WO2017150365A1 - シール構造及びターボ機械 - Google Patents

シール構造及びターボ機械 Download PDF

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Publication number
WO2017150365A1
WO2017150365A1 PCT/JP2017/007028 JP2017007028W WO2017150365A1 WO 2017150365 A1 WO2017150365 A1 WO 2017150365A1 JP 2017007028 W JP2017007028 W JP 2017007028W WO 2017150365 A1 WO2017150365 A1 WO 2017150365A1
Authority
WO
WIPO (PCT)
Prior art keywords
recess
stationary
seal
side recess
rotating
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.)
Ceased
Application number
PCT/JP2017/007028
Other languages
English (en)
French (fr)
Japanese (ja)
Inventor
松本　和幸
健一 藤川
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
Priority to KR1020187024427A priority Critical patent/KR102110066B1/ko
Priority to CN201780013860.0A priority patent/CN108699915B/zh
Priority to US16/079,242 priority patent/US10669876B2/en
Priority to DE112017001043.8T priority patent/DE112017001043T5/de
Publication of WO2017150365A1 publication Critical patent/WO2017150365A1/ja
Anticipated expiration legal-status Critical
Ceased 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
    • 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
    • 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
    • F01D11/005—Sealing means between non relatively rotating elements
    • 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
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/28—Arrangement of seals
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/44—Free-space packings
    • F16J15/447—Labyrinth packings
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • 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
    • F05D2240/00—Components
    • F05D2240/55—Seals

Definitions

  • the present invention relates to a seal structure suitable for suppressing unstable vibrations, a seal structure for suppressing leakage of a working fluid from between two relatively rotating structures, and a turbomachine using the seal structure.
  • a turbo machine such as a steam turbine, a gas turbine, and a turbo compressor
  • a working fluid such as steam leaks (leaks) from a gap formed between the stationary structure and the rotating structure
  • the leakage of the working fluid is caused in the turbine. It causes a loss of efficiency (leakage loss).
  • a sealing fin is formed in the gap to form a sealing structure (see, for example, Patent Document 1).
  • the seal excitation force acts on the rotating structure so as to promote the swinging of the rotating structure against minute vibrations of the rotating structure generated for some reason, and thus causes unstable vibration.
  • the seal excitation force will be further described.
  • the working fluid flowing in the seal portion flows not only in the axial (flow direction) velocity component but also in the circumferential velocity component.
  • the flow in the circumferential direction is referred to as “swirl flow”), and the seal excitation force is caused by this swirl flow.
  • Patent Document 2 As a technique for suppressing such unstable vibration of the turbine, there is a technique disclosed in Patent Document 2.
  • the technique disclosed in Patent Document 2 will be described.
  • the reference numerals used in Patent Document 2 are shown in parentheses.
  • a plurality of seal fins (42) are provided along the rotor axial direction (L) so as to face the shroud (12) provided on the top of the rotor blade (11).
  • the seal ring (41) to which these seal fins (42) are attached is provided with groove portions (43) having the same depth (D2) between the seal fins (42).
  • the depth (D2) of the groove (43) is set to such an extent that the strength for supporting the seal fin (42) is not lowered.
  • the space between the seal fins (42) can be made substantially larger than in the case of a conventional steam turbine seal structure without a groove, and steam whirl (unstable) (Vibration) can be suppressed (see paragraphs [0025] to [0028], FIG. 4).
  • the present invention has been made in view of the above-described problems, and an object thereof is to provide a seal structure and a turbo machine that can effectively suppress unstable vibration.
  • the seal structure of the present invention has a rotating structure that rotates in a predetermined direction around an axial center line, and is opposed in the radial direction with a gap formed on the outer peripheral side of the rotating structure.
  • the depth dimension is set to be smaller in the second stationary side recess arranged on the downstream side of the first stationary side recess in the flow direction than in the first stationary side recess on the side. It is said.
  • the stationary structure is a turbine casing, a plurality of the rotating structures are installed along the axial direction, and are tip shrouds attached to the tips of the moving blades, and the seal fins are the tip shrouds. It is preferable to arrange
  • three or more stationary recesses are provided along the flow direction, and the depth dimension is set to be smaller toward the downstream side in the flow direction.
  • a plurality of the seal fins are provided along the flow direction, and the first seal fin on the most upstream side in the flow direction and the second disposed on the immediately downstream side of the first seal fin in the flow direction. It is preferable that the first stationary side recess is provided between the seal fin and each other.
  • the depth dimension of the first stationary side recess is set to be larger than twice the pitch between the first seal fin and the second seal fin.
  • the pitch between the seal fins is preferably set to be the same.
  • At least one of the seal fins is provided at a predetermined distance in the axial direction from the adjacent stationary recess.
  • At least one of the first stationary side recess and the second stationary side recess is extended in the radial direction.
  • At least one of the stationary side recesses is provided with an axial recess extending in the axial direction.
  • the stationary side recess is provided between the seal fins, and is a dimension related to the axial direction, and a total dimension of the stationary side recess and the axial recess is the dimension of the seal fin. It is preferable that the pitch be set larger than the pitch between them.
  • a rotation-side recess is provided in the rotary structure so as to face the stationary-side recess, and the rotation-side recess is at least a first provided facing the first stationary-side recess. It is preferable that a rotation side recess or a second rotation side recess provided to face the second stationary side recess is provided.
  • the rotary structure is provided with the first rotation side recess and the second rotation side recess, and a distance between a bottom surface of the first stationary side recess and a bottom surface of the first rotation side recess.
  • the distance between the bottom surface of the second stationary side recess and the bottom surface of the second rotation side recess is set shorter.
  • a turbo machine has a rotating structure that rotates in a predetermined direction around an axial center line, and is opposed in the radial direction with a gap formed on the outer peripheral side of the rotating structure. And a sealing structure according to any one of (1) to (12).
  • the rotating structure includes a plurality of tip shrouds provided in the axial direction, and the stationary structure includes a turbine casing that surrounds the plurality of tip shrouds, of the plurality of tip shrouds, It is preferable that the turbine has the seal structure for at least one tip shroud.
  • the at least one tip shroud is a tip shroud disposed closest to the inlet of the working fluid.
  • the at least one tip shroud is a tip shroud disposed in the center in the axial direction.
  • the first stationary side recess is formed on the inner peripheral surface of the cavity of the stationary structure housing the rotating structure and the seal fin from the upstream side as a stationary side recess that alleviates the nonuniformity of the static pressure distribution.
  • the second stationary side recess are provided in this order, and the depth dimension of the second stationary side recess is set smaller than that of the first stationary side recess. Rather than having the same depth dimension in the first stationary side recess and the second stationary side recess, the depth dimension of the downstream second stationary side recess having a small non-uniformity is set to be small and stationary.
  • a reduction in the strength of the structure can be suppressed, and accordingly, the depth dimension of the first stationary recess on the upstream side having a large non-uniformity can be set large while ensuring the strength of the stationary structure. Therefore, according to the present invention, it is possible to effectively suppress unstable vibration while suppressing a decrease in strength of the stationary structure due to providing the recess.
  • FIG. 1 is a schematic longitudinal sectional view showing an overall configuration of a steam turbine according to each embodiment of the present invention.
  • FIG. 2 is a schematic view showing the configuration of the seal structure according to the first embodiment of the present invention, and is a cross-sectional view cut along the radial direction.
  • FIG. 3 is a schematic view showing the configuration of the seal structure according to the second embodiment of the present invention, and is a cross-sectional view cut along the radial direction.
  • FIG. 4 is a schematic view showing the configuration of the seal structure according to the third embodiment of the present invention, and is a cross-sectional view cut along the radial direction.
  • upstream and downstream mean upstream and downstream of the flow component of the leak steam SL in the axial direction A unless otherwise specified. That is, the left side in FIGS. 1 to 4 is the upstream side, and the right side is the downstream side.
  • the direction toward the rotor axial center line (hereinafter also referred to as “axial center line”) CL of the steam turbine is defined as the inner peripheral side or the inner side, and the opposite side, the direction away from the axial center line CL is described as the outer peripheral side or the outer side.
  • the term “circumferential direction” means the circumferential direction centered on the axial center line CL unless otherwise specified.
  • the steam turbine 1 of the present embodiment includes a turbine casing (stationary structure, hereinafter also referred to as “casing”) 10 and a generator (not shown) that is rotatably provided inside the casing 10.
  • the rotor shaft 30 is transmitted to a machine, the stationary blade 60 provided on the casing 10, the rotor blade 50 provided on the rotor shaft 30, and the rotor shaft 30 is rotatably supported around the axis line CL.
  • the bearing part 70 is provided.
  • the stationary blade 60 and the moving blade 50 are blades extending in the radial direction R of the rotor shaft 30. While the casing 10 is stationary, the rotor blade 50 rotates around the axis line CL. That is, the casing 10 and the moving blade 50 (including a chip shroud 4 described later) rotate relative to each other.
  • the casing 10 has an internal space hermetically sealed and a flow path for steam (fluid) S.
  • the steam S is introduced from a main inlet 21 formed in the casing 10 through a steam supply pipe 20 connected to a steam supply source (not shown) and discharged from a steam discharge pipe 22 connected to the downstream side of the steam turbine 1. Is done.
  • a ring-shaped partition plate outer ring 11 is firmly fixed to the inner wall surface of the casing 10.
  • the bearing unit 70 includes a journal bearing device 71 and a thrust bearing device 72, and rotatably supports the rotor shaft 30.
  • the stationary blades 60 extend from the casing 10 toward the inner peripheral side, and constitute a group of annular stationary blades arranged radially so as to surround the rotor shaft 30, and are respectively held by the partition plate outer ring 11 described above. ing.
  • a plurality of annular stator blade groups composed of a plurality of stator blades 60 are formed at intervals in the axial direction A of the rotor shaft 30 and convert the pressure energy of the steam S into velocity energy and are adjacent to the downstream side. It flows into the moving blade 50.
  • the rotor blades 50 are firmly attached to the disk 32 formed on the outer peripheral portion of the rotor shaft body 31 of the rotor shaft 30 and are arranged radially in the downstream side of each annular stator blade group to constitute the annular rotor blade group. is doing. These annular stator blade groups and annular rotor blade groups are grouped into one stage. The tip portions of the plurality of blades 50 constituting each blade group are connected by a ring-shaped tip shroud (rotary structure) 4.
  • a cavity 12 that is recessed from the inner peripheral surface of the partition plate outer ring 11 is formed between the plurality of partition plate outer rings 11.
  • the cavity 12 is an annular space centered on the axis CL, and has an inner peripheral surface (hereinafter also referred to as “cavity bottom surface”) 13 of the casing 10 as a bottom surface.
  • the cavity 12 houses the chip shroud 4, and the cavity bottom surface 13 is opposed to the chip shroud 4 in the radial direction R via the gap Gd.
  • leak steam a part of the steam S (for example, about several percent) steam flow (leak flow, hereinafter also referred to as “leak steam”) SL does not flow into the rotor blade 50 but leaks into the gap Gd. Since the energy of the leak steam SL is not converted into rotational energy, the leak steam SL causes a leak loss that reduces the efficiency of the steam turbine 1.
  • each gap Gd between the casing 10 and each chip shroud 4 is provided with a seal structure 2 as the first embodiment of the present invention.
  • each chip shroud 4 is provided with the seal structure 2 as the first embodiment of the present invention.
  • the tip shroud 4 has a ring shape as described above, and has a rectangular cross-sectional shape that is long in the axial direction A as shown in FIG.
  • the cavity bottom surface 13 is provided with seal fins 6A, 6B, 6C extending toward the inner periphery toward the chip shroud 4 (not shown in FIG. 1).
  • the pitches B1 and B2 refer to the distance between the center lines of the seal fins 6A, 6B, and 6C in the thickness direction (in other words, the axial direction A).
  • seal fins 6A, 6B, and 6C are referred to as seal fins 6. Note that the seal fins 6A, 6B, and 6C need not have the same shape, and may have different shapes.
  • the cavity bottom surface 13 includes a casing recess (hereinafter referred to as “recess” or “radial recess”) extending in the radial direction R toward the outer peripheral side between the seal fins 6A, 6B, 6C. 14A and 14B are formed.
  • the recesses 14A and 14B are not distinguished, they are referred to as the recesses 14.
  • the recess 14 is a ring-shaped recess formed over the entire circumference of the cavity bottom surface 13 with the axial center line CL as the center, and is a ring-shaped recess facing each other and having a width in the radial direction R.
  • the recess 14 is set shallower toward the downstream side, and the depth L2 of the downstream recess 14B is set smaller (shallow) than the depth L1 of the upstream recess 14A ( L2 ⁇ L1).
  • the cavity bottom surface 13 and the bottom surface 14c defining the recesses 14A and 14B are circumferential surfaces centered on the axis line CL, and the depths L1 and L2 of the recesses 14A and 14B are: This is the distance in the radial direction R between the cavity bottom surface 13 and the bottom surface 14c.
  • Each recess 14 is formed with a predetermined distance ⁇ B ( ⁇ B> 0) with respect to the adjacent seal fin 6 in the axial direction A.
  • the recesses 14 ⁇ / b> A and 14 ⁇ / b> B have a function as an absorber (hereinafter referred to as “absorber function”) that reduces non-uniformity (non-uniformity) of the static pressure distribution.
  • a recess 14A having a relatively large depth dimension and a large volume (relatively high absorber function) is provided on the upstream side where the nonuniformity of the static pressure distribution is relatively large.
  • a recess 14B having a relatively small depth dimension and a small volume (relatively low absorber function) is provided.
  • the absorber function can be improved, while the strength of the casing 10 is reduced.
  • the depth dimension L2 of the recess 14B is set to be small, thereby suppressing the strength of the casing 10 from being lowered more than necessary.
  • the depth dimension L1 of the recess 14A can be set large to improve the absorber function by the amount that the depth dimension L2 of the recess 14B is reduced. . Therefore, compared with the case where the depth dimensions L1 and L2 of the recesses 14A and 14B are set to the same dimension, it is possible to effectively suppress the unstable vibration of the turbine while suppressing the decrease in the strength of the casing 10.
  • the depth L1 of the recess 14A between the seal fin 6A and the seal fin 6B is set to be larger than twice the pitch B1 between the seal fin 6A and the seal fin 6B.
  • L1> B1 ⁇ 2 the static pressure distribution can be made uniform, and the unstable vibration of the turbine can be more effectively suppressed.
  • each recess 14 is formed with a predetermined distance ⁇ B with respect to the adjacent seal fin 6 in the axial direction A ( ⁇ B> 0).
  • the seal structure 2A of the second embodiment of the present invention extends in the axial direction A from the outer peripheral end to the downstream side in the radial recess 14A with respect to the seal structure 2 of the first embodiment shown in FIG.
  • the existing axial recess 14A ' is connected continuously, and the axial recess 14B' extending in the axial direction A from the outer peripheral end toward the downstream side is connected to the radial recess 14B.
  • the axial recesses 14A 'and 14B' are recesses that are open in the radial recesses 14A and 14B and are formed in a ring shape around the axial center line CL.
  • the axial recesses 14A ′ and 14B ′ are defined by an outer peripheral side bottom surface 14d, an inner peripheral side bottom surface 14f, and a side surface 14e.
  • the outer peripheral side bottom surface 14d and the inner peripheral side bottom surface 14f face each other and are ring-shaped surfaces each having a width in the axial direction A.
  • the outer peripheral side bottom surface 14d is formed flush with the bottom surface 14c of the radial recess 14.
  • the side surface 14e is a ring-shaped surface that connects the downstream edges of the bottom surfaces 14d and 14f and has a width in the radial direction R.
  • the radial recess 14A can be substantially enlarged.
  • the total axial dimension D1 of the radial recess 14A and the axial recess 14A ′. Is set larger than the pitch B1 between the fins 6A and 6B (D1> B1).
  • the axial recess 14B ′ the radial recess 14B can be substantially enlarged.
  • D2 is set larger than the pitch B2 between the fins 6B and 6C (D2> B2). Since other structures are the same as the seal structure 2 of the first embodiment, description thereof is omitted.
  • the nonuniformity (nonuniformity) of the static pressure distribution is alleviated. Since the volume of the recess to be increased can be increased, unstable vibration of the turbine can be more effectively suppressed than in the first embodiment.
  • the dimension in the axial direction A is set to the pitch B1 and B2 of the seal fins 6A, 6B and 6C.
  • the dimensions of the axial recesses A in the radial recesses 14A and 14B are set to be smaller than the pitches B1 and B2, although partially. Can also be long.
  • the downstream radial recess 14B is formed shallower than the upstream radial recess 14A, an empty space is formed on the downstream side of the outer periphery of the radial recess 14A. Using this empty space, the axial recess 14A ′ can be formed on the downstream side of the outer peripheral portion of the radial recess 14A, and the recess can be efficiently arranged.
  • the axial recesses 14A 'and 14B' are provided at the outer peripheral ends of the radial recesses 14A and 14B.
  • the axial recesses 14A 'and 14B' may be provided at the outer peripheral ends of the radial recesses 14A and 14B.
  • the axial recess 14 ⁇ / b> A ′ may be connected to an intermediate portion in the radial direction R of the radial recess 14 ⁇ / b> A.
  • the axial recesses 14A 'and 14B' are provided on the downstream side of the radial recesses 14A and 14B.
  • the axial recesses 14A 'and 14B' are provided in the radial recesses. It may be provided upstream of the locations 14A and 14B.
  • the seal structure 2B of the third embodiment of the present invention is a shroud recess (hereinafter also referred to as “recess”) 41A formed in the chip shroud 4 with respect to the seal structure 2 of the first embodiment shown in FIG. , 41B are added.
  • the shroud recess 41A first rotation side recess
  • the shroud recess 41B second rotation side recess
  • the recesses 41 ⁇ / b> A and 41 ⁇ / b> B are not distinguished, they are referred to as the recesses 41.
  • the recess 41 is a ring-shaped recess formed over the entire circumference of the outer peripheral surface 42 of the shroud 4 with the axial center line CL as the center.
  • the recess 41 is recessed from the outer peripheral surface of the chip shroud 4 to the inner peripheral side (that is, extends along the radial direction R), and is opposed to each other and has a ring-shaped side surface 41a having a width in the radial direction R. , 41b and a ring-shaped bottom surface 41c having a width in the axial direction A by connecting the inner peripheral edges of these side surfaces 41a, 41b.
  • the depth dimension L2 of the casing recess 14B disposed facing the shroud recess 41B is smaller than the depth dimension L1 of the casing recess 14A disposed facing the shroud recess 41A. Is set.
  • the depth dimension L2 ′ of the downstream shroud recess 41B is set smaller (shallow) than the depth dimension L1 ′ of the upstream shroud recess 41A (L2 ′ ⁇ L1 ′).
  • the height of the space 100A between the recesses 14A and 41A (that is, the distance between the “bottom surface 14c of the casing recess 14A” and the “bottom surface 41c of the shroud recess 41A”) H1 is greater than the recess 14B.
  • the height dimension of the space 100B (that is, the distance between the “bottom surface 14c of the casing recess 14B” and the “bottom surface 41c of the shroud recess 41B”) H2 is set to be smaller ( H1> H2).
  • the spaces 100A and 100B substantially expand the gap Gd between the cavity bottom surface 13 and the chip shroud 4 to alleviate the non-uniformity of the static pressure distribution.
  • the larger space 100A is provided on the upstream side with larger non-uniformity
  • the smaller space 100B is provided on the downstream side with relatively smaller non-uniformity.
  • the space 100A and the space 100B are not distinguished, they are referred to as the space 100.
  • the outer peripheral surface 42 of the chip shroud 4 and the bottom surface 41c that defines the recesses 41A and 41B are circumferential surfaces centering on the axial center line CL, respectively, and the depths L1 ′, S1 of the shroud recesses 41A and 41B are provided.
  • L2 ′ is the distance in the radial direction R between the outer peripheral surface 42 and the bottom surface 41c of the chip shroud 4.
  • the height dimension H1 is a distance in the radial direction R between the bottom surface 14c of the casing recess 14A and the bottom surface 41c of the shroud recess 41A
  • the height dimension H2 is the distance between the bottom surface 14c of the casing recess 14B and the bottom surface 14c.
  • the shroud recess 41 is provided in addition to the casing recess 14, and the space 100 formed between the recesses 14 and 41 is set to be smaller toward the downstream side. Therefore, the unstable vibration of the turbine can be suppressed while suppressing the decrease in the strength of the casing 10 more effectively than in the first embodiment.
  • the depth dimension L2 ′ of the shroud recess 41B is set smaller than the depth dimension L1 ′ of the shroud recess 41A, but it is smaller than the height dimension H1 of the upstream space 100A. If the height dimension H2 of the downstream space 100B is smaller, it is not necessary to set the depth dimension L2 ′ smaller than the depth dimension L1 ′.
  • the depth dimension L1 ′ and the depth dimension L2 ′ may be the same dimension.
  • the casing recess 14 and the shroud recess 41 arranged opposite to the casing recess 14 are set as one set, and two sets are provided for one chip shroud 4. Three or more sets may be provided for one chip shroud 4.
  • the height dimension H2 of the second space 100B from the upstream side may be the same as the height dimension of the third and subsequent spaces (between the recess 14 and the recess 41) from the upstream side.
  • an axial recess may be provided in at least one of the recess 14A and the recess 14B.
  • the seal structure of the present invention is applied to each chip shroud 4, but only the seal structure of the present invention is applied to some (at least one) chip shrouds 4. But you can.
  • the seal structure of the present invention is applied to some chip shrouds 4, the non-uniformity of static pressure is maximized, so that it is closest to the main flow inlet 21 that is the inlet of the steam S (in other words, the highest pressure)
  • the seal structure of the present invention it is preferable to apply the seal structure of the present invention to the tip shroud 4A (see FIG. 1).
  • the amplitude is maximized in the center in the axial direction A, so that the tip shroud 4B (see FIG. 1) in the center in the axial direction A
  • the tip shroud 4B in the center in the axial direction A
  • the seal structure of the present invention is applied to the tip shroud closest to, a synergistic effect is obtained.
  • the present invention can also be applied to a seal of a turbo machine other than the steam turbine, such as a gas turbine or a turbo compressor.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
PCT/JP2017/007028 2016-02-29 2017-02-24 シール構造及びターボ機械 Ceased WO2017150365A1 (ja)

Priority Applications (4)

Application Number Priority Date Filing Date Title
KR1020187024427A KR102110066B1 (ko) 2016-02-29 2017-02-24 시일 구조 및 터보 기계
CN201780013860.0A CN108699915B (zh) 2016-02-29 2017-02-24 密封构造及涡轮机械
US16/079,242 US10669876B2 (en) 2016-02-29 2017-02-24 Seal structure and turbomachine
DE112017001043.8T DE112017001043T5 (de) 2016-02-29 2017-02-24 Dichtstruktur und Strömungsmaschine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2016038047A JP6712873B2 (ja) 2016-02-29 2016-02-29 シール構造及びターボ機械
JP2016-038047 2016-02-29

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US10669876B2 (en) 2020-06-02
DE112017001043T5 (de) 2018-12-20
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CN108699915B (zh) 2021-01-15
CN108699915A (zh) 2018-10-23

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