US20050220622A1 - Integral covered nozzle with attached overcover - Google Patents

Integral covered nozzle with attached overcover Download PDF

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Publication number
US20050220622A1
US20050220622A1 US10/708,909 US70890904A US2005220622A1 US 20050220622 A1 US20050220622 A1 US 20050220622A1 US 70890904 A US70890904 A US 70890904A US 2005220622 A1 US2005220622 A1 US 2005220622A1
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US
United States
Prior art keywords
blades
cover portions
adjacent
overcover
cover
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.)
Abandoned
Application number
US10/708,909
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English (en)
Inventor
Ronald Korzun
Christopher SULLIVAN
Robert BRACKEN
David Fitts
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
Priority to US10/708,909 priority Critical patent/US20050220622A1/en
Assigned to GENERAL ELECTRIC COMPANY reassignment GENERAL ELECTRIC COMPANY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: FITTS, DAVID ORUS, KORZUN, RONALD W., BRACKEN, ROBERT JAMES, SULLIVAN, CHRISTOPHER WALTER
Priority to EP05251814A priority patent/EP1582698A1/en
Priority to CNA2005100595516A priority patent/CN1676885A/zh
Priority to KR1020050026266A priority patent/KR20060044967A/ko
Priority to JP2005097999A priority patent/JP2005291208A/ja
Publication of US20050220622A1 publication Critical patent/US20050220622A1/en
Abandoned 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
    • F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides
    • A—HUMAN NECESSITIES
    • A61—MEDICAL OR VETERINARY SCIENCE; HYGIENE
    • A61M—DEVICES FOR INTRODUCING MEDIA INTO, OR ONTO, THE BODY; DEVICES FOR TRANSDUCING BODY MEDIA OR FOR TAKING MEDIA FROM THE BODY; DEVICES FOR PRODUCING OR ENDING SLEEP OR STUPOR
    • A61M5/00—Devices for bringing media into the body in a subcutaneous, intra-vascular or intramuscular way; Accessories therefor, e.g. filling or cleaning devices, arm-rests
    • A61M5/178—Syringes
    • A61M5/31—Details
    • A61M5/32—Needles; Details of needles pertaining to their connection with syringe or hub; Accessories for bringing the needle into, or holding the needle on, the body; Devices for protection of needles
    • A—HUMAN NECESSITIES
    • A61—MEDICAL OR VETERINARY SCIENCE; HYGIENE
    • A61L—METHODS OR APPARATUS FOR STERILISING MATERIALS OR OBJECTS IN GENERAL; DISINFECTION, STERILISATION OR DEODORISATION OF AIR; CHEMICAL ASPECTS OF BANDAGES, DRESSINGS, ABSORBENT PADS OR SURGICAL ARTICLES; MATERIALS FOR BANDAGES, DRESSINGS, ABSORBENT PADS OR SURGICAL ARTICLES
    • A61L2/00—Methods or apparatus for disinfecting or sterilising materials or objects other than foodstuffs or contact lenses; Accessories therefor
    • A61L2/16—Methods or apparatus for disinfecting or sterilising materials or objects other than foodstuffs or contact lenses; Accessories therefor using chemical substances
    • A61L2/23—Solid substances, e.g. granules, powders, blocks, tablets
    • A61L2/238—Metals or alloys, e.g. oligodynamic metals
    • 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
    • F01D11/005—Sealing means between non relatively rotating elements
    • 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
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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
    • 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
    • A—HUMAN NECESSITIES
    • A61—MEDICAL OR VETERINARY SCIENCE; HYGIENE
    • A61L—METHODS OR APPARATUS FOR STERILISING MATERIALS OR OBJECTS IN GENERAL; DISINFECTION, STERILISATION OR DEODORISATION OF AIR; CHEMICAL ASPECTS OF BANDAGES, DRESSINGS, ABSORBENT PADS OR SURGICAL ARTICLES; MATERIALS FOR BANDAGES, DRESSINGS, ABSORBENT PADS OR SURGICAL ARTICLES
    • A61L2202/00—Aspects relating to methods or apparatus for disinfecting or sterilising materials or objects
    • A61L2202/20—Targets to be treated
    • A61L2202/24—Medical instruments, e.g. endoscopes, catheters, sharps
    • A—HUMAN NECESSITIES
    • A61—MEDICAL OR VETERINARY SCIENCE; HYGIENE
    • A61L—METHODS OR APPARATUS FOR STERILISING MATERIALS OR OBJECTS IN GENERAL; DISINFECTION, STERILISATION OR DEODORISATION OF AIR; CHEMICAL ASPECTS OF BANDAGES, DRESSINGS, ABSORBENT PADS OR SURGICAL ARTICLES; MATERIALS FOR BANDAGES, DRESSINGS, ABSORBENT PADS OR SURGICAL ARTICLES
    • A61L2420/00—Materials or methods for coatings medical devices
    • A61L2420/02—Methods for coating medical devices
    • A—HUMAN NECESSITIES
    • A61—MEDICAL OR VETERINARY SCIENCE; HYGIENE
    • A61M—DEVICES FOR INTRODUCING MEDIA INTO, OR ONTO, THE BODY; DEVICES FOR TRANSDUCING BODY MEDIA OR FOR TAKING MEDIA FROM THE BODY; DEVICES FOR PRODUCING OR ENDING SLEEP OR STUPOR
    • A61M2205/00—General characteristics of the apparatus
    • A61M2205/02—General characteristics of the apparatus characterised by a particular materials
    • A61M2205/0205—Materials having antiseptic or antimicrobial properties, e.g. silver compounds, rubber with sterilising agent
    • A—HUMAN NECESSITIES
    • A61—MEDICAL OR VETERINARY SCIENCE; HYGIENE
    • A61M—DEVICES FOR INTRODUCING MEDIA INTO, OR ONTO, THE BODY; DEVICES FOR TRANSDUCING BODY MEDIA OR FOR TAKING MEDIA FROM THE BODY; DEVICES FOR PRODUCING OR ENDING SLEEP OR STUPOR
    • A61M2205/00—General characteristics of the apparatus
    • A61M2205/02—General characteristics of the apparatus characterised by a particular materials
    • A61M2205/0238—General characteristics of the apparatus characterised by a particular materials the material being a coating or protective layer
    • 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
    • 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
    • F05D2240/40—Use of a multiplicity of similar components

Definitions

  • the present invention relates to steam turbines and, more particularly, to static carriers, or inner shells containing nozzle blades which direct and accelerate steam for impingement on buckets of a steam turbine.
  • a steam turbine conventionally employs nozzles formed by a plurality of stationary blades in the steam path which are aerodynamically shaped to receive the steam, smoothly turn it in a desired direction and accelerate it for impingement on turbine buckets. Precision in the steam path is critical to turbine efficiency. The steam must be precisely directed using diaphragm or nozzle blades which are accurately configured and stably supported to avoid power wasting turbulence or off-design flow characteristics.
  • Some steam turbine design concepts employee diaphragms, which are conventionally formed by inserting opposed ends of blades into cutouts in semi-circular bands known as spacers.
  • the ends of the blades are tack welded to the spacers and outer and inner semi-circular rings are penetration welded to the spacers and to the blades.
  • very deep welding is necessary between the rings and spacers so that the weld penetrates far enough in this interface to also contact and attach the blades.
  • welding defects increase as the weld depth increases.
  • Such welding defects may include, for example, cracks, slag inclusions, lack of complete penetration, etc., which may lead to failure or instability of the nozzle blades.
  • deep welding tends to distort and to thereby deviate the steam path from the design aerodynamic characteristics and thus produce reduced overall efficiency of the apparatus.
  • the spacers have typically been relatively thin such as, for example, less than one-quarter inch, since this thickness was the maximum which conventional punching techniques could accommodate. Due to this thinness, the spacers themselves were effective more as positioning agents prior to welding to the inner and outer rings rather than structural members capable of supporting the blades on their own.
  • a further source of distortion arose due to the fabrication of spacers and blades into semi-circular assemblies. Distortions due to heating and weld shrinkage, material stress relief and tempering tended to distort this subassembly both prior to, and during, mating with the inner and outer semi-circular rings. This distortion could be traced at least in part to the fact that changing stresses in a semi-circular assembly can result in distortion of the semi-circle.
  • a second typical steam turbine concept employs individual nozzles inserted into circumferential slots in an inner shell or carrier.
  • This concept can be further divided into 2 different inner diameter tip configurations: 1) peened on covers and 2) integral covered nozzles. Peened on covers group nozzles together by mechanically peening tenons onto the cover. Though mechanically functional, this design provides numerous leakage paths both between the airfoil and cover and between circumferentially adjacent. Alternatively, integral covered nozzles greatly reduces or eliminates these leakage paths. This is very desirable since sealing is a critical part of steam turbine performance.
  • multiple blade foils multiple respective cover portions defining a first surface configured to span tips of multiple adjacent blades between tip locations of adjacent blades thereby to form the cover portion portions for adjacent blades and wherein the cover portions associated with each respective adjacent blades include facing sides for adjacent cover portions of adjacent blades; and an overcover coupled to a second surface opposite the first surface of the respective cover portions, the overcover configured to at least one of stiffen deterministic constraints of the tips and seal against leakage through the facing sides for adjacent cover portions.
  • a method of constructing equivalent integral covered blading for a turbine having multiple blades supported by a stator includes attaching multiple blade foils with multiple respective cover portions on a first surface thereof configured to span tips of multiple adjacent blades between tip locations of adjacent blades and wherein the cover portions associated with each respective adjacent blades include facing sides for adjacent cover portions of adjacent blades; and coupling an overcover to a second surface opposite the first surface of the respective cover portions, the overcover configured to at least one of stiffen deterministic constraints of the tips and seal against leakage through the facing sides for adjacent cover portions.
  • FIG. 1 shows an axial cross section of a typical diaphragm construction steam turbine
  • FIG. 2 is a side perspective view of an integral covered nozzle (INC) in accordance with an exemplary embodiment
  • FIG. 3 is a bottom perspective view of three ICN's of FIG. 2 coupled together using an overcover in accordance with an exemplary embodiment
  • FIGS. 4 a to 4 e illustrate representative interfaces wherein FIG. 4 a is a Z-cut shaped interface, FIG. 4 b is a rectangular straight cut interface, FIG. 4 c is a nested double wing interface, FIG. 4 d is a single wing interface, and FIG. 4 e is a diagonal interface, wherein the view of all of the blades is from a shaft of the turbine with the bottom of the cover portions being illustrated; and
  • FIG. 5 is a top perspective view of the three ICN's joined in FIG. 3 illustrating an interface between corresponding cover portions.
  • FIG. 1 a cross section is shown of an axial flow steam turbine 10 which includes a casing 12 and a rotatable shaft 14 .
  • a plurality of turbine buckets 16 are affixed in a conventional manner to shaft 14 for rotation therewith.
  • An inlet diaphragm 18 includes an annular row of blades 20 which accelerate and direct incoming steam from a steam chest 22 onto a first row 24 of turbine buckets.
  • Additional diaphragms 26 are disposed between pairs of subsequent stages of turbine buckets 16 for redirecting and accelerating the steam emerging from the upstream stage and impinging it at optimum angle and speed on the respective downstream stage.
  • Each diaphragm 26 includes blades 20 between an outer spacer 28 and an inner spacer 30 .
  • An outer ring 32 is affixed to outer spacer 28 and mates in a conventional manner with casing 12 .
  • An inner ring 34 is affixed to inner spacer 30 and is suspended spaced from shaft 14 .
  • a shaft seal (not shown) may be employed in a seal region 36 at an inner extremity of inner ring 34 to permit shaft 14 to rotate with respect to diaphragm 26 while sealing against axial steam leakage along the rotating shaft.
  • Nozzle 100 includes a dovetail segment 102 configured to be operably fixed in a groove in an inner carrier.
  • a foil or nozzle blade 104 is affixed to dovetail segment 102 at one end and is affixed to a cover portion 106 at an opposite end.
  • a tenon 108 extends from cover portion 106 for operable connection with an overcover 110 discussed more fully below with reference to FIGS. 3 and 5 .
  • Tenon 108 is preferably riveted to cover portion 106 in an exemplary embodiment, but is not limited thereto.
  • overcover 110 is disposed over multiple ICN's 100 such that multiple means more than one, including two or more ICN' 100 .
  • Overcover 110 is preferably configured having a thickness less than each respective cover portion 106 .
  • Overcover 110 includes apertures positioned therein to align with a tenon 108 extending from each cover portion 106 .
  • Each tenon 108 is peened down to retain the overcover 110 which spans across the three nozzles 100 shown.
  • any number is contemplated including two nozzles 100 to a number that would complete a ring around shaft 14 .
  • Each tenon 108 may be any shape or size and is no longer limited to the shape of the airfoil tip generally shown in FIG. 5 —which typically is restrained to fall within the geometry of the airfoil tip in which it is secured.
  • Other methods of retaining overcover 110 may also be used, such as brazing or welding. If brazing or welding is used for attachment of overcover 110 to cover portions 106 , a tenon 108 on cover portions 106 may or may not be used to facilitate this process.
  • a material buildup in the form of a weld buildup or, alternatively, braze, plating, spraying or other mechanical means or metallurgical means is applied to each one of the facing sides 118 of the cover portion portions 106 .
  • the material buildup 119 is illustrated in FIG. 2 in phantom. Machining is effected to remove excess material 120 from the buildup portion 119 and thereby provide a clean contacting interface 121 between adjacent cover portion portions 106 (See FIG. 5 ). Excess material 120 is on an outer circumferential face portion 122 of the cover portion 106 and also on an inner circumferential face portion 123 of each cover portion 106 .
  • the interface 121 can have different interlocking shapes.
  • interface 121 is illustrated as a Z-cut.
  • the interface 121 is a straight line rectangularly directed relative to the turbine blading and parallel to the rotor's rotational axis.
  • the interface 121 is a double e wing or nested construction. This is a construction which has curves directed towards both the trailing edge 124 and leading edge 125 of a turbine blade.
  • a single wing design is illustrated such that the interface 121 has only a single curve 126 in the direction of the trailing edge 124 .
  • the interface 121 is a diagonally directed line.
  • the interface is of a nature such that a snug fit can be achieved between adjacent cover portion portions 106 .
  • a contact at the interface line 121 between neighboring blades or nozzles 100 occurs so that if any blade 104 attempts to vibrate, its motion is dampened by the neighboring blade 104 .
  • FIG. 4 b is likely the most effective structure since, as the blades try to twist due to a nozzle wake frequency, these rectangular shaped cover portion portions cause an increase in pitch as the frequency increases.
  • individual cover portion portions 106 are assembled on blades 104 and then tack welded at 132 to allow the tenons 108 to be riveted without the cover portion portions 106 moving. After the riveting of tenons 108 to the cover portion portions 106 is effected, excess extension material 133 which runs along the edges of each cover portion 106 is removed. In this manner, the tack weld sections 132 are trimmed off on opposite sides (only one side shown in FIG. 5 ) leaving integral cover portion portions 106 affixed to each blade 104 .
  • integral covered blading can be constructed initially in this manner.
  • cover portion portions 106 can be affixed to the tips 111 of each blade 104 by suitable welding or brazing. Thereafter, each blade structure constitutes an equivalent integral covered nozzle.
  • ICN integral covered nozzle

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Health & Medical Sciences (AREA)
  • Animal Behavior & Ethology (AREA)
  • Chemical & Material Sciences (AREA)
  • Veterinary Medicine (AREA)
  • Public Health (AREA)
  • General Health & Medical Sciences (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Anesthesiology (AREA)
  • Hematology (AREA)
  • Heart & Thoracic Surgery (AREA)
  • Biomedical Technology (AREA)
  • Vascular Medicine (AREA)
  • Medicinal Chemistry (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • General Chemical & Material Sciences (AREA)
  • Epidemiology (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US10/708,909 2004-03-31 2004-03-31 Integral covered nozzle with attached overcover Abandoned US20050220622A1 (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
US10/708,909 US20050220622A1 (en) 2004-03-31 2004-03-31 Integral covered nozzle with attached overcover
EP05251814A EP1582698A1 (en) 2004-03-31 2005-03-23 Integral covered nozzle with attached overcover
CNA2005100595516A CN1676885A (zh) 2004-03-31 2005-03-29 具有相连覆接盖的整体盖式导向器
KR1020050026266A KR20060044967A (ko) 2004-03-31 2005-03-30 오버커버가 부착된 일체형 커버식 노즐
JP2005097999A JP2005291208A (ja) 2004-03-31 2005-03-30 取付け式オーバカバーを有する一体形カバー付きノズル

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US10/708,909 US20050220622A1 (en) 2004-03-31 2004-03-31 Integral covered nozzle with attached overcover

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US20050220622A1 true US20050220622A1 (en) 2005-10-06

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ID=34886467

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US10/708,909 Abandoned US20050220622A1 (en) 2004-03-31 2004-03-31 Integral covered nozzle with attached overcover

Country Status (5)

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US (1) US20050220622A1 (zh)
EP (1) EP1582698A1 (zh)
JP (1) JP2005291208A (zh)
KR (1) KR20060044967A (zh)
CN (1) CN1676885A (zh)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9382801B2 (en) 2014-02-26 2016-07-05 General Electric Company Method for removing a rotor bucket from a turbomachine rotor wheel

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1975373A1 (en) * 2007-03-06 2008-10-01 Siemens Aktiengesellschaft Guide vane duct element for a guide vane assembly of a gas turbine engine
CN109869196B (zh) * 2019-04-18 2021-10-01 中国航发沈阳发动机研究所 一种双联或多联的叶轮机转子叶片及具有其的叶轮机
JP2023108322A (ja) * 2022-01-25 2023-08-04 三菱重工コンプレッサ株式会社 ノズルモジュール、ノズルダイアフラム、蒸気タービン、ノズルダイアフラムの組立方法、蒸気タービンの組立方法、及び蒸気タービンの分解方法

Citations (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2221678A (en) * 1938-08-30 1940-11-12 Gen Electric Elastic fluid turbine bucket wheel
US2277484A (en) * 1939-04-15 1942-03-24 Westinghouse Electric & Mfg Co Turbine blade construction
US2315641A (en) * 1942-01-16 1943-04-06 Westinghouse Electric & Mfg Co Turbine blade shroud fastening
US2315655A (en) * 1942-01-23 1943-04-06 Westinghouse Electric & Mfg Co Turbine blade shroud fastening
US3367629A (en) * 1966-12-19 1968-02-06 Westinghouse Electric Corp Continuous shroud for rotor blades
US3702221A (en) * 1971-06-15 1972-11-07 Westinghouse Electric Corp Continuous shrouding-riveted construction
US3910716A (en) * 1974-05-23 1975-10-07 Westinghouse Electric Corp Gas turbine inlet vane structure utilizing a stable ceramic spherical interface arrangement
US4509238A (en) * 1983-03-21 1985-04-09 General Electric Company Method for fabricating a steam turbine diaphragm
US4575911A (en) * 1985-02-08 1986-03-18 Abdite Industries, Inc. Method and apparatus for constructing turbine components
US5146679A (en) * 1991-01-16 1992-09-15 Ortolano Ralph J Method of converting grouped blading to equivalent integral covered blading
US5215432A (en) * 1991-07-11 1993-06-01 United Technologies Corporation Stator vane damper
US5238368A (en) * 1991-01-16 1993-08-24 Ortolano Ralph J Converting grouped blading to equivalent integral covered blading
US6182129B1 (en) * 1997-09-11 2001-01-30 International Business Machines Corporation Apparatus, methods and computer program products for managing sessions with host-based application using session vectors
US6644924B1 (en) * 2002-05-31 2003-11-11 General Electric Company Covers for turbine buckets and methods of assembly
US6679681B2 (en) * 2002-04-10 2004-01-20 General Electric Company Flush tenon cover for steam turbine blades with advanced sealing

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2130128A1 (de) * 1971-06-18 1972-12-28 Kraftwerk Union Ag Verfahren zum Verbinden des Schaufelblattes einer Stroemungsmaschinen-,insbesondere Turbomaschinen-Schaufel,mit einem Deckbandstueck
GB1605309A (en) * 1975-03-14 1989-02-01 Rolls Royce Stator blade for a gas turbine engine
JPS5632006A (en) * 1979-08-24 1981-04-01 Toshiba Corp Turbine nozzle
US6343912B1 (en) * 1999-12-07 2002-02-05 General Electric Company Gas turbine or jet engine stator vane frame

Patent Citations (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2221678A (en) * 1938-08-30 1940-11-12 Gen Electric Elastic fluid turbine bucket wheel
US2277484A (en) * 1939-04-15 1942-03-24 Westinghouse Electric & Mfg Co Turbine blade construction
US2315641A (en) * 1942-01-16 1943-04-06 Westinghouse Electric & Mfg Co Turbine blade shroud fastening
US2315655A (en) * 1942-01-23 1943-04-06 Westinghouse Electric & Mfg Co Turbine blade shroud fastening
US3367629A (en) * 1966-12-19 1968-02-06 Westinghouse Electric Corp Continuous shroud for rotor blades
US3702221A (en) * 1971-06-15 1972-11-07 Westinghouse Electric Corp Continuous shrouding-riveted construction
US3910716A (en) * 1974-05-23 1975-10-07 Westinghouse Electric Corp Gas turbine inlet vane structure utilizing a stable ceramic spherical interface arrangement
US4509238A (en) * 1983-03-21 1985-04-09 General Electric Company Method for fabricating a steam turbine diaphragm
US4575911A (en) * 1985-02-08 1986-03-18 Abdite Industries, Inc. Method and apparatus for constructing turbine components
US5146679A (en) * 1991-01-16 1992-09-15 Ortolano Ralph J Method of converting grouped blading to equivalent integral covered blading
US5238368A (en) * 1991-01-16 1993-08-24 Ortolano Ralph J Converting grouped blading to equivalent integral covered blading
US5215432A (en) * 1991-07-11 1993-06-01 United Technologies Corporation Stator vane damper
US6182129B1 (en) * 1997-09-11 2001-01-30 International Business Machines Corporation Apparatus, methods and computer program products for managing sessions with host-based application using session vectors
US6679681B2 (en) * 2002-04-10 2004-01-20 General Electric Company Flush tenon cover for steam turbine blades with advanced sealing
US6644924B1 (en) * 2002-05-31 2003-11-11 General Electric Company Covers for turbine buckets and methods of assembly

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9382801B2 (en) 2014-02-26 2016-07-05 General Electric Company Method for removing a rotor bucket from a turbomachine rotor wheel

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JP2005291208A (ja) 2005-10-20
KR20060044967A (ko) 2006-05-16
EP1582698A1 (en) 2005-10-05
CN1676885A (zh) 2005-10-05

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