EP2813736A1 - Dichtungsstruktur und drehmaschine damit - Google Patents

Dichtungsstruktur und drehmaschine damit Download PDF

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Publication number
EP2813736A1
EP2813736A1 EP13746796.5A EP13746796A EP2813736A1 EP 2813736 A1 EP2813736 A1 EP 2813736A1 EP 13746796 A EP13746796 A EP 13746796A EP 2813736 A1 EP2813736 A1 EP 2813736A1
Authority
EP
European Patent Office
Prior art keywords
shroud
concave portion
seal structure
circumferential surface
abradable coating
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.)
Granted
Application number
EP13746796.5A
Other languages
English (en)
French (fr)
Other versions
EP2813736A4 (de
EP2813736B1 (de
Inventor
Tomoyuki Onishi
Shin Nishimoto
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.)
Mitsubishi Power Ltd
Original Assignee
Mitsubishi Hitachi Power Systems Ltd
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 Mitsubishi Hitachi Power Systems Ltd filed Critical Mitsubishi Hitachi Power Systems Ltd
Publication of EP2813736A1 publication Critical patent/EP2813736A1/de
Publication of EP2813736A4 publication Critical patent/EP2813736A4/de
Application granted granted Critical
Publication of EP2813736B1 publication Critical patent/EP2813736B1/de
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • 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
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/90—Coating; Surface treatment
    • 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
    • F05D2250/60—Structure; Surface texture
    • F05D2250/61—Structure; Surface texture corrugated
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/611—Coating

Definitions

  • the present invention relates to a seal structure and a rotating machine equipped therewith.
  • an amount of leakage of fluid is reduced to the utmost by minimizing a clearance between a rotor and a stationary side member such as a stator blade around the rotor, which is important from the viewpoint of improving the performance of the rotating machine.
  • a seal structure equipped with fins, which protrudes from an outer circumferential surface of a rotor in a circumferential direction, and a seal member, in which an abradable material having high cuttability is thermally sprayed on places of a stationary side member which are opposite to the fins, is employed (see Patent Document 1 below).
  • the abradable material is cut out. Thereby, the generation of heat can be reduced at a contact place so as to maintain the performance of the rotating machine.
  • the seal member is an annular member extending in the circumferential direction, and is formed with an abradable coating on an inner circumferential surface thereof which is formed by thermally spraying the abradable material.
  • Patent Document 1 Japanese Unexamined Patent Application, First Publication No. 2009-174655
  • the abradable material should bear the shear force.
  • the abradable material since the abradable material has high cuttability, the abradable material that is just thermally sprayed directly on the stator blade is damaged by the shear force, and furthermore there is a possibility of peeling off of the abradable material from the stator blade. As such, it is not possible to simply use only thermal spraying.
  • the present invention has been made in consideration of these circumstances, and an object of the present invention is to provide a seal structure capable of preventing an abradable material from peeling off even when damage is caused to the abradable material.
  • a seal structure which includes a fin configured to protrude from an outer circumferential surface of a rotor in a circumferential direction, and a stator blade having an abradable coating formed on an inner circumferential surface of an inner shroud so as to face the fins.
  • the inner circumferential surface of the inner shroud is formed in an uneven shape, and the abradable coating is formed along the uneven shape.
  • the abradable coating is formed along the uneven shape, and an abradable material enters and is hardened and deposited in the uneven shape portion.
  • the bonding area can be increased, and the abradable coating can be strongly bonded. Accordingly, even when the abradable coating is damaged, the abradable coating can be prevented from being separated from the stator blade because the abradable coating is strongly bonded.
  • the uneven shape may be configured by a concave portion formed from one of the inner circumferential surface of the inner shroud and an outer circumferential surface of the abradable coating toward an interior thereof.
  • the uneven shape is formed by, for instance, the concave portion formed from the inner circumferential surface of the inner shroud toward the interior thereof. Accordingly, since the abradable coating enters the concave portion, the bonding force can be reliably improved. Thus, even when the abradable coating is damaged, the abradable coating can be prevented from being separated from the stator blade.
  • the concave portion may be formed so as to extend in the circumferential direction.
  • the bonding force of the abradable coating can be improved throughout the circumferential direction. Accordingly, even when the abradable coating is damaged, the abradable coating can be prevented from being separated from the stator blade.
  • the concave portion may be formed so as to extend in an axial direction of the rotor.
  • the bonding force of the abradable coating can be improved throughout the axial direction. Accordingly, even when the abradable coating is damaged, the abradable coating can be prevented from being separated from the stator blade.
  • the concave portion may be formed on a boundary line between the inner shrouds adjacent in the circumferential direction.
  • the concave portion is capable of being formed on the boundary line between the neighboring inner shrouds, and the abradable coating is capable of entering the concave portion. Accordingly, when a shear force occurs between the inner shrouds adjacent to the boundary line, the shear force can be reduced according to the amount of the abradable coating that enters the concave portion. As such, the deformation caused by the distortion of the stator blades can be prevented.
  • the one of the inner circumferential surface of the inner shroud and the outer circumferential surface of the abradable coating may be formed with a second concave portion so as to be opposite to the concave portion formed in the other of the inner circumferential surface of the inner shroud and the outer circumferential surface of the abradable coating, and the seal structure may include a pin member inserted between the concave portion and the second concave portion.
  • the concave portion may be formed so that a width thereof in a cross section perpendicular to an extending direction thereof gradually widens from the one of the inner circumferential surface of the inner shroud and the outer circumferential surface of the abradable coating toward a bottom thereof.
  • the bonding area of the abradable coating can be increased. Further, when force is applied to the abradable coating in a separating direction, a resistance force is applied to an inclined surface of the abradable coating which corresponds to a surface formed toward the bottom of the concave portion. As such, the abradable coating can be more strongly bonded. Accordingly, even when the abradable coating is damaged, the abradable coating can be prevented from being separated from the stator blade because the abradable coating is strongly bonded.
  • the concave portion may be formed in an arcuate shape in which a cross section perpendicular to an extending direction thereof swells from the one of the inner circumferential surface of the inner shroud and the outer circumferential surface of the abradable coating.
  • the abradable coating enters and is hardened and deposited in the uneven shape portion. Thereby, the abradable coating can be strongly bonded. For this reason, even when the abradable coating is damaged, the abradable coating can be prevented from being separated from the stator blade.
  • a gas turbine (rotating machine) 1 is equipped with a compressor 2 producing compressed air, a combustor 3 mixing fuel with the compressed air produced by the compressor 2 and burning the mixture to produce a combustion gas M, and a turbine 4 rotatably driven using the combustion gas M produced by the combustor 3 as a working fluid.
  • a rotor 5 is inserted into the compressor 2 and the turbine 4.
  • the compressor 2 includes a compressor casing 2a into which the rotor 5 is inserted, compressor rotor blades 2b rotatable along with the rotor 5, and compressor stator blades 2c fixed to the compressor casing 2a.
  • the plurality of compressor rotor blades 2b and the plurality of compressor stator blades 2c are radially installed in a circumferential direction R.
  • the compressor rotor blades 2b and the compressor stator blades 2c are alternately installed in a shaft direction (axial direction) P, and are each installed in multiple stages, each of which is made up of the plurality of blades installed in the circumferential direction R.
  • the suctioned air is flown between the compressor stator blades 2c, and is repetitively compressed by rotation of the compressor rotor blades 2b downstream therefrom. Thereby, the compressed air is produced.
  • the turbine 4 includes a turbine casing 10 into which the rotor 5 is inserted, turbine rotor blades 20 rotatable along with the rotor 5, and turbine stator blades (stator blades) 30 fixed to the turbine casing 10.
  • the plurality of turbine rotor blades 20 and the plurality of turbine stator blades 30 extend in a radial direction Q, and are radially installed in the circumferential direction R.
  • the turbine rotor blades 20 and the turbine stator blades 30 are alternately installed in the shaft direction P, and are each installed in multiple stages, each of which is made up of the plurality of blades installed in the circumferential direction R.
  • the combustion gas M which is the working fluid introduced from the combustor 3
  • the turbine stator blades 30 are flown between the turbine stator blades 30, and repetitively rotates the turbine rotor blades 20 downstream therefrom.
  • the rotor 5 to which the turbine rotor blades 20 are fixed is torqued and rotated.
  • seal structures 7 for preventing the combustion gas M from leaking from a high pressure side to a low pressure side are installed in the shaft direction P.
  • the seal structures 7 will be described in detail.
  • each seal structure 7 is equipped with a plurality of fins 40 protruding from an outer circumferential surface of the rotor 5, and the turbine stator blades 30.
  • the plurality of fins 40 protrude from the outer circumferential surface of the rotor 5 in the circumferential direction R, and are disposed at intervals in the shaft direction P. Further, each fin 40 is configured so that the outer circumferential surface of the rotor 5 is set as a proximal end 40a, and so that a distal end 40b is formed such that a width thereof narrows from the proximal end 40a toward the turbine stator blades 30. In this way, the plurality of fins 40, 40 ⁇ are configured so that the proximal ends 40a and the distal ends 40b of any fin 40 and the proximal ends 40a and the distal ends 40b of the neighboring fin 40 are alternately arranged in the shaft direction P.
  • the turbine stator blade 30 includes an inner shroud 50 installed on the side of the rotor 5, an abradable coating 60 formed on the inner shroud 50, a blade body 70 extending from the inner shroud 50 in a radial direction, and an outer shroud 80 installed on an end of the blade body 70.
  • the inner shroud 50 is called a Z-patterned shroud in which a Z pattern is made when viewed from the inner side in the radial direction Q. Further, the inner shroud 50 has the Z pattern so as to suppress leakage of a high-temperature gas between itself and its neighboring inner shroud 50 and to prevent distortion of the blade body 70.
  • the inner shroud 50 is disposed in the shaft direction P, and is disposed in contact with the inner shroud 50 adjacent in the circumferential direction R.
  • an inner circumferential surface 50a of the inner shroud 50 is formed in an uneven shape.
  • a concave portion 51 is formed from the inner circumferential surface 50a of the inner shroud 50 toward an interior of the inner shroud 50, that is, toward an outer side in the radial direction Q, so that the concave portion 51 extends in the circumferential direction R.
  • the concave portion 51 has a shroud-side base 51a, a pair of shroud-side walls 51b formed from the inner circumferential surface 50a at approximately a right angle, and a shroud-side bottom 51c connecting the pair of shroud-side walls 51b and is formed at approximately a right angle with respect to the shroud-side walls 51b.
  • the abradable coating 60 is formed on the inner circumferential surface 50a of the inner shroud 50 so as to be opposite to the fins 40 (see FIG. 2 ) in such a way that, in the present embodiment, an abradable material is thermally sprayed.
  • the abradable coating 60 is formed along the uneven shape.
  • the abradable coating 60 has a convex portion 61 formed from the shroud-side base 51a to the shroud-side bottom 51c of the concave portion 51 by thermal spraying.
  • the convex portion 61 protrudes from an outer circumferential surface 60a of the abradable coating 60 toward the interior of the inner shroud 50, and has an abradable-side base 61a, a pair of abradable-side walls 61b formed from the outer circumferential surface 60a at approximately a right angle, and an abradable-side top 61c connecting the pair of abradable-side walls 61b.
  • shroud-side base 51a of the concave portion 51 and the abradable-side base 61a of the convex portion 61 are bonded to each other.
  • the shroud-side walls 51b of the concave portion 51 and the abradable-side walls 61b of the convex portion 61 are bonded to each other.
  • the shroud-side bottom 51c of the concave portion 51 and the abradable-side top 61c of the convex portion 61 are bonded to each other.
  • the abradable material for example, a nickel-based alloy may be employed.
  • the blade body 70 is formed by a pressure side surface 71 constituting a pressure side and a suction side surface 72 constituting a suction side.
  • the pressure side surface 71 is curved so as to swell toward the suction side surface 72, and the suction side surface 72 is curved so as to swell toward the same side as the pressure side surface 71.
  • the outer shroud 80 is disposed in contact with the other outer shroud 80 adjacent in the shaft direction P and in the circumferential direction R.
  • the abradable material as the convex portion 61 enters and is hardened and deposited in the concave portion 51 formed in the inner shroud 50, a bonding area on which the inner shroud 50 and the abradable coating 60 are bonded is increased. Accordingly, as the bonding area increases, the inner shroud 50 and the abradable coating 60 are strongly bonded. Furthermore, since the concave portion 51 is formed so as to extend in the circumferential direction R, a bonding force between the inner shroud 50 and the abradable coating 60 can be improved throughout the circumferential direction R. Thus, for example, although the abradable coating 60 is damaged when the gas turbine 1 is operated, the abradable coating 60 can be prevented from being peeled off of the inner shroud 50.
  • the abradable material can be directly formed on the inner shroud 50. Accordingly, in comparison with a conventional structure in which the abradable material is thermally sprayed onto the seal member installed on the inner shroud 50, the distance between the rotor 5 and the turbine stator blades 30 can be reduced with the amount in which the seal member is not required. Thus, the installation of the turbine 4, and ultimately, of the entire gas turbine 1 can be made small.
  • FIG. 4 a gas turbine 201 according to a second embodiment of the present invention will be described using FIG. 4 .
  • the pair of shroud-side walls 51b of the concave portion 51 formed in the inner shroud 50 are formed at approximately a right angle with respect to the shroud-side base 51 a.
  • a shroud-side wall 251b is formed at approximately a right angle with respect to a shroud-side base 251a
  • a shroud-side wall 251d is formed at an acute angle with respect to the shroud-side base 251a.
  • a concave portion 251 of an inner shroud 250 is formed so that a width of a cross section thereof perpendicular to an extending direction (circumferential direction R) of the concave portion 251 widens from an inner circumferential surface 250a of the inner shroud 250 toward a shroud-side bottom 251c of the concave portion 251.
  • the shroud-side wall 251b is formed at approximately a right angle with respect to a shroud-side base 251a, whereas the shroud-side wall 251 d is formed farther from the opposite shroud-side wall 251b as it is closer to the shroud-side bottom 251c.
  • the width 261 f of the shroud-side bottom 251c of the concave portion 251 is wider than the width 261e of the shroud-side base 251a of the concave portion 251.
  • a convex portion 261 of an abradable coating 260 has a shape corresponding to the concave portion 251, and is configured so that an abradable-side wall 261d is formed farther from an abradable-side wall 261b as it is closer to an abradable-side top 261c.
  • the shroud-side wall 251d and the abradable-side wall 261d are formed at an angle, a bonding area on which the inner shroud 250 and the abradable coating 260 are bonded can be further increased. Further, when force is applied to the abradable coating 260 toward an inner side in a radial direction Q that is a separating direction, a resistant force is applied to the abradable-side wall 261 d toward an outer side in the radial direction Q so as to prevent the separation. Accordingly, since the inner shroud 250 and the abradable coating 260 can be more strongly bonded, even when the abradable coating 260 is damaged, the abradable coating 260 can be prevented from peeling off of the inner shroud 250.
  • FIG. 5 a gas turbine 301 according to a third embodiment of the present invention will be described using FIG. 5 .
  • the shroud-side wall 251b is formed at approximately a right angle with respect to the shroud-side base 251a, and the shroud-side wall 251 d is formed at an acute angle with respect to the shroud-side base 251 a.
  • a shroud-side wall 351b is formed at an acute angle with respect to a shroud-side base 351a along with a shroud-side wall 351d.
  • a concave portion 351 of an inner shroud 350 is formed so that a width of a cross section thereof perpendicular to an extending direction (circumferential direction R) of the concave portion 351 widens from an inner circumferential surface 350a of the inner shroud 350 toward a shroud-side bottom 351c of the concave portion351.
  • the shroud-side walls 351b and 351d are formed farther from each other as it is closer to the shroud-side bottom 351c.
  • the width 361f of the shroud-side bottom 351c of the concave portion 351 is wider than the width 361e of the shroud-side base 351a of the concave portion351.
  • a convex portion 361 of an abradable coating 360 has a shape corresponding to the concave portion 351, and abradable-side walls 361b and 361d are formed farther from each other as it is closer to an abradable-side top 361c.
  • the shroud-side walls 351b and 351d and the abradable-side walls 361b and 361d are formed at an angle, a bonding area on which the inner shroud 350 and the abradable coating 360 are bonded can be further increased. Further, when force is applied to the abradable coating 360 toward an inner side in a radial direction Q that is a separating direction, a resistant force is applied to the abradable-side walls 361b and 361d toward an outer side in the radial direction Q so as to prevent the separation simultaneously. Accordingly, since the inner shroud 350 and the abradable coating 360 can be even more strongly bonded, even when the abradable coating 360 is damaged, the abradable coating 360 can be prevented from peeling off of the inner shroud 350.
  • FIG. 6 a gas turbine 401 according to a fourth embodiment of the present invention will be described using FIG. 6 .
  • a concave portion 451 in a seal structure 407 of the present embodiment is formed so that a cross section perpendicular to an extending direction (circumferential direction R) of the concave portion 451 has an arcuate shape so as to swell from an inner circumferential surface 450a of an inner shroud 450.
  • the concave portion 451 of the inner shroud 450 has a semi-circular shape in which it swells from the inner circumferential surface 450a toward an interior of the inner shroud 450.
  • a convex portion 461 of an abradable coating 460 has a shape corresponding to the concave portion 451, and has a semi-circular shape in which it swells outward from an outer circumferential surface 460a.
  • FIG. 7 a gas turbine 501 according to a fifth embodiment of the present invention will be described using FIG. 7 .
  • the concave portion 51 is formed from the side of the inner circumferential surface 50a of the inner shroud 50 toward the interior of the inner shroud 50.
  • a concave portion 561 is formed from an outer circumferential surface 560a of an abradable coating 560 toward an interior of the abradable coating 560.
  • the concave portion 561 includes an abradable-side base 561a, a pair of abradable-side walls 561b formed from the outer circumferential surface 560a at approximately a right angle, and an abradable-side bottom 561c connecting the pair of abradable-side walls 561b and formed at approximately a right angle to the abradable-side walls 561b.
  • a convex portion 551 has a shape corresponding to the concave portion 561, protrudes from an inner circumferential surface 550a of an inner shroud 550 toward the interior of the abradable coating 560, and includes an inner-shroud base 551a, a pair of shroud-side walls 551b formed from the inner circumferential surface 550a at approximately a right angle, and a shroud-side top 551c connecting the pair of shroud-side walls 551b.
  • any one of the inner shroud 550 and the abradable coating 560 may be selectively provided with a concave portion and the other may be provided with a convex portion, a degree of freedom of design is widened.
  • FIG. 8 a gas turbine 601 according to a sixth embodiment of the present invention will be described using FIG. 8 .
  • the concave portion 51 is formed so as to extend in the circumferential direction R.
  • a concave portion 651 is formed so as to extend in the shaft direction P.
  • the plurality of concave portions 651 are located in the radial direction Q inside respective boundary lines 654 between inner shrouds 650, 650 ⁇ ⁇ ⁇ adjacent in the circumferential direction R, follow the shaft direction P, and are formed at intervals in the circumferential direction R.
  • an abradable coating 660 enters the concave portions 651 to be formed as convex portions 661.
  • each concave portions 651 is formed so as to extend in the shaft direction P, a bonding force between the inner shroud 650 and the abradable coating 660 can be improved throughout the shaft direction P.
  • shear forces between the inner shrouds 650, 650 ⁇ ⁇ ⁇ occur.
  • the shear force can be reduced according to the amount of the abradable coating 660 which forms the convex portions 661 that enters the concave portions 651. Accordingly, deformation caused by distortion of the turbine stator blades 630 can be prevented, and stability of the gas turbine 601 itself can be improved.
  • FIG. 9 a gas turbine 701 according to a seventh embodiment of the present invention will be described using FIG. 9 .
  • the concave portions 651 are formed in the radial direction Q inside the boundary lines 654 between the inner shrouds 650, 650 ⁇ ⁇ ⁇ adjacent in the circumferential direction R.
  • concave portions 751 are formed within dimensions of the shaft direction P of respective inner shrouds 750.
  • the plurality of concave portions 751 are located approximately in the middle of the dimensions of the shaft direction P of the inner shrouds 750, follow the shaft direction P, and are formed at intervals in the circumferential direction R.
  • FIGS. 10 and 11 a gas turbine 801 according to an eighth embodiment of the present invention will be described using FIGS. 10 and 11 .
  • FIG. 10 is a cross-sectional view taken along line Y-Y of FIG. 1 in a seal structure 807 according to the present embodiment
  • FIG. 11 is a cross-sectional view in which portions of inner shrouds 850 of the seal structure 807 are cut out.
  • each concave portion 651 is configured only by being merely formed from the inner circumferential surfaces 650a of the inner shrouds 650 toward the interiors of the inner shrouds 650.
  • each concave portion is made up of a concave portion 851 formed from an inner circumferential surface 850a of one of the inner shrouds 850 toward an interior of the inner shroud 850 and a second concave portion 862 facing the concave portion 851 and formed from an outer circumferential surface 860a of an abradable coating 860 toward an interior of the abradable coating 860.
  • a pin member 890 is inserted between the concave portion 851 and the second concave portion 862.
  • the plurality of concave portions 851 are formed in the radial direction Q inside boundary lines 854 between the inner shrouds 850, 850 ⁇ ⁇ ⁇ adjacent in the circumferential direction R, and from the inner circumferential surfaces 850a of the inner shrouds 850 toward the interiors of the inner shrouds 850 at intervals in the circumferential direction R. Further, as shown in FIG. 11 , the concave portions 851 are formed at two spots for each inner shroud 850 and are spaced apart from each other in the shaft direction P.
  • This numerical value is an example, and the number of spots is not limited to this numerical value, and three or more spots may be used.
  • the plurality of second concave portions 862 are formed in the radial direction Q inside boundary lines 854 between the inner shrouds 850 and 850 adjacent in the circumferential direction R, and from the outer circumferential surface 860a of the abradable coating 860 toward the interior of the abradable coating 860 at intervals in the circumferential direction R. Further, as shown in FIG. 11 , the second concave portions 862 are formed at two spots for each inner shroud 850 and are spaced apart from each other in the shaft direction P.
  • the pin member 890 is a rod-like member, and is configured so that one end 890a thereof is disposed at a shroud-side bottom 851c of the concave portion851 and so that the other end 890b thereof is disposed at an abradable-side bottom 861c of the second concave portion 862.
  • the pin members 890 are inserted into the concave portions 851 of the inner shroud 850, and an abradable material is thermally sprayed to fix the pin members 890 in the concave portions 851 and to form the abradable coating 860.
  • the pin member 890 can strongly couple the neighboring inner shrouds 850, 850 ⁇ ⁇ ⁇ in the circumferential direction R, and reduce displacement in the shaft direction P.
  • the abradable material when the abradable material is thermally sprayed, since the side of the other end 890b of the pin member 890 protrudes, the abradable material can be deposited well to form the abradable coating 860. Accordingly, the inner shrouds 850 and the abradable coating 860 can be strongly bonded via the pin members 890.
  • the gas turbine has been described.
  • the present invention may be also applied to other rotating machines such as a steam turbine.
  • the abradable coating enters and is hardened and deposited in the uneven shape portions. Thereby, the abradable coating can be strongly bonded. For this reason, even when the abradable coating is damaged, the abradable coating can be prevented from being separated from the stator blade.

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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)
EP13746796.5A 2012-02-06 2013-02-05 Dichtungsstruktur Not-in-force EP2813736B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2012023071A JP5308548B2 (ja) 2012-02-06 2012-02-06 シール構造及びこれを備える回転機械
PCT/JP2013/052564 WO2013118701A1 (ja) 2012-02-06 2013-02-05 シール構造及びこれを備える回転機械

Publications (3)

Publication Number Publication Date
EP2813736A1 true EP2813736A1 (de) 2014-12-17
EP2813736A4 EP2813736A4 (de) 2015-11-25
EP2813736B1 EP2813736B1 (de) 2016-11-30

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP13746796.5A Not-in-force EP2813736B1 (de) 2012-02-06 2013-02-05 Dichtungsstruktur

Country Status (7)

Country Link
US (1) US20130216362A1 (de)
EP (1) EP2813736B1 (de)
JP (1) JP5308548B2 (de)
KR (1) KR101600732B1 (de)
CN (1) CN103958949B (de)
IN (1) IN2014MN00911A (de)
WO (1) WO2013118701A1 (de)

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JPH08135403A (ja) * 1994-11-14 1996-05-28 Mitsubishi Heavy Ind Ltd ガスタービン静翼
JPH1018016A (ja) * 1996-07-08 1998-01-20 Suzuki Motor Corp 耐摩耗性部材及びその表面処理方法
JP3477347B2 (ja) * 1997-07-30 2003-12-10 三菱重工業株式会社 ガスタービン段間部シール装置
ATE420272T1 (de) * 1999-12-20 2009-01-15 Sulzer Metco Ag Profilierte, als anstreifschicht verwendete oberfläche in strömungsmaschinen
DE10334698A1 (de) * 2003-07-25 2005-02-10 Rolls-Royce Deutschland Ltd & Co Kg Deckbandsegment für eine Strömungsmaschine
JP2005214148A (ja) * 2004-01-30 2005-08-11 Ishikawajima Harima Heavy Ind Co Ltd エンジン部品及びコーティング方法
JP2006132328A (ja) * 2004-11-02 2006-05-25 Toshiba Corp 軸シール機構および回転機械
FR2895021B1 (fr) * 2005-12-16 2010-09-03 Snecma Systeme d'etancheite inter-etages dans une turbomachine
JP5101317B2 (ja) 2008-01-25 2012-12-19 三菱重工業株式会社 シール構造
JP5411569B2 (ja) * 2009-05-01 2014-02-12 株式会社日立製作所 シール構造とその制御方法
US8172519B2 (en) * 2009-05-06 2012-05-08 General Electric Company Abradable seals
EP2336572B1 (de) * 2009-12-14 2012-07-25 Techspace Aero S.A. Zweiteiliges Gehäuse für einen Stromdiffusor eines Axialkompressors

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KR101600732B1 (ko) 2016-03-07
JP2013160313A (ja) 2013-08-19
EP2813736A4 (de) 2015-11-25
JP5308548B2 (ja) 2013-10-09
EP2813736B1 (de) 2016-11-30
KR20140083048A (ko) 2014-07-03
US20130216362A1 (en) 2013-08-22
IN2014MN00911A (de) 2015-04-17
WO2013118701A1 (ja) 2013-08-15
CN103958949A (zh) 2014-07-30
CN103958949B (zh) 2016-03-16

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