FIGS. 9 and 10, another form of the air injection slot 140 is posted. In addition, in the form shown in FIGS. 9 and 10, an air injection hole 150 may be additionally disposed.

First, referring to FIG. 9, the compressed air (B) is diffused and sprayed in an outward direction based on the center of the cone-shaped part 134, so that the inner surface of the air injection slot 140 has the protruding block 132 An inclined portion 142 having an increased inclination from top to bottom may be formed.

When the compressed air (B) supplied from the central flow path 122 passes through the air injection slot 140, the flow is guided to the outside by the inclined portion 142 to diffuse and be injected. At this time, it is mixed with and mixed with the mixed fluid A flowing from the outside of the partition wall 120 to the combustion chamber 31a.

In addition, one or more air injection holes 150 for injecting compressed air (B) flowing in the central flow path 122 may be disposed around the inner periphery of the protruding block 132. The air injection hole 150 is formed parallel to the flow direction side of the mixed fluid (A), so that the compressed air (B) is injected directly in the direction of the combustion chamber (31a). At this time, when the swirling and flowing mixed fluid (A) diffuses in the vicinity of the cone-shaped portion 134, the compressed air (B) flows along the surface of the cone-shaped portion 134 by the diffusion and performs a cooling action. .

Here, a spiral portion 152 for rotating air may be formed in the air injection hole 150 so as to rotate and inject compressed air B to increase an additional degree of mixing with the fuel-air mixed fluid A. Since compressed air (B) is injected while rotating along the spiral portion 152, the degree of mixing with the mixed fluid (A) is improved.

Next, referring to FIG. 10, the compressed air (B) is diffused and sprayed in an outward direction based on the center of the cone-shaped portion 134, so that the inner surface of the air injection slot 140 is A curved portion 144 whose curvature increases from top to bottom may be formed.

When the compressed air (B) supplied from the central flow path 122 passes through the air injection slot 140, the flow is guided to the outside by the curved portion 144 to diffuse and be sprayed. At this time, it is mixed with and mixed with the mixed fluid A flowing from the outside of the partition wall 120 to the combustion chamber 31a.

Likewise, one or more air injection holes 150 for injecting compressed air B flowing in the central flow path 122 may be disposed around the inner periphery of the protruding block 132. The air injection hole 150 is formed parallel to the flow direction side of the mixed fluid (A), so that the compressed air (B) is injected directly in the direction of the combustion chamber (31a). At this time, when the swirling and flowing mixed fluid (A) diffuses in the vicinity of the cone-shaped portion 134, the compressed air (B) flows along the surface of the cone-shaped portion 134 by the diffusion and performs a cooling action. .

Here, a spiral portion 152 for rotating air may be formed in the air injection hole 150 so as to rotate and inject compressed air B to increase an additional degree of mixing with the fuel-air mixed fluid A. Since compressed air (B) is injected while rotating along the spiral portion 152, the degree of mixing with the mixed fluid (A) is improved.

For reference, although the fluid supplied from the central flow path 122 is limited to compressed air, it may be changed to supply a mixed fluid in which air and fuel are mixed according to the design purpose. In this case, although not shown in the drawing, fuel is supplied through the nozzle base 12, and part of the compressed air is supplied in a mixed state by being introduced through the inlet (not shown) formed on the body frame 110. Can be.

In the second embodiment of the combustor 10 according to the present invention, the fuel-air mixing degree is increased through the above-described structure and the effect of cooling and protecting the front end surface of the center body 100 is achieved.

On the other hand, the gas turbine 1 of the present invention includes a casing 2, a compressor section 4 disposed inside the casing 2 and compressing the introduced air, and the compressor section 4 inside the casing 2 ( 4) connected and arranged, the combustor 10 including the center body 100 for combusting compressed air, and the casing 2 connected to and arranged with the combustor 10, and the combusted air It may be configured to include a turbine section 6 that generates power by using and a diffuser 7 that is connected to and arranged with the turbine section 6 inside the casing 2 and discharges air to the outside.

The above is only showing a specific embodiment of a combustor and a gas turbine.

Therefore, it is to be noted that those of ordinary skill in the art can easily grasp that the present invention can be substituted and modified in various forms within the scope of the scope of the present invention described in the following claims. do.

10: combustor 18: fuel nozzle
19: Whirler 31a: Combustion chamber
100: center body
[First embodiment]
110: body frame 112: central flow path
114: air injection hole 116; cone-shaped part
[Second Example]
120: bulkhead 122: central passage
130: guide block 132; protruding block
134: cone-shaped portion 140: air injection slot
142: inclined portion 144: curved portion
150: air injection hole 152: spiral part
A: Flow of fuel-air mixed fluid
B: Flow of compressed air

Claims (13)

A fuel nozzle disposed on the nozzle tube and formed with a hollow portion;
A center body connected to the nozzle base and disposed in the hollow portion of the fuel nozzle; And
Including; a swirler disposed between the inner surface of the fuel nozzle and the outer peripheral surface of the center body,
The front end of the center body has a cone shape whose cross-sectional area decreases toward the combustion chamber,
The center body,
A partition wall connected to the nozzle base and defining a central flow path through which compressed air flows; And
Includes; a guide block inserted into the partition wall and arranged to guide the flow direction of compressed air flowing through the central flow path,
A cone-shaped portion is formed at the front end of the guide block, and a protruding block is disposed along the outer circumference adjacent to the cone-shaped portion,
One or more air injection slots for injecting compressed air flowing in the central flow channel around the outer periphery of the protruding block.
delete delete delete delete The method of claim 1,
The air injection slot is a combustor, characterized in that formed in the longitudinal direction of the guide block on the protruding block.
The method of claim 1,
A plurality of air injection slots are formed on the protruding block along a radial direction, wherein the air injection slots may be formed to be inclined with respect to a direction of the combustion chamber.
The method of claim 7,
In order to increase the degree of mixing by increasing turbulence in the compressed air period, which is rotated through the swirler and rotated through the fuel-air mixed fluid supplied to the combustion chamber and the air injection slot and supplied to the combustion chamber,
A combustor, characterized in that the inclined direction of the air injection slot and the curved direction of the swirler are formed in opposite directions.
The method according to any one of claims 6 to 8,
A combustor, characterized in that an inclined portion is formed on an inner surface of the air injection slot to increase inclination from the top to the bottom of the protruding block so that compressed air is diffused and injected in an outward direction based on the center of the cone-shaped portion.
The method according to any one of claims 6 to 8,
A combustor, characterized in that a curved portion is formed on an inner surface of the air injection slot to increase a curvature from an upper portion to a lower portion of the protruding block so that fuel is diffused and injected in an outward direction based on the center of the cone-shaped portion.
The method of claim 1,
A combustor, characterized in that at least one air injection hole for injecting compressed air flowing in the central flow path is disposed around the inner circumference of the protruding block.
The method of claim 11,
Compressed air is rotated and injected in the air injection hole to increase the degree of mixing with the fuel-air mixed fluid, and a spiral portion for rotating the air is formed.
Casing;
A compressor section disposed inside the casing and compressing the introduced air;
The combustor of claim 1 connected to and disposed within the casing and combusting compressed air;
A turbine section connected to the combustor in the casing and arranged to generate power using the combusted air; And
A diffuser disposed inside the casing and connected to the turbine section, and discharging air to the outside;
Containing, gas turbine.

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