KR20190059539A - Burner Having Main Nozzle With Sliding Connecting Structure, And Gas Turbine Having The Same - Google Patents

Abstract

Disclosed are a combustor of a gas turbine engine including a main nozzle having a sliding binding structure, and a gas turbine including the same. According to an embodiment of the present invention, the combustor comprises an inner casing and an outer casing, spaced apart by a predetermined distance in an inner diameter direction therein to form an air passage, and mixing air for combustion, flowing through the air passage, with fuel to inject the air mixed with the fuel to a combustion chamber through a central nozzle and a main nozzle. The central nozzle is installed in a shaft direction of a combustor in the center of the inner casing, and the main nozzle is provided as a plurality of main nozzles disposed inside the inner casing to surround the central nozzle. The main nozzle is composed of an inner nozzle (an inner tubular component) and an outer nozzle (an outer tubular component), overlapped by a predetermined width to be bound in a slidable structure, and the inner nozzle and the outer nozzle are slid together by thermal expansion, so a total length of the main nozzle is variable. According to the present invention, bellows installed in the inner nozzle can be removed, and an amount of thermal deformation can be effectively absorbed, so structural stability of the inner and outer nozzles can be stably secured, and a combustor including a structure capable of stably securing the mixer injection efficiency of a combustor and a gas turbine including the same are provided.

Description

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a combustor of a gas turbine engine including a main nozzle of a sliding binding structure, and a gas turbine including the main nozzle,

The present invention relates to a combustor and a gas turbine including the same.

The thermodynamic cycle of a gas turbine engine ideally follows the Brayton cycle. The Breton cycle consists of four processes leading to isentropic compression (adiabatic compression), constant pressure heat radiation, isentropic expansion (adiabatic expansion), and static pressure heat radiation. In other words, after sucking the air in the air and compressing it to a high pressure, the fuel is burned in a constant pressure environment to release heat energy, and the high temperature combustion gas is expanded to kinetic energy, and then the exhaust gas containing residual energy is discharged to the atmosphere . That is, the cycle is performed in four steps of compression, heating, expansion, and heat radiation.

A gas turbine engine that realizes the above-mentioned Brayton cycle includes a compressor, a combustor, and a turbine. 1 is a view schematically showing the overall configuration of a gas turbine engine 1000. As shown in FIG. Although the following description refers to Fig. 1, the description of the present invention can be widely applied to a turbine engine having a configuration equivalent to that of the gas turbine engine 1000 exemplarily shown in Fig.

The compressor 1100 of the gas turbine engine 1000 functions to suck and compress air and supplies combustion air to the combustor 1200 while cooling the gas turbine engine 1000 in a high- The main role is to supply air. The sucked air is adiabatically compressed in the compressor 1100, so that the pressure and the temperature of air passing through the compressor 1100 are increased.

The compressor 1100 included in the gas turbine engine 1000 is usually designed as a centrifugal compressor or an axial compressor while a centrifugal compressor is applied in a small gas turbine engine, Since the gas turbine engine 1000 has to compress a large amount of air, it is common that a multi-stage axial compressor 1100 is applied. The rotary shaft of the compressor 1100 and the rotary shaft of the turbine 1300 are directly connected to each other so that the compressor 1100 is driven using a part of the power output from the turbine 1300.

The combustor 1200 mixes the compressed air supplied from the outlet of the compressor 1100 with the fuel and burns the compressed air at a constant pressure to produce a combustion gas of high energy. 2 shows an example of a combustor 1200 provided in the gas turbine engine 1000. As shown in FIG. The combustor 1200 is disposed downstream of the compressor 1100 and a plurality of burners 1220 are disposed along the annular combustor casing 1210. Each of the burners 1220 is provided with several combustion nozzles 1230. The fuel injected from the combustion nozzles 1230 is mixed with air in an appropriate ratio to be in a state suitable for combustion.

The combustor 1200 requires the proper cooling because it is the hottest environment in the gas turbine engine 1000. Referring to FIG. 2, a duct assembly 1250 connecting the burner 1220 and the turbine 1300 with a high-temperature combustion gas flow, that is, a tube assembly 1250 comprising a transition piece 1260 and a flow sleeve 1270, The compressed air flows along the outer surface of the combustion nozzle 1230 and is supplied to the combustion nozzle 1230. During the course of the compressed air moving along the outer surface of the tube assembly, the heated duct assembly is suitably cooled by the hot combustion gases.

2, the conventional combustor 1200 includes an inner casing 1250 and an outer casing 1250 which are spaced apart from each other by a predetermined distance in the inner diameter direction to form an air passage 1211, The combustion air introduced through the air passage 1211 is mixed with the fuel and injected into the combustion chamber through the central nozzle 1230 and the main nozzle 1231.

The central nozzle 1230 is installed in the center of the inner casing 1250 in the axial direction of the combustor and a plurality of the main nozzles 1231 are disposed inside the inner casing 1250 so as to surround the central nozzle 1230.

3 is a cross-sectional view showing a more specific structure of the main nozzle 1231. As shown in Fig. Referring to FIG. 3, the main nozzle 1231 according to the related art has an inner tubular component 1231-1 and an outer tubular component 1231-2, which have the same central axis and form an air passage therebetween, ). ≪ / RTI >

At this time, the amounts of thermal energy applied to the inner nozzle 1231-1 and the outer nozzle 1231-2 are different from each other, and different thermal deformation behaviors are exhibited. In order to absorb the thermal deformation, bellows 1231-3, To ensure structural stability.

However, in the case of the main nozzle 1231 according to the related art, the bellows 1231-3 having a relatively large volume has a disadvantage in assembly, installation and operation, and the bellows 1231-1 is separately manufactured and assembled It is also disadvantageous in terms of cost for production.

Accordingly, there is a need for a technique for a combustor including a structure capable of solving the problems according to the prior art.

Korean Patent Laid-Open Publication No. 10-2017-0008394 (published Jan. 24, 2017)

The present invention can eliminate the bellows provided in the inner nozzle and secure the structural stability of the inner nozzle and the outer nozzle by an external force due to thermal deformation and can stably ensure the injector efficiency of the combustor And a gas turbine including the combustor.

The combustor according to an embodiment of the present invention includes an inner casing and an outer casing which are spaced apart from each other by a predetermined distance in the inner radius direction and form an air passage, and the combustion air introduced through the air passage is mixed with fuel Wherein the main nozzle is disposed in the axial direction of the combustor at a central portion of the inner casing and a plurality of the main nozzles are disposed in the inner casing so as to surround the central nozzle, The nozzle is composed of an inner tubular component and an outer tubular component which are coupled to each other by a predetermined width so as to be slidable, and the inner nozzle and the outer nozzle are slid together by thermal expansion, May be variable.

In an embodiment of the present invention, a sliding structure may be formed at a portion where the inner nozzle and the outer nozzle overlap each other.

In one embodiment of the present invention, one or more sliding rings may be mounted on the outer circumferential surface of the inner nozzle overlapping the outer nozzle.

In an embodiment of the present invention, one or more piston rings may be mounted on the outer circumferential surface of the inner nozzle overlapping the outer nozzle.

In one embodiment of the present invention, at least one sliding ring and a piston ring may be mounted on an outer circumferential surface of the inner nozzle overlapping the outer nozzle.

In this case, the sliding ring and the piston ring can be alternately arranged alternately.

In addition, the sliding ring and the piston ring may be inserted into the outer peripheral surface of the inner nozzle by a predetermined depth.

In one embodiment of the present invention, the one end of the outer nozzle may be provided with a detent protrusion extending by a predetermined length in the direction of the outer circumference of the inner nozzle to limit the length of the inner changeable sliding of the inner nozzle.

In this case, the detent projection may have a structure in which it is brought into close contact with the outer peripheral surface of the inner nozzle so as to seal the binding portion between the inner nozzle and the outer nozzle.

In addition, a piston ring that slides on the outer peripheral surface of the inner nozzle and seals the inner nozzle and the outer nozzle may be mounted on the inner side of the detent projection.

In addition, a sliding ring and a piston ring, which slide with the outer circumferential surface of the inner nozzle and seal the inner nozzle and the outer nozzle, can be alternately disposed alternately on the inside of the detent projection.

According to an embodiment of the present invention, at least one sliding rail is formed on the outer circumferential surface of the inner nozzle overlapping with the outer nozzle, and a sliding protrusion having a structure corresponding to the sliding rail is formed on an inner circumferential surface of the outer nozzle overlapping with the inner nozzle .

The one end of the outer nozzle may be provided with a stop protrusion extending by a predetermined length in the direction of the outer circumference of the inner nozzle to limit the length of the inner nozzle slidable.

In this case, the detent projection may have a structure in which it is brought into close contact with the outer peripheral surface of the inner nozzle so as to seal the binding portion of the inner nozzle and the outer nozzle.

According to an embodiment of the present invention, a sealing member of a spring structure composed of a material having an elastic restoring force of a predetermined size may be mounted on a portion where the inner nozzle and the outer nozzle overlap.

In this case, the sealing member may be mounted such that the inner nozzle and the outer nozzle are mutually displaceable relative to each other in the axial direction.

In an embodiment of the present invention, the lower end of the sealing member is inserted and attached to the outer circumferential surface of the inner nozzle by a predetermined depth, and the upper end of the sealing member is inserted into the inner circumferential surface of the outer nozzle by a predetermined depth .

In one embodiment of the present invention, the sealing member absorbs a relative amount of deformation of the inner nozzle and the outer nozzle by heat energy provided from the outside, and when the supply of heat energy from the outside is cut off, The relative position can be restored.

The present invention can also provide a gas turbine including the combustor.

According to the embodiment of the present invention, by providing the main nozzle composed of the inner nozzle and the outer nozzle which are bound to the slidable structure having the specific structure, the bellows installed in the inner nozzle can be removed, The present invention can provide a combustor including a structure capable of ensuring structural stability of an inner nozzle and an outer nozzle, and stably ensuring a mixture injection efficiency of the combustor, and a gas turbine including the same.

According to still another embodiment of the present invention, by inserting the inner nozzle and the outer nozzle overlapping each other by a predetermined width, and attaching the sliding ring and the piston ring to the engaging portion, the inner nozzle and the outer nozzle And a structure capable of effectively achieving a sealing structure between the inner nozzle and the outer nozzle and consequently stably ensuring the mixture injection efficiency of the combustor, and a gas turbine including the same Can be provided.

According to still another embodiment of the present invention, by forming detent protrusions having a specific structure at one end portion of the outer nozzle, thermal deformation of the inner nozzle and the outer nozzle due to thermal deformation changes the relative positions of the inner nozzle and the outer nozzle It is possible to provide a combustor and a gas turbine including the same that can easily limit the range of change and ensure the structural stability of the inner nozzle and the outer nozzle.

According to still another embodiment of the present invention, by forming the sliding rails and the sliding projections of a specific structure on specific portions of the inner nozzle and the outer nozzle, the bellows provided on the inner nozzle can be removed and the amount of thermal deformation can be effectively absorbed The present invention can provide a combustor including a structure capable of ensuring structural stability of an inner nozzle and an outer nozzle, and stably ensuring a mixture injection efficiency of the combustor, and a gas turbine including the same.

According to still another aspect of the present invention, a sealing structure of a spring structure composed of a material having elastic restoring force of a specific size is disposed between an inner nozzle and an outer nozzle which are coupled by a slidable structure, A combustor including a structure capable of effectively absorbing thermal deformation, securing structural stability of an inner nozzle and an outer nozzle, and stably ensuring a mixture injecting efficiency of the combustor, and a combustor including the same A gas turbine can be provided.

1 is a perspective view showing the overall structure of a gas turbine engine according to the prior art.
FIG. 2 is a cross-sectional view showing only a combustor portion in the gas turbine engine shown in FIG. 1; FIG.
3 is a cross-sectional view showing a main nozzle of a conventional combustor.
FIG. 4 is an enlarged partial enlarged view showing only a binding portion of an inner nozzle and an outer nozzle of a main nozzle according to an embodiment of the present invention.
FIG. 5 is an enlarged partial enlarged view showing only a binding portion of an inner nozzle and an outer nozzle of a main nozzle according to another embodiment of the present invention.
6 is an enlarged partial enlarged view showing only the binding portion of the inner nozzle and the outer nozzle of the main nozzle according to another embodiment of the present invention.
FIG. 7 is an enlarged partial enlarged view showing only a binding portion of an inner nozzle and an outer nozzle of a main nozzle according to another embodiment of the present invention.
FIG. 8 is an enlarged partial enlarged view showing only a binding portion of an inner nozzle and an outer nozzle of a main nozzle according to another embodiment of the present invention.
FIG. 9 is an enlarged partial enlarged view showing only a binding portion of an inner nozzle and an outer nozzle of a main nozzle according to another embodiment of the present invention.
FIG. 10 is an enlarged partial enlarged view showing only a binding portion of an inner nozzle and an outer nozzle of a main nozzle according to another embodiment of the present invention. FIG.

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

In describing the embodiments of the present invention, a description of well-known structures that can be easily understood by those skilled in the art will be omitted so as not to obscure the gist of the present invention. In the drawings, like reference numerals refer to like elements throughout. The same elements will be denoted by the same reference numerals even though they are shown in different drawings. Referring to the drawings, The size of the elements, etc., may be exaggerated for clarity and convenience of explanation.

In describing the components of the embodiment of the present invention, terms such as first, second, A, B, (a), and (b) may be used. These terms are intended to distinguish the constituent elements from other constituent elements, and the terms do not limit the nature, order or order of the constituent elements. When a component is described as being "connected", "coupled", or "connected" to another component, the component may be directly connected or connected to the other component, Quot; coupled " or " connected " indirectly while intervening in the context of the present invention.

FIG. 4 is an enlarged partial enlarged view showing only the binding portion of the inner nozzle and the outer nozzle of the main nozzle according to the embodiment of the present invention.

Referring to FIG. 4, the combustor according to the present embodiment includes an inner casing and an outer casing which are spaced apart from each other by a predetermined distance in the inner diameter direction inside the outer casing as described above, The main nozzle is composed of an inner tubular component (110) and an outer tubular component (120) having a specific structure. The combustion nozzle (100). ≪ / RTI >

The inner nozzle 110 and the outer nozzle 120 constituting the main nozzle 100 according to the present embodiment are bound to each other by the structure 101 that can slide relative to each other due to thermal expansion and thus the bellows installed in the inner nozzle can be removed A combustor including a structure capable of effectively absorbing a thermal deformation amount, securing structural stability of an inner nozzle and an outer nozzle, and stably ensuring a mixture injection efficiency of the combustor, and a gas turbine including the same can do.

Hereinafter, various configurations of the main nozzle 100 of the combustor according to the present embodiment will be described in detail with reference to several embodiments.

4 shows a structure of a main nozzle 100 according to a first embodiment of the present invention.

The inner nozzle 110 and the outer nozzle 120 constituting the main nozzle 100 according to the present embodiment are overlapped with each other by a predetermined width W so that the inner nozzle 110 and the outer nozzle 120 are overlapped A sliding structure may be formed.

Here, the sliding structure refers to a structure in which axial lengths of the inner nozzle 110 and the outer nozzle 120 are relatively changed by thermal deformation to change the relative positions of the non-in nozzle 110 and the outer nozzle 120 Structure. Therefore, the structure that can be adopted in the sliding structure is not particularly limited as long as it can absorb the axial length by thermal deformation.

For example, one or more sliding rails are formed on the outer circumferential surface of the inner nozzle 110 overlapping with the outer nozzle 120, and an inner circumferential surface of the outer nozzle 120, which overlaps with the inner nozzle 110, A sliding protrusion of a structure can be formed.

5 shows a structure of an inner nozzle 110 and an outer nozzle 120 constituting the main nozzle 100 according to the second embodiment of the present invention.

The inner nozzle 110 and the outer nozzle 120 according to the present embodiment are also overlapped with each other by a predetermined width W so that the inner nozzle 110, which overlaps with the outer nozzle 120, 131 may be mounted.

5, it is preferable that the sliding ring 131 is inserted into the outer peripheral surface of the inner nozzle 110 by a predetermined depth d. Further, when one or more sliding rings 131 are mounted, a predetermined amount of lubricant material 134 may be filled between the sliding rings 131. At this time, the lubricant material 134 to be filled is preferably made of a heat-resistant material.

The above-mentioned sliding ring 131 is mounted on a portion where the inner nozzle 110 and the outer nozzle 120 are in contact with each other to stably induce the axial sliding deformation due to thermal deformation. In addition, It is also possible to ensure sealing of the binding portion of the outer nozzle 110 and the outer nozzle 120.

5, one or more sliding rings 131 may be mounted on the outer circumferential surface of the inner nozzle 110. As shown in Fig. It goes without saying that the number of mounting and mounting positions of the sliding ring 131 can be appropriately changed in consideration of the amount of thermal deformation.

6 shows a structure of an inner nozzle 110 and an outer nozzle 120 constituting the main nozzle 100 according to the third embodiment of the present invention.

The inner nozzle 110 and the outer nozzle 120 according to the present embodiment are also overlapped by a predetermined width W so that the outer circumferential surface of the inner nozzle 110 overlapped with the outer nozzle 120 is provided with one or more piston rings 132 and a sliding ring 131 can be mounted.

5, the piston ring 132 is also inserted into the outer circumferential surface of the inner nozzle 110 by a predetermined depth d.

The piston ring 132 may be mounted on a portion where the inner nozzle 110 and the outer nozzle 120 are in contact with each other to seal the binding portion of the inner nozzle 110 and the outer nozzle 120, It is a configuration that can also be guaranteed.

In some cases, as shown in FIG. 6, the piston ring 132 and the sliding ring 131 may each be mounted in two or more, in which case they may be alternately arranged. It goes without saying that the mounting number and mounting position of the piston ring 132 and the sliding ring 131 can be appropriately changed in consideration of the amount of thermal deformation.

7 shows the structure of the inner nozzle 110 and the outer nozzle 120 constituting the main nozzle 100 according to the fourth embodiment of the present invention.

The inner nozzle 110 and the outer nozzle 120 according to the present embodiment are also overlapped by a predetermined width W so that one end of the outer nozzle 120 is spaced apart from the inner nozzle 110 by a predetermined length in the direction of the outer peripheral surface of the inner nozzle 110 A stopping protrusion 121 may be formed to extend the inner diameter of the inner nozzle 110 to limit the length of the inner diameter of the inner nozzle 110.

In this case, the detent projection 121 preferably has a structure in which it is brought into close contact with the outer peripheral surface of the inner nozzle 110 so as to seal the inner nozzle 110 and the binding portion of the outer nozzle 120.

Also, a detent protrusion 111 having a contact surface corresponding to the inner circumferential surface of the outer nozzle 120 may be formed at one end of the inner nozzle 110. In this case, the detent protrusion 111 formed on the inner nozzle 110 is engaged with the detent protrusion 121 formed on the outer nozzle 120, so that the sliding changeable length of the inner nozzle 110 can be more stably restricted.

8 shows the structure of the inner nozzle 110 and the outer nozzle 120 constituting the main nozzle 100 according to the fifth embodiment of the present invention.

Stopping protrusions 111 and 121 may be formed at the respective ends of the inner nozzle 110 and the outer nozzle 120 according to the present embodiment. At this time, a sliding ring 131 or a piston ring 132 may be mounted on the inside of the detent protrusions 111 and 121, which are arbitrarily selected.

At this time, the sliding ring 131 or the piston ring 132 mounted on the inner side of the detent projection 121 of the outer nozzle 120 is mounted on the inner circumferential surface of the outer nozzle 120 to slide along with the movement of the outer nozzle 120 .

The sliding ring 131 or the piston ring 132 mounted on the inner side of the detent projection 111 of the inner nozzle 110 is mounted on the outer circumferential surface of the inner nozzle 110, .

9, at least two sliding rings 131 or piston rings 132 are provided between the detent protrusion 111 of the inner nozzle 110 and the detent protrusion 121 of the outer nozzle 120, The sliding ring 131 and the piston ring 132 are alternately disposed alternately so that not only stable sliding operation of the inner nozzle 110 and the outer nozzle 120 but also stable sealing can be ensured have.

10 shows a structure of an inner nozzle 110 and an outer nozzle 120 constituting the main nozzle 100 according to the sixth embodiment of the present invention.

The outer nozzle 120 and the outer nozzle 120 according to the present embodiment are also overlapped by a predetermined width W so that the outer nozzle 120 and the inner nozzle 110 are in contact with each other, A sealing member 133 having a spring structure made of a material having an elastic restoring force of the elastic restoring force can be mounted.

Specifically, the sealing member 133 may be mounted such that the inner nozzle 110 and the outer nozzle 120 can be relatively displaced relative to each other in the axial direction.

10, the lower end of the sealing member 133 is inserted into the outer circumferential surface of the inner nozzle 110 by a predetermined depth, and the upper end of the sealing member 133 is inserted into the outer nozzle surface of the outer nozzle 120 It is preferable that the inner circumferential surface is inserted and attached by a predetermined depth.

In this case, the sealing member 133 according to the present embodiment absorbs the relative amount of deformation of the inner nozzle 110 and the outer nozzle 120 by the heat energy provided from the outside, and when the supply of the thermal energy from the outside is blocked The initial relative positions of the inner nozzle 110 and the outer nozzle 120 can be restored.

The present invention can also provide a gas turbine including the compressor according to the above-mentioned present invention, and more particularly to a gas turbine including a structure capable of reducing the stress applied to the compressor while improving the flow characteristics of the compressed air A turbine can be provided.

It will be apparent to those skilled in the art that various modifications and variations can be made in the present invention without departing from the spirit of the invention as set forth in the appended claims. The present invention can be variously modified and changed by those skilled in the art, and it is also within the scope of the present invention.

1000: gas turbine according to the prior art
1100: Compressor
1200: Combustor
1210: External casing
1211: Air passage
1230: central nozzle
1231: Main nozzle
1250: Internal casing
1300: Turbine
100: main nozzle
101: Slidable coupling structure
110: inner tubular component
111: detent projection
120: outer tubular component
121: detent projection
131: Sliding ring
132: Piston ring
133: sealing member
134: lubricating material

Claims (18)

And an outer casing which is spaced apart from each other by a predetermined distance in an inner diameter direction and forms an air passage, wherein the combustion air introduced through the air passage is mixed with fuel and is injected into the combustion chamber through the central nozzle and the main nozzle As the combustor,
Wherein the central nozzle is installed in an axial direction of the combustor at a central portion of the inner casing and a plurality of the main nozzles are disposed inside the inner casing so as to surround the central nozzle,
The main nozzle is composed of an inner tubular component and an outer tubular component which are bound to each other by a predetermined width so as to be slidable,
Wherein the inner nozzle and the outer nozzle slide relative to each other due to thermal expansion to change the overall length of the main nozzle.
The method according to claim 1,
Wherein at least one sliding ring is mounted on an outer circumferential surface of the inner nozzle overlapping with the outer nozzle.
The method according to claim 1,
Wherein at least one piston ring is mounted on an outer circumferential surface of the inner nozzle overlapping with the outer nozzle.
The method according to claim 1,
Wherein at least one sliding ring and a piston ring are mounted on the outer circumferential surface of the inner nozzle overlapping with the outer nozzle.
5. The method of claim 4,
Wherein the sliding ring and the piston ring are alternately arranged alternately.
5. The method of claim 4,
Wherein the sliding ring and the piston ring are inserted and mounted on the outer peripheral surface of the inner nozzle by a predetermined depth.
The method according to claim 1,
Wherein one end of the outer nozzle is provided with a detent protrusion extending by a predetermined length in the direction of the outer circumference of the inner nozzle to limit the length of the inner nozzle slidable.
8. The method of claim 7,
Characterized in that the detent projection has a structure in which it is brought into close contact with an outer peripheral surface of the inner nozzle so as to seal a binding portion between the inner nozzle and the outer nozzle.
9. The method of claim 8,
And a piston ring which slides on the outer circumferential surface of the inner nozzle and seals the inner nozzle and the outer nozzle is mounted on the inner side of the detent projection.
9. The method of claim 8,
Wherein a sliding ring and a piston ring which are slid with the outer circumferential surface of the inner nozzle and seal the inner nozzle and the outer nozzle are alternately arranged alternately and mounted on the inner side of the detent projection.
The method according to claim 1,
At least one sliding rail is formed on the outer circumferential surface of the inner nozzle overlapping with the outer nozzle,
And a sliding protrusion having a structure corresponding to the sliding rail is formed on an inner circumferential surface of the outer nozzle overlapping with the inner nozzle.
12. The method of claim 11,
Wherein one end of the outer nozzle is provided with a detent protrusion extending by a predetermined length in the direction of the outer circumference of the inner nozzle to limit the length of the inner nozzle slidable.
13. The method of claim 12,
Characterized in that the detent projection has a structure in which it is brought into close contact with the outer circumferential surface of the inner nozzle so as to seal the binding portion of the inner nozzle and the outer nozzle.
The method according to claim 1,
Wherein a sealing member of a spring structure composed of a material having an elastic restoring force of a predetermined size is mounted on a portion where the inner nozzle and the outer nozzle are overlapped.
15. The method of claim 14,
Wherein the sealing member is mounted such that the inner nozzle and the outer nozzle are mutually displaceable relative to each other in the axial direction.
16. The method of claim 15,
The lower end of the sealing member is inserted and attached to the outer peripheral surface of the inner nozzle by a predetermined depth,
Wherein an upper end of the sealing member is inserted into the inner peripheral surface of the outer nozzle by a predetermined depth.
15. The method of claim 14,
Wherein the sealing member absorbs the relative positional deformation amount of the inner nozzle and the outer nozzle by heat energy provided from the outside and restores the initial relative position of the inner nozzle and the outer nozzle when the supply of heat energy from the outside is interrupted burner.
A gas turbine comprising a combustor according to any one of claims 1 to 17.

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