KR102651451B1 - Gas turbine combustor and gas turbine having same - Google Patents

Abstract

The present invention includes a nozzle casing that receives compressed air from a compressor; A liner connected to the nozzle casing and forming a combustion chamber in which the mixed fluid generated by mixing compressed air and fuel inside the nozzle casing is combusted; a transition piece connected to the liner and supplying combustion gas generated by combustion in the liner to the turbine; A porous block provided inside the nozzle casing and guiding the mixed fluid generated by mixing compressed air and fuel in the mixing area through the inlet to the outlet; An inner tube body centered on the porous block and surrounding the inlet of the porous block; An outer tube body provided at a certain distance from the circumference of the inner tube body based on the center of the inner tube body, forming a passage through which compressed air and fuel flows between the inner tube body and the inner tube body; and a plurality of bodies arranged radially between the inner tube body and the outer tube body with respect to the center of the inner tube body, and providing a swirler effect to the compressed air and fuel flowing along the passage between the inner tube body and the outer tube body. Including two mixing vanes, the mixing of compressed air and fuel is improved through a swirler effect through the mixing vanes, ultimately supplying a uniform flow rate of mixed fluid to the porous block, and also compressed air A gas turbine combustor and a gas turbine equipped with the same are provided in which the supply shortage of the mixed fluid generated by mixing compressed air and fuel is resolved by directly bypassing a portion of the gas through a porous block.

Description

Gas turbine combustor and gas turbine having same {Gas turbine combustor and gas turbine having same}

The present invention relates to a gas turbine combustor and a gas turbine equipped therewith, and more specifically, to a gas turbine combustor equipped with the same, which mixes compressed air supplied from a compressor with fuel for combustion and supplies the generated combustion gas to a turbine. It's about gas turbines.

In general, a turbomachine refers to a device that generates power for power generation through fluid (particularly gas) passing through the turbomachine. Therefore, turbo machines are usually installed and used together with a generator. These turbo machines may include gas turbines, steam turbines, wind power turbines, etc. A gas turbine is a device that generates combustion gas by mixing compressed air and natural gas and combustion, and uses the generated combustion gas to generate power for power generation. A steam turbine is a device that generates power for power generation using steam generated by heating water. A wind turbine is a device that converts wind power into power for power generation.

Looking at the gas turbine among turbo machines, the gas turbine includes a compressor, combustor, and turbine. The compressor has a plurality of compressor vanes and compressor blades arranged alternately within the compressor casing. And the compressor sucks in external air through the compressor inlet scroll strut. The air sucked in this way passes through the inside of the compressor and is compressed by the compressor vanes and compressor blades. The combustor receives compressed air from the compressor and mixes it with fuel. Additionally, the combustor ignites fuel mixed with compressed air with an igniter to generate high-temperature, high-pressure combustion gas. The combustion gas generated in this way is supplied to the turbine. The turbine has a plurality of turbine vanes and turbine blades arranged alternately within the turbine casing. And the turbine receives the combustion gas generated from the combustor and passes it inside. The combustion gas passing through the inside of the turbine rotates the turbine blades, and the combustion gas that has completely passed through the inside of the turbine is discharged to the outside through the turbine diffuser.

In the combustor, compressed air and fuel are supplied to a plurality of microtubes formed on one side of the combustion chamber. The microtubes supply compressed air and fuel to the combustion chamber and combust them to generate high-temperature, high-pressure gas.

However, although it is desirable that the compressed air and fuel supplied to the plurality of microtubes are supplied uniformly, there have been cases where the compressed air and fuel are not supplied uniformly to the plurality of microtubes, and in this case, the flame is uniformly induced. However, there was a problem in that noise and vibration occurred during the combustion process due to uneven supply of compressed air and fuel.

The technology behind the present invention can be referred to Korean Patent No. 10-2164622 (registered on October 5, 2020).

The present invention provides a mixing vane at the location where compressed air and fuel meet, and improves the mixing of compressed air and fuel through a swirler effect through the mixing vane, ultimately producing a mixed fluid with a uniform flow rate. To provide a gas turbine combustor and a gas turbine equipped with the same that can be supplied to the block and also bypass some of the compressed air directly to the porous block, thereby resolving the shortage of supply of the mixed fluid generated by mixing compressed air and fuel. The purpose.

A gas turbine combustor according to the present invention includes a nozzle casing that receives compressed air from the compressor; A liner connected to the nozzle casing and forming a combustion chamber that burns a mixed fluid generated by mixing compressed air and fuel inside the nozzle casing; a transition piece connected to the liner and supplying combustion gas generated by combustion in the liner to the turbine; A porous block provided inside the nozzle casing and supplying the mixed fluid to the combustion chamber; An inner tube body disposed at the entrance of the porous block and surrounding the entrance to the porous block; an outer tube body disposed spaced apart from the inner tube body and forming a passage through which compressed air and fuel flow between the inner tube body and the inner tube body; and a plurality of mixing vanes arranged radially between the inner tube body and the outer tube body and providing a swirler effect to the compressed air and fuel flowing along the passage between the inner tube body and the outer tube body.

At this time, the inner tube body according to the present invention is formed with a bypass hole that guides a portion of the mixed fluid that has passed through the mixing vane to the inlet of the porous block.

Here, the bypass holes according to the present invention are formed in plural numbers and arranged at regular intervals along the circumference of the inner tube body.

And the bypass hole according to the present invention can be formed with an inner diameter that gradually becomes smaller as it moves from the inlet to the outlet of the inner tube body.

Additionally, the bypass hole according to the present invention may be formed in an oval shape with a long axis in the longitudinal direction of the inner tube body.

In addition, the outer pipe body according to the present invention may have a plurality of fuel inlet holes formed at regular intervals along the position line corresponding to the mixing vane among the circumference of the outer pipe body.

At this time, a fuel nozzle is provided in the fuel inlet hole according to the present invention to control the amount of fuel ejected through the fuel inlet hole.

In addition, the porous block according to the present invention has a multi-tube inside it that guides the mixed fluid generated by mixing compressed air and fuel along its length from the inlet to the outlet.

delete

The gas turbine according to the present invention includes a compressor that compresses air supplied from the outside; A turbine that generates power for electric power generation as combustion gases are passed therein; and a combustor that mixes compressed air supplied from the compressor with fuel and combusts it, and supplies the generated combustion gas to the turbine, wherein the combustor includes a nozzle casing that receives compressed air from the compressor, and a combustor in the nozzle casing. A liner is connected to form a combustion chamber that burns the mixed fluid produced by mixing compressed air and fuel inside the nozzle casing, and is connected to the liner to supply combustion gas generated by combustion in the liner to the turbine. a transition piece, a porous block provided inside the nozzle casing and supplying the mixed fluid to the combustion chamber, an inner tube body disposed at the inlet of the porous block and surrounding the inlet of the porous block, and the inner tube body An outer tube body disposed spaced apart on the outside of the tube body and forming a passage through which compressed air and fuel flows between the inner tube body and the inner tube body, and arranged radially between the inner tube body and the outer tube body, between the inner tube body and the outer tube body. It includes a plurality of mixing vanes that provide a swirler effect to the compressed air and fuel flowing along the passage.

The effects of the gas turbine combustor according to the present invention and the gas turbine equipped with the same are as follows.

A mixing vane is provided at the location where compressed air and fuel meet, and the mixing of compressed air and fuel is improved through a swirler effect through the mixing vane, ultimately supplying a uniform flow rate of mixed fluid to the porous block. It has a possible effect.

In addition, some of the compressed air is directly bypassed through the porous block, which has the effect of resolving the supply shortage of the mixed fluid produced by mixing compressed air and fuel.

1 is a cross-sectional view showing a gas turbine according to the present invention.
FIG. 2 is a diagram schematically showing the combustor shown in FIG. 1.
Figure 3 is a schematic cross-sectional view of a gas turbine combustor according to an example of the present invention.
Figure 4 is a perspective view showing the configuration of an inner tube, an outer tube, and a mixing vane in a gas turbine combustor according to an example of the present invention.
Figure 5 is a cross-sectional view showing an example of a bypass hole formed in the inner tube of a gas turbine combustor according to an example of the present invention.
Figure 6 is a perspective view of an inner tube body according to another embodiment of the present invention.
Figure 7 is a cross-sectional view showing a gas turbine combustor equipped with an inclined flange according to an example of the present invention.

Hereinafter, preferred embodiments according to the present invention will be described in detail with reference to the attached drawings. Prior to this, the terms or words used in this specification and claims should not be construed as limited to their usual or dictionary meanings, and the inventor should appropriately define the concept of terms in order to explain his or her invention in the best way. Based on the principle of definability, it must be interpreted with meaning and concept consistent with the technical idea of the present invention.

Therefore, the embodiments described in this specification and the configurations shown in the drawings are only the most preferred embodiments of the present invention, and do not represent the entire technical idea of the present invention, so at the time of filing this application, they can be replaced by equivalent equivalents. It should be understood that variations may exist.

The present invention provides a mixing vane at the location where compressed air and fuel meet, improving the mixing of compressed air and fuel through a swirler effect through the mixing vane, and ultimately producing a mixed fluid with a uniform flow rate through the porous hole. This relates to a gas turbine combustor that can be supplied to a block and a gas turbine equipped with the same, which is as follows with reference to the drawings.

Referring to Figures 1 and 2, the gas turbine 10 according to the present invention includes a compressor 11, a combustor 100, and a turbine 12.

Based on the flow direction of gas (compressed air or combustion gas), a compressor 11 is placed on the upstream side of the gas turbine 10 and a turbine 12 is placed on the downstream side, and the compressor 11 and turbine 12 ) The combustor 100 is disposed between them.

The compressor 11 accommodates compressor vanes and a compressor rotor inside a compressor casing, and the turbine 12 accommodates turbine vanes and a turbine rotor inside a turbine casing. These compressor vanes and compressor rotors are arranged in multi-stages along the flow direction of compressed air, and the turbine vanes and turbine rotors are also arranged in multi-stages along the flow direction of combustion gas.

At this time, the internal space of the compressor 11 decreases from the front stage to the rear stage so that the sucked air can be compressed, and on the contrary, the turbine 12 allows the combustion gas supplied from the combustor to expand. It is designed with a structure in which the internal space increases from the front to the rear.

Meanwhile, between the compressor rotor located at the extreme end of the compressor 11 and the turbine rotor located at the extreme end of the turbine 12, the rotational torque generated by the turbine 12 is transmitted to the compressor 11. A torque tube as a torque transmission member is disposed.

The torque tube may be composed of a plurality of torque tube disks consisting of a total of three stages as shown in Figure 1, but this is only one of several embodiments of the present invention, and the torque tube may have four or more stages or It may be composed of a plurality of torque tube disks consisting of two or less stages.

The compressor rotor includes a compressor disk and compressor blades. A plurality of compressor disks (for example, 14 disks) are provided inside the compressor casing, and each compressor disk is fastened by a tie rod so as not to be spaced apart in the axial direction.

More specifically, each of the compressor disks is aligned along the axial direction with its central portion penetrated by the tie rod, and each adjacent compressor disk has its opposing side pressed by the tie rod, so that the compressor disks are aligned relative to each other. It is placed so that it cannot rotate.

A plurality of compressor blades are radially coupled to the outer peripheral surface of the compressor disk.

Additionally, a plurality of compressor vanes installed in an annular shape on the inner peripheral surface of the compressor casing based on the same stage are disposed between the compressor blades.

Unlike the compressor disk, the compressor vane maintains a fixed state so as not to rotate, and serves to guide the compressed air to the compressor blade located downstream by aligning the flow of compressed air passing through the compressor blade.

At this time, the compressor casing and compressor vane may be defined by the comprehensive name of compressor stator to distinguish them from the compressor rotor.

The tie rod is disposed to penetrate the center of the plurality of compressor disks and the turbine disk, which will be described later, and one end is fastened to the compressor disk located at the front end of the compressor, and the other end is fastened by a fixing nut. do.

Since the shape of the tie rod may have various structures depending on the gas turbine, it is not necessarily limited to the shape shown in FIG. 1.

That is, as shown, one tie rod may have a shape that penetrates the central part of the compressor disk and the turbine disk, or a plurality of tie rods may have a shape arranged circumferentially, and a combination of these may be possible.

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

The combustor 100 mixes and combusts the incoming compressed air with fuel to produce high-energy, high-temperature, high-pressure combustion gas, and raises the temperature of the combustion gas to the heat resistance limit that the combustor and turbine parts can withstand through the isobaric combustion process. do.

A number of combustors constituting the combustion system of the gas turbine 10 may be arranged in a combustor casing formed in a cell shape, and may include a fuel nozzle 162 for injecting fuel, a liner 120 forming a combustion chamber; Liner), and a transition piece (130) that is the connection between the combustor 100 and the turbine 12.

Specifically, the liner 120 provides a combustion space in which the fuel injected by the fuel nozzle 162 is mixed with compressed air of the compressor 11 and burned. This liner 120 is formed with a combustion chamber that provides a combustion space in which fuel mixed with air is burned, and a liner annular flow path that surrounds the combustion chamber and forms an annular space.

Additionally, a fuel nozzle 162 that injects fuel is coupled to the front end of the liner 120, and an igniter is coupled to the side wall.

Compressed air introduced through a plurality of holes provided on the outer wall of the liner 120 flows in the liner annular passage, and compressed air that cools the transition piece 130, which will be described later, also flows through this.

As compressed air flows along the outer wall of the liner 120, the liner 120 can be prevented from being thermally damaged by heat generated by combustion of fuel in the combustion chamber.

At the rear end of the liner 120, a transition piece 130 is connected to send combustion gas burned by the spark plug to the turbine side.

Like the liner 120, the transition piece 130 is formed with a transition piece annular passage surrounding the internal space of the transition piece 130, and the transition piece annular passage is formed to prevent damage due to the high temperature of the combustion gas. The outer wall is cooled by compressed air flowing along it.

Meanwhile, the high-temperature, high-pressure combustion gas from the combustor 100 is supplied to the turbine 12 described above. The high-temperature, high-pressure combustion gas supplied to the turbine 12 expands as it passes through the interior of the turbine 12, and accordingly applies impulse and reaction forces to the turbine blades, which will be described later, to generate rotational torque. The rotational torque obtained in this way is transmitted to the compressor through the torque tube described above, and the portion exceeding the power required to drive the compressor is used to drive a generator, etc.

The turbine 12 is basically similar in structure to the compressor 11. That is, the turbine 12 is also provided with a plurality of turbine rotors similar to the compressor rotor of the compressor 11. Accordingly, the turbine rotor also includes a turbine disk and a plurality of turbine blades radially disposed therefrom.

Between the turbine blades, a plurality of turbine vanes are installed annularly on the turbine casing based on the same stage, and the turbine vanes guide the flow direction of combustion gas passing through the turbine blades. At this time, the turbine casing and turbine vane may also be defined by the comprehensive name turbine stator to distinguish them from the turbine rotor.

The gas turbine combustor 100 according to an embodiment of the present invention with reference to FIGS. 3 to 7 includes a nozzle casing 110, a liner 120, a transition piece 130, a porous block 140, and an inner tube body 150. , an outer tube body 160, and a mixing vane 170.

First, the nozzle casing 110 receives compressed air from the compressor 11, and rotates the compressed air in the turning area 111 formed inside the nozzle casing 110.

The liner 120 is connected to the downstream side of the nozzle casing 110 based on the flow direction of compressed air or combustion gas, and forms a combustion chamber 120a therein, which is formed from the nozzle casing 110. The injected mixed fluid (created by mixing compressed air and fuel) is burned.

The transition piece 130 is connected to the downstream side of the liner 120 and supplies combustion gas generated in the combustion chamber of the liner 120 to the turbine 12.

The porous block 140 is provided inside the nozzle casing 110 and guides the mixed fluid generated by mixing compressed air and fuel in the mixing area M to the outlet through the inlet.

At this time, the porous block 140 allows the mixed fluid generated by mixing compressed air and fuel to flow into the combustion chamber, and has a multi-tube inside ( 141).

It is preferable that the multi-tubes 141 are plural and have a micro-sized inner diameter.

Therefore, the porous block 140 can supply the mixed gas to the combustion chamber 120a at a uniform flow rate through a plurality of multi-tubes 141 having a micro-sized inner diameter.

delete

In addition, with the porous block 140 at the center, an inner tube body 150 surrounding the inlet of the porous block 140 is provided.

At this time, on one side of the inner pipe body 150 located in the mixing area (M), an inclined flange 151 is formed to be inclined in the outer circumferential direction as shown in FIG. 7. The inclined flange 151 is used to supply compressed air and fuel. By gradually reducing the width of the passage through which the gas flows, the flow speed of the compressed air and fuel flowing along the passage can be increased, while the flow speed of the compressed air and fuel turning to the mixing region can be increased.

Therefore, the compressed air and fuel that swirl and flow into the mixing zone flow in turbulence through the mixing zone and mix with each other to create a mixed fluid.

In addition, the inclined flange 151 can be formed by forming the inner tube body 150 to be inclined in the outer circumferential direction where the bypass hole 152 is formed.

And the combustor 100 includes an outer tube body 160 that is spaced apart from the circumference of the inner tube body 150 at a certain distance, with respect to the center of the inner tube body 150, and the inner tube body 150 Based on the center of , a plurality of mixing vanes 170 are arranged radially between the inner tube body 150 and the outer tube body 160.

The plurality of mixing vanes 170 provide a swirler effect to compressed air flowing into the mixing area through the inner tube body 150 and the outer tube body 160.

Accordingly, the compressed air flowing between the inner tube body 150 and the outer tube body 160 generates a swirler effect by the mixing vane 170, causing the compressed air to flow in turbulence while rotating along the passage.

Here, the inner tube body 150 forms a bypass hole 152 on the circumference of the inner tube body 150 on a position line corresponding to the entrance of the porous block 140, and the bypass hole 152 is formed in the inner tube body 150. Some of the compressed air, fuel, and mixed fluid flowing along the circumference are bypassed to the inlet of the porous block 140.

It is preferable that a plurality of bypass holes 152 are arranged at regular intervals along the circumference of the inner tube body 150.

Here, the bypass hole 152 is formed to have an inner diameter that gradually becomes smaller as it moves from the inlet to the outlet, or is formed to have an inner diameter that gradually becomes larger as it moves from the inlet to the outlet of the bypass hole (152). 152), the flow rate of some of the compressed air, fuel, and mixed fluid passing through is increased or decreased by Bernoulli's law, so that the flow amount of compressed air, fuel, and mixed fluid can be more uniformly controlled.

Figure 6 is a perspective view of an inner tube body according to another embodiment of the present invention.

Referring to FIG. 6, the inner tube body 150 according to another embodiment of the present invention is formed so that the size of the bypass hole 152 decreases toward the outlet of the inner tube body 150, so that the multi-porous block The amount of flow supplied to the tube can be uniformly adjusted.

3 to 7, the outer pipe body 160 according to an embodiment of the present invention has a plurality of fuel inlet holes 161 at regular intervals along the position line corresponding to the mixing vane 170 among its circumference. formed by

At this time, a fuel nozzle 162 is provided at the end of the fuel inlet hole 161, and the fuel introduced through the fuel inlet hole 161 is injected into the passage between the inner pipe body 150 and the outer pipe body 160. Fuel is injected into the compressed air flowing into.

Therefore, the fuel injected into the passage between the inner pipe body 150 and the outer pipe body 160 is mixed with the compressed air flowing in the passage between the inner pipe body 150 and the outer pipe body 160 to generate a mixed fluid, and the mixing Fluid is provided to the inlet of the porous block 140 through the mixing zone.

At this time, the compressed air is uniformly mixed with the fuel due to a swirler effect caused by the mixing vane 170.

Therefore, a gas turbine combustor according to an embodiment of the present invention and a gas turbine equipped with the same are provided with a mixing vane at a location where compressed air and fuel meet, and the compressed air and fuel are mixed through a swirler effect through the mixing vane. By improving the mixing, it is possible to supply mixed fluid at a uniform flow rate to the porous block. Additionally, by bypassing some of the compressed air directly to the porous block, the supply of mixed fluid generated by mixing compressed air and fuel is reduced. It can be resolved.

Additionally, the fuel may be supplied inside the vane 170 and through a hole formed in the wall of the vane 170.

Figure 7 is a cross-sectional view showing a gas turbine combustor according to another embodiment of the present invention.

Referring to FIG. 7, an inclined flange 151 is formed at the inlet end of the inner tube 150 of a gas turbine combustor according to another embodiment of the present invention.

The inclined flange 151 extends radially outward from the inlet of the inner tube body and is formed to be inclined at a certain angle with the inner tube body 150. The inclined flange 151 adjusts the inclination with the inner tube body 150 to appropriately guide the flow of some of the compressed air, fuel, and mixed fluid flowing along the circumference of the inner tube body 150 to the outside, thereby creating a porous structure. The amount of flow supplied to the multi-tube of the block can be uniformly adjusted.

The present invention has been described with reference to the embodiments shown in the drawings, but these are merely exemplary, and those skilled in the art will understand that various modifications and equivalent other embodiments are possible therefrom. Therefore, the true scope of technical protection of the present invention should be determined by the technical spirit of the attached patent claims.

100: Gas turbine combustor
110: nozzle casing
111: turning area
120: Liner
130: Transition piece
140: Porous block
141: Multitube
150: inner tube body
151: Inclined flange
152: Bypass hole
160: outer tube body
161: Fuel inlet hole
162: Fuel nozzle
170: Mixing vane
M: Mixed area

Claims (18)

In the combustor, which mixes compressed air supplied from the compressor with fuel and combusts it, and supplies the generated combustion gas to the turbine,
a nozzle casing that receives compressed air from the compressor;
A liner connected to the nozzle casing and forming a combustion chamber that burns a mixed fluid generated by mixing compressed air and fuel inside the nozzle casing;
a transition piece connected to the liner and supplying combustion gas generated by combustion in the liner to the turbine;
A porous block provided inside the nozzle casing and supplying the mixed fluid to the combustion chamber;
An inner tube body disposed at the entrance of the porous block and surrounding the entrance to the porous block;
an outer tube body disposed spaced apart from the inner tube body and forming a passage through which compressed air and fuel flow between the inner tube body and the inner tube body; and
A gas turbine combustor comprising a plurality of mixing vanes arranged radially between the inner tube body and the outer tube body and providing a swirler effect to the compressed air and fuel flowing along the passage between the inner tube body and the outer tube body. .
In claim 1,
The inner tube body is
A gas turbine combustor in which a bypass hole is formed to guide a portion of the mixed fluid that has passed through the mixing vane to the inlet of the porous block.
In claim 2,
The bypass hole is
A gas turbine combustor formed in plural pieces arranged at regular intervals along the circumference of the inner tube body.
In claim 2,
The bypass hole is
A gas turbine combustor characterized in that the inner diameter of the inner tube gradually becomes smaller from the inlet to the outlet.
In claim 1,
A gas turbine combustor including an inclined flange in which an inlet end of the inner tube body is formed to be inclined.
In claim 1,
The outer tube body is
A gas turbine combustor in which a plurality of fuel inlet holes are formed at regular intervals along a line corresponding to the mixing vane.
In claim 6,
A gas turbine combustor including a fuel nozzle formed in the fuel inlet hole and controlling the amount of fuel ejected through the fuel inlet hole.
In claim 1,
The porous block is
A gas turbine combustor equipped with a multi-tube inside the length that guides the mixed fluid created by mixing compressed air and fuel from the inlet to the outlet.
delete A compressor that compresses air supplied from outside;
A turbine that generates power for electric power generation as combustion gases are passed therein; and
It includes a combustor that mixes the compressed air supplied from the compressor with fuel and combusts it, and supplies the generated combustion gas to the turbine,
The combustor
a nozzle casing that receives compressed air from the compressor;
A liner connected to the nozzle casing and forming a combustion chamber that burns a mixed fluid generated by mixing compressed air and fuel inside the nozzle casing;
a transition piece connected to the liner and supplying combustion gas generated by combustion in the liner to the turbine;
A porous block provided inside the nozzle casing and supplying the mixed fluid to the combustion chamber;
An inner tube body disposed at the entrance of the porous block and surrounding the entrance to the porous block;
an outer tube body disposed spaced apart from the inner tube body and forming a passage through which compressed air and fuel flow between the inner tube body and the inner tube body; and
A gas turbine comprising: a plurality of mixing vanes arranged radially between the inner tube body and the outer tube body and providing a swirler effect to the compressed air and fuel flowing along the passage between the inner tube body and the outer tube body.
In claim 10,
The inner tube body is
A gas turbine in which a bypass hole is formed to guide a portion of the mixed fluid that has passed through the mixing vane to the inlet of the porous block.
In claim 11,
The bypass hole is
A gas turbine formed by forming a plurality of gas turbines arranged at regular intervals along the circumference of the inner tube body.
In claim 11,
The bypass hole is
A gas turbine characterized by the inner diameter becoming gradually smaller from the inlet to the outlet of the inner tube.
In claim 10,
A gas turbine including an inclined flange in which an inlet end of the inner tube body is formed to be inclined.
In claim 10,
The outer tube body is
A gas turbine in which a plurality of fuel inlet holes are formed at regular intervals along the line corresponding to the mixing vane.
In claim 15,
A gas turbine comprising a fuel nozzle formed in the fuel inlet hole and controlling the amount of fuel ejected through the fuel inlet hole.
In claim 10,
The porous block is
A gas turbine equipped with a multi-tube inside the length that guides the mixed fluid created by mixing compressed air and fuel from the inlet to the outlet. delete

Images