JP2002303156A - Gas turbine equipment - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a gas turbine equipment wherein a bearing for journaling a gas turbine shaft is mounted on a proper position, and the operation of the gas turbine shaft can be stabilized while keeping the sealability between a lubricant of the bearing and the working fluid. SOLUTION: In this gas turbine equipment, the gas turbine shaft is divided into at least one or more, a front gas turbine shaft 12c as one of the divided gas turbine shaft is formed coaxially and integrally with a compressor shaft 13, a bearing 21 for compressor and a bearing 22 for the front gas turbine are mounted to journal both ends of the front gas turbine shaft 12c, and further a bearing 31 for a rear gas turbine is mounted to journal the rear gas turbine shaft 32 as the other part of the divided gas turbine shaft.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a gas turbine facility applied to a power plant or an aero engine.

[0002]

2. Description of the Related Art As a gas turbine operated in a power plant or the like, for example, a gas turbine having a configuration shown in FIG. 8 is known. That is, the gas turbine shaft 2 housed in the gas turbine casing 1a and the air compressor casing 1b
The air compressor shaft 3 housed therein is provided coaxially,
A moving blade 5 provided on the gas turbine shaft 2 and a stationary blade 4 provided on the gas turbine casing 1a constitute a gas turbine stage 5a. An air compressor stage 7a is constituted by a stationary blade 6 provided on the air compressor casing 1b and a moving blade 7 provided on the air compressor shaft 3. A gas turbine combustor 8 is provided between the gas turbine stage 5a and the air compressor stage 7a, and the compressed air compressed by the air compressor stage 7a is supplied to the gas turbine combustor 8 to burn fuel. Then, the high-temperature combustion gas FG generated by the combustion is guided to the gas turbine stage 5 a via the transition piece (tail tube) 9, and the moving blade 5 is driven to rotate and the work is performed by the gas turbine shaft 2.

The gas turbine equipment for a power plant having such a configuration raises the temperature of the combustion gas emitted from the gas turbine combustor 8 to 1,300 ° C. or more from 1,100 ° C. to 1,300 ° C., thereby increasing the temperature. Accordingly, higher output and higher plant thermal efficiency are being developed.

[0004]

By the way, in recent gas turbine facilities, in consideration of a decrease in reserves of fossil fuels,
The development of a hydrogen gas turbine using hydrogen as fuel is underway. In this case, since the temperature of the combustion gas (steam) is high, it is difficult to perform the expansion work according to the design value with only one gas turbine from the viewpoint of the material strength. It is equipment. Moreover, the rotation speed of the gas turbine equipment on another shaft is relatively lower than the rotation speed of another gas turbine equipment, resulting in two different rotation speeds. The reason why the rotation speed of the separate gas turbine equipment was reduced is that it is difficult to withstand the centrifugal force generated during operation if the blades located in the last stage of the gas turbine are made longer, in terms of strength. Based on becoming.

[0005] Incidentally, the gas turbine equipment has a separate shaft 2.
In the case of the shaft type, it is necessary to secure a wider installation area, and furthermore, a control system is required for each axis, which causes erroneous operation due to the complexity of the system.

For this reason, when increasing the output and increasing the thermal efficiency of a plant by using, for example, hydrogen as fuel, the conventional gas turbine equipment shown in FIG. 8 is used as it is, and then the outlet side of the final stage of the gas turbine is used. Providing a new gas turbine casing for accommodating a gas turbine stage is advantageous in securing the installation area and simplifying the control system.

However, when connecting and extending a new gas turbine casing to an existing gas turbine casing, the gas turbine shaft becomes extremely long, so that it is necessary to improve the operation stability. In particular, it is necessary to improve the position of the bearing that supports the long gas turbine shaft and the sealing property between the lubricating oil of the bearing and water vapor as the working fluid.

The present invention has been made in view of the above circumstances. In order to increase the temperature of combustion gas or water vapor as a working fluid to an ultra-high temperature to achieve high output and high plant thermal efficiency, the gas turbine shaft is used. An object of the present invention is to provide a gas turbine facility that stabilizes the operation of a gas turbine shaft while maintaining the sealing performance between a bearing lubricating oil and a working fluid while arranging a bearing to be supported at an appropriate position.

[0009]

SUMMARY OF THE INVENTION In order to achieve the above object, a gas turbine system according to the present invention includes a compressor casing accommodating a compressor shaft and a gas turbine shaft accommodating the compressor shaft. In a gas turbine facility having a gas turbine combustor between the gas turbine casing and the gas turbine casing, the gas turbine shaft is divided into at least one or more, and one of the divided front gas turbine shafts is coaxially integrated with the compressor shaft. Along with providing a compressor bearing and a front gas turbine part bearing that support both ends thereof,
A bearing for a rear gas turbine section that supports the other of the divided rear gas turbine shafts is provided.

Further, the gas turbine equipment according to the present invention comprises:
In order to achieve the above object, as set forth in claim 2, a gas turbine facility including a gas turbine combustor between a compressor casing containing a compressor shaft and a gas turbine casing containing a gas turbine shaft. In the above, the gas turbine shaft is divided into at least one or more, one of the divided front gas turbine shafts is formed integrally coaxially with the compressor shaft, and a compressor bearing for supporting the compressor shaft side is provided. An inlet-side rear gas turbine section bearing and an outlet-side rear gas turbine section bearing that support both ends of the other divided rear gas turbine shaft are provided.

Further, the gas turbine equipment according to the present invention comprises:
In order to achieve the above object, a gas turbine facility having a gas turbine combustor between a compressor casing containing a compressor shaft and a gas turbine casing containing a gas turbine shaft as described in claim 3. , The gas turbine shaft is divided into at least one or more, and one of the divided front gas turbine shafts is formed coaxially and integrally with the compressor shaft, and a compressor bearing and a front gas turbine that support both ends thereof. And a bearing for the inlet-side rear gas turbine and a bearing for the outlet-side rear gas turbine that support both ends of the other split rear gas turbine shaft.

Further, the gas turbine equipment according to the present invention comprises:
In order to achieve the above object, as described in claim 4, a gas turbine casing accommodating a front gas turbine shaft and a rear gas turbine shaft is divided at an outlet side of the front gas turbine shaft, The flange is connected to a gas turbine casing accommodating the rear gas turbine shaft.

Further, the gas turbine equipment according to the present invention comprises:
In order to achieve the above object, as described in claim 5, a bearing for a front gas turbine section that supports a front gas turbine shaft and a bearing for a rear gas turbine section that supports a rear gas turbine shaft, At least one or more of the inlet side rear gas turbine section bearing and the outlet side rear gas turbine section bearing are formed so as to be surrounded by a gas turbine inner casing.

Further, the gas turbine equipment according to the present invention comprises:
In order to achieve the above object, a front gas turbine shaft bearing for supporting a front gas turbine shaft and an inlet-side rear gas turbine shaft for supporting a rear gas turbine shaft are supported. The bearing is formed by being surrounded by an intermediate gas turbine inner casing.

Further, the gas turbine equipment according to the present invention comprises:
In order to achieve the above object, the intermediate gas turbine inner casing is supported by the gas turbine casing with a casing stradde interposed therebetween.

Further, the gas turbine equipment according to the present invention comprises:
In order to achieve the above-mentioned object, as described in claim 8, the intermediate gas turbine inner casing has an upper half intermediate gas turbine inner casing with a horizontal joint surface of a flange for the intermediate gas turbine inner casing facing the inner diameter side. And a lower half intermediate gas turbine inner casing.

Further, the gas turbine equipment according to the present invention comprises:
In order to achieve the above-mentioned object, as described in claim 9, the flange for the intermediate gas turbine inner casing has a sealing plate mounted in the sealing groove.

Further, the gas turbine equipment according to the present invention comprises:
In order to achieve the above object, as described in claim 10, a front gas turbine section bearing that supports the front gas turbine shaft and a rear gas turbine section bearing that supports the rear gas turbine shaft, At least one or more of the inlet side rear gas turbine section bearing and the outlet side rear gas turbine section bearing are supported by the gas turbine inner casing with a gas turbine inner casing stradde interposed therebetween.

Further, the gas turbine equipment according to the present invention comprises:
In order to achieve the above object, as described in claim 11, a front gas turbine part bearing that supports the front gas turbine shaft and a rear gas turbine part bearing that supports the rear gas turbine shaft, The inlet-side rear gas turbine section bearing and the outlet-side rear gas turbine section bearing include a bearing body and a sliding section, and form a lubricating oil supply passage at the center of the bearing body and the sliding section. A lubricating oil / seal air mixture recovery passage, a seal air supply passage, and a working fluid / seal air mixture recovery passage are formed starting from the lubricating oil supply passage toward at least one of the outside and the inside.

Further, the gas turbine equipment according to the present invention comprises:
In order to achieve the above object, as described in claim 12, the bearing body has a labyrinth on a side facing each of the front gas turbine shaft and the rear gas turbine shaft.

[0021]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Hereinafter, embodiments of a gas turbine facility according to the present invention will be described with reference to the drawings and reference numerals attached to the drawings.

FIG. 1 is a half sectional view in which the upper half of the upper half and the lower half of the gas turbine equipment according to the present invention is sectioned.

The gas turbine equipment according to the present embodiment has a front gas turbine shaft 12c in a gas turbine casing 10 and a compressor casing 11 formed as a continuous unit.
And the compressor shaft 13 are accommodated coaxially.

The gas turbine equipment includes a gas turbine rotor blade 14 installed on the front gas turbine shaft 12c and a gas turbine stationary blade 15 engaged with the gas turbine casing 10.
And constitute the gas turbine stage 16 with
A compressor stage 19 is constituted by a compressor rotor blade 17 implanted on the compressor shaft 13 and a compressor stationary blade 18 engaged with the compressor casing 11.

A plurality of gas turbine combustors 20 in an annular arrangement are provided between the gas turbine stage 16 and the compressor stage 19, and air or hydrogen compressed by the compressor stage 19 is supplied to perform combustion. The generated high-temperature combustion gas or steam working fluid WF is guided to the gas turbine stage 16 via the transition piece (tail tube) 20a, where the gas turbine rotor blades 14 are driven to rotate. The work is performed by the gas turbine shaft 12c.

In the gas turbine equipment having such a configuration, in the present embodiment, the gas turbine section 12 is divided into a front gas turbine section 12a and a rear gas turbine section 12b, while the front gas Turbine shaft 12
c and the compressor shaft 13 are coaxially integrated, a compressor bearing 21 and a front gas turbine bearing 22 are provided at both ends, and one rear gas turbine shaft 32 is mounted on the rear gas turbine shaft 32 of the rear gas turbine unit 12b having a small number of stages. Turbine bearing 3
1 is provided.

That is, in this embodiment, a compressor bearing 21 for supporting the compressor shaft 13 is provided on the inlet side of the compressor casing 11, and the final gas turbine in the gas turbine casing 10 of the front gas turbine section 12a is provided. A front gas turbine section bearing 22 that supports the front gas turbine shaft 12c at the outlet side of the paragraph 16 is provided, that is, a so-called two-sided support structure is provided.

In this embodiment, a gas turbine inner casing 23 forming a passage for the working flow WF is provided on the outlet side of the front gas turbine section bearing 22, and the gas turbine inner casing 23 is connected to the front gas turbine. A gas turbine casing of a rear gas turbine section 12b that accommodates a gas turbine stage 27 composed of a gas turbine rotor blade 25 and a gas turbine stationary blade 26 while providing a casing stradder 24 supported by the gas turbine casing 10 of the turbine section 12a. 28 are connected via a flange 29.

Further, in the present embodiment, a rear gas turbine provided with a gas turbine inner casing 30 forming a passage for a working fluid WF at an outlet side of a gas turbine stage 27 housed in a gas turbine casing 28 of the rear gas turbine section 12b. And the rear gas turbine unit 12b.
A so-called cantilever support structure for supporting the rear gas turbine shaft 32.

FIG. 2 is a sectional view taken along the line AA of FIG.

The gas turbine casing 10 of the front gas turbine section 12a is divided into an upper gas turbine casing 10a and a lower gas turbine casing 10b at the horizontal joint surface of the flange 35, and the casing stradder 24 is interposed. Gas turbine inner casing 23
It is configured to support. The gas turbine casing 28 of the rear gas turbine section 12b has the same configuration as described above.

The gas turbine inner casing 23
Is divided into an upper half gas turbine inner casing 23a and a lower half gas turbine inner casing 23b at the horizontal joint surface of the gas turbine inner casing flange 33 projecting toward the gas turbine shaft 12, and the front gas turbine shaft There is provided a gas turbine inner casing strut 34 that supports the front gas turbine section bearing 22 that supports the shaft 12c.

FIG. 7 is a view taken in the direction of arrows BB in FIG.
It is a half cut sectional view.

The front gas turbine section bearing 22 includes a bearing body 52 and a sliding portion 53.

The front gas turbine section bearing 22 is
A lubricating oil supply passage 54 is provided at the center of the front gas turbine shaft 12c.
The lubricant oil / seal air mixture recovery passages 55a and 55b and the seal air supply passages 56a and 56
b and working fluid / seal air mixture recovery passage 57
While each of a and 57b is formed toward the front gas turbine shaft 12c, labyrinths 58a and 58b are provided so as to face the front gas turbine shaft 12c. The rear gas turbine section bearing 31 has the same configuration as described above.

As described above, in the present embodiment, the compressor shaft 13 and the front gas turbine shaft 12c, which are coaxially integrated, are provided with the so-called both-end-supported compressor bearing 21 and the front gas turbine unit bearing 22. , Front gas turbine bearing 2
2 is divided into an upper half gas turbine inner casing 23a and a lower half gas turbine inner casing 23b, and the upper half gas turbine inner casing 23a and the lower half gas turbine inner casing 23b are divided into two. Of the front gas turbine section 12b, and is fixed by a gas turbine internal casing flange 33 protruding toward the front gas turbine section bearing 22 while the front gas turbine section bearing 22 is fixed. Of the front gas turbine shaft 12c.
In addition, the compressor shaft 13 can be operated stably, and the lubricating oil supplied to the front gas turbine section bearing 22 and the working fluid WF can be reliably prevented from being mixed.

In this embodiment, a rear gas turbine shaft 32 having a gas turbine inner casing 30 and a rear gas turbine shaft bearing 32 having a gas turbine inner casing 30 are provided on a rear gas turbine shaft 32 having a small number of gas turbine stages 27. Since it is supported, the rear gas turbine shaft 32 of the rear gas turbine section 12b can be operated stably.

FIG. 3 is a half sectional view showing a second embodiment of the gas turbine equipment according to the present invention, in which an upper half portion is sectioned. The same components as those of the first embodiment are denoted by the same reference numerals.

In the gas turbine equipment according to this embodiment, the gas turbine section 12 is divided into a front gas turbine section 12a and a rear gas turbine section 12b, and the gas turbine casing 10 and the rear section of the front gas turbine section 12a are divided. The gas turbine casing 28 of the gas turbine section 12b is connected to the gas turbine casing 28 by the flange 29, and the front gas turbine shaft 12c and the compressor shaft 13 having a small number of stages are coaxially integrated with each other, and the compressor bearing 21 is provided on the compressor inlet side. While a so-called cantilevered configuration is provided, an inlet-side rear gas turbine section bearing 36 and an outlet-side rear gas turbine section bearing 37 are provided at both ends of a rear gas turbine shaft 32 having a large number of stages. This is a so-called two-sided support structure.

The other components, the support structure and the seal structure of the inlet-side rear gas turbine section bearing 36 and the outlet-side rear gas turbine section bearing 37 are the same as those of the first embodiment. Is omitted.

As described above, in this embodiment, the so-called cantilevered compressor bearing 21 is mounted on the coaxially integrated compressor shaft 13 and the front gas turbine shaft 12c having a small number of stages of the front gas turbine section 12a. In addition to the above, the rear gas turbine shaft 32 having a large number of paragraphs of the rear gas turbine
A so-called double-sided bearing 3 for the inlet-side rear gas turbine section
6 and the outlet side rear gas turbine section bearing 37, the front gas turbine shaft 1 of the front gas turbine section 12a is provided.
The stable operation can be performed on each of the rear gas turbine shaft 32 of the rear gas turbine section 12c and the rear gas turbine section 12b.

FIG. 4 is a half sectional view showing a third embodiment of the gas turbine equipment according to the present invention, in which an upper half portion is sectioned. The same components as those of the first embodiment are denoted by the same reference numerals.

The gas turbine equipment according to this embodiment includes a front gas turbine shaft 38 and a rear gas turbine shaft 39 housed in a gas turbine casing 10 and coaxially integrated with the compressor shaft 13.

In the gas turbine equipment according to the present embodiment, a casing stradder 24 is interposed between a front gas turbine shaft 38 and a rear gas turbine shaft 39 at an intermediate portion of the gas turbine casing 10 and supported. And an intermediate gas turbine inner casing 40,
The gas turbine inner casing 30 is also provided on the outlet side of the rear gas turbine shaft 39.

A front gas turbine shaft 38 coaxially integrated with the compressor shaft 13 has a front gas turbine stage 41 composed of a gas turbine rotor blade 25 and a gas turbine stationary blade 26.
Equipped with a front gas turbine section bearing 22 on the final exit side of
Along with the compressor bearing 21 provided on the compressor shaft 13, a so-called both-end support structure is provided.

The rear gas turbine shaft 39 is provided with an inlet-side rear gas turbine section bearing 43 and an outlet-side rear gas turbine section bearing 44 at both ends of the inlet side and the outlet side. It has a configuration. Note that the rear gas turbine shaft 39 is connected to the gas turbine rotor blade 25.
And a gas turbine stationary blade 26.

FIG. 5 is a cross-sectional view taken along the line CC of FIG.

The intermediate portion of the gas turbine casing 10 is
At the horizontal joint surface of the flange 35, the upper gas turbine casing 10a and the lower gas turbine casing 10b are divided into two parts, and the intermediate gas turbine inner casing 46 is supported with the casing stradde 24 interposed therebetween. .

The intermediate gas turbine inner casing 4
6 is a horizontal joint surface of an intermediate gas turbine casing flange 49 protruding toward the inner diameter side, which is divided into an upper half intermediate gas turbine inner casing 47 and a lower half intermediate gas turbine inner casing 48 and is divided into two parts. A sealing groove 50 is provided in a casing flange 49 and a seal plate 51 is mounted.

As shown in FIG. 6, the sealing plate 51
It is made of a member such as copper having one side end formed in a notch shape.

As described above, in the present embodiment, the front gas turbine shaft 38 and the rear gas turbine shaft 39 coaxially integrated with the compressor shaft 13 are housed in the gas turbine casing 10, and the front portion coaxially integrated with the compressor shaft 13. The gas turbine shaft 38 is supported at both ends by a bearing 21 for the compressor and a bearing 22 for the front gas turbine unit, and is provided on each of the inlet side and the outlet side of the rear gas turbine shaft 39. The bearing 43 for the inlet-side rear gas turbine unit and the bearing 45 for the outlet-side rear gas turbine unit have a so-called two-sided support structure, so that the front gas turbine shaft 38 and the rear unit are coaxially integrated with the compressor shaft 13. The gas turbine shaft 39 can be operated stably.

In this embodiment, the flange 49 for the intermediate gas turbine inner casing of the intermediate gas turbine inner casing 46 provided between the front gas turbine shaft 38 and the rear gas turbine shaft 39 coaxially integrated with the compressor shaft. Since the sealing plate 51 is mounted in the sealing groove 50, the lubricating oil supplied to the bearing and the working fluid WF are prevented from being mixed with each other, and the sealing can be reliably performed.

[0053]

As described above, in the gas turbine equipment according to the present invention, the gas turbine shaft housed in the gas turbine casing is divided into at least one or more, and the divided gas turbine shaft is supported at an appropriate position. A bearing is provided, and the divided gas turbine shafts supported by the bearings are divided into so-called cantilever supports and both-end supports, so that the divided gas turbine shafts can be operated stably.

Further, the gas turbine equipment according to the present invention
Since the bearing and the inner casing of the intermediate gas turbine are provided with the sealing means, it is possible to reliably prevent the lubricating oil of the bearing from being mixed into the working fluid.

[Brief description of the drawings]

FIG. 1 is a half sectional view showing a first embodiment of a gas turbine facility according to the present invention, and showing a cross section of an upper half portion.

FIG. 2 is a cross-sectional view taken along the line AA of FIG.

FIG. 3 is a half sectional view showing a second embodiment of the gas turbine equipment according to the present invention, in which an upper half portion is sectioned;

FIG. 4 is a half sectional view showing a third embodiment of the gas turbine equipment according to the present invention, in which an upper half portion is sectioned;

FIG. 5 is a cross-sectional view as viewed from the direction of arrows CC in FIG. 4;

FIG. 6 is a partially enlarged view of a portion D in FIG. 5;

FIG. 7 is a cross-sectional view as viewed from the direction of arrows BB in FIG. 2;

FIG. 8 is a half cross-sectional view of the upper half of the conventional gas turbine equipment.

[Explanation of symbols]

 1a Gas Turbine Casing 1b Air Compressor Casing 2 Gas Turbine Shaft 3 Air Compressor Shaft 4 Stator Blade 5 Moving Blade 5a Gas Turbine Stage 6 Stator Blade 7 Moving Blade 7a Air Compressor Stage 8 Gas Turbine Combustor 9 Transition Piece 10 Gas Turbine Casing Reference Signs List 10a Upper half gas turbine casing 10b Lower half gas turbine casing 11 Compressor casing 12 Gas turbine section 12a Front gas turbine section 12b Rear gas turbine section 12c Front gas turbine shaft 13 Compressor shaft 14 Gas turbine rotor blade 15 Gas turbine stationary blade Reference Signs List 16 Gas turbine stage 17 Compressor rotor blade 18 Compressor stationary blade 19 Compressor stage 20 Gas turbine combustor 20a Transition piece 21 Compressor bearing 22 Front gas turbine part bearing 23 Gas turbine inner casing 23 a Upper half gas turbine inner casing 23b Lower half gas turbine inner casing 24 Casing strut 25 Gas turbine rotor blade 26 Gas turbine stationary blade 27 Gas turbine stage 28 Gas turbine casing 29 Flange 30 Gas turbine inner casing 31 Rear gas turbine part bearing 32 Rear Gas Turbine Shaft 33 Gas Turbine Inner Casing Flange 34 Gas Turbine Inner Casing Strut 35 Flange 36 Inlet Rear Gas Turbine Bearing 37 Outlet Rear Gas Turbine Bearing 38 Front Gas Turbine Shaft 39 Rear Gas Turbine Shaft Reference Signs List 40 Intermediate gas turbine inner casing 41 Front gas turbine section 42 Bearing for front gas turbine section 43 Bearing for inlet side rear gas turbine section 44 Bearing for outlet side rear gas turbine section 45 Rear gas turbine section 46 Intermediate gas turbine inner casing 47 Upper half intermediate gas turbine inner casing 48 Lower half intermediate gas turbine inner casing 49 Intermediate gas turbine inner casing flange 50 Seal groove 51 Seal plate 52 Bearing body 53 Sliding part 54 Lubrication Oil supply passage 55a, 55b Lubricating oil / seal air mixture recovery passage 56a, 56b Seal air supply passage 57a, 57b Working fluid / seal air mixture recovery passage 58a, 58b Labyrinth

Claims (12)

[Claims] In a gas turbine facility having a gas turbine combustor between a compressor casing containing a compressor shaft and a gas turbine casing containing a gas turbine shaft, the gas turbine shaft is divided into at least one or more. Then, one of the divided front gas turbine shafts is formed coaxially and integrally with the compressor shaft, and a compressor bearing and a front gas turbine portion bearing that support both ends thereof are provided,
A gas turbine facility comprising a rear gas turbine part bearing that supports the other of the divided rear gas turbine shafts. 2. In a gas turbine facility having a gas turbine combustor between a compressor casing containing a compressor shaft and a gas turbine casing containing a gas turbine shaft, the gas turbine shaft is divided into at least one or more. One of the divided front gas turbine shafts is formed coaxially and integrally with the compressor shaft, and a compressor bearing for supporting the compressor shaft side is provided. A gas turbine facility comprising an inlet-side rear gas turbine section bearing and an outlet-side rear gas turbine section bearing that are supported. 3. In a gas turbine facility having a gas turbine combustor between a compressor casing accommodating a compressor shaft and a gas turbine casing accommodating a gas turbine shaft, the gas turbine shaft is divided into at least one or more. Then, one of the divided front gas turbine shafts is formed coaxially and integrally with the compressor shaft, and a compressor bearing and a front gas turbine portion bearing that support both ends thereof are provided,
A gas turbine facility comprising an inlet-side rear gas turbine section bearing and an outlet-side rear gas turbine section bearing that support both ends of the other divided rear gas turbine shaft. 4. A gas turbine casing accommodating a front gas turbine shaft and a rear gas turbine shaft, divided at an outlet side of the front gas turbine shaft, and a gas turbine casing accommodating the rear gas turbine shaft and a flange. The gas turbine equipment according to claim 1, wherein the gas turbine equipment is connected. 5. A bearing for a front gas turbine section that supports a front gas turbine shaft, a bearing for a rear gas turbine section that supports a rear gas turbine shaft, a bearing for an inlet-side rear gas turbine section, and an outlet-side rear gas. Of the turbine bearings,
The gas turbine equipment according to any one of claims 1 to 3, wherein at least one or more is surrounded by a gas turbine inner casing. 6. A front gas turbine section bearing that supports the front gas turbine shaft and an inlet side rear gas turbine section bearing that supports the rear gas turbine shaft are formed to be surrounded by an intermediate gas turbine inner casing. The gas turbine equipment according to claim 3, wherein 7. The gas turbine equipment according to claim 6, wherein the intermediate gas turbine inner casing is supported by the gas turbine casing with a casing stradde interposed therebetween. 8. The intermediate gas turbine inner casing is divided into an upper half intermediate gas turbine inner casing and a lower half intermediate gas turbine inner casing with a horizontal joint surface of the intermediate gas turbine inner casing flange facing the inner diameter side as a boundary. The gas turbine equipment according to claim 6, wherein 9. The gas turbine equipment according to claim 8, wherein the flange for the intermediate gas turbine inner casing has a sealing plate mounted in a sealing groove. 10. A bearing for a front gas turbine section for supporting a front gas turbine shaft, a bearing for a rear gas turbine section for supporting a rear gas turbine shaft, a bearing for an inlet-side rear gas turbine section, and an outlet-side rear gas. The gas turbine equipment according to claim 1, wherein at least one or more of the turbine section bearings are supported by the gas turbine inner casing with a gas turbine inner casing stradde interposed therebetween. 11. A bearing for a front gas turbine section that supports a front gas turbine shaft, a bearing for a rear gas turbine section that supports a rear gas turbine shaft, a bearing for an inlet-side rear gas turbine section, and an outlet-side rear gas. The bearing for a turbine unit includes a bearing body and a sliding portion, and a lubricant oil supply passage is formed at the center of the bearing body and the sliding portion. Lubricating oil / seal air mixture recovery passage,
4. The gas turbine equipment according to claim 1, wherein a seal air supply passage and a working fluid / seal air mixture recovery passage are formed. 12. The gas turbine equipment according to claim 11, wherein the bearing body has a labyrinth on a side facing each of the front gas turbine shaft and the rear gas turbine shaft.