KR102153014B1 - Combuster and gas turbine having the same - Google Patents

Abstract

The present invention relates to a combustor and a gas turbine including the same. According to the present invention, an arrangement structure of a swirler disposed in a fuel nozzle and a arrangement structure of an injection hole can be improved to increase the fuel-air mixing degree and reduce combustion vibration. The combustor includes: the fuel nozzle disposed on a nozzle tube; and a center body disposed in the center of the fuel nozzle and connected to a fuel nozzle base.

Description

Combustor and gas turbine including the same {COMBUSTER AND GAS TURBINE HAVING THE SAME}

The present invention relates to a combustor and a gas turbine including the same, and more particularly, by improving the arrangement structure of the swirler disposed in the fuel nozzle and the arrangement structure of the injection hole, it is possible to increase fuel-air mixing degree and reduce combustion vibration. It relates to a combustor and a gas turbine including the same.

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.

FIG. 1 discloses a fuel nozzle 93 and a center body 92 that form a passage for mixing and supplying air and fuel to a conventional combustion chamber 96. A swirler 94 is disposed between the fuel nozzle 93 and the center body 92 to control the flow of air supplied to the combustion chamber.

At this time, in one form of the gas turbine, as shown in FIG. 1, a fuel injection hole 94a is disposed on the swirler 94, and when air passes through the swirlers 94, fuel is injected to mix fuel and air. Is done.

However, in the conventional general form, the reference lines A in the circumferential direction between the plurality of swirlers 94 on the center body 92 coincide with each other, and the injection holes 94a were also disposed at relatively the same position.

In this case, when the vibration frequency generated when air flows through the inside of the fuel nozzle 93 and the vibration frequency generated when fuel is injected from the injection hole 94a and the vibration frequency generated during combustion in the combustion chamber 96 match, combustion Vibration occurs largely, which causes noise problems.

Domestic patent registration number: 10-1885413

The present invention was conceived to solve the problems of the related technical field as described above, and an object of the present invention is to improve the arrangement structure of the swirler disposed in the fuel nozzle and the arrangement structure of the injection hole to increase the fuel-air mixing degree and It is to provide a combustor capable of reducing vibration and a gas turbine including the same.

The present invention for achieving the above objects relates to a combustor and a gas turbine including the same, comprising: a fuel nozzle disposed on a nozzle tube; A center body disposed at the center of the fuel nozzle and connected to the fuel nozzle base; And a plurality of swirlers disposed to be spaced apart from each other in a circumferential direction between the center body and the fuel nozzle, wherein the plurality of swirlers are arranged extending along the circumferential direction between the center body and the fuel nozzle It is disposed along a reference line, and any one of the plurality of swirlers may be disposed along an arrangement reference line different from at least any one of the remaining swirlers.

In addition, in an embodiment of the present invention, each of the plurality of swirlers includes an upper portion disposed parallel to the airflow direction; A lower portion disposed to form a predetermined curvature or an angle in the airflow direction; And an injection hole formed on the upper part or the lower part and for injecting fuel.

In addition, in an embodiment of the present invention, the plurality of swirlers includes at least three or more swirlers, and the plurality of swirlers are formed to have the same length, and may be arranged in a zigzag between the center body and the fuel nozzle. have.

In addition, in an embodiment of the present invention, the plurality of swirlers includes at least three or more swirlers, and between the swirlers alternately disposed among the plurality of swirlers, the upper end of the swirler is extended in the circumferential direction. The arrangement reference line and the arrangement reference line extending the lower end of the swirler in the circumferential direction may coincide with each other.

In addition, in an embodiment of the present invention, the plurality of swirlers includes at least four or more swirlers, and among the plurality of swirlers alternately arranged, the lengths of the swirlers are the same, and the plurality of swirlers The lengths of the swirlers are configured differently between the swirlers arranged adjacent to each other, but between the swirlers alternately arranged among the plurality of swirlers, the arrangement reference line extending the upper end of the swirler in the circumferential direction is They coincide with each other, and the arrangement reference lines extending the lower end portions of the plurality of swirlers along the circumferential direction may coincide with each other.

In addition, in an embodiment of the present invention, the plurality of swirlers may be arranged in a helical direction along a circumferential direction between the center body and the fuel nozzle.

In addition, in an embodiment of the present invention, the plurality of swirlers are configured to have the same length as each other, and the arrangement reference line extending the upper end of the plurality of swirlers along the circumferential direction and the lower end of the plurality of swirlers are Layout baselines extending along the circumferential direction may be inconsistent with each other.

In addition, in an embodiment of the present invention, the plurality of swirlers are configured to have different lengths, and the reference lines of the arrangement extending along the circumferential direction of the upper end portions of the plurality of swirlers are arranged to be offset from each other, The arrangement reference lines extending the lower end of the circumferential direction may coincide with each other.

Further, in an embodiment of the present invention, a plurality of injection holes are provided, and the injection holes may be disposed at the same position in the radial direction on the upper side of the swirler.

In addition, in an embodiment of the present invention, a plurality of injection holes are provided, so as to increase air-fuel mixing and to distribute vibration frequencies generated when fuel is injected from the plurality of injection holes, the injection hole is It may be arranged in a plurality of stages on the upper side of the waller based on the air flow direction.

In addition, in an embodiment of the present invention, a plurality of injection holes are provided, so as to increase air-fuel mixing and to distribute vibration frequencies generated when fuel is injected from the plurality of injection holes, the injection hole is It may be irregularly arranged on the upper side of the waller.

In addition, in an embodiment of the present invention, a cyclone spiral portion may be formed in the injection hole so that the fuel is injected while forming a turbulent flow in the injection hole to increase the air-fuel mixing degree.

In addition, in an embodiment of the present invention, the cyclone spiral portion may include a steel wire formed in a spiral direction inside the injection hole; And a tapered portion formed to be tapered from the inside to the outside of the injection hole.

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, there is an effect of improving the arrangement structure of the swirler disposed in the fuel nozzle and the arrangement structure of the injection hole to increase the fuel-air mixing degree and reduce combustion vibration.

1 is a view showing an arrangement structure of a conventional swirler.
2 is a side cross-sectional view showing the basic structure of the gas turbine.
3 is a perspective cross-sectional view showing the basic structure of a combustor.
4 is a view showing a first embodiment of the arrangement structure of the swirler of the present invention.
5 is a view showing a second embodiment of the arrangement structure of the swirler of the present invention.
6 is a view showing a third embodiment of the arrangement structure of the swirler of the present invention.
7 is a view showing a fourth embodiment of the arrangement structure of the swirler of the present invention.
8 is a view showing a form of an arrangement form of a spray hole in the swirler of the present invention.
9 is a view showing another form of the arrangement of the injection hole in the swirler of the present invention.
10 is a view showing another form of the arrangement form of the injection hole in the swirler of the present invention.
11 is a view showing a form of the injection hole of the present inventors whirler.
12 is a view showing another form of the injection hole of the swirler of the present invention.

Hereinafter, preferred embodiments of a combustor according to the present invention and a gas turbine including the same 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 a center body 14 extending from the center of the cylindrical space in the front-rear direction of the combustor. One end of the center body 14 is connected to the fuel nozzle base 12 to receive fuel therefrom, and this fuel is a fuel injection opening formed around the swirler 100 and/or the center body 14 ( (Not shown) and may be mixed with compressed air. In the present invention, a fuel injection opening (not shown) is formed on the swirler 100. 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.

4 is a diagram showing a first embodiment of the arrangement structure of the swirler 100 according to the present invention.

Referring to FIG. 4, in the first embodiment of the combustor according to the present invention, a fuel nozzle 18, a center body 14, and a swirler 100 may be included.

As discussed in FIG. 3, a plurality of fuel nozzles 18 may be disposed on the nozzle tube 13, and the center body 14 is disposed at the center of the plurality of fuel nozzles 18, respectively, and It can be connected to the nozzle base 12.

The swirler 100 may be spaced apart from each other along the circumferential direction between the center body 14 and the fuel nozzle 18, and a plurality of swirlers 100 may be disposed.

At this time, the plurality of swirlers 100 may be disposed along an arrangement reference line extending along the circumferential direction between the center body 14 and the fuel nozzle 18. In the first embodiment of the present invention, any one of the plurality of swirlers 100 may be disposed along an arrangement reference line different from at least one of the remaining swirlers 100.

Referring to FIG. 4, a plurality of swirlers 100 are disposed between the fuel nozzle base 12 and the combustion chamber 31a based on the air flow direction. In the present embodiment, a structure in which four swirlers are arranged is shown to facilitate explanation, but the present invention is not limited thereto, and a different number of swirlers may be arranged.

For ease of explanation, a plurality of swirlers 100 disposed between the fuel nozzle 18 and the center body 14 are shown in FIG. 4, the first swirler 110 and the second swirler 120 , Designated as the third swirler 130 and the fourth swirler 140.

Here, the swirlers 110, 120, 130, 140 may include upper portions 111, 121, 131 and 141, lower portions 113, 123, 133, and 143, and injection holes 110a, 120a, 130a, and 140a. The upper portions 111, 121, 131, and 141 of the swirler are portions disposed parallel to the air flow direction, and the lower portions 113, 123, 133, and 143 of the swirler may be portions disposed to form a predetermined curvature or a predetermined angle in the air flow direction. In addition, the injection holes 110a, 120a, 130a, 140a are formed in the upper portions 111, 121, 131, 141 or the lower portions 113, 123, 133, and 143, and may be portions for injecting fuel.

Between the fuel nozzle 18 and the center body 14, the end of the upper part 111 of the first swirler 110 is arranged along the B1 arrangement reference line, and the end of the lower part 113 of the first swirler 110 May be placed along the B3 placement baseline. In addition, an end of the upper part 121 of the second swirler 120 may be disposed along the B2 placement reference line, and an end of the lower part 123 of the second swirler 120 may be disposed along the B4 placement reference line.

In addition, an end of the upper portion 131 of the third swirler 130 may be disposed along the B1 placement reference line, and the end of the lower side portion 133 of the third swirler 130 may be disposed along the B3 placement reference line. In addition, an end of the upper part 141 of the fourth swirler 140 may be disposed along the B2 placement reference line, and the lower end 143 of the fourth swirler 140 may be disposed along the B4 placement reference line.

That is, the plurality of swirlers 110, 120, 130, and 140 are formed to have the same length, and may be arranged in a zigzag between the center body 14 and the fuel nozzle 18.

In this structure, a time difference occurs between the air entering the first and third swirlers 110 and 130 and the second and fourth swirlers 120 and 140. In addition, the positions of the injection holes 110a and 130a of the first and third swirlers 110 and 130 and the injection holes 120a and 140a of the second and fourth swirlers 120 and 140 are different from each other, so that the fuel injection positions are different.

In this case, the vibration frequency generated when air flows through the inside of the fuel nozzle 18 is inconsistent at the moment of entering the plurality of swirlers 110, 120, 130, 140 arranged in zigzag at different positions, and also the plurality of swirlers ( Since the positions of the injection holes 110a, 120a, 130a, and 140a between 110, 120, 130 and 140 are different, the vibration frequencies generated during fuel injection are also inconsistent. This makes it more difficult to coincide with the vibration frequency generated during combustion in the combustion chamber 31a, and as a whole, it is possible to derive the effect of reducing vibration and noise of the gas turbine.

5 is a diagram showing a second embodiment of the arrangement structure of the swirler 100 according to the present invention.

Referring to FIG. 5, in the second embodiment of the combustor according to the present invention, a fuel nozzle 18, a center body 14, and a swirler 100 may be included.

As discussed in FIG. 3, a plurality of fuel nozzles 18 may be disposed on the nozzle tube 13, and the center body 14 is disposed at the center of the plurality of fuel nozzles 18, respectively, and It can be connected to the nozzle base 12.

The swirler 100 may be spaced apart from each other along the circumferential direction between the center body 14 and the fuel nozzle 18, and a plurality of swirlers 100 may be disposed.

At this time, the plurality of swirlers 100 may be disposed along an arrangement reference line extending along the circumferential direction between the center body 14 and the fuel nozzle 18. In the first embodiment of the present invention, at least one or more of the plurality of swirlers 100 may be disposed along an arrangement reference line different from that of other swirlers.

Referring to FIG. 5, a plurality of swirlers 100 are disposed between the fuel nozzle base 12 and the combustion chamber 31a based on the air flow direction. In the present embodiment, a structure in which four swirlers are arranged is shown to facilitate explanation, but the present invention is not limited thereto, and a different number of swirlers may be arranged.

For ease of explanation, a plurality of swirlers 100 disposed between the fuel nozzle 18 and the center body 14 are shown in FIG. 5, the first swirler 110 and the second swirler 120 , Designated as the third swirler 130 and the fourth swirler 140.

Here, the swirlers 110, 120, 130, 140 may include upper portions 111, 121, 131 and 141, lower portions 113, 123, 133, and 143, and injection holes 110a, 120a, 130a, and 140a. The upper portions 111, 121, 131, and 141 of the swirler are portions disposed parallel to the air flow direction, and the lower portions 113, 123, 133, and 143 of the swirler may be portions disposed to form a predetermined curvature or a predetermined angle in the air flow direction. In addition, the injection holes 110a, 120a, 130a, 140a are formed in the upper portions 111, 121, 131, 141 or the lower portions 113, 123, 133, and 143, and may be portions for injecting fuel.

Between the fuel nozzle 18 and the center body 14, the end of the upper part 111 of the first swirler 110 is arranged along the C1 arrangement reference line, and the end of the lower part 113 of the first swirler 110 Can be placed along the C4 placement baseline. In addition, an end of the upper part 121 of the second swirler 120 may be disposed along the C2 placement reference line, and the end of the lower part 123 of the second swirler 120 may be disposed along the C4 placement reference line.

In addition, an end of the upper part 131 of the third swirler 130 may be disposed along the C1 placement reference line, and the end of the lower part 133 of the third swirler 130 may be disposed along the C4 placement reference line. In addition, an end of the upper part 141 of the fourth swirler 140 may be disposed along the C2 placement reference line, and an end of the lower part 143 of the fourth swirler 140 may be disposed along the C4 placement reference line.

That is, some of the plurality of swirlers (110, 120, 130, 140) are formed with different lengths, and based on the air flow direction between the center body 14 and the fuel nozzle 18, the upper portions 111, 121, 131, 141 are arranged along different arrangement reference lines. , The lower parts 113, 123, 133, and 143 may be disposed along the same C4 placement reference line.

In this case, the air entering the area where the plurality of swirlers 110, 120, 130, and 140 are disposed enters at different time intervals, but when exiting the area where the plurality of swirlers 110, 120, 130, and 140 are disposed, deviate from the same C4 placement baseline. Therefore, the tornado flow in the lower portions 113, 123, 133, and 143 of the swirler is maintained relatively uniformly.

Here, a time difference occurs between the air entering the first and third swirlers 110 and 130 and the second and fourth swirlers 120 and 140. In addition, the positions of the injection holes 110a and 130a of the first and third swirlers 110 and 130 and the injection holes 120a and 140a of the second and fourth swirlers 120 and 140 are different from each other, so that the fuel injection positions are different.

In this case, the vibration frequency generated when air flows through the inside of the fuel nozzle 18 is inconsistent at the moment of entering the plurality of swirlers 110, 120, 130, 140 arranged in zigzag at different positions, and also the plurality of swirlers ( Since the positions of the injection holes 110a, 120a, 130a, and 140a between 110, 120, 130 and 140 are different, the vibration frequencies generated during fuel injection are also inconsistent. This makes it more difficult to coincide with the vibration frequency generated during combustion in the combustion chamber 31a, and as a whole, it is possible to derive the effect of reducing vibration and noise of the gas turbine.

And since the lower portions of the plurality of swirlers 110, 120, 130, 140 are all aligned with the C4 placement reference line, the swirl flow of the air-fuel mixture exiting the region where the plurality of swirlers 110, 120, 130, 140 are disposed has the effect of forming relatively uniformly.

6 is a diagram showing a third embodiment of the arrangement structure of the swirler 100 according to the present invention.

Referring to FIG. 6, in the third embodiment of the combustor according to the present invention, a fuel nozzle 18, a center body 14, and a swirler 100 may be included.

As discussed in FIG. 3, a plurality of fuel nozzles 18 may be disposed on the nozzle tube 13, and the center body 14 is disposed at the center of the plurality of fuel nozzles 18, respectively, and It can be connected to the nozzle base 12.

The swirler 100 may be spaced apart from each other along the circumferential direction between the center body 14 and the fuel nozzle 18, and a plurality of swirlers 100 may be disposed.

At this time, the plurality of swirlers 100 may be disposed along an arrangement reference line extending along the circumferential direction between the center body 14 and the fuel nozzle 18. In the third embodiment of the present invention, at least one or more of the plurality of swirlers 100 may be disposed along an arrangement reference line different from that of other swirlers.

Referring to FIG. 6, a plurality of swirlers 100 are disposed between the fuel nozzle base 12 and the combustion chamber 31a based on the air flow direction. In the present embodiment, a structure in which four swirlers are arranged is shown to facilitate explanation, but the present invention is not limited thereto, and a different number of swirlers may be arranged.

For ease of explanation, a plurality of swirlers 100 disposed between the fuel nozzle 18 and the center body 14 are shown in FIG. 6, as shown in FIG. 6, the first swirler 110 and the second swirler 120. , Designated as the third swirler 130 and the fourth swirler 140.

Here, the swirlers 110, 120, 130, 140 may include upper portions 111, 121, 131 and 141, lower portions 113, 123, 133, and 143, and injection holes 110a, 120a, 130a, and 140a. The upper portions 111, 121, 131, and 141 of the swirler are portions disposed parallel to the air flow direction, and the lower portions 113, 123, 133, and 143 of the swirler may be portions disposed to form a predetermined curvature or a predetermined angle in the air flow direction. In addition, the injection holes 110a, 120a, 130a, 140a are formed in the upper portions 111, 121, 131, 141 or the lower portions 113, 123, 133, and 143, and may be portions for injecting fuel.

In the third embodiment of the present invention, the first, second, third, and fourth swirlers 110, 120, 130, and 140 may be arranged in a spiral shape along the circumferential direction between the fuel nozzle 18 and the center body 14. In this case, the lengths of the first, second, third, and fourth swirlers 110, 120, 130, and 140 may be the same or different.

If the lengths between the 1st, 2nd, 3rd, 4th swirlers (110, 120, 130, 140) are the same, the upper end (111, 121, 131, 141) of the 1st, 2nd, 3rd and 4th swirlers (110, 120, 130, 140) is extended along the circumferential direction and Arrangement reference lines extending the ends of the lower portions 113, 123, 133, and 143 of the first, second, third, and fourth swirlers 110, 120, 130, and 140 along the circumferential direction do not coincide with each other.

In the case of such a structure, a time difference occurs in the air entering the first, second, third, and fourth swirlers 110, 120, 130, and 140, respectively. In addition, the injection hole (110a) of the first swirler (110), the injection hole (120a) of the second swirler (120) and the injection hole (130a) of the third swirler (130) of the fourth swirler (140) The positions of the injection holes 140a are different from each other, so that the fuel injection positions are different.

In this case, the vibration frequency generated when the air flows through the inside of the fuel nozzle 18 is inconsistent at the moment of entering the plurality of swirlers 110, 120, 130, 140 arranged in the spiral direction at different positions, and the plurality of swirlers Since the positions of the injection holes 110a, 120a, 130a, and 140a between (110, 120, 130, 140) are different, the vibration frequencies generated during fuel injection are also inconsistent. This makes it more difficult to coincide with the vibration frequency generated during combustion in the combustion chamber 31a, and as a whole, it is possible to derive the effect of reducing vibration and noise of the gas turbine.

7 is a diagram showing a fourth embodiment of the arrangement structure of the swirler 100 according to the present invention.

Referring to FIG. 7, in the fourth embodiment of the combustor according to the present invention, a fuel nozzle 18, a center body 14, and a swirler 100 may be included.

As discussed in FIG. 3, a plurality of fuel nozzles 18 may be disposed on the nozzle tube 13, and the center body 14 is disposed at the center of the plurality of fuel nozzles 18, respectively, and It can be connected to the nozzle base 12.

The swirler 100 may be spaced apart from each other along the circumferential direction between the center body 14 and the fuel nozzle 18, and a plurality of swirlers 100 may be disposed.

At this time, the plurality of swirlers 100 may be disposed along an arrangement reference line extending along the circumferential direction between the center body 14 and the fuel nozzle 18. In the first embodiment of the present invention, at least one or more of the plurality of swirlers 100 may be disposed along an arrangement reference line different from that of other swirlers.

Referring to FIG. 7, a plurality of swirlers 100 are disposed between the fuel nozzle base 12 and the combustion chamber 31a based on the air flow direction. In the present embodiment, a structure in which four swirlers are arranged is shown to facilitate explanation, but the present invention is not limited thereto, and a different number of swirlers may be arranged.

For ease of explanation, a plurality of swirlers 100 disposed between the fuel nozzle 18 and the center body 14 are shown in FIG. 7, a first swirler 110 and a second swirler 120 , Designated as the third swirler 130 and the fourth swirler 140.

Here, the swirlers 110, 120, 130, 140 may include upper portions 111, 121, 131 and 141, lower portions 113, 123, 133, and 143, and injection holes 110a, 120a, 130a, and 140a. The upper portions 111, 121, 131, and 141 of the swirler are portions disposed parallel to the air flow direction, and the lower portions 113, 123, 133, and 143 of the swirler may be portions disposed to form a predetermined curvature or a predetermined angle in the air flow direction. In addition, the injection holes 110a, 120a, 130a, 140a are formed in the upper portions 111, 121, 131, 141 or the lower portions 113, 123, 133, and 143, and may be portions for injecting fuel.

In the fourth embodiment of the present invention, the lower portions 113, 123, 133, and 143 of the swirler may be bent and disposed along the E5 placement reference line, but are not limited thereto.

The end of the upper part 111 of the first swirler 110 between the fuel nozzle 18 and the center body 14 is disposed along the E1 arrangement reference line, and the end of the lower part 113 of the first swirler 110 May be placed along the E6 placement baseline. In addition, an end of the upper part 121 of the second swirler 120 may be disposed along the E3 placement reference line, and an end of the lower part 123 of the second swirler 120 may be disposed along the E6 placement reference line.

In addition, an end of the upper part 131 of the third swirler 130 may be disposed along the E2 placement reference line, and the end of the lower part 133 of the third swirler 130 may be disposed along the E6 placement reference line. In addition, the end of the upper part 141 of the fourth swirler 140 may be disposed along the E4 placement reference line, and the end of the lower part 143 of the fourth swirler 140 may be disposed along the E6 placement reference line.

That is, a plurality of swirlers (110, 120, 130, 140) are formed with different lengths, and based on the air flow direction between the center body 14 and the fuel nozzle 18, the upper portions 111, 121, 131, 141 are arranged along different arrangement reference lines, The lower portions 113, 123, 133, and 143 may be disposed along the same E6 placement reference line.

In this case, the air entering the area where the plurality of swirlers 110, 120, 130, and 140 are disposed enters at different time intervals, but when exiting the area where the plurality of swirlers 110, 120, 130, and 140 are disposed, deviate from the same E6 placement baseline. Therefore, the tornado flow at the lower side of the swirlers 110, 120, 130, and 140 is maintained relatively uniformly.

Here, a time difference occurs in the air entering the first, second, third, and fourth swirlers 110, 120, 130, and 140. In addition, the injection hole (110a) of the first swirler (110), the injection hole (120a) of the second swirler (120), the injection hole (130a) of the third swirler (130), the fourth swirler (140) The positions of the injection holes 140a are different from each other, so that the fuel injection positions are different.

In this case, the vibration frequency generated when air flows through the inside of the fuel nozzle 18 is inconsistent at the moment of entering the plurality of swirlers 110, 120, 130, 140 disposed at different positions, and also the plurality of swirlers (110, 120, 130, 140) Since the positions of the injection holes 110a, 120a, 130a, and 140a are different from each other, vibration frequencies generated during fuel injection are also inconsistent. This makes it more difficult to coincide with the vibration frequency generated during combustion in the combustion chamber 31a, and as a whole, it is possible to derive the effect of reducing vibration and noise of the gas turbine.

And since the lower portions of the plurality of swirlers 110, 120, 130, 140 are all aligned with the E6 placement reference line, the tornado flow of the air-fuel mixture exiting the region where the plurality of swirlers 110, 120, 130, 140 are disposed has an effect of forming relatively uniformly.

FIG. 8 is a view showing an arrangement of the injection holes 151 in the swirler 100 of the present invention, and FIG. 9 is a view showing another arrangement of the injection holes 151 and 153 in the swirler 100 of the present invention. It is a view showing the form, Figure 10 is a view showing another form of the arrangement of the injection holes (151, 153, 155) in the swirler 100 of the present invention.

First, referring to FIG. 8, a plurality of injection holes 151 of the swirler 100 are provided, and may be disposed at the same position in the radial direction on the upper portion 100b of the swirler 100. When the injection holes 151 are disposed at the same position, the air-fuel mixture may be formed at a time by injecting fuel relatively uniformly along the radial direction into the air entering the swirler 100.

Alternatively, referring to FIG. 9, a plurality of injection holes 151 and 153 of the swirler 100 are provided, but may be disposed in a plurality of stages based on the air flow direction in the upper portion 100b of the swirler 100 . When the injection holes 151 and 153 are arranged in a plurality of stages, since an area in which air and fuel can be mixed increases, the degree of air-fuel mixing can be increased. In addition, the effect of dispersing the vibration frequencies that may be generated when fuel is injected can be expected.

Next, referring to FIG. 10, a plurality of injection holes 151, 153, and 155 of the swirler 100 are provided, and may be irregularly disposed on the upper portion 100b of the swirler 100. Also, when the injection holes 151, 153, and 155 are arranged irregularly, since the area in which air and fuel can be mixed increases, the degree of air-fuel mixing can be increased. In addition, the effect of dispersing the vibration frequencies that may be generated when fuel is injected can be expected.

11 is a view showing one form of the spray holes 151 and 153 of the swirler 100 according to the present invention, and FIG. 12 is a view showing another form of the spray holes 151 and 153 of the swirler 100 according to the present invention.

First, referring to FIG. 11, the injection hole 151 disposed in front of the upper portion 100b of the swirler 100 based on the air flow direction may be disposed perpendicular to the air flow direction, and the swirler 100 The injection hole 153 disposed at the rear end of the upper portion 100b may be disposed at an angle inclined to the airflow direction. The fuel injected from the injection hole 151 increases the degree of mixing due to the resistance with air, and the fuel injected from the injection hole 153 is injected obliquely in the air flow direction, so that it is naturally mixed without interfering with the flow of air. do.

Next, referring to FIG. 12, a cyclone spiral portion 180 may be formed in the injection holes 151 and 153 so that fuel is injected while forming a turbulent flow in the injection holes 151 and 153 to increase air-fuel mixing.

The cyclone spiral portion 180 may include a steel wire 182 and a tapered portion 181. First, the steel wire 182 may be formed in a spiral direction inside the spray hole. Next, the tapered portion 181 may be formed to be tapered from the inside to the outside of the injection holes 151 and 153.

The fuel injected from the injection holes 151 and 153 of the swirler 100 spirally rotates along the steel wire 182, and as the tapered portion 181 is formed, the speed gradually increases and is injected according to the law of fluid continuity. As a result, the fuel swirls and is injected into the fuel nozzle 18.

The tornadoes form turbulent flow and the discharged fuel increases the degree of mixing with air in the fuel nozzle 18, which helps to reduce combustion vibration in the combustion chamber 31a.

Meanwhile, referring to FIG. 2, the gas turbine of the present invention includes a casing 2, a compressor section 4 disposed inside the casing 2 and compressing the introduced air, and a compressor section 4 inside the casing 2 ) Is connected and disposed, and the combustor 10 reflecting the above-described embodiments of burning compressed air, and the casing 2 is connected to and disposed with the combustor 10, and power is generated by using the combusted air. It may comprise a producing turbine section 6 and a diffuser 7 connected to the turbine section 6 inside the casing 2 and disposed, and discharging air to the outside.

The above is merely showing a specific embodiment of a combustor and a gas turbine including the same.

Therefore, it will be clarified 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.

12: fuel nozzle base 13: nozzle tube
14: center body 18: fuel nozzle
31a: combustion chamber
100: swirler 110; first swirler
120;2nd swirler 130;3rd swirler
140: 4th swirler 151,153,155: injection hall
180: cyclone spiral portion 181: tapered portion
182: steel wire
B1 to B4: batch baseline (first embodiment)
C1 to C4: batch baseline (second embodiment)
E1 to E6: Batch baseline (Third Example)

Claims (14)

A fuel nozzle disposed on the nozzle tube;
A center body disposed at the center of the fuel nozzle and connected to the fuel nozzle base; And
Including; a plurality of swirlers disposed to be spaced apart from each other along the circumferential direction between the center body and the fuel nozzle,
The plurality of swirlers are disposed along an arrangement reference line extending along the circumferential direction between the center body and the fuel nozzle,
Any one of the plurality of swirlers is disposed along an arrangement reference line different from at least one of the remaining swirlers,
Each of the plurality of swirlers,
An upper portion disposed parallel to the air flow direction;
A lower portion disposed to form a predetermined curvature or an angle in the airflow direction; And
An injection hole formed on the upper side or the lower side and injecting fuel;
Containing, combustor.
delete The method of claim 1,
The plurality of swirlers includes at least three or more swirlers,
The plurality of swirlers are formed to have the same length, and are arranged in a zigzag between the center body and the fuel nozzle.
The method of claim 3,
Between the swirlers alternately arranged among the plurality of swirlers, the arrangement reference line extending the upper end of the swirler in the circumferential direction and the arrangement reference line extending the lower end of the swirler in the circumferential direction coincide with each other.
The method of claim 1,
The plurality of swirlers includes at least four or more swirlers,
Among the plurality of swirlers that are alternately arranged, the lengths of the swirlers are configured to be the same, and between the plurality of swirlers arranged adjacent to each other, the lengths of the swirlers are configured to be different from each other,
Between the swirlers that are alternately arranged among the plurality of swirlers, the arrangement reference lines extending the upper end of the swirler in the circumferential direction coincide with each other,
An arrangement reference line extending in the circumferential direction of the lower end portions of the plurality of swirlers coincide with each other.
The method of claim 1,
The plurality of swirlers are arranged in a helical direction along a circumferential direction between the center body and the fuel nozzle.
The method of claim 6,
The plurality of swirlers are configured to have the same length as each other,
The arrangement reference line extending the upper end of the plurality of swirlers along the circumferential direction and the arrangement reference line extending the lower end of the plurality of swirlers along the circumferential direction are inconsistent with each other.
The method of claim 1,
The plurality of swirlers are composed of different lengths,
The arrangement reference lines extending the upper ends of the plurality of swirlers along the circumferential direction are arranged to be offset from each other,
An arrangement reference line extending in the circumferential direction of the lower end portions of the plurality of swirlers coincide with each other.
The method of claim 1,
A plurality of injection holes are provided,
The injection hole is disposed at the same position in the radial direction on the upper side of the swirler.
The method of claim 1,
A plurality of injection holes are provided,
In order to increase the air-fuel mixing degree and distribute the vibration frequencies generated when fuel is injected from the plurality of injection holes, the injection holes are arranged in a plurality of stages based on the air flow direction on the upper side of the swirler. , Combustor.
The method of claim 1,
A plurality of injection holes are provided,
The injection hole is irregularly disposed on the upper side of the swirler so as to increase the air-fuel mixing degree and to distribute the vibration frequency generated when fuel is injected from the plurality of injection holes.
The method of claim 1,
In order to increase the air-fuel mixing degree, a cyclone spiral part; is formed in the injection hole so that the fuel is injected while forming a turbulent flow in the injection hole.
The method of claim 12,
The cyclone spiral portion,
A steel wire formed in a spiral direction inside the injection hole; And
A tapered portion formed to be tapered from the inside to the outside of the injection hole;
Containing, combustor.
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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