KR20150085748A - Multiple nozzle gas turbine combustor - Google Patents

Abstract

According to an aspect of the present invention, a multiple nozzle gas turbine combustor comprises: an external casing; an internal casing installed in an inner side of the external casing to form an air path in a space with the external casing; a central nozzle placed in the center of the internal casing and installed in an axial direction of the combustor; and a plurality of main nozzles placed on an inner circumferential surface of the internal casing. Air for combustion flowing through the air path is mixed with fuel to be injected to a combustion chamber through the main nozzles. Provided is a multiple nozzle gas turbine combustor, wherein a position of the main nozzles injecting a mixture to a combustion chamber and a position of a dead end of the central nozzle are mutually different for a state of a flow of a mixture respectively injected through the main nozzles and the central nozzle to be different.

Description

[0001] MULTIPLE NOZZLE GAS TURBINE COMBUSTOR [0002]

The present invention relates to a multi-nozzle gas turbine combustor, and more particularly, to a multi-nozzle gas turbine combustor capable of minimizing combustion vibration.

Turbine is a mechanism that obtains rotational force by impulsive force or reaction force using flow of compressible fluid such as steam or gas. It is called a steam turbine when steam is used and gas turbine when combustion gas is used.

The thermal cycle of a gas turbine is a Brayton cycle consisting of a compressor, a combustor, and a turbine. The operating principle of the gas turbine is to suck air from the atmosphere, compress it with a compressor, send it to a combustor, and make a high-temperature, high-pressure gas to operate the turbine and discharge the exhaust gas to the atmosphere. That is, it consists of four steps of compression, heating, expansion, and heat radiation.

The compressor of the gas turbine sucks air from the atmosphere and supplies the combustion air to the combustor, and the pressure and the air temperature are increased because of the adiabatic compression process.

The combustor mixes and burns the incoming compressed air with the fuel to produce a high-energy combustion gas, which increases the temperature of the combustion gas up to the heat limit to withstand the combustor and turbine components.

In the turbine, the high temperature and high pressure combustion gas from the combustor expands and converts impulse and reaction force to the rotating wing of the turbine into mechanical energy. The mechanical energy obtained from the turbine is supplied to the compressor as the energy required to compress the air and the remainder is used to drive the generator to produce power.

Since gas turbines have no reciprocating motion in major components, there is no mutual friction part such as piston-cylinder, consumption of lubricating oil is extremely small, amplitude characteristic, which is characteristic of reciprocating machine, is drastically reduced, and high speed operation is possible.

The present invention relates to a combustor constituting the gas turbine, and more particularly to a nozzle for injecting a mixed gas of fuel and compressed air into a combustion chamber.

FIG. 1 is a side sectional view of a simplex nozzle, FIG. 2 is a side sectional view of a duplex nozzle, and FIGS. 3 and 4 are a side sectional view and a front sectional view, respectively, of a multiple nozzle.

In the single nozzle, the fuel is injected from the center hole of the nozzle and the atomizing air is supplied through the external passage. Sprayed fuel is injected at wide angle out of the nozzle and is mainly used in small gas turbines.

The double nozzle is a nozzle with a double injection type and two connecting passages. The spring type check valve separates the internal fuel path and the external fuel path. Before the stable flame is established, the fuel is injected in the form of diffusion through the inner passage of the nozzle. Once the fuel is burned and the speed is increased, the fuel oil pressure is increased to push the spring to open the check valve, Lt; / RTI >

A multi-nozzle is a type in which a plurality of nozzles are mounted in one combustion chamber.

Although the single nozzle shown in FIG. 1 has one nozzle, there is no possibility of mutual interference or the like. In the double nozzle shown in FIGS. 2 to 5 and the multiple nozzles, the number of nozzles is large, And the vortex generated at this time will affect each other.

When a mixture of fuel and compressed gas is injected through the nozzle, the area of the flow suddenly increases and vortex is generated. Since the flow accompanied by this vortex is known as a source of combustion vibration, It is necessary to minimize it.

As shown in FIGS. 2 to 5, in a conventional gas turbine combustor having a plurality of nozzles, each nozzle or a burner tube surrounding the nozzle has the same angle, and the positions of the ends are the same. Therefore, the vortices generated in each nozzle also have the same phase, and the same phases are merged with each other, so that the amplitude of the vibration is further increased.

FIG. 5 shows a state in which the end positions of the plurality of nozzles and the spraying direction are the same. As a flow of the same phase is injected, a larger vibration can be generated in a portion where the flow overlaps.

In order to reduce such combustion vibration, conventionally, a separate structure such as a resonator or a damping system has been added to reduce the vibration. However, as a separate structure is added, the overall structure is complicated and installation costs are increased.

US Open Patent 2011-0048021

Embodiments of the present invention can reduce the occurrence of vibration by making the phase of the mixer flow different without any additional configuration so that the magnitude of the vortex amplitude is canceled out by the phase difference.

To this end, in the embodiment of the present invention, the length of the nozzles is adjusted so that the end positions of the nozzles are different from each other, and the occurrence of vibration is reduced by using the phase difference generated through the nozzles.

In addition, the nozzle is tilted to adjust the injection direction, and as a result, the generation of the vibration is reduced by using the phase difference generated due to the different end positions of the nozzles.

According to an aspect of the present invention, there is provided an internal casing (32) having an outer casing (31) and an air passage (30) provided inside the outer casing (31) A central nozzle 35 located in the center of the casing 32 in the axial direction of the combustor and a plurality of main nozzles 36 located on the inner peripheral surface of the inner casing 32 and arranged to surround the central nozzle 35 A multi-nozzle gas turbine combustor for mixing combustion air introduced through the air passage (30) with fuel and injecting the mixed air through the main nozzle (36) into a combustion chamber (33)

A plurality of main nozzles 36 and a central nozzle 36 for injecting a mixture into the combustion chamber 33 are provided in order to change the phases of the mixture flows injected through the plurality of main nozzles 36 and the central nozzles 35, 35 are different from each other in the position of the end of the gas turbine combustor.

The positions of the ends of the plurality of main nozzles 36 and the center nozzles 35 may be controlled by the amount and speed of the fuel to be supplied, the amount and speed of the air, and the like.

The apparatus may further include a nozzle position controller for adjusting positions of the plurality of main nozzles 36 and the center nozzle 35.

In addition, the nozzle position control unit adjusts the length of the nozzle so that the positions of the ends of the plurality of main nozzles 36 and the center nozzle 35 are changed.

The nozzle position control unit adjusts the position of the nozzle tip by pulling the nozzle forward or pushing back the nozzle when the length of the nozzle is fixed.

The nozzle position control unit adjusts the position of the nozzle tip by adjusting the length of the nozzle hole that is adjustable in length, which is coupled to the nozzle tip.

According to another aspect of the present invention, there is provided an internal casing (32) having an outer casing (31) and an air passage (30) provided inside the outer casing (31) And a plurality of main nozzles (36) located at the center of the casing (32) and disposed in the axial direction of the combustor, and a plurality of main nozzles (36) positioned at the inner peripheral surface of the inner casing (32) , A plurality of main nozzles (36), and a plurality of main nozzles (36), wherein the main nozzles (36) and the plurality of main nozzles (36) are formed by mixing combustion air introduced through the air passage A plurality of main nozzles 36 and a central nozzle 35 for injecting a mixture into the combustion chamber 33 are different from each other in injection direction so as to change the phase of the mixture flow injected through the central nozzle 35 A multi-nozzle There's a turbine combustor can be provided.

The direction of injection of the plurality of main nozzles 36 and the central nozzles 35 may be controlled by the amount and speed of the fuel to be supplied and the amount and speed of the air.

The apparatus may further include a nozzle injection direction controller for adjusting the injection directions of the plurality of main nozzles 36 and the central nozzles 35.

In addition, the nozzle ejection direction control unit controls the ejection directions of the plurality of main nozzles 36 and the central nozzles 35 by tilting the nozzles.

In addition, the nozzle ejection direction control unit controls the ejection direction of the plurality of main nozzles 36 and the central nozzles 35 by tilting the entire nozzle about the opposite end.

When the nozzle includes a tilting portion in a part of the nozzle, the tilting portion of the nozzle is tilted to adjust the direction of spraying the plurality of main nozzles 36 and the central nozzle 35 .

When the nozzle includes a spray direction switching unit for switching the spray direction of the nozzles, the nozzle spray direction control unit controls the spray directions of the plurality of main nozzles 36 and the central nozzles 35 by controlling the spray direction switching unit . ≪ / RTI >

According to another aspect of the present invention, there is provided an air conditioner comprising an outer casing (31), an inner casing (32) provided inside the outer casing (31) and defining an air passage (30) And a plurality of main nozzles 36 located at the center of the inner casing 32 and disposed in the axial direction of the combustor and disposed at the inner circumferential surface of the inner casing 32 and surrounding the central nozzle 35 A multi-nozzle gas turbine combustor for mixing combustion air introduced through the air passage (30) with fuel and injecting the fuel into the combustion chamber (33) through the main nozzle (36), wherein the plurality of main nozzles (36) A plurality of main nozzles 36 for spraying a mixer into the combustion chamber 33 and a plurality of main nozzles 36 for spraying a mixture of the main nozzles 36 and the central nozzles 35, Are different from each other A multi-nozzle gas turbine combustor may be provided.

The position and the direction of the ends of the plurality of main nozzles 36 and the central nozzles 35 may be controlled by the amount and speed of the fuel to be supplied and the amount and speed of the air.

The apparatus may further include a nozzle controller for adjusting the positions of the ends of the plurality of main nozzles 36 and the center nozzle 35 and the spray direction.

When the length of the nozzle is fixed, the nozzle control unit adjusts the length of the nozzle so that the length of the nozzle can be adjusted by adjusting the length of the nozzle, And when the nozzle includes a tilting portion, the tilting portion of the nozzle is tilted, or when the nozzle includes a tilting portion, or when the nozzle includes a tilting portion, And controls the ejection direction switching unit to control the ejection directions of the plurality of main nozzles 36 and the central nozzles 35.

Embodiments of the present invention can reduce the occurrence of vibration by making the phase of the mixer flow different without any additional configuration so that the magnitude of the vortex amplitude is canceled out by the phase difference.

For this, in the embodiment of the present invention, the lengths of the nozzles are adjusted so that the end positions of the nozzles are different from each other, and the phase difference is generated thereby reducing the vibration.

In addition, the nozzles are tilted to adjust the spraying direction, and the end positions of the nozzles are different from each other, so that a phase difference is generated and the vibration can be reduced.

1 is a side cross-sectional view of a simplex nozzle.
2 is a side cross-sectional view of a duplex nozzle.
3 is a side cross-sectional view of a multiple nozzle.
4 is a front cross-sectional view of a multiple nozzle.
FIG. 5 shows a vortex generated when the end position of the nozzle and the injection direction are both the same.
FIG. 6 is a side cross-sectional view of a multi-nozzle in which an end position of a nozzle is adjusted according to an embodiment of the present invention.
FIG. 7 illustrates vortex generated in a multi-nozzle in which a nozzle end position is adjusted according to an embodiment of the present invention.
8 is a side cross-sectional view of a multi-nozzle in which the direction of injection of the nozzles is adjusted according to another embodiment of the present invention.
FIG. 9 shows vortices generated in a multi-nozzle in which the direction of injection of the nozzles is adjusted according to another embodiment of the present invention.
10 is a side cross-sectional view of a multi-nozzle in which a nozzle end position and a spray direction are adjusted according to another embodiment of the present invention.
11 illustrates a vortex generated in a multi-nozzle in which a nozzle end position and an injection direction are adjusted according to another embodiment of the present invention.

Various embodiments of the present invention will now be described by way of specific embodiments shown in the accompanying drawings. The differences between the embodiments of the present invention described below are to be understood as mutually exclusive. That is, the specific shapes, structures, and characteristics described may be embodied in other embodiments in accordance with one embodiment without departing from the spirit and scope of the present invention, It is to be understood that the arrangements may be altered, where like reference numerals refer to like or similar features throughout the several views, and length and area, thickness, and the like may be exaggerated for convenience.

First, the process of supplying the mixer to the combustion chamber through the nozzle will be described.

FIG. 3 is a side sectional view of a multiple nozzle, and FIG. 4 is a front sectional view of a multiple nozzle, and is a view showing the arrows A-A in FIG. 3 and 4, in the multi-nozzle gas turbine combustor, the inner casing 32, which forms the air passage 30 at a predetermined interval, is located inside the outer casing 31, and the inner casing 32, Is connected to the combustion chamber (33).

The inner casing 32 is a central portion of the inner casing 32 and a central nozzle 35 is disposed along the direction of the combustion chamber axis S which is the extending direction of the combustion chamber axis S. The central nozzle 35 can be fitted with a communication pipe 35a in the shape of a cylinder around the distal end thereof. Further, the central nozzle 35 may be provided with a central swirler 35b between the outer peripheral surface thereof and the inner peripheral surface of the combustion chamber 35a.

A plurality of main nozzles 36 are arranged in parallel with the combustion axis S so as to surround the central nozzle 35 along the circumferential direction on the inner circumferential surface of the inner casing 32. The main nozzle 36 may be fitted with an extension 36a formed in a tubular shape around the distal end thereof. The main nozzle 36 may be provided with a main swirler 36b between the outer circumferential surface of the main nozzle 36 and the inner circumferential surface of the extension 36a.

The central nozzles 35 and the main nozzles 36 are provided with fuel ports 35c and 36c on the outer side where fuel is advanced, and fuel is supplied through the fuel ports 35c and 36c. A rectifying plate 38 may be provided between the outer casing 31 and the inner casing 32 at an inlet of the air passage 30 so that the rectifying plate 38 is installed to cover the air passage 30 And a plurality of holes communicating the upstream side and the downstream side of the air passage (30).

In the inner casing 32, a turning portion 39 may be provided at a base end portion of the air passage 30. The turning part 39 cooperates with the partition wall to substantially invert the flow direction of the air passage 30. The turning portion 39 may be formed to have an increased thickness so that the inner surface facing the outer casing 31 side is closer to the outer casing 31 side so as to form a part of the air passage 30. [

In addition, a turning vane 39a may be installed inside the turning part 39 inside the inner casing 32. The turning vane 39a extends from the outer side of the main nozzle 36 in the radial direction toward the combustion axis S and is curved in an arc shape toward the tip end side of the main nozzle 36 in the vicinity of the position of the main nozzle 36, Respectively.

When compressed air of high temperature and high pressure flows into the air passage 30 in the multi-nozzle gas turbine combustor, the compressed air passes through the rectifying plate 38 and is rectified. Further, the flow is narrowed by the turning unit 39, And is further rectified by the turning vane 39a and is guided to the combustion chamber 35a of the central nozzle 35 and the extension chamber 36a of the main nozzle 36. The center swirl chamber 35b and the main swirl chamber 35b, The airflow is turned by the waller 36b. And is mixed with the fuel supplied through the fuel ports 35c and 36c to be injected into the combustion chamber 33. [

However, as shown in FIGS. 3 to 5, the vortexes generated by the flow of the injected gas have the same phase since the ends of the nozzles are located at the same positions and the injection directions are the same. There is a problem that vibration is further increased.

In order to solve the above-described problems, the embodiments of the present invention attempt to reduce the combustion vibration by making the positions of the ends of the nozzles different from each other, .

Accordingly, embodiments of the present invention provide a method of adjusting the position of the end of a nozzle, a method of adjusting the direction of injection of the nozzle, and a method of adjusting the position of the end of the nozzle and the direction of injection, .

FIG. 6 is a side cross-sectional view of a multi-nozzle in which an end position of a nozzle is adjusted according to an embodiment of the present invention. FIG. 7 is a cross-sectional view illustrating a vortex generated in a multi- Respectively.

6 and 7, a multi-nozzle gas turbine combustor according to an exemplary embodiment of the present invention includes an outer casing 31 and an outer casing 31 disposed inside the outer casing 31, A central nozzle 35 disposed in the center of the inner casing 32 and disposed in the axial direction of the combustor and a central nozzle 35 located in the inner peripheral surface of the inner casing 32 and defining the central nozzle 35 The combustion air introduced through the air passage 30 is mixed with the fuel and is injected into the combustion chamber 33 through the main nozzle 36. [ A multi-nozzle gas turbine combustor comprising a plurality of main nozzles (36) and a plurality of main nozzles (35) for injecting a mixer into the combustion chamber (33) so as to vary the phase of a mixer flow injected through the plurality of main nozzles (36) and the central nozzle (35) It characterized in that the end positions are different from each other.

That is, unlike the prior art, the positions of the ends of the plurality of nozzles are different from each other, so that the phase of the vortex generated is different, and accordingly, the amplitudes cancel each other to reduce vibration.

Since the flow is injected from the end of the nozzle and vortices are generated accordingly, if the positions of the ends are different, a phase difference is generated in proportion to the difference in length of the end of the nozzle, thereby reducing vibration.

At this time, the difference in position in the longitudinal direction between the nozzle ends can be controlled by the amount and speed of the supplied fuel and the amount and speed of the air. It may also be controlled by the number of nozzles.

If a certain amount of fuel is injected at a constant speed by mixing a specific amount of air, the positional difference between the nozzle tips optimized in that case can be fixed and fixed, but the amount of fuel, the amount of air, If so, it is necessary to adjust the positional difference between the nozzle tips optimized in that case.

For this, a plurality of main nozzles 36 and a nozzle position controller for adjusting the positions of the ends of the central nozzles 35 may be further included.

In order to adjust the position of the nozzle end, a method of adjusting the length of the nozzle may be used. That is, in order to make a certain length difference, the position of the end is adjusted by using a method of extending or reducing the length of a specific nozzle.

Also, if the length of the nozzle is fixed, it is also possible to adjust the position of the nozzle tip by pushing the entire nozzle forward or pushing it backward.

In addition, since only the position of the ejected tip can be adjusted, it is possible to adjust the position of the nozzle tip by adding a separate nozzle for controlling the length.

FIG. 8 is a side cross-sectional view of a multi-nozzle in which the direction of injection of the nozzles is adjusted according to another embodiment of the present invention, and FIG. 9 is a cross- It shows the vortex.

8 and 9, a multi-nozzle gas turbine combustor according to another aspect of the present invention includes an outer casing 31 and an air passage (not shown) provided between the outer casing 31 and the outer casing 31, A central nozzle 35 disposed in the center of the inner casing 32 and disposed in the axial direction of the combustor and a central nozzle 35 located on the inner peripheral surface of the inner casing 32 and defining the central nozzle 35, A plurality of main nozzles 36 arranged to surround the combustion chamber 33 and injecting the combustion air introduced through the air passage 30 into the combustion chamber 33 through the main nozzle 36, A gas turbine combustor comprising a plurality of main nozzles (36) for injecting a mixer into the combustion chamber (33) to vary the phase of the mixer flow injected through the plurality of main nozzles (36) and the central nozzle (35) And the central nozzle 35 Direction are different from each other.

As described above, since the flow is injected from the end of the nozzle and vortex is generated accordingly, a phase difference occurs when the position of the end is different. Accordingly, if the position of the end in the forward and backward direction is adjusted in the above-described embodiment, the position of the end in the lateral direction may be adjusted to generate a phase difference in another embodiment of the present invention.

At this time, how much to tilt the injection direction of the nozzles can be controlled by the amount and speed of the supplied fuel and the amount and speed of the air. It may also be controlled by the number of nozzles.

In addition, the nozzle injection direction control unit may further include a nozzle injection direction control unit for adjusting the amount of fuel, the amount of air, and the like so as to adjust the injection direction of the nozzle optimized in that case.

And the nozzle ejection direction control unit controls the ejection directions of the plurality of main nozzles 36 and the central nozzles 35 by tilting the nozzles. At this time, the entire nozzle may be tilted as shown in FIG. 8, but it is also possible to adjust the injection direction by tilting only the tip of the nozzle by designing the nozzle so that only a part of the nozzle can be tilted.

In addition, a separate direction changing unit may be added to the nozzle end to adjust the spraying direction.

FIG. 10 is a side cross-sectional view of a multi-nozzle in which an end position and a spray direction of the nozzle are adjusted according to another embodiment of the present invention. FIG. 11 is a cross- And the vortex generated in this controlled multi-nozzle.

10 and 11, a multi-nozzle gas turbine combustor according to another aspect of the present invention includes an outer casing 31 and an air passage (not shown) provided between the outer casing 31 and the outer casing 31, A central nozzle 35 disposed in the center of the inner casing 32 and disposed in the axial direction of the combustor and a central nozzle 35 located on the inner peripheral surface of the inner casing 32 and defining the central nozzle 35, A plurality of main nozzles 36 arranged to surround the combustion chamber 33 and injecting the combustion air introduced through the air passage 30 into the combustion chamber 33 through the main nozzle 36, A gas turbine combustor comprising a plurality of main nozzles (36) for injecting a mixer into the combustion chamber (33) to vary the phase of the mixer flow injected through the plurality of main nozzles (36) and the central nozzle (35) And the central nozzle 35 The position or orientation of the injection stage is characterized in that different from each other.

Another embodiment of the present invention is a combination of the features of the above-described two embodiments. To completely counteract the vibration, the two phases must be opposite to each other if there are two nozzles. For this purpose, it is difficult to control only the position of the tip of the nozzle or the direction of injection so that the phases are reversed. Furthermore, when the number of nozzles is three or more, more precise control is required to completely cancel the vibration. To this end, in another embodiment of the present invention, both the position of the end of the nozzle and the direction of injection can be simultaneously adjusted to reduce the vibration.

In addition, when the amount of fuel, the amount of air, and the like are continuously varied, a nozzle control unit may be further included to maintain the phase difference.

The nozzle control unit is a combination of the nozzle position control unit and the nozzle injection direction control unit. The nozzle control unit adjusts the length of the nozzle, or when the length of the nozzle is fixed, the entire nozzle is pulled forward or backward, It is possible to control the position of the nozzle end by adjusting the length of the combined injection port and to tilt the entire nozzle around the opposite end or to tilt the tilting part of the nozzle when the nozzle includes a tilting part, When the nozzles include a spray direction switching unit for switching the spray direction of the nozzles, the spray directions of the plurality of main nozzles 36 and the central nozzles 35 are controlled by controlling the spray direction switching unit.

While the present invention has been particularly shown and described with reference to exemplary embodiments thereof, it will be understood by those skilled in the art that various changes and modifications may be made therein without departing from the spirit and scope of the invention as defined by the appended claims. Deletion, addition or the like of the present invention may be variously modified and changed within the scope of the present invention.

30: air passage
31: outer casing
32: Internal casing
33: Combustion chamber
35: central nozzle
35a: communication
35b: Central Swallar
35c: fuel port
36: Main nozzle
36a: Toolbox
36b: Main swallower
36c: fuel port
38: rectification plate
39: turning part
39a: turning vane
S: Combustion axis

Claims (17)

An inner casing 32 which is provided inside the outer casing 31 and forms an air passage 30 between the outer casing 31 and the inner casing 32, And a plurality of main nozzles (36) disposed on an inner circumferential surface of the inner casing (32) and arranged to surround the central nozzle (35), wherein the air passage (30) (33) through the main nozzle (36), wherein the combustion gas is introduced into the combustion chamber (33)
A plurality of main nozzles 36 and a central nozzle 36 for injecting a mixture into the combustion chamber 33 are provided in order to change the phases of the mixture flows injected through the plurality of main nozzles 36 and the central nozzles 35, 35) are different from each other in the position of the end of the gas turbine combustor.
The method according to claim 1,
The positions of the ends of the plurality of main nozzles (36) and the center nozzle (35) are controlled by the amount and speed of the fuel to be supplied, the amount and speed of the air,
3. The method of claim 2,
Further comprising a nozzle position control unit for adjusting positions of the ends of the plurality of main nozzles (36) and the center nozzle (35).
The method of claim 3,
Wherein the nozzle position control unit adjusts the length of the nozzle so that the positions of the ends of the plurality of main nozzles and the center nozzle are changed.
The method of claim 3,
Wherein the nozzle position control unit adjusts the position of the nozzle tip by pulling the nozzle forward or pushing back the nozzle when the length of the nozzle is fixed.
The method of claim 3,
Wherein the nozzle position control unit adjusts a position of a nozzle end by adjusting a length of an injection hole that is adjustable in length, which is coupled to a nozzle end.
An inner casing 32 which is provided inside the outer casing 31 and forms an air passage 30 between the outer casing 31 and the inner casing 32, And a plurality of main nozzles (36) disposed on an inner circumferential surface of the inner casing (32) and arranged to surround the central nozzle (35), and the air passage (30) Nozzle gas turbine combustor which mixes the combustion air introduced through the main nozzle with the fuel and injects it into the combustion chamber (33) through the main nozzle (36)
A plurality of main nozzles 36 and a central nozzle 35 for spraying a mixer into the combustion chamber 33 are provided in order to change the phase of the mixer flow injected through the plurality of main nozzles 36 and the central nozzles 35. [ ) Are different from each other in the direction of injection of the gas.
8. The method of claim 7,
The direction of injection of the plurality of main nozzles (36) and the central nozzle (35) is controlled by the amount and speed of the fuel to be supplied and the amount and speed of the air.
8. The method of claim 7,
Further comprising a nozzle ejection direction control unit for controlling the ejection direction of the plurality of main nozzles (36) and the central nozzle (35).
10. The method of claim 9,
Wherein the nozzle ejection direction control unit controls the ejection direction of the plurality of main nozzles (36) and the central nozzle (35) by tilting the nozzles.
11. The method of claim 10,
Wherein the nozzle ejection direction control unit controls the ejection direction of the plurality of main nozzles (36) and the central nozzle (35) by tilting the entire nozzle around the opposite end.
11. The method of claim 10,
Wherein the nozzle ejection direction control unit adjusts the ejection direction of the plurality of main nozzles (36) and the central nozzle (35) by tilting the tilting unit of the nozzle when the nozzle includes a tilting unit in a part thereof burner.
11. The method of claim 10,
The nozzle ejection direction control unit controls the ejection direction switching unit to control the ejection directions of the plurality of main nozzles 36 and the central nozzles 35 when the nozzles include the ejection direction switching unit for switching the ejection direction of the nozzles Gas turbine combustor.
An inner casing 32 which is provided inside the outer casing 31 and forms an air passage 30 between the outer casing 31 and the inner casing 32, And a plurality of main nozzles (36) disposed on an inner circumferential surface of the inner casing (32) and arranged to surround the central nozzle (35), and the air passage (30) Nozzle gas turbine combustor which mixes the combustion air introduced through the main nozzle with the fuel and injects it into the combustion chamber (33) through the main nozzle (36)
A plurality of main nozzles 36 and a central nozzle 35 for spraying a mixer into the combustion chamber 33 are provided in order to change the phase of the mixer flow injected through the plurality of main nozzles 36 and the central nozzles 35. [ ) And the jetting direction are different from each other.
15. The method of claim 14,
The position and the direction of the end of the plurality of main nozzles 36 and the central nozzle 35 are controlled by the amount and speed of the fuel to be supplied and the amount and speed of the air.
15. The method of claim 14,
Further comprising a nozzle control unit for controlling a position and an injection direction of the ends of the plurality of main nozzles (36) and the central nozzle (35)
16. The method of claim 15,
The nozzle control unit adjusts the length of the nozzle by adjusting the length of the nozzle, pushing the entire nozzle forward or backward when the length of the nozzle is fixed, or adjusting the length of the nozzle, And a tilting portion of the nozzle is tilted when the nozzle includes a tilting portion in a part thereof or a jet direction switching portion in which the nozzle changes the jetting direction of the nozzle, (36) and the central nozzle (35) by controlling the direction switching unit (40).

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