Gas turbine module, gas turbine plant including the same, method of unloading gas turbine module, and method of exchanging gas turbine module

A gas turbine module includes a gas turbine that has a gas turbine rotor and a turbine shell; an inlet plenum that is connected to an inlet of the gas turbine; an exhaust plenum that is connected to an exhaust of the gas turbine; an enclosure that covers the gas turbine; and a common base on which the gas turbine, the inlet plenum, the exhaust plenum, and the enclosure are mounted. When moving the gas turbine, the gas turbine module is moved together.

BACKGROUND OF THE INVENTION

Field of the Invention

The present disclosure relates to a gas turbine module including a gas turbine, a gas turbine plant including the same, a method of unloading a gas turbine module, and a method of exchanging a gas turbine module.

Priority is claimed on Japanese Patent Application No. 2019-219761, filed Dec. 4, 2019, the content of which is incorporated herein by reference.

Description of Related Art

When inspecting a gas turbine, it is necessary to isolate a plurality of components constituting the gas turbine and then inspect each component. Therefore, the inspection period of the gas turbine becomes long. However, an operator has a desire to make the operation period of the gas turbine as long as possible.

Patent Document 1 below proposes a method of exchanging a gas turbine in operation with another gas turbine of the same type. Patent Document 1 discloses a method of separating a compressor and a turbine that constitute the gas turbine and then individually unloading the compressor and the turbine.

PATENT DOCUMENTS

SUMMARY OF THE INVENTION

In the technique described in Patent Document 1, by exchanging the gas turbine in operation with the gas turbine of the same type, it is possible to prevent the gas turbine from being stopped for a long period due to inspection and repair of the gas turbine. However, the operator has a desire to facilitate the exchange work of the gas turbine and to shorten a work period.

An object of the present disclosure is to provide a technique capable of facilitating the exchanging work of the gas turbine and shortening the work period.

A method of unloading a gas turbine module according to an aspect of the present disclosure for achieving the above-described object involves moving the following gas turbine module.

The gas turbine module includes a gas turbine that has a gas turbine rotor capable of rotating about an axis, and a turbine shell which covers the gas turbine rotor and in which an inlet and an exhaust are formed; an inlet plenum that is connected to the inlet of the gas turbine and is configured to guide air from an inlet duct into the gas turbine; an exhaust plenum that is connected to the exhaust of the gas turbine and is configured to guide exhaust gas from the gas turbine to an exhaust duct; an enclosure that covers the gas turbine; and a common base on which the gas turbine, the inlet plenum, the exhaust plenum, and the enclosure are mounted and which is connected to a gas turbine foundation.

A method of moving a gas turbine module according to the aspect includes executing the steps including a connection release step of releasing a connection between the common base and the gas turbine foundation, and releasing connections between the gas turbine module and a plurality of connection objects that are connected to the gas turbine module and constitute a part of a gas turbine plant; a module raising step of lifting the gas turbine module from the gas turbine foundation after the connection release step; a moving equipment disposition step of disposing moving equipment that is configured to move the gas turbine module in a gap between the common base and the gas turbine foundation during the module raising step; a module lowering step of ending the module raising step after the moving equipment disposition step and placing the gas turbine module on the moving equipment; and an unloading step of driving the moving equipment after the module lowering step and moving the gas turbine module.

In a method of exchanging a gas turbine module according to an aspect of the present disclosure for achieving the above-described object, the method of unloading a gas turbine module according to the above-described aspect is executed and a loading method of loading a no. 2 gas turbine module different from a no. 1 gas turbine module which is the gas turbine module is executed.

The no. 2 gas turbine module includes a no. 2 gas turbine that has a no. 2 gas turbine rotor capable of rotating about an axis, and a no. 2 turbine shell which covers the no. 2 gas turbine rotor and in which a no. 2 inlet and a no. 2 exhaust are formed; a no. 2 inlet plenum that is connected to the no. 2 inlet of the no. 2 gas turbine and is configured to guide air from the inlet duct into the no. 2 gas turbine; a no. 2 exhaust plenum that is connected to the no. 2 exhaust of the no. 2 gas turbine and is configured to guide exhaust gas from the no. 2 gas turbine to the exhaust duct; a no. 2 enclosure that covers the no. 2 gas turbine; and a no. 2 common base on which the no. 2 gas turbine, the no. 2 inlet plenum, the no. 2 exhaust plenum, and the no. 2 enclosure are mounted and which is connected to the gas turbine foundation. The no. 2 gas turbine module is capable of being connected to the plurality of connection objects that were connected to the no. 1 gas turbine module.

The loading method includes executing the steps including a no. 2 moving equipment disposition step of disposing the moving equipment on the gas turbine foundation; a loading step of driving the moving equipment after the no. 2 gas turbine module is placed on the moving equipment and moving the no. 2 gas turbine module to a location on the gas turbine foundation where the no. 1 gas turbine module was present; a no. 2 module raising step of lifting the no. 2 gas turbine module from the moving equipment after the loading step; a moving equipment removing step of removing the moving equipment from above the gas turbine foundation during the no. 2 module raising step; a no. 2 module lowering step of ending the no. 2 module raising step after the moving equipment removing step and placing the no. 2 gas turbine module on the gas turbine foundation; and a connection step of connecting the no. 2 common base and the gas turbine foundation to each other and connecting the no. 2 gas turbine module and the plurality of connection objects to each other.

A gas turbine module according to an aspect of the present disclosure for achieving the above-described object includes a gas turbine that has a gas turbine rotor capable of rotating about an axis, and a turbine shell which covers the gas turbine rotor and in which an inlet and an exhaust are formed; an inlet plenum that is connected to the inlet of the gas turbine and is configured to guide air from an inlet duct into the gas turbine; an exhaust plenum that is connected to the exhaust of the gas turbine and is configured to guide exhaust gas from the gas turbine to an exhaust duct; an enclosure that covers the gas turbine; a gas turbine base on which the gas turbine and the inlet plenum are mounted; and a common base on which the gas turbine base, the enclosure, and the exhaust plenum are mounted.

A gas turbine plant according to an aspect of the present disclosure for achieving the above-described object includes the gas turbine module according to the above-described aspect; inlet rotating equipment that has a rotor and is disposed more on a no. 1 axial side where the inlet is present with respect to the exhaust in an axial direction in which the axis extends than the gas turbine module; and an inlet coupling that is configured to connect the rotor of the inlet rotating equipment and an end of the gas turbine rotor on the no. 1 axial side to each other. An inlet flange is formed at an end of the gas turbine rotor on the no. axial 1 side. The inlet coupling has a no. 1 flange capable of being connected to the inlet flange and a no. 2 flange capable of being connected to the rotor of the inlet rotating equipment. In a state in which the no. 1 flange of the inlet coupling is connected to the inlet flange, the no. 2 flange of the inlet coupling is located more on the no. 1 axial side than the inlet plenum.

A gas turbine plant according to another aspect of the present disclosure for achieving the above-described object includes the gas turbine module according to the above-described aspect; exhaust rotating equipment that has a rotor and is disposed more on a no. 2 axial side where the exhaust is present with respect to the inlet in an axial direction in which the axis extends than the gas turbine module; and an exhaust coupling that is configured to connect the rotor of the exhaust rotating equipment and an end of the gas turbine rotor on the no. 2 axial side to each other. An exhaust flange is formed at an end of the gas turbine rotor on the no. 2 axial side. The exhaust coupling has a no. 1 flange capable of being connected to the exhaust flange and a no. 2 flange capable of being connected to the rotor of the exhaust rotating equipment. In a state in which the no. 1 flange of the exhaust coupling is connected to the exhaust flange, the no. 2 flange of the exhaust coupling is located more on the no. 2 axial side than the exhaust plenum.

According to the gas turbine module, the method of moving a gas turbine module, and the method of exchanging a gas turbine module of the present disclosure, the exchanging work of the gas turbine can be easily performed, and the work period can be shortened.

DETAILED DESCRIPTION OF THE INVENTION

Hereinafter, a gas turbine module, a method of moving a gas turbine module, and a method of exchanging a gas turbine module according to an embodiment of the present disclosure will be described in detail with reference to the drawings.

[Gas Turbine and Gas Turbine Plant Including the Same]

A gas turbine and a gas turbine plant including the same of the present embodiment will be described with reference toFIGS. 1 and 2.

As shown inFIG. 1, the gas turbine plant of the present embodiment includes a no. 1 gas turbine module M1, an inlet duct101, an exhaust duct102, inlet rotating equipment110, exhaust rotating equipment120, lube oil supply equipment131, an ACC enclosure130, a plant building140that covers these, and control equipment150that controls the operations of these. Although the control equipment150may be disposed in the plant building140, the control equipment is basically disposed in a control enclosure outside the plant building140.

The no. 1 gas turbine module M1includes a gas turbine10, an inlet plenum60, an exhaust plenum61, a load compartment65, an enclosure66, a ventilation system67, a gas turbine base80, and a common base85.

The gas turbine10of the present embodiment is a two-shaft gas turbine. The gas turbine10includes a compressor20that compresses air A to generate compressed air, a plurality of combustors30that combust fuel F in the compressed air to generate combustion gas Gc, a high pressure turbine40that is driven by the combustion gas Gc from the plurality of combustors30, a low pressure turbine45that is driven by the combustion gas Gc exhausted from the high pressure turbine40, a discharge casing16, an exhaust casing50, an inlet bearing55, and an exhaust bearing56.

The compressor20includes a compressor rotor21that rotates about an axis Ar, a compressor casing22that covers an outer peripheral side of the compressor rotor21, and inlet guide vane equipment (IGV equipment)25that controls a flow rate of air that is sucked into the compressor casing22. In the following, a direction in which the axis Ar extends is referred to as an axial direction Da, a circumferential direction about the axis Ar is simply referred to as a circumferential direction Dc, and a direction perpendicular to the axis Ar is referred to as a radial direction Dr. Further, one side in the axial direction Da is referred to as an axial upstream side (or a no. 1 axis Ar side) Dau, and a side opposite to the axial upstream side is referred to as an axial downstream side (or a no. 2 axis Ar side) Dad. Further, a side closer to the axis Ar in the radial direction Dr is referred to as a radial direction inner side Dri, and a side opposite to the radial direction inner side is referred to as a radial direction outer side Dro.

The compressor casing22has an inlet23for sucking the air and a discharge24for discharging the compressed air. The inlet23is formed at an end of the compressor casing22on the axial upstream side Dau, and the discharge24is formed at an end of the compressor casing22on the axial downstream side Dad. The IGV equipment25includes a vane26disposed on the inlet23side in the compressor casing22, and a driver27that drives the vane26.

The high pressure turbine40is disposed on the axial downstream side Dad of the compressor20. The high pressure turbine40includes a high pressure turbine rotor41that rotates about the axis Ar, and a high pressure turbine casing42that covers an outer peripheral side of the high pressure turbine rotor41.

The low pressure turbine45is disposed on the axial downstream side Dad of the high pressure turbine40. The low pressure turbine45includes a low pressure turbine rotor46that rotates about the axis Ar, and a low pressure turbine casing47that covers an outer peripheral side of the low pressure turbine rotor46. The low pressure turbine casing47is connected to an end of the high pressure turbine casing42on the axial downstream side Dad.

The exhaust casing50is connected to an end of the low pressure turbine casing47on the axial downstream side Dad. The exhaust casing50includes an exhaust diffuser51. The exhaust diffuser51includes a cylindrical outer diffuser510centered on the axis Ar and an inner diffuser51iwhich is cylindrical about the axis Ar and is disposed on the radial direction inner side Dri of the outer diffuser51o. A diffuser area52through which exhaust gas Gex exhausted from the low pressure turbine45passes is formed between an inner peripheral side of the outer diffuser510and an outer peripheral side of the inner diffuser51i. A portion defined by an edge of the outer diffuser510on the axial downstream side Dad and an edge of the inner diffuser51ion the axial downstream side Dad forms an exhaust53.

The discharge casing16is disposed between the compressor casing22and the high pressure turbine casing42in the axial direction Da, and connects the compressor casing22and the high pressure turbine casing42to each other. The compressed air discharged from the discharge24of the compressor20flows into the discharge casing16.

The plurality of combustors30are provided in the discharge casing16. The plurality of combustors30are connected to a fuel supply source through fuel piping31. The fuel piping31includes main fuel piping31aconnected to the fuel supply source and a plurality of pieces of fuel piping for combustors31bbranched from the main fuel piping31a. The fuel piping for combustors31bis provided for each of the plurality of combustors30, and each is connected to the corresponding one combustor30. The main fuel piping31ais provided with a main fuel control valve32a. The plurality of pieces of fuel piping for combustors31bare each provided with a fuel control valve for a combustor32b. The fuel F from the fuel piping31is supplied to the combustor30, and the compressed air in the discharge casing16flows into the combustor. The combustor30combusts the fuel F in the compressed air to generate the combustion gas Gc. The combustion gas Gc flows into the high pressure turbine casing42and drives the high pressure turbine40.

The compressor rotor21and the high pressure turbine rotor41are located on the same axis Ar and are connected to each other to form a no. 1 rotor11a. The low pressure turbine rotor46constitutes a no. 2 rotor11b. The no. 2 rotor11bis not mechanically connected to the no. 1 rotor11a. Therefore, the no. 2 rotor11bcan rotate independently of the rotation of the no. 1 rotor11a. In other words, the low pressure turbine rotor46can rotate independently of the rotation of the high pressure turbine rotor41. A gas turbine rotor11includes the no. 1 rotor11aand the no. 2 rotor11b. An inlet flange13is formed at an end of the gas turbine rotor11on the axial upstream side Dau, in other words, at an end of the no. 1 rotor11aon the axial upstream side Dau. Further, an exhaust flange14is formed at an end of the gas turbine rotor11on the axial downstream side Dad, in other words, at an end of the no. 2 rotor11bon the axial downstream side Dad. Note that both of the inlet flange13and the exhaust flange14are connection flanges.

The inlet bearing55supports a portion of the gas turbine rotor11on the axial upstream side Dau to be capable of rotatably supporting the gas turbine rotor11. Further, the exhaust bearing56supports a portion of the gas turbine rotor11on the axial downstream side Dad to be capable of rotatably supporting the gas turbine rotor11.

A turbine shell15is configured to include the compressor casing22, the discharge casing16, the high pressure turbine casing42, the low pressure turbine casing47, and the exhaust casing50. The inlet23of the compressor casing22constitutes an inlet of the turbine shell15. Further, the exhaust53of the exhaust casing50constitutes an exhaust of the turbine shell15.

The inlet plenum60is connected to the inlet duct101and is connected to the inlet23of the turbine shell15. The air A that is sucked by the compressor20flows into the inlet duct101. In the inlet duct101, an upstream side portion related to the flow of the air A is provided with an inlet filter, for example. In the inlet duct101, and in a downstream side portion related to the flow of the air A, the air A flows in the radial direction Dr with respect to the axis Ar. The inlet plenum60smoothly guides the air from the inlet duct101into the compressor casing22. Specifically, the inlet plenum60gradually converts the flow of the air A from the inlet duct101in the radial direction Dr into a flow in the axial direction Da. Further, the inlet plenum60distributes the air A from the inlet duct101substantially evenly in the circumferential direction Dc in the compressor casing22. The inlet flange13and the inlet bearing55are located on the radial direction inner side Dri of the inlet plenum60.

The exhaust plenum61is connected to the exhaust duct102and is connected to the exhaust53of the turbine shell15. The exhaust gas Gex exhausted from the exhaust casing50flows through the exhaust plenum61and the exhaust duct102. In the exhaust duct102, and in an upstream side portion related to the flow of the exhaust gas Gex, the exhaust gas Gex flows in the radial direction Dr with respect to the axis Ar. The exhaust plenum61guides the exhaust gas Gex exhausted from the exhaust casing50to the exhaust duct102. The exhaust plenum61gradually converts the flow of the exhaust gas Gex exhausted from the exhaust casing50into a flow in the radial direction Dr. The exhaust plenum61includes an exhaust gas guide62and an exhaust plenum casing63. The exhaust gas guide62is connected to the edge of the inner diffuser51ion the axial downstream side Dad, in other words, is connected to a part of the exhaust53of the turbine shell15, and causes a direction of the flow of the exhaust gas Gex that has passed through the diffuser area52to gradually face the radial direction outer side Dro. The exhaust plenum casing63covers portions of the inner diffuser51iand the outer diffuser510on the axial downstream side Dad, and the exhaust gas guide62. The exhaust plenum casing63is connected to the exhaust duct102.

The load compartment65is located more on the axial downstream side Dad than the exhaust plenum61and is connected to the exhaust plenum61. The load compartment65partitions an area defined by the inner diffuser51iof the exhaust casing50and the exhaust gas guide62of the exhaust plenum61on the radial direction inner side Dri from the outside. This area forms an exhaust bearing area64. The exhaust flange14and the exhaust bearing56are located in the exhaust bearing area64. It can be said that the exhaust flange14and the exhaust bearing56are disposed on the radial direction inner side Dri of the exhaust plenum61.

Cooling air from the outside is supplied into the exhaust bearing area64. The exhaust bearing56in the exhaust bearing area64is cooled by the cooling air.

The enclosure66covers the gas turbine10as shown inFIGS. 1 and 2A to 2C. On the other hand, the enclosure66does not cover the inlet plenum60and the exhaust plenum61.

Therefore, the enclosure66does not cover the inlet23of the gas turbine10which is connected to the inlet plenum60and the exhaust53of the gas turbine10which is connected to the exhaust plenum61. Further, the enclosure66does not cover the inlet flange13and the inlet bearing55disposed on the radial direction inner side Dri of the inlet plenum60. Further, the enclosure66does not cover the exhaust flange14and the exhaust bearing56disposed on the radial direction inner side Dri of the exhaust plenum61.

The ventilation system67is provided above the enclosure66. The ventilation system67ventilates the air inside the enclosure66and prevents the temperature inside the enclosure66from becoming high.

The inlet plenum60and the gas turbine10are mounted on the gas turbine base80. The gas turbine base80includes an upper surface81on which the inlet plenum60and the gas turbine10are mounted, and a pair of side surfaces82. The upper surface81of the gas turbine base80extends in a horizontal direction. As shown inFIG. 2C, the upper surface81is a rectangle whose longitudinal direction is the axial direction Da. One side surface82of the pair of side surfaces82is connected to one long side of a pair of long sides of the rectangular upper surface81. Further, the other side surface82is connected to the other long side of the pair of long sides of the rectangular upper surface81. Therefore, both of the pair of side surfaces82extend in the axial direction Da and are parallel to each other.

Here, a direction that is a horizontal direction and is perpendicular to the axis Ar is referred to as a side direction Ds. In the side direction Ds, one side is referred to as a no. 1 side direction side Ds1and the other side is referred to as a no. 2 side direction side Ds2. The position of the gas turbine10in the side direction Ds of the axis Ar is the center between the position of the one side surface82and the position of the other side surface82in the side direction Ds.

The one side surface82and the other side surface82of the gas turbine base80are each provided with a no. 1 trunnion83aand a no. 2 trunnion83b. The no. 2 trunnion83bis disposed more on the axial downstream side Dad than the no. 1 trunnion83a. The no. 1 trunnion83aand the no. 2 trunnion83bprotrude from the side surface82of the gas turbine base80in the side direction Ds. The no. 1 trunnion83aprovided on the one side surface82and the no. 1 trunnion83aprovided on the other side surface82have the same position in the axial direction Da. Further, the no. 2 trunnion83bprovided on the one side surface82and the no. 2 trunnion83bprovided on the other side surface82have the same position in the axial direction Da. Each of the trunnions83aand83bserves to receive a load that is generated when the gas turbine base80is lifted.

As shown inFIGS. 1 and 2A to 2C, the gas turbine base80, the enclosure66, the exhaust plenum61, and the load compartment65are mounted on the common base85. The common base85includes an upper surface86on which the gas turbine base80, the enclosure66, the exhaust plenum61, and the load compartment65are mounted, and a pair of side surfaces87. The upper surface86of the common base85extends in the horizontal direction. As shown inFIG. 2C, the upper surface86is a rectangle whose longitudinal direction is the axial direction Da. One side surface87of the pair of side surfaces87is connected to one long side of a pair of long sides of the rectangular upper surface86. Further, the other side surface87is connected to the other long side of the pair of long sides of the rectangular upper surface86. Therefore, both of the pair of side surfaces87extend in the axial direction Da and are parallel to each other. The position of the gas turbine10in the side direction Ds of the axis Ar is a center between the position of the one side surface87and the position of the other side surface87in the side direction Ds. Note that the side direction Ds is also a direction along the upper surface81of the gas turbine base80or the upper surface86of the common base85and perpendicular to the axis Ar.

The one side surface87and the other side surface87of the common base85are each provided with a no. 1 trunnion88aand a no. 2 trunnion88b. The no. 2 trunnion88bis disposed more on the axial downstream side Dad than the no. 1 trunnion88a. The no. 1 trunnion88aand the no. 2 trunnion88bprotrude from the side surface87of the common base85in the side direction Ds. The no. 1 trunnion88aprovided on the one side surface87and the no. 1 trunnion88aprovided on the other side surface87have the same position in the axial direction Da. Further, the no. 2 trunnion88bprovided on the one side surface87and the no. 2 trunnion88bprovided on the other side surface87have the same position in the axial direction Da. Each of the trunnions88aand88bserves to receive a load that is generated when the common base85is lifted.

The no. 1 trunnion83aof the gas turbine base80is disposed at a position overlapping the no. 1 trunnion88aof the common base85in the axial direction Da. Further, the no. 2 trunnion83bof the gas turbine base80is disposed at a position overlapping the no. 2 trunnion88bof the common base85in the axial direction Da.

The above-described gas turbine base80is connected to the common base85by a plurality of connection parts (for example, bolts and nuts)84, as shown inFIG. 1. The common base85is disposed on a gas turbine foundation145. The common base85is fixed to the gas turbine foundation145by a plurality of anchor bolts89. The anchor bolts89are not welded to the common base85so that they can be easily removed from the common base85.

The above-described enclosure66covers the gas turbine10and all of the portions of the gas turbine base80except the portion on which the inlet plenum60is mounted.

As shown inFIG. 1, the no. 1 gas turbine module M1further includes an inlet support90, an exhaust support91, an IGV support92, an exhaust plenum support93, and a load compartment support94. Both of the inlet support90and the exhaust support91support the gas turbine10. The inlet support90is fixed to the upper surface81of the gas turbine base80and supports the inlet plenum60. The inlet support90supports the inlet plenum60, thereby supporting the gas turbine10connected to the inlet plenum60. The exhaust support91is fixed to the upper surface81of the gas turbine base80and supports a portion of the gas turbine10on the axial downstream side Dad. The IGV support92is fixed to the upper surface81of the gas turbine base80and supports the IGV equipment25. The exhaust plenum support93is fixed to the upper surface86of the common base85and supports the exhaust plenum61. The load compartment support94is fixed to the upper surface86of the common base85and supports the load compartment65.

The inlet rotating equipment110is, for example, a starter motor for starting rotation of the gas turbine rotor11that is stopped. The inlet rotating equipment110is disposed on the axial upstream side Dau of the no. 1 gas turbine module M1. The inlet rotating equipment110includes a rotor111that rotates about the axis Ar and a casing113that covers the rotor111. An end of the rotor111on the axial downstream side Dad protrudes from the casing113to the axial downstream side Dad. A flange112is formed at the end of the rotor111on the axial downstream side Dad. An inlet coupling115is disposed between the flange112of the inlet rotating equipment110and the inlet flange13of the gas turbine rotor11. The inlet coupling115includes a no. 1 flange116capable of being connected to the inlet flange13of the gas turbine rotor11and a no. 2 flange117capable of being connected to the flange112of the inlet rotating equipment110. The rotor111of the inlet rotating equipment110and the gas turbine rotor11are connected to each other via the inlet coupling115. Therefore, the inlet flange13of the gas turbine rotor11can be connected to the rotor111of the inlet rotating equipment110via the inlet coupling115. The no. 2 flange117of the inlet coupling115is located more on the axial upstream side Dau than the inlet plenum60. Note that all of the flange112, the no. 1 flange116, and the no. 2 flange117are connection flanges.

The lube oil supply equipment131supplies lube oil to the inlet bearing55and the exhaust bearing56via the lube oil piping132.

The ACC enclosure130covers various ACCs including the inlet rotating equipment110and the lube oil supply equipment131.

The exhaust rotating equipment120is, for example, rotating equipment that is driven by the gas turbine10. Specifically, the exhaust rotating equipment120is, for example, a generator, a rotary compressor, a rotary pump, or the like. The exhaust rotating equipment120is disposed on the axial downstream side Dad of the no. 1 gas turbine module M1. The exhaust rotating equipment120includes a rotor121that rotates about the axis Ar and a casing123that covers the rotor121. An end of the rotor121on the axial upstream side Dau protrudes from the casing123to the axial upstream side Dau. A flange122is formed at the end of the rotor121on the axial upstream side Dau. An exhaust coupling125is disposed between the flange122of the exhaust rotating equipment120and the exhaust flange14of the gas turbine rotor11. The exhaust coupling125includes a no. 1 flange126capable of being connected to the exhaust flange14of the gas turbine rotor11and a no. 2 flange127capable of being connected to the flange122of the exhaust rotating equipment120. The rotor121of the exhaust rotating equipment120and the gas turbine rotor11are connected to each other via the exhaust coupling125. Therefore, the exhaust flange14of the gas turbine rotor11can be connected to the rotor121of the exhaust rotating equipment120via the exhaust coupling125. The no. 2 flange127of the exhaust coupling125is located more on the axial downstream side Dad than the exhaust plenum61and the load compartment65. Note that all of the flange122, the no. 1 flange126, and the no. 2 flange127are connection flanges.

The control equipment150is connected to the IGV equipment25, the main fuel control valve32a, the plurality of fuel control valves for combustors32b, the lube oil supply equipment131, and the like by various cables151.

The plant building140is built on a plant foundation146, as shown inFIG. 3. The gas turbine foundation145is located inside the plant building140and is provided on the plant foundation146. The plant building140has an opening141. The opening141is provided on the no. 1 side direction side Ds1of the no. 1 gas turbine module M1. The width of the opening141in the axial direction Da is larger than the width of the no. 1 gas turbine module M1in the axial direction Da.

[Methods of Unloading and Loading Gas Turbine Module, and Method of Exchanging Gas Turbine Module for Executing These]

Methods of unloading and loading a gas turbine module, and a method of exchanging a gas turbine module for executing these according to the present embodiment will be described with reference toFIGS. 4 to 13.

The method of exchanging a gas turbine module is executed by executing the methods of unloading and loading a gas turbine module. First, the method of unloading the no. 1 gas turbine module M1will be described with reference to a flowchart shown inFIG. 4.

In the method of unloading the no. 1 gas turbine module M1, first, a connection release step (S11) is executed. In the connection release step (S11), a connection C1(seeFIG. 1) between the common base85and the gas turbine foundation145is released. Specifically, the plurality of anchor bolts89that fix the common base85to the gas turbine foundation145are removed. Since the anchor bolts89are not welded to the common base85as described above, the anchor bolts89can be removed from the common base85without cutting a part of the common base85or the anchor bolts89. Further, a connection with a plurality of connection objects connected to the no. 1 gas turbine module M1is released. All of the plurality of connection objects form a part of the gas turbine plant. Examples of the connection objects include the inlet coupling115and the exhaust coupling125which are connected to the gas turbine rotor11, the inlet duct101, the exhaust duct102, the fuel piping31which is connected to the combustor30, the lube oil piping132which is connected to each of the inlet bearing55and the exhaust bearing56, the various cables151which are connected to the fuel control valves32aand32bor the IGV equipment25, and the like. Therefore, in the connection release step (S11), a connection C3between the no. 2 flange117of the inlet coupling115and the flange112of the rotor111of the inlet rotating equipment110(seeFIG. 1) is released and a connection C5between the no. 2 flange127of the exhaust coupling125and the flange122of the rotor121of the exhaust rotating equipment120is released. Further, a connection C6between the inlet plenum60and the inlet duct101, a connection C7between the exhaust plenum61and the exhaust duct102, a connection between the combustor30and the fuel piping31, a connection of each of the inlet bearing55and the exhaust bearing56with the lube oil piping132, and a connection of each of the fuel control valves32aand32bor the IGV equipment25with each of the cables151are released.

In the connection release step (S11), a connection C2between the gas turbine rotor11and the inlet coupling115(seeFIG. 1) and a connection C4between the gas turbine rotor11and the exhaust coupling125are released as necessary.

In the method of unloading the no. 1 gas turbine module M1, next, a module raising step (S12) is executed. In the module raising step (S12), the no. 1 gas turbine module M1is lifted from the gas turbine foundation145. At this time, as shown inFIG. 6, a jack166is disposed between each of the plurality of trunnions88aand88bprovided on the common base85and the gas turbine foundation145. Then, as shown inFIG. 7, the jack166lifts the no. 1 gas turbine module M1.

In the method of unloading the no. 1 gas turbine module M1, next, a moving equipment disposition step (S13) is executed. In the moving equipment disposition step (S13), first, as shown inFIG. 8, auto transport equipment165is disposed outside the plant building140at a position along the opening141of the plant building140. A level of an upper surface of the auto transport equipment165is substantially the same as a level of the gas turbine foundation145in the plant building140. Next, as shown inFIGS. 9 and 10, moving equipment160that moves the no. 1 gas turbine module M1is disposed in a gap between the common base85and the gas turbine foundation145. The moving equipment160includes a pair of rails161and moving carts162that move on the rails161. In disposing the moving equipment160, first, the rails161are disposed such that the rails161extend from below the common base85to the auto transport equipment165which is a moving destination in the no. 1 side direction side Ds1. As shown inFIG. 8, the rail161includes a rail for indoor161ain the plant building140and a rail on transport equipment161bon the auto transport equipment165. The rail for indoor161ais basically installed permanently, and the rail on transport equipment161bis installed temporarily. However, it may be appropriately selected whether the rail for indoor161ais permanently installed or temporarily installed, and whether the rail on transport equipment161bis temporarily installed or permanently installed. As described above, the level of the upper surface of the auto transport equipment165is substantially the same as the level of the gas turbine foundation145in the plant building140. A cross-sectional shape of the rail on transport equipment161bis substantially the same as a cross-sectional shape of the rail for indoor161a. Therefore, an upper surface level of the rail on transport equipment161bis substantially the same as an upper surface level of the rail for indoor161a. As a drive source for moving the moving carts162, an electric motor, a linear electric actuator, a hydraulic cylinder, or the like can be considered. Next, the moving carts162are disposed on the rail161.

When the moving equipment disposition step (S13) ends, a module lowering step (S14) is executed. In the module lowering step (S14), the module raising step (S12) ends, and the no. 1 gas turbine module M1is placed on the moving carts162of the moving equipment160, as shown inFIG. 11. Specifically, after lowering a drive end of the jack166, the jack166is removed from between each of the trunnions88aand88band the gas turbine foundation145. As a result, the no. 1 gas turbine module M1is lowered, and the no. 1 gas turbine module M1is placed on the moving cart162.

When the module lowering step (S14) ends, an unloading step (S15) is executed. In the unloading step (S15), as shown inFIG. 12, the moving carts162are driven, and the no. 1 gas turbine module M1is moved along the rail161to above the auto transport equipment165.

With this, the method of unloading the no. 1 gas turbine module M1according to the present embodiment ends.

As described above, when the unloading of the no. 1 gas turbine module M1ends, the no. 1 gas turbine module M1is moved to, for example, a repair factory together with the auto transport equipment165and the moving carts162, and the no. 1 gas turbine module M1is inspected and repaired in the repair factory. Further, when the unloading of the gas turbine module M1ends, a method of loading a no. 2 gas turbine module M2is executed in parallel with or prior to the inspection and repair of the no. 1 gas turbine module M1in the repair factory. The method of loading the no. 2 gas turbine module M2will be described with reference to a flowchart shown inFIG. 5.

Here, the no. 2 gas turbine module M2is a gas turbine module that can replace the no. 1 gas turbine module M1that is the unloaded no. 1 gas turbine module M1. Specifically, the no. 2 gas turbine module M2is a gas turbine module that can be smoothly connected to the plurality of connection objects without modifying the plurality of connection objects were connected to the no. 1 gas turbine module M1. Therefore, the no. 2 gas turbine module M2may be a gas turbine module of exactly the same type as the no. 1 gas turbine module M1. In addition, as long as the no. 2 gas turbine module M2can be smoothly connected to the plurality of connection objects without modifying the plurality of connection objects, the no. 2 gas turbine module may be partially different from the no. 1 gas turbine module M1(for example, in an internal blade shape, IGV equipment, or the like). Note that, like the no. 1 gas turbine module M1, the no. 2 gas turbine module M2also includes the gas turbine base (a no. 2 gas turbine base)80and the common base (a no. 2 common base)85in addition to the gas turbine (a no. 2 gas turbine)10, the inlet plenum (a no. 2 inlet plenum)60, and the exhaust plenum (a no. 2 exhaust plenum)61.

In the method of loading the no. 2 gas turbine module M2, first, a no. 2 moving equipment disposition step (S21) is executed. In the no. 2 moving equipment disposition step (S21), first, as shown inFIG. 12, auto transport equipment165on which the no. 2 gas turbine module M2is mounted is disposed outside the plant building140at a position along the opening141of the plant building140. Then, in a case in which the moving carts162are not disposed between the no. 2 gas turbine module M2and the auto transport equipment165, the no. 2 gas turbine module M2is lifted and the moving carts162are disposed between the no. 2 gas turbine module M2and the auto transport equipment165.

When the no. 2 moving equipment disposition step (S21) ends, a loading step (S22) is executed. In the loading step (S22), the moving carts162are driven and the no. 2 gas turbine module M2is moved along the rail161to a region on the gas turbine foundation145where the no. 1 gas turbine module M1was installed.

When the loading step (S22) ends, a no. 2 module raising step (S23) is executed. In the no. 2 module raising step (S23), the no. 2 gas turbine module M2is lifted from the moving carts162. At this time, as shown inFIG. 13, alignment adjust equipment167and the jack166are disposed between each of the plurality of trunnions88aand88bprovided on the common base85and the gas turbine foundation145. Note that a jack is disposed on the alignment adjust equipment167. Then, the jack166lifts the no. 2 gas turbine module M2.

In the method of loading the no. 2 gas turbine module M2, next, a moving equipment removing step (S24) is executed. In the moving equipment removing step (S24), the moving equipment160is removed from above the gas turbine foundation145. That is, the moving carts162and the rails161are removed from above the gas turbine foundation145.

When the moving equipment removing step (S24) ends, an alignment adjust step (S25) is executed. As shown inFIG. 13, the above-described alignment adjust equipment167includes an adjust table167aformed of a low friction material such as a fluororesin and a support table167bfor supporting the adjust table167a. In the alignment adjust step (S25), positions of the no. 2 gas turbine module M2in the horizontal direction, specifically, the position in the axial direction Da and the position in the side direction Ds, are adjusted.

When the no. 2 gas turbine module M2is moved in the horizontal direction, the adjust table167ais moved in the horizontal direction relative to the support table167bby an electric actuator, a hydraulic cylinder, or the like. As a result, the adjust table167a, the jack166on the adjust table167a, and the no. 2 gas turbine module M2on the jack166are moved in the horizontal direction.

When the alignment adjust step (S25) ends, a no. 2 module lowering step (S26) is executed. In the no. 2 module lowering step (S26), the no. 2 module raising step (S23) ends, and the no. 2 gas turbine module M2is placed on the gas turbine foundation145. Specifically, after lowering a drive end of the jack166, the jack166is removed from between each of the trunnions88aand88band the gas turbine foundation145. Further, the alignment adjust equipment167is removed from above the gas turbine foundation145. As a result, the no. 2 gas turbine module M2is lowered, and the no. 2 gas turbine module M2is placed on the gas turbine foundation145.

When the no. 2 module lowering step (S26) ends, a connection step (S27) is executed. In the connection step (S27), the common base85of the no. 2 gas turbine module M2and the gas turbine foundation145are connected to each other. Specifically, the common base85of the no. 2 gas turbine module M2is fixed to the gas turbine foundation145using the plurality of anchor bolts89. Furthermore, the above-described plurality of connection objects are connected to the no. 2 gas turbine module M2. In the connection step (S27), the no. 1 flange116of the inlet coupling115and the inlet flange13of the gas turbine rotor11are connected to each other, and the no. 2 flange117of the inlet coupling115and the flange112of the rotor111of the inlet rotating equipment110are connected to each other. Furthermore, in the connection step (S27), the no. 1 flange126of the exhaust coupling125and the exhaust flange14of the gas turbine rotor11are connected to each other, and the no. 2 flange127of the exhaust coupling125and the flange122of the rotor121of the exhaust rotating equipment120are connected to each other.

With this, the method of loading the no. 2 gas turbine module M2according to the present embodiment ends. As a result, the method for exchanging a gas turbine module according to the present embodiment ends, and the no. 1 gas turbine module M1is exchanged with the no. 2 gas turbine module M2.

In the present embodiment, since the entire gas turbine10is mounted on the common base85, the common base85is moved together with the gas turbine10, and thus it is not necessary to partially isolate the gas turbine10, which can facilitate the unloading work and the loading work and shorten the work time. Therefore, in the present embodiment, the exchange work of the gas turbine10can be easily performed, and the work period can be shortened.

In the present embodiment, since the no. 1 gas turbine module M1is moved in the side direction Ds in the unloading step (S11), even if the rotors111and121of the other rotating equipment110and120are connected to the ends of the gas turbine rotor11, the no. 1 gas turbine module M1can be unloaded without moving the other rotating equipment110and120. Particularly, in the present embodiment, the rotor111of the inlet rotating equipment110is not located inside the inlet plenum60, and thus the no. 1 gas turbine module M1including the inlet plenum60can be easily unloaded without isolating the inlet plenum60. Furthermore, in the present embodiment, the rotor121of the exhaust rotating equipment120is not located inside the exhaust plenum61, and thus the no. 1 gas turbine module M1including the exhaust plenum61can be easily unloaded without isolating the exhaust plenum61.

Since the gas turbine10is a type of rotating equipment, it is also preferable to minimize the flexure thereof in the moving process thereof. In the present embodiment, the heaviest gas turbine10in the no. 1 gas turbine module M1is mounted on the gas turbine base80, and the gas turbine base80is mounted on the common base85. That is, the heaviest gas turbine10in the no. 1 gas turbine module M1is supported by the two overlapping bases. Furthermore, the load of the gas turbine10on the common base85can be dispersed from the gas turbine base80. Therefore, in the present embodiment, it is possible to suppress the flexure of the gas turbine10in the moving process thereof. Moreover, in the present embodiment, the exhaust plenum61which is lighter than the gas turbine10in the no. 1 gas turbine module M1is not mounted on the gas turbine base80but is mounted on the common base85. That is, in the present embodiment, the gas turbine base80is mounted only on a part of the upper surface86of the common base85. Therefore, in the present embodiment, it is possible to suppress the flexure of the gas turbine10in the moving process thereof while suppressing an increase in weight of the no. 1 gas turbine module M1.

In the present embodiment, the reason why the no. 1 gas turbine module M1has two bases of the gas turbine base80and the common base85, is also due to the following reason.

The exhaust diffuser51of which a part on the axial downstream side Dad is disposed in the exhaust plenum61is formed such that a cross-sectional area of the diffuser area52through which the exhaust gas Gex passes becomes larger toward the axial downstream side Dad. Therefore, a distance from the axis Ar to a lower end of the exhaust plenum61is larger than a distance from the axis Ar to the lowermost end of the gas turbine10.

It is assumed that the no. 1 gas turbine module M1includes the common base85and does not include the gas turbine base80. In this case, to avoid interference between the common base85and the exhaust plenum61, it is necessary to increase the height of each of the inlet support90and the exhaust support91which support the gas turbine10, and the height of the IGV support92. However, if the height of the inlet support90, the height of the exhaust support91and the height of the IGV support92are increased, it is disadvantageous in terms of vibration and support strength. Therefore, in the present embodiment, to avoid the interference between the common base85and the exhaust plenum61, and to suppress the height of the inlet support90, the height of the exhaust support91, and the height of the IGV support92, the no. 1 gas turbine module M1includes the gas turbine base80in addition to the common base85.

In the present embodiment, by engaging a drive end of the jack166or a wire end of a crane with each of the trunnions88aand88bof the common base85, the no. 1 gas turbine module M1can be lifted by the jack166, the crane, or the like.

A load that is generated when the gas turbine base80on which the inlet plenum60and the gas turbine10are placed is lifted is applied to the trunnions83aand83bof the gas turbine base80. Therefore, the trunnions83aand83bare provided in the gas turbine base80at high strength portions.

A load that is generated when the common base85on which the gas turbine base80and the exhaust plenum61are placed is lifted is applied to the trunnions88aand88bof the common base85. Therefore, the trunnions88aand88bare provided in the common base85at high strength portions.

In the present embodiment, the trunnions83aand83bof the gas turbine base80are disposed at positions overlapping the trunnions88aand88bof the common base85in the axial direction Da. Therefore, in the present embodiment, the position of the high strength portion in the gas turbine base80overlaps the position of the high strength portion in the common base85in the axial direction Da. For this reason, in the present embodiment, a strength of a base in which the gas turbine base80and the common base85are combined is increased, and it is possible to suppress the flexure of the gas turbine10in the moving process thereof.

It is also possible to lift and move the no. 1 gas turbine module M1by a crane such as an overhead crane. However, since the no. 1 gas turbine module M1is extremely heavy, it may be difficult to lift and move the gas turbine module by the crane. Even if there is a crane capable of moving the no. 1 gas turbine module M1, the crane is very large, and the execution cost of the module raising step (S12) and the unloading step (S15) becomes extremely high. In the present embodiment, since the no. 1 gas turbine module M1is lifted by the jack166and the no. 1 gas turbine module M1is moved by the moving equipment160including the pair of rails161and the moving carts162, the execution cost of the module raising step (S12) and the unloading step (S15) can be suppressed.

Modification Example

The gas turbine10in the above embodiment is a two-shaft gas turbine including the high pressure turbine40and the low pressure turbine45. However, the gas turbine may be a general single-shaft gas turbine including only one turbine.

The gas turbine10in the above embodiment is connected to the inlet rotating equipment110and the exhaust rotating equipment120. However, the gas turbine may be connected to only one of the inlet rotating equipment110and the exhaust rotating equipment120. As described above, as the rotating equipment that is connected to the gas turbine, for example, there is a generator that can function as a starter.

The inlet flange13of the gas turbine rotor11is disposed on the radial direction inner side Dri of the inlet plenum60. However, the inlet flange13may be disposed on the axial upstream side Dau of the inlet plenum60. Even in this case, the no. 2 flange117of the inlet coupling115is disposed more on the axial upstream side Dau than the inlet plenum60. Further, the exhaust flange14of the gas turbine rotor11is disposed on the radial direction inner side Dri of the exhaust plenum61. However, the exhaust flange14may be disposed more on the axial downstream side Dad than the exhaust plenum61and the load compartment65. Even in this case, the no. 2 flange127of the exhaust coupling125is disposed more on the axial downstream side Dad than the exhaust plenum61and the load compartment65.

The rotor111of the inlet rotating equipment110is directly connected to the inlet coupling115. However, the rotor111of the inlet rotating equipment110and the inlet coupling115may be connected to each other via a transmission. In this case, the rotor111of the inlet rotating equipment110may rotate about an axis different from the axis Ar of the gas turbine rotor11. The rotor121of the exhaust rotating equipment120is directly connected to the exhaust coupling125. However, the rotor121of the exhaust rotating equipment120and the exhaust coupling125may be connected to each other via a transmission. In this case, the rotor121of the exhaust rotating equipment120may rotate about an axis different from the axis Ar of the gas turbine rotor11.

Although the preferred embodiments of the present invention and a modification example thereof have been described above, the present invention is not limited to these embodiments and the modification example thereof. It is possible to add, omit, replace, and change configurations without departing from the gist of the present invention. The present invention is not limited by the above description, but is limited only by the scope of the appended claims.

APPENDIX

The method of unloading a gas turbine module in the above embodiment is understood as follows, for example.

(1) In a method of moving a gas turbine module according to a first aspect, the following no. 1 gas turbine module M1is moved.

The no. 1 gas turbine module M1includes a gas turbine10that has a gas turbine rotor11capable of rotating about an axis Ar, and a turbine shell15which covers the gas turbine rotor11and in which an inlet23and an exhaust53are formed; an inlet plenum60that is connected to the inlet23of the gas turbine10and is configured to guide air from an inlet duct101into the gas turbine10; an exhaust plenum61that is connected to the exhaust53of the gas turbine10and is configured to guide exhaust gas Gex from the gas turbine10to an exhaust duct102; an enclosure66that covers the gas turbine10; and a common base85on which the gas turbine10, the inlet plenum60, the exhaust plenum61, and the enclosure66are mounted and which is connected to a gas turbine foundation145.

A method of moving a gas turbine module according to the first aspect includes executing the steps including a connection release step (S11) of releasing a connection between the common base85and the gas turbine foundation145, and releasing connections between the no. 1 gas turbine module M1and a plurality of connection objects that are connected to the No. 1 gas turbine module M1and constitute a part of a gas turbine plant; a module raising step (S12) of lifting the no. 1 gas turbine module M1from the gas turbine foundation145after the connection release step (S11); a moving equipment disposition step (S13) of disposing moving equipment160that is configured to move the no. 1 gas turbine module M1in a gap between the common base85and the gas turbine foundation145during the module raising step (S12); a module lowering step (S14) of ending the module raising step (S12) after the moving equipment disposition step (S13) and placing the no. 1 gas turbine module M1on the moving equipment160; and an unloading step (S15) of driving the moving equipment160after the module lowering step (S14) and moving the no. 1 gas turbine module M1.

In the present aspect, since the no. 1 gas turbine module M1including the entire gas turbine10is unloaded, it is not necessary to partially isolate the gas turbine10, and the unloading work is facilitated and the work time can be shortened. Moreover, in the present aspect, since all of the components except the common base85in the no. 1 gas turbine module M1are mounted on the common base85, it is possible to easily unload the gas turbine10by unloading the common base85.

(2) According to a method of moving a gas turbine module of a second aspect, in the method of unloading a gas turbine module according to the first aspect, in the module raising step (S12), the no. 1 gas turbine module M1is lifted from the gas turbine foundation145using a jack166.

It is also possible to lift the no. 1 gas turbine module M1by a crane such as an overhead crane.

However, since the no. 1 gas turbine module M1is extremely heavy, it may be difficult to lift the gas turbine module by the crane. Even if there is a crane capable of lifting the no. 1 gas turbine module M1, the crane is very large, and the execution cost of the module raising step becomes extremely high. In the present aspect, since the no. 1 gas turbine module M1is lifted using the jack166, the execution cost of the module raising step can be suppressed, and the preparation for the module raising step can be simplified.

(3) According to a method of moving a gas turbine module of a third aspect, in the method of unloading a gas turbine module according to the first or second aspect, the moving equipment160includes a pair of rails161and moving carts162capable of moving on the rails161, and in the moving equipment disposition step (S13), each of the pair of rails161is disposed to extend toward a moving destination of the no. 1 gas turbine module M1from below the common base85, and the moving carts162are disposed on the pair of rails161.

It is also possible to move the no. 1 gas turbine module M1by a crane such as an overhead crane. However, since the no. 1 gas turbine module M1is extremely heavy, it may be difficult to move the gas turbine module by the crane. Even if there is a crane capable of moving the no. 1 gas turbine module M1, the crane is very large, and the execution cost of the unloading step becomes extremely high.

In the present aspect, since the no. 1 gas turbine module M1is moved by the moving equipment160including the pair of rails161and the moving carts162, the execution cost of the unloading step can be suppressed.

(4) According to a method of moving a gas turbine module of a fourth aspect, in the method of unloading a gas turbine module according to any one of the first to third aspects, the no. 1 gas turbine module M1includes a gas turbine base80on which the gas turbine10and the inlet plenum60are mounted, and the gas turbine base80, the enclosure66, and the exhaust plenum61are mounted on the common base85.

Since the gas turbine10is a type of rotating equipment, it is preferable to minimize the flexure thereof also in the moving process thereof. In the present aspect, the heaviest gas turbine10in the no. 1 gas turbine module M1is mounted on the gas turbine base80, and the gas turbine base80is mounted on the common base85. That is, the heaviest gas turbine10in the no. 1 gas turbine module M1is supported by the two overlapping bases. Furthermore, the load of the gas turbine10on the common base85can be dispersed from the gas turbine base80. Therefore, in the present aspect, it is possible to suppress the flexure of the gas turbine10in the moving process thereof. Moreover, in the present aspect, the exhaust plenum61which is lighter than the gas turbine10in the no. 1 gas turbine module M1is not mounted on the gas turbine base80but is mounted on the common base85. That is, in the present aspect, the gas turbine base80is mounted only on a part of the upper surface86of the common base85. Therefore, in the present aspect, it is possible to suppress the flexure of the gas turbine10in the moving process thereof while suppressing an increase in weight of the no. 1 gas turbine module M1.

(5) According to a method of moving a gas turbine module of a fifth aspect, in the method of unloading a gas turbine module according to any one of the first to fourth aspects, the gas turbine rotor11includes at least one flange of an inlet flange13that is formed at an end on a no. 1 axial side Dau where the inlet23is present with respect to the exhaust53in an axial direction Da in which the axis Ar extends and is capable of being connected to a rotor111of inlet rotating equipment110, and an exhaust flange14that is formed at an end on a no. 2 axial side Dad where the exhaust53is present with respect to the inlet23in the axial direction Da and is capable of being connected to a rotor121of the exhaust rotating equipment120. In the unloading step (S15), the no. 1 gas turbine module M1is moved along an upper surface86of the common base85on which the gas turbine10, the inlet plenum60, the exhaust plenum61, and the enclosure66are mounted and in a side direction Ds that is a direction different from the axial direction Da.

In the present aspect, since the no. 1 gas turbine module M1is moved in the side direction Ds in the unloading step, even if the rotors111and121of the other rotating equipment110and120are connected to the ends of the gas turbine rotor11, the no. 1 gas turbine module M1can be unloaded without moving the other rotating equipment110and120.

(6) According to a method of moving a gas turbine module of a sixth aspect, in the method of unloading a gas turbine module according to the fifth aspect, the side direction Ds is a direction perpendicular to the axial direction Da.

(7) According to a method of moving a gas turbine module of a seventh aspect, in the method of unloading a gas turbine module according to the fifth or sixth aspect, the gas turbine rotor11includes the inlet flange13.

The gas turbine plant includes, as one of the plurality of connection objects, an inlet coupling115that has a no. 1 flange116capable of being connected to the inlet flange13and a no. 2 flange117capable of being connected to the rotor111of the inlet rotating equipment110. In a state in which the no. 1 flange116of the inlet coupling115is connected to the inlet flange13, the no. 2 flange117of the inlet coupling115is located more on the no. 1 axial side Dau than the inlet plenum60. In the connection release step (S11), a connection between the no. 1 flange116of the inlet coupling115and the inlet flange13is released, and a connection between the no. 2 flange117of the inlet coupling115and the rotor111of the inlet rotating equipment110is released.

In the present aspect, the rotor111of the inlet rotating equipment110is not located inside the inlet plenum60, and thus the no. 1 gas turbine module M1including the inlet plenum60can be easily unloaded without isolating the inlet plenum60.

(8) According to a method of moving a gas turbine module of an eighth aspect, in the method of unloading a gas turbine module according to any one of the fifth to seventh aspects, the gas turbine rotor11includes the exhaust flange14. The gas turbine plant includes, as one of the plurality of connection objects, an exhaust coupling125that has a no. 1 flange126capable of being connected to the exhaust flange14and a no. 2 flange127capable of being connected to the rotor121of the exhaust rotating equipment120. In a state in which the no. 1 flange126of the exhaust coupling125is connected to the exhaust flange14, the no. 2 flange127of the exhaust coupling125is located more on the no. 2 axial side Dad than the exhaust plenum61. In the connection release step (S11), a connection between the no. 1 flange126of the exhaust coupling125and the exhaust flange14is released, and a connection between the no. 2 flange127of the exhaust coupling125and the rotor121of the exhaust rotating equipment120is released.

In the present aspect, the rotor121of the exhaust rotating equipment120is not located inside the exhaust plenum61, and thus the no. 1 gas turbine module M1including the exhaust plenum61can be easily unloaded without isolating the exhaust plenum61.

Further, the method of exchanging a gas turbine module in the above embodiment is understood as follows, for example.

(9) In a method of exchanging a gas turbine module according to a ninth aspect, the method of unloading a gas turbine module according to any one of the first to eighth aspects is executed and a loading method of loading a no. 2 gas turbine module M2different from a no. 1 gas turbine module M1which is the gas turbine module is executed.

The no. 2 gas turbine module M2includes a no. 2 gas turbine10that has a no. 2 gas turbine rotor11capable of rotating about an axis Ar, and a no. 2 turbine shell15which covers the no. 2 gas turbine rotor11and in which a no. 2 inlet23and a no. 2 exhaust53are formed; a no. 2 inlet plenum60that is connected to the no. 2 inlet23of the no. 2 gas turbine10and is configured to guide air from the inlet duct101into the no. 2 gas turbine10; a no. 2 exhaust plenum61that is connected to the no. 2 exhaust53of the no. 2 gas turbine10and is configured to guide exhaust gas Gex from the no. 2 gas turbine10to the exhaust duct102; a no. 2 enclosure66that covers the no. 2 gas turbine10; and a no. 2 common base85on which the no. 2 gas turbine10, the no. 2 inlet plenum60, the no. 2 exhaust plenum61, and the no. 2 enclosure66are mounted and which is connected to the gas turbine foundation145. The no. 2 gas turbine module M2is capable of being connected to the plurality of connection objects that were connected to the no. 1 gas turbine module M1.

The loading method includes executing the steps including a no. 2 moving equipment disposition step (S21) of disposing the moving equipment160on the gas turbine foundation145; a loading step (S22) of driving the moving equipment160after the no. 2 gas turbine module M2is placed on the moving equipment160and moving the no. 2 gas turbine module M2to a location on the gas turbine foundation145where the no. 1 gas turbine module M1was present; a no. 2 module raising step (S23) of lifting the no. 2 gas turbine module M2from the moving equipment160after the loading step (S22); a moving equipment removing step (S24) of removing the moving equipment160from above the gas turbine foundation145during the no. 2 module raising step (S23); a no. 2 module lowering step (S26) of ending the no. 2 module raising step (S23) after the moving equipment removing step (S24) and placing the no. 2 gas turbine module M2on the gas turbine foundation145; and a connection step (S27) of connecting the no. 2 common base85and the gas turbine foundation145to each other and connecting the no. 2 gas turbine module M2and the plurality of connection objects to each other.

In the present aspect, the unloading method described above is executed and, in the loading method as well, the no. 2 gas turbine module M2including the entire gas turbine10is loaded, and thus the exchanging work of the gas turbine10is facilitated and the work period can be shortened.

Further, the gas turbine module in the above embodiment is understood as follows, for example.

(10) A gas turbine module according to a tenth aspect includes a gas turbine10that has a gas turbine rotor11capable of rotating about an axis Ar, and a turbine shell15which covers the gas turbine rotor11and in which an inlet23and an exhaust53are formed; an inlet plenum60that is connected to the inlet23of the gas turbine10and is configured to guide air from an inlet duct101into the gas turbine10; an exhaust plenum61that is connected to the exhaust53of the gas turbine10and is configured to guide exhaust gas Gex from the gas turbine10to an exhaust duct102; an enclosure66that covers the gas turbine10; a gas turbine base80on which the gas turbine10and the inlet plenum60are mounted; and a common base85on which the gas turbine base80, the enclosure66, and the exhaust plenum61are mounted.

In the present aspect, since the entire gas turbine10is mounted on the common base85, the common base85is moved together with the gas turbine10, and thus, it is not necessary to partially isolate the gas turbine10, the moving work is facilitated, and the work time can be shortened.

Since the gas turbine10is a type of rotating equipment, it is preferable to minimize the flexure thereof also in the moving process thereof. In the present aspect, the heaviest gas turbine10in the no. 1 gas turbine module M1is mounted on the gas turbine base80, and the gas turbine base80is mounted on the common base85. That is, the heaviest gas turbine10in the no. 1 gas turbine module M1is supported by the two overlapping bases. Furthermore, the load of the gas turbine10on the common base85can be dispersed from the gas turbine base80. Therefore, in the present aspect, it is possible to suppress the flexure of the gas turbine10in the moving process thereof. Moreover, in the present aspect, the exhaust plenum61which is lighter than the gas turbine10in the no. 1 gas turbine module M1is not mounted on the gas turbine base80but is mounted on the common base85. That is, in the present aspect, the gas turbine base80is mounted only on a part of the upper surface86of the common base85. Therefore, in the present aspect, it is possible to suppress the flexure of the gas turbine10in the moving process thereof while suppressing an increase in weight of the no. 1 gas turbine module M1.

(11) According to a gas turbine module of an eleventh aspect, the gas turbine module according to the tenth aspect further includes a plurality of trunnions88aand88bthat are provided on the common base85and is configured to receive a load that is generated when the common base85is lifted.

In the present aspect, by engaging a drive end of the jack166or a wire end of a crane with each of the trunnions88aand88b, the no. 1 gas turbine module M1can be lifted by the jack166, the crane, or the like.

(12) According to a gas turbine module of a twelfth aspect, in the gas turbine module according to the eleventh aspect, the common base85includes an upper surface86on which the gas turbine base80, the enclosure66, and the exhaust plenum61are mounted, and a pair of side surfaces87that extend in an axial direction Da in which the axis Ar extends and face each other in a side direction Ds perpendicular to the axial direction Da and along the upper surface86. The trunnions88aand88bare provided on each of the pair of side surfaces87. In the pair of side surfaces87, the trunnions88aand88bprovided on one side surface87and the trunnions88aand88bprovided on the other side surface87have the same positions in the axial direction Da.

(13) According to a gas turbine module of a thirteenth aspect, in the gas turbine module according to the twelfth aspect, the gas turbine base80includes an upper surface81on which the gas turbine10and the inlet plenum60are mounted, and a pair of side surfaces82that extend in an axial direction Da in which the axis Ar extends and face each other in a side direction Ds perpendicular to the axial direction Da and along the upper surface81. Each of the pair of side surfaces82of the gas turbine base80is provided with trunnions83aand83bthat is configured to receive a load that is generated when the gas turbine base80is lifted. In the pair of side surfaces82of the gas turbine base80, the trunnions83aand83bprovided on one side surface82and the trunnions83aand83bprovided on the other side surface82have the same positions in the axial direction Da. The trunnions83aand83bprovided on the gas turbine base80are disposed at positions overlapping the trunnions88aand88bprovided on the common base85in the axial direction Da.

In the present aspect, by engaging a drive end of the jack166or a wire end of a crane with each of the trunnions83aand83bof the gas turbine base80, the gas turbine base80and the gas turbine10mounted thereon can be lifted by the jack166, the crane, or the like.

A load that is generated when the gas turbine base80is lifted is applied to the trunnions83aand83bof the gas turbine base80. Therefore, the trunnions83aand83bare provided in the gas turbine base80at high strength portions. A load that is generated when the common base85is lifted is applied to the trunnions88aand88bof the common base85. Therefore, the trunnions88aand88bare provided in the common base85at high strength portions.

In the present aspect, the trunnions83aand83bof the gas turbine base80are disposed at positions overlapping the trunnions88aand88bof the common base85in the axial direction Da. Therefore, in the present aspect, the position of the high strength portion in the gas turbine base80overlaps the position of the high strength portion in the common base85in the axial direction Da. For this reason, in the present aspect, a strength of a base in which the gas turbine base80and the common base85are combined is increased, and it is possible to suppress the flexure of the gas turbine10in the moving process thereof.

Further, the gas turbine plant in the above embodiment is understood as follows, for example.

(14) A gas turbine plant of a fourteenth aspect includes the gas turbine module according to any one of the tenth to thirteenth aspects; inlet rotating equipment110that has a rotor111and is disposed more on a no. 1 axial side Dau where the inlet23is present with respect to the exhaust53in an axial direction Da in which the axis Ar extends than the gas turbine module; and an inlet coupling115that is configured to connect the rotor111of the inlet rotating equipment110and an end of the gas turbine rotor11on the no. 1 axial side Dau to each other.

An inlet flange13is formed at an end of the gas turbine rotor11on the no. 1 axial side Dau. The inlet coupling115has a no. 1 flange116capable of being connected to the inlet flange13and a no. 2 flange117capable of being connected to the rotor111of the inlet rotating equipment110. In a state in which the no. 1 flange116of the inlet coupling115is connected to the inlet flange13, the no. 2 flange117of the inlet coupling115is located more on the no. 1 axial side Dau than the inlet plenum60.

(15) A gas turbine plant of the fifteenth aspect includes the gas turbine module according to any one of the tenth to thirteenth aspects; an exhaust rotating equipment120that has a rotor121and is disposed more on a no. 2 axial side Dad where the exhaust53is present with respect to the inlet23in an axial direction Da in which the axis Ar extends than the gas turbine module; and an exhaust coupling125that is configured to connect the rotor121of the exhaust rotating equipment120and an end of the gas turbine rotor11on the no. 2 axial side Dad to each other.

An exhaust flange14is formed at an end of the gas turbine rotor11on the no. 2 axial side Dad. The exhaust coupling125has a no. 1 flange126capable of being connected to the exhaust flange14and a no. 2 flange127capable of being connected to the rotor121of the exhaust rotating equipment120. In a state in which the no. 1 flange126of the exhaust coupling125is connected to the exhaust flange14, the no. 2 flange of the exhaust coupling125is located more on the no. 2 axial side Dad than the exhaust plenum61.

EXPLANATION OF REFERENCES