KR20230126372A - Gas turbine combustor and gas turbine having same - Google Patents

Abstract

The present invention provides a gas turbine combustor and a gas turbine including the same. The gas turbine combustor includes: a nozzle casing receiving compressed air from a compressor; a liner connected to the nozzle casing and forming a combustion chamber in which a mixed fluid generated by mixing the compressed air and fuel is combusted inside the nozzle casing; a transition piece connected to the liner and supplying flue gas generated by combustion in the liner to a turbine; a porous block provided inside the nozzle casing and directing the mixed fluid generated by mixing the compressed air and fuel in a mixing zone through an inlet to an outlet; an inner tube centered on the porous block and surrounding the periphery of the inlet side of the porous block; an outer tube spaced at a distance from the periphery of the inner tube with respect to the center of the inner tube and forming a passage through which the compressed air and fuel flow between the inner tube and the outer tube; and a plurality of mixing vanes arranged radially between the inner tube and the outer tube, relative to the center of the inner tube, to impart a swirler effect to the compressed air and fuel flowing along the passage between the inner tube and the outer tube. The mixing vane improves the mixing of compressed air and fuel through a swirler effect, ultimately supplying the mixed fluid at a uniform flow rate to the porous block. In addition, some of the compressed air is directly bypassed through the porous block, eliminating the supply shortage of the mixed fluid generated by mixing the compressed air and fuel.

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 with the same, and more particularly, to a gas turbine combustor for mixing and combusting compressed air supplied from a compressor with fuel and supplying the generated combustion gas to a turbine, and having the same It's about gas turbines.

In general, a turbo machine means a device that generates power for power generation through a fluid (particularly, a gas) passing through the turbo machine. Therefore, turbomachines are usually installed and used together with generators. Such turbomachines may include gas turbines, steam turbines, wind power turbines, and the like. A gas turbine is a device that generates combustion gas by mixing and combusting compressed air and natural gas, and generates power for power generation using the combustion gas generated in this way. 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 electricity generation.

Looking at a gas turbine among turbomachines, a gas turbine includes a compressor, a combustor, and a turbine. In the compressor, a plurality of compressor vanes and compressor blades are alternately arranged in a compressor casing. And the compressor sucks in air from the outside through a compressor inlet scroll strut. Air sucked in as described above is compressed by the compressor vanes and compressor blades while passing through the inside of the compressor. The combustor receives compressed air from the compressor and mixes it with fuel. In addition, the combustor generates high-temperature and high-pressure combustion gas by igniting the fuel mixed with compressed air with an igniter. The combustion gas thus generated is supplied to the turbine. In the turbine, a plurality of turbine vanes and turbine blades are alternately arranged in a turbine casing. The turbine receives the combustion gas generated from the combustor and passes it through the inside. The combustion gas passing through the inside of the turbine rotates the turbine blades, and the combustion gas passing completely 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 a combustion chamber, and the microtubes supply compressed air and fuel to the combustion chamber and burn them to generate high-temperature, high-pressure gas.

However, it is preferable that the compressed air and fuel supplied to the plurality of microtubes be uniformly supplied, but there is a case where the compressed air and fuel are not uniformly supplied to the plurality of microtubes. In this case, the flame is uniformly induced. However, there was a problem in that noise and vibration were generated during the combustion process due to the non-uniform supply of compressed air and fuel.

The background technology of the present invention may refer to Korean Patent Registration No. 10-2164622 (registered on October 5, 2020).

In the present invention, a mixing vane is provided at a position where compressed air and fuel meet, and mixing of compressed air and fuel is improved by a swirl effect through the mixing vane, and finally, a mixed fluid having a uniform flow rate is obtained through porous It is possible to supply a gas turbine combustor that can be supplied to a block, and also bypasses some of the compressed air directly to a porous block, thereby solving a shortage of supply of a mixed fluid produced by mixing compressed air and fuel, and a gas turbine equipped with the same. The purpose.

The gas turbine combustor according to the present invention includes a nozzle casing receiving compressed air from the compressor; a liner connected to the nozzle casing and forming a combustion chamber for burning 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 disposed at the inlet of the porous block and surrounding the circumference of the inlet of the porous block; an outer tube body spaced apart from the outer side of 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 to give 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 for guiding a part of the mixed fluid passing through the mixing vane to the inlet side of the porous block.

Here, the bypass holes according to the present invention are formed by being arranged at regular intervals along the circumference of the inner tube body in plurality.

In addition, the bypass hole according to the present invention may have an inner diameter gradually decreasing from the inlet to the outlet of the inner tube body.

In addition, the bypass hole according to the present invention may be formed in an elliptical shape having 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 a position line corresponding to the mixing vane among its periphery.

At this time, it is formed in the fuel inlet hole according to the present invention, and is provided with a fuel nozzle for adjusting the ejection amount of the fuel ejected through the fuel inlet hole.

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

At this time, the inlet of the porous block according to the present invention may protrude toward the mixing region.

A gas turbine according to the present invention includes a compressor for compressing air supplied from the outside; A turbine that generates power for power generation as the combustion gas passes therein; and a combustor which mixes the compressed air supplied from the compressor with fuel and supplies the generated combustion gas to the turbine, wherein the combustor includes a nozzle casing receiving compressed air from the compressor, and a nozzle casing A liner connected to the nozzle casing and forming a combustion chamber for burning a mixed fluid generated by mixing compressed air and fuel inside the nozzle casing, connected to the liner, and supplying combustion gas generated by combustion in the liner to the turbine. a transition piece provided inside the nozzle casing and supplying the mixed fluid to the combustion chamber; an inner tube disposed at the inlet of the porous block and surrounding the circumference of the inlet of the porous block; and , Arranged spaced apart from the outside of the inner tube body, the outer tube body forming a passage through which compressed air and fuel flow between the inner tube body, and radially arranged between the inner tube body and the outer tube body, the inner tube body and It includes a plurality of mixing vanes that give a swirler effect to the compressed air and fuel flowing along the passage between the outer tube bodies.

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

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

In addition, a part of the compressed air is directly bypassed to the porous block, so that the compressed air and the fuel are mixed to have an effect of resolving the supply shortage of the generated mixed fluid.

1 is a cross-sectional view showing a gas turbine according to the present invention.
FIG. 2 is a diagram schematically illustrating the combustor shown in FIG. 1 .
3 is a schematic cross-sectional view of a gas turbine combustor according to an embodiment of the present invention.
4 is a perspective view showing configurations of an inner pipe body, an outer pipe body, and a mixing vane in a gas turbine combustor according to an example of the present invention.
5 is a cross-sectional view showing an example of a bypass hole formed in an inner tube body of a gas turbine combustor according to an example of the present invention.
6 is a perspective view of an inner tubular body according to another embodiment of the present invention.
7 is a cross-sectional view showing a gas turbine combustor having 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 accompanying drawings. Prior to this, the terms or words used in this specification and claims should not be construed as being limited to the usual or dictionary meaning, and the inventor appropriately uses the concept of the term in order to explain his/her invention in the best way. Based on the principle that it can be defined, it should be interpreted as meaning and concept consistent with the technical spirit 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 all of the technical ideas of the present invention, so at the time of the present application, they are equivalent alternatives that can be replaced. It should be understood that variations may exist.

In the present invention, a mixing vane is provided at a position where compressed air and fuel meet, and mixing of compressed air and fuel is improved by a swirl effect through the mixing vane, and finally, a mixed fluid having a uniform flow rate is provided. It relates to a gas turbine combustor that can be supplied to a block and a gas turbine equipped with the same, referring to the drawings as follows.

Referring to FIGS. 1 and 2 , a 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), the compressor 11 is disposed on the upstream side of the gas turbine 10 and the turbine 12 is disposed on the downstream side. The compressor 11 and the turbine 12 ) The combustor 100 is disposed between them.

The compressor 11 accommodates a compressor vane and a compressor rotor inside a compressor casing, and the turbine 12 accommodates a turbine vane 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 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 intake air can be compressed, and the turbine 12, on the contrary, expands the combustion gas supplied from the combustor. It is designed with a structure in which the internal space increases from the front end to the rear end.

On the other hand, between the compressor rotor located at the rear end of the compressor 11 and the turbine rotor located at the front end of the turbine 12, the rotational torque generated in the turbine 12 is transmitted to the compressor 11 A torque tube as a torque transmission member is disposed.

As shown in FIG. 1, the torque tube may be composed of a plurality of torque tube disks having a total of three stages, 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 also consist of a plurality of torque tube disks with two or less stages.

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

More specifically, the respective compressor disks are aligned along the axial direction with their central portions penetrated by the tie rods, and the opposing surfaces of the adjacent compressor disks are compressed by the tie rods, so that relative to each other. It is arranged so that it cannot rotate.

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

In addition, between the compressor blades, a plurality of compressor vanes which are annularly installed on the inner circumferential surface of the compressor casing are disposed on the basis of the same stage.

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 positioned downstream by aligning the flow of compressed air passing through the compressor blade.

In this case, the compressor casing and the compressor vane may be defined as a comprehensive name of a compressor stator in order to be distinguished from the compressor rotor.

The tie rod is disposed to pass through the center of the plurality of compressor disks and a turbine disk to be described later, one end is fastened into 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 be formed in 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 penetrating the center of the compressor disk and the turbine disk, or a plurality of tie rods may have a shape in which a plurality of tie rods are disposed in a circumferential shape, and a combination thereof is also possible.

Although not shown, a deswirler serving as a guide vane may be installed in the compressor of the gas turbine 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.

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

A plurality of combustors constituting the combustion system of the gas turbine 10 may be arranged in a combustor casing formed in a cell shape, and include a fuel nozzle 160 for injecting fuel, a liner 120 for forming a combustion chamber; Liner), and a transition piece 130 serving as a 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 160 is mixed with compressed air of the compressor 11 and burned. The liner 120 is formed with a combustion chamber providing a combustion space in which fuel mixed with air is combusted, and a liner annular flow path forming an annular space while surrounding the combustion chamber.

In addition, a fuel nozzle 160 for injecting fuel is coupled to the front end of the liner 120, and an igniter is coupled to a side wall.

Compressed air introduced through a plurality of holes provided in the outer wall of the liner 120 flows in the annular liner passage, and compressed air cooling the transition piece 130 to be described later also flows therethrough.

As the compressed air flows along the outer wall of the liner 120, it is possible to prevent the liner 120 from being thermally damaged by heat generated by combustion of fuel in the combustion chamber.

A transition piece 130 is connected to the rear end of the liner 120 so as to send the combustion gas burned by the spark plug to the turbine side.

Like the liner 120, the transition piece 130 has a transition piece annular flow path surrounding the inner space of the transition piece 130, and the transition piece annular flow path prevents damage due to high temperature of the combustion gas. The outer wall is cooled by the 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 and high-pressure combustion gas supplied to the turbine 12 expands while passing through the inside of the turbine 12, and thus applies impulse and reaction forces to the turbine blades to be described later so that rotational torque is generated. The rotational torque obtained in this way is transmitted to the compressor via the above-described torque tube, and a portion exceeding the power necessary for driving the compressor is used to drive a generator or the like.

The turbine 12 is basically similar to the structure of 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 which are annularly installed in the turbine casing with reference to the same stage are provided, and the turbine vanes guide the flow direction of the combustion gas passing through the turbine blades. At this time, the turbine casing and the turbine vane may also be defined as a comprehensive name of a turbine stator in order 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 a 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 the compressed air or combustion gas, and forms a combustion chamber 120a therein, the combustion chamber from the nozzle casing 110. Combusts the injected mixed fluid (which creates a mixture of compressed air and fuel).

The transition piece 130 is connected to the downstream side of the liner 120 and supplies the 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 the multi-tube guides the mixed fluid mixed in the mixing area along its length from the inlet to the outlet. (141).

It is preferable that the multi-tube 141 is plural, and the inner diameter thereof forms a micro size.

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

In addition, the inlet of the porous block 140 protrudes toward the mixing area, so that the uniformity of the mixed fluid can be improved.

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

At this time, an inclined flange 151 is formed to be inclined in an outer circumferential direction on one side of the inner tube body 150 located in the mixing area M. By gradually reducing, the flow rate of the compressed air and fuel flowing along the passage can be increased while the flow rate of the compressed air and fuel turning into the mixing area can be increased.

Therefore, the compressed air and the fuel, which are swirled and introduced into the mixing region, are mixed with each other while flowing in the mixing region in a turbulent flow to create a mixed fluid.

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

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

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

Therefore, 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, so that the compressed air flows in a turbulent flow while turning along the passage.

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

The number of bypass holes 152 is preferably arranged at regular intervals along the circumference of the inner tube body 150 .

Here, the bypass hole 152 is formed so that the inner diameter gradually decreases from the inlet to the outlet, or the inner diameter gradually increases from the inlet to the outlet of the bypass hole 152, so that the bypass hole ( 152), the flow rate of some of the compressed air, fuel, and mixed fluids passing through is increased or decreased according to Bernoulli's law, so that the flow rates of compressed air, fuel, and mixed fluids can be more uniformly controlled.

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

Referring to FIG. 6, in the inner tube body 250 according to another embodiment of the present invention, the bypass hole 252 is formed so that the size decreases toward the outlet of the inner tube body 250, The amount of flow supplied to the tube can be uniformly controlled.

3 to 8, the outer tube body 160 according to an embodiment of the present invention has a plurality of fuel inlet holes 161 at regular intervals along a position line corresponding to the mixing vane 170 in its circumference. form with

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

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 create a mixed fluid, and the mixing The 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 by generating a swirler effect according to the mixing vane 170 .

Therefore, a gas turbine combustor and a gas turbine equipped with the same according to an embodiment of the present invention are provided with a mixing vane at a position where compressed air and fuel meet, and through the mixing vane, the compressed air and fuel are swirled in a swirl effect. By improving the mixing of the mixture, it is possible to finally supply the mixed fluid with a uniform flow rate to the porous block, and also bypass some of the compressed air directly to the porous block, so that the supply of the mixed fluid produced by mixing the compressed air and fuel is eliminated. can be resolved

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

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 351 is formed at an outlet end of the inner tube body 350 of the gas turbine combustor according to another embodiment of the present invention.

The inclined flange 351 extends outward in the radial direction from the outlet of the inner tube body and is inclined at a predetermined angle with the inner tube body 350 . The inclined flange 351 adjusts the inclination with the inner tube body 350 to appropriately guide the flow of some of the compressed air, fuel, and mixed fluid flowing along the circumference of the inner tube body 350 to the outside, It is possible to uniformly adjust the amount of flow supplied to the multi-tube of the block.

Although the present invention has been described with reference to the embodiments shown in the drawings, this is only exemplary, and those skilled in the art will understand that various modifications and equivalent other embodiments are possible therefrom. Therefore, the true technical protection scope of the present invention should be determined by the technical spirit of the appended claims.

100: gas turbine combustor
110: nozzle casing
111: turning area
120: liner
130: transition piece
140: porous block
141: multitube
150: inner tube
151: inclined flange
152: bypass hole
160: outer tube
161: fuel inlet hole
162: fuel nozzle
170: mixed vane
M: mixed region

Claims (18)

In a combustor that mixes and burns compressed air supplied from a compressor with fuel and supplies the generated combustion gas to a turbine,
a nozzle casing receiving compressed air from the compressor;
a liner connected to the nozzle casing and forming a combustion chamber for burning 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 disposed at the inlet of the porous block and surrounding the circumference of the inlet of the porous block;
an outer tube body spaced apart from the outer side of 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 including a plurality of mixing vanes arranged radially between the inner tube body and the outer tube body to give a swirler effect to compressed air and fuel flowing along a passage between the inner tube body and the outer tube body. .
The method of claim 1,
the inner tube
A gas turbine combustor having a bypass hole for guiding a portion of the mixed fluid passing through the mixing vane to the inlet side of the porous block.
The method of claim 2,
The bypass hole is
A plurality of gas turbine combustors arranged at regular intervals along the circumference of the inner tube body.
The method of claim 2,
The bypass hole is
A gas turbine combustor, characterized in that the inner diameter gradually decreases from the inlet to the outlet of the inner tube body.
The method of claim 1,
A gas turbine combustor including an inclined flange in which one side of the inner tube is formed to be inclined.
The method of claim 1,
the outer tube
A gas turbine combustor in which a plurality of fuel inlet holes are formed at regular intervals along a position line corresponding to the mixing vane among its circumference.
The method of claim 6,
A gas turbine combustor having a fuel nozzle formed in the fuel inlet hole and controlling an ejection amount of fuel ejected through the fuel inlet hole.
The method of claim 1,
The porous block is
A gas turbine combustor having a multi-tube therein for guiding a mixed fluid generated by mixing compressed air and fuel along a length thereof from an inlet to an outlet.
The method of claim 8,
The porous block is
A gas turbine combustor whose inlet part protrudes toward the mixing region.
A compressor for compressing air supplied from the outside;
A turbine that generates power for power generation as the combustion gas passes therein; and
A combustor mixing and combusting the compressed air supplied from the compressor with fuel and supplying the generated combustion gas to the turbine,
the combustor
a nozzle casing receiving compressed air from the compressor;
a liner connected to the nozzle casing and forming a combustion chamber for burning 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 disposed at the inlet of the porous block and surrounding the circumference of the inlet of the porous block;
an outer tube body spaced apart from the outer side of 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 radially arranged between the inner tube body and the outer tube body to give a swirler effect to the compressed air and fuel flowing along the passage between the inner tube body and the outer tube body.
The method of claim 10,
the inner tube
A gas turbine having a bypass hole for guiding a portion of the mixed fluid passing through the mixing vane to the inlet side of the porous block.
The method of claim 11,
The bypass hole is
A gas turbine formed by arranging a plurality of pieces at regular intervals along the circumference of the inner tube body.
The method of claim 11,
The bypass hole is
A gas turbine, characterized in that the inner diameter gradually decreases from the inlet to the outlet of the inner tube body.
The method of claim 10,
A gas turbine comprising an inclined flange in which one side of the inner tube is formed to be inclined.
The method of claim 10,
the outer tube
A gas turbine in which a plurality of fuel inlet holes are formed at regular intervals along the position line corresponding to the mixing vane among its periphery.
The method of claim 15
A gas turbine having a fuel nozzle formed in the fuel inlet hole to control an ejection amount of fuel ejected through the fuel inlet hole.
The method of claim 10,
The porous block is
A gas turbine having a multi-tube inside which guides a mixed fluid generated by mixing compressed air and fuel along its length from an inlet to an outlet.
The method of claim 17
The porous block is
A gas turbine whose inlet part protrudes toward the mixing area.

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