Turbomachine

Abstract

Leakage of a working fluid from a shaft sealing device of a turbomachine which handles a liquid as the working liquid is reduced and also unstable fluid force which acts on a rotor is reduced. For this purpose, the turbomachine has a rotor having an impeller, a bearing which rotatably supports the rotor, a casing which contains the rotor therein and forms a stationary flow passage, and the shaft sealing device which reduces the leakage of the working fluid through a gap part between the casing and the rotor. The working fluid is a liquid. A plurality of axial grooves which are intermittently arranged in axial direction and circumferential direction of the rotor with a land part being interposed are provided in an inner circumferential surface of the shaft sealing device.

Claims

1. A turbomachine comprising: a rotor having an impeller; a bearing which rotatably supports the rotor; a casing which contains the rotor therein and forms a stationary flow passage; and a shaft sealing device which reduces leakage of a working fluid through a gap part between the casing and the rotor, wherein the working fluid is a liquid, and a plurality of axial grooves which have been intermittently arranged in an axial direction and a circumferential direction of the rotor with a land part being interposed between the adjacent axial grooves are provided in an inner circumferential surface of the shaft sealing device.

2. The turbomachine according to claim 1, wherein the axial groove is configured in a rectangular shape which is long in the axial direction and the plurality of axial grooves are arranged in parallel with one another.

3. The turbomachine according to claim 2, wherein the plurality of axial grooves are arranged in a staggered state at least in one direction of the axial direction and the circumferential direction of the rotor.

4. The turbomachine according to claim 3, wherein the plurality of axial grooves are arranged in the staggered state in the axial direction of the rotor and the axial grooves which are arranged in the staggered state are configured so as to partially overlap one another in the axial direction.

5. A turbomachine comprising: a rotor having an impeller; a bearing which rotatably supports the rotor; a casing which contains the rotor therein and forms a stationary flow passage; and a shaft sealing device which reduces leakage of a working fluid through a gap part between the casing and the rotor, wherein the working fluid is a liquid, an axial groove group which includes a plurality of axial grooves which have been intermittently arranged on the same straight line directed in an axial direction with a land part being interposed between the adjacent axial grooves is provided in an inner circumferential surface of the shaft sealing device, and a plurality of the axial groove groups are adjacently arranged in the circumferential direction, and the plurality of axial groove groups which have been adjacently arranged in the circumferential direction are arranged so as to be parallel with one another with the land part being interposed between the adjacent axial groove groups.

6. The turbomachine according to claim 5, wherein the plurality of axial grooves are arranged in a staggered state in at least one direction of the axial direction and the circumferential direction of the rotor.

7. The turbomachine according to claim 6, wherein the plurality of axial grooves are arranged in the staggered state in the circumferential direction of the rotor and the axial grooves which are arranged in the staggered state are configured so as to partially overlap one another in the circumferential direction.

8. The turbomachine according to claim 5, wherein the plurality of axial grooves which configure each of the axial groove groups are configured by grooves of a plurality of sizes which are mutually different in length in the axial direction.

9. The turbomachine according to claim 8, wherein the plurality of axial grooves which configure each of the axial groove groups are configured by small grooves and large grooves which are mutually different in length in the axial direction, and one large groove is arranged every time the plurality of small grooves are arranged in the axial direction.

10. The turbomachine according to claim 5, wherein the plurality of axial grooves are arrayed in a grid form.

11. The turbomachine according to claim 5, wherein the shape of an axial section of the axial groove is configured in an arc shape or an almost rectangular shape.

12. The turbomachine according to claim 5, wherein the axial grooves are provided by inclining the axial grooves from the axial direction to a rotation direction of the rotor, and the respective axial groove groups which are arranged in a plural number in the circumferential direction are arranged so as to be parallel with one another by respectively inclining the axial groove groups from the axial direction to the rotation direction of the rotor.

Description

BRIEF DESCRIPTION OF DRAWINGS

[0019] FIG. 1 is a partial longitudinal sectional diagram illustrating an embodiment 1 of a turbomachine of the present invention.

[0020] FIG. 2 is a diagram illustrating an inner surface shape of a shaft sealing device in the turbomachine illustrated in FIG. 1, that is, the main part development diagram illustrating the shaft sealing device by developing the device in a circumferential direction.

[0021] FIG. 3 is a sectional diagram on arrow along the line in FIG. 2.

[0022] FIG. 4 is a diagram illustrating a first modified example of the shaft sealing device in the turbomachine illustrated in FIG. 1, that is, the diagram corresponding to the diagram in FIG. 2.

[0023] FIG. 5 is a sectional diagram on arrow along the V-V line in FIG. 4.

[0024] FIG. 6 is a diagram illustrating a second modified example of the shaft sealing device in the turbomachine illustrated in FIG. 1, that is, the diagram corresponding to the diagram in FIG. 2.

[0025] FIG. 7 is a sectional diagram on arrow along the VII-VII line in FIG. 6.

[0026] FIG. 8 is a diagram illustrating a third modified example of the shaft sealing device in the turbomachine illustrated in FIG. 1, that is, the diagram corresponding to the diagram in FIG. 2.

[0027] FIG. 9 is a sectional diagram on arrow along the IX-IX line in FIG. 8.

[0028] FIG. 10 is a diagram illustrating a fourth modified example of the shaft sealing device in the turbomachine illustrated in FIG. 1, that is, the diagram corresponding to the diagram in FIG. 2.

[0029] FIG. 11 is a sectional diagram on arrow along the XI-XI line in FIG. 10.

[0030] FIG. 12 is a diagram illustrating a fifth modified example of the shaft sealing device in the turbomachine illustrated in FIG. 1, that is, the diagram corresponding to the diagram in FIG. 2.

[0031] FIG. 13 is a sectional diagram on arrow along the XIII-XIII line in FIG. 12.

DESCRIPTION OF EMBODIMENTS

[0032] In the following, specific embodiments of the turbomachine of the present invention will be described on the basis of the appended drawings. In the respective drawings, parts designated by the same numerals indicate the same or corresponding parts.

Embodiment 1

[0033] The embodiment 1 of a turbomachine of the present invention will be described using FIG. 1 to FIG. 3.

[0034] FIG. 1 is a partial longitudinal sectional diagram illustrating a uniaxial multistage centrifugal pump as a turbomachine 1 of the present invention. First, an overall configuration of the turbomachine 1 of the present embodiment 1 will be described with reference to FIG. 1. Incidentally, as the uniaxial multistage centrifugal pump, for example, a boiler feed pump and so forth are available.

[0035] In FIG. 1, the turbomachine 1 of the present embodiment is configured by a rotor 3 having an impeller 2, a bearing (not illustrated) which rotatably supports this rotor 3, an inner-side casing (an inner casing) 5 which contains the rotor 3 therein and forms a stationary flow passage 4, an outer-side casing (an outer casing) 6 which contains the inner-side casing 5 therein and so forth. The stationary flow passage 4 is provided with a diffuser vane 7 which has been provided on the discharge side of the impeller 2 and a return vane 8 which has been provided on the next-stage impeller 2 side.

[0036] In addition, a wearing ring 9a is provided on an inner surface of a stationary part (an inner surface of the casing 5 in this example) which faces an outer circumferential surface of a mouth ring part 2a of the impeller 2 and this wearing ring 9a configures one labyrinth shaft sealing device 9 which seals a gap between the mouth ring part 2a of the impeller 2 and the stationary part.

[0037] A cylindrical part 2b is provided on the rear face side of the impeller 2, a stage bush 9b is provided on the inner surface of the stationary part (the inner surface of the casing 5) which faces an outer circumferential surface of this cylindrical part 2b, and this stage bush 9b configures another labyrinth shaft sealing device 9 which seals a gap between the cylindrical part 2b of the impeller 2 and the stationary part.

[0038] 10 denotes a balance drum adapted to achieve a balance of thrust force which acts on the rotor 3, a balance drum shaft sealing device 9c is provided on the inner surface of the stationary part (the inner surface of the casing 5 or 6) which faces an outer circumferential surface of this balance drum 10, and this balance drum shaft sealing device 9c configures a further labyrinth shaft sealing device 9 which seals a gap between the balance drum 10 and the stationary part.

[0039] Next, an operation of the turbomachine 1 which is configured as mentioned above will be described. The working fluid (a liquid such as water and so forth in this example) is sucked into the impeller 2 by rotating the rotor 3, is discharged onto the stationary flow passage 4 by being applied with a dynamic pressure by this impeller 2 and the dynamic pressure so applied is converted into a static pressure on the stationary flow passage 4 which is provided with the diffuser vane 7 and the return vane 8. Thereby, the working fluid turns into the high-pressure working fluid, the pressure of the high-pressure working fluid is increased as the fluid sequentially flows into the next-stage impeller 2, and the high-pressure working fluid which has been discharged from the final-stage impeller 2 is fed to the demander and so forth under pressure.

[0040] Part of the working fluid which flows through within the turbomachine 1 leaks to the outside through the gap parts between the stationary part such as the casing 5 and so forth and the rotor 3, that is, the gap between the outer circumferential surface of the mouth ring part 2a of the impeller 2 and the stationary part, the gap between the outer circumferential surface of the cylindrical part 2b of the impeller 2 and the stationary part, the gap between the outer circumferential surface of the balance drum 10 and the stationary part and so forth which have been described before.

[0041] The labyrinth shaft sealing devices 9 are respectively provided in the aforementioned respective gap parts in order to reduce these leakage flows. That is, the wearing ring 9a is provided on the mouth ring part 2a at the entrance of the impeller 2, the stage bush 9b is provided on the cylindrical part 2b on the rear face of the impeller 2, and the balance drum shaft sealing device 9c is provided on a part of the balance drum 10 on the rear face of the final-stage impeller 2 respectively.

[0042] Next, configurations of these shaft sealing devices will be described using FIG. 2 and FIG. 3. FIG. 2 is a diagram illustrating the inner surface shape of the shaft sealing device in the turbomachine 1 illustrated in FIG. 1, that is, a main part development diagram illustrating the shaft sealing device 9 by developing the shaft sealing device 9 in the circumferential direction, and FIG. 3 is a sectional diagram on arrow along the line in FIG. 2. An arrow which indicates the circumferential direction matches a rotation direction. The same shall apply hereinafter. In addition, the leakage flow has a swirling component and therefore flows into the device 9 in a state of inclining from the axial direction to the circumferential direction.

[0043] Incidentally, as the labyrinth shaft sealing devices 9 which are provided in the turbomachine 1, the wearing ring 9a which has been provided on the mouth ring part 2a at the entrance of the impeller 2, the stage bush 9b which has been provided on the cylindrical part 2b on the rear face of the impeller 2, and the balance drum shaft sealing device 9c which has been provided on the part of the balance drum 10 on the rear face of the final-stage impeller 2 are provided as described before. In the present embodiment, the inner surface shapes of the above-mentioned shaft sealing devices 9a to 9c are made the same as one another and the shaft sealing device 9 illustrated in FIG. 2 and FIG. 3 has a structure which is commonly applied to the wearing ring 9a, the stage bush 9b, and the balance drum shaft sealing device 9c which have been described above. Therefore, in the following, the shaft sealing devices 9a, 9b and 9c will be described simply as the shaft sealing device (or the labyrinth shaft sealing device) 9.

[0044] As illustrated in FIG. 2, many grooves which are parallel with the axial direction of the rotor 3, that is, axial grooves 11 are provided in an inner surface of the shaft sealing device 9 in the present embodiment 1. Describing in more detail, an axial groove group A (A1, A2, A3, . . . and A8) which has been configured by a plurality (four grooves in this example) of the axial grooves 11 which have been intermittently arranged on the same straight line which is parallel with the axial direction of the rotor 3 with a land part 12 being interposed between the adjacent grooves 11 is provided in the inner surface of the shaft sealing device 9. The axial groove groups A are adjacently arranged in a plurality of lines in the circumferential direction of the inner surface of the shaft sealing device 9. In the example illustrated in FIG. 2, eight axial groove groups A1, A2, . . . and A8 are provided in the circumferential direction in an illustrated range thereof as the plurality of lines of the axial groove groups which have been adjacently arranged in the circumferential direction. In addition, the plurality of axial groove groups A1, A2, . . . and A8 which have been adjacently arranged in the circumferential direction are arranged to be parallel with or almost parallel with one another.

[0045] In addition, in the example illustrated in FIG. 2, the plurality of axial grooves 11 which configure the shaft sealing device 9 are provided so as to form a staggered arrangement that the positions of the adjacent grooves deviate from each other in both of the circumferential direction and the axial direction of the rotor. Further, the plurality of axial grooves 11 which are arranged in a staggered state each is formed into a rectangular shape that a length in the axial direction becomes longer than a length in the circumferential direction, the plurality of axial grooves 11 are arranged so as to partially overlap one another in the circumferential direction, and the respective axial grooves 11 in each of the axial direction groove groups A1, A2, . . . and A8 are configured so as to not overlap the axial grooves 11 in the other axial groove groups in the axial direction.

[0046] It is possible to easily machine each of the axial grooves 11 which are provided in the shaft sealing device 9 by pressing a circular tool such as, for example, an end mil and so forth against the inner surface of the shaft sealing device 9, and it is possible to form semi-circular (an arc-shaped) grooves which are parallel with one another in the axial direction by a plural number and intermittently with ease as illustrated in FIG. 3. A length of the land part 12 which is favorable in a case of handling the liquid as the working fluid is sufficiently ensured by intermittently forming the axial grooves 11 and thereby it becomes possible to produce with ease the shaft sealing device 9 that the land part 12 has a thickness. It becomes possible to effectively reduce an amount of the leakage flow which leaks from the shaft sealing device in the axial direction by sufficiently ensuring the length of the land part 12.

[0047] On the other hand, owing to provision of a configuration that many axial grooves 11 which are long in the axial direction and short in the circumferential direction have been arranged in the circumferential direction in the inner surface of the shaft sealing device 9, it is possible to reduce an amount of the working fluid which escapes in the circumferential direction when displacing the rotor 3, in the working fluid which has flown into the axial grooves 11, and thereby it is possible to improve the vibration damping property of the shaft sealing device 9.

[0048] In addition, since the plurality of axial groove groups A (A1, A2, . . . and A8) are arranged in the circumferential direction in the inner surface of the shaft sealing device 9 and the respective axial grooves 11 in the respective axial groove groups A are arranged in the staggered state so as to partially overlap one another in the circumferential direction, the leakage flow alternately passes over parts of the land parts 12 and the axial grooves 11. Therefore, it is possible to effectively suppress a swirling-direction flow which would cause generation of the unstable fluid force.

[0049] That is, since it is possible to suppress flowing of the leakage flow which flows into the shaft sealing device 9 in the axial direction by turning into the swirling flow which swirls along the rotation direction of the rotor 3, it is possible to reduce generation of the unstable flow force which would further encourage the swirling movement which works in the circumferential direction due to vibration relative to the rotor 3 and thereby it is possible to suppress generation of an unstable vibration in the rotor 3.

[0050] Moreover, according to the present embodiment, although most of the leakage flow which is directed in the axial direction alternately passes over the parts of the land parts 12 and the axial grooves 11, the land part 12 has a sufficient thickness (for example, a thickness which corresponds to at least a half of the length of the axial groove 11) in the axial direction and therefore the viscous friction generated when the leakage flow flows over this land part 12 becomes large and it is also possible to reduce the axial-direction flow owing to abrupt expansion of the leakage flow passage when the leakage flow flows into the axial groove 11.

[0051] Incidentally, since the axial groove 11 in the above-mentioned present embodiment 1 is formed into the rectangular shape that the length in the axial direction becomes longer than the length in the circumferential direction, it is possible to more increase the effect of suppressing turning of the leakage flow which has flown into the shaft sealing device 9 into the swirling flow. However, an aspect ratio of the axial-direction width to the circumferential-direction width of the axial groove 11 is not limited to the aspect ratio which allows formation of the axial groove into the rectangular shape which is long in the axial direction and the shape of the groove may be appropriately selected in accordance with the shape of the tool used for forming the axial grooves 11 and, for example, the axial-direction width and the circumferential-direction width of the axial groove 11 may be configured to be almost the same as each other.

[0052] In addition, although it is preferable to apply the above-mentioned shaft sealing device 9 to all of the shaft sealing devices 9 (the wearing ring 9a, the stage bush 9b and the balance drum shaft sealing device 9c) of the turbomachine 1, the above-mentioned shaft sealing device 9 may be applied to at least one of the shaft sealing devices 9 and it is effective to apply the present invention, in particular, to the shaft sealing device 9 for a high-pressure part that the unstable fluid force and the leakage amount become large.

[0053] Next, modified examples of the turbomachine 1 of the above-mentioned embodiment 1 will be described using FIG. 4 to FIG. 13. Since, in the respective drawings, the parts to which the same numerals as those in FIG. 1 to FIG. 3 are assigned indicate the same or corresponding parts and the overall configuration of the turbomachine 1 is the same as the configuration in FIG. 1 which has been described in the above-mentioned embodiment 1, description of the overall configuration of the turbomachine 1 is omitted and only parts which are different in configuration from those in FIG. 1 to FIG. 3 in the shaft sealing device 9 will be described.

[0054] A first modified example of the shaft sealing device 9 in the above-mentioned embodiment 1 will be described with reference to FIG. 4 and FIG. 5. FIG. 4 is a diagram illustrating the first modified example of the shaft sealing device in the turbomachine illustrated in FIG. 1, that is, the diagram which corresponds to FIG. 2, and FIG. 5 is a sectional diagram on arrow along the V-V line in FIG. 4.

[0055] While in the example illustrated in FIG. 2, the plurality of axial grooves 11 which configure the shaft sealing device 9 are provided to be arranged in the staggered state in both of the circumferential direction and the axial direction of the rotor 3, in this first modified example, the plurality of axial grooves 11 which are parallel with one another in the axial direction and are formed into the rectangular shape are arrayed in a grid form that the positions of the adjacent axial grooves become the same as each other (that is, are on the same straight line) as illustrated in FIG. 4.

[0056] In the present embodiment, the axial grooves 11 may be arrayed in the grid form in this way. In this case, since the plurality of axial grooves 11 are arranged side by side (on the same straight line) respectively in the axial direction and in the circumferential direction, each land part 12 which is the part where the axial grooves 11 are not present is formed continuously (that is, so as to extend) in the circumferential direction. For this reason, the effect of suppressing turning of the leakage flow which flows into the shaft sealing device 9 into the swirling flow which swirls along the rotation direction of the rotor is reduced. However, work for positioning the tool and the material when machining the axial grooves 11 is reduced owing to provision of the configuration of this first modified example and therefore it is possible to obtain an effect of greatly improving productivity.

[0057] A second modified example of the shaft sealing device 9 in the above-mentioned embodiment 1 will be described with reference to FIG. 6 and FIG. 7. FIG. 6 is a diagram illustrating the second modified example of the shaft sealing device in the turbomachine illustrated in FIG. 1, that is, the diagram which corresponds to FIG. 2 and FIG. 7 is a sectional diagram on arrow along the VII-VII line in FIG. 6.

[0058] While the example that the axial-direction section of the axial groove 11 which is long in the axial direction has been formed into the semicircular arc-shape is illustrated in FIG. 2, in this second modified example, the axial-direction section of the axial groove 11 is formed into an almost rectangular shape as illustrated in FIG. 7. It is possible to form the axial-direction section of the axial groove 11 into shapes other than the arc shape in this way, such as, for example, a rectangular shape, an elliptical shape, a trapezoidal shape, a triangular shape and so forth, not limited to the arc shape and the leakage flow reduction effect and the unstable fluid force reduction effect which are the same as the above are obtained. Incidentally, such an advantage that it is possible to easily perform machining of each axial groove 11 is obtained by forming the axial-direction section of each axial groove 11 into the arc shape as illustrated in FIG. 3.

[0059] A third modified example of the shaft sealing device 9 in the above-mentioned embodiment 1 will be described with reference to FIG. 8 and FIG. 9. FIG. 8 is a diagram illustrating the third modified example of the shaft sealing device in the turbomachine illustrated in FIG. 1, that is, the diagram which corresponds to FIG. 2 and FIG. 9 is a sectional diagram on arrow along the IX-IX line in FIG. 8.

[0060] While the examples that the axial grooves 11 of the same shape and the same size have been provided in the shaft sealing devices 9 have been described in the above-mentioned FIG. 2 to FIG. 7, in this third modified example, the axial grooves 11 are configured by two kinds of the grooves, that is, a large groove 11a which is large in axial-direction and radial-direction sizes and a small groove 11b which is small in the axial-direction and radial-direction sizes as illustrated in FIG. 8 and FIG. 9. It is favorable to arrange the large grooves 11a one by one every time several small groves 11b are arranged in the axial direction. In the example illustrated in FIG. 8 and FIG. 9, the axial grooves 11a and 11b are configured such that the large groove 11a is arranged one by one every time the small grooves 11b are arranged two by two in the axial direction. Also the respective axial groove groups A1, A2, . . . and A8 which are arranged in the plural number in the circumferential direction are configured in the same way.

[0061] Since it is possible for the large grooves 11a to more effectively suppress growing of the swirling flow which is the cause for generation of the unstable fluid force by obstructing uniformity of the flow, it is possible to improve the effect of reducing the unstable fluid force. Incidentally, the number of the kinds of the axial grooves 11 is not limited to two and three or more kinds of axial grooves which are different from one another in axial-direction and radial-direction sizes may be configured as the axial grooves 11.

[0062] A fourth modified example of the shaft sealing device 9 in the above-mentioned embodiment 1 will be described with reference to FIG. 10 and FIG. 11. FIG. 10 is a diagram illustrating the fourth modified example of the shaft sealing device 9 in the turbomachine 1 illustrated in FIG. 1, that is, the diagram which corresponds to FIG. 2 and FIG. 11 is a sectional diagram on arrow along the XI-XI line in FIG. 10.

[0063] The examples that the aforementioned axial grooves 11 are formed as the grooves which are parallel with one another in the axial direction and also the respective axial groove groups A1, A2, . . . and A8 which are provided in the plural number in the circumferential direction are arranged in parallel with one another respectively in the axial direction have been described in the shaft sealing devices 9 illustrated in the above-mentioned FIG. 2 to FIG. 9. In contrast, in this fourth modified example, the axial grooves 11 are provided by inclining them from the axial direction to the rotation direction (the circumferential direction) of the motor 3 and also the respective axial groove groups A1, A2, . . . and A8 which are provided in the plural number in the circumferential direction are arranged so as to be parallel with one another by respectively inclining the axial groove groups from the axial direction to the rotation direction of the rotor 3.

[0064] Since it is possible to proximate the direction that the axial grooves 11 are directed to the direction that the leakage flow flows into the shaft sealing device 9 by inclining the axial grooves 11 and the axial groove groups A1, A2, . . . and A8 which configure the shaft sealing device 9 from the axial direction to the rotation direction of the rotor 3 in this way, it is possible to more effectively decelerate a flow velocity of the leakage flow. Accordingly, it is possible to more reduce the leakage flow and it is also possible to effectively suppress the unstable fluid force.

[0065] Incidentally, since it is desirable for the shaft sealing device 9 to suppress the leakage flow as much as possible, it is preferable that an angle formed by the direction that the axial grooves 11 are directed or the direction that the axial groove groups A1, A2, . . . and A8 are directed and the axial direction of the rotor 3 be less than about 45 degrees, that is, an angle formed by the direction that the axial grooves 11 are directed or the direction that the axial groove groups A1, A2, . . . and A8 are directed and the rotation direction of the rotor 3 be at least about 45 degrees. In addition, in the description of the present invention, the grooves and the groove groups whose angle relative to the axial direction of the rotor 3 is less than about 45 degrees are also called the axial grooves and the axial groove groups respectively.

[0066] A fifth modified example of the shaft sealing device 9 in the above-mentioned embodiment 1 will be described with reference to FIG. 12 and FIG. 13. FIG. 12 is a diagram illustrating the fifth modified example of the shaft sealing device in the turbomachine illustrated in FIG. 1, that is, the diagram which corresponds to FIG. 2 and FIG. 13 is a sectional diagram on arrow along the XIII-XIII line in FIG. 12.

[0067] The fifth modified example is an example that the aforementioned shaft sealing device 9 of the embodiment 1 illustrated in FIG. 2 and FIG. 3 is partially modified, the basic configuration thereof is the same as that illustrated in FIG. 2 and FIG. 3 and therefore description will be made focusing on different points.

[0068] In the fifth modified example, the plurality of axial grooves 11 are the same as those in the example illustrated in FIG. 2 and FIG. 3 in the point that the plurality of axial grooves 11 are arranged in the staggered state in the axial direction of the rotor 3. However, while in the example illustrated in FIG. 2 and FIG. 3, the axial grooves 11 which are arranged on the same straight line in the axial direction are configured so as not overlap the axial grooves 11 on another same straight line, in the fifth modified example, the axial grooves 11 which are arranged on the same straight line in the axial direction are configured so as to partially overlap the other axial grooves 11 which are arranged adjacently to the above-mentioned axial grooves 11 in the circumferential direction or the axial grooves 11 which are arranged on another same straight line.

[0069] Describing with reference to FIG. 12, for example, the axial grooves 11 in the axial groove group A1 are arranged so as to partially overlap the axial grooves 11 in the axial groove group A2 (in the example in FIG. 12, only one groove is illustrated) which is adjacent to the axial groove group A1 in the circumferential direction. The same applies to other axial groove groups A3 to A12. In addition, the respective axial grooves 11 in one of the aforementioned respective axial groove groups A1 to A12 are configured so as not to overlap, in the circumferential direction, the axial grooves 11 in another one of the axial groove groups A1 to A12 which is adjacent to the above-mentioned axial groove group in the circumferential direction. Accordingly, in this fifth modified example, each land part 12 is provided continuously (that is, so as to extend) in the circumferential direction. Other configurations are the same as those of the example illustrated in FIG. 2 and FIG. 3.

[0070] According to the fifth modified example, the axial grooves 11 are configured so as to partially overlap one another in the axial direction and therefore an effect of more reducing the leakage flow in the axial direction is obtained.

[0071] As described above, according to the embodiment and the respective modified examples which have been described above, since in the shaft sealing device, the plurality of axial grooves 11 which have been intermittently arranged in the axial direction and the circumferential direction of the rotor with the land part being interposed between the adjacent axial grooves 11 are provided in the inner circumferential surface thereof, it is possible to obtain the turbomachine which is capable of reducing the leakage of the working fluid in the shaft sealing device of the turbomachine which handles the liquid as the working fluid and is also capable of reducing the unstable fluid force which acts on the rotor.

[0072] Incidentally, the present invention is not limited to the above-mentioned embodiment and various modified examples are included. For example, although in the above-mentioned embodiment, the case where the present invention has been applied to the uniaxial multistage centrifugal pump as the turbomachine has been described by way of example, the present invention is not limited to the uniaxial multistage centrifugal pump and is also applicable to a single-stage centrifugal pump, a reversible pump turbine, a hydraulic turbine and so forth similarly.

[0073] In addition, it is also possible to replace part of the configuration of the embodiment or each of the modified examples which have been described above with the configuration of another modified example and it is also possible to add the configuration of another modified example to the configuration of the embodiment or one of the modified examples which have been described above. Further, the above-mentioned embodiment has been described for comprehensibly describing the present invention and is not necessarily limited to the turbomachine which includes all of the configurations which have been described above.