EP1722070A2 - Méthode de fabrication de segments statoriques pour une turbine à vapeur - Google Patents

Méthode de fabrication de segments statoriques pour une turbine à vapeur Download PDF

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Publication number
EP1722070A2
EP1722070A2 EP06252184A EP06252184A EP1722070A2 EP 1722070 A2 EP1722070 A2 EP 1722070A2 EP 06252184 A EP06252184 A EP 06252184A EP 06252184 A EP06252184 A EP 06252184A EP 1722070 A2 EP1722070 A2 EP 1722070A2
Authority
EP
European Patent Office
Prior art keywords
segments
flat plate
plate stock
nozzle
airfoils
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Withdrawn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
EP06252184A
Other languages
German (de)
English (en)
Other versions
EP1722070A3 (fr
Inventor
David Orus Fitts
Sterling R. Hathaway
Larry Duclos
Robert James Bracken
Ronald W. Korzun
William Edward Adis
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 EP1722070A2 publication Critical patent/EP1722070A2/fr
Publication of EP1722070A3 publication Critical patent/EP1722070A3/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Withdrawn legal-status Critical Current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
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using 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
    • 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

Definitions

  • This invention relates to a method of producing steam turbine components and, specifically, dovetailed reaction nozzle segments.
  • a plurality of nozzles are manufactured by machining from a single piece of flat plate stock.
  • a single solid donut-shaped ring is cut from flat plate stock and then cut into two 180° segments.
  • the cut ends of the segments may then be configured for temporary attachment to a machining jig or the like, or the segments may be temporarily joined together (by, e.g., bolts) on a jig and subsequently machined to include integral shroud covers, airfoils and dovetails.
  • the two 180° segments are loaded into the nozzle carrier or casing dovetail in the usual manner.
  • four 90° segments may be cut from the solid ring and subsequently machined to each include 25% of the required nozzles.
  • arcuately shorter segments may be machined to include as few as two integral nozzle airfoils, thus still reducing the nozzle components by half.
  • the invention relates to a method of manufacturing reaction nozzles for a turbine comprising (a) providing a piece of flat plate stock of predetermined size and thickness; and (b) machining the piece of flat plate stock to form a unitary, arcuate reaction nozzle segment including at least two adjacent nozzle airfoils.
  • the invention in another aspect, relates to a method of manufacturing reaction nozzles for a turbine comprising (a) providing a single piece of flat plate stock of predetermined size and thickness; and (b) cutting the flat plate stock to form a 360° ring; (c) cutting the 360° ring into two or more arcuate segments; and (d) machining each of the segments to include a plurality of nozzle airfoils.
  • the invention relates to a reaction nozzle component for a steam turbine comprising a unitary arcuate segment formed to include a plurality of adjacent nozzle airfoils.
  • a conventional steam turbine reaction nozzle 10 includes an airfoil 12 and an integral radially inner tip shroud or cover 14.
  • the radially outer end of the nozzle is formed with a base 16 having a dovetail configuration.
  • the base or dovetail 16 is provided with a pair of flanges 18 and 20 projecting in both axially upstream and downstream directions, defining recesses 22 therebetween.
  • the nozzle casing or carrier (not shown) is provided with generally correspondingly shaped dovetail grooves which allow the nozzles 10 to be individually loaded into the carrier or casing at a conventional notched cut-out.
  • each nozzle can be loaded into the dovetail slot in the carrier until the entire row of nozzles has been assembled.
  • the dovetail arrangement may be reversed, with the dovetail groove component formed in the nozzle and the dovetail hook component formed on the carrier or casing.
  • Figure 2 illustrates a unitary arcuate dovetail reaction nozzle component or segment manufactured in accordance with an exemplary embodiment of the invention.
  • the segment 24 is machined from a single piece of flat metal plate stock and includes a plurality of adjacent airfoil portions (or simply “airfoils") 26 with an integral, common tip shroud or cover 28 at the radially inner ends of the airfoils, and an integral, common dovetail hook 30 at the radially inner ends of the airfoils.
  • the arcuate length of the segments may be varied as desired to include as few as two airfoils or as many as 50% of the airfoils required for a full 360° reaction nozzle ring.
  • the common dovetail comprises a centerline support mechanism for a 180° segment.
  • the segments 38 and 40 are then machined to include the airfoils 26, integral tip shrouds or tip covers 28, and dovetail hooks 30 as shown in Figure 2, but noting that Figure 2 illustrates an arcuately shorter segment. After machining, the segments 38 and 40 are disassembled or removed from the jig and are ready for insertion into the carrier or casing dovetail groove.
  • a solid ring 48 may be cut from the flat plate stock into four individual 90° segments 50, 52, 54 and 56 and machined to each include 25% of the required airfoils.
  • the arcuate length of the airfoil segments may be altered as desired with each segment including at least two airfoils.
  • the flat plate stock 38 may be high grade 400 Series stainless steel with 12% chromium, or other suitable material.
  • shims of appropriate thickness may be placed between the segments at the dovetail.
  • the segments may be held in place in the dovetail via conventional radial end or axial shims which eliminate the radial end or axial gap between the segment dovetail and the dovetail groove in the casing or carrier.
  • machined segment concept in accordance with aspects of this invention also improves the ability to service/repair rows relative to current practice; creates a known/repeatable/unvarying boundary condition; reduces the number of parts per stage; and insures that segments are assembled in the correct location/direction.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP06252184A 2005-04-27 2006-04-22 Méthode de fabrication de segments statoriques pour une turbine à vapeur Withdrawn EP1722070A3 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US11/115,371 US20060245923A1 (en) 2005-04-27 2005-04-27 Arcuate nozzle segment and related method of manufacture

Publications (2)

Publication Number Publication Date
EP1722070A2 true EP1722070A2 (fr) 2006-11-15
EP1722070A3 EP1722070A3 (fr) 2011-10-12

Family

ID=36994715

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06252184A Withdrawn EP1722070A3 (fr) 2005-04-27 2006-04-22 Méthode de fabrication de segments statoriques pour une turbine à vapeur

Country Status (4)

Country Link
US (1) US20060245923A1 (fr)
EP (1) EP1722070A3 (fr)
CN (1) CN1880731B (fr)
RU (1) RU2006114341A (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1764482A2 (fr) * 2005-09-07 2007-03-21 General Electric Company Anneau statorique en une pièce et procédé de fabrication

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070071605A1 (en) * 2005-09-23 2007-03-29 General Electric Company Integrated nozzle and bucket wheels for reaction steam turbine stationary components and related method
EP2735707B1 (fr) * 2012-11-27 2017-04-05 Safran Aero Boosters SA Redresseur de turbomachine axiale avec virole interne segmentée et compresseur associé
PL3967846T3 (pl) 2020-09-10 2024-07-01 General Electric Technology Gmbh Segment dyszy, turbina parowa z membraną z wielu segmentów dysz i sposób ich montażu

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6425738B1 (en) * 2000-05-11 2002-07-30 General Electric Company Accordion nozzle
EP1764482A2 (fr) * 2005-09-07 2007-03-21 General Electric Company Anneau statorique en une pièce et procédé de fabrication
EP1785594A2 (fr) * 2005-11-11 2007-05-16 General Electric Company Assemblage de stator pour turbine à vapeur à réaction

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3091383A (en) * 1957-02-14 1963-05-28 Stalker Corp Bladed rotor for fluid machines
US3056583A (en) * 1960-11-10 1962-10-02 Gen Electric Retaining means for turbine shrouds and nozzle diaphragms of turbine engines
US3302926A (en) * 1965-12-06 1967-02-07 Gen Electric Segmented nozzle diaphragm for high temperature turbine
SE463702B (sv) * 1989-06-01 1991-01-14 Abb Stal Ab Saett vid framstaellning av en delad cirkulaer ring
US5174715A (en) * 1990-12-13 1992-12-29 General Electric Company Turbine nozzle
US5438755A (en) * 1993-11-17 1995-08-08 Giberson; Melbourne F. Method of making a monolithic shrouded impeller
US6183192B1 (en) * 1999-03-22 2001-02-06 General Electric Company Durable turbine nozzle
GB9922248D0 (en) * 1999-09-21 1999-11-17 Rolls Royce Plc Improvements in or relating to methods and apparatus for machining workpieces
JP4040922B2 (ja) * 2001-07-19 2008-01-30 株式会社東芝 組立式ノズルダイアフラムおよびその組立方法
CA2366325A1 (fr) * 2001-12-27 2003-06-27 Todd Howley Methode de formage des talons d'ailettes de turbine
US6722848B1 (en) * 2002-10-31 2004-04-20 General Electric Company Turbine nozzle retention apparatus at the carrier horizontal joint face
FR2873940B1 (fr) * 2004-08-03 2008-01-04 Snecma Moteurs Sa Procede de fabrication de pieces constitutives d'une aube creuse par laminage
US20070071605A1 (en) * 2005-09-23 2007-03-29 General Electric Company Integrated nozzle and bucket wheels for reaction steam turbine stationary components and related method

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6425738B1 (en) * 2000-05-11 2002-07-30 General Electric Company Accordion nozzle
EP1764482A2 (fr) * 2005-09-07 2007-03-21 General Electric Company Anneau statorique en une pièce et procédé de fabrication
EP1785594A2 (fr) * 2005-11-11 2007-05-16 General Electric Company Assemblage de stator pour turbine à vapeur à réaction

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1764482A2 (fr) * 2005-09-07 2007-03-21 General Electric Company Anneau statorique en une pièce et procédé de fabrication
EP1764482A3 (fr) * 2005-09-07 2010-05-05 General Electric Company Anneau statorique en une pièce et procédé de fabrication

Also Published As

Publication number Publication date
US20060245923A1 (en) 2006-11-02
EP1722070A3 (fr) 2011-10-12
CN1880731B (zh) 2010-05-12
RU2006114341A (ru) 2007-11-10
CN1880731A (zh) 2006-12-20

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