WO2016103340A1 - ノズル構造、及び回転機械 - Google Patents
ノズル構造、及び回転機械 Download PDFInfo
- Publication number
- WO2016103340A1 WO2016103340A1 PCT/JP2014/084037 JP2014084037W WO2016103340A1 WO 2016103340 A1 WO2016103340 A1 WO 2016103340A1 JP 2014084037 W JP2014084037 W JP 2014084037W WO 2016103340 A1 WO2016103340 A1 WO 2016103340A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- nozzle
- rotor
- axis
- peripheral surface
- nozzle structure
- Prior art date
Links
Images
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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/047—Nozzle boxes
-
- 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
- F01D11/02—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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/246—Fastening of diaphragms or stator-rings
-
- 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
- F16J15/445—Free-space packings with means for adjusting the clearance
-
- 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
- F16J15/4472—Labyrinth packings with axial path
-
- 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
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/31—Application in turbines in steam turbines
-
- 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
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
-
- 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
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
- F05D2240/128—Nozzles
-
- 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
-
- 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
- F05D2240/57—Leaf seals
Definitions
- the present invention relates to a nozzle structure and a rotating machine equipped with the nozzle structure.
- a moving blade row provided on the outer peripheral surface of a rotor and a stationary blade row provided on an inner peripheral surface of a casing are alternately arranged along the axis of the turbine. Yes. Thereby, a steam flow path is formed inside the casing.
- Patent Document 1 An apparatus described in Patent Document 1 is known as an example of such a technique.
- a steam turbine described in Patent Document 1 includes a diaphragm inner ring provided on an inner peripheral side of a stationary blade cascade via an inner peripheral side configuration part, and a labyrinth packing fixedly supported on the inner peripheral side of the diaphragm inner ring. I have. This rabin rinse packing covers the outer peripheral surface of the rotor with a gap.
- This invention is made
- a nozzle structure according to an aspect of the present invention is a nozzle structure provided in a gap between a rotor that rotates about an axis and a passenger compartment that surrounds the rotor from an outer peripheral side, and the inner peripheral surface of the passenger compartment
- An outer ring formed in an annular shape along the circumferential direction around the axis, and an annular nozzle fixed on the radially inner side of the outer ring and having a wing portion for guiding the fluid flow direction in the axial direction.
- a labyrinth seal that is supported on the radially inner side of the nozzle so as to face the outer peripheral surface of the rotor and seals between an inner peripheral surface of the nozzle and an outer peripheral surface of the rotor; and the nozzle and the labyrinth seal; And an elastic member that urges the labyrinth seal toward the radially inner side.
- the nozzle structure according to one aspect of the present invention includes a strength compensation portion that is provided between the casing and the outer ring and compensates for the strength of the nozzle in the radial direction, and the outer ring has the strength described above. You may fix to the said compartment via a supplement part.
- the outer ring is attached to the vehicle compartment via the strength compensation portion.
- the strength compensation portion it is possible to sufficiently ensure the strength of the nozzle in the radial direction.
- the outer ring is fixed to the inner peripheral surface of the vehicle compartment via the strength compensation portion, and the strength compensation portion is formed in an annular shape around the axis. It may be an inner casing.
- the nozzle includes a plurality of nozzle divided bodies arranged in the circumferential direction, and a weld bead that connects a pair of adjacent nozzle divided bodies in the circumferential direction. You may have.
- nozzle division bodies are connected to the circumferential direction by welding (welding bead). Thereby, nozzle division bodies can be firmly fixed to each other.
- the labyrinth seal may have both end surfaces in the axial direction perpendicular to the axial line.
- both end faces in the axial direction of the labyrinth seal are perpendicular to the axial line. Therefore, the possibility of impairing the sealing performance of the labyrinth seal can be reduced.
- a rotating machine includes the nozzle structure according to any one of the above aspects.
- Such a configuration can provide a steam turbine having sufficient sealing performance and durability.
- nozzle structure and rotating machine of the present invention it is possible to provide a nozzle structure having sufficient sealing performance and durability, and a steam turbine including the nozzle structure.
- a steam turbine 100 (rotary machine 100) of this embodiment is an external combustion engine that extracts steam energy as rotational power, and is used for a generator in a power plant.
- the steam turbine 100 is provided inside the passenger compartment 1, the rotor 2 extending along the axis O so as to penetrate the passenger compartment 1, and rotating around the axis O, and the inside of the passenger compartment 1.
- the nozzle structure 3 (the stationary blade), the moving blade row 4 provided on the rotor 2, and the bearing portion 5 that supports the rotor 2 so as to be rotatable around the axis.
- a plurality of blade rows 4 are arranged on the outer peripheral surface of the rotor 2 along the direction of the axis O.
- the moving blade row 4 located on the upstream side has a smaller radial dimension of each moving blade. In other words, the radial dimension of each moving blade increases as the moving blade row 4 is located on the downstream side.
- the region where the rotor blade row 4 is provided in the rotor 2 is covered by the casing 1 from the outer peripheral side.
- a nozzle structure 3 is provided inside the casing 1 in a region corresponding to the rotor blade row 4 on the rotor 2.
- a certain gap is formed between the nozzle structure 3 and the moving blade row 4 to form a steam flow path 6.
- An external steam supply source (not shown) is connected to the steam channel 6 via a steam inlet 7 provided on the upstream side of the passenger compartment 1.
- the high-temperature and high-pressure steam that has flowed in from the steam inlet 7 collides with the rotor blade row 4 while flowing through the steam flow path 6, rotates the rotor 2, and then passes through the exhaust port 8 provided on the downstream side to the outside. It is exhausted toward.
- the bearing portion 5 includes journal bearings 5 ⁇ / b> A provided at both ends of the rotor 2 and a thrust bearing 5 ⁇ / b> B provided at one end of the rotor 2.
- the nozzle structure 3 is alternately arranged with the above-described moving blade row 4 along the axis O direction inside the passenger compartment 1.
- the nozzle structure 3 includes an inner casing 10 provided on the inner peripheral surface of the passenger compartment 1, and a plurality (2 of the inner casing 10 arranged along the axis O direction on the inner peripheral surface of the inner casing 10. ) Nozzle unit 30.
- the inner casing 10 is an annular member extending along the inner peripheral surface of the passenger compartment 1.
- a nozzle unit 30 to be described later is arranged on the inner side in the radial direction of the inner casing 10. That is, the strength of the nozzle unit 30 is compensated by being supported from the radially outer side by the inner casing 10 as the strength compensation portion S.
- the radially outer surface of the inner casing 10 is formed to protrude toward the radially outer side, thereby forming the attachment portion 11.
- the mounting portion 11 is fitted to an annular groove 12 provided along the circumferential direction on the inner peripheral surface of the passenger compartment 1.
- the concave groove 12 has a concave groove bottom surface 12A that forms a radially outer surface, and a pair of concave groove side surfaces 12B that extend radially inward from the concave groove bottom surface 12A.
- the separation dimension between the pair of concave groove side surfaces 12B is substantially the same as the dimension of the mounting portion 11 in the direction of the axis O.
- a gap is formed between the groove bottom surface 12 ⁇ / b> A and the end surface on the radially outer side of the attachment portion 11. As described above, the fitting of the attachment portion 11 in the concave groove 12 restricts the movement of the inner casing 10 in the direction of the axis O.
- the inner peripheral surface of the inner casing 10 is provided with two outer ring support grooves 12C arranged along the axis O direction.
- the outer ring support groove 12 ⁇ / b> C is an annular square groove provided so as to be recessed from the inner peripheral surface of the inner casing 10 toward the radially outer side.
- the outer ring support grooves 12C are separated from each other along the direction of the axis O.
- One outer ring 20 to be described later is provided in each of the two outer ring support grooves 12C.
- the surface facing the upstream side of the steam channel 6 is an upstream end surface 10A, and the surface facing the downstream side is a downstream end surface 10B. Both the upstream end face 10A and the downstream end face 10B extend in a direction that is substantially perpendicular to the direction of the axis O.
- Each nozzle unit 30 includes an outer ring 20, a nozzle 31 provided on the radially inner side of the outer ring 20, and a labyrinth seal 50 provided on the radially inner side of the nozzle 31.
- the two nozzle units 30 arranged along the direction of the axis O have the same shape as each other, except that some dimensions are different. Accordingly, in the following description, one nozzle unit 30 will be representatively described.
- the outer ring 20 is an annular member that is supported inside the passenger compartment 1 by the outer ring support groove 12C.
- the outer ring 20 includes an outer ring main body 21 that supports a nozzle 31 described later, and a moving blade seal ring 22 that is fixed to the outer ring main body 21 in the direction of the axis O. .
- the outer ring main body 21 has a smaller radial dimension than the inner casing 10 described above. Both surfaces of the outer ring main body 21 in the direction of the axis O extend in a direction generally perpendicular to the direction of the axis O. Further, a nozzle support groove 21 ⁇ / b> A is formed on a surface on the radially inner side of the outer ring main body 21.
- the nozzle support groove 21 ⁇ / b> A is an annular square groove formed so as to be recessed from the inner peripheral surface of the outer ring main body 21 toward the radially outer side. A part of a later-described nozzle 31 is fitted in the nozzle support groove 21A.
- the rotor blade seal ring 22 is fixed to the downstream surface of the outer ring main body 21 described above.
- the radially inner side on the downstream side of the moving blade seal ring 22 is formed as a protruding portion 33 by being formed to protrude toward the downstream side.
- a plurality of flow guides 24 arranged at intervals from each other along the axis O direction are provided on the inner peripheral surface of the rotor blade seal ring 22.
- the flow guide 24 is a member that guides the direction in which steam flows by facing the radially outer end of the rotor blade.
- Each flow guide 24 is formed by a thin plate extending radially inward from the inner peripheral surface of the bucket seal ring 22.
- These flow guides 24 are fixed to the inner peripheral surface of the moving blade seal ring 22 by pins 25.
- the outer ring main body 21 and the rotor blade seal ring 22 configured as described above may be fixed to each other by, for example, welding or the like between end faces facing each other along the axis O direction.
- the total dimension in the axis O direction of the outer ring main body 21 and the rotor blade seal ring 22 in a state of being fixed to each other is substantially the same as the dimension in the axis O direction of the outer ring support groove 12C described above.
- the outer ring 20 is supported inside the passenger compartment 1 by fitting into the outer ring support groove 12C.
- the nozzle 31 is provided on the annular nozzle ring portion 32 provided on the inner peripheral surface of the outer ring 20, the wing portion 34 provided on the inner peripheral surface of the nozzle ring portion 32, and the inner peripheral surface of the wing portion 34. And an inner ring 35.
- a nozzle mounting portion 23 is provided on the outer peripheral surface of the nozzle ring portion 32.
- the nozzle mounting portion 23 is formed so as to protrude outward in the radial direction from the outer peripheral surface of the nozzle ring portion 32.
- the dimension of the nozzle mounting portion 23 in the axis O direction is substantially the same as the dimension of the nozzle support groove 21A in the axis O direction.
- the nozzle attachment part 23 is fitted in the nozzle support groove 21 ⁇ / b> A, thereby supporting the nozzle 31.
- the nozzle ring portion 32 and the outer ring 20 are joined to each other by welding in a state where the nozzle mounting portion 23 is fitted in the nozzle support groove 21A.
- the outer ring 20 is joined by performing build-up welding (build-up weld M) on the radially inner portions on both sides in the axis O direction.
- the blade portion 34 is a member that extends radially inward from the inner peripheral surface of the nozzle ring portion 32 and has an airfoil cross section (not shown) as viewed from the radial direction.
- On the inner peripheral surface of the nozzle ring portion 32 a plurality of wing portions 34 are arranged in the circumferential direction at intervals. These blade portions 34 and the above-described moving blades (the moving blade row 4) are arranged so as to overlap each other when viewed in the radial direction.
- the rotor 2 After the flow direction of the steam, which is the working fluid of the steam turbine 100, is guided by the blade part 34, the rotor 2 is rotated about the axis O by colliding with the moving blade row 4.
- An inner ring 35 is provided on the radially inner edge of the wing part 34. Each end edge on the radially inner side of the plurality of wing portions 34 is supported by the inner ring 35.
- the inner ring 35 has a substantially C-shaped cross section viewed from the circumferential direction.
- the above-described wing portion 34 is fixed to the outer peripheral surface of the inner ring 35.
- a seal support groove 36 for supporting the labyrinth seal 50 is formed on the inner peripheral surface of the inner ring 35.
- the seal support groove 36 is a groove formed so as to be recessed from the inner peripheral surface of the inner ring 35 toward the radially outer side. That is, the seal support groove 36 opens toward the inside in the radial direction.
- a locking portion 37 is formed in the radially inner region so as to protrude so as to be close to each other in the axis O direction.
- a leaf spring accommodating groove 38 for accommodating a leaf spring 40 (described later) as the elastic member 40 is formed on the radially outer surface of the seal support groove 36.
- the dimension of the leaf spring accommodating groove 38 in the axis O direction is smaller than the dimension of the seal support groove 36 in the axis O direction.
- the labyrinth seal 50 is a seal member formed of, for example, an alloy containing copper.
- the labyrinth seal 50 according to the present embodiment includes a plate-like seal base 51 extending along the axis O direction, and a plurality of thin plate-like fins 52 extending radially inward from the seal base 51. Yes. Both end edges of the seal base 51 in the direction of the axis O engage with the locking portion 37 of the seal support groove 36 described above.
- Each fin 52 is formed so that the dimension in the direction of the axis O gradually decreases from the radially outer side toward the inner side. Further, the two fins 52 positioned on both sides in the direction of the axis O are respectively an upstream fin 52A positioned on the most upstream side and a downstream fin 52B positioned on the most downstream side. These upstream fins 52 ⁇ / b> A and downstream fins 52 ⁇ / b> B have shapes different from those of the other fins 52. That is, the end surface 521 facing the upstream side of the upstream fin 52A is formed to be perpendicular to the direction of the axis O.
- the end surface 522 facing the downstream side of the downstream fin 52B is formed to be perpendicular to the axis O direction. Note that the end surface 521 and the end surface 522 do not have to be completely perpendicular to the direction of the axis O, and they only need to intersect substantially at right angles.
- the labyrinth seal 50 is accommodated in the seal support groove 36 in the inner ring 35.
- the leaf spring 40 as the elastic member 40 is accommodated in the leaf spring accommodation groove 38. The leaf spring 40 is urged so as to press the radially outer surface of the seal base 51 of the labyrinth seal 50 toward the radially inner side.
- the elastic force toward the radially inner side is applied to the labyrinth seal 50 by the leaf spring 40 and is supported from the radially inner side by the locking portion 37 in the inner ring 35.
- the plurality of fins 52 are supported in the seal support groove 36 so as to be slightly spaced from the outer peripheral surface of the rotor 2 along the radial direction.
- the nozzle 31 configured as described above includes a plurality of nozzle division bodies 31D divided along the circumferential direction.
- the nozzle 31 is divided according to the number of wing parts 34. That is, the nozzle 31 having n wings 34 is divided into n nozzle division bodies 31D.
- the nozzle division bodies 31D adjacent to each other along the circumferential direction are joined to each other by welding. Specifically, as shown in FIG. 3, the end faces on both sides in the axis O direction of the inner ring 35 and the end faces on the downstream side of the nozzle ring portion 32 are brought into contact with each other to form a joint portion. By welding each of the joints, a weld bead W is formed at the joint.
- the steam supplied from the outside circulates in the steam flow path 6 so that the rotor 2 rotates.
- vibration of the rotor 2 may occur during the operation of the steam turbine 100.
- the rotor 2 moves slightly in the radial direction.
- the rotor 2 comes into contact with the labyrinth seal 50.
- the labyrinth seal 50 is fixed with respect to the inner ring 35, a high stress is applied to the labyrinth seal 50 and the rotor 2, which may cause damage.
- the labyrinth seal 50 is supported by the leaf spring 40 as the elastic member 40. Therefore, even if it is a case where the rotor 2 contacts the labyrinth seal 50, the stress produced between the rotor 2 can be relieve
- the inner ring 35 in the nozzle structure 3 is integrally formed as one member, which is advantageous in reducing the size of the steam turbine 100.
- the space for providing the elastic member 40 may be lost due to restrictions on the radial dimension of the nozzle structure 3.
- a space (plate spring accommodating groove 38) in which the elastic member 40 is provided can be provided without impairing the strength of the inner ring 35.
- the outer ring 20 can be accommodated through the strength compensating portion S even when the radial dimension of the nozzle structure 3 is reduced, for example, in order to reduce the size of the device. By being attached to 1, sufficient strength of the nozzle 31 in the radial direction can be secured.
- the nozzle 31 is divided
- both end faces of the labyrinth seal 50 in the direction of the axis O can be reduced even when, for example, the radial dimension of the nozzle structure 3 is reduced in reducing the size of the apparatus. Since it is perpendicular to the axis O, the labyrinth seal 50 can be easily attached to the seal housing groove. Thereby, possibility of impairing the sealing performance of the labyrinth seal 50 can be reduced.
- the nozzle structure 3 according to the present invention can be applied to a rotary machine such as the steam turbine 100.
- Nozzle 31D ... Nozzle segment 32 ... Nozzle ring part 33 ... Projection part 34 ... Wing part 35 ... Inner ring 36 ... Seal support groove 37 ... Locking part 38 ... Plate Spring accommodating groove 40 ... elastic member 40 ... leaf spring 50 ... labyrinth seal 51 ... seal base 5A ... ja Null bearing 5B ... Thrust bearing 52 ... fin 52A ... upstream fins 52B ... downstream fin M ... the overlay weld part S ... strength interpolator W ... weld bead
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
Abstract
Description
本発明の一の態様に係るノズル構造は、軸線回りに回転するロータと、前記ロータを外周側から囲む車室との間の間隙に設けられるノズル構造であって、前記車室の内周面に固定され、前記軸線を中心として周方向に沿って環状に形成された外輪と、前記外輪の径方向内側に固定され、軸線方向における流体の流通方向を案内する翼部を有する環状のノズルと、前記ノズルの径方向内側に前記ロータの外周面に対向するように支持され、前記ノズルの内周面と前記ロータの外周面との間をシールするラビリンスシールと、前記ノズルと前記ラビリンスシールとの間に設けられて、前記ラビリンスシールを径方向内側に向かって付勢する弾性部材と、を備える。
このように取付部11が凹溝12に嵌合することによって、インナーケーシング10の軸線O方向への移動が規制されている。
Claims (6)
- 軸線回りに回転するロータと、前記ロータを外周側から囲む車室との間の間隙に設けられるノズル構造であって、
前記車室の内周面に固定され、前記軸線を中心として環状に形成された外輪と、
前記外輪の径方向内側に固定され、軸線方向における流体の流通方向を案内する翼部を有する環状のノズルと、
前記ノズルの径方向内側に前記ロータの外周面に対向するように支持され、前記ノズルの内周面と前記ロータの外周面との間をシールするラビリンスシールと、
前記ノズルと前記ラビリンスシールとの間に設けられて、前記ラビリンスシールを径方向内側に向かって付勢する弾性部材と、
を備えるノズル構造。 - 前記車室と、前記外輪との間に設けられて、径方向における前記ノズルの強度を補填する強度補填部を備え、
前記外輪は、前記強度補填部を介して前記車室に固定される請求項1に記載のノズル構造。 - 前記外輪は、前記強度補填部を介して前記車室の内周面に固定され、
前記強度補填部は、前記軸線を中心として環状に形成されたインナーケーシングである請求項2に記載のノズル構造。 - 前記ノズルは、
周方向に配列された複数のノズル分割体と、
隣接する一対の前記ノズル分割体同士を周方向に接続する溶接ビードと、
を有する請求項2又は3に記載のノズル構造。 - 前記ラビリンスシールは、前記軸線方向における両端面が、該軸線に対して垂直をなしている請求項1から4のいずれか一項に記載のノズル構造。
- 請求項1から5のいずれか一項に記載の前記ノズル構造を備えた回転機械。
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
PCT/JP2014/084037 WO2016103340A1 (ja) | 2014-12-24 | 2014-12-24 | ノズル構造、及び回転機械 |
US15/539,336 US20170350264A1 (en) | 2014-12-24 | 2014-12-24 | Nozzle structure and rotary machine |
JP2016565637A JPWO2016103340A1 (ja) | 2014-12-24 | 2014-12-24 | ノズル構造、及び回転機械 |
EP14908948.4A EP3232010B1 (en) | 2014-12-24 | 2014-12-24 | Nozzle structure and rotary machine |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
PCT/JP2014/084037 WO2016103340A1 (ja) | 2014-12-24 | 2014-12-24 | ノズル構造、及び回転機械 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2016103340A1 true WO2016103340A1 (ja) | 2016-06-30 |
Family
ID=56149441
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/JP2014/084037 WO2016103340A1 (ja) | 2014-12-24 | 2014-12-24 | ノズル構造、及び回転機械 |
Country Status (4)
Country | Link |
---|---|
US (1) | US20170350264A1 (ja) |
EP (1) | EP3232010B1 (ja) |
JP (1) | JPWO2016103340A1 (ja) |
WO (1) | WO2016103340A1 (ja) |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP7051656B2 (ja) * | 2018-09-28 | 2022-04-11 | 三菱重工コンプレッサ株式会社 | タービンステータ、蒸気タービン、及び仕切板 |
JP7190370B2 (ja) | 2019-02-28 | 2022-12-15 | 三菱重工業株式会社 | 軸流タービン |
US11933180B2 (en) * | 2021-12-16 | 2024-03-19 | Pratt & Whitney Canada Corp. | Labyrinth seal |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS5918207A (ja) * | 1982-07-21 | 1984-01-30 | Toshiba Corp | 蒸気タ−ビンの隙間調整装置 |
JPS61138803A (ja) * | 1984-12-12 | 1986-06-26 | Toshiba Corp | 蒸気タ−ビン軸封装置 |
JPS6372371U (ja) * | 1986-10-31 | 1988-05-14 | ||
JPH01119802U (ja) * | 1988-02-09 | 1989-08-14 |
Family Cites Families (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS5794439A (en) * | 1980-12-04 | 1982-06-11 | Ookawa Seira Kogyo Kk | Screw rolling planetary die |
JPS608402A (ja) * | 1983-06-29 | 1985-01-17 | Toshiba Corp | 蒸気タ−ビンの動翼先端部冷却装置 |
JPH0676763B2 (ja) * | 1987-06-29 | 1994-09-28 | 三菱重工業株式会社 | タ−ビン静翼の栓溶接方法 |
US5603510A (en) * | 1991-06-13 | 1997-02-18 | Sanders; William P. | Variable clearance seal assembly |
JP3620167B2 (ja) * | 1996-07-23 | 2005-02-16 | 富士電機システムズ株式会社 | 再熱式軸流蒸気タービン |
JPH1119802A (ja) * | 1997-06-28 | 1999-01-26 | Hitachi Seiki Co Ltd | 主軸移動型立形工作機械におけるワーク載置装置 |
JP2002285802A (ja) * | 2001-03-26 | 2002-10-03 | Toshiba Corp | 回転機械のラビリンスシール装置 |
JP2003214113A (ja) * | 2002-01-28 | 2003-07-30 | Toshiba Corp | 地熱タービン |
EP1473442B1 (en) * | 2003-04-30 | 2014-04-23 | Kabushiki Kaisha Toshiba | Steam turbine, steam turbine plant and method of operating a steam turbine in a steam turbine plant |
GB0324076D0 (en) * | 2003-10-14 | 2003-11-19 | Alstom Switzerland Ltd | Sealing arrangement using flexible seals |
US7344357B2 (en) * | 2005-09-02 | 2008-03-18 | General Electric Company | Methods and apparatus for assembling a rotary machine |
AU2006252172A1 (en) * | 2006-01-04 | 2007-07-19 | General Electric Company | Rotary machines and methods of assembling |
US7748945B2 (en) * | 2006-12-07 | 2010-07-06 | Jerry Wayne Johnson | Floating sealing ring |
US8591180B2 (en) * | 2010-10-12 | 2013-11-26 | General Electric Company | Steam turbine nozzle assembly having flush apertures |
JP2014152696A (ja) * | 2013-02-08 | 2014-08-25 | Hitachi Ltd | ラビリンスシール装置、およびそれを用いたターボ機械 |
-
2014
- 2014-12-24 WO PCT/JP2014/084037 patent/WO2016103340A1/ja active Application Filing
- 2014-12-24 JP JP2016565637A patent/JPWO2016103340A1/ja active Pending
- 2014-12-24 EP EP14908948.4A patent/EP3232010B1/en active Active
- 2014-12-24 US US15/539,336 patent/US20170350264A1/en not_active Abandoned
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS5918207A (ja) * | 1982-07-21 | 1984-01-30 | Toshiba Corp | 蒸気タ−ビンの隙間調整装置 |
JPS61138803A (ja) * | 1984-12-12 | 1986-06-26 | Toshiba Corp | 蒸気タ−ビン軸封装置 |
JPS6372371U (ja) * | 1986-10-31 | 1988-05-14 | ||
JPH01119802U (ja) * | 1988-02-09 | 1989-08-14 |
Non-Patent Citations (1)
Title |
---|
See also references of EP3232010A4 * |
Also Published As
Publication number | Publication date |
---|---|
US20170350264A1 (en) | 2017-12-07 |
EP3232010A1 (en) | 2017-10-18 |
EP3232010A4 (en) | 2018-01-10 |
EP3232010B1 (en) | 2019-06-19 |
JPWO2016103340A1 (ja) | 2017-11-02 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
JP4740730B2 (ja) | タービン | |
US9103223B2 (en) | Shaft sealing device and rotating machine comprising same | |
US20130149125A1 (en) | Turbine and method for manufacturing turbine | |
JP6423144B2 (ja) | 一体形カバーバケット組立体 | |
JP6012505B2 (ja) | 軸シール装置及び回転機械 | |
EP3159582B1 (en) | Shaft seal device and rotary machine | |
RU2647170C2 (ru) | Лопаточный аппарат и соответствующий способ изготовления лопаточного аппарата | |
CN108603603B (zh) | 密封装置及旋转机械 | |
WO2016103340A1 (ja) | ノズル構造、及び回転機械 | |
JP2016084861A (ja) | ラビリンスシール装置および軸流型ターボ機械 | |
US9103224B2 (en) | Compliant plate seal for use with rotating machines and methods of assembling a rotating machine | |
WO2012090793A1 (ja) | 軸シール装置及びこれを備える回転機械 | |
US8517688B2 (en) | Rotor assembly for use in turbine engines and methods for assembling same | |
US9574453B2 (en) | Steam turbine and methods of assembling the same | |
KR102256876B1 (ko) | 축방향 지향 밀봉 시스템 | |
CN105324554B (zh) | 轴流膨胀机 | |
WO2019106024A1 (en) | Film-riding sealing system | |
US11066946B2 (en) | Axial turbomachinery | |
JP6842963B2 (ja) | 軸シール装置、回転機械 | |
CN109073088B (zh) | 密封段及旋转机械 | |
US10060534B2 (en) | Sealing structure for turbine | |
US20170159494A1 (en) | Steam turbine nozzle segment with complete sidewall and integrated hook design | |
WO2023214507A1 (ja) | タービン翼環組立体及びタービンの組立て方法 | |
US20120076642A1 (en) | Sealing assembly for use in turbomachines and method of assembling same |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
121 | Ep: the epo has been informed by wipo that ep was designated in this application |
Ref document number: 14908948 Country of ref document: EP Kind code of ref document: A1 |
|
WWE | Wipo information: entry into national phase |
Ref document number: 15539336 Country of ref document: US |
|
ENP | Entry into the national phase |
Ref document number: 2016565637 Country of ref document: JP Kind code of ref document: A |
|
NENP | Non-entry into the national phase |
Ref country code: DE |
|
REEP | Request for entry into the european phase |
Ref document number: 2014908948 Country of ref document: EP |