Gas turbine rotor, gas turbine and gas turbine equipment

Abstract

A gas turbine rotor (2) configured to rotate about an axial line (Ar) in a gas turbine casing (3), the gas turbine rotor (2) comprising:a compressor rotor (20; 20a; 20b; 20c) of a compressor (10) configured to rotate about the axial line (Ar); and a turbine rotor (120; 120a) of a turbine (110) arranged on the axial line (Ar) and connected to the compressor rotor (20; 20a; 20b; 20c) to rotate integrally with the compressor rotor (20; 20a; 20b; 20c) about the axial line (Ar), wherein the gas turbine rotor (2) has formed therein: a ventilation flow path (22; 22a; 22b; 22c) for guiding compressed air (Acom) flowing within the gas turbine casing (3), further on an axially upstream side (Dau) than an air outlet port (18) of the compressor (10), to an interior of the compressor rotor (20; 20a; 20b; 20c); a cooling air flow path (178; 122;123) for guiding cooling air (Ac) having a lower temperature than that of the compressed air (Acom) flowing through the ventilation flow path (22; 22a; 22b; 22c) to a part further on the axial downstream side (Dad) than the air outlet port (18); a mixing space (177) connected to the ventilation flow path (22; 22a; 22b; 22c) and the cooling air flow path (178; 122; 123), and configured such that in the mixing space (177) the compressed air (Acom) flowing through the ventilation flow path (22; 22a; 22b; 22c) and the cooling air (Ac) flowing through the cooling air flow path (178; 122; 123) are mixed; anda mixed air flow path (137) connected to the mixing space (177) and configured to direct mixed air (Am) generated by mixing the compressed air (Acom) and the cooling air (Ac) into the turbine rotor (120; 120a);characterized in that .the gas turbine rotor (2) further comprises an intermediate rotor shaft (171) which is arranged on the axial line (Ar) between the compressor rotor (20; 20a; 20b; 20c) and the turbine rotor (120; 120a) and is connected to the compressor rotor (20; 20a; 20b; 20c) and the turbine rotor (120; 120a), wherein the cooling air flow path (178; 122; 123) and the mixing space (177) are formed in the intermediate rotor shaft (171);

Description

The present invention relates to a gas turbine rotor, a gas turbine, and a gas turbine apparatus.A gas turbine is provided with a compressor for generating compressed air by compressing air, a combustor for generating a combustion gas by combustion in the compressed air, and a turbine driven by the combustion gas. The compressor includes a compressor rotor that rotates about an axial line and a compressor housing that covers the compressor rotor. The turbine includes a turbine rotor that rotates centered on the axial line and a turbine housing that covers the turbine rotor. Each of the compressor rotor and the turbine rotor includes a rotor shaft and a plurality of blade rows fixed to an outer periphery of the rotor shaft. A gas turbine rotor is formed by arranging the compressor rotor and the turbine rotor on the same axial line and connecting the two to each other. In addition, a gas turbine casing is formed by connecting the compressor casing and the turbine casing to each other.Of the gas turbine rotors, the turbine rotor is exposed to combustion gas of high temperature, and therefore the rotor needs to be cooled using air and the like.A technology for cooling a turbine rotor using compressed air from a compressor is disclosed in JP 2004-218 480 A. With this technology, compressed air extracted from a middle stage of the compressor is introduced into a compressor rotor of the gas turbine rotors, and this compressed air is then introduced from the compressor rotor to a turbine rotor to cool the turbine rotor.DE 44 33 289 A1 describes a gas turbine rotor which comprises a compressor rotor and a gas turbine rotor which form a common shaft, the part of which located between the turbine and the compressor is formed as a drum. The drum is surrounded by a drum cover, so that an annular channel runs between the drum and the drum cover in the axial direction of the shaft. Compressed air is introduced into the annular channel from the side of the compressor and is conducted through the annular channel in the downstream direction. Turbine rotor cooling air is supplied via a further line coming from the compressor into the opposite end of the annular channel in the region of an edge side space and is conducted upstream through the annular channel in the axial direction. In the annular channel, mixing of the two cooling air streams occurs in the region of widened collecting spaces. The mixed cooling air is then conducted via suction devices from the collecting spaces to cooling air extraction annular spaces in the compressor housing.US 2014 / 0 248 122 A1 discloses a shaft of a gas turbine which is cooled internally via a plurality of ventilation paths.A gas turbine rotor according to the preamble of claims 1, 2 or 5 is known from US 2008 / 0 041 064 A1.In recent years, the temperature of combustion gas supplied to turbines has increased along with the increased efficiency of gas turbines. Therefore, it has become more and more likely that even if compressed air extracted from a middle stage of a compressor is supplied as it is to a turbine rotor to cool the turbine rotor as with the technology of JP 2004-218 480 A, it is impossible to adequately cool the turbine rotor.Thus, an object of the present invention is to provide a technology capable of better cooling a turbine rotor of a gas turbine rotor.According to the invention, the above object is achieved by a gas turbine rotor according to any one of claims 1, 2 or 5 as well as by a gas turbine according to claim 6 and a gas turbine equipment according to claim 7. The dependent claims relate to further advantageous embodiments of the invention. In the gas turbine rotor of the invention, the ventilation flow path is formed in the compressor rotor, so that the interior of the compressor rotor is ventilated by the compressed air flowing through the ventilation flow path. Therefore, in the gas turbine rotor, the thermal response of the compressor rotor can be increased with respect to a temperature change in an air compression flow path where air is compressed by the compressor. In addition, in the gas turbine rotor, compressed air that has passed through the ventilation flow path of the compressor rotor and cooling air are mixed in the mixing space, and mixed air generated by this mixing is introduced into the turbine rotor. Therefore, in the gas turbine rotor, the turbine rotor can be cooled by air having a lower temperature than in a case where the compressed air that has exhausted from a compressor rotor shaft is supplied as it is to a turbine rotor shaft. In addition, in the gas turbine rotor, the compressed air that has exhausted from the ventilation flow path of the compressor rotor can be effectively used for cooling the turbine rotor.In one aspect of the present invention, the turbine rotor can be cooled to a greater extent. FIG. 1 is a schematic cross-sectional view of gas turbine equipment in a first embodiment according to the present invention. FIG. 2 is a cross-sectional view of main components of a compressor in the embodiment according to the present invention. FIGS. 3A and 3B illustrate a rotor disk of the compressor in the embodiment according to the present invention, wherein FIG. 3A is a cross-sectional view of the rotor disk and FIG. 3B is an arrow B view of FIG. 3A. FIG. 4 is a cross-sectional view of main components around a moving blade and a vane of the compressor in the embodiment according to the present invention. FIG. 5 is a cross-sectional view around a combustor of the gas turbine in the embodiment according to the present invention. FIG. 6 is a cross-sectional view of main components of a turbine in the embodiment according to the present invention. FIG. 7 is a cross-sectional view of major components around a moving blade and a vane of the turbine in the embodiment according to the present invention. FIG. 8 is a cross-sectional view of main components of a compressor in a first modification example of the embodiment according to the present invention. FIG. 9 is a cross-sectional view of main components of a compressor in a second modification example of the embodiment according to the present invention. FIG. 10 is a cross-sectional view of main components of a compressor in a third modification example of the embodiment according to the present invention. FIG. 11 is a cross-sectional view of main components of a turbine in a modification example of the embodiment according to the present invention.An embodiment and various modification examples of gas turbine equipment according to the present invention will be described in detail below with reference to the drawings.An embodiment of the gas turbine equipment according to the present invention will be described with reference to FIGS. 1 to 7.As illustrated in FIG. 1, the gas turbine equipment according to the present embodiment is provided with a gas turbine 1 and a cooling system 200 for generating cooling air.The gas turbine 1 is provided with a compressor 10 for generating compressed air Acom by compressing outside air A, a combustor 80 for generating a combustion gas by burning a fuel F from a fuel source in the compressed air Acom, and a turbine 110 driven by the combustion gas.The compressor 10 includes a compressor rotor 20 that rotates about an axial line Ar and a cylindrical compressor housing 11 that covers the compressor rotor 20. Note that a direction in which the axial line Ar extends is hereinafter referred to as an axial direction Da. In addition, one axial direction side Da is referred to as an upstream axial side Dau, and the other axial direction side Da is referred to as a downstream axial side Dad. A radial direction based on the axial line Ar is simply referred to as a radial direction Dr. In addition, a side far from the axial line Ar in the radial direction Dr is referred to as a radially outer side Dro, and a side close to the axial line Ar in the radial direction Dr is referred to as a radially inner side Dri.The compressor 10 is an axial compressor. Therefore, the compressor rotor 20 has a compressor rotor shaft 21 centered on the axial line Ar in the axial direction Da, and a plurality of blade rows 51 aligned in the axial direction Da and fixed to an outer periphery of the compressor rotor shaft 21. An end on the upstream axial side Dau of the compressor housing 11 is open, and this opening forms an air inlet port 12. Each vane row 61 has a plurality of vanes 62, and the plurality of vanes 62 are aligned centered on the axial line Ar in the circumferential direction Dc, and form one of the vane rows 61, and each vane row 51 has a plurality of vanes 52. The plurality of blades 52 are aligned centered on the axial line Ar in the circumferential direction Dc, and form one of the blade rows 51.The turbine 110 is provided on the axially downstream side Dad of the compressor 10. The turbine 110 includes a turbine rotor 120 that rotates about the axial line Ar and a cylindrical turbine housing 111 that covers the turbine rotor 120. The turbine rotor 120 includes a turbine rotor shaft 121 centered on the axial line Ar in the axial direction Da, and a plurality of blade rows 151 aligned in the axial direction Da and fixed to an outer periphery of the turbine rotor shaft 121. A blade row 161 is fixed at a position on an upstream side of each blade row 151 on an inner peripheral side of the turbine casing 111. Each vane row 161 has a plurality of vanes 162. The plurality of vanes 162 are aligned centered on the axial line Ar in the circumferential direction Dc, and form one of the vane rows 161. In addition, each vane row 151 includes a plurality of blades 152. The plurality of blades 152 are aligned centered on the axial line Ar in the circumferential direction Dc, and form one of the blade rows 151.The gas turbine 1 according to the present embodiment also includes an inter-rotor shaft 171, an inter-rotor shaft cover 181, a cooling air pipe 189, and an inter-housing 191. The inter-rotor shaft 171 connects the compressor rotor 20 and the turbine rotor 120 to each other. Therefore, the inter-rotor shaft 171 is disposed between the compressor rotor 20 and the turbine rotor 120 in the axial direction Da. The compressor rotor 20, the inter-rotor shaft 171, and the turbine rotor 120 are arranged on the same axial line Ar and rotate together about the axial line Ar. These form a gas turbine rotor 2. The intermediate housing 191 covers an outer circumferential side of the intermediate rotor shaft 171. Therefore, the intermediate housing 191 is disposed between the compressor housing 11 and the turbine housing 111 in the axial direction Da. The compressor housing 11, the intermediate housing 191, and the turbine housing 111 are joined together to form a gas turbine housing 3. The combustion chamber 80 is fixed to the intermediate case 191. The compressed air Acom from the compressor 10 flows into the intermediate housing 191. The compressed air Acom flows from the intermediate casing 191 into the combustor 80. The intermediate rotor shaft cover 181 is disposed on the radially inner side Dri of the gas turbine casing 3 and covers the radially outer side Dro of the intermediate rotor shaft 171. The interrotor shaft cover 181 is fixed to the gas turbine casing 3. A first end of the cooling air pipe 189 is fixed to the intermediate housing 191, and a second end of the cooling air pipe 189 is fixed to the intermediate rotor shaft cover 181.The cooling system 200 includes a cooling air line 201 and a radiator 205. The cooling air duct 201 is provided on an outer side of the gas turbine casing 3. A first end of the cooling air duct 201 is connected to the intermediate casing 191, and a second end of the cooling air duct 201 is connected to the cooling air pipe 189 of the gas turbine 1. The compressed air Acom inside the intermediate housing 191 flows from the first end of the cooling air duct 201 into the cooling air duct 201. The radiator 205 is provided on the cooling air pipe 201. The cooler 205 cools the compressed air Acom that has flowed into the cooling air pipe 201, to thereby generate a cooling air Ac from the compressed air Acom. For example, the radiator 205 is a heat exchanger that performs heat exchange between the compressed air Acom in the cooling air pipe 201 and a coolant, and thus cools the compressed air Acom. Note that the radiator 205 may be configured with a radiator through the inside of which compressed air Acom flows and a blower for blowing air to the outside of the radiator. The cooling air Ac generated from the radiator 205 flows into the cooling air pipe 189 through the cooling air pipe 201.As illustrated in FIG. 2, the compressor housing 11 has a compressor housing main body 13 and a vane retaining ring 14 provided inside the compressor housing main body 13. The vane retaining ring 14 forms an annular shape centered on the axial line Ar. The vane retaining ring 14 is fixed to the compressor housing main body 13. The plurality of vanes 62 are fixed to the vane retaining ring 14.As illustrated in FIG. 4, the vane 62 has a blade body 63 extending in the radial direction Dr, an outer shell 64 provided on the radially outer side Dro of the blade body 63, and an inner shell 65 provided on the radially inner side Dri of the blade body 63. The outer shell 64 is fixed to the radially inner side Dri of the vane retaining ring 14. A seal ring 66 is provided on the inner shell 65 at the radially inner side Dri thereof. The moving blade 52 includes a blade body 53 extending in the radial direction Dr, a platform 54 provided on the radially inner side Dri of the blade body 53, and a blade root 55 provided on the radially inner side Dri of the platform 54. The blade root 55 is embedded in the compressor rotor shaft 21.As illustrated in FIG. 2, an air compression flow path 15 through which air flows during a compression process forms an annular shape centered on the axial line Ar in the compressor 10. An outer circumferential side of the air compression flow path 15 is defined by the compressor housing 11 and the outer casings 64 of the vanes 62. In addition, an inner circumferential side of the air compression flow path 15 is defined by the platforms 54 of the moving blades 52 and the inner casings 65 of the blades 62.A diffuser 16 is provided on the axial downstream side Dad of the vane row 61 that is the farthest on the axial downstream side Dad among the plurality of vane rows 61. The diffuser 16 has an annular outer diffuser 16 oand an annular inner diffuser 16 iprovided on the radially inner side Dri of the outer diffuser 16 o. The outer diffuser 16 oexpands, and an inner diameter thereof gradually increases from the outer shell 64 of the plurality of vanes 62 constituting the vane row 61 that is the farthest on the axial downstream side Dad toward the axial downstream side Dad. Meanwhile, the inner diffuser 16 iexpands, and an inner diameter thereof gradually becomes smaller from the inner shell 65 of the plurality of blades 62 constituting the blade row 61 that is the farthest on the axial downstream side Dad toward the axial downstream side Dad. An annular clearance between the annular outer diffuser 16 oand the annular inner diffuser 16 iconstitutes an air outlet flow path 17 connected to the annular air compression flow path 15. An end on the axially downstream side Dad of the air outlet flow path 17 is open to the intermediate housing 191. This opening forms an air outlet port 18 in the compressor 10.The rotation of the compressor rotor 20 causes the outside air A to flow from the air inlet port 12 into the air compression flow path 15 (see FIG. 1 ), and the air flows from the axially upstream side Dau to the axially downstream side Dad, thereby being compressed in the air compression flow path 15. The compressed air Acom, which is the compressed air inside the air compression flow path 15, flows into the air outlet flow path 17.A plurality of cavities 33 are formed separately from each other in the radial direction Dr in the compressor rotor shaft 21, thereby forming ring shapes centered on the axial line Ar in each position in the axial direction Da respectively between the plurality of blade rows 51, that is, in each position in the axial direction Da of the plurality of vane rows 61, A plurality of cavities 33 formed in one position in the axial direction Da between a pair in the axial direction Da of adjacent blade rows 51 form a cavity group 32, and therefore a plurality of the cavity groups 32 are formed along the axial direction Da in the compressor rotor shaft 21.Each of the cavity groups 32 is composed of three of the cavities 33: an outer cavity 33 oformed furthest on the radially outer side Dro in the compressor rotor shaft 21; an intermediate cavity 33 mformed farther on the radially inner side Dri than the outer cavity 33 o; and an inner cavity 33 iformed furthest on the radially inner side Dri within the compressor rotor shaft 21.Further, a radially outer flow path 31 connecting the outer cavity 33 oand the air compression flow path 15 is formed in the compressor rotor shaft 21.The compressor rotor shaft 21 has a plurality of rotor disks 41 stacked in the axial direction Da, a spindle bolt 29 penetrating the plurality of rotor disks 41 and a plurality of intermediate cavities 33 min the axial direction Da, and a cylindrical torque pin 39 for regulating relative rotation between adjacent rotor disks 41.One of the rotor blade rows 51 is fastened to one of the rotor disks 41. Therefore, there is one rotor disk 41 for each of the plurality of blade rows 51.As illustrated in FIGS. 3A and 3B, a plurality of cavities 33 constituting one of the cavity groups 32 and the radially outer flow path 31 are respectively disposed adjacently between two of the rotor disks 41 in the axial direction Da. Note that FIG. 3A is a cross-sectional view of the rotor disk 41 and FIG. 3B is a view according to arrow B of FIG. 3A.A blade mounting part 49 for mounting the blade roots 55 of the plurality of blades 52 constituting one of the blade rows 51 is formed on the radially outer side Dro of each of the rotor disks 41.An upstream first concave part 43 u, an upstream second concave part 45 u, and an upstream third concave part 47 uare formed in each of the rotor disks 41. In order to form the outer cavity on the upstream 33 oaxial direction side Dau of the rotor disk 41, the upstream first concave part is recessed from a part of the 43 uaxial upstream side Dau on the axial downstream side Dad in the rotor disk 41. In order to form the intermediate cavity 33 mon the axially upstream side Dau of the rotor disk 41, the upstream second concave part 45 uis recessed from a part of the axially upstream side Dau in the rotor disk 41 at a position further on the radially inner side Dri than the upstream first concave part 43 uto the axially downstream side Dad. In order to form the inner cavity 33 ion the axially upstream side Dau of the rotor disk 41, the upstream third concave part 47 uis recessed from a part of the axially upstream side Dau in the rotor disk 41 at a position further on the radially inner side Dri than the upstream second concave part 45 uto the axially downstream side Dad. Therefore, an annular upstream first arm part 42 uprotruding toward the axially upstream side Dau with respect to a lower surface of the upstream first concave part 43 uis formed on the radially outer side Dro of the upstream first concave part 43 u. In addition, an annular upstream second arm part 44 uprotruding toward the axially upstream side Dau with respect to the lower surface of the upstream first concave part 43 uand a lower surface of the upstream second concave part 45 uis formed between the upstream first concave part 43 uand the upstream second concave part 45 u. In addition, an annular upstream third arm part 46 uprotruding toward the axially upstream side Dau with respect to the lower surface of the upstream second concave part 45 uand a lower surface of the upstream third concave part 47 uis formed in a clearance between the upstream second concave part 45 uand the upstream third concave part 47 u. In addition, an annular upstream protruding part 48 uprotruding toward the axially upstream side Dau with respect to the lower surface of the upstream third concave part 47 uis formed on the radial direction inner side Dri of the upstream third concave part 47 u.A plurality of upstream pin grooves 44 uprecessed toward the axially downstream side Dad to connect the upstream first concave part 43 uand the upstream second concave part 45 uare formed in the annular upstream second arm part 44 u. The plurality of upstream pin grooves 44 upare aligned in the circumferential direction Dc.In addition, a downstream first concave part 43 d, a downstream second concave part 45 d, and a downstream third concave part 47 dare formed in each of the rotor disks 41. To form the outer cavity 33 oon the axially downstream side Dad of the rotor disk 41, the downstream first concave part 43 dis recessed toward the axially upstream side Dau from a part of the axially downstream side Dad in the rotor disk 41. To form the intermediate cavity 33 mon the axially downstream side Dad of the rotor disk 41, the downstream second concave part 45 dis recessed from a part of the axially downstream side Dad in the rotor disk 41 at a position on the radial direction inner side Dri from the downstream first concave part 43 dto the axially upstream side Dau. To form the inner cavity 33 ion the axially downstream side Dad of the rotor disk 41, the downstream third concave part 47 dis recessed from a part of the axially downstream side Dad in the rotor disk 41 at a position on the radial direction inner side Dri from the downstream second concave part toward the axially upstream side Dau. Therefore, an annular downstream first arm part 42 dprotruding toward the axial downstream side Dad with respect to a lower surface of the downstream first concave part 43 dis formed on the radial outer side Dro of the downstream first concave part 43 d. In addition, an annular downstream second arm part 44 dprotruding toward the axial downstream side Dad with respect to the lower surface of the downstream first concave part 43 dand a lower surface of the downstream second concave part 45 dis formed in a clearance between the downstream first concave part 43 dand the downstream second concave part 45 d. In addition, an annular downstream third arm part 46 dprotruding toward the axial downstream side Dad with respect to the lower surface of the downstream second concave part 45 dand a lower surface of the downstream third concave part 47 dis formed in a clearance between the downstream second concave part 45 dand the downstream third concave part 47 d. In addition, an annular downstream protruding part 48 dprotruding toward the axial downstream side Dad with respect to the lower surface of the downstream third concave part 47 dis formed on the radial direction inner side Dri of the downstream third concave part 47 d.A plurality of downstream pin grooves 44 dprecessed toward the axially upstream side Dau to connect the downstream first concave part 43 dand the downstream second concave part 45 dis formed in the annular downstream second arm part 44 d. The plurality of post pin grooves 44 dpare aligned in the circumferential direction Dc.The outer cavity 33 ois defined by the downstream first concave part 43 din the rotor disk 41 on the axially upstream side Dau of the two rotor disks 41 adjacent in the axial direction Da and the upstream first concave part 43 uin the rotor disk 41 on the axially downstream side Dad. The intermediate cavity 33 mis defined by the downstream second concave part 45 din the rotor disk 41 on the axially upstream side Dau of the two rotor disks 41 adjacent in the axial direction Da and the upstream second concave part 45 uin the rotor disk 41 on the axially downstream side Dad. The inner cavity 33 iis defined by the downstream third concave part 47 din the rotor disk 41 on the axially upstream side Dau of the two rotor disks 41 adjacent in the axial direction Da and the upstream third concave part 47 uin the rotor disk 41 on the axially downstream side Dad.The downstream first arm part 42 din the rotor disk 41 on the axially upstream side Dau of the two rotor disks 41 adjacent in the axial direction Da and the upstream first arm part 42 uin the rotor disk 41 on the axially downstream side Dad face each other and are separated from each other in the axial direction Da. The radially outer flow path 31 is defined by the downstream first arm part 42 din the rotor disk 41 on the axially upstream side Dau of the two rotor disks 41 adjacent in the axial direction Da and the upstream first arm part 42 uin the rotor disk 41.The plurality of downstream pin grooves 44 dpin the rotor disk 41 on the axially upstream side Dau of the two rotor disks 41 adjacent in the axial direction Da and the plurality of upstream pin grooves 44 upin the rotor disk 41 on the axially downstream side Dad face each other in the axial direction Da. The pin hole in which the torque pin 39 is mounted is defined by the downstream pin groove 44 dpand the upstream pin groove 44 up. The pin hole in which the torque pin 39 is mounted is formed cylindrically to correspond to the shape of the torque pin 39.A bolt through hole 38 into which the spindle bolt 29 is inserted is inserted in the rotor disk 41 to penetrate from the lower surface of the upstream second concave part 45 uto the lower surface of the downstream second concave part 45 d.Further, a ventilation flow path 22 for guiding air flowing between two of the blade rows 51 of the plurality of blade rows 51 in the axial direction Da adjacent to an inner space of the compressor rotor shaft 21 is formed in the compressor rotor shaft 21, as illustrated in FIGS. 1 and 2. Here, the two moving blade rows 51 of the plurality of moving blade rows 51 adjacent in the axial direction Da are two moving blade rows 51 between the moving blade row 51 that is farthest on the axial downstream side Dad and the moving blade row 51 that is farthest on the axial upstream side Dau. Thus, these two blade rows 51 will be referred to as intermediate blade row 51a hereinafter. In addition, the rotor disk 41 to which the intermediate blade row 51 ais fixed is referred to as an intermediate rotor disk 41 a. Note that the rotor disk 41 on the axially upstream side Dau (left side in FIG. 3A ) illustrated in FIG. 3A is the intermediate rotor disk 41 aof the two intermediate rotor disks 41 awhich is on the axially downstream side Dad. In addition, the rotor disk 41 on the axial downstream side Dad (right side in FIG. 3A ) illustrated in FIG. 3A is a rotor disk 41 adjacent to the axial downstream side Dad of the intermediate rotor disk 41 awhich is on the axial downstream side Dad.The ventilation flow path 22 includes an introduction part 23, a plurality of branch parts 27, and a collection part 28. An inlet port 25 into which the compressed air Acom flowing between the two intermediate blade rows 51 aflows as compressor extracted air Bcom is formed in the inflow part 24. The inflow part 24 extends from the inlet port 25 to the radially inner side Dri. The distribution part 26 extends from the inflow part 24 to the axial upstream side Dau and the axial downstream side Dad. The plurality of branch parts 27 branch off from the distribution part 26 of the insertion part 23 and are formed at respectively different positions in the axial direction Da. Flow paths of the plurality of branch parts 27 extend in the radial direction Dr. The collection part 28 is connected to each end of the plurality of branch parts 27 at the radial inner side Dri. The collecting part 28 extends in the axial direction Da. Air after passing through the plurality of branch parts 27 flows into the collection part 28, and air that has flowed in is discharged.As illustrated in FIGS. 2 and 3A and 3B, the inlet port 25 of the inflow part 24 is formed by an opening on the radially outer side Dro of the radially outer flow path 31 formed between the two intermediate rotor disks 41 a. A through hole 37 penetrating in the axial direction Da is formed in the two intermediate rotor disks 41 a. The through hole 37 connected to the through hole 37 of the intermediate rotor disk 41 ais also formed in one or more of the rotor disks 41 that are further on the axially upstream side Dau than the intermediate rotor disk 41 aof the two intermediate rotor disks 41 a, that is, on the axially upstream side Dau. In addition, the through hole 37 connected to the through hole 37 of the intermediate rotor disk 41 ais connected in one or more of the rotor disks 41 that are further on the axial downstream side Dad than the intermediate rotor disk 41 aof the two intermediate rotor disks 41 a, that is, on the axial downstream side Dad. All of these through holes 37 penetrate from a groove bottom of the rotor disc upstream pin groove 44 upto a groove bottom of the downstream pin groove 44 dp.The torque pin 39 is not provided in one or more of the pin holes of the plurality of pin holes formed by the plurality of downstream pin grooves 44 dpin the intermediate rotor disk 41 aon the axially upstream side Dau of the two intermediate rotor disks 41 aand the plurality of upstream pin grooves 44 upin the intermediate rotor disk 41 aon the axially downstream side Dad. Therefore, the pin hole forms a first intermediate flow path 34 connecting the outer cavity 33 oand the intermediate cavity 33 mformed between the two intermediate rotor disks 41 a. The through holes 37 formed in the two intermediate rotor disks 41 aare connected to the first intermediate flow path 34. Note that while the pin hole is used here as the first intermediate flow path 34, a separate hole may be formed in addition to the pin hole, and this hole may be used as the first intermediate flow path 34.A torque pin 39 ais provided in at least one of the pin holes of the plurality of pin holes formed between the intermediate rotor disk 41 aon the axially upstream side Dau and one or more of the rotor disks 41 further on the axially upstream side Dau than the intermediate rotor disk 41 aextending from an intermediate position in the radial direction Dr of the pin holes to the radially outer side Dro. Therefore, an opening on the radially outer side Dro of the pin hole is blocked by the torque pin 39 a, while on the other hand, an opening on the radially inner side Dri of the pin hole is not blocked by the torque pin 39 a. In the pin hole, a part of the radially outer side Dro forms a second intermediate flow path 34 aconnected to the intermediate cavity 33 m.In addition, the torque pin 39 ais provided in at least one of the pin holes of the plurality of pin holes formed between the intermediate rotor disk 41 aon the axial downstream side Dad and one or more of the rotor disks 41 that are further on the axial downstream side Dad than the intermediate rotor disk 41 a, and extends from an intermediate position in the radial direction Dr of the pin holes to the radial outer side Dro. Therefore, an opening on the radially outer side Dro of the pin hole is blocked by the torque pin 39 a, while on the other hand, an opening on the radially inner side Dri of the pin hole is not blocked by the torque pin 39 a. A part on the radially outer side Dro in this pin hole also forms a second intermediate flow path 34 aconnected to the intermediate cavity 33 m. Note that while a part of the pin hole is used here as the second intermediate flow path 34 a, a separate hole may be formed in addition to the pin hole, and this hole may be used as the second intermediate flow path 34 a.The through holes 37 formed in the rotor disk 41 including the intermediate rotor disks 41 aare connected to the second intermediate flow path 34 a.The inflow part 24 of the ventilation flow path 22 is formed by the radially outer flow path 31, the outer cavity 33 o, and a part of the radially outer side Dro of the first intermediate flow path 34, all of which are formed between the two intermediate rotor disks. The distribution part 26 of the ventilation flow path 22 is formed by the through hole 37 formed in the rotor disks 41 including the intermediate rotor disks 41 a.A through hole penetrating in the axial direction Da is formed in the rotor disk 41 that is the farthest on the axially upstream side Dau among the plurality of rotor disks 41 in which the through hole 37 is formed and all the rotor disks 41 that are the farther on the axially downstream side Dad than this rotor disk 41 at a position farther on the radially inner side Dri than the inner cavity 33 i. The collection part 28 of the ventilation flow path 22 is formed by this hole.A first inner flow path 35 connecting the intermediate cavity 33 mand the inner cavity 33 i, and a second inner flow path 36 connecting the inner cavity 33 iand the collection part 28 are respectively formed between the rotor disks 41 including the intermediate rotor disk 41 a. A branch part 27 of the plurality of branch parts 27 in the ventilation flow path 22 is formed by a part of a radially inner side Dri of the first intermediate flow path 34, the intermediate cavity 33 mconnected to the first intermediate flow path 34, the first inner flow path 35 connected to the intermediate cavity 33 m, the inner cavity 33 iconnected to the first inner flow path 35, and the second inner flow path 36 connected to the inner cavity 33 i. In addition, another branch part 27 of the plurality of branch parts 27 is formed in the ventilation flow path 22 from the second intermediate flow path 34 a, the intermediate cavity 33 mconnected to the second intermediate flow path 34 a, the first inner flow path 35 connected to the intermediate cavity 33 m, the inner cavity 33 iconnected to the first inner flow path 35, and the second inner flow path 36 connected to the inner cavity 33 i.As illustrated in FIG. 5, the inter-rotor shaft 171 has a cylindrical part 172 having a cylindrical shape centered on the axial line, an upstream flange part 173 protruding to the radially inner side Dri from a part of the axially upstream side Dau of the cylindrical part 172, and a downstream flange part 175 protruding to the radially inner side Dri from a part of the axially downstream side Dad of the cylindrical part 172. There is a cavity on the radially inner side Dri of the cylindrical part 172, the upstream flange part 173, and the downstream flange part 175. This hollow part forms a mixing space 177. A bolt through hole 174 into which the spindle bolt 29 of the compressor 10 is inserted is formed in the upstream flange part 173. The intermediate rotor shaft 171 and the compressor rotor shaft 21 are connected by the spindle bolt 29. A bolt through hole 176 into which a spindle bolt 129 of the turbine 110 described later is inserted is formed in the downstream flange part 175. The intermediate rotor shaft 171 and the turbine rotor shaft 121 are connected by the spindle bolt 129.A first cooling air flow path 178 that penetrates the mixing space 177 through the downstream flange part 175 from the radially outer side Dro of the inter-rotor shaft 171 is formed in the inter-rotor shaft 171.The inter rotor shaft cover 181 is provided in the inter housing 191. The inter-rotor shaft cover 181 has a cylindrical inner cover 183 covering the radially outer side Dro of the inter-rotor shaft 171 and a cylindrical outer cover 182 covering the radially outer side Dro of the inner cover 183. An end on the axially upstream side Dau of the outer cover 182 is fixed to the gas turbine casing 3 by the diffuser 16 of the compressor 10. In addition, an end on the axially downstream side Dad of the outer cover 182 is fixed to the gas turbine casing 3 by a first vane row 161 amost on the axially upstream side of the plurality of vane rows 161 of the turbine 110. The inner cover 183 covers a region on the radially outer side Dro of the inter-rotor shaft 171 and covers a surface including an opening of the first cooling air flow path 178 in the outer circumferential surface of the inter-rotor shaft 171. An end on the axially upstream side Dau of the inner cover 183 is connected to the inner circumferential surface of the outer cover 182. All parts of the inner cover 183 that are farther on the axial downstream side Dad than the end thereof on the axial upstream side Dau are separated toward the radially inner side Dri from the inner circumferential surface of the outer cover 182. A clearance between the inner peripheral surface of the outer cover and the outer peripheral surface of the inner cover forms an air introduction space 184. The cooling air pipe 189 is connected to the outer cover 182. A through hole 185 penetrating from the radial outer side Dro to the radial inner side Dri is provided in the inner cover 183 at a position substantially the same as the opening of the first cooling air flow path 178 of the inter rotor shaft 171 in the axial direction Da. In addition, an upstream seal 186 and a downstream seal 187 for sealing a clearance between the inter rotor shaft 171 and the inner cover 183 are provided in the inner circumferential surface of the inner cover 183. The upstream seal 186 is provided further on the axially upstream side Dau than the through hole 185 of the inner cover 183. The downstream seal 187 is provided further on the axial downstream side Dad than the through hole 185 of the inner cover 183.A cooling air introducing member 188 for guiding the cooling air Ac from the cooling system 200 to the gas turbine rotor 2 is configured with the cooling air pipe 189 and the inter-rotor shaft cover 181.The collection part 28 of the ventilation flow path 22 formed in the compressor rotor shaft 21 is connected to the mixing space 177. Therefore, the compressor extracted air Bcom after passing through the ventilation flow path 22 of the compressor rotor shaft 21 flows into the mixing space 177. In addition, the cooling air Ac flows from the cooling air pipe 189 into the air introduction space 184 of the interrotor shaft cover 181. The cooling air Ac in the air introduction space 184 flows into the mixing space 177 of the interrotor shaft 171 through the through hole 185 of the inner cover 183 and the first cooling air flow path 178 of the interrotor shaft 171. Therefore, the cooling air Ac from the cooling system 200 and the compressor extracted air Bcom from the compressor rotor shaft 21 are mixed in the mixing space 177.As illustrated in FIG. 6, the turbine housing 111 includes a turbine housing body 112, a blade ring 113 provided in the turbine housing body 112, and a ring segment 114 provided on the radially inner side Dri of the blade ring 113. The blade ring 133 is fixed to the radially inner side Dri of the turbine casing body 112. The ring segment 114 is provided at a position on the radially outer side Dro of the blade row 151 of the turbine 110. The plurality of vanes 162 and the ring segment 114 are fixed to the radially inner side Dri of the vane ring 113.As illustrated in FIG. 7, the vane 162 of the turbine 110 has a vane body 163 extending in the radial direction Dr, an outer shell 164 provided on the radially outer side Dro of the vane body 163, and an inner shell 165 provided on the radially inner side Dri of the vane body 163. The outer shell 164 is fixed to the radially inner side Dri of the blade ring 113. A seal ring 166 is provided on the inner shell 165 at the radially inner side Dri thereof. The moving blade 152 of the turbine 110 has a blade body 153 extending in the radial direction Dr, a platform 154 provided on the radially inner side Dri of the blade body 153, and a blade root 155 provided on the radially inner side Dri of the platform 154. The blade root 155 is embedded in the turbine rotor shaft 121. An air flow path 156 is formed in the blade 152. The air flow path 156 is open on an outer surface of the blade root 155, and extends through the blade root 155 and the platform 154 to the blade body 153.A combustion gas flow path 115 through which a combustion gas G flows from the combustor 80 into the turbine 110 forms a cylindrical shape centered on the axial line Ar. An outer circumferential side of the combustion gas flow path 115 is defined by the ring segments 114 and the outer shell 164 of the vane 162. In addition, the inner circumferential side of the combustion gas flow path 115 is defined by the platforms 154 of the blades 152 and the inner casings 165 of the vanes 162.A plurality of cavities 133 are formed separately from each other in the radial direction Dr in the turbine rotor shaft 121, thereby forming ring shapes centered on the axial line Ar in each position in the axial direction Da respectively between the plurality of blade rows 151, that is, in each position in the axial direction Da of the plurality of blade rows 161. A plurality of cavities 133 formed in a position in the axial direction Da between a pair of blade rows 151 adjacent in the axial direction Da form a cavity group 132. Therefore, a plurality of the cavity groups 132 along the axial direction Da are formed in the turbine rotor shaft 121.Each of the cavity groups 132 is configured of two of the cavities 133: an outer cavity 133 oformed furthest on the radially outer side Dro in the turbine rotor shaft 121; and an inner cavity 133 iformed further on the radially inner side Dri than the outer cavity 133 o.The turbine rotor shaft 121 has a plurality of rotor disks 141 stacked in the axial direction Da and a spindle bolt 129 penetrating the plurality of rotor disks 141 and internal cavities 133 iin the axial direction Da. A tooth clutch (not illustrated in the drawings) for regulating relative rotation between rotor disks 141 adjacent in the axial direction Da is formed for each of the plurality of rotor disks 141.One of the blade rows 151 is fixed to one of the rotor disks 141. Therefore, there is one rotor disk 141 for each of the plurality of blade rows 151.The plurality of cavities 133 configuring a cavity group 132 are formed between two of the rotor disks 141 adjacent in the axial direction Da, like the cavities 33 of the compressor rotor shaft 21.A blade fixing part 149 for fixing the blade roots 155 of the plurality of blades 152 constituting one of the blade rows 151 is formed on the radially outer side Dro of each of the rotor disks 141.An upstream first concave part 143 uand an upstream second concave part 145 uare formed in each of the rotor disks 141. In order to form the outer cavity 133 oon the axially upstream side Dau of the rotor disk 141, the upstream first concave part is recessed from a part of the 143 uaxial upstream side Dau to the axially downstream side Dad in the rotor disk 141. In order to form the inner cavity 133 ion the axially upstream side Dau of the rotor disk 141, the upstream second concave part 145 uis recessed from a part of the axially upstream side Dau in the rotor disk 141 at a position further on the radially inner side Dri from the upstream first concave part 143 uto the axially downstream side Dad. Therefore, an annular upstream first arm part 142 uprotruding toward the axially upstream side Dau with respect to a lower surface of the upstream first concave part 143 uis formed on the radially outer side Dro of the upstream first concave part 143 u. In addition, an annular upstream second arm part 144 uprotruding toward the axially upstream side Dau with respect to the lower surface of the upstream first concave part 143 uand a lower surface of the upstream second concave part 145 uis formed between the upstream first concave part 143 uand the upstream second concave part 145 u.A plurality of upstream connection grooves 144 up, which are recessed toward the axial downstream side Dad to connect the upstream first concave part 143 uand the upstream second concave part 145 u, are formed in the annular upstream second arm part 144 u. The plurality of upstream connection grooves 144 upare aligned in the circumferential direction Dc. The upstream connection groove 144 upis formed, for example, by cutting out a part of a tooth of the above-mentioned tooth clutch in the rotor disk 141.In addition, a downstream first concave part 143 dand a downstream second concave part 145 dare formed in each of the rotor disks 141. To form the outer cavity 133 oon the axially downstream side Dad of the rotor disk 141, the downstream first concave part 143 dis recessed toward the axially upstream side Dau from a part on the axially downstream side Dad in the rotor disk 141. To form the inner cavity 133 ion the axially downstream side Dad of the rotor disk 141, the downstream second concave part 145 dis recessed toward the axially upstream side Dau from a part of the axially downstream side Dad in the rotor disk 141 at a position further on the radially inner side Dri than the downstream first concave part 143 d. Therefore, an annular downstream first arm part 142 dprotruding toward the axial downstream side Dad with respect to a lower surface of the downstream first concave part 143 dis formed on the radially outer side Dro of the downstream first concave part 143 d. In addition, an annular downstream second arm part 144 dprotruding toward the axial downstream side Dad with respect to the lower surface of the downstream first concave part 143 dand a lower surface of the downstream second concave part 145 dis formed between the downstream first concave part 143 dand the downstream second concave part 145 d.A plurality of downstream connecting grooves 144 dprecessed toward the axially upstream side Dau to connect the downstream first concave part 143 dand the downstream second concave part 145 dis formed in the annular downstream second arm part 144 d. The plurality of downstream connection grooves 144 dpare aligned in the circumferential direction Dc. The downstream communication groove 144 dpis formed by cutting out a tooth of the above-mentioned tooth clutch in the rotor disk 141, for example.The outer cavity 133 ois defined by the downstream first concave part 143 din the rotor disk 141 on the axially upstream side Dau of the two rotor disks 141 adjacent in the axial direction Da and the upstream first concave part 143 uin the rotor disk 141 on the axially downstream side Dad. The inner cavity 133 iis defined by the downstream second concave part 145 din the rotor disk 141 on the axially upstream side Dau of the two rotor disks 141 adjacent in the axial direction Da and the upstream second concave part 145 uin the rotor disk 141 on the axially downstream side Dad.The downstream first arm part 142 din the rotor disk 141 on the axially upstream side Dau of the two rotor disks 141 adjacent in the axial direction Da and the upstream first arm part 142 uin the rotor disk 141 on the axially downstream side Dad face each other and are separated from each other in the axial direction Da.The plurality of downstream communication grooves 144 dpin the rotor disk 141 on the axially upstream side Dau of the two rotor disks 141 adjacent in the axial direction Da and the plurality of upstream communication grooves 144 upin the rotor disk 141 on the axially downstream side Dad face each other in the axial direction Da. A communication hole is defined by the downstream communication groove 144 dpand the upstream communication groove 144 up. The pin hole in which the torque pin is mounted is formed cylindrically to correspond to the shape of the torque pin.A bolt through hole 138 into which the spindle bolt 129 is inserted is inserted in the rotor disk 141 to penetrate from the lower surface of the upstream second concave part 145 uto the lower surface of the downstream second concave part 145 d. The spindle hole 129 has a round cross-sectional shape in a direction perpendicular to the axial direction Da. Meanwhile, the cross-sectional shape of the bolt through hole 138 in the axial direction Da is an egg shape and the like. Therefore, when the spindle bolt 129 is inserted into the bolt through hole 138, a gap 138 sis formed between a part of an outer circumferential surface of the spindle bolt 129 and a part of an inner circumferential surface of the bolt through hole 138. The gap 138 sconstitutes a first mixed air flow path 134 from the lower surface of the upstream second concave part 145 uto the lower surface of the downstream second concave part 145 d. Note that the cross-sectional shape of the bolt through hole may be any shape as long as the gap 138 sis formed between a part of the outer circumferential surface of the spindle bolt 129 and a part of the inner circumferential surface of the bolt through hole 138, and may be, for example, a shape that includes two circles having respectively different center positions and that partially overlap each other, and the like.As illustrated in FIG. 6, a part that is farther on the radially outer side Dro than the upstream second arm part 144 uof the first rotor disk 141 a, which is farthest on the axially upstream side Dau of the plurality of rotor disks 141, faces the air introduction space 184. A second cooling air flow path 122 is formed in the first rotor disk 141 a. The second cooling air flow path 122 penetrates an outer surface of the blade attachment part 149 from a surface facing the air introduction space 184 in the first rotor disk 141 a. Therefore, the cooling air Ac in the air introduction space 184 is guided to the moving blades 152 of a first moving blade row 151a fixed to the first rotor disk 141a through the second cooling air flow path 122 and the blade fixing member 149.A part that is farther on the radial inner side Dri than the upstream second arm part 144 uof the first rotor disk 141 a, specifically, a surface forming the upstream second concave part 45 u, faces the mixing space 177. Therefore, mixed air Am flows into the first mixed air flow path 134 formed in the first rotor disk 141 aand opened in the lower surface of the upstream second concave part 45 uthereof. The mixed air Am flows from the first mixed air flow path 134 of the first rotor disk 141 ainto the inner cavity 133 iformed between the first rotor disk 141 aand a second rotor disk 141 b. Subsequently, the mixed air Am flows through the first mixed air flow path 134 formed in each of the first rotor disks 141 into the inner cavity 133 iformed between the rotor disks 141, respectively.The aforementioned plurality of through holes formed between each of the first rotor disk 141 aand the plurality of rotor disks 141 that are further on the axially downstream side Dad than the first rotor disk 141 aform a second mixed air flow path 135 that connects the outer cavity 133 oand the inner cavity 133 iformed between the two rotor disks 141 that are adjacent in the axial direction Da. Therefore, the mixed air Am in the inner cavity 133 iformed between each of the first rotor disk 141 aand the plurality of rotor disks 141 that are further on the axially downstream side Dad than the first rotor disk 141 aflows through the second mixed air flow path 135 into the outer cavity 133 oformed between these rotor disks 141, respectively. Note that, while a communication hole formed by cutting a tip of a tooth of the above-mentioned tooth clutch in the rotor disk 141 is used as the second mixed air flow path 135, a separate hole may be formed, and this hole may be used as the second mixed air flow path 135.A third mixed air flow path 136 penetrating a surface forming the upstream first concave part 143 uthrough an outer surface of the blade fixing part 149 is formed in the plurality of rotor disks 141 that are further on the axially downstream side Dad than the first rotor disk 141 a. Therefore, the mixed air Am in the inner cavity 133 iformed between each of the first rotor disk 141 aand the plurality of rotor disks 141 that are further on the axial downstream side Dad than the first rotor disk 141 aflows through the third mixed air flow path 136 into air flow paths 156 of the moving blades 152 that are fixed to the plurality of rotor disks 141 that are further on the axial downstream side Dad than the first rotor disk 141 a.A mixed air flow path 137 of the turbine rotor shaft 121 through which the mixed air Am flows is configured to include the first mixed air flow path 134, the inner cavity 133 i, the second mixed air flow path 135, the outer cavity 133 o, and the third mixed air flow path 136.The operation of the above-described gas turbine equipment will be described below.As illustrated in FIGS. 1 and 2, when the compressor rotor 20 is rotated, the outside air A flows from the air inlet port 12 of the compressor 10 into the air compression flow path 15. the air A is gradually compressed by the process of flowing from the axially upstream side Dau to the axially downstream side Dad in the air compression flow path 15 to become compressed air Acom. The compressed air Acom from the air compression flow path 15 flows from the air outlet port 18 of the compressor 10 through the air outlet flow path 17 into the intermediate housing 191.A part of the compressed air Acom that has flowed into the intermediate housing 191 flows into the combustion chamber 80 as illustrated in FIGS. 1 and 5. Fuel F is also supplied from the fuel source into the combustor 80.In the combustor 80, the fuel F is burned in the compressed air Acom to generate a combustion gas G having high temperature and high pressure.As illustrated in FIGS. 1 and 6, the high-temperature, high-pressure combustion gas G flows from the combustor 80 into the combustion gas flow path 115 of the turbine 110. By the process of flowing in the combustion gas flow path 115, the combustion gas G rotates the turbine rotor 120. A temperature of the combustion gas G reaches as high as one thousand and several hundred degrees Celsius as it flows out of the combustor 80 in the combustion gas flow path 115 of the turbine 110. The temperature of the combustion gas G gradually decreases as the combustion gas G flows in the combustion gas flow path 115.Another part of the compressed air Acom that has flowed into the intermediate housing 191 flows into the radiator 205 through the cooling air pipe 201 of the cooling system 200, as illustrated in FIGS. 1 and 5. The compressed air Acom flows into the radiator 205 and is cooled thereby, thereby becoming cooling air Ac. Here, a temperature of the compressed air Acom that has flowed into the intermediate housing 191 is 500° C., for example. In addition, the temperature of the compressed air Acom cooled by the radiator 205, that is, the cooling air Ac is 200° C., for example. The cooling air Ac flows the intermediate rotor shaft cover 181 through the cooling air pipe 201 and the cooling air pipe 189 that is introduced into the air introduction space 184 in the intermediate housing 191. A part of the cooling air Ac that has flowed into the air introduction space 184 flows into the air flow path 156 of each of the moving blades 152 of the first moving blade row 151 athat is fixed to the first moving blade 141 athrough the second cooling air flow path 122 formed in the first rotor disk 141 aof the turbine 110. The cooling air Ac cools the moving blade 152 by the process of flowing through the air flow path 156 of the moving blade 152. The cooling air Ac flows outside the moving blade 152, that is, flows into the combustion gas flow path 115 through the air flow path 156. Therefore, with the present embodiment, the plurality of blades 152 fixed to the first rotor disk 141 a, in other words, a plurality of first-stage blades 152 are cooled by the cooling air Ac by 200° C., for example.Part of the compressed air Acom flowing in the air compression flow path 15 of the compressor 10 flows into the ventilation flow path 22 from the inlet port 25 of the ventilation flow path 22 formed in the compressor rotor shaft 21 as the compressor extracted air Bcom, as illustrated in FIGS. 1 and 2. In other words, the part of the compressed air Acom flowing in the air compression flow path 15 of the compressor 10 flows in between the intermediate rotor disks 41 aadjacent in the axial direction Da as the compressor extracted air Bcom. The compressor extracted air Bcom that has flowed into the ventilation flow path 22 from the inlet port 25 of the ventilation flow path 22 flows into the distribution part 26 that extends in the axial direction Da through the inflow part 24 that extends in the radial direction Dr in the ventilation flow path 22. The compressor extracted air Bcom that has flowed into the distribution part 26 flows into the plurality of branch parts 27 formed at respectively different positions in the axial direction Da. All the compressor extracted air Bcom that has flowed into each of the branching parts 27 flows into the collecting part 28 that extends in the axial direction Da, and flows out through the collecting part 28 into the mixing space 177 in the inter-rotor shaft 171.Incidentally, as illustrated in FIG. 4, there is a clearance between an end on the radially outer side Dro of the moving blade 52 of the compressor 10 and an inner circumferential surface of the compressor housing 11 facing this end on the radially outer side Dro in the radial direction Dr. This clearance is generally referred to as a peak clearance CC, and is preferably as small as possible in terms of compressor performance.The radial direction dimension Dr of the compressor rotor 20, and particularly the compressor rotor shaft 21, is larger than the radial direction thickness dimension Dr of the compressor housing 11. therefore, the compressor rotor 20 has a larger heat capacity than the compressor housing 11, and thus the thermal response of the compressor rotor 20 to temperature changes in the compressed air Acom flowing through the air compression flow path 15 is lower than that for the compressor housing 11.When the changes of the peak clearance CC are large, the regular clearance needs to be increased. Note that the regular clearance is the peak clearance CC when the stable operation of the gas turbine 1 is continuous and the temperatures of both the compressor rotor 20 and the compressor casing 11 are continuously equal. When the regular clearance is large, the flow velocity of the compressed air Acom flowing between the end of the radially outer side Dro of the moving blade 52 and the inner circumferential surface of the compressor housing 11 increases during the continuous operation of the gas turbine 1. Therefore, when the regular clearance is large, not only the compressor output during the continuous operation of the gas turbine 1 decreases, but also the gas turbine output decreases.Thus, in the present embodiment, since the compressor extracted air Bcom extracted from the air in the compression flow path 15 flows into the compressor rotor shaft 21 and thus vents the inside of the compressor rotor shaft 21 as described above, the thermal response of the compressor rotor 20 with respect to temperature changes in the compressed air Acom flowing through the air compression flow path 15 increases, which then decreases the changes in the peak clearance CC. In the present embodiment, since changes in the peak clearance CC during startup are so small, the regular clearance can be made small. Therefore, in the present embodiment, the compressor capacity can be increased during the continuous operation of the gas turbine 1, and as a result, the gas turbine capacity can also be increased.In an axial compressor, the pressure and the temperature both increase due to a process of flowing from the axial upstream side Dau to the axial downstream side Dad. Therefore, temperature changes between non-operation and operation of the axial compressor are larger in parts on the axial downstream side Dad thereof than in parts on the axial upstream side Dau thereof. Thus, as illustrated in FIG. 2, in the present embodiment, a part of the compressed air Acom flowing between the two intermediate blade rows 51 aflows between each of the rotor disks 41 furthest on the axial downstream side Dad and the plurality of rotor disks 41 further on the axial upstream side Dau than the rotor disk 41 than the compressor extracted air Bcom, thus raising the thermal reaction of the axial downstream side Dad part inside the compressor rotor 20.As illustrated in FIGS. 1 and 5, the cooling air Ac generated by the cooling system 200 also flows into the mixing space 177 in the intermediate rotor shaft 171 in addition to the compressor extracted air Bcom from the compressor rotor shaft 21. The cooling air Ac generated from the radiator 205 of the cooling system 200 flows into the air introduction space 184 of the interrotor shaft cover 181 through the cooling air pipe 201 and the cooling air pipe 189 provided in the intermediate housing 191. A part of the cooling air Ac that has flowed into the air introduction space 184 flows into the mixing space 177 in the interrotor shaft 171 through the first cooling air flow path 178 formed in the interrotor shaft 171. As described above, the temperature of the cooling air Ac is 200° C. for example, and the temperature of the compressor extracted air Bcom flowing from the compressor rotor shaft 21 into the mixing space 177 is 400° C. The compressor extracted air Bcom from the compressor rotor shaft 21 and the cooling air Ac from the cooling system 200 are mixed in the mixing space 177, thereby becoming, for example, 300° C. warm mixed air Am.The mixed air Am flows through the first mixed air flow path 134 formed in the first rotor disk 141 aof the turbine 110 into the internal cavity 133 ibetween the first rotor disk 141 aand the second rotor disk 141 bas illustrated in FIGS. 1 and 6. A part of the mixed air Am that has flowed into the inner cavity 133 iis flowed into the outer cavity 133 obetween the first rotor disk 141 aand the second rotor disk 141 bthrough the second mixed air flow path 135. The mixed air Am flows through the third mixed air flow path 136 formed in the second rotor disk 141 binto the air flow path 156 of the plurality of blades 152 fixed to the second rotor disk 141 b. The mixed air Am cools the moving blade 152 by the process of flowing through the air flow path 156 of the moving blade 152. The mixed air Am flows outside the moving blade 152, that is, flows into the combustion gas flow path 115 through the air flow path 156.Another part of the mixed air Am that has flowed into the inner cavity 133 ibetween the first rotor disk 141 aand the second rotor disk 141 bflows into the inner cavity 133 ibetween the second rotor disk 141 band a third rotor disk 141 cthrough the first mixed air flow path 134 formed in the second rotor disk 141 b. A part of the mixed air Am that has flowed into the inner cavity 133 iis flowed into the outer cavity 133 obetween the second rotor disk 141 band the third rotor disk 141 cthrough the second mixed air flow path 135. The mixed air Am flows through the third mixed air flow path 136 formed in the third rotor disk 141 cinto the air flow paths 156 of the plurality of blades 152 fixed to the third rotor disk 141 c. The mixed air Am cools the moving blade 152 by the process of flowing through the air flow path 156 of the moving blade 152. The mixed air Am flows outside the moving blade 152, that is, flows into the combustion gas flow path 115 through the air flow path 156.Therefore, in the present embodiment, the turbine rotor shaft 121 is cooled by, for example, the 300° C. warm mixed air Am. In addition, in the present embodiment, the plurality of blades 152 fixed to the second rotor disk 141 band the third rotor disk 141 care also cooled by the mixed air Am warm to 300° C.Assume that the compressor extracted air Bcom that has exhausted from the compressor rotor shaft 21 is guided to the turbine rotor shaft 121 as it is. In this case, the plurality of blades 152 fixed to the turbine rotor shaft 121 would be cooled by, for example, 400° C. warm air. On the other hand, in the present embodiment, each of the blades 152 of the first blade row 151 aof the turbine 110 is cooled by the cooling air Ac (for example, 200° C.) from the cooling system 200. In addition, in the present embodiment, each of the moving blade 152 of the moving blade row 151 is further cooled on the axial downstream side Dad than the first moving blade row 151 aof the turbine 110 by the mixed air Am (for example, 300° C.) of the cooling air Ac from the cooling system and the compressor extracted air Bcom from the compressor rotor shaft 21.Therefore, in the present embodiment, the moving blade 152 of the turbine 110 can be cooled by air of lower temperature than in cases where the moving blade 152 of the turbine 110 is cooled by the compressor extracted air Bcom that has flowed out of the compressor rotor shaft 21. In addition, in the present embodiment, each of the moving blades 152 of the first moving blade row 151 ais cooled by 200° C. of the moving blades 152 of the turbine 110 exposed to the combustion gas G having the highest temperature. Therefore, in the present embodiment, the temperature of the combustion gas G generated from the combustor 80 can be increased, and as a result, output of the gas turbine 1 can be improved.A first modification example of the compressor rotor described above in the embodiments will be described with reference to FIG. 8.In the compressor rotor 20 according to the above-described embodiments, the compressed air Acom in the air compression flow path 15 is supplied to the compressor rotor shaft 21 from a location in the axial direction Da of the compressor rotor shaft 21 as the compressor extracted air Bcom. That is, the ventilation flow path 22 according to the above-mentioned embodiments has the one location in the axial direction Da as the inlet port 25.However, as with a compressor rotor 20 aaccording to the present modification example illustrated in FIG. 8, the compressed air Acom in the air compression flow path 15 may be supplied from a plurality of locations in the axial direction Da of a compressor rotor shaft 21 aas the compressor extracted air Bcom to an interior of a compressor rotor shaft 21 a. That is, the ventilation flow path 22 aaccording to the present modification example has the plurality of axial-direction locations Da as the inlet port 25. in this case, after the compressor extracted air Bcom is guided from one axial-direction location Da of the compressor rotor shaft 21 to a compressor rotor shaft 21 a, the compressor extracted air Bcom can be distributed to the respective different axial-direction locations Da of the compressor rotor shaft 21 a, while simultaneously, after the compressor extracted air Bcom is guided from another axial-direction location Da of the compressor rotor shaft 21 ainto the compressor rotor shaft 21 a, the compressor extracted air Bcom can be distributed to respective different axial-direction locations Da of the compressor rotor shaft 21 a.A second modification example of the compressor rotor described above in the embodiment will be described with reference to FIG. 9.In the compressor rotor 20 according to the above-described embodiments, after the compressed air Acom in the air compression flow path 15 is supplied to the compressor rotor shaft 21 as the compressor extracted air Bcom, the compressor extracted air Bcom is distributed to the axial upstream side Dau and the axial downstream side Dad. That is, the ventilation flow path 22 according to the above-described embodiments uses the inflow part 24 as a reference for the distribution part 26 extending toward the axial upstream side Dau and the axial downstream side Dad, and connects the plurality of branch parts 27 to each of the distribution parts 26 on the axial upstream side Dau and the distribution part 26 on the axial downstream side Dad.However, as with a compressor rotor 20 bof the present modification example illustrated in FIG. 9, after supplying the compressed air Acom in the air compression flow path 15 into the compressor rotor shaft 21 bas the compressor extracted air Bcom, the compressor extracted air Bcom may be distributed only at some locations on the axially upstream side Dau. That is, a ventilation flow path 22 baccording to the present modification example uses an introduction part 24 bas a reference for extending a distribution part 26 btoward only the axially upstream side Dau, and connects the plurality of branch parts 27 to the distribution part 26 b.Note that after the compressed air Acom in the air compression flow path 15 is introduced into the compressor rotor shaft 21 bas the compressor extracted air Bcom, the compressor extracted air Bcom may be distributed only to some locations on the axial downstream side Dad.A third modification example of the compressor rotor described above in the embodiments will be described with reference to FIG. 10.In the compressor rotor 20 according to the above-described embodiments, after the compressed air Acom in the air compression flow path 15 is introduced into the compressor rotor shaft 21 as the compressor extracted air Bcom, the compressor extracted air Bcom is distributed to respectively different positions in the axial direction Da. That is, the ventilation flow path 22 according to the above-mentioned embodiment has the plurality of branch parts 27 at respectively different positions in the axial direction Da.However, as with a compressor rotor 20 cof the present modification example illustrated in FIG. 10, after flowing the compressed air Acom in the air compression flow path 15 into a compressor rotor shaft 21 cas the compressor extracted air Bcom, the compressor extracted air Bcom can flow out as it is into the mixing space 177 without being distributed to a plurality of different locations in the axial direction Da, respectively. That is, although the ventilation flow path 22 caccording to the present modification example includes the inflow part 24, there are no parts therein that are the same as the distribution part 26 or the branching part 27 of the above-described embodiments. In this case, a plurality of inflow parts 24 may be formed at respectively different positions in the axial direction Da, and the compressor extracted air Bcom that has flowed into the inflow parts 24 may be discharged into the mixing space 177 as it is without being distributed to a plurality of respectively different locations in the axial direction Da.A modification example of the turbine rotor described above in the embodiments will be described with reference to FIG. 11.In the turbine rotor 120 according to the above-described embodiments, the cooling air Ac from the cooling system 200 is supplied only to the first blade row 151 a. However, as in a turbine rotor 120 of the present modification example illustrated in FIG. 11, the cooling air Ac may be supplied not only to the first blade row 151 abut also to the second blade row 151 band the third blade row 151 c, which are further on the axial downstream side Dad than the first blade row 151 a.A third cooling air flow path 123 penetrating in the axial direction Da is formed in the plurality of rotor disks 141 configuring a turbine rotor shaft 121 aaccording to the present modification example, the first rotor disk 141 amost on the axial upstream side Dau, and the second rotor disk 141 badjacent to the first rotor disk 141 aon the axial downstream side Dad. The third cooling air flow path 123 formed in the first rotor disk 141 aextends from a part that is farther on the radially outer side Dro than the upstream second arm part 144 uof the first rotor disk 141 a, toward the axially downstream side Dad from a position facing the air introduction space 184, and is open on the lower surface of the downstream first concave part 143 dof the first rotor disk 141 a. Therefore, the outer cavity 133 ois connected between the first rotor disk 141 aand the second rotor disk 141 band the air introduction space 184 through the third cooling air flow path 123. In addition, the third cooling air flow path 123 formed in the second rotor disk 141 bextends from the lower surface of the upstream first concave part 143 uof the second rotor disk 141 bto the axial downstream side Dad, and is open in the lower surface of the downstream first concave part 143 dof the second rotor disk 141 b. Therefore, the outer cavity 133 obetween the first rotor disk 141 aand the second rotor disk 141 band the outer cavity 133 obetween the second rotor disk 141 band the third rotor disk 141 care connected through the third cooling air flow path 123.In the present modification example, the mixed air Am in the inner cavity 133 ibetween the first rotor disk 141 aand the second rotor disk 141 bflows into the outer cavity 133 obetween the first rotor disk 141 aand the second rotor disk 141 bthrough the second mixed air flow path 135. In addition, the cooling air Ac of the air introduction space 184 flows into the outer cavity 133 othrough the third cooling air flow path 123 of the first rotor disk 141 a. Therefore, for example, 200° C. cool air Ac is mixed with 300° C. mixed air Am in the outer cavity 133 obetween the first rotor disk 141 aand the second rotor disk 141 b. As a result, a mixed air Am 1 having a lower temperature than the mixed air Am generated in the mixing space 177 is generated in the outer cavity 133 o. A part of the mixed air Am 1 flows through the third mixed air flow path 136 formed in the second rotor disk 141 binto the air flow path 156 of each of the moving blades 152 of the second moving blade row 151 bfixed to the second rotor disk 141 b.Another part of the mixed air Am 1 in the outer cavity 133 obetween the first rotor disk 141 aand the second rotor disk 141 bflows into the outer cavity 133 obetween the second rotor disk 141 band a third rotor disk 141 cthrough the third cooling air flow path 123 formed in the second rotor disk 141 b. The mixed air Am flows into the outer cavity 133 othrough the second mixed air flow path 135 in the inner cavity 133 ibetween the second rotor disk 141 band the third rotor disk 141 c. Therefore, 300° C. mixed air Am is mixed with the mixed air Am 1 having a temperature below 300° C. in the outer cavity 133 obetween the second rotor disk 141 band the third rotor disk 141 c. As a result, a mixed air Am 2 having a lower temperature than the mixed air Am generated in the mixing space 177 is generated in the outer cavity 133 o. A part of the mixed air Am 2 flows through the third mixed air flow path 136 formed in the third rotor disk 141 cinto the air flow path 156 of each of the moving blades 152 of the third moving blade row 151 cfixed to the third rotor disk 141 c.Therefore, in the present modification example, low-temperature air can be supplied to the plurality of blades 152 fixed to the second rotor disk and the third rotor disk than in the above-described embodiments.In one aspect of the present invention, the turbine rotor can be cooled to a greater extent.1 Gas turbine 2 Gas turbine rotor 3 Gas turbine casing 9 Generator 10 Compressor 11 Compressor casing 12 Air inlet port 13 Compressor casing main body 14 Vane retaining ring 15 Air compression flow path 16 Diffuser 17 Air outlet flow path 18 Air outlet port 20, 20 a, 20 b, 20 c Kompressor rotor 21, 21 a, 21 b, 21 c Kompressor rotor shaft 22, 22 a, 22 b, 22 c Lüftungs flow path 23 Introduction part 24, 24 b Part 25 Inlet port 26 Distribution part 27 Branching part 28 Collection part 29 Spindle bolt 32 Cavity group 33 Cavity 33 o Außen cavity 33 m Zwischen cavity 33 i Innen cavity 38 Bolt through hole 39, 39a torque pin 41 rotor disk 41a intermediate rotor disk 49 blade mounting part 51 blade row 51a intermediate blade row 52 blade 61 blade row 62 blade 80 combustor 110 turbine 111 turbine casing 115 combustion gas flow path 120, 120a turbine rotor 121, 39a torque pin, 121 aturbine shaft 122 second cooling air flow path 123 third cooling air flow path 129 spindle bolt 132 cavity group 133 cavity 133o outer cavity 133i inner cavity 134 first mixed air flow path 135 second mixed air flow path 136 third mixed air flow path 137 mixed air flow path 138 bolt through hole 138s gap 141 rotor disk 141a first rotor disk 141b second rotor disk 141c third rotor disk 149 blade attachment part 151 blade row 151a first blade row 151b second blade row 151c third blade row 152 blade 156 air flow path 161 blade row 161a first blade row 162 blade 171 intermediate rotor shaft 177 mixed space 178 first cooling air flow path (or simply cooling air flow path) 181 intermediate rotor shaft cover 184 air introduction space 188 Cooling air introducing member 189 Cooling air pipe 191 Intermediate housing 200 Cooling system 201 Cooling air pipe 205 Radiator

Claims

A gas turbine rotor (2) configured to rotate about an axial line (Ar) in a gas turbine casing (3), the gas turbine rotor (2) comprising: a compressor rotor (20;20a;20b;20c) of a compressor (10) configured to rotate about the axial line (Ar); and a turbine rotor (120;120a) of a turbine (110) disposed on the axial line (Ar) and connected to the compressor rotor (20;20a;20b;20c) to integrally rotate with the compressor rotor (20;20a;20b;20c) about the axial line (Ar), the gas turbine rotor (2) having formed therein: a ventilation flow path (22;22a;22b;22c) for guiding compressed air (Acom) flowing inside the gas turbine casing (3) further on an axially upstream side (Dau) than an air outlet port (18) of the compressor (10) to an interior of the compressor rotor (20;20a;20b;20c ); a cooling air flow path (178; 122; 123) for guiding cooling air (Ac) having a temperature lower than that of the compressed air (Acom) flowing through the ventilation flow path (22;22a;22b;22c) to a part that is further on the axially downstream side (Dad) than the air outlet port (18); a mixing space (177) connected to the ventilation flow path (22;22a;22b;22c) and the cooling air flow path (178; 122; 123), and configured to mix, in the mixing space (177), the compressed air (Acom) that has passed through the ventilation flow path (22;22a;22b;22c) and the cooling air (Ac) that has passed through the cooling air flow path (178; 122; 123); and a mixed air flow path (137) connected to the mixing space (177) and configured to guide mixed air (Am) generated by mixing the compressed air (Acom) and the cooling air (Ac) into the turbine rotor (120; 120a); characterized in that the gas turbine rotor (2) further comprises an inter-rotor shaft (171) disposed on the axial line (Ar) between the compressor rotor (20;20a;20b;20c) and the turbine rotor (120; 120a) and connected to the compressor rotor (20;20a;20b;20c) and the turbine rotor (120; 120a), the cooling air flow path (178; 122; 123) and the mixing space (177) being formed in the inter-rotor shaft (171).A gas turbine rotor (2) configured to rotate about an axial line (Ar) in a gas turbine casing (3), the gas turbine rotor (2) comprising: a compressor rotor (20;20a;20b;20c) of a compressor (10) configured to rotate about the axial line (Ar); and a turbine rotor (120;120a) of a turbine (110) disposed on the axial line (Ar) and connected to the compressor rotor (20;20a;20b;20c) to integrally rotate with the compressor rotor (20;20a;20b;20c) about the axial line (Ar), the gas turbine rotor (2) having formed therein: a ventilation flow path (22;22a;22b;22c) for guiding compressed air (Acom) flowing inside the gas turbine casing (3) further on an axially upstream side (Dau) than an air outlet port (18) of the compressor (10) to an interior of the compressor rotor (20;20a;20b;20c ); a cooling air flow path (178; 122; 123) for guiding cooling air (Ac) having a temperature lower than that of the compressed air (Acom) flowing through the ventilation flow path (22;22a;22b;22c) to a part that is further on the axially downstream side (Dad) than the air outlet port (18); a mixing space (177) connected to the ventilation flow path (22;22a;22b;22c) and the cooling air flow path (178; 122; 123), and configured to mix, in the mixing space (177), the compressed air (Acom) that has passed through the ventilation flow path (22;22a;22b;22c) and the cooling air (Ac) that has passed through the cooling air flow path (178; 122; 123); and a mixed air flow path (137) connected to the mixing space (177) and configured to direct mixed air (Am) generated by mixing the compressed air (Acom) and the cooling air (Ac) into the turbine rotor (120; 120a); characterized in that the turbine rotor (120; 120a) includes a turbine rotor shaft (121) configured to rotate about the axial line (Ar), and a plurality of blade rows (151) fixed to an outer periphery of the turbine rotor shaft (121) and aligned in an axial direction (Da), and the mixed air flow path (137) is connected through an inner space of the turbine rotor shaft (121) to a blade row (151b, 151c) further on the axially downstream side (Dad) than a first blade row (151a) farthest on the axially upstream side (Dau) among the plurality of blade rows (151).The gas turbine rotor (2) according to claim 2, wherein in addition to a first cooling air flow path (178) being the cooling air flow path connected to the mixing space (177), a second cooling air flow path (122) for guiding the cooling air (Ac) to the first blade row (151a) is also formed.The gas turbine rotor (2) according to claim 3, wherein a third cooling air flow path (123) connecting the second cooling air flow path (122) and the mixed air flow path (137) is formed in the turbine rotor (120; 120a).A gas turbine rotor (2) configured to rotate about an axial line (Ar) in a gas turbine casing (3), the gas turbine rotor (2) comprising: a compressor rotor (20;20a;20b;20c) of a compressor (10) configured to rotate about the axial line (Ar); and a turbine rotor (120;120a) of a turbine (110) disposed on the axial line (Ar) and connected to the compressor rotor (20;20a;20b;20c) to integrally rotate with the compressor rotor (20;20a;20b;20c) about the axial line (Ar), the gas turbine rotor (2) having formed therein: a ventilation flow path (22;22a;22b;22c) for guiding compressed air (Acom) flowing inside the gas turbine casing (3) further on an axially upstream side (Dau) than an air outlet port (18) of the compressor (10) to an interior of the compressor rotor (20;20a;20b;20c ); a cooling air flow path (178; 122; 123) for guiding cooling air (Ac) having a temperature lower than that of the compressed air (Acom) flowing through the ventilation flow path (22;22a;22b;22c) to a part that is further on the axially downstream side (Dad) than the air outlet port (18); a mixing space (177) connected to the ventilation flow path (22;22a;22b;22c) and the cooling air flow path (178; 122; 123), and configured to mix, in the mixing space (177), the compressed air (Acom) that has passed through the ventilation flow path (22;22a;22b;22c) and the cooling air (Ac) that has passed through the cooling air flow path (178; 122; 123); and a mixed air flow path (137) connected to the mixing space (177) and configured to direct mixed air (Am) generated by mixing the compressed air (Acom) and the cooling air (Ac) into the turbine rotor (120; 120a); characterized in that, the compressor rotor (20;20a;20b;20c) having a compressor rotor shaft (21;21a;21b) configured to rotate about the axial line (Ar), and a plurality of blade rows (51) fixed to an outer periphery of the compressor rotor shaft (21;21a;21b) and aligned in the axial direction (Da), the ventilation flow path (22;22a;22b) having an introduction part (23) for guiding the compressed air (Acom) flowing between two blade rows (51) of the plurality of blade rows (51) of the compressor rotor (20;20a;20b;20c) adjacent in the axial direction (Da) to an inner space of the compressor rotor (20;20a;20b;20c), a plurality of branch parts (27), branching off from the introduction part (23) and formed at respectively different positions in the axial direction (Da) so that the compressed air (Acom) can flow into the introduction part (23) from the introduction part (23), and a collection part (28) connected to each of the plurality of branching parts (27) so that the compressed air (Acom) after passing through the plurality of branching parts (27) can flow into the same and through which the compressed air (Acom) that has flowed in can flow out into the mixing space (177), each of the plurality of branching parts (27) has a cavity (33m, 33i), the introduction part (23) has: an inlet port (25) into which the compressed air (Acom) flowing between two blade rows (51, 51a) can flow, an inflow part (24; 24b) extending from the inlet port (25) to a radially inner side (Dri) with respect to the axial direction (Ar), and a distribution part (26) extending from the inflow part (24; 24b) to the axially upstream side (Dau) and the axially downstream side (Dad), wherein the distribution part (26) is formed in a radial direction (Dr) between the inflow part (24; 24b) and the plurality of branch parts (27) and is connected to the plurality of branch parts (27).A gas turbine (1) comprising: a gas turbine rotor (2) according to any one of claims 1 to 5; and a gas turbine casing (3).A gas turbine equipment comprising: a gas turbine (1) according to claim 6; and a cooling system (200) for generating cooling air (Ac) by cooling compressed air (Acom) which is the air compressed in the compressor (10) of the gas turbine (1), wherein the gas turbine (1) has a cooling air introduction member (188) for guiding the cooling air (Ac) generated in the cooling system (200) to the cooling air flow path (178, 122; 123) of the gas turbine rotor (2).

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