WO2014073732A1

WO2014073732A1 - Dual swirling flow combustion device for gas turbine

Info

Publication number: WO2014073732A1
Application number: PCT/KR2012/009939
Authority: WO
Inventors: 이기만
Original assignee: 순천대학교 산학협력단
Priority date: 2012-11-08
Filing date: 2012-11-22
Publication date: 2014-05-15
Also published as: KR101225323B1

Abstract

A dual swirling flow combustion device for a gas turbine according to the present invention comprises: a first fuel supply part which has a fuel inlet formed at one side and a fuel injection hole formed at the other side so as to inject fuel towards a combustion chamber; a second fuel supply part which is formed to surround the outside of the first fuel supply part so as to form a path for the fuel supply together with the first fuel supply part; an air inlet part provided at the outside of the second fuel supply part to supply air to be mixed with the fuel; a first air supply part for guiding the air introduced through the air inlet such that the introduced air can be mixed with the fuel of the first fuel supply part; a second air supply part for guiding the air introduced through the air inlet such that the introduced air can be mixed with the fuel of the second fuel supply part; a first swirler provided at one side of the first air supply part and enabling the air of the first air supply part to swirl such that the air can be pre-mixed with the fuel of the first fuel supply part; and a second swirler provided at one side of the second air supply part and enabling the air of the second air supply part to swirl such that the air can be pre-mixed with the fuel of the second fuel supply part, wherein the fuel pre-mixed by the first swirler and the fuel pre-mixed by the second swirler are mixed together so as to be sprayed at the combustion chamber, and the direction of the air swirling by the first swirler and the direction of the air swirling by the second swirler are opposite to each other.

Description

Gas turbine dual swirl flow combustor

The present invention relates to a gas turbine double swirl flow combustor, and more specifically, a plurality of fuel supply pipe and the gas supplied by the air supply pipe and the fuel is mixed and discharged while rotating in the opposite direction by each swirler A turbine dual swirl flow combustor.

In general, a gas turbine system is a system for driving a turbine by using a high temperature and high pressure combustion gas generated through a compressor and a combustor. Have.

The combustor used in such a gas turbine is a device that generates a flame by using a combustion reaction, and is a device that generates by ignition of fuel under the condition that air is supplied. Fuel and air are supplied to the combustion chamber through a fuel supply pipe and an air supply pipe provided in the combustor, and a swirler is provided at the end of the air supply pipe to mix fuel and air.

However, the combustor according to the prior art has a problem that it is impossible to combust at a uniform temperature during combustion because the mixing is not made because the mixer is rotated in one direction at the end of the air supply pipe.

In this regard, the technology of the premixed gas turbine combustor having a double mixing structure for reducing the NOx (nitrogen oxide) is disclosed as Korea Patent Publication No. 10-1110144, but turning the air supplied in the opposite direction There is a problem in that the turning machine is continuously provided to rotate the air rotating in one direction again in the opposite direction to reduce the discharge pressure. In addition, there is a problem that one fuel supply pipe is provided so that at least one fuel supply pipe is closed when the output of the combustor is adjusted, so that uniform combustion is not possible inside the combustor.

In addition, according to the prior art, the gas turbine engine, which is a continuous combustion engine, has a safety problem, such that the flame is easily extinguished by misfire.

[Preceding technical literature]

[Patent Documents]

Republic of Korea Patent Publication No. 10-1110144 (2012.01.19.)

The present invention is designed to solve the above problems, the gas turbine dual swirl flow combustion apparatus according to the present invention, the fuel is supplied through the first fuel supply and the second fuel supply, respectively, is supplied through the air inlet pipe It is an object of the present invention to provide a gas turbine double swirl flow combustor in which air and fuel are mixed by a swirler which is supplied with air to the first fuel supply unit and the second fuel supply unit and pivots in opposite directions.

Another object of the present invention is to provide a gas turbine double swirl flow combustion apparatus in which the mixed fuel discharged in opposite directions is mixed once again to discharge the mixed fuel uniformly mixed inside the discharge port.

In addition, according to the operating load of the gas turbine, it is possible to block the fuel supply of the second fuel supply unit to control the fire power while supplying fuel to a predetermined set value inside the combustor, and shut off the fuel supply of the second fuel supply unit. It is another object of the present invention to provide a gas turbine double swirl flow combustor capable of improving the stability of the combustor by continuously supplying fuel into the combustor to prevent combustion in the combustor.

The problem to be solved by the present invention is not limited to the above-mentioned problem, another problem to be solved by the present invention not mentioned here is apparent to those skilled in the art from the following description. Can be understood.

Gas turbine double swirl flow combustion apparatus according to the present invention, the fuel inlet is formed on one side, the fuel injection port for injecting fuel toward the combustion chamber on the other side is formed to surround the outside of the first fuel supply and the first fuel supply A second fuel supply unit forming a flow path for supplying fuel together with the first fuel supply unit, and an air inlet unit provided outside the second fuel supply unit and supplying air for mixing with the fuel; A first air supply unit guiding air to be mixed with fuel of the first fuel supply unit and a second air supply unit guiding air introduced into the air inlet unit to be mixed with fuel of the second fuel supply unit; 1 is provided on one side of the air supply unit, by turning the air of the first air supply unit may be premixed with the fuel of the first fuel supply unit. And a second swirler provided at one side of the first swirler and the second air supply unit to pivot the air of the second air supply unit to be premixed with the fuel of the second fuel supply unit. The premixed fuel by the swirler and the premixed fuel by the second swirler are mixed and injected into the combustion chamber, and the turning direction of the air by the first swirler and the turning direction of the air by the second swirler are opposite. It features.

The fuel inlet of the first fuel supply unit and the fuel inlet of the second fuel supply unit are separately formed, and the fuel of the first fuel supply unit and the second fuel supply unit may be independently supplied.

How to cut off the fuel supply of the fuel supply of any one of the first fuel supply and the second fuel supply according to the engine operating conditions or adjusting the fuel supply of any one of the first fuel supply and the second fuel supply. It is characterized in that the thermal power control is possible by the method.

The air supply unit may further include a bypass unit for supplying and premixing the air to the first fuel supply unit before at least a portion of the air reaches the first swirler.

A chamber for uniformly diffusing fuel introduced into the second fuel supply unit may be provided inside the second fuel supply unit.

The second fuel supply unit extends more than the fuel injection port of the first fuel supply unit, and a space for injecting the premixed fuel by the first swirler and the premixed fuel by the second swirler into the combustion chamber therein. The fuel mixing unit is further formed, wherein the inner diameter of the fuel mixing unit is formed such that the inner diameter decreases and increases toward the end of the fuel mixing unit, and the injection force toward the combustion chamber is increased.

The first swirler is provided in a spiral shape capable of turning the air supplied through the first air supply part, and the second swirler is tangentially directed toward the second fuel supply part on the second air supply part track. It is formed to have an inclined surface of the air inlet is characterized in that for turning the air supplied through.

In the gas turbine double swirl flow combustor according to the present invention, the fuel is supplied through the first fuel supply unit and the second fuel supply unit, and the air supplied through the air inlet pipe is supplied by the first means. There is an effect that the air and the fuel is mixed by a swirler which is supplied to the fuel supply unit and the second fuel supply unit and pivots in opposite directions.

Further, inside the discharge port, there is an effect of discharging the mixed fuel uniformly mixed by mixing the mixed fuel discharged in the opposite direction again.

In addition, according to the operating load of the gas turbine, it is possible to block the fuel supply of the second fuel supply unit to control the fire power while supplying fuel to a predetermined set value inside the combustor, and shut off the fuel supply of the second fuel supply unit. The fuel of the first fuel supply unit continuously supplies fuel to the combustor, thereby preventing the combustion in the combustor from stopping and improving the stability of the combustor.

1 is an overall cross-sectional perspective view of a gas turbine double swirl flow combustor according to the present invention.

2 is a partial cross-sectional perspective view of a gas turbine double swirl flow combustor according to the present invention.

3 is a cross-sectional view of the first air supply unit and the second air supply unit of the gas turbine double swirl flow combustion apparatus according to the present invention.

4 is a detailed cross-sectional view of a gas turbine double swirl flow combustor according to the present invention.

Specific matters including the problem to be solved, the solution to the problem, and the effects of the present invention as described above are included in the embodiments and drawings to be described below. Advantages and features of the present invention, and methods for achieving them will be apparent with reference to the embodiments described below in detail in conjunction with the accompanying drawings.

Hereinafter, with reference to the accompanying drawings will be described in detail the present invention.

As shown in FIG. 2, the gas turbine dual swirl flow combustor according to the present invention supplies air for mixing with fuel and a first fuel supply unit 10 and a second fuel supply unit 20 to independently supply fuel. To be mixed with the fuel of the air inlet unit 30, the first air supply unit 40 for guiding air to be mixed with the fuel of the first fuel supply unit 10, and the fuel of the second fuel supply unit 20. A second air supply unit for guiding the air so as to be able to, and the first turning unit 60 for turning the air of the first air supply unit 40 and the second turning the air of the second air supply unit 50 It may be configured to include two swinger (70).

First, the first gas supply unit 10 is provided in the gas turbine double swirl flow combustor according to the present invention. The first fuel supply unit 10 has a fuel inlet on one side and a fuel injection port for injecting fuel toward the combustion chamber on the other side. That is, the first fuel supply unit 10 supplies the fuel supplied through the fuel inlet to the combustion chamber.

The second fuel supply unit 20 is provided outside the first fuel supply unit 10. The second fuel supply unit 20 is formed to surround the outside of the first fuel supply unit 10. The first fuel supply unit 10 corresponds to a flow path for supplying fuel to the combustion chamber, and the second fuel supply unit 20 independently of the first fuel supply unit 10 to a flow path for supplying fuel to the combustion chamber. Corresponding.

That is, the second fuel supply unit 20 also has a fuel inlet on one side and a fuel injection port on the other side to supply fuel to the combustion chamber.

In addition, the fuel inlet of the first fuel supply unit 10 and the fuel inlet of the second fuel supply unit 20 are separately formed to supply fuel. That is, the first fuel supply unit 10 and the second fuel supply unit 20, the fuel is independently supplied to the combustion chamber by a fuel inlet formed separately from the outside of the combustor, respectively.

An air inlet 30 is provided outside the second fuel supply unit 20. The air inlet unit 30 supplies air for mixing with the fuel supplied to the first fuel supply unit 10 and the second fuel supply unit 20.

On the line of the air inlet section 30, a first air supply section 40 is provided. The first air supply unit 40 guides the air introduced through the air inlet unit 30 to be mixed with the fuel of the first fuel supply unit 10.

In more detail, as shown in FIG. 3, the first air supply unit 40 penetrates through the second fuel supply unit 20 from the air inlet unit 30 to the outside of the first fuel supply unit 10. A flow path through which air between the outside of the first fuel supply unit 10 and the inside of the second fuel supply unit 20 flows is formed surrounding the first fuel supply unit 10, and the air inlet unit 30 of the Guide the air to be mixed with the fuel supplied through the first fuel supply (10).

That is, the first air supply part 40 includes an inward flow part for guiding the air of the air inflow part 30 in the inward direction of the air inflow part 30, and the air passing through the inward flow part in the combustion chamber. It includes a discharge flow portion for guiding to discharge toward the. In this case, the inward flow portion of the first air supply portion 40 is formed to guide the air to the discharge flow portion of the first air supply portion 40 through the second fuel supply portion 20. The discharge flow portion of the first air supply unit 40 corresponds to a flow path through which air flows between the outside of the first fuel supply unit 10 and the inside of the second fuel supply unit 20. In addition, the discharge flow portion of the first air supply unit 40 is formed to surround the first fuel supply unit 10.

In addition, a second air supply unit 50 is provided on the air inlet unit 30. The second air supply unit 50 is provided on the air inlet unit 30 so that the air introduced into the air inlet unit 30 can be mixed with the fuel supplied to the second fuel supply unit 20. To guide. That is, the second air supply unit 50 supplies the air supplied to the air inlet unit 30 on the line of the second fuel supply unit 20.

In more detail, the second air supply unit 50 may guide the air of the air inlet unit to the inside of the air inlet unit to flow into the second fuel supply unit 20. The second fuel supply unit 20 is in communication.

In this case, the second air supply unit 50 is located in the direction toward the combustion chamber with respect to the chamber 24 on the air inlet unit 30 track, and the inward flow portion of the first air supply unit 40 Located between the chamber 24 and the second air supply unit 50. That is, the inward flow portion of the first air supply unit 40 is formed through the second fuel supply unit 20 corresponding to the chamber 24 and the second air supply unit 50.

On the other hand, the second fuel supply unit 20, a fuel flow section for guiding to be mixed with the air of the second air supply unit 50 receives the fuel in the fuel inlet, the fuel and the second fuel flow section And a mixed flow unit configured to guide the mixed fuel mixed with the air of the air supply unit 50 to the combustion chamber through the fuel injection port.

In addition, the mixed flow part of the second fuel supply part 20 is formed on the outside with respect to the discharge flow part of the first air supply part 40 so as to surround the discharge flow part of the first air supply part 40. Therefore, as a whole, the discharge flow portion of the first air supply portion 40, the mixed flow portion of the second fuel supply portion 20, and the air supply portion 30 outside the first fuel supply portion 10. ) Will be arranged in order.

One side of the first air supply unit 40 is provided with a first swirler 60. As shown in FIG. 3, the first swirler 60 is spirally wrapped around the first fuel supply unit 10 so as to pivot air supplied through the first air supply unit 40. It is provided at the end of the first air supply (40). That is, the first swirler 60 may mix the fuel of the first fuel supply unit 10 with the air supplied to the air inlet unit 30 at the end of the first fuel supply unit 10. By turning the air, it serves to premix the fuel and air supplied before being blown into the combustor.

One side of the second air supply unit 50 is provided with the second swirler 70. As shown in FIG. 3, the second swirler 70 may be provided at one side of the second air supply unit 50 to pivot the air supplied through the second air supply unit 50 in a tangential direction. Make sure That is, the second swirler 70 has an inclined surface toward the second fuel supply unit 20 on the line of the second air supply unit 50 and is supplied through the air inlet unit 30. Rotates into the second fuel supply unit 20 and serves to pre-mix fuel and air moving inside the second fuel supply unit 20 before injection into the combustor.

In addition, the turning direction of the air by the first swirler 60 and the turning direction of the air by the second swirler 70 are formed in opposite directions to each other in the fuel mixing unit 22 to be described below. It is mixed again to supply a uniformly mixed mixed fuel.

The second fuel supply unit 20 is provided with a fuel mixing unit 22. As shown in FIG. 4, the fuel mixing unit 22 extends further than the fuel injection port of the first fuel supply unit 10, thereby pre-mixing fuel and the second turning by the first swirler 60. The premixed fuel by the group 70 is mixed. That is, the fuel mixing unit 22 includes the fuel before the premixed fuel supplied by the first swirler 60 and the premixed fuel supplied by the second swirler 70 are injected into the combustion chamber. The mixing unit 22 is allowed to mix again. In other words, the premixed fuel supplied while turning in the opposite directions by the first and second swirlers 60 and 70 is formed in the fuel mixing unit 22 to form a vortex, thereby pre-mixing the fuel again. By mixing once more and being injected into the combustion chamber, there is an effect that uniform combustion is possible.

In addition, the inner diameter of the fuel mixing portion 22 is formed in a shrinkage nozzle shape in which the inner diameter decreases and increases toward the end of the fuel mixing portion 22. This is because the premixed fuel supplied by the first swirler 60 and the second swirler 70 is not injected directly into the combustion chamber, but is opposite to each other in the fuel mixing portion 22 formed in the shape of a shrinking nozzle. The mixed fuel turning in the direction is mixed once again to supply the mixed fuel uniformly mixed. In addition, the fuel mixing unit 22 serves to increase the injection speed of the mixed fuel injected toward the combustion chamber by increasing the injection speed of the mixed fuel by the structural feature formed in the shrinkage nozzle shape.

The bypass part 12 may be further provided on the track of the first fuel supply part 10. The bypass unit 12 serves to supply the first fuel supply unit 10 before at least a portion of the air of the first air supply unit 40 reaches the first swirler 60.

The first fuel supply unit 10 receives a fuel from a fuel inlet and guides the fuel flow unit to be mixed with the air of the first air supply unit 40, and the fuel flow of the first fuel supply unit 10. And a mixed flow part configured to guide the fuel mixed with the negative fuel and the air of the first air supply part 40 to the combustion chamber through the fuel injection port.

That is, the bypass unit 12 supplies a part of the air supplied to the first air supply unit 40 into the first fuel supply unit 10 to move inside the first fuel supply unit 10. Before the fuel is discharged toward the combustor, air and fuel are premixed and discharged to the combustion chamber through the mixed flow portion of the first fuel supply unit 10. This has the effect of further increasing the mixing effect of air and fuel by supplying a part of air into the first fuel supply unit 10 before mixing fuel and air by the first swirler 60.

The chamber 24 is provided on the track of the second fuel supply unit 20. The chamber 24 serves to separate the fuel supplied to the first fuel supply unit 10 and the fuel and air supplied to the second fuel supply unit 20 so that they do not mix with each other. That is, the chamber 24 independently supplies the fuel of the first fuel supply unit 10 and the second fuel supply unit 20 by a structural feature formed to surround the first fuel supply unit 10. .

In addition, the chamber 24 is formed to accommodate the fuel introduced into the second fuel supply unit 20, and is provided to uniformly diffuse the fuel introduced into the chamber 24. This has the effect of supplying the fuel flowing through the second fuel supply unit 20 in the direction of the combustion chamber with a uniform pressure.

In addition, the fuel of the first fuel supply unit 10 and the second fuel supply unit 20, which are individually supplied by the structural features of the chamber 24, are supplied without being mixed with each other and are formed separately according to the gas turbine engine load. Through the first fuel supply unit 10 and the second fuel supply unit 20 it is possible to control the thermal power.

Hereinafter, the operation of the gas turbine double swirl flow combustor according to the present invention having the configuration as described above will be described in detail.

First, fuel is supplied through a fuel inlet formed at one side of the first fuel supply unit 10 to move toward the combustion chamber.

Next, air for mixing with the fuel supplied to the first fuel supply unit 10 is supplied through the air inlet unit 30 provided outside the second fuel supply unit 20. The air supplied through the air inlet unit 30 may be mixed with the fuel of the first fuel supply unit 10 by the first air supply unit 40 formed through the second fuel supply unit 20. It is moved to the end of the first fuel supply unit 10 to be.

In addition, at least a portion of the air of the first air supply unit 40 is supplied to the first fuel supply unit 10 by the bypass unit 12 before reaching the first swirler 60. That is, the bypass part 12 supplies a part of the air supplied to the first air supply part 40 into the first fuel supply part 10 to move inside the first fuel supply part 10. Premixed air to the fuel.

In addition, the air moving along the first air supply unit 40 is rotated in one direction by the first swirler formed in a spiral shape on one side of the first air supply unit 40 and discharged in the combustion chamber direction. .

That is, the fuel moved along the first fuel supply unit 10, the fuel ejected through the fuel injection port of the first fuel supply unit 10 meets the air turning by the first swirler 60 is air And mix with each other. In this case, a plurality of fuel injection holes through which fuel may be injected is provided at the end of the first fuel supply unit 10, so that the fuel of the first fuel supply unit 10 is turned into the first air supply unit 40 and the first turning unit. It is pivoted by means 60 and allowed to mix with the air supplied.

Next, fuel is supplied through a fuel inlet formed at one side of the second fuel supply unit 20 to move in the direction of the combustion chamber. In this case, the fuel supplied to the second fuel supply unit 20 and the fuel supplied to the first fuel supply unit 10 are supplied with fuel from a separate fuel supply line outside the combustor.

The fuel supplied to the second fuel supply unit 20 is moved to the chamber 24 so that fuel is accommodated in the chamber 24 by a space formed in the chamber 24. This has the effect of uniformly diffusing the fuel introduced into the chamber 24 and the fuel introduced through the second fuel supply unit 20 to be supplied in the direction of the combustion chamber with a uniform pressure.

Next, the air supplied through the air inlet 30 is moved to the second fuel supply unit 20 through the second air supply unit 50. At this time, the second air supply unit 50 is opposite to the turning direction of the first swirler 60 by the second swirler 70 having a sloping surface in a tangential direction toward the second fuel supply unit 20. Air is supplied to the second fuel supply unit 20 while turning in the direction. That is, the air is supplied into the second fuel supply unit while turning in the other direction as opposed to the direction of turning in one direction by the first turning machine, such that fuel and air are mixed.

The premixed fuel by the first swirler 60 and the premixed fuel by the second swirler 70 are mixed again by the fuel mixing unit 22. That is, the premixed fuels turning in opposite directions meet in the fuel mixing section 22 to form a vortex and mix again uniformly. At this time, the pre-mixed fuel supplied to each separate line, the air and fuel is uniformly mixed in the fuel mixing unit 22 is injected into the combustion chamber.

In addition, when adjusting the thermal power of the gas turbine double swirl flow combustion apparatus of the present invention, the fuel supply of any one of the first fuel supply unit 10 and the second fuel supply unit 20 is cut off the load of the gas turbine engine Depending on the change, it is possible to adjust the firepower based on a predetermined set value. More specifically, in the related art, a plurality of combustion devices are provided in an annular shape on one side of the gas turbine, and the fuel supply of some of the combustion devices is cut off, and the fuel is locally burned locally in the combustor, so that the overall uniformity along the gas turbine circumference is achieved. There was a problem that can not be burned. On the other hand, the present invention, the gas turbine double-swirl flow combustion apparatus, the plurality of combustion apparatus provided on one side of the gas turbine enables the fuel control while uniformly supplying fuel into the combustion chamber. That is, since the fuel supply amount corresponding to the engine operating condition is controlled by blocking the fuel of any one of the first fuel supply unit 10 and the second fuel supply unit 20 according to the engine load, the fuel supply amount is adjusted. It is possible to control fire power according to engine load while burning continuously and uniformly.

For example, the fuel of the first fuel supply unit 10 is continuously supplied according to the gas turbine engine load, and the fuel is continuously controlled in the combustion chamber while controlling the thermal power by blocking the fuel of the second fuel supply unit 20. Combustion can be enabled. In addition, while the fuel supply is blocked or supplied through the second fuel supply unit 20, the fire power may be adjusted by adjusting the fuel supply corresponding to the engine load of the first fuel supply unit 10. Of course, the fuel supply method of the first fuel supply unit 10 and the second fuel supply unit 20 described above may be reversed to adjust the combustor fire power.

This is not a local combustion method inside the combustion chamber during the thermal control, which is the conventional problem described above, but the mixed fuel or the second fuel supply unit supplied by the first fuel supply unit 10 and the first air supply unit 40 ( 20) and the mixed fuel supplied by the second air supply unit 50 by supplying the mixed fuel uniformly and continuously in the combustor, there is an effect capable of controlling the thermal power. In addition, since the gas turbine engine is prevented from being misfired due to other causes, stability is secured.

As such, the technical configuration of the present invention described above can be understood by those skilled in the art that the present invention can be implemented in other specific forms without changing the technical spirit or essential features of the present invention.

Therefore, the above-described embodiments are to be understood as illustrative and not restrictive in all respects, and the scope of the present invention is indicated by the following claims rather than the detailed description, and the meaning and scope of the claims and their All changes or modifications derived from an equivalent concept should be construed as being included in the scope of the present invention.

[Description of the code]

10: first fuel supply unit 12: bypass unit

20: second fuel supply unit 22: fuel mixing unit

30: air inlet 40: first air supply

50: second air supply unit 60: first turning machine

70: second turning machine

Claims

A first fuel supply unit having a fuel inlet port formed at one side thereof and a fuel injection port for injecting fuel toward the combustion chamber at the other side thereof;

A second fuel supply part formed to surround the outside of the first fuel supply part to form a flow path for supplying fuel together with the first fuel supply part;

An air inlet unit provided outside the second fuel supply unit to supply air for mixing with the fuel;

A first air supply unit guiding air introduced through the air inlet unit to be mixed with fuel of the first fuel supply unit;

A second air supply unit guiding the air introduced into the air inlet unit to be mixed with fuel of the second fuel supply unit;

A first swirler provided at one side of the first air supply part to pivot the air of the first air supply part so as to be premixed with the fuel of the first fuel supply part; And

And a second swirler provided at one side of the second air supply unit to pivot the air of the second air supply unit to be premixed with the fuel of the second fuel supply unit.

The premixed fuel by the first swirler and the premixed fuel by the second swirler are mixed and injected into the combustion chamber,

A gas turbine double swirl flow combustion apparatus, characterized in that the turning direction of air by the first swirler and the turning direction of air by the second swirler are opposite.
The method of claim 1,

A fuel inlet of the first fuel supply unit and a fuel inlet of the second fuel supply unit are separately formed, so that the fuel of the first fuel supply unit and the second fuel supply unit are independently supplied. Device.
The method of claim 2,

How to cut off the fuel supply of the fuel supply of any one of the first fuel supply and the second fuel supply according to the engine operating conditions or adjusting the fuel supply of any one of the first fuel supply and the second fuel supply. Gas turbine double swirl flow combustion apparatus, characterized in that the thermal power control is possible by the method.
The method of claim 1,

And a bypass unit for supplying and premixing at least a portion of the air of the first air supply unit to the first fuel supply unit before reaching the first swirler.
The method of claim 1,

Inside the second fuel supply unit,

And a gas turbine is provided with a chamber for uniformly spreading the fuel introduced into the second fuel supply unit.
The method of claim 1,

The second fuel supply unit,

The fuel mixing unit further extends from the fuel injection port of the first fuel supply unit, and has a space for mixing the premixed fuel by the first swirler and the premixed fuel by the second swirler to be injected into the combustion chamber. Including,

The inner diameter of the fuel mixing portion is formed such that the inner diameter decreases and increases toward the end of the fuel mixing portion, and the gas and dual swirl flow combustion apparatus is characterized in that the fuel and air are uniformly mixed and the injection force toward the combustion chamber is increased. .
The method of claim 1,

The first turner,

It is provided in a spiral shape capable of turning the air supplied through the first air supply,

The second turner,

And a gas turbine having a tangential inclined surface toward the second fuel supply part to pivot air supplied through the air inlet part on the second air supply part track.