KR101747550B1

KR101747550B1 - Disk assembly and a turbine using the same

Info

Publication number: KR101747550B1
Application number: KR1020150169974A
Authority: KR
Inventors: 김경국
Original assignee: 두산중공업 주식회사
Priority date: 2015-12-01
Filing date: 2015-12-01
Publication date: 2017-06-27
Also published as: KR20170064330A

Abstract

The present invention relates to a disk assembly and a turbine including the same, and in accordance with an aspect of the invention, there is provided a disk assembly comprising: a first disk engaging a compressor section of a gas turbine; A second disk engaging with a turbine section of the gas turbine and having a through-hole formed to penetrate along the axial direction of the gas turbine; A third disk disposed between the first and second disks for transferring rotational torque applied to the second disk to the first disk; And a damper ring which is disposed between the inner circumferential surface of the second disk and the outer circumferential surface of the tie rod of the gas turbine and fixes the second disk in the radial direction of the tie rod, Is formed to be larger than an interval 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 with a turbine section of the gas turbine and having a through-hole formed to penetrate along the axial direction of the gas turbine; A third disk disposed between the first and second disks for transferring rotational torque applied to the second disk to the first disk; And a damper ring which is disposed between the inner circumferential surface of the second disk and the outer circumferential surface of the tie rod of the gas turbine and fixes the second disk in the radial direction of the tie rod, Is formed to be larger than an interval between the first and second disks and the tie rod.

Here, the damper ring is not necessarily limited to being disposed only on the second disk, but may be disposed on the first disk.

Here, the outer rim of each of the compressor section and the turbine section may be formed at a radially outer side of the first and second disks.

Here, the first and second discs may be located radially inward of the outer rim, and may include an inner rim facing the tie rod.

Here, the through-hole of the second disk may be disposed between the outer rim and the inner rim.

Here, the damper ring may be disposed between the inner rim and the tie rod.

An air storage space is defined by the opposite side surfaces of the first and second disks and the inner surface of the third disk, and the air storage space is a storage space for temporarily storing the air passing through the through hole Function.

Here, a gap is formed between the first disk and the tie rod, and the gap can function as an inlet for air to be introduced into the space.

According to another aspect of the present invention there is provided a turbomachine comprising: a first disk engaging a compressor section of a gas turbine; A second disk engaging with a turbine section of the gas turbine and having a through-hole formed to penetrate along the axial direction of the gas turbine; A third disk disposed between the first and second disks for transferring rotational torque applied to the second disk to the first disk; A damper ring disposed between the inner circumferential surface of the second disk and the outer circumferential surface of the tie rod of the gas turbine and fixing the second disk with respect to the radial direction of the tie rod; And a guide tube extending between the first and second discs.

Here, the gap between the third disk and the tie rod may be larger than the gap between the first and second disks and the tie rod.

The first and second discs may also include an inner rim opposite the tie rod, and the guide tube may be disposed between opposing inner rims of the first and second discs.

In addition, an air storage space may be defined by the first to third disks and the guide tube, and the guide tube may be formed with a plurality of air holes for allowing air to flow into the air storage space.

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 with the turbine section and having a through-hole formed therethrough along a longitudinal direction of the tie rod; A third disk disposed between the first and second disks for transferring rotational torque applied to the second disk to the first disk; And a damper ring which is disposed between the inner circumferential surface of the second disk and the outer circumferential surface of the tie rod of the gas turbine and fixes the second disk in the radial direction of the tie rod, Is formed to be larger than an interval between the first and second disks and the tie rod.

The guide tube may further include a guide tube extending between the first and second disks.

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 at least one disk is radially The vibration and noise generated in the disk assembly during the torque transmission process can be minimized.

Also, by forming one air storage space between the disks, the air flow can be simplified and the designing process can be facilitated. In addition, since the size of the air storage space can be maximized under a given volume, the supply of cooling air can be stabilized.

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.
4 is an enlarged cross-sectional view of a third 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 discharging a combustion gas containing a turbine v is provided at a rear side of the body 102. 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 rotational 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 discs 210 and 220 are formed to have substantially the same shape, while the third disc 230 is formed in such a manner that a hole through which the tie- Differs from the first and second discs in that the diameter of the hole 232 is larger. Hereinafter, specifically, the respective disks will be described.

The first disk 210 is formed to have a substantially I-shaped cross-sectional shape. Specifically, the first disk includes a disk-shaped disk body 212, an outer rim 214 formed on the outer periphery of the disk body so as to protrude from both sides along the axial direction of the tie rod, And an inner rim 216 protruding from both sides along the axial direction of the tie rod. Here, the outer rim 214 and the inner rim 216 are in contact with neighboring disks, so that the disks are prevented from rotating relative to each other. For example, the surfaces of the outer rim 214 and the inner rim 216 may comprise frictional surfaces and may be slidably engaged with the surface of the rotor disk or the surface of the third disk by the pressing force of the fixing nut. have. In addition, a plurality of protrusions may be formed on the surfaces of the outer rim 214 and the inner rim 216 to be engaged with neighboring discs.

The second disk 220 basically has a shape similar to that of the first disk. That is, the second disk 220 may have a substantially I-shaped cross-sectional shape. Like the first disk, the disk 220 may have a disk-shaped disk body 222, And an inner rim 226 protruding from both sides of the inner circumference of the disc body along the axial direction of the tie rod. The outer rim 224 and the inner rim 226 of the second disk 220 are also in contact with neighboring disks to prevent the disks from rotating relative to each other.

For example, the surfaces of the outer rim 224 and the inner rim 226 may be friction surfaces and may be combined with the surface of the turbine side rotor disk or the surface of the third disk by a pressing force of the fixing nut have. Also in the second disk, a plurality of protrusions may be formed on the surfaces of the outer rim 224 and the inner rim 226 to be fastened to neighboring disks.

Meanwhile, the third disk is formed to have a different shape from the first and second disks. As shown in FIG. 2, the third disc 230 is formed to have a substantially "T" shape, and thus does not include a portion corresponding to the inner rim of the first and second discs. However, the third disc 230 has an outer rim 234 such as the first and second discs, and the outer rim 234 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 diameter of the hole 232 through which the tie rod 150 passes is larger than that of the first and second discs. 2, the disc main body 212, 222 of the first and second discs, the inner rim 234 of the third disc, and the tie rod 150 form a space S1 ) Can be defined. The space S1 has a substantially donut shape in which the tie rod 150 is disposed at the center, and functions as an air storage space for temporarily storing the cooling air.

A gap S2 is formed between the inner rim 216 of the first disk 210 and the tie rod 150 in order to allow air to flow into the air storage space S1. The gap is formed such that compressed air drawn out from a specific position of the compressor section can be introduced into the air storage space S1. The air storage space also communicates with a through hole 222a formed in the disc main body 222 of the second disc 220. [

The through hole 222a functions as a nozzle for allowing air in the air storage space S1 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.

As shown, the first embodiment of the disc assembly includes a second disc having a relatively large inner diameter between two discs having an inner rim opposite the tie rod 150, So that the weight can be minimized. In particular, a tension ring 240 is fitted between the inner rim 226 of the second disk and the tie rod 150.

The tension ring 240 has a ring shape made of any material having elasticity. The upper portion of the cross section is in contact with the inner rim 226 and the lower portion 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 second 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, In order to allow cooling air to flow through the disc. However, in some cases, the tension ring may be provided on both the first and second discs, and the through hole 222a may be formed on both the first and second discs, Of the cooling air.

In addition, although the embodiment has a configuration in which a T-shaped disk is arranged between two I-shaped disks, the number and arrangement order of the disks may be arbitrarily changed. 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 as in the first embodiment denote the same elements, and a duplicate description thereof will be omitted.

Referring to FIG. 3, a guide tube 250 is additionally disposed between the inner rims 216 and 226 of the first and second disks. The guide tube 250 has a cylindrical shape spaced apart from the tie rod 150 and has both ends fixed between the inner rims 215 and 226 of the first and second disks. A plurality of ventilation holes 252 are formed in the guide tube 250 so that the air introduced through the gap S2 can be introduced into the air storage space S1.

The guide tube 250 serves to guide the flow of the cooling air. Basically, the guide tube 250 maintains a constant interval between the inner rims of the first and second disks. As a result, the overall rigidity of the disk assembly can be improved and the vibration can be further suppressed.

Meanwhile, the disk assembly may be formed to have the shape of the third embodiment as shown in FIG. Referring to FIG. 3, the third embodiment includes first to third disks 310, 320, and 330, and first and second disks 310 and 320, respectively, Disk bodies 312 and 322 and outer rims 314 and 324 formed on the outer circumferential side of the disk body. However, in the embodiment shown in FIG. 4, the first and second discs do not include the outer rims as shown in FIGS. 2 and 3, so that they have a generally "T" shape as a whole.

The third disk 330 has basically the same shape as the embodiment shown in FIGS. That is, the third disc 330 includes an outer rim 334 and a hole 332, and is fixed between the first and second discs. The embodiment shown in Fig. 4 has a relatively large rotational moment of inertia because the mass disposed radially inward in comparison with the first and second embodiments is relatively small. This has the advantage that stable operation is possible because the sensitivity to load fluctuation and fluctuation of conditions in the combustor is low.

Although not shown in FIG. 4, the third embodiment may be modified to include the guide tube as in the second embodiment.

Claims

A first disk engaging a compressor section of the gas turbine;
A second disk engaging with a turbine section of the gas turbine and having a through-hole formed to penetrate along the axial direction of the gas turbine;
A third disk disposed between the first and second disks for transferring rotational torque applied to the second disk to the first disk;
A tie rod disposed through the center of the compressor section, the first to third disks and the turbine section; And
And a damper ring which is disposed between the inner circumferential surface of the first disk or the second disk and the outer circumferential surface of the tie rod of the gas turbine and fixes the first disk or the second disk in the radial direction of the tie rod,
Wherein a distance between the third disk and the tie rod is larger than a distance between the first and second disks and the tie rod.

The method according to claim 1,
Wherein a radially outer side of the first and second disks is formed with an outer rim that engages the compressor section and the turbine section, respectively.

3. The method of claim 2,
Wherein the first and second disks are located radially inwardly of the outer rim and include an inner rim facing the tie rods.

The method of claim 3,
And the through-hole of the second disc is disposed between the outer rim and the inner rim.

The method of claim 3,
Wherein the damper ring is disposed between the inner rim and the tie rod.

The method according to claim 1,
An air storage space is defined by the opposite side surfaces of the first and second disks and the inner surface of the third disk and the air storage space functions as a storage space for temporarily storing air passing through the through hole Wherein the disk assembly comprises:

The method according to claim 6,
A gap is formed between the first disk and the tie rod, and the gap functions as an inlet for air to be introduced into the space.

A first disk engaging a compressor section of the gas turbine;
A second disk engaging with a turbine section of the gas turbine and having a through-hole formed to penetrate along the axial direction of the gas turbine;
A third disk disposed between the first and second disks for transferring rotational torque applied to the second disk to the first disk;
A damper ring disposed between the inner circumferential surface of the second disk and the outer circumferential surface of the tie rod of the gas turbine and fixing the second disk with respect to the radial direction of the tie rod; And
And a guide tube extending between the first and second disks, wherein air storage spaces are defined by the first to third disks and the guide tube, and air is introduced into the air storage space in the guide tube And a plurality of ventilation holes are formed in the disk assembly.

9. The method of claim 8,
Wherein a distance between the third disk and the tie rod is larger than a distance between the first and second disks and the tie rod.

9. The method of claim 8,
Wherein the first and second discs include an inner rim opposite the tie rod and the guide tube is disposed between opposing inner rims of the first and second discs.

delete

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.