US20140020403A1 - Sealing device, axial turbine and power plant - Google Patents

Sealing device, axial turbine and power plant Download PDF

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Publication number
US20140020403A1
US20140020403A1 US13/944,201 US201313944201A US2014020403A1 US 20140020403 A1 US20140020403 A1 US 20140020403A1 US 201313944201 A US201313944201 A US 201313944201A US 2014020403 A1 US2014020403 A1 US 2014020403A1
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US
United States
Prior art keywords
circumferential surface
inner circumferential
rotor
rotating body
opening member
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Abandoned
Application number
US13/944,201
Other languages
English (en)
Inventor
Tomohiko Tsukuda
Yuki MIMURA
Akihiro Onoda
Naoki Shibukawa
Iwataro Sato
Kazutaka Tsuruta
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Toshiba Corp
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Toshiba Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Toshiba Corp filed Critical Toshiba Corp
Assigned to KABUSHIKI KAISHA TOSHIBA reassignment KABUSHIKI KAISHA TOSHIBA ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: MIMURA, YUKI, ONODA, AKIHIRO, SATO, IWATARO, SHIBUKAWA, NAOKI, TSUKUDA, TOMOHIKO, Tsuruta, Kazutaka
Publication of US20140020403A1 publication Critical patent/US20140020403A1/en
Abandoned legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/28—Three-dimensional patterned
    • F05D2250/283—Three-dimensional patterned honeycomb
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/38—Arrangement of components angled, e.g. sweep angle
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • F05D2260/963—Preventing, counteracting or reducing vibration or noise by Helmholtz resonators

Definitions

  • Embodiments described herein relate to a sealing device, an axial turbine and a power plant.
  • An axial turbine includes a rotor in a casing for closing a working fluid, a rotor vane on a side of an outer circumferential surface of the rotor, and a stator vane on a side of an inner circumferential surface of the casing.
  • a sealing device for sealing the working fluid is provided in a gap between the outer circumferential surface of the rotor and an inner circumferential surface of the stator vane or in a gap between the inner circumferential surface of the casing and an outer circumferential surface of the rotor vane.
  • a labyrinth sealing device is generally used as the sealing device.
  • FIGS. 1A to 1C are sectional views and an arrow view showing a structure of a sealing device of a first embodiment
  • FIGS. 2A to 2C are sectional views and an arrow view showing a structure of a sealing device of a second embodiment
  • FIGS. 3A and 3B are a sectional view and an arrow view showing a structure of a sealing device of a third embodiment
  • FIGS. 4A and 4B are a sectional view and an arrow view showing a structure of a sealing device of a fourth embodiment
  • FIGS. 5A and 5B are sectional views showing a structure of a sealing device of a fifth embodiment
  • FIGS. 6A and 6B are sectional views showing a structure of a sealing device of a sixth embodiment
  • FIG. 7 is a sectional view showing a structure of a sealing device of a seventh embodiment
  • FIG. 8 is a sectional view showing a structure of a sealing device of an eighth embodiment
  • FIGS. 9A and 9B are a sectional view and an arrow view showing a structure of a sealing device of a ninth embodiment
  • FIG. 10 is a sectional view showing a structure of a sealing device of a tenth embodiment
  • FIG. 11 is a sectional view showing a structure of a sealing device of an eleventh embodiment
  • FIG. 12 is a sectional view showing a structure of a CO 2 turbine of a twelfth embodiment.
  • FIG. 13 is a schematic view showing a configuration of a thermal power generation system of a thirteenth embodiment.
  • the destabilizing fluid force causes unstable vibration of the rotor at worst. Particularly, in a case where the rotor is rotated at high speed or in a case where a differential pressure is large between an inlet and an outlet of the sealing device, the destabilizing fluid force is larger.
  • honeycomb sealing device including a honeycomb member on the side of the inner circumferential surface of the casing or the stator vane is used instead of the labyrinth sealing device, an effect of damping the destabilizing fluid force is larger than the labyrinth sealing device. Therefore, it is known that the honeycomb sealing device can stabilize the unstable vibration of the rotor.
  • the honeycomb sealing device due to a large pressure decrease in the axial direction in the honeycomb sealing device, there is a possibility that honeycomb holes of the honeycomb member are damaged.
  • the axial turbine is a steam turbine or a CO 2 turbine which are driven by a high-pressure working fluid, the honeycomb holes are more easily damaged.
  • a sealing device in one embodiment, includes seal fins provided on an inner circumferential surface of a stationary body or an outer circumferential surface of a rotating body so as to be adjacent to each other in an axial direction of the rotating body in a gap between the outer circumferential surface of the rotating body and the inner circumferential surface of the stationary body.
  • the device further includes at least one opening member provided on the inner circumferential surface of the stationary body, the opening member being provided at a position between seal fins adjacent to each other in the axial direction, and having holes opened on a side of the inner circumferential surface of the stationary body.
  • FIGS. 1A to 1C are sectional views and an arrow view showing a structure of a sealing device of a first embodiment.
  • FIGS. 1A to 1C show the sealing device provided in an axial turbine as an example.
  • An example of this axial turbine includes a steam turbine and a CO 2 turbine.
  • FIG. 1A is a meridional sectional view showing the structure of the sealing device.
  • FIG. 1B is an arrow view in which the sealing device is seen in the A direction of FIG. 1A .
  • FIG. 1C is a sectional view along line B-B of FIG. 1A .
  • FIGS. 1A to 1C show a rotor 1 , a stator vane 2 , a stator vane inner ring 3 , a plurality of seal fins 4 , and a plurality of honeycomb members 5 as components of the sealing device.
  • the rotor 1 is a rotation shaft for transmitting rotation energy to a power generator.
  • FIGS. 1A to 1C show a X direction which is parallel to the axial direction of the rotor 1 , and Y and Z directions which are perpendicular to the axial direction of the rotor 1 .
  • a rotor vane (not shown) is attached.
  • the rotor 1 is an example of a rotating body of the disclosure.
  • the stator vane 2 is attached on a side of an inner circumferential surface of a casing (not shown). On a side of an inner circumferential surface of the stator vane 2 , the stator vane inner ring 3 integrated with the stator vane 2 or formed as a separate body is provided.
  • the stator vane 2 and the stator vane inner ring 3 are examples of a stationary body of the disclosure.
  • the sealing device of FIG. 1 is provided in a gap between the outer circumferential surface of the rotor 1 and an inner circumferential surface of the stator vane inner ring 3 .
  • a sealing device provided in a gap between the inner circumferential surface of the casing and an outer circumferential surface of a shroud cover of the rotor vane or the like will be described later.
  • the seal fins 4 are members for sealing a working fluid, and are provided on the inner circumferential surface of the stator vane inner ring 3 in a gap between the rotor 1 and the stator vane inner ring 3 .
  • the seal fins 4 extend in the circumferential direction of the rotor 1 along the outer circumferential surface of the rotor 1 , and are arranged adjacently to each other in the axial direction of the rotor 1 . Radial length of the seal fins 4 is set so as to have a minute gap from the rotor 1 . By such seal fins 4 , leakage of the working fluid from the upstream side to the downstream side of the sealing device is reduced.
  • the seal fins 4 are integrated with the stator vane inner ring 3 or formed as separate bodies.
  • the honeycomb members 5 are attached to the inner circumferential surface of the stator vane inner ring 3 , and have a large number of honeycomb holes 5 a opened on the side of the inner circumferential surface of the stator vane inner ring 3 .
  • Each of the honeycomb holes 5 a has a hexagonal cylinder shape with a dead end.
  • Members forming bottom surfaces of the honeycomb holes 5 a may be the honeycomb members 5 or the stator vane inner ring 3 .
  • the honeycomb members 5 of the present embodiment has a large number of regularly arranged honeycomb holes 5 a , and specifically has plural rows of honeycomb holes 5 a , in each of which the honeycomb holes 5 a are placed in one line in the circumferential direction.
  • the honeycomb members 5 and the honeycomb holes 5 a are examples of at least one opening member and holes of the disclosure, respectively.
  • the sealing device of the present embodiment is provided not only with a plurality of seal fins 4 but also a plurality of honeycomb members 5 .
  • Each honeycomb member 5 is arranged at a position between seal fins 4 adjacent to each other in the axial direction on the inner circumferential surface of the stator vane inner ring 3 .
  • a distance between an inner circumferential surface of the honeycomb member 5 and the outer circumferential surface of the rotor 1 is set to be longer than a distance between front ends of the seal fins 4 and the outer circumferential surface of the rotor 1 .
  • the honeycomb members 5 are not installed on the opposite surfaces to the seal fins 4 , but installed at the positions between the seal fins 4 adjacent to each other in the axial direction, on the inner circumferential surface of the stator vane inner ring 3 which is the same side as the seal fins 4 .
  • the pressure difference between the upstream side and the downstream side of a seal fin 4 is large, there is almost no pressure difference in a region between the seal fins 4 adjacent to each other in the axial direction. Therefore, according to the present embodiment, a possibility that the honeycomb holes 5 a receive an excessive force in the axial direction can be reduced, so that the risk that the honeycomb holes 5 a are damaged can be decreased.
  • the honeycomb members 5 by installing the honeycomb members 5 in the regions surrounded by the adjacent seal fins 4 , unbalance of circumferential pressure distribution can be eased by a damper effect by the honeycomb members 5 . Therefore, according to the present embodiment, a destabilizing fluid force that destabilizes the rotor 1 can be reduced.
  • the honeycomb holes 5 a with dead ends work as resistances against a circumferential flow rate of the fluid, a swirling flow rate in a cavity serving as a generation source of the unbalance of the circumferential pressure distribution of the fluid can be reduced. Therefore, according to the present embodiment, the destabilizing fluid force that destabilizes the rotor 1 can further be reduced.
  • the honeycomb members 5 are installed at the positions between the seal fins 4 adjacent to each other in the axial direction of the rotor 1 . Therefore, according to the present embodiment, damage to the honeycomb holes 5 a can be suppressed while reducing the destabilizing fluid force by the honeycomb members 5 .
  • FIGS. 2A to 2C are sectional views and an arrow view showing a structure of a sealing device of a second embodiment.
  • FIGS. 2A to 2C are a meridional sectional view, an A-direction arrow view, and a B-B sectional view corresponding to FIGS. 1A to 1C , respectively.
  • the seal fins 4 are provided not on the inner circumferential surface of the stator vane inner ring 3 but on the outer circumferential surface of the rotor 1 .
  • the seal fins 4 may be integrated with the rotor 1 or formed as separate bodies from the rotor 1 .
  • the inner circumferential surface of the stator vane inner ring 3 has first surfaces S 1 which are the inner circumferential surfaces of the honeycomb members 5 , and second surfaces S 2 placed between the honeycomb members 5 adjacent to each other in the axial direction, placed on the upstream side of the most upstream honeycomb member 5 , or placed on the downstream side of the most downstream honeycomb member 5 .
  • the first surfaces S 1 have a hollow structure having a large number of honeycomb holes 5 a
  • the second surfaces S 2 have a solid structure having no such holes.
  • the seal fins 4 are provided at positions facing the second surfaces S 2 on the outer circumferential surface of the rotor 1 .
  • the honeycomb members 5 are arranged at positions between the seal fins 4 adjacent to each other in the axial direction on the inner circumferential surface of the stator vane inner ring 3 .
  • the honeycomb members 5 are installed at the positions between the seal fins 4 adjacent to each other in the axial direction of the rotor 1 . Therefore, according to the present embodiment, as well as the first embodiment, the damage to the honeycomb holes 5 a can be suppressed while reducing the destabilizing fluid force by the honeycomb members 5 .
  • seal fins 4 on the side of the rotor 1 , for example, free-polished member layers (not shown) can be formed on the second surfaces S 2 . Thereby, the minute gaps between the seal fins 4 and the stator vane inner ring 3 are downsized, so that a seal leakage flow rate can be reduced.
  • the width in the axial direction of the second surfaces S 2 is desirably set to be such sufficient width that the seal fins 4 continue to face the second surfaces S 2 even when the position of the rotor 1 is displaced.
  • FIGS. 3A and 3B are a sectional view and an arrow view showing a structure of a sealing device of a third embodiment.
  • FIGS. 3A and 3B are a meridional sectional view and an A-direction arrow view corresponding to FIGS. 1A and 1B , respectively.
  • the seal fins 4 are provided on the inner circumferential surface of the stator vane inner ring 3 , and the honeycomb members 5 are arranged at the positions between the seal fins 4 adjacent to each other in the axial direction on the inner circumferential surface of the stator vane inner ring 3 ( FIG. 3A ).
  • each honeycomb member 5 of the present embodiment is divided into a plurality of members 5 b and 5 c in the circumferential direction of the rotor 1 as shown in FIG. 3B , and include a reinforcing member 6 between the divided members 5 b and 5 c adjacent to each other in the circumferential direction.
  • the seal fin 4 Since there is a pressure difference between an upstream side surface S 3 and a downstream side surface S 4 of a seal fin 4 , the seal fin 4 receives a force from the upstream side surface S 3 to the downstream side surface S 4 within a range from a height of an outer circumferential surface of the honeycomb members 5 to a height of the inner circumferential surface of the honeycomb members 5 .
  • the reinforcing member 6 for reinforcing the seal fins 4 in the axial direction is installed between the divided members 5 b and 5 c adjacent to each other in the circumferential direction so as to be brought into contact with side surfaces of the seal fins 4 . Therefore, in the present embodiment, since the reinforcing member 6 receives the force from the upstream side surface S 3 to the downstream side surface S 4 , deformation and breakage of the seal fin 4 is suppressed, so that reliability of the seal fin 4 can be improved.
  • the division number of dividing each honeycomb member 5 in the circumferential direction may be any number.
  • each honeycomb member 5 is divided into four members in the circumferential direction, four reinforcing members 6 are installed between these divided members.
  • the direction and the shape of the reinforcing members 6 are not limited to those shown in FIG. 3B but the direction of the reinforcing members 6 may be the direction which is not parallel to the X direction, and the shape of the reinforcing members 6 may be a shape which is other than a rod shape, for example.
  • Each reinforcing member 6 may be in contact with seal fins 4 on both the sides or may be in contact with only a seal fin 4 on one side.
  • FIGS. 4A and 4B are a sectional view and an arrow view showing a structure of a sealing device of a fourth embodiment.
  • FIGS. 4A and 4B are a meridional sectional view and an A-direction arrow view corresponding to FIGS. 2A and 2B , respectively.
  • the seal fins 4 are provided on the outer circumferential surface of the rotor 1 , and the honeycomb members 5 are arranged at the positions between the seal fins 4 adjacent to each other in the axial direction on the outer circumferential surface of the stator vane inner ring 3 ( FIG. 4A ).
  • each honeycomb member 5 of the present embodiment is divided into the plurality of members 5 b and 5 c in the circumferential direction of the rotor 1 as shown in FIG. 4B , and include the reinforcing member 6 between the divided members 5 b and 5 c adjacent to each other in the circumferential direction. This is the same as the third embodiment.
  • the wall receives a force from the upstream side surface S 5 to the downstream side surface S 6 within the range from the height of the outer circumferential surface of the honeycomb members 5 to the height of the inner circumferential surface of the honeycomb members 5 .
  • the reinforcing member 6 for reinforcing the wall in the axial direction is installed between the members 5 b and 5 c adjacent to each other in the circumferential direction so as to be brought into contact with side surfaces of the wall. Therefore, in the present embodiment, since the reinforcing members 6 receive the force from the upstream side surfaces S 5 to the downstream side surfaces S 6 , deformation and breakage of the wall is suppressed, so that reliability of the honeycomb members 5 can be improved.
  • FIGS. 5A and 5B are sectional views showing a structure of a sealing device of a fifth embodiment.
  • FIGS. 5A and 5B are a meridional sectional view and a B-B sectional view corresponding to FIGS. 1A and 1C , respectively.
  • An arrow C of FIG. 5B indicates the rotation direction of the rotor 1 .
  • An arrow D indicates the inward normal direction on the inner circumferential surface of the stator vane inner ring 3 .
  • An arrow E indicates the direction from bottom regions to opening regions of the honeycomb holes 5 a.
  • the direction E from the bottom regions to the opening regions of the honeycomb holes 5 a is inclined opposite to the rotation direction C of the rotor 1 with respect to the normal direction D at the same position.
  • a resistance given to the circumferential flow rate of the fluid by the honeycomb holes 5 a is increased. Therefore, according to the present embodiment, the swirling flow rate can be more reduced and the destabilizing fluid force can further be reduced.
  • FIGS. 6A and 6B are sectional views showing a structure of a sealing device of a sixth embodiment.
  • FIGS. 6A and 6B are a meridional sectional view and a B-B sectional view corresponding to FIGS. 1A and 1C , respectively.
  • each honeycomb member 5 of the present embodiment alternately includes first regions 5 d and second regions 5 e in which heights of inner circumferential surfaces are different from each other along the circumferential direction of the rotor 1 .
  • each honeycomb member 5 of the present embodiment has steps 7 between the first regions 5 d and the second regions 5 e in the circumferential direction of the rotor 1 .
  • the steps 7 work as resistances against the circumferential flow rate of the fluid, the swirling flow rate can be more reduced and the destabilizing fluid force can further be reduced.
  • the steps 7 may be provided on a border between segments of the stator vane inner ring 3 , for example.
  • the individual segment includes any one of the first region 5 d and the second region 5 e .
  • Each honeycomb member 5 may have the steps 7 by including three or more types of regions in which heights of inner circumferential surfaces are different from each other.
  • FIG. 7 is a sectional view showing a structure of a sealing device of a seventh embodiment.
  • FIG. 7 is a meridional sectional view corresponding to FIG. 1A .
  • slits 8 extending in the circumferential direction of the rotor 1 is provided on the inner circumferential surfaces of the honeycomb members 5 . According to the present embodiment, since the slits 8 work as resistances against the circumferential flow rate of the fluid, the swirling flow rate can be more reduced and the destabilizing fluid force can further be reduced.
  • Each slit 8 may be provided on the entire circumference in the circumferential direction on the inner circumferential surface of a honeycomb member 5 (i.e., 360 degree range of the circumference), or may be provided only on a part on the circumference in the circumferential direction on the inner circumferential surface of a honeycomb member 5 .
  • the slits 8 can pass through the honeycomb members 5 or not pass through. However, from a view point to extend an installment area of the honeycomb members 5 as far as possible, the slits 7 do desirably not pass through.
  • FIG. 8 is a sectional view showing a structure of a sealing device of an eighth embodiment.
  • FIG. 8 is a meridional sectional view corresponding to FIG. 1A .
  • the sealing device of FIG. 8 is provided with an upstream side honeycomb member 9 and a downstream side honeycomb member 10 in addition to the components shown in FIGS. 1A to 1C .
  • the upstream side honeycomb member 9 is provided at a position on the upstream side of the most upstream seal fin 4 on the inner circumferential surface of the stator vane inner ring 3 , and has a large number of honeycomb holes 9 a opened on the side of the inner circumferential surface of the stator vane inner ring 3 .
  • the downstream side honeycomb member 10 is provided at a position on the downstream side of the most downstream seal fin 4 on the inner circumferential surface of the stator vane inner ring 3 , and has a large number of honeycomb holes 10 a opened on the side of the inner circumferential surface of the stator vane inner ring 3 .
  • the upstream side honeycomb member 9 and the downstream side honeycomb member 10 are examples of at least one outside opening member of the disclosure.
  • the damper effect can further be enhanced and generation of the destabilizing fluid force can further be reduced.
  • the sealing device of the present embodiment may be provided with only one of the upstream side honeycomb member 9 and the downstream side honeycomb member 10 .
  • FIGS. 9A and 9B are a sectional view and an arrow view showing a structure of a sealing device of a ninth embodiment.
  • FIGS. 9A and 9B are a meridional sectional view and an A-direction arrow view corresponding to FIGS. 1A and 1B , respectively.
  • the honeycomb members 5 are replaced with opening members 11 .
  • Each opening member 11 is provided at a position between seal fins 4 adjacent to each other in the axial direction on the inner circumferential surface of the stator vane inner ring 3 , and has a large number of holes 11 a opened on the side of the inner circumferential surface of the stator vane inner ring 3 .
  • Each hole 11 a has a cylindrical shape with a dead end.
  • the damage to the holes 11 a can be suppressed while reducing the destabilizing fluid force by the opening members 11 as well as the first to eighth embodiments.
  • the shape of the holes 11 a may be a shape other than a cylindrical shape (for example, a square pillar shape).
  • FIG. 10 is a sectional view showing a structure of a sealing device of a tenth embodiment.
  • FIG. 10 is a meridional sectional view corresponding to FIG. 1A .
  • FIG. 10 shows the sealing device provided in an axial turbine as one example.
  • FIG. 10 shows a casing 12 , a rotor vane 13 , a shroud cover 14 , the plurality of seal fins 4 , and the plurality of honeycomb members 5 as components of the sealing device.
  • the casing 12 is configured to close the working fluid.
  • the rotor 1 described above is provided in this casing 12 .
  • the casing 12 is an example of the stationary body of the disclosure.
  • the rotor vane 13 is attached on the side of the outer circumferential surface of the rotor 1 described above.
  • the shroud cover 14 integrated with the rotor vane 13 or formed as a separate body is provided on the side of an outer circumferential surface of the rotor vane 13 .
  • the rotor vane 13 and the shroud cover 14 are examples of the rotating body of the disclosure.
  • the sealing device of FIG. 10 is provided in a gap between an inner circumferential surface of the casing 12 and an outer circumferential surface of the shroud cover 14 .
  • the seal fins 4 are provided on the inner circumferential surface of the casing 12 in a gap between the casing 12 and the shroud cover 14 .
  • the seal fins 4 extend in the circumferential direction along the outer circumferential surface of the shroud cover 14 and are arranged adjacently to each other in the axial direction.
  • the seal fins 4 are integrated with the casing 12 or formed as separate bodies.
  • the honeycomb members 5 are attached to the inner circumferential surface of the casing 12 . Specifically, the honeycomb members 5 are arranged at the positions between the seal fins 4 adjacent to each other in the axial direction on the inner circumferential surface of the casing 12 .
  • the damage to the honeycomb holes 5 a can be suppressed while reducing the destabilizing fluid force by the honeycomb members 5 as well as the first embodiment and the like.
  • FIG. 11 is a sectional view showing a structure of a sealing device of an eleventh embodiment.
  • FIG. 11 is a meridional sectional view corresponding to FIG. 1A .
  • the seal fins 4 are provided not on the inner circumferential surface of the casing 12 but on the outer circumferential surface of the shroud cover 14 .
  • the seal fins 4 may be integrated with the shroud cover 14 or formed as separate bodies from the shroud cover 14 .
  • the inner circumferential surface of the casing 12 has the first surfaces S 1 which are the inner circumferential surfaces of the honeycomb members 5 , and the second surfaces S 2 placed between the honeycomb members 5 adjacent to each other in the axial direction, placed on the upstream side of the most upstream honeycomb member 5 , or placed on the downstream side of the most downstream honeycomb member 5 .
  • the first surfaces S 1 have a hollow structure having a large number of honeycomb holes 5 a
  • the second surfaces S 2 have a solid structure having no such holes.
  • the seal fins 4 are provided at positions facing the second surfaces S 2 on the outer circumferential surface of the shroud cover 14 .
  • the honeycomb members 5 are arranged at the positions between the seal fins 4 adjacent to each other in the axial direction on the inner circumferential surface of the casing 12 .
  • the damage to the honeycomb holes 5 a can be suppressed while reducing the destabilizing fluid force by the honeycomb members 5 as well as the second embodiment and the like.
  • the sealing devices of the first to eleventh embodiments may be installed in a place other than the gap between the outer circumferential surface of the rotor 1 and the inner circumferential surface of the stator vane inner ring 3 , and the gap between the inner circumferential surface of the casing 12 and the outer circumferential surface of the shroud cover 14 .
  • the sealing devices may be installed in a ground packing of the axial turbine for example.
  • FIG. 12 is a sectional view showing a structure of a CO 2 turbine 101 of a twelfth embodiment.
  • the CO 2 turbine 101 of FIG. 12 is an example of an axial turbine of the disclosure.
  • Rotor vanes 105 are arranged at fixed intervals in an annular form on the outer side in the radial direction from a turbine rotor 103 . These rotor vanes 105 are also arranged at predetermined intervals in the axial direction, and a stator vane 106 is arranged between the rotor vanes 105 adjacent to each other in the axial direction. The stator vanes 106 are arranged at fixed intervals in an annular form. Base parts of the rotor vanes 105 are planted on an outer circumferential surface of the turbine rotor 103 .
  • FIG. 12 shows an example of a five-step configuration in which five rotor vanes 105 and five stator vanes 106 are alternately arranged in the axial direction, there is no particular limit in the step number of the rotor vanes 105 and the stator vanes 106 .
  • the CO 2 turbine 101 of FIG. 12 drives the turbine rotor 103 by using CO 2 in a supercritical state as the working fluid, and circulates and charges CO 2 discharged from the CO 2 turbine 101 into the CO 2 turbine 101 so as to use CO 2 for cooling the parts.
  • a critical point of CO 2 is at 31° C. and 7.4 MPa, and the CO 2 turbine 101 of FIG. 12 is based on the assumption that CO 2 is used at a higher temperature and a higher pressure than this critical point.
  • a sleeve pipe 107 is provided on the upstream side of the CO 2 turbine 101 of FIG. 12 , and a CO 2 gas in a supercritical state is charged from this sleeve pipe 107 into the turbine as the working fluid.
  • the charged CO 2 gas flows from the upstream side to the downstream side along the axial direction and is discharged from a discharge pipe (not shown).
  • the turbine rotor 103 is rotated and driven by using a force in which the fluid collides with the rotor vanes 105 , and there is a need for providing a gap between outer circumferential surfaces of the rotor vanes 105 and a facing inner circumferential surface of an inside casing 102 and between inner circumferential surfaces of the stator vanes 106 and the facing inner circumferential surface of the turbine rotor 103 . Therefore, a part of the fluid is leaked out through the gap on the side of the outer circumferential surfaces of the rotor vanes 105 and the gap on the side of the inner circumferential surfaces of the stator vanes 106 . In order to suppress this leakage, sealing devices 108 are respectively arranged on the side of the outer circumferential surfaces of the rotor vanes 105 and on the side of the inner circumferential surfaces of the stator vanes 106 .
  • Each sealing device 108 is configured that seal fins 109 are arranged at predetermined intervals on at least one of the outer circumferential surfaces of the rotor vanes 105 on the side of the turbine rotor 103 and the opposite surfaces of the inside casing 102 , and the inner circumferential surfaces of the stator vanes 106 and the opposite surfaces of the turbine rotor 103 , and thereby the gaps are narrowed down, so that the fluid is not easily leaked out.
  • the sealing devices 108 are provided not only on the circumferential surfaces of the rotor vanes 105 or the stator vanes 106 and the opposite surfaces thereof, but also on a ground packing 111 on the upper step side of the uppermost stator vane 106 .
  • honeycomb members 110 are provided in this sealing device 108 , the honeycomb members 110 of the structure of the first to eleventh embodiments (honeycomb members 5 ) are desirably adopted.
  • FIG. 13 is a schematic view showing a configuration of a thermal power generation system 120 of a thirteenth embodiment.
  • the thermal power generation system of FIG. 13 is an example of a power plant of the disclosure.
  • the CO 2 turbine 101 of FIG. 12 can be assembled into the thermal power generation system 120 capable of generating power and separating and collecting CO 2 at the same time.
  • the thermal power generation system 120 of FIG. 13 is provided with an oxygen production apparatus 121 , a combustor 122 , the CO 2 turbine 101 shown in FIG. 12 , a power generator 123 , a regenerative heat exchanger 124 , a cooler 125 , a moisture separator 126 , and a CO 2 pump 127 .
  • the oxygen production apparatus 121 removes nitrogen contained in the air and extracts only oxygen.
  • the combustor 122 generates a high-temperature combustion gas by using the oxygen extracted in the oxygen production apparatus 121 , fuel and CO 2 . Components of this combustion gas are CO 2 and water. A natural gas not using nitrogen such as a methane gas is used as the fuel used by the combustor 122 .
  • the high-temperature and high-pressure CO 2 gas generated in the combustor 122 is charged into the CO 2 turbine 101 shown in FIG. 12 and used for rotating and driving the turbine rotor 103 .
  • the power generator 123 is connected to a rotation shaft of the turbine rotor 103 , and the power generator 123 generates the power by using a rotation driving force of the turbine rotor 103 .
  • CO 2 and water vapor discharged from the CO 2 turbine 101 are cooled down in the regenerative heat exchanger 124 and then further cooled down in the cooler 125 . After that, water is removed in the moisture separator 126 , and only CO 2 is extracted. This CO 2 is compressed and its pressure is boosted in the CO 2 pump 127 .
  • a temperature of a part of the high-pressure CO 2 whose pressure is boosted in the CO 2 pump 127 is increased to about 400° C. in the regenerative heat exchanger 124 .
  • the CO 2 discharged from the regenerative heat exchanger 124 is used for cooling the CO 2 turbine 101 as cooling CO 2 and also supplied to the combustor 122 .
  • extra CO 2 other than the CO 2 used for power generation via the regenerative heat exchanger 124 is collected to be stored or used for other purposes (for example, used for increasing an oil drilling amount).
  • the power generation system 120 of the present embodiment generates power by using only CO 2 generated by combustion and water, and circulates and re-uses most parts of CO 2 . Therefore, there is no fear that NO x which is a harmful gas is discharged, and there is no need for separately providing facilities for separating and collecting CO 2 . Further, extra CO 2 can be collected in a highly-pure state straightaway, which is easily used for various uses other than power generation.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US13/944,201 2012-07-20 2013-07-17 Sealing device, axial turbine and power plant Abandoned US20140020403A1 (en)

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JP2012-161746 2012-07-20
JP2012161746A JP2014020509A (ja) 2012-07-20 2012-07-20 シール装置、軸流タービン、および発電プラント

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US20150184750A1 (en) * 2012-08-23 2015-07-02 Mitsubishi Hitachi Power Systems, Ltd. Rotary machine
EP3228826A1 (de) * 2016-04-05 2017-10-11 MTU Aero Engines GmbH Dichtungssegmentanordnung mit steckverbindung, zugehörige gasturbine und herstellungsverfahren
EP3228827A1 (de) * 2016-04-05 2017-10-11 MTU Aero Engines GmbH Dichtungsträger für eine turbomaschine, zugehörige gasturbine und herstellungsverfahren
US9816388B1 (en) * 2016-09-22 2017-11-14 General Electric Company Seal in a gas turbine engine having a shim base and a honeycomb structure with a number of cavities formed therein
US20170370476A1 (en) * 2015-01-27 2017-12-28 Mitsubishi Hitachi Power Systems, Ltd. Rotary machine
US10066750B2 (en) * 2012-11-13 2018-09-04 Mitsubishi Heavy Industries Compressor Corporation Rotary machine
US20180320596A1 (en) * 2017-05-02 2018-11-08 Rolls-Royce Corporation Shaft seal crack obviation
US10385714B2 (en) * 2013-12-03 2019-08-20 Mitsubishi Hitachi Power Systems, Ltd. Seal structure and rotary machine
US10711628B2 (en) 2016-10-24 2020-07-14 MTU Aero Engines AG Sealing fin having an axially asymmetric tip portion
US20220259982A1 (en) * 2019-07-23 2022-08-18 Mitsubishi Power, Ltd Seal member and rotary machine
US20220275731A1 (en) * 2019-08-06 2022-09-01 Safran Aircraft Engines Abradable member for a turbine of a turbomachine, comprising a wear face provided with guide vanes
US20230175411A1 (en) * 2021-12-07 2023-06-08 Mitsubishi Heavy Industries, Ltd. Rotary machine

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US20150184750A1 (en) * 2012-08-23 2015-07-02 Mitsubishi Hitachi Power Systems, Ltd. Rotary machine
US9879786B2 (en) * 2012-08-23 2018-01-30 Mitsubishi Hitachi Power Systems, Ltd. Rotary machine
US10066750B2 (en) * 2012-11-13 2018-09-04 Mitsubishi Heavy Industries Compressor Corporation Rotary machine
US10385714B2 (en) * 2013-12-03 2019-08-20 Mitsubishi Hitachi Power Systems, Ltd. Seal structure and rotary machine
US20170370476A1 (en) * 2015-01-27 2017-12-28 Mitsubishi Hitachi Power Systems, Ltd. Rotary machine
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EP3228826A1 (de) * 2016-04-05 2017-10-11 MTU Aero Engines GmbH Dichtungssegmentanordnung mit steckverbindung, zugehörige gasturbine und herstellungsverfahren
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US20230175411A1 (en) * 2021-12-07 2023-06-08 Mitsubishi Heavy Industries, Ltd. Rotary machine

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CN103573298A (zh) 2014-02-12
CN103573298B (zh) 2016-03-16
EP2687683A2 (en) 2014-01-22
JP2014020509A (ja) 2014-02-03

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