EP2360349A2 - Aube statorique de turbine à vapeur ayant une interface arquée - Google Patents

Aube statorique de turbine à vapeur ayant une interface arquée Download PDF

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Publication number
EP2360349A2
EP2360349A2 EP11154455A EP11154455A EP2360349A2 EP 2360349 A2 EP2360349 A2 EP 2360349A2 EP 11154455 A EP11154455 A EP 11154455A EP 11154455 A EP11154455 A EP 11154455A EP 2360349 A2 EP2360349 A2 EP 2360349A2
Authority
EP
European Patent Office
Prior art keywords
sidewall
steam turbine
arcuate
static nozzle
airfoil
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.)
Withdrawn
Application number
EP11154455A
Other languages
German (de)
English (en)
Inventor
Steven Sebastian Burdgick
Jason Paul Mortzheim
Dominick Joseph Werther
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of EP2360349A2 publication Critical patent/EP2360349A2/fr
Withdrawn legal-status Critical Current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
    • 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
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • F01D5/14—Form or construction
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • 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
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • F01D9/044—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators permanently, e.g. by welding, brazing, casting or the like
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • 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
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F05D2230/237—Brazing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/23—Three-dimensional prismatic
    • F05D2250/232—Three-dimensional prismatic conical
    • 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
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • F05D2250/711—Shape curved convex
    • 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
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • F05D2250/712—Shape curved concave

Definitions

  • the subject matter disclosed herein relates to a steam turbine nozzle assembly, or diaphragm stage. Specifically, the subject matter disclosed herein relates to a steam turbine nozzle assembly including a plurality of nozzle segments with arcuate or "conical” (e.g., arced concave, arced convex) interfaces.
  • arcuate or "conical” e.g., arced concave, arced convex
  • Steam turbines include static nozzle (or "airfoil”) segments that direct flow of a working fluid into turbine buckets connected to a rotating rotor.
  • a complete assembly of nozzle segments is commonly referred to as a diaphragm stage of the steam turbine.
  • One method of constructing the diaphragm stage is to weld (or alternatively, braze) a plurality of single airfoils with integrated sidewalls ("static nozzle blades", or “singlets”) to inner and outer rings.
  • static nozzle blades or “singlets”
  • interfaces include an axial leading edge section (or “pressure-side” section) oriented parallel to the steam turbine's axis, and an angled trailing edge section (or “suction-side” section). While the current singlet design including angled interface sections allows for a tight fit between individual segments, the angled interfaces make removal and repair of individual segments nearly impossible.
  • a steam turbine static nozzle blade includes: an airfoil; an inner sidewall integral with a first side of the airfoil; and an outer sidewall integral with a second side of the airfoil; the inner sidewall and the outer sidewall each including: a pressure side having an arcuate concave surface extending substantially an entire length of the sidewall; and a suction side having an arcuate convex surface extending substantially the entire length of the sidewall.
  • a first aspect of the invention includes a steam turbine static nozzle blade comprising: an airfoil; an inner sidewall integral with a first side of the airfoil; and an outer sidewall integral with a second side of the airfoil; the inner sidewall and the outer sidewall each including: a pressure side having an arcuate concave surface extending substantially an entire length of the sidewall; and a suction side having an arcuate convex surface extending substantially the entire length of the sidewall.
  • a second aspect of the invention includes a steam turbine diaphragm assembly comprising: an outer diaphragm ring; an inner diaphragm ring; and an annulus of static nozzle blades between the inner diaphragm ring and the outer diaphragm ring, each static nozzle blade comprising: an airfoil; an inner sidewall integral with a first side of the airfoil; and an outer sidewall integral with a second side of the airfoil; the inner sidewall and the outer sidewall each including: a pressure side having an arcuate concave surface extending substantially an entire length of the sidewall; and a suction side having an arcuate convex surface extending substantially the entire length of the sidewall; wherein at least one of the static nozzle blades is demountably attached to a second one of the static nozzle blades.
  • a third aspect of the invention includes a steam turbine diaphragm assembly comprising: an outer diaphragm ring; an inner diaphragm ring; and an annulus of static nozzle blades between the inner diaphragm ring and the outer diaphragm ring, each static nozzle blade comprising: an airfoil; an inner sidewall integral with a first side of the airfoil; and an outer sidewall integral with a second side of the airfoil; the inner sidewall and the outer sidewall each including: a pressure side having an arcuate concave surface extending substantially an entire length of the sidewall; and a suction side having an arcuate convex surface extending substantially the entire length of the sidewall, wherein at least one of the static nozzle blades is demountably attached to a second one of the static nozzle blades in an axial direction; and a plurality of removable weld joints, each removable weld joint substantially removably affixing one of the static nozzle blades to one
  • aspects of the invention provide for a steam turbine nozzle segment having a conical interface.
  • aspects of the invention provide for a steam turbine nozzle assembly including a plurality of nozzle segments with arcuate or "conical” (e.g., arced concave, arced convex) interfaces. These arced interfaces may allow for removal and/or repair of individual nozzle segments while substantially maintaining the structural integrity of the nozzle assembly.
  • FIGS. 1-2 show a nozzle assembly 100 for a steam turbine (not shown).
  • FIG. 1 shows a plan view of nozzle assembly 100
  • FIG. 2 shows a three-dimensional schematic of nozzle assembly 100.
  • Nozzle assembly 100 includes a static nozzle blade 10 including at least one airfoil 12 having an inner sidewall 14 and an outer sidewall 16.
  • Nozzle assembly 100 further includes an inner ring 18 and an outer ring 20.
  • Inner and outer refer to a radial position relative to a rotor (not shown) to which an inner end of airfoil 12 is coupled via inner ring 18.
  • Inner ring 18 and inner sidewall 14 are coupled together at an interface 80, which is understood to refer to the entire area where the rings and sidewall are adjacent and coupled.
  • Inner ring 18 and inner sidewall 14 are welded (or alternatively, brazed) together at several points at interface 80 ( FIG. 1 ).
  • brazing may be performed as an alternative to welding.
  • welding and brazing may be used to join metals together.
  • welding may be performed by melting and fusing metals together, usually by adding a filler material.
  • Brazing by contrast, usually does not involve melting the base metals being joined, and is usually performed at lower temperatures than welding. While metal joints are described herein as “weld joints”, it is understood that these metal joints may alternatively be described as "braze joints.”
  • Interfaces 80 between rings 18, 20 and sidewalls 14, 16 may each include a mechanical radial stop 19 which maintains airfoil 12 in the correct radial position during welding and prevents weld shrinkage.
  • Interfaces 80 each may further include a mechanical axial stop 17 which maintains airfoil 12 in the correct axial position and controls the weld length depth.
  • the nozzle assembly 100 of FIG. 2 is shown, further including a plurality of static nozzle blades 10 arranged in a portion of a diaphragm assembly (full assembly omitted for clarity).
  • sidewalls 14, 16 of static nozzle blades 10 may include angled interfaces 34 (e.g., a "dogleg" interface including two surfaces oriented at obtuse angles). These angled interfaces 34 may allow for a plurality of static nozzle blades to be arranged substantially flush with one another in nozzle assembly 100.
  • the plurality of static nozzle blades 10 are held within inner 18 and outer sidewalls 20 via the plurality of welds 90.
  • Static nozzle blade 110 may include an airfoil 112, an inner sidewall 114, and an outer sidewall 116.
  • inner sidewall 114 may be integral with a first side of the airfoil 112 (e.g., via machining from a forging or block, welding, casting, brazing, etc.)
  • outer sidewall 116 may be integral with a second side of the airfoil 112 (e.g., via machining from a forging or block, welding, casting, brazing, etc.).
  • the inner sidewall 114 and the outer sidewall 116 may each include a pressure side 124 and a suction side 126.
  • pressure side and suction side correspond to the pressure side and suction side of airfoil 112, respectively.
  • the pressure side of airfoil 112 is the high-pressure side designed to guide the flow of a working fluid through the static nozzle blade 110.
  • the suction side of airfoil 112 is the lower-pressure side substantially opposing the pressure side.
  • Each pressure side 124 may have an arcuate concave surface 134
  • each suction side 126 may have an arcuate convex surface 136.
  • the arcuate concave surface 134 may extend substantially an entire length L of the sidewall 114, 116, respectively, and the arcuate convex surface 136 may extend substantially the entire length L of the sidewall 114, 116, respectively.
  • the arcuate concave surface 134 of the inner sidewall 114 has a substantially equal arc radius to the arcuate convex surface 136 of the inner sidewall 114.
  • the arcuate concave surface 134 of the outer sidewall 116 and the arcuate convex surface 136 of the outer sidewall 116 may have a substantially equal arc radius.
  • the arcuate concave surfaces 134 of the inner sidewall 114 and outer sidewall 116, respectively may have substantially equal arc lengths as the arcuate convex surfaces 136 of the inner sidewall 114 and outer sidewall 116, respectively.
  • the arcuate concave surface 134 of the inner sidewall 114 and the arcuate concave surface 134 of the outer sidewall 116 complement the arcuate convex surface 136 of the inner sidewall 114 and the arcuate convex surface 136 of the outer sidewall 116, respectively. That is, in an arrangement including more than one steam turbine static nozzle blade 110 ( FIGS. 5-7 ), the arcuate convex surface 136 of an inner sidewall 114 of a first steam turbine static nozzle blade 110 complements the arcuate concave surface 134 of an inner sidewall 114 on a second similar steam turbine static nozzle blade 110.
  • arcuate convex surface 136 of an outer sidewall 116 of a first steam turbine static nozzle blade 110 complements the arcuate concave surface 134 of an outer sidewall 116 on a second similar steam turbine static nozzle blade 110.
  • the term “complement(s)” refers to a relationship between surfaces in which portions of those surfaces may be arranged substantially flush with one another.
  • pressure-side (arcuate concave) surfaces and suction-side (arcuate convex) surfaces may be arranged in a steam turbine diaphragm assembly ( FIG.
  • each of the respective (inner, outer) arcuate concave surfaces of a first steam turbine static nozzle blade 110 are substantially flush with the respective (inner, outer) arcuate convex surfaces of a second steam turbine static nozzle blade 110.
  • the relationship between pressure-side surfaces and suction-side surfaces is further explained with reference to FIGS. 5-7 .
  • FIGS. 5 and 6 arrangements including a plurality of substantially similar steam turbine static nozzle blades 110 are shown.
  • steam turbine static nozzle blades 110 may be arranged such that their complementary surfaces (arcuate concave surfaces 134 and arcuate convex surfaces 136, respectively) are substantially flush with one another. This may allow for, among other things, efficient feeding of steam across airfoils 112 and mechanical stability.
  • FIG. 5 shows an arrangement including the plurality of steam turbine static nozzle blades 110 of FIG. 5 , along with additional substantially similar blades, forming part of a steam turbine diaphragm assembly (diaphragm rings omitted). As described with respect to FIG. 5 , and shown more clearly in FIG.
  • part of a steam turbine diaphragm assembly may be formed by arranging complementary conical surfaces of steam turbine static nozzle blades 110 flush with one another.
  • the plurality of steam turbine static nozzle blades 110 may be demountably attached to one another in an axial direction (denoted by "A"). This demountable attachment may allow for axial removal of one or more steam turbine static nozzle blades 110 from the assembly without substantially disturbing the structural integrity (e.g., weld joints 190) of the remainder of the assembly.
  • portion of a steam turbine diaphragm assembly 200 is shown according to an embodiment.
  • Portion of steam turbine diaphragm assembly 200 may include a plurality of steam turbine static nozzle blades 110 arranged with substantially flush complementary surfaces as described with reference to FIGS. 5-6 .
  • portion of steam turbine diaphragm assembly 200 may include an inner diaphragm ring 118 and an outer diaphragm ring 120, which may be substantially similar to those inner and outer rings (18 and 20) shown and described with reference to FIGS. 1-3 .
  • the plurality of steam turbine static nozzle blades 110 may form an annulus between the inner diaphragm ring 118 and the outer diaphragm ring 120.
  • plurality of steam turbine static nozzle blades 110 may be demountably attached to one another.
  • the plurality of steam turbine static nozzle blades 110 may be substantially removably affixed to at least one of the inner diaphragm ring 118 and outer diaphragm ring 120 via the plurality of removable weld joints 190.
  • a steam turbine static nozzle blade 110 may be removed from the steam turbine diaphragm assembly 200 without removing weld joints 190 of one or more adjacent steam turbine static nozzle blades 110.
  • each steam turbine static nozzle blade 110 that is not welded to one of the inner diaphragm ring 118 and outer diaphragm ring 120 may be removed or inserted between two fixed (e.g., welded) steam turbine static nozzle blades 110 in the axial direction (A).
  • each steam turbine static nozzle blade 110 may be demountably attached to an adjacent steam turbine static nozzle blade 110 in an axial direction.
  • each steam turbine static nozzle blade 110 is substantially removably affixed to at least one of the inner diaphragm ring 118 and outer diaphragm ring 120 by only the plurality of removable weld joints 190 (or alternatively, braze joints).
  • the steam turbine static nozzle blades 110 including conical (arcuate concave, arcuate convex) interfaces as described herein may allow for removal of individual blades 110 from an assembly (e.g., steam turbine diaphragm assembly 200) by removing (e.g., by grinding, machining and/or heating) only those removable weld joints 190 (or braze joints) associated with the individual blade being removed. This may allow for, among other things, faster and more efficient repair, replacement, and/or enhancement of individual steam turbine static nozzle blades 110.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP11154455A 2010-02-16 2011-02-15 Aube statorique de turbine à vapeur ayant une interface arquée Withdrawn EP2360349A2 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US12/706,198 US20110200430A1 (en) 2010-02-16 2010-02-16 Steam turbine nozzle segment having arcuate interface

Publications (1)

Publication Number Publication Date
EP2360349A2 true EP2360349A2 (fr) 2011-08-24

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ID=43639928

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11154455A Withdrawn EP2360349A2 (fr) 2010-02-16 2011-02-15 Aube statorique de turbine à vapeur ayant une interface arquée

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US (1) US20110200430A1 (fr)
EP (1) EP2360349A2 (fr)
JP (1) JP5926888B2 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2690255A3 (fr) * 2012-07-23 2017-07-19 General Electric Company Segment statorique pour système de turbine
FR3082878A1 (fr) * 2018-06-20 2019-12-27 Safran Aircraft Engines Aube de turbomachine

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8118550B2 (en) * 2009-03-11 2012-02-21 General Electric Company Turbine singlet nozzle assembly with radial stop and narrow groove
US8770931B2 (en) * 2011-05-26 2014-07-08 United Technologies Corporation Hybrid Ceramic Matrix Composite vane structures for a gas turbine engine
ITCO20110060A1 (it) * 2011-12-12 2013-06-13 Nuovo Pignone Spa Turbina a vapore, paletta e metodo
US9506362B2 (en) * 2013-11-20 2016-11-29 General Electric Company Steam turbine nozzle segment having transitional interface, and nozzle assembly and steam turbine including such nozzle segment
US9756401B2 (en) * 2015-04-07 2017-09-05 Sony Corporation Processing and providing an image in which a plurality of symbols are encoded
USD777212S1 (en) * 2015-06-20 2017-01-24 General Electric Company Nozzle ring
US10927688B2 (en) 2015-06-29 2021-02-23 General Electric Company Steam turbine nozzle segment for partial arc application, related assembly and steam turbine
US10436047B2 (en) 2015-08-18 2019-10-08 General Electric Company Method for repair of a diaphragm of a rotary machine
KR101796590B1 (ko) * 2017-04-27 2017-12-01 진영티비엑스(주) 터빈용 노즐 플레이트 어셈블리
US11346246B2 (en) * 2017-12-01 2022-05-31 Siemens Energy, Inc. Brazed in heat transfer feature for cooled turbine components
KR102235024B1 (ko) 2019-07-01 2021-04-01 두산중공업 주식회사 터빈 베인 및 이를 포함하는 가스 터빈
CN110953022B (zh) * 2019-11-25 2022-05-10 东方电气集团东方汽轮机有限公司 一种汽轮机喷嘴组及六弧段全周进汽式喷嘴结构

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5966948A (ja) * 1982-10-09 1984-04-16 Ebara Corp 軸流タービンのノズルリングの製造に用いられる金型
JPS6022002A (ja) * 1983-07-18 1985-02-04 Hitachi Ltd タ−ボ機械の翼構造
US4639189A (en) * 1984-02-27 1987-01-27 Rockwell International Corporation Hollow, thermally-conditioned, turbine stator nozzle
GB9823840D0 (en) * 1998-10-30 1998-12-23 Rolls Royce Plc Bladed ducting for turbomachinery
US6290459B1 (en) * 1999-11-01 2001-09-18 General Electric Company Stationary flowpath components for gas turbine engines
US6553665B2 (en) * 2000-03-08 2003-04-29 General Electric Company Stator vane assembly for a turbine and method for forming the assembly
US6371725B1 (en) * 2000-06-30 2002-04-16 General Electric Company Conforming platform guide vane
EP1329593B1 (fr) * 2002-01-17 2005-03-23 Siemens Aktiengesellschaft Aube de turbine ayant une plateforme supportant les gaz chaux et une plateforme supportant les charges mécaniques
GB0319002D0 (en) * 2003-05-13 2003-09-17 Alstom Switzerland Ltd Improvements in or relating to steam turbines
JP2005146896A (ja) * 2003-11-11 2005-06-09 Toshiba Corp 蒸気タービンのノズルダイアフラムおよび蒸気タービンプラント
GB0505978D0 (en) * 2005-03-24 2005-04-27 Alstom Technology Ltd Interlocking turbine blades
US7427187B2 (en) * 2006-01-13 2008-09-23 General Electric Company Welded nozzle assembly for a steam turbine and methods of assembly
JP2008144687A (ja) * 2006-12-12 2008-06-26 Mitsubishi Heavy Ind Ltd タービン静翼構造
GB0700633D0 (en) * 2007-01-12 2007-02-21 Alstom Technology Ltd Turbomachine
US8292580B2 (en) * 2008-09-18 2012-10-23 Siemens Energy, Inc. CMC vane assembly apparatus and method

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2690255A3 (fr) * 2012-07-23 2017-07-19 General Electric Company Segment statorique pour système de turbine
FR3082878A1 (fr) * 2018-06-20 2019-12-27 Safran Aircraft Engines Aube de turbomachine

Also Published As

Publication number Publication date
JP2011169318A (ja) 2011-09-01
JP5926888B2 (ja) 2016-05-25
US20110200430A1 (en) 2011-08-18
RU2011105278A (ru) 2012-08-20

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