KR101772334B1 - Disk assembly and a turbine using the same - Google Patents

Abstract

The present invention relates to a disk assembly to provide a torque transfer means more improved than an existing torque tube; and a turbine including the same. According to one aspect of the present invention, the disk assembly comprises: a first disk engaged with a compressor section of a gas turbine; a second disk engaged with a turbine section of the gas turbine and having a through-hole formed to penetrate along an axial direction of the gas turbine; a third disk disposed between the first and second disks to transfer a rotary torque applied to the second disk to the first disk; and a damper ring disposed between the inner circumferential surface of the second disk and the outer circumferential surface of a tie rod of the gas turbine to fixate the second disk in a radial direction of the tie rod. A distance between the third disk and the tie rod is longer than a distance between the first and second disks and the tie rod.

Description

DISC ASSEMBLY AND A TURBINE USING THE SAME < RTI ID = 0.0 >

The present invention relates to a disk assembly and a turbine including the turbine, and more particularly to a disk assembly disposed between a compressor section and a turbine section in a turbine, particularly a gas turbine, for transferring rotational torque generated by the turbine section to a compressor section, .

A gas turbine is a kind of prime mover that injects combustion gas to the blade side of a turbine to obtain rotational force, and can be largely divided into a compressor, a combustor, and a turbine. The compressor receives a part of the power generated from the rotation of the turbine, compresses the introduced air to a high pressure, and the compressed air is transmitted to the combustor.

The combustor mixes and burns the compressed air and the fuel to generate a high-temperature combustion gas stream and injects the high-temperature combustion gas stream to the turbine side, and the injected combustion gas rotates the turbine to obtain a rotational force.

Here, the compressor and the turbine include a plurality of rotor disks having blades radially coupled to the outer periphery. Generally, the compressor includes more rotor discs than the turbine. In the following, a plurality of rotor discs disposed in the compressor are referred to as compressor sections, and a plurality of rotor discs disposed on the turbine side are referred to as turbine sections.

Each of the rotor disks is fastened to rotate with a neighboring rotor disk. In addition, each of the rotor discs is fixed in a tight state so as not to move in the axial direction by using the tie rod.

The tie rods are inserted so as to penetrate through the center of each rotor disk and can be fastened so that the rotor disks do not move in the axial direction through the pressing nuts fastened to both ends of the tie rod.

On the other hand, since the combustor is arranged between the compressor section and the turbine section, the compressor section and the turbine section are spaced from each other to form a space for the combustor to be disposed. The tie rod only limits the axial movement of the rotor disc so that the rotor disc is free to rotate with respect to the tie rod. Therefore, a torque transmitting member capable of transmitting the rotational torque generated in the turbine section to the compressor section via the combustor must additionally be provided.

One of these torque transmitting members is a torque tube. The torque tube has a generally hollow cylinder shape and is configured such that both ends thereof are respectively coupled to a most-end rotor disk of the compressor section and a most-end rotor disk of the turbine section, and to transmit torque therebetween.

The torque tube must be resistant to deformation and distortion due to the characteristics of a gas turbine that is continuously operated for a long period of time, and should be easy to assemble and disassemble in order to facilitate maintenance. In addition, since the torque tube also functions as an air flow path for transferring the cooling air supplied from the compressor section to the turbine section, the cooling air must be smoothly supplied.

SUMMARY OF THE INVENTION It is an object of the present invention to provide an improved torque transmission means as compared with a conventional torque tube.

The present invention also has a technical object to provide a turbine having such torque transmitting means.

According to an aspect of the present invention, there is provided a gas turbine comprising: a first disk engaging with a compressor section of a gas turbine; A second disk engaging a turbine section of the gas turbine; A third disc disposed between the first disc and the second disc to transmit rotational torque applied to the second disc to the first disc and having at least one through hole; And a damper ring disposed between the inner circumferential surface of the third disk and the outer circumferential surface of the tie rod of the gas turbine and fixing the third disk in the radial direction of the tie rod,

A first space portion communicating with the compressor section and the turbine section is formed between the first disk and the third disk and between the second disk and the third disk,

And a second space portion communicating with the first space portion is formed between the compressor section and the first disk and between the turbine section and the second disk, respectively.

Here, an outer rim extending in the longitudinal direction of the tie rod may be formed on the radially outer side of the first to third disks.

Here, the outer rims formed on the first to third discs may be interlocked with each other so that the first to third discs may be coupled so that they can not rotate relative to each other.

The through hole of the third disk may be disposed between the outer rim and the tie rod.

The damper ring may be disposed at a gap formed between the end surface of the third disk and the tie rod.

First and second air storage spaces may be defined on both sides of the third disk, and the first and second air storage spaces may communicate with each other through the through holes.

In addition, a gap may be formed between the first and second disks and the tie rod, and the gap may be communicated with the first and second air storage spaces.

An inner rim extending in the longitudinal direction of the tie rod may be formed on the inner side of the third disk in the radial direction.

Here, the first to third discs may have the same shape except for the through-hole.

In addition, the first space portion may have a larger volume than the second space portion.

According to another aspect of the present invention, there is provided a compressor comprising: a compressor section having a plurality of compressor-side rotor discs; A turbine section having a plurality of turbine side rotor disks disposed downstream of the compressor side rotor disk; A tie rod penetrating through the rotor disk provided in the compressor section and the turbine section to closely contact each other; A first disk engaging the compressor section; A second disk engaging the turbine section; A third disc disposed between the first disc and the second disc to transmit rotational torque applied to the second disc to the first disc and having at least one through hole; And a damper ring disposed between the inner circumferential surface of the third disk and the outer circumferential surface of the tie rod of the gas turbine and fixing the third disk in the radial direction of the tie rod .

In addition, an outer rim extending in the longitudinal direction of the tie rod may be formed on the radially outer side of the first to third disks.

According to another aspect of the present invention, there is provided a compressor comprising: a compressor section having a plurality of compressor-side rotor discs; A turbine section having a plurality of turbine side rotor disks disposed downstream of the compressor side rotor disk; A tie rod penetrating through the rotor disk provided in the compressor section and the turbine section to closely contact each other; A first disk engaging the compressor section; A second disk engaging the turbine section; And a third disk disposed between the first and second disks to transmit rotation torque applied to the second disk to the first disk and having at least one through hole formed therein, A radially extending disk body and an axially extending outer rim about a radially outer end of the disk body.

Here, the outer rims, which are respectively formed in the first and second discs, may be coupled at least partially at different portions from the outer rim of the third disc.

According to the aspects of the present invention having the above-described structure, not only the fixing operation to the tie rod is facilitated by using a plurality of disks as the torque transmitting member, but also the third disk is radially The vibration and noise generated in the disk assembly during the torque transmission process can be minimized.

In addition, it is possible to simplify the flow of the cooling air passing through the first to third disks, to improve the use efficiency of the cooling air, and to facilitate the analysis work on the cooling air flow at the time of designing.

1 is a cross-sectional view schematically showing an inner structure of a gas turbine to which a first embodiment of a disk assembly according to the present invention is applied.
Fig. 2 is an enlarged cross-sectional view of the first embodiment shown in Fig. 1. Fig.
3 is an enlarged cross-sectional view of a second embodiment of the disk assembly.

Hereinafter, an embodiment of a disk assembly according to the present invention and a gas turbine to which the present invention is applied will be described in detail with reference to the accompanying drawings.

1 is a cross-sectional view schematically showing an inner structure of a gas turbine 100 to which a first embodiment 200 of a disk assembly according to the present invention is applied. Referring to FIG. 1, the embodiment includes a body 102, and a diffuser 106 is disposed at a rear side of the body 102 to discharge a combustion gas passing through the turbine. A combustor 104 for supplying compressed air to the front of the diffuser 106 and combusting the air is disposed.

Referring to the flow direction of the air, the compressor section 110 is located on the upstream side of the body 102, and the turbine section 120 is disposed on the downstream side. Between the compressor section 110 and the turbine section 120, there is disposed a disk assembly 200 as a torque transmitting member for transmitting the rotation torque generated in the turbine section to the compressor section. A total of 14 compressor rotor discs 140 are provided in the compressor section 110 and each compressor rotor disc 140 is tightened in a manner not to be axially spaced apart by one tie rod 150.

Specifically, each of the compressor rotor discs 140 is arranged substantially in the center along the axial direction with the tie rods passing through them. In addition, a plurality of protrusions (not shown) are formed in the vicinity of the outer circumference of the compressor rotor disk 140, and a flange 142 coupled to the neighboring rotor disk such that the rotor disk is relatively rotatable is formed to be axially protruded.

A plurality of blades 144 are radially coupled to the outer circumferential surface of the compressor rotor disk 140. Each of the blades 144 includes a dovetail portion 146 and is fastened to the compressor rotor disk 140. The coupling between the blades and the compressor rotor disk 140 is not limited to dovetail .

Meanwhile, the turbine section 120 is provided with four turbine rotor discs 180. Each of the turbine rotor disks 180 is basically similar in shape to the compressor rotor disk. Accordingly, the turbine rotor disk 180 also includes a plurality of turbine blades 184 having a flange 182 with coupling protrusions for engagement with the neighboring turbine rotor disk, and radially disposed. The turbine blade 184 may also be coupled to the turbine rotor disk 180 in a dovetail fashion.

The tie rod 150 is disposed so as to pass through the center of the plurality of compressor rotor discs 140. One end of the tie rod 150 is coupled to the compressor rotor disk located at the uppermost position and the other end of the tie rod 150 is connected to the turbine rotor disk And is fastened to a fixing nut 190 disposed on the downstream side of the fixing nut 190. Specifically, the other end of the tie rod 150 is screwed to the fixing nut 190, whereby the fixing nut presses the turbine-side rotor disk disposed in the downstream most in the axial direction. As a result, the plurality of disks arranged on the tie rod 150 are fixed so as to be unable to move in the axial direction while being in close contact with each other.

Here, the disk assembly 200 is fixed at both ends thereof in contact with the compressor section 110 and the turbine section 120, respectively. That is, the compressor section side end of the disk assembly is in contact with the most downstream compressor rotor disk, and the turbine section side end of the disk assembly is in contact with the most upstream turbine rotor disk. As described above, the disc assembly also has a plurality of protrusions formed therein, which can be fixed to each rotor disc so that relative rotation is not possible.

On the other hand, in the gas turbine described above, one tie rod is disposed so as to extend across the compressor and the turbine, but is not limited thereto. As an example, an example in which a separate tie rod is provided on the compressor side and the turbine side may be considered. Instead of one tie rod passing through the center of each disk, a plurality of tie rods May also be considered. It is also conceivable to dispose one tie rod passing through the center in either the compressor section or the turbine section and a plurality of tie rods arranged radially in the remaining sections.

Now, referring to FIG. 2, the disk assembly 200 will be described in detail.

Referring to FIG. 2, the disc assembly 200 includes three discs. The first and second disks 210 and 230 are formed to have substantially the same shape, while the third disk 220 and the third disk 220 are formed in the same manner in that a hole through which the tie- Has a difference in that a through hole 224a for providing a flow path through which cooling air to be described later is further formed is formed. That is, if there is no through-hole, the first through third disks may have the same shape.

Hereinafter, specifically, the respective disks will be described.

The first disk 210 is formed to have a substantially T-shaped cross-sectional shape. Specifically, the first disk includes a disk-shaped disk body 214 and an outer rim 212 protruding from the outer periphery of the disk body along the axial direction of the tie rod. Here, the outer rim 212 is in contact with neighboring disks, and serves to prevent the disks from rotating relative to each other. For example, the surface of the outer rim 212 may be a frictional surface, and may be combined with the surface of the rotor disk or the surface of the third disk by a pressing force of the fixing nut. In addition, a plurality of protrusions may be formed on the surface of the outer rim 212 to be engaged with neighboring discs.

One end of the disk body 214 of the first disk, specifically, an end opposite to the tie rod 150 is disposed to be spaced from the surface of the tie rod. Thus, a clearance S2 is formed between the surface of the tie rod and the end of the disk body 214. [ The gap will be described later.

The second disk 230 basically has a shape similar to that of the first disk. That is, the second disk 230 may be formed to have a substantially T-shaped cross-sectional shape. Like the first disk, a disk-shaped disk body 234 and an outer peripheral portion of the disk- And an outer rim 232 protruded on both sides along the axial direction of the outer rim 232. The outer rim 232 of the second disk 230 is also in contact with neighboring disks to prevent the disks from rotating relative to each other.

For example, the surface of the outer rim 232 may be a friction surface, and may be combined with the surface of the turbine rotor disk or the surface of the third disk by a pressing force of the fixing nut. Also in the second disk, a plurality of protrusions may be formed on the surface of the outer rim 232 so as to be engaged with neighboring disks. Also, a clearance S2, which is the same as that of the first disk, is disposed on the tie rod side end of the second disk.

Meanwhile, the third disk is formed to have a different shape from the first and second disks. As shown in FIG. 2, the third disk 220 is the same as the first and second disks in that it is formed to have a substantially "T" shape. Thus, the third disc 220 has an outer rim 222, such as the first and second discs, and the outer rim 222 is coupled to the outer rim of the first and second discs, respectively. Thereby, the rotational torque generated in the turbine section can be transmitted to the compressor section via the second, third and first disks.

The disk body 224 of the third disk 220 has a through hole 224a extending downward from the center of the outer rim 222 and extending in the longitudinal direction of the tie rod 150 . The through hole 224a functions as a passage through which the cooling air passes. Although the through hole is formed parallel to the longitudinal direction of the tie rod in FIG. 2, the through hole 224a is not necessarily formed in such a shape, and the through hole 224a may have any shape passing through the disk body 224 Lt; / RTI >

For example, the through hole may be formed to be inclined toward the gap S2 of the second disk 230.

First and second air storage spaces S1 are defined on both sides of the main body of the third disk 220 as an example of the first space. The first and second air storage spaces S1 are defined by the respective disk bodies on both sides, the upper surface is defined by the outer rim, and the lower surface is defined by the surface of the tie rod.

The first air storage space (S1) disposed between the first disk and the second disk functions as a space in which the cooling air supplied from the compressor section is primarily stored. The first air storage space S1 is communicated with the gap S2 of the first disk. Through this, the cooling air added from the compressor section can be temporarily stored in the first air storage space.

Meanwhile, the through holes 224a communicate with the two air storage spaces S1. Therefore, the cooling air stored in the first air storage space can flow into the second air storage space through the through hole 224a. The introduced cooling air temporarily stays in the second air storage space and is supplied to the turbine section side through the gap S2 of the second disk 230. [

Here, the gap S2 formed in the second disk serves as a nozzle for allowing the air stored in the second air storage space to be ejected into the turbine section. Since the air charged in the air storage space is supplied from the compressor section as described above and has a pressure higher than atmospheric pressure, air can be injected toward the turbine side by this compression pressure, do.

In order to further increase the cooling efficiency, the arrangement direction of the gap S2 may be inclined toward a specific portion of the turbine section.

The first and second storage spaces communicate with the second space portion formed in the compressor section and the turbine section, respectively. That is, on both side surfaces of the first disk, a second space portion, which is disposed in the compressor section, and the first storage space are disposed, and on both sides of the second disk are disposed a second space portion disposed in the turbine section, A storage space is disposed.

In this way, two cooling air storage spaces are disposed on both sides of the third disk, and these two cooling air storage spaces can function as buffers for smoothly supplying cooling air.

Meanwhile, in the first embodiment of the disk assembly, the three disks having the end opposite to the tie rod 150 are configured to maintain the engagement by the axial pressure of the tie rod. At this time, in order to support the first to third disks in the radial direction, a tension ring 240 is fitted between the end of the third disk and the tie rod 150.

2, the upper portion of the cross section is in contact with the disk body 224, and the lower portion thereof is in contact with the outer peripheral surface of the tie rod 150 . Accordingly, the tension ring absorbs vibrations that may be generated during operation, thereby preventing the life of the device from being shortened, and minimizing noise generation.

Here, in the example shown in FIG. 2, it can be seen that a tension ring is provided only in the third disk. This is because the three disks are fixed in the axial direction between the compressor and the turbine section by the tie rods as described above, so that even a single tension ring can absorb vibration to a required extent, And the flow of cooling air through the second disk. However, in some cases, the tension ring may be provided on both the first and second discs, and the through hole 224a may be formed on both the first and second discs, Of the cooling air.

In addition, in the above-described embodiment, all three discs have a T-shape, but an I-shaped disc may be disposed between the two T-shaped discs. In this case, the number and arrangement order of the discs may be arbitrarily changed have. The first and second disks are spaced apart from each other and are supported by each other via the third disk. However, the first and second disks may be provided with additional members for connecting the two to improve the vibration absorbing performance.

FIG. 3 shows a second embodiment of the disk assembly. In the second embodiment, the same reference numerals are assigned to the same components as those of the first embodiment, and a duplicate description will be omitted.

The disks included in the second embodiment shown in FIG. 3 are basically similar to those of the first embodiment. Thus, the second embodiment also includes first and second discs 310 and 330 having two T-shaped cross-sections, the first and second discs having outer rims 312 and 332 and a disc body 314 and 334, respectively.

The third disk 320 includes an outer rim 322 and a disk body 324 formed integrally with the outer rim. The disk body 324 is provided with a through hole 324a which functions as a passage through which cooling air flows. Meanwhile, the third disk 320 has an inner rim 326 at a radially inner end of the disk body 324. The inner rim 326 extends from both sides of the disc body to protrude along the tie rods.

The inner rim 326 not only improves the rigidity of the third disk but also serves to guide the cooling air passing through the through hole 324a. That is, the upper surface of the inner rim 326 is formed of a tapered surface inclined along the flow direction of the cooling air. Therefore, the cooling air can flow into the through hole naturally while flowing along the tapered surface, and can be discharged therefrom.

Claims (11)

A first disk engaging a compressor section of the gas turbine;
A second disk engaging a turbine section of the gas turbine;
A third disc disposed between the first disc and the second disc to transmit rotational torque applied to the second disc to the first disc and having at least one through hole; And
And a damper ring disposed between the inner circumferential surface of the third disk and the outer circumferential surface of the tie rod of the gas turbine and fixing the third disk in the radial direction of the tie rod,
A first space portion communicating with the compressor section and the turbine section is formed between the first disk and the third disk and between the second disk and the third disk,
And a second space portion communicating with the first space portion is formed between the compressor section and the first disk and between the turbine section and the second disk, respectively. The method according to claim 1,
And an outer rim extending in the longitudinal direction of the tie rod is formed on a radially outer side of the first to third disks. 3. The method of claim 2,
Wherein outer rims formed on the first to third discs are engaged with each other so that the first to third discs are coupled so as not to be rotatable relative to each other. The method of claim 3,
And a through hole of the third disk is disposed between the outer rim and the tie rod. The method of claim 3,
Wherein the damper ring is disposed in a gap formed between the end surface of the third disk and the tie rod. The method according to claim 1,
First and second air storage spaces are defined on both sides of the third disk, and the first and second air storage spaces communicate with each other through the through holes. The method according to claim 6,
A gap is formed between the first and second disks and the tie rod, and the gap is communicated with the first and second air storage spaces. 3. The method of claim 2,
And an inner rim extending in the longitudinal direction of the tie rod is formed inside the third disk in the radial direction. 3. The method of claim 2,
Wherein the first to third disks have the same shape except for the through holes. The method according to claim 1,
Wherein the first space portion has a larger volume than the second space portion. A compressor section having a plurality of compressor-side rotor discs;
A turbine section having a plurality of turbine side rotor disks disposed downstream of the compressor side rotor disk;
A tie rod penetrating through the rotor disk provided in the compressor section and the turbine section to closely contact each other;
A gas turbine comprising a disc assembly according to any one of claims 1 to 10.

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