RU2006114341A - METHOD FOR PRODUCING A REACTIVE GUIDE BLADE FOR TURBINE (OPTIONS) - Google Patents

METHOD FOR PRODUCING A REACTIVE GUIDE BLADE FOR TURBINE (OPTIONS) Download PDF

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Publication number
RU2006114341A
RU2006114341A RU2006114341/06A RU2006114341A RU2006114341A RU 2006114341 A RU2006114341 A RU 2006114341A RU 2006114341/06 A RU2006114341/06 A RU 2006114341/06A RU 2006114341 A RU2006114341 A RU 2006114341A RU 2006114341 A RU2006114341 A RU 2006114341A
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RU
Russia
Prior art keywords
flat sheet
segment
turbine
reactive
guide vane
Prior art date
Application number
RU2006114341/06A
Other languages
Russian (ru)
Inventor
Дэвид Орус ФИТТС (US)
Дэвид Орус ФИТТС
Роберт Джеймз БРАКЕН (US)
Роберт Джеймз БРАКЕН
Стерлинг Р. ХАТАУЭЙ (US)
Стерлинг Р. ХАТАУЭЙ
Рональд У. КОРЗУН (US)
Рональд У. КОРЗУН
Ларри ДАКЛОС (US)
Ларри ДАКЛОС
Уилль м Эдвард ЭЙДИС (US)
Уилльям Эдвард ЭЙДИС
Original Assignee
ДЖЕНЕРАЛ ЭЛЕКТРИК КОМПАНИ (э Нью Йорк Корпорейшн)(US)
ДЖЕНЕРАЛ ЭЛЕКТРИК КОМПАНИ (э Нью Йорк Корпорейшн)
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 ДЖЕНЕРАЛ ЭЛЕКТРИК КОМПАНИ (э Нью Йорк Корпорейшн)(US), ДЖЕНЕРАЛ ЭЛЕКТРИК КОМПАНИ (э Нью Йорк Корпорейшн) filed Critical ДЖЕНЕРАЛ ЭЛЕКТРИК КОМПАНИ (э Нью Йорк Корпорейшн)(US)
Publication of RU2006114341A publication Critical patent/RU2006114341A/en

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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

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)

Claims (10)

1. Способ изготовления реактивной направляющей лопатки для турбины, при котором выполняют деталь из плоской листовой заготовки (38) заданных размера и толщины, и обрабатывают деталь из плоской листовой заготовки (38) для получения цельного дугообразного сегмента (24) реактивной направляющей лопатки, включающего в себя, по меньшей мере, две примыкающие аэродинамические поверхности (26) направляющей лопатки.1. A method of manufacturing a reactive guide vane for a turbine, in which a part is made from a flat sheet billet (38) of a given size and thickness, and a part is machined from a flat sheet billet (38) to obtain a solid arcuate segment (24) of a reactive guide vane, including at least two adjacent aerodynamic surfaces (26) of the guide vanes. 2. Способ по п.1, при котором сегмент (24) реактивной направляющей лопатки дополнительно содержит общую для концов крышку (28) кожуха и общую скобу (30) в виде ласточкина хвоста на противоположных концах, охватывающие, по меньшей мере, две примыкающие аэродинамические поверхности (26) направляющей лопатки.2. The method according to claim 1, in which the segment (24) of the reactive guide vane further comprises a common end cover (28) of the casing and a common bracket (30) in the form of a dovetail at opposite ends, covering at least two adjacent aerodynamic surface (26) of the guide vanes. 3. Способ по п.1, при котором плоскую листовую заготовку (38) выполняют из нержавеющей стали.3. The method according to claim 1, wherein the flat sheet stock (38) is made of stainless steel. 4. Способ по п.3, при котором используют нержавеющую сталь, представляющую собой высококачественную нержавеющую сталь 400 с 12% хрома.4. The method according to claim 3, in which stainless steel is used, which is a high-quality stainless steel 400 with 12% chromium. 5. Способ по п.1, при котором каждый дугообразный сегмент (24) проходит, по существу, на 180°.5. The method according to claim 1, wherein each arcuate segment (24) extends essentially 180 °. 6. Способ по п.1, при котором каждый дугообразный сегмент (24) проходит, по существу, на 90°.6. The method according to claim 1, in which each arcuate segment (24) extends essentially 90 °. 7. Способ изготовления реактивной направляющей лопатки для турбины, при котором7. A method of manufacturing a jet guide vane for a turbine, in which а) выполняют цельную деталь из плоской листовой заготовки (38) заданных размера и толщины,a) perform an integral part of a flat sheet blank (38) of a given size and thickness, б) разрезают плоскую листовую заготовку (38) для образования 360° кольца (36),b) cut the flat sheet blank (38) to form a 360 ° ring (36), в) разрезают 360° кольцо (36) на два или более дугообразных сегмента (40, 42), иC) cut 360 ° ring (36) into two or more arcuate segments (40, 42), and г) обрабатывают каждый сегмент для образования множества аэродинамических поверхностей (26) направляющей лопатки.d) treat each segment to form a variety of aerodynamic surfaces (26) of the guide vanes. 8. Способ по п.7, при котором на этапе г) каждый сегмент дополнительно образует выполненную за одно целое общую для концов крышку (28) кожуха и выполненный за одно целое общий элемент (30) в виде ласточкина хвоста.8. The method according to claim 7, in which, at step d), each segment additionally forms a single cover common for the ends of the casing cover (28) and one common element (30) made in the form of a dovetail. 9. Способ по п.7, при котором этапы б) и в) осуществляют на проволочном электроэрозионном станке.9. The method according to claim 7, in which steps b) and c) are carried out on a wire EDM machine. 10. Способ по п.7, при котором на этапе в) кольцо разрезают на четыре 90° сегмента (50, 52, 54, 56).10. The method according to claim 7, wherein in step c) the ring is cut into four 90 ° segments (50, 52, 54, 56).
RU2006114341/06A 2005-04-27 2006-04-26 METHOD FOR PRODUCING A REACTIVE GUIDE BLADE FOR TURBINE (OPTIONS) RU2006114341A (en)

Applications Claiming Priority (2)

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
US11/115,371 2005-04-27

Publications (1)

Publication Number Publication Date
RU2006114341A true RU2006114341A (en) 2007-11-10

Family

ID=36994715

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2006114341/06A RU2006114341A (en) 2005-04-27 2006-04-26 METHOD FOR PRODUCING A REACTIVE GUIDE BLADE FOR TURBINE (OPTIONS)

Country Status (4)

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

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070053773A1 (en) * 2005-09-07 2007-03-08 General Electric Company Integrated nozzle wheel for reaction steam turbine stationary components and related method
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 (en) * 2012-11-27 2017-04-05 Safran Aero Boosters SA Axial turbomachine guide nozzle with segmented inner shroud and corresponding compressor
EP3967846B1 (en) 2020-09-10 2024-04-03 General Electric Technology GmbH Nozzle segment, steam turbine with diaphragm of multiple nozzle segments and method for assembly thereof

Family Cites Families (16)

* 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 (en) * 1989-06-01 1991-01-14 Abb Stal Ab SET TO MAKE A SHARED CIRCULAR 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
US6425738B1 (en) * 2000-05-11 2002-07-30 General Electric Company Accordion nozzle
JP4040922B2 (en) * 2001-07-19 2008-01-30 株式会社東芝 Assembly type nozzle diaphragm and its assembly method
CA2366325A1 (en) * 2001-12-27 2003-06-27 Todd Howley Method of forming turbine blade root
US6722848B1 (en) * 2002-10-31 2004-04-20 General Electric Company Turbine nozzle retention apparatus at the carrier horizontal joint face
FR2873940B1 (en) * 2004-08-03 2008-01-04 Snecma Moteurs Sa METHOD FOR MANUFACTURING CONSTITUENT PIECES OF A HOLLOW DRAW BY ROLLING
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
US20070053773A1 (en) * 2005-09-07 2007-03-08 General Electric Company Integrated nozzle wheel for reaction steam turbine stationary components and related method
US7497658B2 (en) * 2005-11-11 2009-03-03 General Electric Company Stacked reaction steam turbine stator assembly

Also Published As

Publication number Publication date
CN1880731A (en) 2006-12-20
EP1722070A2 (en) 2006-11-15
CN1880731B (en) 2010-05-12
US20060245923A1 (en) 2006-11-02
EP1722070A3 (en) 2011-10-12

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FA92 Acknowledgement of application withdrawn (lack of supplementary materials submitted)

Effective date: 20100521