KR101937589B1 - Turbine blade of turbine and turbine vane of turbine and turbine and gas turbine comprising the same - Google Patents

Abstract

The present invention relates to a turbine blade of a turbine installed on multiple layers of turbine discs of the turbine, which are installed in an axial direction of a tie rod, to be rotated along with the tie rod by the pressure made by the flow of combustion gas. The turbine blade includes: a turbine blade airfoil passing the combustion gas; a platform having one side combined with the turbine blade airfoil and keeping a gap with the adjacent turbine blade airfoil; and a turbine blade root member formed on the other side of the platform and mounting the turbine blade airfoil on the turbine discs. The turbine blade airfoil includes: a thermal expansion inducing space part formed to induce thermal expansion generated by heat from the combustion gas; and a partition part dividing the thermal expansion inducing space part into a plurality of inducing spaces. At least one of the inducing spaces has a trapezoidal cross section, the spaces have different heights and widths, and the spaces have the same cross-sectional area. Accordingly, the present invention provides the turbine blade of a turbine, a turbine vane of a turbine, and a turbine and a gas turbine including the same. Therefore, since a thermal expansion inducing space, which is an empty space to induce thermal expansion generated by combustion gas, is formed in the turbine blade passing the combustion gas and the turbine vane guiding the combustion gas passed by the turbine blade, the thermal expansion of the turbine blade and the turbine vane is induced, and thus, the present invention is capable of preventing the turbine blade and the turbine vane from being damaged by thermal expansion.

Description

TECHNICAL FIELD [0001] The present invention relates to a turbine blade, a turbine vane, and a turbine and gas turbine including the turbine blade,

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a turbine blade of a turbine, a turbine vane and a turbine and a gas turbine including the same, and more particularly, And a turbine and a gas turbine including the turbine blade, a turbine vane and a turbine including the turbine blade and the turbine blade, respectively, in which a space for inducing thermal expansion generated by the heat of the combustion gas is formed.

Turbine is a mechanism that obtains rotational force by impulsive force or reaction force by using a flow of compressible fluid such as steam or gas. The turbine includes a steam turbine using steam and a gas turbine using high temperature combustion gas. The gas turbine includes a compressor, a combustor, and a turbine. The compressor includes an air inlet for introducing air, and a plurality of compressor vanes and compressor blades are alternately arranged in the compressor casing.

The combustor supplies fuel to the compressed air compressed in the compressor and ignites it with a burner, so that combustion gas of high temperature and high pressure is generated. The turbine has a plurality of turbine vanes and turbine blades disposed alternately in the turbine casing. Further, a rotor is arranged to pass through the center of the compressor, the combustor, the turbine and the exhaust chamber.

Since these gas turbines have no reciprocating mechanism such as piston of 4-stroke engine, there is no mutual friction part like piston-cylinder, consumption of lubricating oil is extremely small, amplitude characteristic which is characteristic of reciprocating machine is greatly reduced, There are advantages.

Briefly describing the operation of the gas turbine, the compressed air in the compressor is mixed with the fuel and burned to produce a high-temperature combustion gas, and the combustion gas thus produced is injected toward the turbine. The injected combustion gas passes through the turbine vane and the turbine blades to generate a rotational force, which causes the rotor to rotate.

As a technology related to the turbine of such a gas turbine, Korean Utility Model Registration No. 20-0174662 discloses a gas turbine.

The turbine of the conventional gas turbine The turbine vane and the turbine vane that guide the flow of the combustion gas passing through the turbine blade are thermally expanded due to the high temperature combustion gas, and the portion where the turbine blade is fixed to the disk and the portion where the turbine vane is fixed to the casing are subjected to thermal stress There is a problem that the life of the turbine blades and the turbine vanes is reduced due to damage of the turbine blades and the turbine vanes due to thermal expansion and thermal stress.

The present invention has been made to solve the above problems, and it is an object of the present invention to provide a turbine vane which guides a flow of a combustion gas passing through a turbine blade and a turbine blade to a space for inducing thermal expansion generated by heat of the combustion gas A turbine blade and a turbine vane having a structure capable of preventing thermal expansion of a turbine blade and a turbine vane from being damaged by inducing thermal expansion of the turbine blade and the turbine vane, and a turbine and a gas turbine including the same. have.

According to an aspect of the present invention, there is provided a turbine for a turbine, which is installed in a turbine disk of a turbine provided at multiple stages along an axial direction of a tie rod and rotates together with the tie rod by a pressure when a combustion gas flows, A turbine blade airfoil for passing the combustion gas through the turbine blade airfoil; a platform coupled to one side of the turbine blade airfoil to maintain an interval between adjacent turbine blade airfoils; And a turbine blade root member for mounting the blade airfoil on the turbine disk, wherein the turbine blade airfoil is provided therein with a thermal expansion induction space for inducing thermal expansion generated by the heat of the combustion gas, And a partition wall part dividing the part into a plurality of guide spaces Wherein at least one of the plurality of induction spaces has a trapezoidal cross section, the plurality of induction spaces have different heights and widths, and the plurality of induction spaces have the same cross-sectional area. Blade.

In the turbine blade of the turbine according to the present invention, the inner surface of the turbine blade airfoil constituting the thermal expansion inducing space may have the same shape as the outer surface of the turbine blade airfoil.

The plurality of guide spaces may have a height greater than a guide space formed on an adjacent lower side, and corners of the guide space having a trapezoidal cross section may be rounded.

The partition wall may be formed of a plurality of partition walls, and the partition wall may have the same thickness as the side wall of the turbine blade airfoil.

The outer surface of the turbine disk may have a turbine disk slot on which the turbine blade root member is mounted, and the turbine disk slot may have a shape corresponding to the shape of the turbine blade root member.

According to another aspect of the present invention, there is provided a turbine rotor comprising a plurality of turbine blades installed in a turbine disk of a turbine provided at multiple stages along an axial direction of a tie rod, The turbine vane being installed in multiple stages along the axial direction of the turbine casing and guiding the flow direction of the combustion gas passing through the turbine blades, the turbine vane being configured to guide the flow direction of the combustion gas passing through the turbine blades, And a turbine vane outer shroud which is coupled to the turbine vane airfoil and fixes the turbine vane airfoil to the turbine casing, wherein the turbine vane airfoil is generated by the heat of the combustion gas inside the turbine vane airfoil A first thermal expansion inducing space for inducing thermal expansion is formed, Wherein at least one of the plurality of first guide spaces has a trapezoidal cross-section, and the plurality of first guide spaces are different from each other, and the guide spaces are divided into a plurality of first guide spaces, And the plurality of first induction spaces have the same cross-sectional area.

In the turbine vane of the turbine according to the present invention, the inner surface of the turbine vane airfoil constituting the first thermal expansion induction space portion may have the same shape as the outer surface of the turbine vane airfoil.

The plurality of first guide spaces may have a height greater than that of the first guide space formed on an adjacent lower side, and the corners of the first guide space having a trapezoidal cross section may be rounded.

The first partition wall may have a plurality of first partition walls, and the first partition wall may have the same thickness as the sidewalls of the turbine vane airfoil.

According to still another aspect of the present invention, there is provided a turbine for generating a power for generating electric power by passing a combustion gas supplied from a combustor to a plurality of turbine disks, A turbine blade airfoil for passing the combustion gas, a platform coupled to the turbine blade airfoil and spaced apart from the adjacent turbine blade airfoil, a turbine blade airfoil formed on the other surface of the platform, A turbine rotor including a plurality of turbine blades including a turbine blade root member mounted to a disk; A turbine casing for accommodating the turbine rotor therein; A turbine vane airfoil installed inside the turbine casing to be disposed between the plurality of turbine blades and guiding a flow direction of the combustion gas passing through the turbine blades; And a plurality of turbine vanes including a turbine vane outer shroud for fixing a turbine vane airfoil inside the turbine casing, wherein the turbine blade airfoil has a thermal expansion induction for inducing thermal expansion generated by the heat of the combustion gas, Wherein at least one of the plurality of induction spaces has a trapezoidal cross-section, and the plurality of induction spaces have different heights and a plurality of induction spaces, Wherein the plurality of guide spaces have a cross-sectional area It provides a turbine, characterized in that a.

In the turbine according to the present invention, the inner surface of the turbine blade airfoil forming the thermal expansion inducing space may have the same shape as the outer surface of the turbine blade airfoil.

The plurality of guide spaces may have a height greater than that of the guide spaces formed on the adjacent lower side, and the edges of the guide space having a trapezoidal cross section may be rounded.

The partition wall may be formed of a plurality of partition walls, and the partition wall may have the same thickness as the side wall of the turbine blade airfoil.

The outer surface of the turbine disk may have a turbine disk slot on which the turbine blade root member is mounted, and the turbine disk slot may have a shape corresponding to the shape of the turbine blade root member.

According to another aspect of the present invention, there is provided a compressor comprising: a compressor for sucking and compressing air; A combustor for combusting the fuel through the compressed air supplied from the compressor to generate a combustion gas; And a turbine blade airfoil coupled to an outer surface of the plurality of turbine disks to allow the combustion gas to pass therethrough, wherein the turbine blade airfoil is rotated by a combustion gas supplied from the combustor, And a plurality of turbine blades formed on the other side of the platform and including a turbine blade root member for mounting the turbine blade airfoil on the turbine disk, A turbine casing disposed inside the turbine casing so as to be disposed between the plurality of turbine blades and configured to guide the flow direction of the combustion gas passing through the turbine blades, An airfoil, one side of the turbine vane airfoil And a turbine vane outer shroud for coupling the turbine vane airfoil and the turbine vane airfoil inside the turbine casing, wherein the turbine blade airfoil includes a plurality of turbine vanes And a partition wall part for dividing the thermal expansion induction space part into a plurality of induction spaces, at least one of the plurality of induction spaces having a trapezoidal cross section, The plurality of induction spaces have different heights and widths, and the plurality of induction spaces have the same cross-sectional area.

In the gas turbine according to the present invention, the inner surface of the turbine blade airfoil constituting the thermal expansion inducing space may have the same shape as the outer surface of the turbine blade airfoil.

The plurality of guide spaces may have a height greater than that of the guide spaces formed on the adjacent lower side, and the edges of the guide space having a trapezoidal cross section may be rounded.

The partition wall may be formed of a plurality of partition walls, and the partition wall may have the same thickness as the side wall of the turbine blade airfoil.

The outer surface of the turbine disk may have a turbine disk slot on which the turbine blade root member is mounted, and the turbine disk slot may have a shape corresponding to the shape of the turbine blade root member.

The turbine blades and the turbine vanes of the turbine according to the present invention, and the turbines and gas turbines including the turbine blades, the turbine blades and the turbine blades having the turbine blades and the gas turbines according to the present invention are provided with a turbine blade for passing the combustion gas and a thermal expansion And the thermal expansion of the turbine blades and the turbine vanes is induced, thereby preventing damage and destruction of the turbine blades and the turbine vanes due to thermal expansion.

FIG. 1 is a schematic view of a gas turbine to which a turbine blade and a turbine vane are applied according to an embodiment of the present invention. Referring to FIG.
Fig. 2 is an enlarged perspective view of the turbine blade shown in Fig. 1. Fig.
3 is a sectional view taken along the line aa in Fig.
4 is a cross-sectional view taken along the line bb in Fig.
Fig. 5 is an enlarged perspective view of the turbine vane shown in Fig. 1. Fig.
6 is a cross-sectional view taken along line cc of Fig.

Hereinafter, a turbine blade and a turbine vane of a turbine according to the present invention, and a turbine and a gas turbine including the same, will be described with reference to the drawings.

1, a gas turbine 10 according to the present invention includes a tie rod 100, a compressor 200, a torque tube 300, a combustor 400, and a turbine 1000, The tie rod 100 is a rod member installed to cross the center portion of the gas turbine 10 and the tie rod 100 serves to fasten the compressor 200 and the turbine 1000.

The gas turbine 10 is provided with a housing 10a and a diffuser 10b through which the combustion gas passing through the turbine 1000 is discharged is disposed at a rear side of the housing 10a. A combustor 400 for supplying compressed air to the combustion chamber 400 is disposed.

Referring to the flow direction of the air, the compressor 20 is positioned on the upstream side of the housing 10a and the turbine 1000 is disposed on the downstream side of the housing 10a. A torque tube 300 is disposed between the compressor 200 and the turbine 1000 as a torque transmitting member for transmitting the rotation torque generated from the turbine 1000 to the compressor 200.

The compressor 200 is provided with a plurality of (for example, fourteen) compressor discs 220 and the respective compressor discs 220 are fastened in the axial direction by the tie rods 100 .

Specifically, each of the compressor discs 220 is aligned substantially along the axial direction with the tie rods 100 passing through the center thereof. Here, each adjacent compressor disk 220 is disposed such that the opposing surfaces thereof are squeezed by the tie rod 100 and can not be rotated.

A plurality of compressor blades 240 are radially coupled to the outer circumferential surface of the compressor disk 220. Each of the compressor blades 240 has a compressor blade root member 260 and is fastened to the compressor disk 220.

Between each of the compressor disks 220, there is a compressor vane 280 fixed to the housing 10a. The compressor vane 280 is fixed to the compressor disk 220 so as not to rotate unlike the compressor disk 220. The compressor vane 280 aligns the flow of the compressed air having passed through the compressor blade 240 of the compressor disk 220, To guide the air to the compressor blade (240) of the compressor (220).

The fastening method of the compressor blade root member 260 is a tangential type and an axial type. This can be chosen according to the required structure of the commercial gas turbine and can have a generally known dovetail or fir-tree. In some cases, the compressor blades may be fastened to the compressor rotor disk using fasteners other than those described above, such as keys or bolts.

The tie rod 100 is disposed to pass through the center of the plurality of compressor disks 220. One end of the tie rod 100 is fastened to the compressor disk 220 located at the most upstream side and the other end of the tie rod 100 is fastened to the inside of the torque tube 3000 .

The combustor 400 mixes and combusts the introduced compressed air with the fuel to produce a high-temperature high-temperature and high-pressure combustion gas. In the course of the rolling process, the combustion gas temperature is increased to the heat resistance limit tolerated by the combustor and the turbine component do.

A plurality of combustors constituting a combustion system of a gas turbine may be arranged in a casing formed in a cell shape and include a burner including a fuel injection nozzle and the like, a combustor liner forming a combustion chamber, And a transition piece as a connection part of the turbine.

Specifically, the liner provides a combustion space in which the fuel injected by the fuel nozzle is mixed with the compressed air of the compressor and burned. Such a liner may include a flame passage providing a combustion space in which fuel mixed with air is combusted, and a flow sleeve forming an annular space surrounding the flame tube. A fuel nozzle is coupled to the front end of the liner, and a spark plug is coupled to the side wall.

On the other hand, a transition piece is connected to the rear end of the liner so that the combustion gas burned by the spark plug can be sent to the turbine side. This transition piece is cooled by compressed air supplied from the compressor through the outer wall portion so as to prevent breakage by the high temperature of the combustion gas.

 To this end, the transition piece is provided with cooling holes for blowing air inward, and the compressed air flows to the liner side after cooling the body inside the holes through the holes.

In the annular space of the liner, the cooling air cooled by the transition piece flows. On the outer wall of the liner, compressed air is supplied from the outside of the flow sleeve through the cooling holes provided in the flow sleeve to collide with the cooling air.

The high-temperature and high-pressure combustion gases from the combustor 400 are supplied to the turbine 1000 described above. The supplied high-temperature and high-pressure combustion gas expands and gives a reaction force to the rotating blades of the turbine to induce a rotating torque. The torque thus obtained is transmitted to the compressor 200 through the torque tube 300 described above, The power exceeding the required power is used to drive the generator.

The turbine 1000 is basically similar in structure to the compressor 200. The turbine 1000 includes a plurality of turbine rotors 1100, a turbine casing 1200 that accommodates the plurality of turbine rotors 1100, And a plurality of turbine vanes 1300 provided between the plurality of turbine rotors 1100.

Referring to FIGS. 1 and 2, the plurality of turbine rotors 1100 includes a plurality of turbine disks 1120 and a plurality of turbine blades 1140. The turbine blades 1140 may include a turbine blade airfoil 1142, a platform 1144, and a turbine blade root member 1146.

The turbine blade airfoil 1142 is coupled to the outer surfaces of the plurality of turbine disks 1120 to allow the combustion gas to pass therethrough and the platform 1144 is coupled to the turbine blade airfoil 1142 And the interval between the airfoil 1142 and the turbine blade airfoil 1142 is maintained. The turbine blade root member 1146 is formed on the other surface of the platform 1144 and functions to mount the turbine blade airfoil 1142 on the turbine disk 1120.

The turbine disk 1120 is formed with a turbine disk slot 1120a on which the turbine blade root member 1146 is mounted and the turbine disk slot 1120a is formed on an outer surface of the turbine disk 1120, The turbine disk slot 1120a preferably has a shape corresponding to the shape of the turbine blade root member 1146. [

A plurality of turbine blades 1140 are installed on the outer circumferential surface of the tie rod 100 to allow the combustion gas to pass through the turbine casing 1200 while being rotated by the pressure of the combustion gas. The blade airfoil 1142 is preferably provided with a thermal expansion inducing space 1143 for inducing thermal expansion generated by the heat of the combustion gas.

3 and 4, the thermal expansion induction space 1143 is divided into a plurality of induction spaces 1143a by partition walls 1143b, and the induction spaces 143a have a substantially trapezoidal cross section And the edges of the trapezoidal shape are preferably round-processed. The guide space 1143a is prevented from being damaged or broken at the time of thermal expansion owing to the rounding of the corners of the guide space 1143a and the guide space 1143a has a trapezoidal shape, can do. At least one of the plurality of guide spaces may have a trapezoidal cross section.

The inner surface 1142a of the turbine blade airfoil 1142 forming the thermal expansion inducing space 1143 has the same shape as the outer surface 1142b of the turbine blade airfoil 1142, The plurality of guide spaces 1143a spaced apart from each other by the guide rails 1143a and 1143b have different heights and widths. The plurality of partition walls 1143c constituting the partition wall portion 1143b preferably have the same thickness as the side wall 1142c of the turbine blade airfoil 1142 and have the same thickness to uniformly induce thermal expansion do.

The turbine blade airfoil 1142 has a cross-sectional shape that is thicker on one side of the turbine blade airfoil 1142 and is sloped from one surface to the other surface of the turbine blade airfoil 1142 toward the other surface The inner surface 1142a of the turbine blade airfoil 1142 forming the thermal expansion inducing space 1143 has the same shape as the outer surface 1142b to form a plurality of It is preferable that the guide spaces 1143a have different heights and widths to have the same cross-sectional area.

The plurality of guide spaces 1143a may have a height greater than that of the guide spaces 1143a formed on the lower side and may have the same cross-sectional area as the guide spaces 1143a formed on the lower side adjacent to the guide spaces 1143a. The plurality of guide spaces 1143a have the same cross-sectional area, so that the thermal expansion can be guided uniformly.

1 and 5, a turbine vane 1300 for guiding the flow direction of the combustion gas passing through the turbine blade 1140 is mounted on an inner circumferential surface of the casing 1200, and the turbine vane 1300 A turbine vane outer foil 1320 for guiding the flow direction of the combustion gas and a turbine vane outer shroud 1340 for fixing one end of the turbine vane airfoil 1320 to the inside of the turbine casing 1200. The turbine casing 1200 may be formed with a separate groove 1220 through which the turbine vane outer shroud 1340 is mounted.

Referring to FIG. 6, a first thermal expansion guide space 1321 is formed in the turbine vane airfoil 1320 in the same manner as the turbine blade airfoil 1142, The partition 1321 is partitioned into a plurality of first guide spaces 1322 by a first partition wall 1323 and the first partition wall 1323 includes a plurality of first partition walls 1323a. The first thermal expansion inducing space part 1321 is substantially the same as the thermal expansion inducing space part 1143 and a detailed description thereof will be given to a thermal expansion inducing space part 1143 formed inside the turbine blade airfoil 1142 It will be omitted because it is duplicated.

The turbine disk 1120 is a rotating body rotating together with the turbine blade 1140 as the turbine blade 1140 rotates by the combustion gas. The turbine vane 1300 is fixed to the turbine casing 1200, And the combustion gas passes through the turbine blade 1140 and pushes the turbine blade 1140. In this case, When the combustion gas pushes the turbine blade 1140, the turbine blade 1140 and the turbine disk 1120 rotate about the tie rod 100 as a center axis, and the combustion gas passing through the turbine blade 1140 The turbine vane airfoil 1320 of the turbine vane 1300 is guided in the flow direction and discharged to the outside through the diffuser 10b.

A turbine blade 1140 for passing the combustion gas introduced into the turbine casing 1200 and a thermal expansion generated by the combustion gas in the turbine vane 1300 for guiding the combustion gas passed through the turbine blade 1140 The thermal expansion of the turbine blade 1140 and the turbine vane 1300 by inducing thermal expansion of the turbine blade 1140 and the turbine vane 1300 to prevent damage and breakage of the turbine blade 1140 and the turbine vane 1300 due to thermal expansion can do.

While the present invention has been described with reference to exemplary embodiments, it is to be understood that the invention is not limited to the disclosed exemplary embodiments, but, on the contrary, is intended to cover various modifications and equivalent arrangements included within the spirit and scope of the appended claims. Accordingly, the true scope of the present invention should be determined by the technical idea of the appended claims.

10: gas turbine 100: tie rod
200: compressor 220: compressor disk
240: Compressor blade 260: Compressor blade root member
300: Torque tube 400: Combustor
1000: Turbine 1100: Turbine rotor
1120: Turbine disk 1140: Turbine blade
1142: turbine blade airfoil 1144: platform
1146: turbine blade root member 1200: turbine casing
1300: Turbine vane 1320: Turbine vane air foil
1340: Turbine vane outer shroud

Claims (27)

1. A turbine blade of a turbine provided on a turbine disk of a turbine provided at multiple stages along an axial direction of a tie rod and rotating together with the tie rod by a pressure when a combustion gas flows,
A turbine blade airfoil for passing the combustion gas,
A platform coupled to one side of the turbine blade airfoil and spaced apart from adjacent turbine blade airfoils;
A turbine blade root member formed on the other side of the platform and mounting the turbine blade airfoil to the turbine disk,
Wherein the turbine blade airfoil includes a thermal expansion inducing space for inducing thermal expansion generated by the heat of the combustion gas,
And a partition wall part dividing the thermal expansion induction space part into a plurality of induction spaces,
Wherein at least one of the plurality of guide spaces has a trapezoidal cross section,
Wherein the plurality of induction spaces have different heights and widths, and the plurality of induction spaces have the same cross-sectional area.
The method according to claim 1,
Wherein the inner surface of the turbine blade airfoil forming the thermal expansion inducing space has the same shape as the outer surface of the turbine blade airfoil.
delete The method according to claim 1,
Wherein each of the plurality of guide spaces has a height greater than an induction space formed on an adjacent lower side of the turbine blade.
The method according to claim 1,
The edge of the guide space having a trapezoidal cross section is rounded.
The method according to claim 1,
Wherein the barrier rib is formed of a plurality of barrier ribs,
Wherein the partition wall has the same thickness as the side wall of the turbine blade airfoil.
The method according to claim 1,
Wherein an outer surface of the turbine disk is formed with a turbine disk slot on which the turbine blade root member is mounted and the turbine disk slot has a shape corresponding to the shape of the turbine blade root member.
A plurality of turbine blades installed along the axial direction of the tie rod and installed at multiple stages along the axial direction of the tie rod between the turbine blades installed on the turbine disk of the turbine provided along the axial direction of the tie rod and rotated together with the tie- And a turbine vane fixed to the turbine casing and guiding a flow direction of the combustion gas passing through the turbine blade,
A turbine vane airfoil for guiding a flow direction of the combustion gas passing through the turbine blades,
A turbine vane outer shroud having one side joined to the turbine vane airfoil and fixing the turbine vane airfoil to the turbine casing,
A first thermal expansion inducing space for inducing thermal expansion generated by heat of the combustion gas is formed inside the turbine vane airfoil,
And a first partition wall part dividing the first thermal expansion inducing space part into a plurality of first induction spaces,
Wherein at least one of the plurality of first guide spaces has a trapezoidal cross section,
Wherein the plurality of first guide spaces have different heights and widths, and the plurality of first guide spaces have the same cross-sectional area.
The method of claim 8,
Wherein the inner surface of the turbine vane airfoil forming the first thermal expansion inducing space portion has the same shape as the outer surface of the turbine vane airfoil.
delete The method of claim 8,
Wherein the plurality of first guide spaces have a height greater than a first guide space formed on an adjacent lower side of the turbine vane.
The method of claim 8,
The edge of the first guide space having a trapezoidal cross section is rounded.
The method of claim 8,
The first partition wall may include a plurality of first partition walls,
Wherein the first bulkhead has a thickness equal to the sidewall of the turbine vane airfoil.
1. A turbine for generating a power for generating electric power by passing a combustion gas supplied from a combustor,
A plurality of turbine disks, a turbine blade airfoil coupled to an outer surface of each of the plurality of turbine disks to allow the combustion gas to pass therethrough, a gap between the turbine blade airfoil and a turbine blade airfoil A plurality of turbine blades formed on the other side of the platform and including a turbine blade root member for mounting the turbine blade airfoil to the turbine disk;
A turbine casing for accommodating the turbine rotor therein; And
A turbine vane airfoil installed inside the turbine casing to be disposed between the plurality of turbine blades and guiding a flow direction of the combustion gas passing through the turbine blades; And a plurality of turbine vanes including a turbine vane outer shroud for fixing the vane airfoil inside the turbine casing,
Wherein the turbine blade airfoil includes a thermal expansion inducing space for inducing thermal expansion generated by the heat of the combustion gas,
And a partition wall part dividing the thermal expansion induction space part into a plurality of guide spaces,
Wherein at least one of the plurality of guide spaces has a trapezoidal cross section,
Wherein the plurality of induction spaces have different heights and widths, and the plurality of induction spaces have the same cross-sectional area.
15. The method of claim 14,
Wherein the inner surface of the turbine blade airfoil constituting the thermal expansion inducing space portion has the same shape as the outer surface of the turbine blade airfoil.
delete 15. The method of claim 14,
And each of the plurality of guide spaces has a height greater than a guide space formed on an adjacent lower side.
15. The method of claim 14,
The edge of the guide space having a trapezoidal cross section is rounded.
15. The method of claim 14,
Wherein the barrier rib is formed of a plurality of barrier ribs,
Wherein the partition wall has the same thickness as the side wall of the turbine blade airfoil.
15. The method of claim 14,
A turbine disk slot in which the turbine blade root member is mounted is formed on the outer surface of the turbine disk, and the turbine disk slot has a shape corresponding to the shape of the turbine blade root member.
A compressor for sucking and compressing air;
A combustor for combusting the fuel through the compressed air supplied from the compressor to generate a combustion gas; And
A turbine blade airfoil coupled to an outer surface of the plurality of turbine disks to allow the combustion gas to pass therethrough, and a plurality of turbine blade airfoils A plurality of turbine blades including a platform for coupling and maintaining spacing between adjacent turbine blade airfoils, and a turbine blade root member formed on the other side of the platform for mounting the turbine blade airfoils to the turbine disk A rotor,
A turbine casing for accommodating the turbine rotor therein,
A turbine vane airfoil installed inside the turbine casing so as to be disposed between the plurality of turbine blades and guiding a flow direction of the combustion gas passing through the turbine blades, a turbine vane airfoil coupled to the turbine vane airfoil, A turbine including a plurality of turbine vanes including a turbine vane outer shroud for securing an airfoil inside the turbine casing,
Wherein the turbine blade airfoil includes a thermal expansion inducing space for inducing thermal expansion generated by the heat of the combustion gas,
And a partition wall part dividing the thermal expansion induction space part into a plurality of guide spaces,
Wherein at least one of the plurality of guide spaces has a trapezoidal cross section,
Wherein the plurality of guide spaces have different heights and widths, and the plurality of guide spaces have the same cross-sectional area.

23. The method of claim 21,
Wherein the inner surface of the turbine blade airfoil forming the thermal expansion inducing space portion has the same shape as the outer surface of the turbine blade airfoil.
delete 23. The method of claim 21,
Wherein each of the plurality of guide spaces has a height greater than a guide space formed on an adjacent lower side.
23. The method of claim 21,
The edge of the guide space having a trapezoidal cross section is rounded.
23. The method of claim 21,
Wherein the barrier rib is formed of a plurality of barrier ribs,
Wherein the partition wall has the same thickness as the side wall of the turbine blade airfoil.
23. The method of claim 21,
Wherein the outer surface of the turbine disk is formed with a turbine disk slot on which the turbine blade root member is mounted, and the turbine disk slot has a shape corresponding to the shape of the turbine blade root member.

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