KR20230028978A - Compressor rotor assembly and compressor and gas turbine including same - Google Patents

Abstract

The present invention provides a compressor rotor assembly, and a compressor and a gas turbine including the same. The compressor rotor assembly comprises: a plurality of compressor rotor disks in which a plurality of slots are formed on the outer circumferential surface and a plurality of tie rod through holes are formed in a circular shape adjacent to the outer circumferential surface; each blade of a plurality of compressor blades is inserted into and installed in the slot of each compressor rotor disk; and a plurality of compressor tie rods inserted into the plurality of tie rod through holes formed in the plurality of compressor rotor disks to connect the plurality of compressor rotor disks. The compressor rotor assembly further comprises a toothed joint portion formed on one side of the compressor rotor disk, and coupled to an adjacent compressor rotor disk to form a space inside where cooling air flows; and a cooling passage portion causing the cooling air having passed through the toothed joint portion to move toward the center of the compressor rotor disk. Therefore, power generation efficiency can be improved by applying the toothed joint to the coupling between the plurality of compressor rotor disks while excluding a center tie rod from a compressor section and employing the multi-compressor tie rods that penetrate the vicinity of the outer circumferential surface of the compressor rotor disk. Moreover, cooling efficiency can be enhanced by preventing compressed air flowing into a compressor rotor disk from leaking into the spaces of other compressor rotor disks.

Description

Compressor rotor assembly and compressor and gas turbine including same}

The present invention relates to a compressor rotor assembly and a compressor and a gas turbine including the same, and more particularly, to a compressor rotor assembly installed in a compressor casing and a compressor and a gas turbine including the same.

A turbine is a mechanical device that obtains rotational force by impulse or reaction force using a flow of compressible fluid such as steam or gas, and includes a steam turbine using steam and a gas turbine using high-temperature combustion gas.

Among these, a gas turbine is largely composed of a compressor, a combustor, and a turbine. The compressor is provided with an air inlet for introducing air, and a plurality of compressor vanes and compressor blades are alternately arranged in a compressor casing.

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

In the turbine, a plurality of turbine vanes and turbine blades are alternately arranged in a teabin casing. In addition, the rotor is arranged so as to pass through the center of the compressor, combustor, turbine, and exhaust chamber.

Both ends of the rotor are rotatably supported by bearings. Then, a plurality of disks are fixed to the rotor, each blade is connected, and a drive shaft of a generator or the like is connected to an end portion on the exhaust chamber side.

Since these gas turbines do not have a reciprocating mechanism such as a piston of a 4-stroke engine, there is no mutual friction part such as a piston-cylinder, so the consumption of lubricating oil is extremely low, the amplitude characteristic of reciprocating machines is greatly reduced, and high-speed operation is possible There are advantages.

Briefly explaining the operation of the gas turbine, high-temperature combustion gas is produced by mixing and combusting air compressed in a compressor with fuel, and the combustion gas thus produced is injected toward the turbine side. The injected combustion gas generates rotational force while passing through the turbine vanes and turbine blades, thereby causing the rotor to rotate, generating power while generating power and cooling efficiency. Research on gas turbines capable of further improving is being conducted. There is a situation.

The background technology of the present invention is disclosed in Korean Patent Publication No. 10-2006-0087872 (published on August 3, 2006).

The present invention has been created to meet the above circumstances, and an object of the present invention is to provide a compressor rotor assembly and a compressor and gas turbine including the same, which can further improve power generation efficiency and cooling efficiency.

In order to achieve the above object, the present invention provides a plurality of compressor rotor disks in which a plurality of slots are formed on an outer circumferential surface and a plurality of tie rod through-holes are formed in a circular shape adjacent to the outer circumferential surface; A plurality of compressor blades inserted into the slots of each compressor rotor disk; and a plurality of compressor tie rods inserted into the plurality of tie rod through-holes formed in the plurality of compressor rotor disks to connect the plurality of compressor rotor disks, wherein the compressor rotor disk is formed on one side of the compressor rotor disk and is adjacent to the compressor rotor disk. and a compressor rotor assembly having a toothed joint portion formed with a space in which cooling air flows and a cooling passage portion formed to flow the cooling air passing through the toothed joint portion toward the center of the compressor rotor disk.

The compressor rotor assembly according to the present invention is inserted into the plurality of compressor tie rods and seals a gap between each compressor tie rod and a tie rod through hole into which each compressor tie rod is inserted. ) may be further included.

In the compressor rotor assembly according to the present invention, each compressor rotor disk has a disk body having a disk shape, a plurality of tie rod through-holes formed to form a circle adjacent to the outer circumferential surface of the disk body, and both side surfaces of the disk body A toothed joint portion formed of a plurality of toothed joints formed to be spaced apart from each other between each tie rod through hole and the outer circumferential surface of the disk body to form a compressed air inlet, and a plurality of compressed air inlets and the disk body A cooling passage portion formed to communicate with the central portion may be included.

The cooling passage part includes a plurality of compressed air passage grooves formed to communicate with the plurality of compressed air inlets and the central portion of the disk body, and a plurality of compressed air passage grooves formed in the central portion of the disk body to pass through the disk body. It may include a flow path through-hole in communication with.

The plurality of toothed joints may include a plurality of toothed protrusions protruding outward from one side and the other side of the disk body, and a plurality of toothed grooves formed between the plurality of toothed protrusions, and a plurality of compressor rotor disks. When the disc body comes into close contact, the tooth protrusion formed on one side of the disk body may be inserted into the tooth groove formed on the other side of the disk body disposed adjacent thereto.

The plurality of compressed air passage grooves may be formed to have an arc shape from the plurality of compressed air inlets to the passage through-hole.

One end of the plurality of compressor tie rods is connected to a torque tube to receive torque generated from a turbine through the torque tube to rotate a plurality of compressor rotor disks, and the seal bushing has a hollow interior It may have a cylindrical shape, and a circumferential surface of the seal bushing may be larger than a diameter of the tie rod through hole.

On the other hand, the present invention is coupled to the multi-stage vane on the inner surface, a casing formed with a heating flow path through which the combustion gas discharged from the turbine circulates; And a plurality of compressor rotor disks installed inside the casing, having a plurality of slots formed on the outer circumferential surface and having a plurality of tie rod through-holes formed in a circular shape adjacent to the outer circumferential surface, and inserted into the slots of each compressor rotor disk. It includes a plurality of compressor blades and a plurality of compressor tie rods inserted into the plurality of tie rod through holes formed in the plurality of compressor rotor disks to connect the plurality of compressor rotor disks, formed on one side of the compressor rotor disks. A compressor rotor assembly having a tooth joint portion coupled to an adjacent compressor rotor disk and forming a space in which cooling air flows inside, and a cooling passage portion for flowing cooling air passing through the tooth joint portion toward the center of the compressor rotor disk. It provides a compressor that includes.

On the other hand, the present invention provides a compressor for sucking and compressing air by rotating compressor blades, a combustor for mixing compressed air supplied from the compressor with fuel and combusting it, and passing combustion gas supplied from the combustor into the inside. In a gas turbine including a turbine that uses turbine blades to generate power for power generation, the compressor has multi-stage vanes coupled to an inner surface and a casing formed with a heating passage through which combustion gas discharged from the turbine circulates ; And a plurality of compressor rotor disks installed inside the casing, having a plurality of slots formed on the outer circumferential surface and having a plurality of tie rod through-holes formed in a circular shape adjacent to the outer circumferential surface, and inserted into the slots of each compressor rotor disk. It includes a plurality of compressor blades and a plurality of compressor tie rods inserted into the plurality of tie rod through holes formed in the plurality of compressor rotor disks to connect the plurality of compressor rotor disks, formed on one side of the compressor rotor disks. A compressor rotor assembly having a tooth joint portion coupled to an adjacent compressor rotor disk and forming a space in which cooling air flows inside, and a cooling passage portion for flowing cooling air passing through the tooth joint portion toward the center of the compressor rotor disk. It provides a gas turbine comprising

The compressor rotor assembly according to the present invention and the compressor and gas turbine including the same exclude the center tie rod from the compressor section and apply a multi-compressor tie rod penetrating the vicinity of the outer circumferential surface of the compressor rotor disk, while the coupling between the plurality of compressor rotor disks is sawtooth Generation efficiency can be improved by applying the joint, and cooling efficiency can be improved by preventing compressed air flowing into each compressor rotor disk from leaking into a space of another compressor rotor disk.

1 is a view showing the inside of a gas turbine including a compressor rotor assembly according to an embodiment of the present invention.
2 is a longitudinal cross-sectional view of a part of the gas turbine shown in FIG. 1;
FIG. 3 is an enlarged view of part “A” which is a main part of FIG. 2 .
4 is an enlarged view of the compressor rotor assembly shown in FIG. 1;
5 is a view showing the flow of compressed air when there is no seal bushing in the compressor rotor assembly according to an embodiment of the present invention.
6 is a view showing the flow of compressed air when there is a seal bushing in the compressor rotor assembly according to an embodiment of the present invention.
7 is a diagram illustrating a flow of compressed air from a compressor to a turbine in a gas turbine including a compressor rotor assembly according to an embodiment of the present invention.

Hereinafter, preferred embodiments according to the present invention will be described in detail with reference to the accompanying drawings. Prior to this, the terms or words used in this specification and claims should not be construed as being limited to the usual or dictionary meaning, and the inventor appropriately uses the concept of the term in order to explain his/her invention in the best way. It should be interpreted as a meaning and concept consistent with the technical idea of the present invention based on the principle that it can be defined.

1 is a view showing the inside of a gas turbine including a compressor rotor assembly according to an embodiment of the present invention, and FIG. 2 is a longitudinal cross-sectional view of a part of the gas turbine shown in FIG. 1 .

1 and 2 , a gas turbine 100 according to an embodiment of the present invention includes a compressor 1000, a combustor 2000, and a turbine 3000.

The compressor 1000 intakes and compresses external air, the combustor 2000 mixes fuel with the air compressed by the compressor 1000 and burns it, and the turbine 3000 supplies the air from the combustor 2000. The received combustion gas is passed through the inside to generate power for power generation.

The gas turbine 100 has a housing 100a, and a rear side of the housing 100a is provided with a diffuser 100b through which combustion gas passing through the turbine 3000 is discharged, and the diffuser 100b In front of the combustor 2000 for receiving and burning compressed air is disposed.

Referring to the flow of air, the compressor 1000 is located on the upstream side of the housing 100a, and the turbine 3000 is disposed on the downstream side. Preferably, a torque tube T is disposed between the compressor 1000 and the turbine 3000 as a torque transmission member for transmitting rotational torque generated in the turbine 3000 to the compressor 1000.

The compressor 1000 includes a plurality (for example, 14) of compressor rotor assemblies 1200, and the compressor rotor assemblies 1200 are installed inside a casing (not shown). A multi-stage vane (not shown) is coupled to the inner surface of the casing 1100, and a heating passage through which combustion gas discharged from the turbine 3000 described later circulates is formed.

FIG. 3 is an enlarged view of part “A” which is a main part of FIG. 2 .

Referring to FIG. 3 , the compressor rotor assembly 1200 includes a plurality of compressor rotor disks 1210, a plurality of compressor blades 1220, a plurality of compressor tie rods 1230, and a seal bushing 1240 may further include.

The compressor rotor disk 1210 fixes the plurality of compressor blades 1220, rotates according to the rotation of the plurality of compressor tie rods 1230 to rotate the plurality of compressor blades 1220, and rotates the plurality of compressor rotor disks ( 1210 is fastened to the plurality of compressor tie rods 1230 so as not to be spaced apart in the axial direction.

A plurality of compressor blades 1220 are radially coupled to the outer circumferential surface of each compressor rotor disk 1210, and the compressor blades 1220 include a root portion 1221, a shank portion 1222, and a wing portion 1223. ), and the compressor blade 1220 is fastened to a plurality of slots 1211a formed on an outer circumferential surface of the compressor rotor disk 1210 by a root portion 1221.

The root portion 1221 is inserted into a plurality of slots 1211a formed on the outer circumferential surface of the compressor rotor disk 1210, and the fastening methods of the root portion 1221 are tangential type and axial type. ) is there. It may be selected according to the required structure of a commercially available gas turbine, and may have a commonly known dovetail or fir tree shape.

A shank portion 1222 is coupled to an upper portion of the root portion 1221, and a wing portion 1223 is provided on an upper surface of the shank portion 1222. The wings 1223 are formed to have an optimized airfoil shape according to the specifications of the gas turbine 100 .

The compressor blade 1220 inserted into the slot 1211a is preferably fixed by a separate blade fixing structure (not shown) so as not to move in the axial direction of the compressor rotor disk 1210.

FIG. 4 is an enlarged view of the compressor rotor assembly shown in FIG. 1 .

3 and 4, each compressor rotor disk 1210 on which a plurality of compressor blades 1220 are mounted on a circumferential surface has a disk body 1211, a tie rod through hole 1212, and a toothed joint portion 1213 and a cooling passage part 1214 are included.

The disk body 1211 has a disk shape, and a plurality of slots 1211a into which the compressor blades 1220 are inserted are formed on a circumferential surface of the disk body 1211 .

Adjacent to the outer circumferential surface of the disk body 1211, a plurality of tie rod through holes 1212 are formed in a circular shape, and a compressor tie rod connecting a plurality of compressor rotor disks 1210 to the tie rod through holes 1212. 1230 is inserted through the compressor rotor disk 1210.

The tie rod through holes 1212 are formed in a number corresponding to the number of the compressor tie rods 1230, and the tie rods 1230 and the compressor rotor disk 1210 are easily assembled. The rod through hole 1212 is preferably formed with a larger diameter than the diameter of the compressor tie rod 1230 .

A toothed joint portion 1213 is formed on both sides of the disk body 1211, and the toothed joint portion 1213 is mutually connected between each tie rod through hole 1212 and the outer circumferential surface of the disk body 1211. It consists of a plurality of toothed joints 1213a formed to be spaced apart, and a compressed air inlet 1213d through which compressed air flows is formed between the spaced apart toothed joints 1213a.

Each of the plurality of toothed joints 1213a formed to be spaced apart from each other on both sides of the disk body 1211 includes a plurality of toothed protrusions 1213b and a plurality of toothed grooves 1213c.

The plurality of sawtooth projections 1213b protrude outward from one side and the other side of the disk body 1211, and the plurality of sawtooth grooves 1213c are formed between the plurality of sawtooth projections 1213b.

When the plurality of compressor rotor disks 1210 come into close contact with each other, the tooth protrusions 1213b formed on one side of the disk body 1211 are adjacent to the tooth grooves 1213c formed on the other side of the disk body 1211. A plurality of compressor rotor disks 1210 are inserted into each other and rotated when rotating.

The cooling passage part 1214 is formed to communicate with the compressed air inlet 1213d and the central part of the disk body 1211, and the cooling passage part 1214 includes a plurality of compressed air passage grooves 1214a and a passage It includes a through hole 1214b.

The plurality of compressed air passage grooves 1214a communicate with the central portion of the disk body 1211 with the plurality of compressed air inlets 1213d formed between the plurality of toothed joints 1213a. ), and the plurality of compressed air passage grooves 1214a are formed to have the same number as the plurality of compressed air inlets 1213d.

The passage through-hole 1214b is formed at the center of the disk body 1211 to pass through the disk body 1211, communicates with the plurality of compressed air passage grooves 1214a, and passes through the plurality of compressed air passage grooves. 1214a is formed to have an arc shape from the plurality of compressed air inlets 1213d to the passage through-hole 1214b.

A portion of the compressed air flowing through the compressor 1000 is introduced into the compressor rotor assembly 1200 through the compressed air inlet 1213d and then flows into the compressor rotor assembly 1200 through the compressed air passage groove 1214a. It can flow from outside to inside.

The passage through-hole 1214b is formed to a predetermined size in the central portion of the disk body 1211, and the compressed air flowing through the compressed air passage groove 1214a flows into the passage through-hole 1214b.

A plurality of passage through-holes 1214b respectively formed in the plurality of compressor rotor disks 1210 are arranged in series to form a compressed air supply passage 1400 . The compressed air introduced into the passage through-hole 1214b flows along the compressed air supply passage 1400 and is finally supplied to the turbine blades 3200 formed in the turbine 3000 to cool the inside (see FIG. 7).

7 is a diagram illustrating a flow of compressed air from a compressor to a turbine in a gas turbine including a compressor rotor assembly according to an embodiment of the present invention.

2 and 7, a plurality of compressor tie rods 1230 are inserted into the plurality of tie rod through holes 1212 formed in the plurality of compressor rotor disks 1210 to form a plurality of compressor rotor disks 1210. Connected.

One end of the compressor tie-rod 1230 is connected to the torque tube (T) and the other end is connected to any one of the compressor rotor disks 1210 disposed in the front, and the compressor tie-rod is connected to the torque tube (T). One end of 1230 may use a fixing means such as a press nut when connected to the torque tube (T).

As one end of the plurality of compressor tie rods 1230 is connected to the torque tube T, the torque generated in the turbine 3000 is transmitted through the torque tube T to rotate the plurality of compressor rotor disks 1210. will make

5 is a view showing the flow of compressed air when there is no seal bushing in the compressor rotor assembly according to an embodiment of the present invention.

Referring to FIGS. 3 and 5 , to facilitate assembly of the compressor tie rod 1230 and the compressor rotor disk 1210, a plurality of tie rod through holes 1212 have a diameter smaller than the diameter of the compressor tie rod 1230. Since it is formed to have a large diameter, a gap G may be formed between the outer circumferential surfaces of the plurality of compressor tie rods 1230 and the inner circumferential surfaces of the plurality of tie rod through holes 1212 .

This gap G becomes a passage through which some of the compressed air introduced through the compressed air inlet 1213d may leak. In FIG. 5, reference numeral F denotes the flow of compressed air introduced through the compressed air inlet 1213d, and reference numeral F1 denotes the flow of compressed air introduced into the passage through-hole 1214b through the compressed air passage groove 1214a. Indicates the flow, reference numeral F2 indicates the flow of compressed air leaked through the gap (G). When the compressed air introduced into the compressor rotor assembly 1210 leaks, the amount of compressed air supplied to the turbine 3000 is reduced and the cooling effect of the turbine blades 3200 and the like is reduced.

6 is a view showing the flow of compressed air when there is a seal bushing in the compressor rotor assembly according to an embodiment of the present invention.

Referring to FIG. 6 , the seal bushing 1240 is fitted to the compressor tie rod 1230, and the seal bushing 1240 includes each compressor tie rod 1230 and each compressor tie rod 1230 ) serves to seal the gap G between the tie rod through-holes 1212 into which the seal bushing 1240 is inserted, and the seal bushing 1240 has a hollow cylindrical shape, and the circumferential surface of the seal bushing 1240 is It is preferable to have a larger diameter than the inner circumferential surface of the tie rod through hole.

The seal bushing 1240 seals the gap G between the compressor tie rod 1230 and the tie rod through hole 1212, so that the compressed air introduced through the compressed air inlet 1213d is adjacent to another rotor space ( S) to prevent leakage.

The compressed air compressed by the compressor 1000 is supplied to the combustor 2000, and the combustor 2000 mixes and burns the introduced compressed air with fuel to produce high-energy, high-temperature, high-pressure combustion gas, etc. The rolling process raises the temperature of the combustion gas to the limit of heat resistance that the combustor and turbine parts can withstand.

Referring to FIG. 1, a plurality of combustors constituting the combustion system of a gas turbine may be arranged in a casing formed in a cell shape, and a burner including a fuel injection nozzle, etc., and a combustor liner forming a combustion chamber ( Combustor Liner), and a transition piece that connects the combustor and the turbine.

Specifically, the combustor liner provides a combustion space in which fuel injected through a fuel nozzle is mixed with compressed air supplied from the compressor 1000 and burned.

This combustor liner may include a flame tube providing a combustion space in which fuel mixed with compressed air is combusted, and a flow sleeve surrounding the flame tube to form an annular space, and at the front end of the combustor liner A fuel nozzle is coupled, and a spark plug is coupled to the side wall.

Meanwhile, a transition piece capable of sending combustion gas burned by a spark plug to the turbine 3000 is connected to the rear end of the combustor liner. The outer wall of this transition piece is cooled by compressed air supplied from the compressor 1000 to prevent damage due to high temperature of the combustion gas.

To this end, holes for cooling are provided in the transition piece so that air can be injected into the inside, and the compressed air cools the body therein through the holes and then flows toward the combustor liner.

Cooling air for cooling the aforementioned transition piece flows in the annular space of the combustor liner, and compressed air from the outside of the flow sleeve is supplied to the outer wall of the combustor liner as cooling air through cooling holes provided in the flow sleeve to collide. there is.

High-temperature, high-pressure combustion gas from the combustor 2000 is supplied to the turbine 3000. As the supplied high-temperature and high-pressure combustion gas expands, it collides with the rotor blades of the turbine and gives a reaction force to generate rotational torque. Power in excess of the power required for this is used to drive a generator or the like.

1 and 2, the turbine 3000 is basically similar in structure to the compressor 1000, and the turbine 3000 includes a plurality of turbine rotor disks 3100 and a plurality of turbine blades 3200. ) and a plurality of turbine tie rods 3300 connecting the plurality of turbine rotor disks 3100.

Since the structure of the turbine 3000 is similar to that of the compressor 1000, the detailed description of the structure of the turbine 3000 overlaps with the detailed description of the structure of the compressor 1000, overlapping parts. The description of will be omitted.

Unlike the compressor blades 1220, the turbine blades 3200 come into direct contact with high-temperature, high-pressure combustion gas, and since the temperature of the combustion gas is high enough to reach 1700° C., a cooling means is required.

To this end, it is preferable to have a cooling passage (not shown) for extracting compressed air from some places on the side of the compressor 1000 and supplying it to the turbine blades 3200 on the side of the turbine 3000.

Although the present invention has been described with reference to the embodiments shown in the drawings, this is merely exemplary, and those skilled in the art will understand that various modifications and equivalent other embodiments are possible therefrom. Therefore, the true technical protection scope of the present invention should be determined by the technical spirit of the appended claims.

100: gas turbine 1000: compressor
1200: compressor rotor assembly 1210: compressor rotor disk
1220: compressor blade 1230: compressor tie rod
1240: seal bushing 2000: combustor
3000: turbine 3200: turbine rotor assembly

Claims (24)

A plurality of compressor rotor disks having a plurality of slots formed on an outer circumferential surface and a plurality of tie rod through-holes formed in a circular shape adjacent to the outer circumferential surface;
A plurality of compressor blades inserted into the slots of each compressor rotor disk; and
A plurality of compressor tie rods inserted into the plurality of tie rod through holes formed in the plurality of compressor rotor disks to connect the plurality of compressor rotor disks,
A sawtooth joint formed on one side of the compressor rotor disk and coupled to an adjacent compressor rotor disk and having a space for cooling air flowing therein, and cooling air passing through the sawtooth joint to flow toward the center of the compressor rotor disk A compressor rotor assembly in which a cooling passage portion is formed.
The method of claim 1,
The compressor rotor assembly further comprising a seal bushing inserted into the plurality of compressor tie rods and sealing a gap between each compressor tie rod and a tie rod through hole into which each compressor tie rod is inserted. .
The method of claim 2,
Each compressor rotor disk is
A disk body having a disc shape;
A plurality of tie rod through-holes formed in a circular shape adjacent to an outer circumferential surface of the disk body;
A toothed joint portion formed of a plurality of toothed joints formed to be spaced apart from each other between each tie rod through hole on both side surfaces of the disk body and an outer circumferential surface of the disk body to form a compressed air inlet;
A compressor rotor assembly comprising a cooling passage formed to communicate with the plurality of compressed air inlets and a central portion of the disk body.
The method of claim 3,
The cooling passage part,
a plurality of compressed air passage grooves formed to communicate with the plurality of compressed air inlets and the central portion of the disk body;
A compressor rotor assembly comprising a passage through-hole formed at a central portion of the disk body to penetrate the disk body and communicating with the plurality of compressed air passage grooves.
The method of claim 3,
Each of the plurality of toothed joints,
A plurality of toothed protrusions protruding outward from one side and the other side of the disk body;
It includes a plurality of sawtooth grooves formed between the plurality of sawtooth protrusions,
Compressor rotor assembly, characterized in that when the plurality of compressor rotor disks are in close contact with each other, the tooth protrusion formed on one side of the disk body is inserted into the tooth groove formed on the other side of the adjacent disk body.
The method of claim 4,
The plurality of compressed air flow path grooves are formed to have an arc shape from the plurality of compressed air inlets to the flow passage through-hole.
The method of claim 2,
One end of the plurality of compressor tie rods is connected to a torque tube to receive torque generated from a turbine through the torque tube to rotate a plurality of compressor rotor disks.
The method of claim 2,
The seal bushing has a cylindrical shape with a hollow inside, and a circumferential surface of the seal bushing is larger than a diameter of the tie rod through-hole.
A casing having a multi-stage vane coupled to an inner surface and a heating passage through which the combustion gas discharged from the turbine circulates; and
A plurality of compressor rotor disks installed inside the casing, having a plurality of slots formed on the outer circumferential surface and having a plurality of tie rod through-holes formed in a circular shape adjacent to the outer circumferential surface, and inserted into the slots of each compressor rotor disk to be installed A plurality of compressor blades and a plurality of compressor tie rods inserted into the plurality of tie rod through holes formed in the plurality of compressor rotor disks to connect the plurality of compressor rotor disks, formed on one side of the compressor rotor disk A compressor rotor assembly having a tooth joint portion coupled to an adjacent compressor rotor disk and forming a space in which cooling air flows, and a cooling passage portion for flowing cooling air passing through the tooth joint portion toward the center of the compressor rotor disk. Compressor to do.
The method of claim 9,
The compressor further includes a seal bushing inserted into the plurality of compressor tie rods and sealing a gap between each compressor tie rod and a tie rod through hole into which each compressor tie rod is inserted.
The method of claim 10,
Each compressor rotor disk is
A disk body having a disc shape;
A plurality of tie rod through-holes formed in a circular shape adjacent to an outer circumferential surface of the disk body;
A toothed joint portion formed of a plurality of toothed joints formed to be spaced apart from each other between each tie rod through hole on both side surfaces of the disk body and an outer circumferential surface of the disk body to form a compressed air inlet;
A compressor comprising a cooling passage formed to communicate with the plurality of compressed air inlets and a central portion of the disk body.
The method of claim 11,
The cooling passage part,
a plurality of compressed air passage grooves formed to communicate with the plurality of compressed air inlets and the central portion of the disk body;
A compressor comprising a passage through-hole formed at a central portion of the disk body to penetrate the disk body and communicating with the plurality of compressed air passage grooves.
The method of claim 11,
Each of the plurality of toothed joints,
A plurality of toothed protrusions protruding outward from one side and the other side of the disk body;
It includes a plurality of sawtooth grooves formed between the plurality of sawtooth protrusions,
The compressor characterized in that when the plurality of compressor rotor disks are in close contact with each other, the tooth protrusion formed on one side of the disk body is inserted into the tooth groove formed on the other side of the adjacent disk body.
The method of claim 12,
The plurality of compressed air passage grooves are formed to have an arc shape from the plurality of compressed air inlets to the flow passage through-holes.
The method of claim 10,
One end of the plurality of compressor tie rods is connected to a torque tube, characterized in that for receiving the torque generated in the turbine through the torque tube to rotate the plurality of compressor rotor disks.
The method of claim 10,
The seal bushing has a cylindrical shape with a hollow inside, and a circumferential surface of the seal bushing is larger than a diameter of the tie rod through-hole.
A compressor that sucks in and compresses air by rotating a compressor blade, a combustor that mixes the compressed air supplied from the compressor with fuel and combusts it, and passes the combustion gas supplied from the combustor into the inside to generate electric power using turbine blades. In the gas turbine comprising a turbine for generating power for,
the compressor,
A casing having a multi-stage vane coupled to an inner surface and a heating passage through which the combustion gas discharged from the turbine circulates; and
A plurality of compressor rotor disks installed inside the casing, having a plurality of slots formed on the outer circumferential surface and having a plurality of tie rod through-holes formed in a circular shape adjacent to the outer circumferential surface, and inserted into the slots of each compressor rotor disk to be installed A plurality of compressor blades and a plurality of compressor tie rods inserted into the plurality of tie rod through holes formed in the plurality of compressor rotor disks to connect the plurality of compressor rotor disks, formed on one side of the compressor rotor disk A compressor rotor assembly having a tooth joint portion coupled to an adjacent compressor rotor disk and forming a space in which cooling air flows, and a cooling passage portion for flowing cooling air passing through the tooth joint portion toward the center of the compressor rotor disk. gas turbine to do.
The method of claim 17
The gas turbine further includes a seal bushing inserted into the plurality of compressor tie rods and sealing a gap between each compressor tie rod and a tie rod through hole into which each compressor tie rod is inserted.
The method of claim 18
Each compressor rotor disk is
A disk body having a disc shape;
A plurality of tie rod through-holes formed in a circular shape adjacent to an outer circumferential surface of the disk body;
A toothed joint portion formed of a plurality of toothed joints formed to be spaced apart from each other between each tie rod through hole on both side surfaces of the disk body and an outer circumferential surface of the disk body to form a compressed air inlet;
A gas turbine comprising a cooling passage portion formed to communicate the plurality of compressed air inlets and a central portion of the disk body.
The method of claim 19
The cooling passage part,
a plurality of compressed air passage grooves formed to communicate with the plurality of compressed air inlets and the central portion of the disk body;
and a passage through-hole formed at a central portion of the disk body to penetrate the disk body and communicating with the plurality of compressed air passage grooves.
The method of claim 19
Each of the plurality of toothed joints,
A plurality of toothed protrusions protruding outward from one side and the other side of the disk body;
It includes a plurality of sawtooth grooves formed between the plurality of sawtooth protrusions,
The gas turbine according to claim 1 , wherein when the plurality of compressor rotor disks are brought into close contact, the sawtooth protrusions formed on one side of the disk body are inserted into the tooth grooves formed on the other side of the adjacent disk body.
The method of claim 20
The plurality of compressed air passage grooves are formed to have an arc shape from the plurality of compressed air inlets to the flow passage through-holes.
The method of claim 18
One end of the plurality of compressor tie rods is connected to a torque tube to receive torque generated from the turbine through the torque tube to rotate the plurality of compressor rotor disks.
The method of claim 18
The seal bushing has a cylindrical shape with a hollow inside, and a circumferential surface of the seal bushing is larger than a diameter of the tie rod through hole.

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