KR20150085394A - Combuster of gas turbine, gasturbineincluding the same, and cooling method thereof - Google Patents

Abstract

Disclosed are a combustor of a gas turbine, a gas turbine having the same, and a cooling method thereof. According to an embodiment of the present invention, the combustor of the gas turbine comprises: a liner arranged between a turbine and a compressor; a transition unit coupled to the liner and connected to the turbine for combustion gas of the liner to be supplied to a turbine side; and a cooling separation unit wherein compressed air respectively colliding with a plurality of areas is arranged to be mutually spaced from at least one of the transition unit and the liner for mutual interference to be limited when compressed air supplied to a combustor side from the compressor is respectively injected to the areas in the longitudinal direction of at least one of the transition unit and the liner.

Description

FIELD OF THE INVENTION [0001] The present invention relates to a combustor for a gas turbine, a gas turbine including the combustor, and a cooling method for the gas turbine,

The present invention relates to a combustor of a gas turbine and a gas turbine including the combustor and a cooling method thereof, and more particularly to a combustor of a gas turbine that provides a flow conduit such that combustion gas combusted by the liner flows toward the turbine side, A gas turbine and a cooling method thereof.

In a gas turbine, a combustor is connected to a compressor that compresses air, and a turbine is connected to the combustor. These compressors, combustors, and turbines are placed on the same central axis.

Among these, a combustor includes a fuel nozzle for injecting fuel, an ignition plug to which the fuel nozzle is connected and which can combust fuel mixed with air, a liner to provide an ignition space, and a transition to the combustion gas to the turbine side, Piece.

The transition piece is supplied with compressed air of a compressor supplied to the liner to prevent breakage of the turbine by the combustion gas. In this transition piece, holes are provided for cooling so that air can be blown in, and the compressed air cools the body inside through the holes.

Such a conventional transition piece is cooled as compressed air is injected through holes and then repeatedly collided with the main body side.

However, in the conventional transition piece, since the compressed air injected through the holes collides with the main body, the flow areas mutually interfere with each other, so that the kinetic energy of the compressed air corresponding to the holes located at different positions can be reduced, There is a problem that the cooling efficiency of the compressed air with respect to the combustion gas passing through the combustion chamber is deteriorated.

U. S. Patent No. 6, 923, 0002

In an embodiment of the present invention, when the cooling air supplied from the compressor collides with the outer wall portion, the phenomenon of flowing in the same direction as the direction of movement of the combustion gas is prevented, And a cooling method of the gas turbine, and a cooling method of the same.

According to an aspect of the invention, there is provided a turbine comprising: a liner disposed between a turbine and a compressor; A transition unit coupled to the liner and connected to the turbine to supply a combustion gas of the liner to the turbine; And when compressed air supplied from the compressor to the combustor is injected into a plurality of regions along a longitudinal direction of at least one of the transition unit and the liner, the compressed air, which is respectively impinged on the plurality of regions, And a cooling separation unit provided between the transition unit and the liner to be spaced apart from each other.

The cooling separation unit may include a plurality of the tabulator members spaced apart from each other along the longitudinal direction of the transition unit corresponding to the boundary region between the plurality of regions to which the compressed air is injected.

The tabulator member may be provided with a corrugated structure.

The plurality of the tabulator units may be provided such that a plurality of waveform regions are connected to corresponding regions, and the waveform region is connected to a narrower region that is gradually narrowed and an enlarged region that is widened gradually.

The waveform region may be arranged to be symmetrical with respect to the center line, and may be formed to form at least one of a circle, a square, and a rhombus.

The plurality of the tabulator members may be annularly arranged so as to surround the outer wall of the transition unit.

The collision protrusion may be provided in the corrugated area so that the flow direction is separated while the compressed air is collided when the compressed air flows along the outer wall of the transition unit.

Wherein the transition unit includes: a traction body provided so as to allow the combustion gas to pass therethrough, the turbulator member being disposed on an outer wall; And a cooling air spraying outer body which is provided to correspond to the transition body and is spaced apart from the transition body and surrounds the transition body and has cooling holes for spraying the compressed air to the transition body.

According to another aspect of the present invention, there is provided a turbine compressor comprising: a transition unit coupled to a liner within a combustor disposed between a turbine and a compressor, the transition unit being connected to the turbine such that the turbine is driven by combustion gas of the liner; And when compressed air supplied from the compressor to the combustor side is separately injected into a plurality of regions of the transition unit that cross the flow direction of the combustion gas, the compressed air is caused to collide with the plurality of regions while being separated from each other A combustor of a gas turbine including a cooling and separating unit provided to be spaced apart from the transition unit may be provided.

Wherein the transition unit includes a transition body provided so as to allow the combustion gas to pass therethrough so as to narrow the flow cross section toward the turbine side, wherein the cooling and separating unit is configured such that the corrugated regions corresponding to the compressed air are connected, And a plurality of tabulator members arranged in an annular shape spaced apart from each other on the outer wall of the transition body so as to be provided with a waveform structure.

Wherein a cooling air injection outer casing having a plurality of cooling holes for spraying the compressed air to the transition body side while surrounding the outside of the transition body is disposed outside the transition body, And the cooling holes of the cooling holes are symmetrical with each other.

The tabulator member may have a curved waveform structure.

The cooling separation unit may be provided with a cooling air passage so that the compressed air can pass therethrough.

The cooling air passage may be provided so as to allow the compressed air to flow into a region where the compressed air is injected from the transition unit.

The cooling fins may be disposed on the outer wall of the cooling / separating unit so as to allow the compressed air to flow from the transition unit to a region where the compressed air is injected.

According to another aspect of the present invention, a gas turbine including a combustor of the gas turbine described above can be provided.

According to yet another aspect of the present invention, there is provided a method comprising: supplying a combustion gas of the liner to the turbine side through a transition unit coupled to each liner within a combustor disposed between the turbine and the compressor; Spraying compressed air supplied from the compressor to the combustor side while supplying a combustion gas to the turbine side to a plurality of regions along the longitudinal direction of at least one of the transition unit and the liner; And limiting the mutual interference of the compressed air, which are respectively collided with the plurality of regions, by a cooling separation unit provided mutually spaced from the transition unit, can be provided.

The cooling separation unit may be provided to provide a corrugated area corresponding to cooling holes for supplying compressed air to the transition unit, and may provide the compressed air to the corrugated area.

The compressed air may flow to the cooling hole side by the cooling / separating unit after colliding with the outer wall of the transition unit.

The waveform region is provided with a narrow section and an enlarged section, and the compressed air can be provided in an enlarged section of the waveform area.

According to an embodiment of the present invention, when the cooling air supplied from the compressor collides with the outer wall portion, the phenomenon of the lateral movement of the combustion gas is prevented, and the cooling holes, It is possible to provide a combustor of a gas turbine and a gas turbine including the combustor of the gas turbine and a method of cooling the combustor.

1 is a schematic cross-sectional view of a gas turbine combustor having a transition piece according to an embodiment of the present invention.
Figure 2 is a schematic view of the transition piece of Figure 1;
Fig. 3 is a schematic view showing a tabulator member providing a rhombic waveform region with respect to the transition piece of Fig. 1; Fig.
Figure 4 is a schematic view showing a tabulator member providing a rectangular waveform region for the transition piece of Figure 1;
5 is a schematic view of a transition piece according to another embodiment of FIG.
6 is a perspective view of a tabulator member according to another embodiment of the present invention.
7 is a perspective view of a tabulator member according to another embodiment of the present invention.
Figure 8 is a schematic cross-sectional view of a gas turbine combustor with a liner according to an 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.

As shown in Figures 1 and 2, the transition piece 120 according to the present embodiment includes a transition piece 120 disposed within a combustor 100 disposed between a turbine (not shown) and a compressor (not shown) . The liner 110 provides a combustion space in which fuel injected by the fuel nozzle 111 is mixed with compressed air of a compressor (not shown) and burned. A fuel nozzle 111 is coupled to the front end of the liner 110 and an ignition plug 112 is coupled to the side wall.

A transition piece 120 is connected to the rear end of the liner 110 so that the combustion gas burned by the spark plug 112 can be sent to the turbine (not shown). The transition piece 120 is cooled by compressed air supplied from a compressor (not shown) so that breakage of the turbine (not shown) due to the high temperature of the combustion gas can be prevented.

Also, the transition piece 120 is provided with a flow path for accelerating the gas so as to accelerate the combustion gas, and a plurality of annularly arranged connection regions of the turbine (not shown) may be disposed in the same manner as the liner 110. The transition piece 120 according to the present embodiment will be described with reference to a can annular type combustor 100, but the present invention is not limited thereto.

1 and 2, the transition piece 120 according to the present embodiment includes a transition unit (not shown) connected to a turbine (not shown) to supply the combustion gas of the liner 110 to the turbine And a cooling separation unit 140 disposed in the transition unit 125 such that the flow of compressed air to the transition unit 125 is smoothly performed.

2, the transition unit 125 shown in FIG. 3 to FIG. 5 has a transitional body 130 disposed in a plan view along the longitudinal direction of the cooling air injection outer cylinder 150, Although the separation unit 140 is shown in a plan view thereof, substantially the cooling separation unit 140 is disposed so as to annularly surround the transition body 130, so that it can be seen to be distorted in a curved shape on the transition body 130. In this embodiment, since the cooling separation unit 140 is conceptually shown, the cooling separation unit 140 may differ from the actual implementation aspect.

According to the present embodiment, the transition unit 125 is provided with cooling holes 127 through which compressed air of a compressor (not shown) flows. The cooling holes 127 may be arranged at regular intervals along the longitudinal direction of the transition unit 125 and annularly arranged along the circumferential direction of the transition unit 125.

The compressed air flowing through the cooling holes 127 flows into the interior of the transition unit 125 and is sprayed on the inner wall surrounding the flow passage through which the combustion gas of the transition unit 125 passes. The compressed air can flow at a speed close to the speed of sound and hit the transition unit 125 to cool the transition unit 125.

At this time, the compressed air bumps into the transition unit 125, and then flows in the longitudinal direction along the flow direction of the combustion gas, passes through the inside of the transition unit 125 and compressed air that hits another region, It may interfere with the flow of compressed air flowing.

In order to smooth the flow by interfering with the compressed air, the transition unit 125 according to the present embodiment is provided with the cooling / separating unit 140 as described above. The cooling separation unit 140 may be disposed corresponding to the cooling holes 127 for supplying compressed air to the transition unit 125. [

When the compressed air supplied from the compressor (not shown) to the combustor 100 side is injected into a plurality of regions along the longitudinal direction of the transition unit 125, the cooling separation unit 140 according to the present embodiment has a plurality of The compressed air which is in collision with the regions is provided to be spaced apart from each other in the transition unit 125 so that mutual interference is limited.

The cooling separation unit 140 includes a plurality of tabulator members 145 spaced apart from each other along the longitudinal direction of the transition unit 125 corresponding to the boundary region between the plurality of regions to which the compressed air is injected, . ≪ / RTI >

That is, the cooling and separating unit 140 according to the present embodiment is provided with a tabulator member 145 disposed between the cooling holes 17 arranged along the longitudinal direction along the flow direction of the combustion gas. Such a tabulator member 145 may be provided to have a corrugated structure.

A plurality of the tabulator members 145 according to the present embodiment may be arranged such that a plurality of tabular regions 145 corresponding to the plurality of tabular regions 145 are connected to one another.

As an example, between the two tabulator members 145, a corrugated area 146 may be repeatedly formed. One corrugated area 146 may be disposed in a region corresponding to one cooling hole 127. [ In the corrugated area 146, compressed air flowing in one cooling hole 127 may mainly collide.

In addition, the waveform region 146 may be formed by connecting the gradually narrowing narrow region 147 and the gradually enlarging enlargement region 148. The enlarged section 148 of the corrugated area 146 may correspond to the cooling hole 127 and the narrow section 147 may be provided to connect the enlarged section 148 with each other.

At this time, the compressed air is supplied to the enlarged section 148 of the corrugated area 146 and then collided with the outer wall part of the transition body 130, which will be described later, of the transition unit 125, .

The waveform region 146 according to the present embodiment may be provided in a symmetrical sinusoidal wave form or wave form. Such a waveform region 146 may be provided in a different shape as shown in FIGS.

The corrugated area 146 may be disposed symmetrically with respect to the center line between the tablets 145 and may be formed to form at least one of a circle, a square, and a rhombus.

In Fig. 3, the corrugated area 146 is provided in a rhombic shape. The rhombic shaped corrugated area 146 can block the dispersed flow of the compressed air corresponding to the strong pressure of the compressed air unlike the corrugated corrugated area 146, . In addition, as shown in FIG. 4, a rectangular waveform region 146 in which rectangular regions are repeatedly arranged may be provided, unlike a rhombus shape.

As described above, the corrugated area 146 can be provided in a circular shape of a curved line like a wavy shape, or can be provided in a rhombus or rectangular shape. The waveform area 146 may be continuously arranged in the circumferential direction of the transition body 130 and may be arranged so that the number of the waveforms gradually decreases from the front end to the rear end of the transition body 130 or the arrangement interval increases.

4, collision protrusions 149 are provided in the corrugated area 146 according to the present embodiment so that the compressed air is collided when the compressed air flows along the outer wall of the transition unit 125, .

This impingement projection 149 can act as a cooling fin against the transition unit 125 like the tabulator member 145 to provide a wider cooling area and can provide cooling of the transition unit 125 by compressed air Performance can be improved.

This collision projection 149 is shown only in the rectangular-shaped waveform area 146, but may also be provided in the waveform area 146 of another shape. At this time, the impingement protrusion 149 may be formed in a shape like a double-edged knife whose cross section is gradually narrowed from the lower end portion to the upper end portion coupled to the transition body 130 so that the flow resistance against the compressed air is small.

The compressed air flowing into the transition body 130 can flow toward the respective cooling holes 127 without causing mutual interference in the respective waveform regions 146 provided by the tabulator member 145 May be joined to the compressed air flowing to the liner 110 side along the transition body 130 and returned to the cooling and combustion air of the liner 110.

The compressed air that cools the transition body 130 can cool the combustion gas flowing in the transition body 130 and the combustion gas can flow through the narrowed outlet 133 of the transition body 130 to the turbine To drive the turbine (not shown).

At this time, since the temperature of the combustion gas is provided at a temperature which is lower than the combustion time by cooling the compressed air, it is possible to prevent the blade (not shown) of the turbine (not shown) from cracking and breaking due to thermal stress.

The plurality of the above-described plurality of the tabulator members 145 may be annularly arranged so as to surround the outer wall portion of the transition unit 125. [ That is, the tabulator member 145 may be disposed so as to surround the transition body 130 as described later.

The transition unit 125 according to the present embodiment may include a transition body 130 corresponding to an inner cylinder and a cooling air injection outer cylinder 150 corresponding to an outer cylinder surrounding the transition body 130.

At this time, the transition body 130 is provided so as to allow the combustion gas to pass therethrough, and the tabulator member 145 is disposed on the outer wall portion. That is, the tab member 145 for forming the corrugated area 146 on the outer wall of the transition body 130 may be brazed, welded, or integrally formed.

The cooling air spraying outer body 150 is provided to correspond to the transition body 130 and surrounds the transition body 130 by being spaced apart from the transition body 130. The cooling air spraying outer body 150 has a cooling hole 127 are provided.

The cooling air spraying outer pipe 150 is a portrated sleeve having openings corresponding to the cooling holes 127 and may be connected to the flow sleeve 115 corresponding to the outer surface of the liner 110 have.

The compressed air impinging on the transition body 130 can flow to the side of the flow sleeve 115 through the porous sleeve and flows into the combustion space of the flame tube (not shown) on the inner side while passing through the flow sleeve 115 Can be introduced. The compressed air introduced into the combustion space in this way may act to lower the ignition temperature to lower the combustion temperature of the liner 110, that is, lean lean combustion.

A transition piece according to another embodiment of the present invention, which is almost the same as the transition piece as described above but differs in the configuration of the tabulator member, can be provided as shown in Figs. 5 to 7.

5, a transition piece according to another embodiment of the present invention includes a transition unit 225 coupled to a liner within a combustor disposed between a turbine and a compressor and connected to the turbine to drive the turbine by the combustion gas of the liner And a control unit for controlling the operation of the transition unit 225 such that compressed air supplied from the compressor to the combustor side is separated and injected into a plurality of regions of the transition unit 225 crossing the flow direction of the combustion gas, And a cooling separation unit 240 provided to be spaced apart from each other.

In effect, the transition unit 225 according to the present embodiment is provided with the waveform area 246 by the cooling separation unit 240 in almost the same width as in the above-described embodiment.

The compressed air can flow to the cooling hole 227 side after hitting the transition unit 225 and also flows along the cooling separation unit 240 to cool the cooling separation unit 240 and the transition body 230 .

The transition piece according to another embodiment may include a transition body 230 provided to allow combustion gas to pass therethrough and to be narrowed in the flow cross section toward the turbine side, And a plurality of tabulator units 245 arranged in a ring shape and spaced apart from each other on the outer wall of the transition body 230 so as to provide an annular cooling zone.

Such a tabulator member 245 may be provided in a corrugated structure having not only a curved waveform but also a corrugated structure having an angle in the same direction.

These plurality of the tabulator members 245 may be provided in a wavy structure and may be arranged at equal intervals or at different intervals. That is, the plurality of the tabulator members 245 can be arranged so that the interval gradually increases from the front end to the rear end of the transition body 230.

A cooling air spraying outer 250 having a plurality of cooling holes 227 for spraying compressed air to the transition body 230 side while covering the outside of the transition body 230 is disposed outside the transition body 230 And the plurality of the tabulator members 245 may be arranged so as to have a shape symmetrical to each other between the plurality of cooling holes 227.

That is, the tabulator member 245 may be arranged to be symmetrical with respect to the line connecting the cooling holes 227 disposed along the inner center line along the transition body 230 or at the outer periphery.

Meanwhile, as shown in FIG. 6, the cooling separation unit 240 according to another embodiment of the present invention may be provided with a cooling air passage 251 so that compressed air can pass therethrough. That is, the cooling air passage 251 may be formed in the tab member 245 so that the compressed air impinging on the transition body 230 may flow into the transition member 230 and pass therethrough.

The cooling air passage 251 may be connected to the upper end portion of the tabulator member 245 from the lower end thereof. Thus, the cooling air passage 251 is provided so as to allow the compressed air to flow into the region where the compressed air is injected from the transition unit 225.

In this manner, the cooling separation unit 240 in which the cooling air passage 251 is provided can be provided. 7, a cooling separation unit 240 according to yet another embodiment is shown.

The outer wall of the cooling separation unit 240 according to this another embodiment is provided with a cooling pin (not shown) for guiding the flow of the compressed air so as to allow the compressed air to flow into the region where the compressed air is injected from the transition unit 225 255 may be arranged.

Such a cooling fin 255 not only can guide the compressed air hitting the transition body 230 to the region where the cooling hole 227 is present but also can expand the cooling area of the tabulator member 245, The cooling efficiency with respect to the combustion gas passing through the transition body 230 by the rotor member 245 can be improved.

This cooling fin 255 can be disposed in the tabulator member 245 together with the cooling air passage 251 described above.

In addition, the cooling separation unit 140, 240 according to the above-described embodiments provides a continuous annular corrugated area 246, whereby the scope of the present invention is not limited thereto, (Not shown) having a plurality of circular, rectangular, or rhomboid shaped tubular portions (not shown) disposed on the outer wall of the bodies 130 and 230 but having a closed cooling area and the lower portion interconnected by a conduit.

In addition, according to one embodiment of the present invention, a gas turbine including the above-described combustor 100 can be provided.

On the other hand, the cooling method of the combustor 100 of the gas turbine according to the present embodiment is a method of cooling the transition units 130 and 230 by the compressed air, by the cooling separation units 140 and 240, 227, respectively, of the compressed air.

8, the cooling structure and method of the transition piece 110, 220 by the tabulator members 145, 245 of the cooling and separating units 140, 240 described above is the same as that of the flow sleeves of the liner 110 The cooling air can be introduced into the inner space between the flow sleeves 115 and 116 through holes (not shown) provided in the flow sleeves 115 and 115, so that the same can be applied to the flow sleeves 115 and 116.

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.

100: combustor 110: liner
111: fuel nozzle 112: spark plug
115, 116: Flow sleeve
120, 220: transition piece 125, 225: transition unit
127, 227: cooling holes 130, 230:
133: exhaust port 140, 240: cooling separation unit
145, 245: Teflator member 146, 246: Waveform region
147: Narrow section 148: Enlarged section
149: collision projection 150, 250: cooling air injection outer cylinder
251: cooling air passage 255: cooling pin

Claims (20)

A liner disposed between the turbine and the compressor;
A transition unit coupled to the liner and connected to the turbine to supply a combustion gas of the liner to the turbine; And
When compressed air supplied from the compressor to the combustor is injected into a plurality of regions along the longitudinal direction of at least one of the transition unit and the liner, And a cooling separation unit provided between at least one of the transition unit and the liner so as to be limited. The method according to claim 1,
Wherein the cooling separation unit includes a plurality of the tabulator members spaced apart from each other along the longitudinal direction of the transition unit corresponding to a boundary region between a plurality of regions into which the compressed air is injected. 3. The method of claim 2,
Wherein the turbogenerator member is provided with a corrugated structure. 3. The method of claim 2,
The combustor of a gas turbine according to any one of claims 1 to 5, wherein the plurality of the turbulator members comprises a plurality of waveform regions connected to corresponding regions, and the waveform region is connected to a narrower region where the waveform region is gradually narrowed and an enlarged region. 5. The method of claim 4,
Wherein the corrugated area is symmetrically disposed with respect to a center line, and is formed to form at least one of a circle, a square, and a rhombus. 5. The method of claim 4,
Wherein the plurality of the tabulator members are annularly arranged so as to surround the outer wall of the transition unit. The method according to claim 6,
And the impingement protrusions are provided in the corrugated area so that the impinging protrusions are collided when the compressed air flows along the outer wall part of the transition unit so that the flow direction is separated. 3. The method of claim 2,
The transition unit includes:
A traction body provided to allow the combustion gas to pass therethrough, the turbulator member being disposed on an outer wall portion; And
And a cooling air spraying outer body provided to correspond to the transition body and spaced apart from the transition body to surround the transition body and to discharge the compressed air to the transition body. A transition unit coupled to the liner within a combustor disposed between the turbine and the compressor and connected to the turbine such that the turbine is driven by the combustion gas of the liner; And
Wherein when the compressed air supplied from the compressor to the combustor side is separately injected into a plurality of regions of the transition unit that cross the flow direction of the combustion gas, the compressed air is divided into the plurality of regions, And a cooling separation unit provided to be spaced apart from at least one of the transition unit and the liner. 10. The method of claim 9,
The transition unit includes:
And a transition body provided so as to allow the combustion gas to pass therethrough, the transition body being provided so as to be narrowed toward the turbine side,
The cooling /
And a plurality of turbulator members arranged in an annular shape spaced apart from each other on the outer wall of the transition body so as to provide an annular cooling section, the turbulence components corresponding to the compressed air, Of the combustor. 11. The method of claim 10,
Wherein a cooling air spraying outer casing is provided outside the transition body and has a plurality of cooling holes for spraying the compressed air toward the transition body while enclosing the outside of the transition body,
Wherein the plurality of the tablets are arranged so as to have mutually symmetrical shapes between the plurality of cooling holes. 12. The method of claim 11,
The combustor of the gas turbine is provided with a curved wave structure. 10. The method of claim 9,
Wherein the cooling separation unit is provided with a cooling air passage so that the compressed air can pass therethrough. 14. The method of claim 13,
Wherein the cooling air passage is provided so as to allow the compressed air to flow into a region where the compressed air is injected from the transition unit. 10. The method of claim 9,
Wherein the cooling fins are disposed on the outer wall of the cooling and separating unit so as to allow the compressed air to flow into a region where the compressed air is ejected from the transition unit. A gas turbine comprising a combustor of said gas turbine according to any one of the preceding claims. Supplying a combustion gas of the liner to the turbine side through a transition unit coupled to each liner within a combustor disposed between the turbine and the compressor;
Spraying compressed air supplied from the compressor to the combustor side while supplying a combustion gas to the turbine side to a plurality of regions along the longitudinal direction of at least one of the transition unit and the liner; And
And limiting the mutual interference of the compressed air, which is respectively collided with the plurality of regions, by a cooling separation unit provided to be separated from at least one of the transition unit and the liner. 18. The method of claim 17,
Wherein the cooling separation unit is provided to provide a corrugated area corresponding to cooling holes for supplying compressed air to the transition unit,
And providing said compressed air to said corrugated area. 19. The method of claim 18,
Wherein the compressed air flows into the cooling hole side by the cooling / separating unit after colliding with the outer wall of the transition unit. 19. The method of claim 18,
Wherein the corrugated area is provided with a narrow section and an enlarged section, and the compressed air is provided in an enlarged section of the corrugated area.

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