KR101985098B1 - Gas turbine - Google Patents

Abstract

The present invention relates to a gas turbine including a housing, a rotor, a compressor, a combustor and a turbine, the turbine including a turbine blade rotated together with the rotor, the turbine blade including a turbine blade root portion extending toward the rotor side Wherein the rotor includes a turbine blade engagement slot into which the turbine blade root portion is inserted and the turbine blade engagement slot is formed to be larger than the turbine blade root portion so that a gap between the root portion of the turbine blade and the turbine blade engagement slot A clearance may be formed between the root of the turbine blade and the turbine blade coupling slot, and a gap reducing member may be interposed between the root of the turbine blade and the turbine blade coupling slot to reduce the gap during operation. This not only facilitates fastening between the turbine blades and the turbine rotor disk but also prevents the cooling fluid discharged from the turbine rotor disk from leaking through the gap for cooling the turbine blades.

Description

[0001] GAS TURBINE [0002]

The present invention relates to a gas turbine.

Generally, a turbine is a machine that converts the energy of a fluid such as water, gas, steam, etc. into mechanical work. It usually plantes several feathers or wings on the circumference of a rotating body and emits vapor or gas to it. Turbine type machines that rotate are called turbines.

Examples of such turbines include a hydraulic turbine that utilizes the energy of water at high places, a steam turbine that utilizes the energy of the steam, an air turbine that uses the energy of high-pressure compressed air, a gas that utilizes the energy of high- Turbines and the like.

Among them, the gas turbine includes a compressor, a combustor, a turbine, and a rotor.

The compressor includes a plurality of compressor vanes and a plurality of compressor blades disposed alternately with each other.

The combustor supplies fuel to the compressed air compressed in the compressor and ignites it with a burner to generate combustion gas of high temperature and high pressure.

The turbine includes a plurality of turbine vanes and a plurality of turbine blades alternately arranged.

The rotor is formed to pass through the center of the compressor, the combustor, and the turbine. Both ends of the rotor are rotatably supported by bearings, and one end is connected to the drive shaft of the generator.

The rotor includes a plurality of compressor rotor disks coupled with the compressor blades, a plurality of turbine rotor disks coupled with the turbine blades, and a torque tube transmitting torque from the turbine rotor disks to the compressor rotor disk.

In the gas turbine according to this configuration, the compressed air in the compressor is mixed with the fuel in the combustion chamber to be burned, thereby being converted into a high-temperature combustion gas, and the combustion gas thus produced is injected toward the turbine, So that the rotor rotates.

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.

Here, the turbine blade includes a turbine blade root portion extending toward the turbine rotor disk for coupling between the turbine blade and the turbine rotor disk, and the turbine rotor disk has a turbine blade engagement slot into which the turbine blade root portion is inserted .

The turbine blade root portion and the turbine blade coupling slot are formed such that the turbine blade root portion and the turbine blade coupling slot are easily engageable with each other so that the turbine blade coupling slot is formed larger than the turbine blade root portion, A clearance is formed between the turbine blade root portion and the turbine blade engagement slot.

Unlike the compressor, the turbine is required to have a cooling means for preventing damage such as deterioration due to contact with combustion gas of high temperature and high pressure. To this end, compressed air (cooling fluid) is added at a portion of the compressor, Wherein the cooling passage is formed as an internal passage extending through the inside of the rotor and communicates with a turbine blade cooling passage formed inside the turbine blade, A discharge port is formed in the compressor blade engagement slot, and an inlet of the turbine blade cooling passage is formed in the root portion of the turbine blade.

However, in such a conventional gas turbine, a part of the cooling fluid (air) discharged from the discharge port of the cooling flow path flows into the cooling path of the turbine blade, but a part of the cooling fluid (air) discharged from the discharge port of the cooling flow path Is leaked to the space through which the combustion gas passes through the clearance, thereby lowering the cooling efficiency.

Korean Patent Publication No. 10-1509383

Accordingly, the present invention is based on the finding that when a gap is formed between a turbine blade and a turbine rotor disk to facilitate fastening between the turbine blade and the turbine rotor disk, the cooling fluid discharged from the turbine rotor disk for cooling the turbine blade Which can prevent the gas turbine from leaking through the gas turbine.

The present invention, in order to achieve the above-mentioned object, comprises a housing; A rotor rotatably installed in the housing; A compressor which receives rotational force from the rotor and compresses air; A combustor for combusting the compressed air in the compressor to generate a combustion gas; And a turbine that rotates the rotor by receiving a rotational force from the combustion gas generated from the combustor, wherein the turbine includes a turbine blade rotated together with the rotor, and the turbine blade includes a turbine blade root Wherein the rotor includes a turbine blade engagement slot into which the turbine blade root portion is inserted and the turbine blade engagement slot is formed to be larger than the turbine blade root portion so that a gap between the root portion of the turbine blade and the turbine blade engagement slot And a gap reducing member interposed between the root of the turbine blade and the turbine blade coupling slot to reduce the gap during operation.

The gap reducing member may be coupled to one of the turbine blade root portion and the turbine blade coupling slot and may be spaced apart from the other one of the turbine blade root portion and the turbine blade coupling slot.

During operation, the gap reducing member may be formed to expand toward the other of the turbine blade root portion and the turbine blade engagement slot.

A negative angular groove may be formed in one of the turbine blade root portion and the turbine blade engaging slot and the gap reducing member may be inserted in the negative angular groove.

The gap reducing member may be formed so as not to protrude from the negative angular groove.

The gap reducing member may be formed so as not to be stepped with the surface.

The gap reducing member may be formed of a material different from the material forming the root portion of the turbine blade and the material forming the turbine blade coupling slot.

The gap reducing member may be formed of a material forming the root of the turbine blade and a material having a thermal expansion coefficient higher than that of the material forming the turbine blade coupling slot.

The root portion of the turbine blade may be formed of a material having a thermal expansion coefficient higher than that of the material forming the turbine blade coupling slot.

The gap reducing member may be formed of a material having a thermal expansion coefficient higher than that of the material forming the turbine blade coupling slot.

The gap reducing member may be formed of a material having a thermal expansion coefficient smaller than that of the material forming the root portion of the turbine blade.

The gap reducing member may be formed of a material forming the root portion of the turbine blade and a material having a lower yield strength than a material forming the turbine blade coupling slot.

The root portion of the turbine blade may be formed of a material having a higher yield strength than a material forming the turbine blade coupling slot.

Wherein the turbine blade root portion and the turbine blade engagement slot are formed in the form of a fir or dovetail, the turbine blade root portion comprising: a turbine blade root inward surface facing the rotation axis of the rotor; And an outward surface of a turbine blade root that forms a back surface of the turbine blade root inward surface, the turbine blade engagement slot comprising: a turbine blade mating slot outward surface facing the turbine blade root portion inward surface; And a turbine blade engagement slot inward surface facing the turbine blade root portion outward surface, wherein the gap reduction member is fastened to either the turbine blade root inward surface and the turbine blade mating slot outward surface, And may be spaced apart from the other of the turbine blade root inward surface and the turbine blade mating slot outward surface.

Wherein the turbine blade root inward surface includes a turbine blade root basal surface formed at a distal end of the turbine blade root portion and the outward surface of the turbine blade engagement slot includes a turbine blade engaging slot base opposite the root of the turbine blade root Wherein the gap reducing member is secured to either the bottom of the root of the turbine blade and the bottom of the turbine blade mating slot and may be spaced apart from the other of the bottom of the root of the turbine blade and the base of the turbine blade mating slot. have.

The turbine blade root portion and the turbine blade coupling slot are formed in the form of a fir or a dovetail, and the root portion of the turbine blade is a turbine blade root portion disposed sequentially in the direction in which the turbine blade root portion is inserted into the turbine blade coupling slot. Wherein the turbine blade coupling slot includes one side of a turbine blade coupling slot that is opposite to one side of the turbine blade root portion and a side of the turbine blade root portion that is opposite to the center of the turbine blade root portion A turbine blade coupling slot center portion and a turbine blade coupling slot side portion opposed to a side portion of the turbine blade root portion, wherein the gap reducing member is formed of one of a turbine blade root portion side and a turbine blade coupling slot side portion A first gap reducing member fastened to one of the turbine blade root portion and the other of the one side of the turbine blade mating slot; And a second clearance reducing member fastened to one side of the root portion of the turbine blade and the other side of the turbine blade slot and spaced apart from the other side of the turbine blade root portion and the other side of the turbine blade slot; . ≪ / RTI >

A cooling fluid outlet for discharging a cooling fluid for cooling the turbine blade is formed at a central portion of the turbine blade engagement slot, and a cooling fluid inlet through which the cooling fluid discharged from the cooling fluid discharge port is formed is formed at the center of the turbine blade root portion .

The center portion of the root portion of the turbine blade may be recessed toward the centrifugal side of the rotor in the radial direction of the rotor than the one side portion of the root portion of the turbine blade and the other side portion of the root portion of the turbine blade.

And, the present invention provides a semiconductor device comprising: a housing; A rotor rotatably installed in the housing; A blade coupled to the rotor and rotated together with the rotor; And a gap reducing member for reducing a clearance between the rotor and the blade during operation.

And, the gas turbine includes a compressor for compressing air; A combustor for combusting the compressed air in the compressor to generate a combustion gas; And a turbine for obtaining a rotational force by using a combustion gas generated from the combustor, wherein the blade includes: a compressor blade included in the compressor; And a turbine blade included in the turbine, wherein the rotor includes: a compressor rotor disk coupled with the compressor blade; And a turbine rotor disk coupled with the turbine blade, wherein the gap reducing member may be formed in at least one of between the compressor blade and the compressor rotor disk, and between the turbine blade and the turbine rotor disk.

A gas turbine according to the present invention includes: a housing; A rotor rotatably installed in the housing; A compressor which receives rotational force from the rotor and compresses air; A combustor for combusting the compressed air in the compressor to generate a combustion gas; And a turbine that rotates the rotor by receiving a rotational force from the combustion gas generated from the combustor, wherein the turbine includes a turbine blade rotated together with the rotor, and the turbine blade includes a turbine blade root Wherein the rotor includes a turbine blade engagement slot into which the turbine blade root portion is inserted and the turbine blade engagement slot is formed to be larger than the turbine blade root portion so that a gap between the root portion of the turbine blade and the turbine blade engagement slot A gap reducing member may be interposed between the root portion of the turbine blade and the turbine blade coupling slot to reduce the gap during operation. This not only facilitates fastening between the turbine blades and the turbine rotor disk but also prevents the cooling fluid discharged from the turbine rotor disk from leaking through the gap for cooling the turbine blades.

1 is a cross-sectional view of a gas turbine according to an embodiment of the present invention,
FIG. 2 is an exploded perspective view showing a turbine rotor disk, a turbine blade and a gap reducing member in the gas turbine of FIG. 1;
3 is a cross-sectional view of the turbine rotor disk, turbine blade and gap reduction member of FIG.
FIG. 4 is a sectional view showing a state where the gap reducing member of FIG.
FIG. 5 is a cross-sectional view of the turbine rotor disk, the turbine blade, and the gap reducing member of FIG. 2 taken along line BB in the assembled state,
6 is a sectional view showing a state in which the gap reducing member of Fig.

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

1 is an exploded perspective view showing a turbine rotor disk, a turbine blade and a gap reducing member in the gas turbine of FIG. 1, FIG. 3 is an exploded perspective view of the gas turbine of FIG. FIG. 4 is a sectional view showing a state in which the gap reducing member of FIG. 3 is reduced in operation, and FIG. 5 is a cross-sectional view of the gap reducing member of FIG. FIG. 6 is a cross-sectional view illustrating a state where the gap reducing member of FIG. 5 is reduced in operation during the operation of the turbine rotor disk, the turbine blade, and the gap reducing member of FIG. 2 .

Referring to FIG. 1, a gas turbine according to an embodiment of the present invention includes a housing 100, a rotor 600 rotatably installed in the housing 100, A combustor 400 which mixes and ignites the fuel in the air compressed by the compressor 200 to generate a combustion gas, a combustor 400 for combusting the combusted gas, A turbine 500 for rotating the rotor 600 with a rotational force from a combustion gas generated from the turbine 500, a generator interlocked with the rotor 600 for generating electricity, and a diffuser . ≪ / RTI >

The housing 100 includes a compressor housing 110 in which the compressor 200 is accommodated, a combustor housing 120 in which the combustor 400 is accommodated, and a turbine housing 130 in which the turbine 500 is accommodated can do.

Here, the compressor housing 110, the combustor housing 120, and the turbine housing 130 may be sequentially arranged from the upstream side to the downstream side in the fluid flow direction.

The rotor 600 includes a compressor rotor disk 610 housed in the compressor housing 110, a turbine rotor disk 630 housed in the turbine housing 130, and a turbine rotor disk 630 housed in the combustor housing 120, A torque tube 620 connecting the rotor disk 610 and the turbine rotor disk 630, a tie rod 610 for fastening the compressor rotor disk 610, the torque tube 620 and the turbine rotor disk 630 640 and a locking nut 650. [

The plurality of compressor rotor discs 610 may be arranged along the axial direction of the rotor 600. That is, the compressor rotor disk 610 may be formed in multiple stages.

Each of the compressor rotor discs 610 is formed in a substantially disc shape, and a compressor blade coupling slot 612, which is coupled to the compressor blade 210 to be described later, may be formed at the outer periphery thereof, as shown in FIG.

The compressor blade mating slot 612 is formed in a fir-tree shape (not shown) so as to prevent the compressor blade 210, which will be described later, from being detached from the compressor blade mating slot 612 in the radial direction of rotation of the rotor 600. [ As shown in FIG.

Here, the compressor rotor disk 610 and the compressor blade 210 to be described later are typically combined in a tangential type or an axial type. In this embodiment, the compressor rotor disk 610 and the compressor blade 210 are formed to be coupled in an axial type. The plurality of compressor blade engagement slots 612 may be radially arranged along the circumferential direction of the compressor rotor disk 610, have.

The turbine rotor disk 630 may be formed similarly to the compressor rotor disk 610. That is, a plurality of the turbine rotor discs 630 may be formed, and a plurality of the turbine rotor discs 630 may be arranged along the axial direction of the rotor 600. That is, the turbine rotor disk 630 may be formed in multiple stages.

Each of the turbine rotor discs 630 is formed in a substantially disc shape, and a turbine blade coupling slot 632, which is coupled to a turbine blade 510 to be described later, may be formed at an outer circumferential portion thereof, as shown in FIG.

The turbine blade engagement slot 632 may be formed in a fir form so as to prevent the turbine blade 510, which will be described later, from being detached from the turbine blade engagement slot 632 in the radial direction of rotation of the rotor 600 .

Here, the turbine rotor disk 630 and a turbine blade 510 to be described later are typically coupled in a tangential type or an axial type. In this embodiment, the turbine rotor disk 630 and the turbine blade 510 are formed to be coupled in an axial type. The plurality of turbine blade coupling slots 632 may be radially arranged along the circumferential direction of the turbine rotor disk 630. The plurality of turbine blade coupling slots 632 may be radially arranged along the circumferential direction of the turbine rotor disk 630 have.

The torque tube 620 is a torque transmitting member that transmits the rotational force of the turbine rotor disk 630 to the compressor rotor disk 610. The torque tube 620 includes one end of the torque tube 620 and the other end of the plurality of compressor rotor disks 610, Can be fastened to the turbine rotor disk 630 fastened to the compressor rotor disk 610 located at the downstream end and positioned at the most upstream end of the plurality of turbine rotor disks 630 in the flow direction of the combustion gas . Each of the torque tube 620 and the turbine rotor disk 630 has a protrusion formed on one end and the other end of the torque tube 620. Grooves for engaging the protrusions are formed on the compressor rotor disk 610 and the turbine rotor disk 630, Relative rotation of the compressor rotor disk 620 with respect to the compressor rotor disk 610 and the turbine rotor disk 630 can be prevented.

The torque tube 620 may be formed in the shape of a hollow cylinder so that the air supplied from the compressor 200 flows through the torque tube 620 and flows into the turbine 500.

In addition, the torque tube 620 is formed strong against deformation and distortion due to characteristics of a gas turbine that is continuously operated for a long period of time, and can be easily assembled and disassembled for easy maintenance.

The tie rod 640 is formed to penetrate a plurality of the compressor rotor discs 610, the torque tube 620 and a plurality of the turbine rotor discs 630. One end of the tie rod 640 is connected to a plurality of the compressor rotor discs 610, A turbine rotor disk (610) fastened in a compressor rotor disk (610) located at the most upstream end in the flow direction of the air and the other end being located at the most downstream end of the plurality of turbine rotor disks (630) 630 to the opposite side of the compressor 200 and may be fastened to the fixing nut 650.

The fixing nut 650 presses the turbine rotor disk 630 positioned at the most downstream end of the compressor toward the compressor 200 and rotates the compressor rotor disk 610 located at the most upstream end A plurality of the compressor rotor discs 610, the torque tube 620 and a plurality of the turbine rotor discs 630 are arranged in the axial direction of the rotor 600 as the spacing between the turbine rotor discs 630 is reduced, Lt; / RTI > Accordingly, axial movement and relative rotation of the plurality of compressor rotor discs 610, the torque tube 620, and the plurality of turbine rotor discs 630 can be prevented.

Meanwhile, in the present embodiment, one tie rod 640 is formed to pass through the center portions of the plurality of compressor rotor discs 610, the torque tube 620, and the plurality of turbine rotor discs 630, But is not limited thereto. That is, a separate tie rod 640 may be provided on the side of the compressor 200 and the side of the turbine 500, or a plurality of tie rods 640 may be radially arranged along the circumferential direction, It is also possible.

Both ends of the rotor 600 are rotatably supported by bearings, and one end of the rotor 600 can be connected to the drive shaft of the generator.

The compressor 200 includes a compressor blade 210 rotated together with the rotor 600 and a compressor vane 220 fixed to the housing 100 to align the flow of air flowing into the compressor blade 210. [ ).

The plurality of compressor blades (210) are formed in a plurality of stages along the axial direction of the rotor (600), and the plurality of compressor blades (210) And may be formed radially along the rotation direction of the rotor 600.

2, each of the compressor blades 210 includes a plate-shaped compressor blade platform portion, a compressor blade root portion extending from the compressor blade platform portion toward the radially inner side in the radial direction of rotation of the rotor 600 214 and a portion of the compressor blade airfoil extending from the compressor blade platform portion toward the centrifugal side in the radial direction of rotation of the rotor 600. [

The compressor blade platform portion may contact the neighboring compressor blade platform portion and may maintain a gap between the compressor blade airfoil portions.

The compressor blade root portion 214 may be formed in a so-called axial type in which the compressor blade root portion 214 is inserted into the compressor blade coupling slot 612 along the axial direction of the rotor 600 as described above.

The compressor blade root portion 214 may be formed in a fir shape corresponding to the compressor blade coupling slot 612.

In this embodiment, the compressor blade root 214 and the compressor blade coupling slot 612 are formed in the form of a fir tree, but the present invention is not limited thereto and may be formed in a dovetail shape or the like. Alternatively, the compressor blades 210 may be fastened to the compressor rotor disk 610 using fasteners such as keys or bolts, other than the above.

The compressor blade root portion 214 and the compressor blade mating slot 612 are configured such that the compressor blade root portion 214 and the compressor blade mating slot 612 can be easily coupled to each other, A gap between the compressor blade root portion 214 and the compressor blade coupling slot 612 is formed to be larger than the compressor blade root portion 214 of the compressor 200, (Gc)) may be formed.

The compressor blade root portion 214 and the compressor blade coupling slot 612 are fixed by separate pins so that the compressor blade root portion 214 is connected to the compressor blade coupling slot 612, Can be prevented from being displaced in the axial direction of the rotor (600).

The compressor blade airfoil portion is formed to have an airfoil optimized in accordance with the gas turbine specification and is located on the upstream side in the flow direction of the air and is positioned on the downstream side in the flow direction of the air and the leading edge, And a trailing edge through which air is emitted.

The plurality of compressor vanes 220 may be formed in a plurality of stages along the axial direction of the rotor 600. Here, the compressor vane 220 and the compressor blade 210 may be alternately arranged along the air flow direction.

The plurality of compressor vanes 220 may be radially formed along the rotating direction of the rotor 600 at each stage.

Each of the compressor vanes 220 includes a compressor vane platform portion formed in an annular shape along the rotating direction of the rotor 600 and a compressor vane platform portion extending from the compressor vane platform portion in a radial direction of the rotor 600, Can include a can part.

The compressor vane platform portion includes a root-side compressor vane platform portion formed at a boom portion of the compressor vane airfoil portion and fastened to the compressor housing 110, and a rotor-side compressor vane platform portion formed at an end portion of the compressor vane airfoil portion, And a tip-side compressor vane platform portion opposite to the tip-side compressor vane platform portion.

Here, the compressor vane platform unit according to the present embodiment supports not only the boom rope portion of the compressor vane airfoil but also the end portion of the compressor vane airfoil to support the compressor vane airfoil portion more stably, And a tip-side compressor vane platform portion. That is, the compressor vane platform portion may include the root side compressor vane platform portion and may be formed so as to support only the tip portion of the compressor vane airfoil portion.

The compressor vane airfoil portion is formed to have an airfoil optimized in accordance with the gas turbine specification and is located on the upstream side in the air flow direction and positioned on the downstream side in the flow direction of the air and the leading edge on which air is incident, Lt; RTI ID = 0.0 > trailing < / RTI >

The combustor 400 mixes and combusts the air introduced from the compressor 200 with fuel to produce a high-temperature high-pressure high-pressure combustion gas. The combustor 400 and the turbine 500 withstand the high- It is possible to increase the combustion gas temperature up to the heat resistance limit.

The plurality of combustors 400 may be arranged along the rotational direction of the rotor 600 in the combustor housing 120. The plurality of combustors 400 may be disposed along the rotational direction of the rotor 600. [

Each combustor 400 includes a liner into which air compressed by the compressor 200 flows, a burner that injects and burns fuel into the air flowing into the liner, and a combustion gas generated in the burner, ) Of the transition piece.

The liner may include a flame tube that forms a combustion chamber, and a flow sleeve that surrounds the flame tube and forms an annular space.

The burner includes a fuel injection nozzle formed at a front end side of the liner so as to inject fuel into the air introduced into the combustion chamber and an ignition plug formed in a wall portion of the liner so that fuel and air mixed in the combustion chamber are ignited .

The transition piece may be formed so that the outer wall of the transition piece is cooled by the air supplied from the compressor 200 so that the transition piece is not damaged by the high temperature of the combustion gas.

That is, the transition piece may have a cooling hole for injecting air into the interior thereof, and air may cool the body inside the cooling hole.

On the other hand, the air cooled by the transition piece flows into the annular space of the liner, and air is supplied to the outer wall of the liner from the outside of the flow sleeve through the cooling holes provided in the flow sleeve, have.

Although not shown in the drawing, a deswooler is provided between the compressor 200 and the combustor 400 to adjust the flow angle of the air flowing into the combustor 400 to a designed flow angle. .

The turbine 500 may be formed similarly to the compressor 200.

That is, the turbine 500 includes a turbine blade 510 rotated together with the rotor 600, and a turbine vane 500 fixed to the housing 100 to align the flow of air flowing into the turbine blade 510. (520).

The plurality of turbine blades 510 are formed in a plurality of stages along the axial direction of the rotor 600 and the plurality of the turbine blades 510 are formed in a plurality of stages, And may be formed radially along the rotation direction of the rotor 600.

2, each of the turbine blades 510 includes a plate-shaped turbine blade platform portion, a turbine blade root portion extending from the turbine blade platform portion to the radially inner side in the radial direction of rotation of the rotor 600 514) and a turbine blade airfoil portion extending from the turbine blade platform portion to the centrifugal side in the radial direction of rotation of the rotor (600).

The turbine blade platform portion may contact the neighboring turbine blade platform portion and may maintain a gap between the turbine blade airfoil portions.

The turbine blade root portion 514 may be formed in a so-called axial type in which the turbine blade root portion 514 is inserted into the turbine blade coupling slot 632 along the axial direction of the rotor 600 as described above.

The root portion 514 of the turbine blade may be formed in the shape of a fir to correspond to the turbine blade coupling slot 632.

Here, in the present embodiment, the turbine blade root 514 and the turbine blade coupling slot 632 are formed in the form of a fir tree, but the present invention is not limited thereto and may be formed in a dovetail shape or the like. Alternatively, the turbine blades 510 may be fastened to the turbine rotor disk 630 using fasteners such as keys or bolts other than those described above.

3, the turbine blade root portion 514 and the turbine blade coupling slot 632 are formed in a manner such that the turbine blade root portion 514 and the turbine blade coupling slot 632 can be easily fastened, The turbine blade coupling slot 632 is formed to be larger than the turbine blade root portion 514 and the gap between the turbine blade root portion 514 and the turbine blade coupling slot 632 in the engaged state (Hereinafter, a turbine side clearance) Gt may be formed.

The root portion 514 of the turbine blade and the coupling slot 632 of the turbine blade are fixed by separate pins so that the root portion 514 of the turbine blade is inserted into the turbine blade coupling slot 632, Can be prevented from being displaced in the axial direction of the rotor (600).

The turbine blade airfoil portion is formed to have an airfoil optimized in accordance with the gas turbine specification and is positioned on the upstream side in the flow direction of the combustion gas and positioned on the downstream side in the flow direction of the combustion gas and the leading edge on which the combustion gas is incident And may include a trailing edge from which combustion gases are emitted.

A plurality of the turbine vanes 520 may be formed and a plurality of the turbine vanes 520 may be formed in a plurality of stages along the axial direction of the rotor 600. The turbine vanes 520 and the turbine blades 510 may be alternately arranged along the air flow direction.

The plurality of turbine vanes 520 may be radially formed at each stage along the rotational direction of the rotor 600.

Each of the turbine vanes 520 includes a turbine vane platform portion formed in an annular shape along the rotating direction of the rotor 600 and a turbine vane air portion extending from the turbine vane platform portion in the radial direction of rotation of the rotor 600. [ Can include a can part.

The turbine vane platform part includes a root side turbine vane platform part formed at a tip of the turbine vane airfoil part and fastened to the turbine housing part 130 and a rotor 600 formed at an end portion of the turbine vane airfoil part, Side turbine vane platform portion opposed to the turbine vane platform portion.

Here, the turbine vane platform unit according to the present embodiment supports not only the tip of the turbine vane airfoil but also the tip end of the turbine vane airfoil to support the turbine vane airfoil portion more stably, And a tip-side turbine vane platform portion. That is, the turbine vane platform portion may include the root side turbine vane platform portion and may be formed so as to support only the tip portion of the turbine vane airfoil portion.

The turbine vane airfoil portion is formed to have an airfoil optimized in accordance with the gas turbine specification and is located on the upstream side in the flow direction of the combustion gas and on the downstream side in the flow direction of the combustion gas and the leading edge on which the combustion gas is incident And may include a trailing edge from which combustion gases are emitted.

Unlike the compressor 200, the turbine 500 is in contact with a high-temperature and high-pressure combustion gas, and thus requires a cooling means for preventing damage such as deterioration.

Accordingly, the gas turbine according to the present embodiment further includes a cooling channel 710 for adding air compressed at a portion of the compressor 200 (hereinafter referred to as cooling fluid) to the turbine 500 .

The cooling passage 710 may extend from the outside of the housing 100 (an external passage), extend through the interior of the rotor 600 (an internal passage), use both an external passage and an internal passage The cooling passage 710 extends through the inside of the rotor 600 according to the present embodiment.

The cooling passage 710 communicates with the turbine blade cooling passage 720 formed in the turbine blade 510 so that the turbine blade 510 can be cooled by the cooling fluid. The outlet of the cooling passage 710 may be formed in the turbine blade coupling slot 632 and the inlet of the turbine blade cooling passage 720 may be formed in the turbine blade root portion 514.

The turbine blade cooling channel 720 is communicated with a turbine blade film cooling hole formed on a surface of the turbine blade 510 so that cooling fluid is supplied to the surface of the turbine blade 510, 510 may be so-called film cooling by the cooling air.

In addition, the turbine vane 520 may be formed to be cooled by receiving a cooling fluid from the cooling channel 710 similarly to the turbine blade 510.

Meanwhile, the turbine 500 needs a clearance space between the end of the turbine blade 510 and the inner circumferential surface of the turbine housing 130 so that the turbine blade 510 can rotate smoothly.

However, the larger the spacing space is, the more advantageous in terms of prevention of interference between the turbine blades 510 and the turbine housing 130, but disadvantageous in terms of leakage of the combustion gas, and vice versa. That is, the flow of the combustion gas injected from the combustor 400 is divided into a main flow passing through the turbine blades 510 and a leakage flow passing through a space between the turbine blades 510 and the turbine housing 130 The leakage flow is increased and the gas turbine efficiency is lowered. However, interference between the turbine blade 510 and the turbine housing 130 due to thermal deformation or the like and damage due to thermal deformation are prevented . On the other hand, as the spacing distance is narrowed, the leakage flow is reduced to improve the gas turbine efficiency, but interference between the turbine blades 510 and the turbine housing 130 due to thermal deformation or the like may be caused, .

Accordingly, the gas turbine according to the present embodiment can prevent the interference between the turbine blades 510 and the turbine housing 130 and damage therefrom, while securing an appropriate space for minimizing the deterioration of the gas turbine efficiency. And may further include sealing means.

The sealing means may include a shroud located at a tip of the turbine blade 510, a labyrinthine chamber protruding from the shroud to a centrifugal side in the radial direction of rotation of the rotor 600, and an inner circumferential surface of the turbine housing 130 Honeycomb seal may be included.

The sealing means according to this configuration is provided with an adequate space between the labyrinth seal chamber and the honeycomb seal chamber so as to minimize deterioration of the gas turbine efficiency due to leakage of the combustion gas, It is possible to prevent direct contact between the honeycomb seals and damage caused thereby.

In addition, the turbine 500 may further include sealing means for blocking leakage between the turbine vane 520 and the rotor 600. In addition to the above-described labyrinth, Can be utilized.

In the gas turbine according to this configuration, the air introduced into the housing 100 is compressed by the compressor 200, and the air compressed by the compressor 200 is mixed with the fuel by the combustor 400 The combustion gas generated in the combustor 400 flows into the turbine 500 and the combustion gas introduced into the turbine 500 flows through the turbine blades 510 600, and then discharged to the atmosphere through the diffuser. The rotor 600, which is rotated by the combustion gas, can drive the compressor 200 and the generator. That is, some of the mechanical energy obtained from the turbine 500 may be supplied to the compressor 200 as energy required to compress the air, and the remainder may be used to produce power to the generator.

Meanwhile, as described above, the turbine side clearance Gt is formed for easy assembly and disassembly between the turbine blade root portion 514 and the turbine blade engaging slot 632, but the turbine side clearance Gt So that the cooling efficiency may be deteriorated. That is, a part of the cooling fluid discharged from the discharge port of the cooling channel 710 flows into the turbine blade cooling channel 720, but a part of the cooling fluid discharged from the discharge port of the cooling channel 710 flows into the turbine- (Gt) to the space through which the combustion gas passes.

In consideration of this, the gas turbine according to the present embodiment includes the gap reducing member 800 that secures the turbine side gap Gt during assembly and reduces the turbine side gap Gt during operation, The cooling fluid discharged from the cooling channel 710 is supplied to the turbine blade slot 532 while maintaining the turbine side gap Gt to facilitate assembling and disassembly between the turbine blade root slot 514 and the turbine blade slot 632, Leakage through the side clearance Gt can be prevented.

2 to 6, the gap reducing member 800 is basically fastened (at the time of assembly and disassembly) to the turbine blade root portion 514, and the turbine blade engagement slot 632 is spaced apart . Accordingly, the gap reducing member 800 is interposed between the turbine blade root portion 514 and the turbine blade coupling slot 632, and the gap reducing member 800 prevents the turbine side gap Gt It is possible to prevent the assembly and disassembly between the turbine blade root portion 514 and the turbine blade coupling slot 632 from becoming difficult. That is, the gap reducing member 800 may secure the turbine side gap Gt during assembly and still facilitate assembly and disassembly between the turbine blade root portion 514 and the turbine blade mating slot 632 have.

Herein, in the turbine blade root portion 514, a negative angular groove F is formed from the surface of the turbine blade root portion 514, and the gap reducing member 800 is inserted into the negative angular groove F . The gap reducing member 800 may be formed so as not to protrude from the negative angular groove F. [ That is, the gap reducing member 800 may be formed not to be stepped with the surface of the turbine blade root portion 514. Accordingly, even if the gap reducing member 800 is provided, the gap Gt on the turbine side is secured to the same level as the case where the gap reducing member 800 is not provided, and the turbine blade root portion 514 The gap reduction member 800 is prevented from being caught in the turbine blade engagement slot 632 when inserted into the turbine blade engagement slot 632 so that the turbine blade root portion 514 and the turbine blade engagement slot 632 Assembly and disassembly can be made easier.

The gap reducing member 800 is formed of a material having a thermal expansion coefficient higher than that of the material forming the turbine blade root portion 514 and the material forming the turbine blade coupling slot 632, And can be expanded toward the coupling slot 632 side to reduce the turbine side gap Gt.

Here, when the gap reducing member 800 is thermally expanded, the gap reducing member 800 is still spaced from the turbine blade coupling slot 632 so that the turbine side gap Gt may be small, but may still exist, The gap reducing member 800 contacts the turbine blade engagement slot 632 so that the turbine side clearance Gt is temporarily but may disappear. However, when the gap reducing member 800 contacts the turbine blade engaging slot 632, the turbine blade root portion 514 and the turbine blade engaging slot 632 may be damaged. That is, when the gap reducing member 800 is further heated in a state where additional thermal expansion between the turbine blade root portion 514 and the turbine blade coupling slot 632 is limited, And the turbine blade coupling slot 632 is pressed by the blade root portion 514 and the contact portion between the gap reducing member 800 and the turbine blade root portion 514, Damage may occur at the contact area between the coupling slots 632. In order to prevent this, the gap reducing member 800 may be formed of a material having a lower yield strength than a material forming the turbine blade root portion 514 and a material forming the turbine blade coupling slot 632. Since the turbine blade 510 requires more severe requirements than the turbine rotor disk 630, the turbine blade root portion 514 has a higher yield strength than the material forming the turbine blade coupling slot 632 And may be formed of a material.

In the meantime, as described above, the turbine blade root portion 514 and the turbine blade coupling slot 632 may be formed in the form of a fir tree or a dovetail. In this case, the gap reducing member 800 may be an effective cooling fluid leakage prevention The stress concentration, the cost, and the like, it may be formed only in a part of the region between the turbine blade root portion 514 and the turbine blade coupling slot 632.

When the turbine blade root portion 514 and the turbine blade coupling slot 632 are formed in a fir shape or a dovetail shape, the turbine blade root portion 514 is opposed to the rotation axis of the rotor 600 And a turbine blade root engaging slot (632) formed on the outer circumferential surface of the turbine blade root engaging slot (632), the turbine blade root engaging slot (632) A turbine blade engagement slot outboard surface 632c that is opposed to the secondary inward surface 514a and a turbine blade engagement slot inward surface 632a that is opposite the turbine blade root outboard surface 514c.

However, the turbine blade root inward surface 514a and the turbine blade mating slot outward surface 632c are spaced from each other during operation, but the turbine blade root outward surface 514c and the turbine blade mating slot inward surface 632a May be in contact with each other during operation.

Thus, cooling fluid leakage may occur between the turbine blade root portion inward surface 514a and the turbine blade mating slot outward surface 632c while the turbine blade root portion outward surface 514c and the turbine blade engagement surface The gap reducing member 800 is formed between the turbine blade root portion inward surface 514a and the turbine blade mating slot outward surface 632c since cooling fluid leakage does not occur between the slot inward surface 632a , The gap reducing member 800 may not be formed between the turbine blade root portion outward surface 514c and the turbine blade coupling slot inward surface 632a.

Here, the outward surface 514c of the turbine blade root portion and the inward surface 632a of the turbine blade coupling slot are regions where stress is concentrated during operation, and the outward surface 514c of the turbine blade root portion, It may be preferable from the viewpoint of durability that the gap reducing member 800 is not formed between the surfaces 632a.

When the clearance reducing member 800 is formed only between the turbine blade root portion inward surface 514a and the turbine blade engaging slot outward surface 632c, the turbine blade root portion outward surface 514c and The gap reducing member 800 and the negative angular groove F can be less formed between the turbine blade coupling slot inward surface 632a and the gap reducing member 800 than in the case where the gap reducing member 800 is formed, Can be saved.

The turbine blade root portion inward surface 514a includes a root portion root 514b of the turbine blade root formed at the tip of the turbine blade root portion 514, Includes a turbine blade mating slot base surface 632b opposite the turbine blade root base surface 514b wherein cooling fluid leakage occurs primarily between the turbine blade root base surface 514b and the turbine blade mating slot base surface 632b Since the gap reducing member 800 is formed only between the turbine blade root base bottom surface 514b and the turbine blade slot base surface 632b, the cooling fluid leakage can be more effectively prevented while further reducing the manufacturing cost Lt; / RTI >

When the root portion 514 of the turbine blade and the slot 632 of the turbine blade are formed in the form of a fir or a dovetail, the root portion 514 of the turbine blade has a root portion 514 of the turbine blade, A turbine blade root portion central portion 514C and a turbine blade root portion other side portion 514B disposed in the turbine blade root portion side portion 514A, the turbine blade root portion central portion 514C and the turbine blade root portion side portion 514B, The coupling slot 632 includes a side portion 632A of the turbine blade coupling slot which is opposite to the side portion 514A of the turbine blade root portion, a turbine blade coupling slot central portion 632C opposed to the turbine blade root portion central portion 514C, And a turbine blade coupling slotted side portion 632B opposed to the other side portion 514B of the turbine blade root portion, Since the discharge port of the cooling passage 710 is formed in the upper portion 632C and the inlet of the turbine blade cooling passage 720 is formed in the middle portion 514C of the root portion of the turbine blade, And between the turbine blade root portion one side portion 514A and the turbine blade coupling slot side portion 632A and between the turbine blade root portion other side portion 514B and the turbine blade coupling slot side portion 632B, It is possible to more effectively prevent leakage of the cooling fluid. That is, as in the present embodiment, the gap reducing member 800 includes a first gap reducing member 810 interposed between the one side portion 514A of the turbine blade root portion and the one side portion 632A of the turbine blade coupling slot, And a second gap reducing member 820 interposed between the other side 514B of the turbine blade root portion and the other side portion 632B of the turbine blade slot. Since the leakage of the cooling fluid is prevented by the first gap reducing member 810 and the second gap reducing member 820, the weight of the turbine blade root portion central portion 514C is reduced to the weight of the turbine blade root portion It is not necessary to worry about the leakage of the cooling fluid even if it is formed to be closer to the centrifugal side in the radial direction of rotation of the rotor 600 than the one side portion 514A and the side portion 514B of the turbine blade root portion.

In the present embodiment, the negative angular groove F is formed in the turbine blade root portion 514 and the gap reducing member 800 is formed in the negative angular groove formed in the turbine blade root portion 514 F, and the gap reducing member 800 is formed so as to be spaced apart from the turbine blade coupling slot 632. However, the present invention is not limited to this, but a negative angular groove F may be formed in the turbine blade engaging slot 632, and the gap reducing member 800 may be formed in the negative angular groove formed in the turbine blade engaging slot 632 F, and the gap reducing member 800 may be formed so as to be spaced apart from the turbine blade root portion 514.

Meanwhile, in the present embodiment, the gap reducing member 800 is formed of a material forming the turbine blade root portion 514 and a material having a thermal expansion coefficient larger than that of the material forming the turbine blade coupling slot 632. However, the present invention is not limited thereto. That is, the root portion 514 of the turbine blade is formed of a material having a thermal expansion coefficient higher than that of the material forming the turbine blade coupling slot 632, so that the turbine side gap Gt The gap reducing member 800 may be formed of a material having a coefficient of thermal expansion larger than that of the material forming the turbine blade coupling slot 632 and a thermal expansion coefficient smaller than that of the material forming the turbine blade root portion 514 The gap Gt on the turbine side can be reduced during operation.

Meanwhile, in the case of this embodiment, the gap reducing member 800 is formed on the turbine 500 side. However, the present invention is not limited thereto, and the gap reducing member 800 may be formed on the compressor 200 side. That is, the gap reducing member 800 may be formed between the compressor blade root portion 214 and the compressor blade mating slot 612.

100: Housing
200: compressor
210: compressor blade
214: compressor blade root portion
400: Combustor
500: Turbine
510: turbine blade
514: Turbine blade root portion
514a: turbine blade root inward surface
514b: turbine blade roots base plane
514c: turbine blade root portion outward surface
514A: turbine blade root part one side
514B: turbine blade roots other side
514C: turbine blade root center portion
600: Rotor
610: Compressor rotor disk
612: Compressor blade coupling slot
630: Turbine rotor disk
632: Turbine blade coupling slot
632a: turbine blade coupling slot inward surface
632b: Turbine blade coupling slot base
632c: turbine blade coupling slot outward surface
632A: turbine blade coupling slot side
632B: turbine blade coupling slot other side
632C: turbine blade coupling slot center portion
800: gap reduction member
810: first gap reducing member
820: second gap reducing member

Claims (20)

A housing (100);
A rotor 600 rotatably installed in the housing 100;
A compressor (200) that receives rotational force from the rotor (600) and compresses air;
A combustor 400 that mixes and ignites the fuel in the air compressed by the compressor 200 to generate a combustion gas; And
And a turbine (500) for rotating the rotor (600) by receiving a rotational force from the combustion gas generated from the combustor (400)
The turbine 500 includes a turbine blade 510 rotated together with the rotor 600,
The turbine blade 510 includes a turbine blade root portion 514 extending toward the rotor 600. The rotor 600 includes a turbine blade coupling slot 632 into which the turbine blade root portion 514 is inserted, / RTI >
The turbine blade coupling slot 632 is formed larger than the turbine blade root portion 514 so that a gap Gt is formed between the turbine blade root portion 514 and the turbine blade coupling slot 632,
A gap reducing member 800 for reducing the gap Gt during operation is interposed between the turbine blade root portion 514 and the turbine blade coupling slot 632,
The turbine blade root portion 514 and the turbine blade coupling slot 632 are formed in a fir shape or a dovetail shape,
The turbine blade root portion 514 includes a turbine blade root portion inward surface 514a opposite the rotational axis of the rotor 600; And a turbine blade root outward surface (514c) forming a back surface of the turbine blade root portion inward surface (514a)
The turbine blade mating slot 632 includes a turbine blade mating slot outward surface 632c facing the turbine blade root portion inward surface 514a; And a turbine blade engagement slot inward surface (632a) facing the turbine blade root portion outward surface (514c)
The gap reducing member 800 is fastened to either the turbine blade root inward surface 514a and the turbine blade mating slot outward surface 632c and has a turbine blade root inward surface 514a, And is formed spaced apart from the other of the blade engagement slot outward surfaces (632c). delete The method according to claim 1,
During operation, the gap reducing member (800) expands toward the other of the turbine blade root portion (514) and the turbine blade mating slot (632). The method according to claim 1,
Grooved grooves F are formed in one of the turbine blade root portion 514 and the turbine blade coupling slot 632 from one surface thereof,
The gap reducing member (800) is inserted into the negative angular groove (F). 5. The method of claim 4,
Wherein the gap reducing member (800) is formed so as not to protrude from the negative angular groove (F). 6. The method of claim 5,
The gap reducing member (800) is formed so as not to be stepped with the surface. The method according to claim 1,
Wherein the gap reducing member (800) is formed of a material forming the turbine blade root portion (514) and a material different from the material forming the turbine blade coupling slot (632). 8. The method of claim 7,
Wherein the gap reducing member 800 is formed of a material forming the turbine blade root portion 514 and a material having a thermal expansion coefficient higher than that of the material forming the turbine blade coupling slot 632. [ 9. The method of claim 8,
Wherein the turbine blade root portion (514) is formed of a material having a thermal expansion coefficient higher than that of the material forming the turbine blade coupling slot (632). 8. The method of claim 7,
Wherein the gap reducing member (800) is formed of a material having a thermal expansion coefficient higher than that of the material forming the turbine blade coupling slot (632). 11. The method of claim 10,
Wherein the gap reducing member (800) is formed of a material having a thermal expansion coefficient smaller than that of the material forming the turbine blade root (514). 8. The method of claim 7,
Wherein the gap reducing member (800) is formed of a material forming the turbine blade root portion (514) and a material having a lower yield strength than a material forming the turbine blade coupling slot (632). 13. The method of claim 12,
Wherein the turbine blade root portion (514) is formed of a material having a higher yield strength than a material forming the turbine blade coupling slot (632). delete The method according to claim 1,
The turbine blade root portion inward surface 514a includes a turbine blade root portion base 514b formed at the tip of the turbine blade root portion 514,
The turbine blade engagement slot outward surface 632c includes a turbine blade engagement slot base surface 632b opposite the turbine blade root portion base surface 514b,
The gap reducing member 800 is coupled to one of the turbine blade root base bottom surface 514b and the turbine blade coupling slot base surface 632b and is configured to receive the turbine blade root base surface 514b and the turbine blade engagement slot A gas turbine configured to be spaced apart from the other of the bases (632b). The method according to claim 1,
The turbine blade root portion 514 includes a turbine blade root portion one side portion 514A disposed sequentially in the direction in which the turbine blade root portion 514 is inserted into the turbine blade engagement slot 632, (514C) and a turbine blade root portion (514B)
The turbine blade engagement slot 632 includes a side portion 632A of the turbine blade engagement slot which is opposed to the turbine blade root portion side portion 514A and a turbine blade engagement slot center portion And a turbine blade coupling slotted side portion 632B opposed to the other side portion 514B of the turbine blade root portion,
The gap reducing member (800)
The turbine blades are fixed to one side of the root portion 514A of the turbine blade and the one side portion 632A of the turbine blade slot and the one side portion 514A of the turbine blade root portion and the side portion 632A of the turbine blade coupling slot A first gap reducing member (810) spaced apart from the other; And
The turbine blade root portion 514B and the turbine blade coupling slot side portion 632B are coupled to any one of the turbine blade root portion 514B and the turbine blade slotted side portion 632B, And a second gap reducing member (820) spaced apart from the other. 17. The method of claim 16,
A cooling fluid discharge port through which the cooling fluid for cooling the turbine blade 510 is discharged is formed in the center portion 632C of the turbine blade coupling slot,
And a cooling fluid inlet through which the cooling fluid discharged from the cooling fluid discharge port flows is formed in the center portion 514C of the turbine blade root portion. 17. The method of claim 16,
The center portion 514C of the turbine blade root portion 514C is formed to be closer to the centrifugal side of the rotor 600 than the one side portion 514A of the turbine blade root portion and the side portion 514B of the turbine blade root portion, . A housing (100);
A rotor 600 rotatably installed in the housing 100;
Blades (210, 510) fastened to the rotor (600) and rotated together with the rotor (600); And
And a gap reducing member (800) for reducing gaps (Gc, Gt) between the rotor (600) and the blades (210, 510) during operation,
The blades 210 and 510 include blade root portions 214 and 514 extending toward the rotor 600. The rotor 600 includes a blade coupling slot in which the blade root portions 214 and 514 are inserted 612 and 632,
The blade root portions 214 and 514 and the blade coupling slots 612 and 632 are formed in a fir shape or a dovetail shape,
The blade root portions (214, 514) include a blade root inward surface facing the rotational axis of the rotor (600); And a blade root portion outward facing surface forming a back surface of the blade root portion inward surface,
The blade engaging slots (612, 632) include: a blade engaging slot outward surface facing the blade root inward surface; And a blade engagement slot inward surface facing the blade root portion outward surface,
The gap reducing member 800 is coupled to one of the blade root inward surface and the blade mating slot outward surface and is spaced apart from the other of the blade root inward surface and the blade mating slot outward surface Gas turbine. 20. The method of claim 19,
A compressor (200) for compressing air;
A combustor 400 that mixes and ignites the fuel in the air compressed by the compressor 200 to generate a combustion gas; And
And a turbine (500) for obtaining a rotational force by using the combustion gas generated from the combustor (400)
The blades (210, 510)
A compressor blade 210 included in the compressor 200; And
And a turbine blade (510) included in the turbine (500)
The rotor (600)
A compressor rotor disk 610 coupled to the compressor blade 210; And
And a turbine rotor disk (630) fastened to the turbine blade (510)
The gap reducing member 800 is formed in at least one of between the compressor blade 210 and the compressor rotor disk 610 and between the turbine blade 510 and the turbine rotor disk 630.

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