JP2005009440A - Gas turbine and method for assembling the same - Google Patents

Abstract

A gas turbine having a plurality of turbine rotors and a method of assembling the same are provided.
A gas turbine having turbine rotors (9, 10) includes a high-pressure turbine casing (5) surrounding the high-pressure turbine rotor (9) and a low-pressure turbine casing (6) surrounding the low-pressure turbine rotor (10). The retainer ring 18 engaged and supported in the horizontal direction in either the high-pressure turbine casing 5 or the low-pressure turbine casing 6, and supported on the inner peripheral side of the retainer ring 18, between the rotating shafts of the turbine rotors 3 and 4. And a partition wall 15 for blocking.
[Selection] Figure 1

Description

[0001]
BACKGROUND OF THE INVENTION
The present invention relates to a gas turbine having a plurality of turbine rotors and an assembling method thereof.
[0002]
[Prior art]
Generally, in a gas turbine provided with a plurality of turbine rotors, the rotating shafts of adjacent turbine rotors are separated from each other. For this reason, some turbine casings are fitted and fixed with a partition wall between the rotating shafts of the turbine rotor inside the stationary blade located between the turbine rotors (see, for example, Patent Document 1). ).
[0003]
[Patent Document 1]
Japanese Examined Patent Publication No. 6-35807 [0004]
[Problems to be solved by the invention]
In general, the thermal expansion from the high-temperature and high-pressure working fluid or the cooling air causes the partition wall to heat out radially outward, whereas the stationary blade heats radially inward from the point of engagement with the casing. Elongation occurs. Therefore, as in the technique described in Patent Document 1, when the partition wall is fitted and firmly fixed to the inner peripheral side of the stationary blade fixed to the casing, the partition wall may be damaged due to high compressive stress due to hot elongation. There is. In addition, when the partition wall is damaged, in order to restore the partition wall in the technique described in Patent Document 1, it is necessary to remove the partition wall together with the stationary blade with which the partition wall is fitted from the casing. Since it is directly fixed, it is difficult to remove and assemble the partition wall, and a lot of labor and time are required for the work.
[0005]
An object of the present invention is to provide a gas turbine having a plurality of turbine rotors and a method for assembling the same, in which partition walls can be easily removed and assembled.
[0006]
[Means for Solving the Problems]
To achieve the above object, according to the present invention, in a gas turbine having a plurality of turbine rotors, among the plurality of turbine rotors, a high-pressure turbine casing that surrounds a high-pressure turbine rotor, and the plurality of turbine rotors, A low-pressure turbine casing that surrounds the low-pressure side turbine rotor; support means that is engaged and supported in a horizontal direction by either the high-pressure turbine casing or the low-pressure turbine casing; The partition wall which interrupts | blocks between the rotating shafts of this turbine rotor is provided.
[0007]
According to another aspect of the present invention, a gas turbine having a plurality of turbine rotors includes: a high-pressure turbine casing that surrounds a high-pressure turbine rotor of the plurality of turbine rotors; and a low-pressure turbine rotor of the plurality of turbine rotors. A surrounding low pressure turbine casing, a support means engaged and supported from the horizontal direction through a gap on the inner peripheral side of either the high pressure turbine casing or the low pressure turbine casing, and supported on the inner peripheral side of the support means And a partition wall that cuts off between the rotating shafts of the plurality of turbine rotors.
[0008]
In another aspect of the invention, the support means is supported by the low-pressure turbine casing.
[0009]
In another aspect of the invention, the support means is a retainer ring that supports a stationary blade positioned between the plurality of turbine rotors.
[0010]
In another aspect of the invention, the retainer ring is divided into two at least in the circumferential direction.
[0011]
In another aspect of the invention, a diaphragm is provided on the inner peripheral side of the stationary blade, and the partition is attached to the diaphragm.
[0012]
Another invention includes a compressed air introduction pipe that faces a cavity in the retainer ring via the high-pressure turbine casing or the low-pressure turbine casing.
[0013]
In another aspect of the invention, the compressed air introduction pipe extends through the retainer ring and further extends to a tip position of the stationary blade.
[0014]
According to another aspect of the present invention, there is provided an intermediate casing interposed between the high pressure turbine casing and the low pressure turbine casing, and an intermediate disposed in the intermediate casing and disposed between the high pressure turbine rotor and the low pressure turbine rotor. A duct.
[0015]
According to another aspect of the present invention, there is provided a gas turbine assembling method having a plurality of turbine rotors, wherein a partition wall that cuts off between the rotation shafts of the plurality of turbine rotors is integrated with a retainer ring in another place in advance. The retainer ring to which is attached is inserted into the low-pressure turbine casing in the axial direction, and the retainer ring is engaged and supported by the low-pressure turbine casing from the horizontal direction.
[0016]
DETAILED DESCRIPTION OF THE INVENTION
Hereinafter, a first embodiment of the present invention will be described with reference to the drawings.
The gas turbine of the present invention has a plurality of turbine rotors in the turbine, and rotates each turbine rotor with combustion gas generated by burning compressed air from the compressor together with fuel in a combustor to obtain rotational power. Is. The high-pressure turbine rotor is connected to the compressor rotor, and the rotational power obtained by the high-pressure turbine rotor is used as a driving force for the compressor. On the other hand, the low-pressure side turbine rotor is connected to, for example, a generator rotor, and when connected to the generator rotor, the rotational power obtained by the low-pressure side turbine rotor is converted into electric energy. In this way, by providing a plurality of turbine rotors, it becomes possible to rotate a compressor, a generator, etc. at different rotational speeds, reducing energy loss compared to a single-shaft gas turbine that does not divide the turbine rotor. It can be made to.
[0017]
FIG. 1 is a vertical sectional view in the axial direction of a turbine representing the main structure of the gas turbine according to the present embodiment, and FIG. 2 is a sectional view taken along the line II-II in FIG.
As shown in FIGS. 1 and 2, the gas turbine according to the present embodiment is a so-called two-shaft gas turbine, which includes a high-pressure turbine 1 and a low-pressure turbine 2. A high-pressure turbine rotor 3 and a low-pressure turbine rotor 4 that are separated from each other and can be rotated at different rotational speeds are provided. These turbine rotors 3 and 4 are respectively surrounded by a high-pressure turbine casing 5 and a low-pressure turbine casing 6.
[0018]
The turbine rotors 3 and 4 are rotating bodies that constitute a rotating shaft and are provided with at least one stage of turbine disks 9 and 10 that are radially provided with a plurality of powers 7 and 8 on the outer peripheral portion, and each has a gas path 11. It is driven to rotate by combustion gas from a flowing combustor (not shown). The high-pressure turbine rotor 3 is connected to a compressor rotor (not shown), and the low-pressure turbine rotor 4 is connected to a generator rotor (not shown). The rotational power obtained by the high-pressure turbine rotor 3 is compressed. The rotational power obtained by the low-pressure side turbine rotor 4 is converted into electric energy.
[0019]
The high-pressure turbine casing 5 and the low-pressure turbine casing 6 have an upper and lower divided structure as illustrated by the low-pressure turbine casing 6 in FIG. Are fastened with bolts via vertical flange portions 12 and 13 provided on the opposite end surfaces. Moreover, the shroud 14 is intermittently attached to each inner wall surface in the axial direction. In the present embodiment, the position of the rear end of the shroud 14a is set so that the upstream end of the low-pressure turbine casing 6, that is, the end facing the high-pressure turbine casing 5 is an axial gap between the shrouds 14a and 14b. The boundary between the turbine casing 5 and the low-pressure turbine casing 6 is used. In addition, although mentioned later for details, the retainer ring 18 (after-mentioned) is inserted in the axial direction gap | interval between this shroud 14a, 14b.
[0020]
The turbine disks (rotating shafts) 9 and 10 of the high-pressure turbine rotor 3 and the low-pressure turbine rotor 4 are separated from each other, but the turbine disks 9 and 10 are blocked by a partition wall 15. The fluid leakage between 9, 10 is prevented, and an appropriate pressure difference between the high pressure side and the low pressure side is ensured. The partition wall 15 is a substantially disk-shaped member having an integral structure. In the present embodiment, a simple flat plate-shaped member is illustrated, but the structure is not particularly limited. For example, a cooling air passage may be provided in the interior, a two-sheet structure may be used, or the air may be curved.
[0021]
The partition wall 15 is attached to a diaphragm 17 that is attached to the inside of a stationary blade (first-stage stationary blade of the low-pressure turbine 2) 16 located between the high-pressure turbine rotor 3 and the low-pressure turbine rotor 4. The stationary blade 16 includes a plurality of segment parts divided in the circumferential direction, and each segment part is attached to the inner wall of the retainer ring 18 with an outer ring 16a. A groove for attaching the outer ring 16a is provided inside the retainer ring 18, and the outer ring 16a is attached to the retainer ring 18 by fitting into the groove. The diaphragm 17 is also divided into a plurality of segment parts in the circumferential direction, and each segment part is fitted and attached to the inner ring 16 b of the corresponding stationary blade 16. Therefore, the partition wall 15 is supported via the stationary blade 16 and the diaphragm 17 on the inner peripheral side of the retainer ring 18 as a support means. The segment parts of the diaphragm 17 are sealed with packing (not shown).
[0022]
A cavity 19 formed between the retainer ring 18 and the outer ring 16 a of the stationary blade 16 is provided on the inner peripheral portion of the retainer ring 18, and a compressed air introduction pipe 20 faces the cavity 19. The tip of the compressed air introduction pipe 20 passes through the casing (low pressure turbine casing 6) and is inserted into a through hole 18a provided on the outer wall of the retainer ring 18 through the casing. The other end (not shown) of the compressed air introduction pipe 20 communicates with a bleed slit (not shown) provided in a compressed air flow path (not shown) of a compressor (not shown) via the outside of the casing. ing. On the other hand, the cavity 19 communicates with a cavity 22 in the diaphragm 17 via a flow path 21 in the stationary blade provided through the stationary blade 16 in the radial direction. At the front and rear of the diaphragm 17, orifices 17a and 17b for jetting compressed air are provided in gaps between the turbine disks 9 and 10, respectively.
[0023]
With the above-described flow path structure, the compressed air of a required pressure extracted from a bleed slit (not shown) is guided into the diaphragm 17 through a path of the compressed air introduction pipe 20 → the cavity 19 → the stationary vane flow path 21 → the cavity 22. Finally, it is ejected before and after the diaphragm 17 through the orifices 17a and 17b. A part of the compressed air ejected from the orifices 17a and 17b is directed radially outward, discharged to the gas path 11 as seal air between the turbine disks 9 and 10 and the diaphragm 17, respectively, and the flow directed radially inward is It is used for cooling the turbine disks 9 and 10 or for warming up the start-up.
[0024]
As shown in FIG. 2, the retainer ring 18 described above is supported by the low-pressure turbine casing 6 in this embodiment, and is incorporated in the upstream end portion of the low-pressure turbine casing 6 described above. In this embodiment, the retainer ring 18 has a vertically divided structure, and the upper half ring 18a and the lower half ring 18b are bolted to each other via flanges 18aa and 18ba. In FIG. 2, these flanges 18aa and 18ba protrude outward in the radial direction so as to substantially follow the horizontal center line of the retainer ring 18. However, the flanges 18aa and 18ba may protrude in the horizontal direction even if they are not in the vertical center position. On the other hand, the inner wall of the low-pressure turbine casing 6 is provided with a notch 23 at a position facing the flanges 18aa and 18ba so as to engage with the flanges 18aa and 18ba. That is, the retainer ring 18 is supported on the inner wall of the low-pressure turbine casing 6 from the horizontal direction by the flanges 18aa and 18ba being engaged and supported by the notch 23.
[0025]
At this time, in the present embodiment, a radial direction having a predetermined size is determined between the outer peripheral surface of the retainer ring 18 and the inner wall surface of the low-pressure turbine casing 6 in accordance with the temperature environment in the vicinity assumed during operation. A gap is provided. Therefore, although the retainer ring 18 falls by the radial gap, the gap is secured with the low-pressure turbine casing 6 over the entire circumference of the retainer ring 18 by supporting from the horizontal direction as described above. It can be done. The notch 23 is also formed between the flanges 18aa and 18ba with a gap in the radial direction and the vertical direction.
However, in the present embodiment, as shown in FIG. 2, the flanges 18aa and 18ba of the retainer ring 18 are configured to engage with the casing. However, the present invention is not limited to this. It is good also as a structure which is provided and it engages with the notch provided in the retainer ring 18 outer peripheral part. In addition, the flanges 18aa and 18ba and the protrusions do not necessarily have to be integrated with the retainer ring 18 and the casing, regardless of whether the retainer ring 18 or the casing is provided, and sufficient load resistance is structurally ensured. For example, it may be retrofitted by bolt fastening, welding, or a fitting structure as a separate member.
[0026]
FIG. 3 is a diagram schematically showing an assembling procedure of the partition wall portion in the gas turbine of the present embodiment.
In this embodiment, when assembling the partition wall 15, first, the low-pressure turbine 2 is installed at an appropriate place. As described above, since the low-pressure turbine casing 6 has a half-divided structure divided into upper and lower parts, first, the lower half casing of the low-pressure turbine casing 6 is installed at an appropriate place, and the shroud 14 and the stationary blades are assembled thereto. You may install the lower half casing which assembled | attached the shroud 14 and the stationary blade previously. Next, the pre-assembled low-pressure turbine rotor 4 is suspended in the lower half casing and supported by bearings (not shown). Thereafter, the upper half casing to which the shroud 14 and the stationary blades are assembled is put on the lower half casing, and the flanges are fastened with bolts to assemble the low-pressure turbine 2.
[0027]
In addition, before and after the assembly of the low-pressure turbine 2, the partition wall 15 is assembled to the diaphragm 17 at another location and integrated with the retainer ring 18, the stationary blade 16, and the diaphragm 17. In this case, since the retainer ring 18 has a circumferentially divided structure (half-split structure) in this embodiment, each segment of the stationary blade 16 is assembled to the lower half ring 18b, and the diaphragm 17 is further attached to the stationary blade 16. Assemble. The diaphragm 17 may be assembled to each segment of the stationary blade 16 and may be assembled to the retainer ring 18. Subsequently, the partition wall 15 is attached to the assembled diaphragm 17, and the upper half ring 18a of the retainer ring 18 to which the stationary blade 16 and the diaphragm 17 are attached is covered with this, and the flanges 18aa and 18ba of the retainer ring 18 are bolted.
[0028]
When the installation of the low-pressure turbine 2 and the attachment of the partition wall 15 to the retainer ring 18 are completed, the flanges 18aa and 18ba of the retainer ring 18 are inserted into the notches 23 of the low-pressure turbine casing 6 as shown in FIG. 3, the retainer ring 18 having the partition wall 15 attached thereto is inserted into the low-pressure turbine casing 6 from the axial direction. Thereby, the retainer ring 18 is supported by the low pressure turbine casing 6 from the horizontal direction. After that, the high-pressure turbine 1 is assembled before and after the above, the high-pressure turbine 1 is connected to the low-pressure turbine 2 in which the partition wall 15 has been assembled, and the vertical flange portions 12 and 13 are bolted to each other to fasten the turbine. Complete assembly. When the assembly on the compressor (not shown) side is finally completed, the compressed air introduction pipe 20 is inserted into the retainer ring 18 through the low-pressure turbine casing 6. For disassembly, the above procedure may be reversed.
[0029]
Next, functions and effects obtained by the present embodiment will be described sequentially.
(1) Facilitation of assembly and disassembly Here, as a comparative example with the present embodiment, a configuration in which the stationary blade 16 supporting the diaphragm 17 and the partition wall 15 is directly fixed to the casing is shown in FIG. However, in FIG. 4, the same reference numerals are given to the same parts as those in the previous drawings, and the description will be omitted.
In the comparative example of FIG. 4, the stationary blade 16 is fitted and directly attached to the shrouds 14a and 14b. During operation, the partition wall 15 extends radially outward and the stationary blade 16 extends radially inward from the shrouds 14a and 14b due to thermal effects of combustion gas and compressed air. As a result, in the structure in which the partition wall 15 is rigidly fixed to the stationary blade 16 tightly fixed to the shrouds 14a and 14b through the diaphragm 17, a large compressive stress is applied to the partition wall 15 and the stationary blade 16 to damage them. there is a possibility. When damaged, it is necessary to remove the bulkhead 15 together with the stationary blade 16 from the casing. However, in the structure of FIG. 4, it is not easy to remove the stationary blade 16 from the casing (strictly speaking, the shrouds 14a and 14b).
[0030]
On the other hand, in the present embodiment, as described above, the partition wall 15 that blocks between the rotating shafts of the high-pressure turbine rotor 3 and the low-pressure turbine rotor 4 is supported by the retainer ring 18 via the stationary blade 16 and the diaphragm 17. The retainer ring 18 is engaged and supported by the casing from the horizontal direction. As a result, when the partition wall 15 is assembled, the partition wall 15 is integrated with the retainer ring 18 and the stationary blade 16 at another location in advance, and the retainer ring 18 is inserted into the casing from the axial direction so as to engage with the casing. Easy assembly by the assembly method. The same applies to decomposition.
[0031]
As described above, since the partition 15 can be easily incorporated or removed, even when the partition 15 is damaged, the time and labor required for the assembly and disassembly work can be greatly reduced, and it can be recovered in a short time. Contributes to improved efficiency. Further, since the heat spread in the radial direction can be made uniform over the entire circumference in this way, the load applied to the compressed air introduction pipe 20 due to the thermal deformation of the retainer ring 18 and the like can be suppressed as much as possible, and the compressed air Deformation and damage of the introduction pipe 20 can be suppressed.
[0032]
Further, in the present embodiment, as described above, a radial gap is provided between the retainer ring 18 and the casing. The dimension of the notch 23 provided in the casing is also larger than the thickness and length of the flanges 18aa and 18ba of the retainer ring 18, and the flanges 18aa and 18ba are inserted into the notch 23 with a gap. It has become. Also by this, the retainer ring 18 can be easily inserted into the casing, and the assembling property and the disassembling property can be greatly improved.
[0033]
(2) Prevention of breakage of the partition wall As described above, in the configuration as in the comparative example of FIG. 4, a large compressive stress acts on the partition wall 15 and the stationary blade 16, so that the partition wall 15, the stationary blade 16, the diaphragm 17, etc. Easy to damage. On the other hand, in the present embodiment, the structure of the partition wall 15, the diaphragm 17, the stationary blade 16 and the retainer ring 18 tends to extend radially outward, but this thermal extension is provided between the retainer ring 18 and the casing. It is absorbed (allowed) by the gap. As described with reference to FIG. 2, since the retainer ring 18 is supported by the casing from the horizontal direction, a gap can be secured over the entire circumference of the retainer ring 18. As a result, the retainer ring 18, the stationary blade 16, the diaphragm 17 and the partition wall 15 attached to the retainer ring 18 are not restrained in thermal expansion over the entire circumferential direction, and the partition wall 15 is damaged due to the generation of thermal stress. Can be prevented. Therefore, it is possible to provide a highly reliable gas turbine with fewer defects.
[0034]
(3) Compressed air leakage prevention Further, in the comparative example shown in FIG. 4 above, the casing 30 is provided with a compressed air introduction hole 31, and the compressed air from the compressed air introduction hole 31 is placed between the shrouds 14a and 14b. It is introduced into the stationary blade 16 and the diaphragm 17 through the formed cavity 32. Therefore, there is a possibility that compressed air leaks between the stationary blade 16 and the shrouds 14 a and 14 b and between adjacent segments of the stationary blade 16.
[0035]
Therefore, in the present embodiment, as described above with reference to FIG. 1, the compressed air introduction pipe 20 is configured to pass through the casing and have the tip thereof face the retainer ring 18, thereby cooling or sealing. Compressed air can be directly introduced into the retainer ring 18, and leakage of the compressed air from the gap between the retainer ring 18 and the casing can be suppressed.
[0036]
In addition, the gas turbine of this invention is not limited to the aspect demonstrated above, A design change is possible suitably in the range which does not deviate from the technical idea of this invention. In short, it is only necessary that the supporting means for supporting the partition wall is supported by the casing from the horizontal direction.
Hereinafter, some modified examples of the present invention will be described with reference to FIGS. 5 and 6.
[0037]
(1) Modification 1
FIG. 5 is a diagram showing a modification example that further facilitates assembly and disassembly. That is, in FIG. 5, an intermediate casing 35 is interposed between the high pressure turbine casing 5 and the low pressure turbine casing 6. At both ends of the intermediate casing 35, flanges 36 and 37 are provided, and bolted to the flanges 12 and 13 of the high-pressure turbine casing 5 and the low-pressure turbine casing 6, respectively. An intermediate duct 39 is provided inside the intermediate casing 35 via a support member 38. The intermediate duct 39 is disposed between the high-pressure side turbine rotor 3 and the low-pressure side turbine rotor 4, and includes a double cylinder having an outer cylinder 39 a and an inner cylinder 39 b supported inside the outer cylinder 39 a via struts 40. It has a tube structure, and a flow path 41 constituting a part of the gas path 11 is formed between the outer cylinder 39a and the inner cylinder 39b. Other configurations are the same as those of the first embodiment described above, and the same reference numerals are given to the same parts as those in the previous drawings, and the description thereof is omitted.
[0038]
In the first embodiment described above, when the partition wall 15 is assembled (or removed) with the retainer ring 18, the high pressure turbine 1 and the low pressure turbine 2 must be connected or disassembled. At least one must be moved. In contrast, in the present embodiment, when the retainer ring 18 is removed, the intermediate casing 35 is removed, so that a sufficient space for removing the retainer ring 18 is created. Therefore, the high pressure turbine 1 and the low pressure turbine 2 are installed. The partition 15 can be easily disassembled as it is. Of course, also when installing, the retainer ring 18 is easily installed from between the high-pressure turbine 1 and the low-pressure turbine 2, and then the intermediate duct 39 is attached, so that the partition wall 15 can be easily formed while the high-pressure turbine 1 and the low-pressure turbine 2 remain installed. Can be incorporated. This configuration is also effective for various maintenance such as inspection.
[0039]
(2) Modification 2
FIG. 6 is a diagram showing a configuration that more reliably prevents leakage of compressed air for cooling or sealing. That is, in this modified example, as shown in FIG. 6, the compressed air introduction pipe 20 passes through the retainer ring 18, extends further radially inward, and extends to the position of the inner ring 16 b inside the stationary blade 16. The tip of the compressed air introduction pipe 20 directly faces the internal space of the diaphragm 17. Other configurations are the same as those in the first embodiment, and the same parts as those in the previous drawings are denoted by the same reference numerals and the description thereof is omitted.
[0040]
According to this modification, the same effect as that of the first embodiment can be obtained, and leakage of compressed air from the retainer ring 18 and the shrouds 14a and 14b and between adjacent segments of the stationary blade 16 can be prevented. The amount of leak of compressed air flowing through the compressed air introduction pipe 20 can be further reduced as compared with the first embodiment. Also in the present embodiment, as in the first embodiment described above, the thermal expansion of the retainer ring 18 and the stationary blade 16 is uniform over the entire circumference, so that a large load may be applied to the compressed air introduction pipe 20. Further, the compressed air introduction pipe 20 is not deformed.
[0041]
In the embodiment and each modification described above, the retainer ring 18 is used as a support means for supporting the partition wall 15 on the inner peripheral side, and the partition wall 8 is disposed on the inner peripheral side of the retainer ring 18 via the stationary blade 16 and the diaphragm 17. However, the present invention is not necessarily limited to this as long as the ease of assembling and disassembling, which is an essential effect of the present invention, is obtained. As long as assembling and disassembling is facilitated, the configuration may not be such that the partition 15 is attached via the stationary blade 16 or the diaphragm 17, but may be configured such that the partition is directly supported by the retainer ring 18, for example. Further, the support means need not be the retainer ring 18; It is also possible to use the wing 16 as a support means and omit the retainer ring 18. In these cases, the same effect is obtained.
[0042]
Further, in the first embodiment, a structure in which the retainer ring 18 is supported by the low-pressure turbine casing 6 is illustrated, but a structure supported by the high-pressure turbine casing 5 may be used. Although an example in which one partition 15 is provided has been described, a plurality of partitions may be provided. In addition, as long as the ease of assembly and disassembly, which is an essential effect of the present invention, is achieved, the compressed air introduction pipe 20 is not necessarily provided, and the compressed air need not be directly introduced into the retainer ring 18. In these cases, the same effect as described above can be obtained.
[0043]
【The invention's effect】
According to the present invention, in a gas turbine having a plurality of turbine rotors, removal and assembly of the partition walls can be facilitated. Further, the amount of leakage of compressed air for cooling or sealing can be reduced. Therefore, reliability can be improved.
[Brief description of the drawings]
FIG. 1 is a vertical sectional view in the axial direction of a turbine that represents a main part structure of a gas turbine according to a first embodiment of the present invention.
FIG. 2 is a cross-sectional view taken along the line II-II in FIG.
FIG. 3 is a view schematically showing an assembling procedure of partition walls in the gas turbine of the present invention.
FIG. 4 is a diagram illustrating a configuration of a comparative example with the present invention.
FIG. 5 is a diagram showing a main part structure of a first modification of the gas turbine of the present invention.
FIG. 6 is a view showing a main part structure of a second modification of the gas turbine of the present invention.
[Explanation of symbols]
3 High-pressure turbine rotor (turbine rotor)
4 Low pressure side turbine rotor (turbine rotor)
5 High-pressure turbine casing 6 Low-pressure turbine casing 9, 10 Turbine disk (rotary shaft)
15 Bulkhead 16 Stator vane 17 Diaphragm 18 Retainer ring (supporting means)
19 Cavity 20 Compressed air introduction pipe 35 Intermediate casing 39 Intermediate duct

Claims (10)

In a gas turbine having a plurality of turbine rotors,
Among the plurality of turbine rotors, a high-pressure turbine casing that surrounds the high-pressure side turbine rotor;
Among the plurality of turbine rotors, a low-pressure turbine casing surrounding the low-pressure side turbine rotor;
Support means engaged and supported from either the high-pressure turbine casing or the low-pressure turbine casing from the horizontal direction;
A gas turbine, comprising: a partition wall supported on an inner peripheral side of the support means and configured to block between rotation shafts of the plurality of turbine rotors. In a gas turbine having a plurality of turbine rotors,
Among the plurality of turbine rotors, a high-pressure turbine casing that surrounds the high-pressure side turbine rotor;
Among the plurality of turbine rotors, a low-pressure turbine casing surrounding the low-pressure side turbine rotor;
Support means engaged and supported from the horizontal direction through a gap on the inner peripheral side of either the high-pressure turbine casing or the low-pressure turbine casing;
A gas turbine, comprising: a partition wall supported on an inner peripheral side of the support means and configured to block between rotation shafts of the plurality of turbine rotors. 3. The gas turbine according to claim 1, wherein the support means is supported by the low-pressure turbine casing. The gas turbine according to any one of claims 1 to 3, wherein the support means is a retainer ring that supports a stationary blade positioned between the plurality of turbine rotors. The gas turbine according to claim 4, wherein the retainer ring is divided into at least two parts in a circumferential direction. 6. The gas turbine according to claim 4, wherein a diaphragm is provided on an inner peripheral side of the stationary blade, and the partition wall is attached to the diaphragm. The gas turbine according to any one of claims 4 to 6, further comprising a compressed air introduction pipe that faces a cavity in the retainer ring through the high-pressure turbine casing or the low-pressure turbine casing. The gas turbine according to claim 7, wherein the compressed air introduction pipe passes through the retainer ring and further extends to a tip position of the stationary blade. 9. The gas turbine according to claim 1, wherein an intermediate casing interposed between the high-pressure turbine casing and the low-pressure turbine casing, and the high-pressure turbine rotor and the low-pressure side provided in the intermediate casing. A gas turbine comprising: an intermediate duct disposed between the turbine rotor. In a method for assembling a gas turbine having a plurality of turbine rotors,
A partition that blocks between the rotating shafts of the plurality of turbine rotors is integrated with the retainer ring in another place in advance,
An assembly method comprising inserting a retainer ring to which the partition wall is attached into a low-pressure turbine casing in an axial direction, and engaging and supporting the retainer ring from the horizontal direction on the low-pressure turbine casing.

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