Turbine rotor fixing device, turbine module which is equipped with the turbine rotor fixing device, and shipping methods of turbine module

Abstract

Provided are a turbine rotor fixing device capable of easily fixing a turbine rotor in a radial direction and an axial direction, and a shipping method of a turbine module. A fixing device (30) of a turbine rotor (11) includes a radial direction fixing jig (32) provided in a gland part (21A) that seals a clearance between the turbine rotor (11) and a turbine casing disposed to cover a periphery of the turbine rotor (11), to fix relative movement of the turbine rotor (11) to the gland part (21A) in a radial direction, and an axial direction fixing jig (31) provided between the turbine rotor (11) and the gland part (21A), to fix relative movement of the turbine rotor (11) to the gland part (21A) in an axis (X) direction.

Claims

1. A turbine rotor fixing device comprising: a radial direction fixing jig provided in a gland part that seals a clearance between a turbine rotor and a turbine casing disposed to cover a periphery of the turbine rotor, to fix relative movement of the turbine rotor to the gland part in a radial direction, and an axial direction fixing jig provided between the turbine rotor and the gland part, to fix relative movement of the turbine rotor to the gland part in an axial direction, wherein an inner peripheral surface of the gland part is provided with one seal ring groove which is formed in the axial direction and into which the radial direction fixing jig is incorporated, and an other seal ring groove into which the axial direction fixing jig is incorporated.

2. The turbine rotor fixing device according to claim 1, wherein the axial direction fixing jig is located on a side of a rotor end of the turbine rotor outside the turbine casing away from the radial direction fixing jig, and the axial direction fixing jig is provided with a cutout in a measuring position of a clearance between the turbine rotor and the gland part so that the clearance is visible from the rotor end side of an end face of the turbine rotor away from the axial direction fixing jig.

3. The turbine rotor fixing device according to claim 2, wherein one end of a measuring jig is inserted into the cutout and is attachable to the gland part on the rotor end side of the turbine rotor in the gland part, and the measuring jig is configured to measure a clearance between the end face of the turbine rotor on the rotor end side and the gland part in the axial direction.

4. A turbine module comprising: a turbine rotor, a turbine casing disposed to cover a periphery of the turbine rotor, and the turbine rotor fixing device according to claim 1 to fix the relative movement of the turbine rotor to the turbine casing.

5. A shipping method of a turbine module by use of a turbine rotor fixing device comprising a radial direction fixing jig provided in a gland part that seals a clearance between a turbine rotor and a turbine casing disposed to cover a periphery of the turbine rotor, to fix relative movement of the turbine rotor to the gland part in a radial direction, and an axial direction fixing jig provided between the turbine rotor and the gland part, to fix relative movement of the turbine rotor to the gland part in an axial direction, the shipping method of the turbine module comprising: a radial direction fixing step of fixing, with the radial direction fixing jig, the relative movement of the turbine rotor to the gland part in the radial direction, an axial direction fixing step of fixing, with the axial direction fixing jig, the relative movement of the turbine rotor to the gland part in the axial direction, and a shipping step of shipping the turbine module comprising the turbine rotor fixing device, the turbine rotor fixed by the turbine rotor fixing device, and the turbine casing, wherein an inner peripheral surface of the gland part is provided with one seal ring groove which is formed in the axial direction and into which the radial direction fixing jig is incorporated, and an other seal ring groove into which the axial direction fixing jig is incorporated.

Description

BRIEF DESCRIPTION OF DRAWINGS

(1) FIG. 1 is a schematic side cross-sectional view showing a turbine module according to an embodiment of the present disclosure.

(2) FIG. 2 is a schematic perspective view showing a state where an upper half of a gland part is removed, as seen from outside a paper surface right side of FIG. 1 to inside a turbine casing, in a vicinity of the gland part on the paper surface right side in the turbine module of FIG. 1.

(3) FIG. 3 is a partially cross-sectional view showing a state where a turbine rotor fixing device according to the embodiment of the present disclosure is provided between a turbine rotor and the gland part.

(4) FIG. 4 is a perspective view showing an example of a radial direction fixing jig according to the embodiment of the present disclosure.

(5) FIG. 5 is a perspective view showing an example of an axial direction fixing jig according to the embodiment of the present disclosure.

(6) FIG. 6 is a partially schematic perspective view showing a state where a measuring jig is attached to the gland part, as seen from outside the paper surface right side of FIG. 1 to inside the turbine casing, in the vicinity of the gland part on the paper surface right side in the turbine module of FIG. 1.

(7) FIG. 7 is a partially cross-sectional view showing a state where the measuring jig is attached to the gland part.

DESCRIPTION OF EMBODIMENTS

(8) Hereinafter, description will be made as to an embodiment of a turbine rotor fixing device, a turbine module which is equipped with the turbine rotor fixing device, and shipping methods of the turbine module according to the present disclosure, with reference to the drawings. In the present embodiment, an upper side indicates a vertical upper direction, and a lower side indicates a vertical lower direction.

(9) [Turbine Module]

(10) Hereinafter, description will be made as to a turbine module according to an embodiment of the present disclosure with reference to the drawings.

(11) FIG. 1 is a schematic side cross-sectional view showing the turbine module (a steam turbine or a high intermediate pressure turbine) according to the present embodiment.

(12) As shown in FIG. 1, for a turbine module (the high intermediate pressure turbine) 1, a high pressure blade row (a rotating machine) 2A on one side (a paper surface right side) in an axis X direction and an intermediate pressure blade row (a rotating machine) 2B on the other side (a paper surface left side) in the axis X direction are constituted in one turbine module 1.

(13) The high intermediate pressure turbine 1 includes a rotatably supported turbine rotor 11, and a stator 50. In the following description, an extending direction of an axis X will be referred to as “the axis X direction of the turbine rotor 11”, a circumferential direction of the axis X will be referred to as “the circumferential direction of the turbine rotor 11”, and a radial direction of the axis X will be referred to as “the radial direction of the turbine rotor 11”.

(14) The turbine rotor 11 includes rotating blade rows 12A, 12B constituted of a plurality of rotating blade stages. The stator 50 includes a turbine casing 51, stational blade rows 52A, 52B constituted of a plurality of stational blade stages, and the like.

(15) The turbine rotor 11 extends through the stator 50 in the axis X direction, and has opposite rotor end sides in the axis X direction supported by bearings 91, 92 disposed outside the stator 50. In the present embodiment, the turbine module 1 is mounted on a module support (not shown) and shipped, in a state where the bearings 91, 92 are not included and shaft coupling is removed during the shipping of the turbine module 1.

(16) The rotating blade rows 12A, 12B are constituted of a plurality of rotating blade stages, and each of the rotating blade stages is constituted of rotating blades arranged and held on an outer periphery of the turbine rotor 11 in the circumferential direction.

(17) The stational blade rows 52A, 52B are constituted of a plurality of stational blade stages, and each of the stational blade stages is constituted of stational blades arranged in the circumferential direction and held on an inner periphery of a blade ring 53 fitted in the turbine casing 51. The rotating blade stages and stational blade stages are alternately arranged, to form the high pressure blade row 2A and the intermediate pressure blade row 2B, respectively.

(18) The turbine casing 51 is disposed to cover a periphery of the turbine rotor 11, and is inserted into the turbine rotor 11. Opposite rotor ends of the turbine rotor 11 protrude from opposite ends of the turbine casing 51 in the axis X direction. Note that in the opposite ends of the turbine casing 51 in the axis X direction, any clearance formed between the turbine casing 51 and the turbine rotor 11 is sealed from an exterior part outside the turbine casing 51 by gland parts 21A, 21B.

(19) An unshown seal ring is provided between the turbine casing 51 and the turbine rotor 11, and the clearance between the turbine casing 51 and the turbine rotor 11 is strictly managed to inhibit steam from leaking to the exterior part outside the turbine casing 51 or inhibit outside air from flowing inside.

(20) [Turbine Rotor Fixing Device]

(21) Next, description will be made as to a turbine rotor fixing device according to the present embodiment with reference to FIG. 2. The turbine rotor fixing device according to the present embodiment is applied, for example, to the gland parts 21A, 21B of FIG. 1.

(22) FIG. 2 is a schematic perspective view showing a state where an upper half of the gland part 21A is removed, as seen from outside the paper surface right side of FIG. 1 to inside the turbine casing 51, in a vicinity of the gland part 21A on the paper surface right side in the turbine module of FIG. 1. Note that FIG. 2 omits drawing of the turbine rotor 11 for convenience of explanation. As shown in FIG. 2, the gland part 21A is provided with a turbine rotor fixing device 30 to fix relative movement of the turbine rotor 11 to the gland part 21A in the axis X direction, and relative movement of the turbine rotor 11 to the gland part 21A in the radial direction. The turbine rotor fixing device 30 comprises an axial direction fixing jig 31 to fix the relative movement of the turbine rotor 11 to the gland part 21A in the axis X direction, and a radial direction fixing jig 32 to fix the relative movement of the turbine rotor 11 to the gland part 21A in the radial direction. Examples of a material of the axial direction fixing jig 31 and the radial direction fixing jig 32 include metals such as an SS material and an SUS material.

(23) The axial direction fixing jig 31 has a semi-circular shape, that is, a half-split ring shape. The axial direction fixing jig 31 is located on a rotor end X1 side of the turbine rotor 11 (outside the turbine casing 51 in the axis X direction) away from the radial direction fixing jig 32. Only one axial direction fixing jig 31 is disposed on a lower half side of the gland part 21A. After modularization, a seal ring is provided on an upper side of the axial direction fixing jig 31, and movement of the axial direction fixing jig 31 in the circumferential direction is fixed with this seal ring. A shape of the axial direction fixing jig 31 will be described later in detail.

(24) The radial direction fixing jig 32 has a semi-circular shape, that is, a half-split ring shape. The radial direction fixing jig 32 is located on a rotor end X2 side of the turbine rotor 11 (inside the turbine casing 51 in the axis X direction) away from the axial direction fixing jig 31. Two radial direction fixing jigs 32 are provided on an upper half side and a lower half side of the divided gland part 21A, and are inserted so that an entire circumference of the turbine rotor 11 is surrounded with the two radial direction fixing jigs 32. A shape of the radial direction fixing jig 32 will be described later in detail.

(25) As shown in FIG. 2, the turbine rotor fixing device 30 according to the present embodiment comprises a circumferential direction fixing jig (e.g., a rod-like member having a thread groove, such as a bolt) 33 that fixes movement of the turbine rotor 11 in the circumferential direction (a rotating direction). The circumferential direction fixing jig 33 is inserted to protrude from outside the turbine casing 51 (a position of the turbine rotor 11 on the rotor end X1 side away from the turbine casing 51) into the turbine casing 51. Specifically, in the present embodiment, the circumferential direction fixing jig 33 is inserted in a state where an inserting portion tip of the circumferential direction fixing jig 33 is inclined obliquely downward to the axis X, by use of a balance plug hole 34 for vibration adjustment provided in the turbine casing 51. The inserted circumferential direction fixing jig 33 comes in contact with a part of the turbine rotor 11, and is held and fixed so that the turbine rotor 11 does not rotate to the turbine casing 51. Thus, the movement of the turbine rotor 11 in the circumferential direction (the rotating direction) is fixed. Note that in the present disclosure, the circumferential direction fixing jig 33 is not indispensable.

(26) Next, description will be made as to a method of fixing the turbine rotor 11 by the turbine rotor fixing device 30 according to the present embodiment with reference to FIGS. 3 to 5. FIG. 4 is a perspective view showing an example of the radial direction fixing jig 32 according to the present embodiment. FIG. 5 is a perspective view showing an example of the axial direction fixing jig 31 according to the present embodiment. Note that FIGS. 3 to 5 also show the axis X for the convenience of explanation.

(27) As shown in FIG. 4, the radial direction fixing jig 32 includes a turbine rotor side fitting part 35 that fits with an outer peripheral surface of the turbine rotor 11 described above, and a gland part side fitting part 36 that fits with an inner peripheral surface of the gland part 21A described above. The turbine rotor side fitting part 35 is formed so that an uneven part is formed in an inner peripheral surface of the radial direction fixing jig 32 and corresponds to an uneven shape of a fitting groove 13 (see FIG. 3) of the turbine rotor 11. The gland part side fitting part 36 is formed in a convex protrusion protruding outward from an outer peripheral surface of the radial direction fixing jig 32 in the radial direction.

(28) As shown in FIG. 5, the axial direction fixing jig 31 includes a semi-circular fitting part 37 that fits with the inner peripheral surface of the gland part 21A described later. In a surface of the fitting part 37 on the rotor end X1 side, a protrusion 38 protruding from the fitting part 37 along the axis X direction is formed. In an end of the protrusion 38 toward the axis X direction (the end on a side opposite to the fitting part 37), a fixing part 39 is formed to protrude inward from the axis X in the radial direction. The fixing part 39 comes in contact with a surface (an after-mentioned end face 14) of the turbine rotor 11 described above on the rotor end X1 side and is locked.

(29) The protrusion 38 and the fixing part 39 are not formed all around the fitting part 37, and are provided with cutouts 40 cut out to open a part (in the present embodiment, three parts in total in horizontal opposite end directions and on the vertical lower side seen from the rotor end X1 side) in the circumferential direction. There are not any special restrictions on positions and a number of the cutouts 40 to be provided.

(30) After the axial direction fixing jig 31 is disposed, each cutout 40 is formed so that a clearance between the turbine rotor 11 and the gland part 21A can be visually verified from a position of the turbine rotor 11 on the rotor end X1 side to the end face 14 away from the axial direction fixing jig 31 and so that the clearance can be easily measured with a measuring instrument or the like. There are not any special restrictions on a width H of the cutout 40 (for the cutout 40 on the vertical lower side in FIG. 5, a length in a horizontal right-left direction), as long as the clearance between the turbine rotor 11 and the gland part 21A can be visually verified and the clearance can be measured with the measuring instrument or the like, and the width is, for example, from 20 mm to 60 mm.

(31) FIG. 3 is a partially cross-sectional view showing a state where the turbine rotor fixing device 30 according to the present embodiment is provided between the turbine rotor 11 and the gland part 21A. Specifically, FIG. 3 is a cross-sectional view cut to include a part of the axial direction fixing jig 31 including the protrusion 38 and the fixing part 39 (not to include a part in which the cutout 40 is formed). In FIG. 3, a paper surface left direction indicates a rotor end X1 direction of the turbine rotor 11 outside the turbine casing 51, and a paper surface right direction indicates a rotor end X2 direction of the turbine rotor 11 inside the turbine casing 51 (inside the gland part 21A).

(32) As shown in FIG. 3, the inner peripheral surface of the gland part 21A is provided with a (one) seal ring groove 22 formed in the axis X direction, to fit with the gland part side fitting part 36 of the radial direction fixing jig 32, and a (the other) seal ring groove 23 that fits with the fitting part 37 of the axial direction fixing jig 31. The seal ring grooves 22, 23 are provided along the inner peripheral surface of the gland part 21A. The outer peripheral surface of the turbine rotor 11 is provided with the fitting groove 13 having the uneven shape that fits with the turbine rotor side fitting part (the uneven part) 35 of the radial direction fixing jig 32.

(33) To fix the relative movement of the turbine rotor 11 in the axis X direction with the axial direction fixing jig 31, a clearance between the fixing part 39 of the axial direction fixing jig 31 and the surface of the turbine rotor 11 on the rotor end X1 side in a region C1 of FIG. 3 is adjusted into a dimension close to 0 (e.g., from 0 to 1 mm). To inhibit rattling of the axial direction fixing jig 31 itself (to fix a position of the axial direction fixing jig 31), a clearance between the protrusion 38 of the axial direction fixing jig 31 and the inner peripheral surface of the gland part 21A in a region C2 of FIG. 3 is adjusted into a dimension close to 0 (e.g., from 0 to 0.1 mm). For a clearance between the fitting part 37 of the axial direction fixing jig 31 and the inner peripheral surface of the gland part 21A, a tolerance is strictly managed, but a slight clearance is tolerated. The slight clearance is a clearance to such an extent that the fitting part 37 of the axial direction fixing jig 31 is movable in the axial direction and the radial direction to be easily inserted in the clearance between the turbine rotor 11 and the gland part 21A.

(34) To fix the relative movement of the turbine rotor 11 in the radial direction with the axial direction fixing jig 31, a clearance between the turbine rotor side fitting part 35 of the radial direction fixing jig 32 (specifically, a convex portion of the turbine rotor side fitting part 35) and the fitting groove 13 (specifically, a concave portion of the fitting groove 13) of the turbine rotor 11 in a region C3 of FIG. 3 is adjusted into a dimension close to 0 (e.g., from 0 to 0.1 mm). For a similar reason, a clearance between the gland part side fitting part 36 of the radial direction fixing jig 32 and the inner peripheral surface of the gland part 21A (in a part in which the seal ring groove 22 is formed) in a region C4 of FIG. 3 is adjusted into a dimension close to 0 (e.g., from 0 to 0.1 mm).

(35) An example of a method of disposing the axial direction fixing jig 31 in the seal ring groove 23 or disposing the radial direction fixing jig 32 in the seal ring groove 22 is a method of rotating each jig in the circumferential direction to insert the jig in the upper half of the divided gland part 21A, but the method is not limited to this example.

(36) The turbine rotor fixing device 30 described above is also provided in the gland part 21B of FIG. 1.

(37) Next, description will be made as to a method of verifying a length of the clearance between the turbine rotor 11 and the gland part 21A, and misalignment between the turbine rotor 11 and the gland part 21A in the axis X direction, with reference to FIGS. 6 and 7.

(38) FIG. 6 is a partially schematic perspective view showing a state where a measuring jig is attached to the gland part, as seen from outside the paper surface right side of FIG. 1 to inside the turbine casing 51, in the vicinity of the gland part on the paper surface right side in the turbine module of FIG. 1. Note that FIG. 6 omits drawing of the turbine rotor 11 for the convenience of explanation. Furthermore, FIG. 6 also shows the axis X for the convenience of explanation. As shown in FIG. 6, one end 42 of a measuring jig 41 is attachable to come in contact with the turbine rotor 11 on the rotor end X1 side in the gland part 21A. As the measuring jig 41, for example, a block body having an L-shaped cross section and including the one end 42 extending in the axis X direction and another end 43 extending in the radial direction may be used.

(39) FIG. 7 is a partially cross-sectional view showing a state where the measuring jig 41 is attached to the gland part 21A. Specifically, FIG. 7 is a cross-sectional view of the axial direction fixing jig 31 cut to include a part in which the cutout 40 is formed. In FIG. 7, a paper surface left direction indicates the rotor end X1 direction of the turbine rotor 11 outside the turbine casing 51, and a paper surface right direction indicates the rotor end X2 direction of the turbine rotor 11 inside the turbine casing 51 (inside the gland part 21A). FIG. 7 also shows the axis X for the convenience of explanation.

(40) Since the axial direction fixing jig 31 is provided with the cutout 40, the clearance between the turbine rotor 11 and the gland part 21A can be visually verified through the cutout 40 from the position of the turbine rotor 11 on the rotor end X1 side away from the axial direction fixing jig 31, without opening the upper half of the gland part 21A, and the clearance can be easily measured with the measuring instrument or the like. A clearance dimension L between the turbine rotor 11 and the gland part 21A can be measured, for example, with the measuring instrument, such as a micrometer or a cylinder gauge.

(41) The measuring jig 41 is configured to measure a clearance in the end face 14 of the turbine rotor 11 on the rotor end X1 side. During the measuring, the one end 42 of the measuring jig 41 is attached to come in contact with a reference surface 24 on the rotor end X1 side in the gland part 21A with a magnet or the like. At this time, the other end 43 of the measuring jig 41 is adjusted to face, in parallel, the end face 14 of the turbine rotor 11 and the end face of the gland part orthogonal to the axis X direction. In this state, a distance D between the other end 43 of the measuring jig 41 and the end face 14 of the turbine rotor 11 (a length of the turbine rotor 11 in the axis X direction) is measured with the micrometer or the like, and a measured value is compared with a measured value prior to start of the shipping. Consequently, the clearance in the turbine rotor 11 in the axial direction is measured. Note that the other end 43 of the measuring jig 41 does not have to be disposed to face, in parallel, the end face 14 of the turbine rotor 11 and the end face of the gland part orthogonal to the axis X direction, and the measuring with the measuring jig 41 may be performed in another mode.

(42) [Shipping Method of Turbine Module]

(43) Next, a shipping method of the turbine module according to the present embodiment will be described.

(44) Hereinafter, a case of shipping the turbine module 1 shown in FIG. 1 will be described as an example, but the method is not limited to this example.

(45) (Radial Direction Fixing Step)

(46) A radial direction fixing step includes fixing, with the radial direction fixing jig 32, the relative movement of the turbine rotor 11 to the gland parts 21A, 21B in the radial direction.

(47) (Axial Direction Fixing Step)

(48) An axial direction fixing step includes, after performing the radial direction fixing step, inserting the axial direction fixing jig 31, to fix the relative movement of the turbine rotor 11 to the gland parts 21A, 21B in the axial direction.

(49) (Shipping Step)

(50) The turbine module 1 is shipped after completing the fixing of the position of the turbine rotor 11 by the turbine rotor fixing device 30. In the present embodiment, during the shipping of the turbine module 1, the bearings 91, 92 are removed, and the turbine module 1 is fixed to the module support (not shown) or the like, mounted on a moving means, and shipped.

(51) With the above described configuration, according to the present embodiment, the following operations and effects are exhibited.

(52) According to the turbine rotor fixing device 30 of the present embodiment, the turbine rotor 11 is fixed to the turbine casing 51 via the gland parts 21A, 21B separately in the radial direction and axial direction of the turbine rotor, with two jigs including the radial direction fixing jig 32 and the axial direction fixing jig 31. Therefore, the relative movement of the turbine rotor 11 in the radial direction and the relative movement in the axis X direction can be fixed more easily than in the case where the relative movement of the turbine rotor 11 in the radial direction and the relative movement in the axis X direction are fixed with one jig. Furthermore, the jig to fix the relative movement of the turbine rotor 11 in the radial direction and the jig to fix the relative movement in the axis X direction can be separately manufactured, and hence the manufacturing of the jigs is facilitated.

(53) If each of the gland parts 21A, 21B is provided with the seal ring grooves 22, 23, the radial direction fixing jig 32 and the axial direction fixing jig 31 can be incorporated in the seal ring grooves 22, 23 of the gland part 21A, 21B. Furthermore, for example, if the seal ring grooves 22, 23 are provided in the inner peripheral surface of the gland part 21A, 21B in the circumferential direction, each jig can be rotated along the circumferential direction to the clearance formed between the turbine rotor 11 and the gland part 21A, 21B, and inserted and incorporated in the seal ring groove 22, 23. Specifically, in a case where one jig to fix the turbine rotor 11 in the radial direction and the axial direction is used, portions of the jig that come in contact with the turbine rotor 11 and the gland part 21A, 21B increase to fix the position of the jig, and the portions come in contact in a plurality of directions. Consequently, it is difficult to rotate and insert the jig in the circumferential direction between the turbine rotor 11 and the gland part 21A, 21B. On the other hand, in a case where, as in the present embodiment, two jigs including the jig to fix the relative movement of the turbine rotor 11 in the radial direction and the jig to fix the relative movement in the axis X direction are separately used, portions of each jig that come in contact with the turbine rotor 11 and the gland part 21A, 21B can be appropriately reduced to necessary portions. Consequently, it is easy to rotate and insert each jig in the circumferential direction between the turbine rotor 11 and the gland part 21A, 21B.

(54) If the axial direction fixing jig 31 is provided with the cutout 40, the clearance between the turbine rotor 11 and the gland part 21A, 21B can be visually verified through the cutout 40 from the position of the turbine rotor 11 on the rotor end X1 side outside the turbine casing 51 away from the axial direction fixing jig 31, without opening the upper half of the gland part 21A, 21B, and the clearance can be easily measured with the measuring instrument or the like. Therefore, even after the modularization of the turbine rotor 11 and turbine casing 51, the clearance dimension L between the turbine rotor 11 and the gland part 21A, 21B can be easily measured. Furthermore, the above clearance dimension L is measured after assembly, before the shipping and during the shipping of the turbine module 1. Consequently, it can be grasped, from a difference between respective measured values, whether the turbine rotor 11 moves in the radial direction due to vibration or the like during the shipping, and a movement amount can be grasped. This facilitates quality assurance after the shipping.

(55) If the measuring jig 41 is attachable to the rotor end X1 side of the turbine rotor 11 in the gland part 21A, 21B outside the turbine casing 51, the clearance between the turbine rotor 11 and the gland part 21A, 21B in the axis X direction can be verified with the measuring jig 41 from the position of the turbine rotor 11 on the rotor end X1 side, without opening the upper half of the gland part 21A, 21B. Therefore, even after the modularization of the turbine rotor 11 and the turbine casing 51, the clearance between the turbine rotor 11 and the gland part 21A, 21B in the axis X direction can be easily measured. Furthermore, the distance D between the measuring jig 41 and the turbine rotor 11 is measured after the assembly, before the shipping and during the shipping of the turbine module 1. Consequently, it can be grasped, from the difference between the respective measured values, whether the turbine rotor 11 moves in the axis X direction due to the vibration or the like during the shipping, and the movement amount can be grasped. This facilitates the quality assurance after the shipping.

(56) Since the turbine module 1 of the present embodiment comprises the turbine rotor fixing device 30, the fixing of the position of the turbine rotor 11 to the turbine casing 51 and measuring of a mutual positional relation can be facilitated. Therefore, the turbine module 1 having excellent operation properties can be obtained.

(57) In the shipping method of the turbine module 1 of the present embodiment, the turbine rotor 11 is fixed to the turbine casing 51 via the gland parts 21A, 21B, separately in the radial direction and axial direction of the turbine rotor, with two jigs (in two steps) including the radial direction fixing jig 32 (the radial direction fixing step) and the axial direction fixing jig 31 (the axial direction fixing step). Therefore, the relative movement of the turbine rotor 11 in the radial direction and the relative movement in the axis X direction can be fixed more easily than in the case where the relative movement of the turbine rotor 11 in the radial direction and the relative movement in the axis X direction are fixed with one jig. Furthermore, since the jig to fix the relative movement of the turbine rotor 11 in the radial direction and the jig to fix the relative movement in the axis X direction can be separately manufactured, the manufacturing of the jigs can be facilitated.

(58) Note that in the above described embodiment, the case of using the jigs having the semi-circular shape as the axial direction fixing jig 31 and the radial direction fixing jig 32 has been described as an example, but the shape of each jig is not limited to this example. Furthermore, there are not any special restrictions on the number of the respective jigs. That is, a number of axial direction fixing jigs 31 is not limited to one, and may be two or more. Furthermore, a number of the radial direction fixing jig 32 is not limited to two in an up-down direction, and may be three or more.

REFERENCE SIGNS LIST

(59) 1 Turbine module (a high intermediate pressure turbine) 2A High pressure blade row (a rotating machine) 2B Intermediate pressure blade row (a rotating machine) 11 Turbine rotor 12A, 12B Rotating blade row 13 Fitting groove 14 End face 21A, 21B Gland part 22 (one) Seal ring groove 23 (the other) Seal ring groove 24 Reference surface 30 Turbine rotor fixing device 31 Axial direction fixing jig (a jig) 32 Radial direction fixing jig (a jig) 33 Circumferential direction fixing jig (a jig) 34 Balance plug hole 35 Turbine rotor side fitting part 36 Gland part side fitting part 37 Fitting part 38 Protrusion 39 Fixing part 40 Cutout 41 Measuring jig 42 One end 43 The other end 50 Stator 51 Turbine casing 52a, 52b Stational blade row 53 Blade ring 91, 92 Bearing D Distance H Width L Clearance dimension X Axis X1, X2 Rotor end