Gas turbine rotor

Abstract

To provide a gas turbine rotor capable of improving workability of work for fastening a plurality of compressor disks and a flange part of an intermediate shaft by a bolt and a nut.SOLUTION: A gas turbine rotor, wherein a compressor rotor includes a plurality of compressor disks arranged along an axial direction, and at least one intermediate disk provided between a compressor disk of a final stage among the plurality of compressor disks and an intermediate shaft, no blade is provided on an outer circumferential surface of each of the at least one intermediate disk, and a first flange portion protruding inward in a radial direction is formed on a compressor rotor side of the intermediate shaft, the gas turbine rotor further includes a bolt penetrating the plurality of compressor disks, the at least one intermediate disk, and the first flange part in the axial direction, and a nut attached to the bolt on a side opposite to the at least one intermediate disk with respect to the first flange part.SELECTED DRAWING: Figure 2

Description

[Technical Field]

[0001] The present disclosure relates to gas turbine rotors. [Background technology]

[0002] Patent Document 1 discloses a gas turbine rotor including a compressor rotor, a turbine rotor, and a cylindrical intermediate shaft for connecting the compressor rotor and the turbine rotor. The compressor rotor includes a plurality of compressor disks arranged along the axial direction, and a flange portion protruding radially outward from the cylindrical intermediate shaft is fastened to the plurality of compressor disks with bolts. [Prior art documents] [Patent documents]

[0003] [Patent Document 1] Japanese Patent Application Laid-Open No. 2004-218480 Summary of the Invention [Problem to be solved by the invention]

[0004] In a configuration in which a flange portion that protrudes radially inward is formed on the compressor rotor side of a cylindrical intermediate shaft, when attaching a nut to a bolt on the opposite side of the flange portion from the compressor rotor, it is necessary to access the nut through the inner peripheral side of the cylindrical intermediate shaft. Therefore, when the axial length of the intermediate shaft is long or when the opening on the cylindrical intermediate shaft opposite the nut is narrow, the workability of the nut attachment work decreases. In particular, when multiple combustors are arranged on the outer peripheral side of the intermediate shaft and the combustors are large relative to the size of the gas turbine rotor, the axial length of the intermediate shaft tends to be long depending on the dimensions of the combustors, making it difficult to access the above-mentioned nut.

[0005] In view of the above circumstances, at least one embodiment of the present disclosure has an object to provide a gas turbine rotor in which a flange portion that protrudes radially inward on the compressor rotor side of a cylindrical intermediate shaft is formed, and which can improve the workability of fastening a plurality of compressor disks to the flange portion of the intermediate shaft with bolts and nuts. [Means for solving the problem]

[0006] In order to achieve the above object, a gas turbine rotor according to at least one embodiment of the present disclosure comprises: A gas turbine rotor including a compressor rotor, a turbine rotor, and a cylindrical intermediate shaft for connecting the compressor rotor and the turbine rotor, The compressor rotor is a plurality of compressor disks arranged along the axial direction of the gas turbine rotor; a plurality of compressor rotor blades fixed to the outer peripheral surfaces of the plurality of compressor disks; at least one intermediate disk provided between a final stage compressor disk among the plurality of compressor disks and the intermediate shaft; Including, The at least one intermediate disk has an outer peripheral surface that is free of blades, a first flange portion protruding inward in a radial direction of the gas turbine rotor is formed on the compressor rotor side of the intermediate shaft, The gas turbine rotor comprises: a bolt that passes through the plurality of compressor disks, the at least one intermediate disk, and the first flange portion in the axial direction; a nut attached to the bolt on the opposite side of the first flange portion from the at least one intermediate disk; Further provided with: [Effects of the Invention]

[0007] According to at least one embodiment of the present disclosure, there is provided a gas turbine rotor in which a flange portion that protrudes radially inward on the compressor rotor side of a cylindrical intermediate shaft is formed, and which can improve the workability of fastening a plurality of compressor disks to the flange portion of the intermediate shaft with bolts and nuts. [Brief explanation of the drawings]

[0008] [Figure 1] 1 is a diagram showing a schematic configuration of a gas turbine 2 according to an embodiment. [Figure 2] 2 is a schematic cross-sectional view taken along the axial direction of a gas turbine rotor 3 included in the gas turbine 2. FIG. [Figure 3] 3 is an enlarged schematic cross-sectional view of the axial center portion of the gas turbine rotor 3 in FIG. 2. [Figure 4] 4 is a schematic cross-sectional view showing an enlarged view of an intermediate disk 16 and its vicinity in FIG. 3. [Figure 5] FIG. 1 is a schematic cross-sectional view showing, arranged one above the other, the configuration of the compressor rotor 10 in a state in which the coupling ring 18 and the turbine rotor 12 are not attached to the intermediate shaft 14 in a gas turbine rotor 03 according to a comparative embodiment, and the configuration of the compressor rotor 10 in a state in which the coupling ring 18 and the turbine rotor 12 are not attached to the intermediate shaft 14 in the gas turbine rotor 3 according to the above-described embodiment. [Figure 6] FIG. 1 is a schematic cross-sectional view showing a state in which a coupling ring 18 and a turbine rotor 12 are not attached to an intermediate shaft 14 in a gas turbine rotor 03 according to a reference embodiment. DETAILED DESCRIPTION OF THE INVENTION

[0009] Hereinafter, several embodiments of the present disclosure will be described with reference to the accompanying drawings. However, the dimensions, materials, shapes, relative arrangements, etc. of components described as embodiments or shown in the drawings are merely illustrative examples and are not intended to limit the scope of the invention. For example, expressions expressing relative or absolute arrangement such as "in a certain direction," "along a certain direction," "parallel," "orthogonal," "center," "concentric," or "coaxial" not only express such an arrangement exactly, but also express a state in which there is a relative displacement with a tolerance or an angle or distance to the extent that the same function is obtained. For example, expressions such as "identical," "equal," and "homogeneous" that indicate that something is in an equal state not only indicate a state of strict equality, but also indicate a state in which there is a tolerance or a difference to the extent that the same function is obtained. For example, expressions representing shapes such as a square shape or a cylindrical shape not only represent shapes such as a square shape or a cylindrical shape in the strict geometric sense, but also represent shapes including uneven portions, chamfered portions, etc., to the extent that the same effect can be obtained. On the other hand, the expressions "comprise," "include," "have," "includes," or "have" of one element are not exclusive expressions that exclude the presence of other elements.

[0010] FIG. 1 is a diagram showing a schematic configuration of a gas turbine 2 according to one embodiment. As shown in Fig. 1, the gas turbine 2 includes a compressor 4, multiple combustors 6, and a turbine 8. The compressor 4 compresses air to generate compressed air, and supplies the compressed air to the multiple combustors 6. The multiple combustors 6 mix the compressed air supplied from the compressor 4 with fuel and combust it to generate combustion gas. The turbine 8 is disposed coaxially with the compressor 4, is driven by the combustion gas generated in the multiple combustors 6, and converts the energy of the combustion gas into mechanical energy.

[0011] 2 is a schematic cross-sectional view taken along the axial direction of a gas turbine rotor 3 included in the gas turbine 2. FIG. 3 is a schematic cross-sectional view showing an enlarged view of the axial center of the gas turbine rotor 3 in FIG. 2, the gas turbine rotor 3 includes a compressor rotor 10, a turbine rotor 12, an intermediate shaft 14, a plurality of intermediate disks 16, and a joint ring 18. The compressor rotor 10, the turbine rotor 12, the intermediate shaft 14, the plurality of intermediate disks 16, and the joint ring 18 are coaxially connected and configured to rotate integrally. The gas turbine 2 also includes a substantially cylindrical intermediate shaft casing 15 that houses the intermediate shaft 14, the plurality of intermediate disks 16, and the joint ring 18, and a plurality of combustors 6 are arranged on the outer circumferential side of the intermediate shaft casing 15 at intervals in the circumferential direction of the gas turbine rotor 3.

[0012] In the following description, unless otherwise specified, "axial direction" means the axial direction of the gas turbine rotor 3 (the direction of the rotational axis O of the gas turbine rotor 3), "radial direction" means the radial direction of the gas turbine rotor 3, and "circumferential direction" means the circumferential direction of the gas turbine rotor 3, unless otherwise specified.

[0013] For example, as shown in FIG. 2 , a compressor rotor 10 includes a plurality of substantially circular compressor disks 20 arranged along the axial direction, and a plurality of compressor blades 24 fixed to the outer peripheral surface 22 of each of the plurality of compressor disks 20. The compressor rotor 10 also includes a plurality of spindle bolts 26 and a plurality of nuts 54 for fastening the plurality of compressor disks 20 together. Each of the compressor disks 20 has a plurality of through holes 28 formed at intervals in the circumferential direction and penetrating the compressor disk 20 in the axial direction. The plurality of spindle bolts 26 are arranged at intervals in the circumferential direction, and each of the spindle bolts 26 extends in the axial direction and is inserted into the through holes 28 that are aligned in the axial direction. As will be described in detail later, the plurality of nuts 54 are attached to the tip ends of the plurality of spindle bolts 26, respectively.

[0014] For example, as shown in FIG. 2 , the turbine rotor 12 includes a plurality of substantially circular turbine disks 30 arranged along the axial direction and a plurality of turbine blades 34 fixed to the outer peripheral surface 32 of each of the plurality of turbine disks 30. The turbine rotor 12 also includes a plurality of spindle bolts 36 and a plurality of nuts 56 for fastening the plurality of turbine disks 30 together. Each of the turbine disks 30 has a plurality of through holes 38 that axially penetrate the turbine disk 30 and are spaced apart in the circumferential direction. The plurality of spindle bolts 36 are arranged at intervals in the circumferential direction, and each of the spindle bolts 36 extends in the axial direction and is inserted into the through holes 38 that are aligned in the axial direction. As will be described in detail later, the plurality of nuts 56 are attached to the tip ends of the plurality of spindle bolts 36, respectively.

[0015] 3, the intermediate shaft 14 is disposed between the compressor rotor 10 and the turbine rotor 12 and is formed in a substantially cylindrical shape. In the illustrated example, the intermediate shaft 14 is disposed between a coupling ring 18 and an intermediate disk 16a, which is the farthest from the compressor rotor 10 among the plurality of intermediate disks 16. A first flange portion 42 protruding radially inward is formed on the intermediate shaft 14 on the compressor rotor 10 side, and a second flange portion 44 protruding radially inward is formed on the intermediate shaft 14 on the turbine rotor 12 side. More specifically, the intermediate shaft 14 includes a cylindrical tubular portion 40, a ring-shaped first flange portion 42 protruding radially inward from one axial end (the end on the compressor rotor 10 side) of the ring-shaped portion 40, and a ring-shaped second flange portion 44 protruding radially inward from the other axial end (the end on the turbine rotor 12 side) of the ring-shaped portion 40.

[0016] 3, the first flange portion 42 has a plurality of through holes 46 axially penetrating the first flange portion 42 and spaced apart in the circumferential direction. The second flange portion 44 has a plurality of through holes 48 axially penetrating the second flange portion 44 and spaced apart in the circumferential direction. In the exemplary embodiment shown in FIG. 3, the inner diameter d2 of the second flange portion 44 is larger than the inner diameter d1 of the first flange portion 42.

[0017] For example, as shown in FIG. 3 , the multiple intermediate disks 16 are arranged in the axial direction between the compressor disk 20f of the final stage 4f of the compressor 4 (i.e., the compressor disk 20f closest to the turbine rotor 12 among the multiple compressor disks 20) and the intermediate shaft 14. In the illustrated example, the multiple intermediate disks 16 are two intermediate disks 16 arranged in the axial direction. Each of the intermediate disks 16 is formed in a substantially circular plate shape, and no blades are provided on the outer peripheral surface 19 of each of the intermediate disks 16. In other words, no compressor rotor blades 24 are provided on the outer peripheral surface 19 of each of the intermediate disks 16, and the entire outer peripheral surface 19 of each of the intermediate disks 16 is formed by a cylindrical surface. Each of the intermediate disks 16 is configured separately from each of the compressor disks 20f and the intermediate shaft 14. In other words, each of the intermediate disks 16 is configured as a separate part from each of the compressor disks 20f and the intermediate shaft 14.

[0018] 3, for example, an intermediate disk 16a, which is closest to the turbine rotor 12 among the multiple intermediate disks 16, faces the first flange portion 42 of the intermediate shaft 14 in the axial direction, and the intermediate disk 16a and the first flange portion 42 of the intermediate shaft 14 are in contact with each other in the axial direction. An intermediate disk 16b, which is farthest from the turbine rotor 12 among the multiple intermediate disks 16, faces the compressor disk 20f of the final stage 4f in the axial direction, and the intermediate disk 16b and the compressor disk 20f are in contact with each other in the axial direction. Each intermediate disk 16 has a plurality of through holes 50 formed at intervals in the circumferential direction, penetrating the intermediate disk 16 in the axial direction.

[0019] 2 and 3, each of the plurality of spindle bolts 26 is configured to axially penetrate through the plurality of compressor disks 20, the plurality of intermediate disks 16, and the first flange portion 42 of the intermediate shaft 14. More specifically, each of the spindle bolts 26 is inserted through the through hole 28 of each compressor disk 20, the through hole 50 of each intermediate disk 16, and the through hole 46 of the first flange portion 42.

[0020] 3, for example, the multiple nuts 54 are attached to the multiple spindle bolts 26 on the opposite side (the turbine rotor 12 side) of the multiple intermediate disks 16 with respect to the first flange portion 42. Therefore, the first flange portion 42 is located between the multiple nuts 54 and the intermediate disk 16. Each nut 54 is attached to the tip end of the corresponding spindle bolt 26 at a position between the first flange portion 42 and the second flange portion 44 on the inner peripheral side of the cylindrical intermediate shaft 14, and is tightened to a position where it contacts the first flange portion 42.

[0021] 3, the coupling ring 18 is disposed between the turbine rotor 12 and the intermediate shaft 14 and has an annular shape. The coupling ring 18 axially faces the turbine disk 30a, which of the multiple turbine disks 30 is closest to the compressor rotor 10, and the turbine disk 30a and the coupling ring 18 are in axial contact. The coupling ring 18 and the second flange portion 44 of the intermediate shaft 14 face each other in the axial direction and are in axial contact with each other. The coupling ring 18 has a plurality of through holes 52 formed at intervals in the circumferential direction, penetrating the coupling ring 18 in the axial direction.

[0022] 2 and 3, each of the plurality of spindle bolts 36 is configured to pass through the plurality of turbine disks 30, the joint ring 18, and the second flange portion 44 of the intermediate shaft 14. More specifically, each of the spindle bolts 36 is inserted through the through hole 38 of each turbine disk 30, the through hole 52 of the joint ring 18, and the through hole 48 of the second flange portion 44.

[0023] For example, as shown in FIG. 3 , the nuts 56 are attached to the spindle bolts 36 on the opposite side of the second flange portion 44 from the turbine rotor 12 (the compressor rotor 10 side). Therefore, the second flange portion 44 is located between the nuts 56 and the turbine rotor 12. Each nut 56 is attached to the tip of a corresponding spindle bolt 36 at a position between the first flange portion 42 and the second flange portion 44 on the inner circumferential side of the cylindrical intermediate shaft 14, and is tightened to a position where it contacts the second flange portion 44. Note that, for convenience, the spindle bolts 26 and 36 are shown in the same cross section in FIGS. 2 and 3 , but the circumferential positions at which the spindle bolts 26 are provided may be different from the circumferential positions at which the spindle bolts 36 are provided. Furthermore, a plurality of coupling bolts (not shown) that fasten the second flange portion 44 and the coupling ring 18 may be provided at circumferential positions different from the positions of the spindle bolts 36.

[0024] FIG. 4 is an enlarged schematic cross-sectional view of the intermediate disc 16 and its vicinity in FIG. 4 etc., the total S of the thicknesses t of the plurality of intermediate disks 16 is greater than the thickness u of the compressor disk 20f in the final stage 4f, and the thickness t of each of the plurality of intermediate disks 16 is greater than the thickness u of the compressor disk 20f in the final stage 4f. Note that in this specification, the thickness t of the intermediate disk 16 means the thickness of the intermediate disk 16 in the axial direction, and the thickness of the compressor disk 20f means the thickness of the compressor disk 20f in the axial direction.

[0025] Each of the intermediate disks 16 includes a first side surface 61 facing the turbine rotor 12 in the axial direction and a second side surface 62 facing the opposite side of the turbine rotor 12 in the axial direction (toward the compressor disk 20f). In the exemplary embodiment shown in FIG. 4 etc., in each of the intermediate disks 16, a recess 63 and a recess 64 are formed on the first side surface 61, and a recess 65 and a recess 66 are formed on the second side surface 62. The recess 63 is located radially inward of the spindle bolt 26 and is formed annularly around the rotation axis O. The recess 64 is located radially inward of the spindle bolt 26 and is formed annularly around the rotation axis O. The recess 65 is located radially inward of the spindle bolt 26 and is formed annularly around the rotation axis O. The recess 66 is located radially inward of the spindle bolt 26 and is formed annularly around the rotation axis O. In the example shown in Figure 4, an annular cavity 67 is defined by a recess 63 in one intermediate disk 16b and a recess 65 in the other intermediate disk 16a of two adjacent intermediate disks 16, and an annular cavity 68 is defined by a recess 64 in one intermediate disk 16b and a recess 66 in the other intermediate disk 16a.

[0026] Here, the effects achieved by the gas turbine rotor 3 will be described with reference to FIG. 5 and other figures. FIG. 5 is a schematic cross-sectional view showing, side by side, the configuration of the compressor rotor 10 in a state where the coupling ring 18 and the turbine rotor 12 are not attached to the intermediate shaft 14 in a gas turbine rotor 03 according to a comparative embodiment, and the configuration of the compressor rotor 10 in a state where the coupling ring 18 and the turbine rotor 12 are not attached to the intermediate shaft 14 in the gas turbine rotor 3 according to the above-described embodiment.

[0027] In the comparative embodiment, the gas turbine rotor 03 does not include an intermediate disk 16, and the compressor rotor 10 and the turbine rotor (not shown) are connected by an intermediate shaft 14 and a coupling ring (not shown). That is, in the gas turbine rotor 03 according to the comparative embodiment, the plurality of compressor disks 20 and the intermediate shaft 14 are connected without an intermediate disk 16, the first flange portion 42 of the intermediate shaft 14 is in contact with the compressor disk 20f of the final stage 4f of the compressor 4, and the second flange portion 44 of the intermediate shaft 14 is in contact with the coupling ring (not shown).

[0028] In contrast, as shown in FIG. 5 , in the gas turbine rotor 3 according to the above embodiment, a plurality of intermediate disks 16 are provided between the intermediate shaft 14 and the compressor disk 20f in the final stage 4f among the plurality of compressor disks 20. This allows the axial length L of the intermediate shaft 14 to be shorter than that of the gas turbine rotor 03 according to the comparative embodiment, in which the plurality of compressor disks 20 and the intermediate shaft 14 are connected without the intermediate disks 16. As a result, as shown by arrow H, the nuts 54 are easily accessible from the turbine rotor side end (second flange portion 44) of the intermediate shaft 14 through the inner peripheral side of the intermediate shaft 14. For example, the plurality of nuts 54 can be disposed in positions that are reachable from the second flange portion 44 side. This improves the ease of attaching and removing the nuts 54 to and from the spindle bolt 26, thereby improving the ease of fastening the plurality of compressor disks 20 and the first flange portion 42 of the intermediate shaft 14 together using the spindle bolt 26 and the nuts 54.

[0029] Furthermore, according to the gas turbine rotor 3, by adjusting the number of intermediate disks 16 and the thickness of each intermediate disk 16 in the axial direction, the length of the intermediate shaft 14 in the axial direction can be easily adjusted to a length that allows for good workability in attaching and removing the nut 54.

[0030] 6, for example, the operability of attaching and removing the nut 54 can be improved by increasing the thickness V of the first flange portion 42 in the axial direction. However, in this case, the centrifugal force acting on the first flange portion 42 of the cylindrical intermediate shaft 14 during rotation of the gas turbine rotor 03 increases, which tends to increase the difference in radial displacement between the solid compressor disk 20f and the hollow intermediate shaft 14, and large stress is likely to occur at the connection portion between the compressor disk 20f and the first flange portion 42. Furthermore, if the thickness V of the first flange portion 42 is large, it tends to make processing and quality control difficult when forming a straight hole along the axis of the intermediate shaft 14. In contrast, when the intermediate disk 16 is provided as described above, the intermediate disk 16 is solid and is provided in a range including the rotation axis O, which has the advantage of reducing the risk of increased stress due to the above-mentioned difference in displacement.

[0031] 3 and other drawings, according to the gas turbine rotor 3, the inner diameter d2 of the second flange portion 44 is larger than the inner diameter d1 of the first flange portion 42, so that a large space can be secured on the inner peripheral side of the second flange portion 44, making it easier to access the nuts 54 on the first flange portion 42 side through the inner peripheral side of the second flange portion 44, thereby improving the workability of attaching and removing the nuts 54 to and from the spindle bolts 26. Therefore, the workability of fastening the plurality of compressor disks 20 and the first flange portion 42 of the intermediate shaft 14 with the spindle bolts 26 and the nuts 54 can be improved.

[0032] 4 and other drawings, in each of the intermediate disks 16, the first side surface 61 is formed with a recess 63 and a recess 64, and the second side surface 62 is formed with a recess 65 and a recess 66. This makes it possible to improve the workability of attaching and removing the nuts 54 while suppressing an increase in the weight of the gas turbine rotor 3.

[0033] The present disclosure is not limited to the above-described embodiments, but also includes modifications to the above-described embodiments and appropriate combinations of these modifications.

[0034] For example, in the above-described embodiment, the gas turbine rotor 3 is illustrated as including two intermediate disks 16, but the number of intermediate disks 16 included in the gas turbine rotor 3 is not particularly limited, and may be, for example, one, or three or more. In other words, it is sufficient that the gas turbine rotor 3 includes at least one intermediate disk 16.

[0035] Furthermore, in the above-described embodiment, the case where two recesses 63, 64 are formed on the first side surface 61 of each intermediate disk 16 has been exemplified, but the number of recesses formed on the first side surface 61 is not particularly limited, and may be, for example, one, or three or more, or no recesses may be formed on the first side surface 61 of each intermediate disk 16. By forming at least one recess on the first side surface 61 of each intermediate disk 16, it is possible to improve the ease of attaching and removing the nuts 54 while suppressing an increase in the weight of the gas turbine rotor 3.

[0036] Furthermore, in the above-described embodiment, the case where two recesses 65, 66 are formed on the second side surface 62 of each intermediate disk 16 has been exemplified, but the number of recesses formed on the second side surface 62 is not particularly limited, and may be, for example, one, or three or more, or no recesses may be formed on the first side surface 61 of each intermediate disk 16. By forming at least one recess on the first side surface 61 of each intermediate disk 16, it is possible to improve the ease of attaching and removing the nuts 54 while suppressing an increase in the weight of the gas turbine rotor 3.

[0037] Furthermore, in the above-described embodiment, spindle bolts 26 are used to fasten the plurality of compressor disks 20, the plurality of intermediate disks 16, and the first flange portion 42 together, but the type of bolts for fastening the plurality of compressor disks 20, the plurality of intermediate disks 16, and the first flange portion 42 together is not particularly limited, and other bolts such as stacking bolts may also be used.

[0038] The contents described in each of the above embodiments can be understood, for example, as follows.

[0039] [1] A gas turbine rotor according to at least one embodiment of the present disclosure (e.g., the gas turbine rotor 3 described above) includes: A gas turbine rotor including a compressor rotor (for example, the above-described compressor rotor 10), a turbine rotor (for example, the above-described turbine rotor 12), and a cylindrical intermediate shaft (for example, the above-described intermediate shaft 14) for connecting the compressor rotor and the turbine rotor, The compressor rotor is a plurality of compressor disks (e.g., the plurality of compressor disks 20 described above) arranged along the axial direction of the gas turbine rotor; a plurality of compressor rotor blades (e.g., the plurality of compressor rotor blades 24 described above) fixed to the outer peripheral surfaces of the plurality of compressor disks; At least one intermediate disk (for example, the plurality of intermediate disks 16) provided between a final stage compressor disk (for example, the above-mentioned compressor disk 20f) among the plurality of compressor disks and the intermediate shaft; Including, The at least one intermediate disk has an outer peripheral surface that is free of blades, a first flange portion (for example, the above-mentioned first flange portion 42) protruding inward in the radial direction of the gas turbine rotor is formed on the compressor rotor side of the intermediate shaft, The gas turbine rotor comprises: a bolt (e.g., the spindle bolt 26 described above) that axially penetrates the plurality of compressor disks, the at least one intermediate disk, and the first flange portion; a nut (e.g., nut 54 described above) attached to the bolt on the opposite side of the first flange portion from the at least one intermediate disk; Further provided with:

[0040] According to the gas turbine rotor described in [1] above, at least one intermediate disk is provided between the intermediate shaft and a final-stage compressor disk among the plurality of compressor disks. This allows the axial length of the intermediate shaft to be shorter than when the plurality of compressor disks are connected to the intermediate shaft without an intermediate disk. This makes it easier to access the nuts from the turbine rotor-side end of the intermediate shaft through the inner peripheral side of the intermediate shaft, improving the operability of attaching and removing the nuts to and from the bolts. This improves the operability of fastening the plurality of compressor disks to the first flange portion of the intermediate shaft with the bolts and nuts.

[0041] [2] In some embodiments, in the gas turbine rotor described in [1] above, The at least one intermediate disk is a plurality of intermediate disks (for example, the above-mentioned plurality of intermediate disks 16) arranged along the axial direction.

[0042] According to the gas turbine rotor described in [2] above, by adjusting the number of intermediate disks and the thickness of each intermediate disk in the axial direction, the length of the intermediate shaft in the axial direction can be adjusted to a length that is convenient for the work of tightening the nut.

[0043] [3] In some embodiments, in the gas turbine rotor described in [2] above, The sum (eg, the above-mentioned sum S) of the thicknesses (eg, the above-mentioned thickness t) of the plurality of intermediate disks is greater than the thickness (eg, the above-mentioned thickness u) of the compressor disk of the final stage.

[0044] According to the gas turbine rotor described in [3] above, the amount of reduction in the axial length of the intermediate shaft can be made greater than the thickness of the final-stage compressor disk compared to when multiple compressor disks and the intermediate shaft are connected without an intermediate disk, thereby enhancing the effect described in [1] above.

[0045] [4] In some embodiments, in the gas turbine rotor described in [3] above, The thickness of each of the intermediate disks is greater than the thickness of the compressor disk of the final stage.

[0046] According to the gas turbine rotor described in [4] above, the length of the intermediate shaft in the axial direction can be reduced by at least twice the thickness of the final-stage compressor disk compared to when multiple compressor disks and the intermediate shaft are connected without an intermediate disk, thereby enhancing the effect described in [1] above.

[0047] [5] In some embodiments, in the gas turbine rotor according to any one of [1] to [4] above, The at least one intermediate disk includes an intermediate disk that is thicker than the compressor disk of the final stage.

[0048] According to the gas turbine rotor described in [5] above, the amount of reduction in the axial length of the intermediate shaft can be made greater than the thickness of the final-stage compressor disk compared to when multiple compressor disks and the intermediate shaft are connected without an intermediate disk, thereby enhancing the effect described in [1] above.

[0049] [6] In some embodiments, in the gas turbine rotor according to any one of [1] to [5] above, a second flange portion (for example, the above-mentioned second flange portion 44) protruding inward in the radial direction is formed on the turbine rotor side of the intermediate shaft, The inner diameter of the second flange portion (for example, the inner diameter d2 mentioned above) is larger than the inner diameter of the first flange portion (for example, the inner diameter d1 mentioned above).

[0050] According to the gas turbine rotor described in [6] above, by ensuring a wider space on the inner circumferential side of the second flange portion than on the inner circumferential side of the first flange portion, it becomes easier to access the nuts on the first flange portion side through the inner circumferential side of the second flange portion, improving the workability of attaching and removing the nuts to the bolts. Therefore, the workability of fastening the plurality of compressor disks and the first flange portion of the intermediate shaft with the bolts and nuts can be improved.

[0051] [7] In some embodiments, in the gas turbine rotor according to any one of [1] to [6] above, Each of the intermediate disks includes a first side surface (e.g., the first side surface 61) facing the turbine rotor in the axial direction, and a second side surface (e.g., the second side surface 62) facing the opposite side from the turbine rotor in the axial direction, At least one recess (for example, the recesses 63, 64, 65, and 66 described above) is formed in each of the first side surface and the second side surface.

[0052] According to the gas turbine rotor described in [7] above, it is possible to improve the workability of fastening the plurality of compressor disks and the first flange portion of the intermediate shaft with bolts and nuts while suppressing an increase in the weight of the gas turbine rotor.

[0053] [8] In some embodiments, in the gas turbine rotor described in [7] above, At least one recess (for example, the above-mentioned recesses 63, 65) is formed in each of the first side surface and the second side surface at a position more inward than the bolt in the radial direction.

[0054] According to the gas turbine rotor described in [8] above, it is possible to improve the workability of fastening the plurality of compressor disks and the first flange portion of the intermediate shaft with bolts and nuts while suppressing an increase in the weight of the gas turbine rotor.

[0055] [9] In some embodiments, in the gas turbine rotor according to [7] or [8] above, At least one recess (for example, the above-mentioned recesses 64, 66) is formed in each of the first side surface and the second side surface at a position overlapping with the bolt in the radial direction.

[0056] According to the gas turbine rotor described in [9] above, it is possible to improve the workability of fastening the plurality of compressor disks and the first flange portion of the intermediate shaft with bolts and nuts while suppressing an increase in the weight of the gas turbine rotor.

[0057]

[10] In some embodiments, in the gas turbine rotor according to any one of [1] to [9] above, The entire outer circumferential surface of the intermediate disc is formed by a cylindrical surface.

[0058] According to the gas turbine rotor described in

[10] above, by using an intermediate disk without blades, it is possible to improve the workability of fastening the plurality of compressor disks and the first flange portion of the intermediate shaft with bolts and nuts while suppressing an increase in the weight of the gas turbine rotor. [Explanation of symbols]

[0059] 2. Gas turbine 3 Gas turbine rotor 4 Compressor 4f final stage 6 Combustor 8 Turbine 10 Compressor rotor 12 Turbine rotor 14 Intermediate shaft 15 Intermediate shaft casing 16, 16a, 16b Intermediate disc 18 Joint ring 19,22,32 Outer surface 20,20f compressor disc 24 Compressor blade 26,36 Spindle bolt 28, 38, 46, 48, 50, 52 through holes 30,30a turbine disc 34 Turbine blade 40 Cylindrical part 42 First flange 44 Second flange 54,56 Nut 61 First aspect 62 Second aspect 63, 64, 65, 66 Recesses 67,68 Cavity

Claims

1. A gas turbine rotor including a compressor rotor, a turbine rotor, and a cylindrical intermediate shaft for connecting the compressor rotor and the turbine rotor, The compressor rotor is a plurality of compressor disks arranged along the axial direction of the gas turbine rotor; a plurality of compressor rotor blades fixed to the outer peripheral surfaces of the plurality of compressor disks; at least one intermediate disk provided between a final stage compressor disk among the plurality of compressor disks and the intermediate shaft; Including, the at least one intermediate disk has an outer peripheral surface that is free of blades; a first flange portion that protrudes inward in a radial direction of the gas turbine rotor is formed on the compressor rotor side of the intermediate shaft, The gas turbine rotor comprises: a bolt that passes through the plurality of compressor disks, the at least one intermediate disk, and the first flange portion in the axial direction; a nut attached to the bolt on the opposite side of the first flange portion from the at least one intermediate disk; The gas turbine rotor further comprises:

2. The gas turbine rotor according to claim 1 , wherein the at least one intermediate disk is a plurality of intermediate disks arranged along the axial direction.

3. The gas turbine rotor according to claim 2 , wherein a sum of thicknesses of each of the plurality of intermediate disks is greater than a thickness of the compressor disk of the final stage.

4. The gas turbine rotor according to claim 3 , wherein a thickness of each of the plurality of intermediate disks is greater than a thickness of the compressor disk of the final stage.

5. The gas turbine rotor of claim 1 , wherein the at least one intermediate disk includes the intermediate disk being thicker than the compressor disk of the final stage.

6. a second flange portion that protrudes inward in the radial direction is formed on the turbine rotor side of the intermediate shaft, 2. The gas turbine rotor according to claim 1, wherein an inner diameter of the second flange portion is larger than an inner diameter of the first flange portion.

7. Each of the intermediate disks includes a first side surface facing the turbine rotor in the axial direction and a second side surface facing the opposite side from the turbine rotor in the axial direction, The gas turbine rotor of claim 1 , wherein each of the first side and the second side defines at least one recess.

8. The gas turbine rotor according to claim 7 , wherein at least one recess is formed in each of the first side surface and the second side surface at a position more inward than the bolt in the radial direction.

9. The gas turbine rotor according to claim 7 , wherein each of the first side surface and the second side surface has at least one recess formed at a position overlapping with the bolt in the radial direction.

10. 2. The gas turbine rotor according to claim 1, wherein the entire outer peripheral surface of said intermediate disk is formed by a cylindrical surface.

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