GB1109457A - Segmented diaphragm assembly for turbines - Google Patents

Segmented diaphragm assembly for turbines

Info

Publication number
GB1109457A
GB1109457A GB38115/65A GB3811565A GB1109457A GB 1109457 A GB1109457 A GB 1109457A GB 38115/65 A GB38115/65 A GB 38115/65A GB 3811565 A GB3811565 A GB 3811565A GB 1109457 A GB1109457 A GB 1109457A
Authority
GB
United Kingdom
Prior art keywords
segments
ring
clearances
pins
expansion
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.)
Expired
Application number
GB38115/65A
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.)
Worthington Corp
Original Assignee
Worthington Corp
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 Worthington Corp filed Critical Worthington Corp
Publication of GB1109457A publication Critical patent/GB1109457A/en
Expired legal-status Critical Current

Links

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
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

1,109,457. Turbine stator blades. WORTHINGTON CORPORATION. Sept. 7, 1965 [Nov.17, 1964], No.38115/65. Heading F1T. In a diaphragm assembly for turbines, a number of nozzle blade segments 30, Fig.1, each comprising at least one blade are attached to an outer segmented ring 14, 16 and located by an inner segmented ring 18, 20 for relative movement therewith for expansion purposes. Preferably, the rings 14, 16 and 18, 20 are forged , and the segments 30 are cast from stainless steel. Radial projections 38, Fig. 2, of the segments 30 are clamped in a circumferential groove 40 in ring 14, 16 by a segmented member 44 containing a seal 48 for the rotor blade tips. Axially extending pins (49), Fig. 3 (not shown), in bores through the junction between the outer surfaces of the projections 38 and the bottom of the groove 40 prevent circumferential movement of the segments 30. Expansion clearances 57 are provided. The ring 18, 20 comprising two segments located together by pins 60, 62, has a peripheral projection 64 extending into channels 66 in the segments 30 with expansion-permitting clearances 68. Moreover, the ring 18, 20 has guide keys 72 which engage grooves in the segments 30 with radial clearances 76. Circumferential clearances 33 are provided between the inner parts 32 of segments 30. The ring 18, 20 carries a labyrinth seal 59 for the rotor. The diaphragm assembly is positioned within the turbine casing by a locating surface 52, and by pins 80 which are located in holes 78 with radial clearances 82.
GB38115/65A 1964-11-17 1965-09-07 Segmented diaphragm assembly for turbines Expired GB1109457A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US411821A US3300180A (en) 1964-11-17 1964-11-17 Segmented diaphragm assembly

Publications (1)

Publication Number Publication Date
GB1109457A true GB1109457A (en) 1968-04-10

Family

ID=23630462

Family Applications (1)

Application Number Title Priority Date Filing Date
GB38115/65A Expired GB1109457A (en) 1964-11-17 1965-09-07 Segmented diaphragm assembly for turbines

Country Status (5)

Country Link
US (1) US3300180A (en)
BE (1) BE669775A (en)
DE (1) DE1426885B2 (en)
GB (1) GB1109457A (en)
NL (1) NL6513461A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150082807A1 (en) * 2012-03-26 2015-03-26 Alstom Technology Ltd. Carrier ring

Families Citing this family (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3443791A (en) * 1966-11-23 1969-05-13 United Aircraft Corp Turbine vane assembly
US3408048A (en) * 1967-05-26 1968-10-29 Westinghouse Electric Corp Diaphragm sealing structure
US3536414A (en) * 1968-03-06 1970-10-27 Gen Electric Vanes for turning fluid flow in an annular duct
JPS59120704A (en) * 1982-12-27 1984-07-12 Toshiba Corp Heat resistant wall body against superhigh temperature
DE4436731A1 (en) * 1994-10-14 1996-04-18 Abb Management Ag compressor
US5772401A (en) * 1995-10-13 1998-06-30 Dresser-Rand Company Diaphragm construction for turbomachinery
DE19547653C2 (en) * 1995-12-20 1999-08-19 Abb Patent Gmbh Guide device for a turbine with a guide vane carrier and method for producing this guide device
US6425738B1 (en) * 2000-05-11 2002-07-30 General Electric Company Accordion nozzle
US20060088409A1 (en) * 2004-10-21 2006-04-27 General Electric Company Grouped reaction nozzle tip shrouds with integrated seals
US20070053773A1 (en) * 2005-09-07 2007-03-08 General Electric Company Integrated nozzle wheel for reaction steam turbine stationary components and related method
US7645117B2 (en) * 2006-05-05 2010-01-12 General Electric Company Rotary machines and methods of assembling
JP2008169705A (en) * 2007-01-09 2008-07-24 Toshiba Corp Steam turbine
US8887390B2 (en) 2008-08-15 2014-11-18 Dresser-Rand Company Method for correcting downstream deflection in gas turbine nozzles
US8226360B2 (en) * 2008-10-31 2012-07-24 General Electric Company Crenelated turbine nozzle
DE102009004934B4 (en) * 2009-01-16 2021-08-26 MTU Aero Engines AG Method for assembling an integral inner ring of a turbo compressor stator
EP2211023A1 (en) * 2009-01-21 2010-07-28 Siemens Aktiengesellschaft Guide vane system for a turbomachine with segmented guide vane carrier
US8157517B2 (en) * 2009-04-27 2012-04-17 Elliott Company Boltless multi-part diaphragm for use with a centrifugal compressor
US8123474B2 (en) * 2009-05-12 2012-02-28 Dresser-Rand Company Repair of industrial gas turbine nozzle diaphragm packing
JP5342579B2 (en) * 2011-02-28 2013-11-13 三菱重工業株式会社 Stator blade unit of rotating machine, method of manufacturing stator blade unit of rotating machine, and method of coupling stator blade unit of rotating machine
JP6546053B2 (en) * 2015-09-18 2019-07-17 株式会社東芝 Assembly type nozzle diaphragm and steam turbine
JP6578053B2 (en) * 2016-02-23 2019-09-18 三菱重工コンプレッサ株式会社 Steam turbine
JP6505860B2 (en) * 2016-03-15 2019-04-24 東芝エネルギーシステムズ株式会社 Turbine and turbine vane
CN111396140B (en) * 2020-03-31 2023-01-31 中国航发动力股份有限公司 Stationary blade ring with stopping structure and machining method thereof
CN113352134A (en) * 2021-07-12 2021-09-07 重庆江增船舶重工有限公司 Manufacturing method of over-positioning type part

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2197521A (en) * 1938-04-21 1940-04-16 Westinghouse Electric & Mfg Co Turbine apparatus
GB633022A (en) * 1946-09-19 1949-12-05 Svenska Turbinfab Ab Guide blade system for rotary elastic fluid machines
US2609176A (en) * 1950-01-21 1952-09-02 A V Roe Canada Ltd Turbine nozzle guide vane construction
US2654566A (en) * 1950-02-11 1953-10-06 A V Roe Canada Ltd Turbine nozzle guide vane construction

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150082807A1 (en) * 2012-03-26 2015-03-26 Alstom Technology Ltd. Carrier ring
US10012094B2 (en) * 2012-03-26 2018-07-03 Ansaldo Energia Switzerland AG Carrier ring

Also Published As

Publication number Publication date
DE1426885B2 (en) 1971-02-18
BE669775A (en) 1966-03-17
US3300180A (en) 1967-01-24
DE1426885A1 (en) 1969-10-23
NL6513461A (en) 1966-05-18

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