US2843356A - Turbo-machine rotor assembly - Google Patents

Turbo-machine rotor assembly Download PDF

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Publication number
US2843356A
US2843356A US420835A US42083554A US2843356A US 2843356 A US2843356 A US 2843356A US 420835 A US420835 A US 420835A US 42083554 A US42083554 A US 42083554A US 2843356 A US2843356 A US 2843356A
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US
United States
Prior art keywords
wheel
bucket
filler
turbine
dovetail
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 - Lifetime
Application number
US420835A
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English (en)
Inventor
Jr Thomas N Hull
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
Priority to BE537113D priority Critical patent/BE537113A/fr
Application filed by General Electric Co filed Critical General Electric Co
Priority to US420835A priority patent/US2843356A/en
Priority to FR1121732D priority patent/FR1121732A/fr
Priority to CH332271D priority patent/CH332271A/de
Application granted granted Critical
Publication of US2843356A publication Critical patent/US2843356A/en
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/326—Locking of axial insertion type blades by other means
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/027—Arrangements for balancing
    • 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
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/323—Locking of axial insertion type blades by means of a key or the like parallel to the axis of the rotor
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T74/00—Machine element or mechanism
    • Y10T74/21—Elements
    • Y10T74/2101—Cams
    • Y10T74/2102—Adjustable

Definitions

  • This invention relates to a high temperature turbomachine rotor assembly, particularly to such a rotor with dovetail type bucket fastenings used in a turbine which is subject to very high temperatures and frequent changes in load.
  • a further object is to provide a slotted rim high temperature bucket wheel with means for avoiding windage losses therethrough.
  • jA still further object is to provide a turbo-machine rotor with a balanoing means which can be easily and efficiently installed and removed;
  • Fig. l is a perspective viewshowing the turbine wheel containing the bucket and filler member and the bucket and filler member'before insertion intothe turbine wheel;
  • Fig. 2 is a front view partially in section showing the last bucket installed on the turbine wheel
  • Fig. 3 is a partial sectional view taken along line 3-3 of Fig. 2 illustrating the side view of the last bucket installed on the turbine wheel;
  • Fig. 4 illustrates the preliminaryand final position" of 2,843,356 Patented July 15, 1958 the bucket during installation. of the last bucket on the turbine wheel;
  • Fig. 5 is a sectional view showing the contour of the turbine wheel and conventional cooling means therefor.
  • the invention is practiced by providing a deep radial slot in the bucket wheel at the bottom of each dovetail groove to-allow therim to expand circumferentially, with special filler pieces to prevent substantialleakage of motive fluid through the slots.
  • a turbine wheel 1 is provided with an evenly spaced circumferential row of axially extending V-shaped dovetail grooves 2 (which areby way of example only), having serrations 3 extending along the sides of the V.
  • Located in each groove is a bucket having a. dovetail base. portion of substantially the same configuration as the dovetail grooves;
  • At the base of the V-shaped grooves there are cut comparative- 1y narrow and deep radial slots 4 which extend axially through the rim portion 1a of the bucket. wheel and radially across the high temperature rim portion 1a of wheel 1.
  • These slots allow thermal expansion to take place at the rim of the turbine wheel without setting up large thermal stresses. Such thermal stresses at the rim of the wheel, if not prevented, would have in time caused cracks to form at the bottom of the dovetail grooves which would have made eventual replacement of the wheel necessary.
  • the filler members 5 are inserted in the slots.
  • the filler member-5 is the same depth as the slot 4 but is very slightly narrower than the slot 4, to form the clearance space shown at 24 in Fig. 2, so as to allow for free thermal expansion of the rim portion 1a without creating excessive thermal stresses.
  • the bucket 6 is keyed to filler member .5 by means. of a groove 13in bucket 6 and tongue 14 on filler member 5.
  • the key means for connecting the bucket and filler plate assembly to the turbine wheel consists of cooperating recesses 7 and 8 in the turbine bucket and wheel respectively,. and keys 9 for insertion. into said. recesses.
  • Recesses 7 and 8 are substantially equal in length to the width of the land portion 23 of turbine Wheel 1 between V-sliaped grooves 2.
  • Thefiller member 5 is shown. ashaving. an internal cut out portion 10, for lightening the filler rnembeiz.
  • This cutout portion 10 can be of various depths as, fonexample, of a depth indicated by the line 11 if additional weight is needed to balance the. turbine wheels More specifically, there may be provided two sets of filler pieces, one set to the shape represented in full lines in Fig; l, and the other. to the modified shape representedv by. the broken line 11.
  • the filler'pieces may be made of different materials, having differing specific weights Then selective assembly of these various types. of filler pieces can be used tosecure proper dynamic balance. of the rotor.
  • the filler member 5 is shown as a solid piecebut can beconstructed of two or more pieces of sheet metal spot Welded together, or in any manner known to one skilled in the art.
  • the contour 12 of the tiller .plate. (see Fig; 5) is designed to conform to the shape of the turbine 3. wheel. This is desirable to allow for smooth flow of the cooling gases around the turbine wheel.
  • Figs. 2, 3 and 4 illustrates the means whereby the last bucket is secured against axial displacement.
  • the last bucket to be installed has on the underside of its base the recess 15.
  • this recess is in alignment with a 'radially extending circular hole 16 in the turbine wheel 1.
  • At the bottom of radial hole 16 there is an axially extending circular hole 17 leading from hole 16 to the side of the turbine wheel, the diameter of the hole 16 being substantially equal to the width of the recess 15 and the diameter of the hole 17 being substantially equal to the depth of recess 15.
  • the bucket.6 is placed adjacent the filler member 5 with tongue 14 fitting recess 13 and both are caused to slide axially into the dovetail groove 2 and slot 4, respectively, the class of fit between the bucket and the wheel beingsuch that the bucket is loosely secured to the wheel. This connection prevents radial displacement of the bucket.
  • the bucket is then secured against axial displacement by inserting key 9 in the cooperating recesses 7, 8. Then the second and successive buckets are similarly keyed to the wheel, with each succeeding bucket abutting against the previously installed key.
  • This method cannot be used for the last bucket since there is no way to insert the key 9. Therefore, the last bucket is installed in the following manner.
  • Pin 19 is first inserted radially into the hole 16, the pins dimensions being substantially the same as the hole 16 and beveled'at the bottom end, as shown at 19a in Fig. 4. The bucket is then slid into its dovetail groove,
  • the pin 18 may be held in place by any suitable method, as by peening an adjacent portion 'of the turbine wheel over the end of the pin, as shown at 20 in Fig. 3.
  • each filler member 5 define a substantially smooth continuation of the adjacent side surfaces of the turbine wheel so that when inserted into the radial slot.
  • the invention prevents high thermal stresses 1n the uncooled rim portion of a turbo- 4' machine rotor assembly with dovetail type bucket fastenings by the provision of deep radial slots at the bottom of each dovetail groove to allow the rim to expand circumferentially, relative to the cooled central portion of the wheel, while leakage of power fluid through the radial slots is substantially prevented by filler members loosely secured in each of the slots.
  • a turbine rotor provided with the inventions described herein has been in operation over 5,000 hours without thermal fatigue cracks developing at the base of the dovetail. This is roughly twice the length of service which in the past has produced cracks in rotors not incorporating the invention.
  • a wheel member having a rim portion defining a circumferential row 'of axially extending dovetail grooves, said rim portion also defining a slot extending axially through the rim at the bottom of each dovetail groove, said slot having a depth at least substantially that of the depth of the dovetail grooves and extending radially across the high temperature rim portion of the wheel, a plurality of buckets each having a dovetail base portion of substantially the same configuration as said dovetail grooves and disposed in one of said grooves, a filler member loosely disposed in. and substantially filling each of said slots to substantially prevent leakage of power fluid therethrough, and means preventing axial displacement of the filler member relative to the wheel.
  • a rotor assembly in accordance with claim 1 in which the means for preventing axial displacement of the filler member relative to the wheel comprises cooperating key means disposed between the bucket and filler member.
  • a rotor assembly in accordance with claim 1 in which at least two of the filler members are of different weights whereby the wheel may be dynamically balanced by selective assembly of the filler members.
  • a rotor assembly in accordance with claim 1 in which the exterior configuration of the filler member conforms to the exterior surface of the turbine wheel at the location of the slot, whereby the edges of the assembled filler pieces define a substantially smooth continuation of the adjacent side surfaces of the wheel to allow for smooth flow of gases around said wheel.
  • a wheel member having a rim portion defining a circumferential row of axially extending dovetail grooves, said rim portion .also defining a slot extending axially through the rim at the bottom of each dovetail groove, said slot extending radially across the high temperature rim portion of the wheel and having an over-all radial depth .on the order of /6 the radius of the wheel, a plurality of buckets each having a dovetail base portion of substantially the same configuration as said dovetail grooves and disposed in one of said grooves, a filler member loosely disposed in and substantially filling each of said slots to substantially prevent leakage of power fluid therethrough, said filler member having an exterior configuration which conforms to theexterior surface of the wheel 6.
  • a Wheel memher having a rim portion defining a circumferential row of axially extending dovetail grooves, said n'm portion also defining a slot extending axially through the rim at the bottom of each dovetail groove, said slot extending radially across the high temperature rim portion of the wheel, a plurality of buckets each having a dovetail base portion of substantially the same configu ration as said dovetail grooves and disposed in one of said grooves, a filler member loosely disposed in and substantially filling each of said slots to substantially prevent leakage of power fluid therethrough, each filler member having a central cutout portion, said cutout portions being of various depths whereby when a change in weight is needed for dynamic balance of the rotor at the place on the wheel where the filler member is inserted, the cutout portion can be of such a depth that the change in weight of the filler member will compensate for any dynamic unbalance of the rotor, and means

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US420835A 1954-04-05 1954-04-05 Turbo-machine rotor assembly Expired - Lifetime US2843356A (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
BE537113D BE537113A (id) 1954-04-05
US420835A US2843356A (en) 1954-04-05 1954-04-05 Turbo-machine rotor assembly
FR1121732D FR1121732A (fr) 1954-04-05 1955-04-01 Perfectionnement à la construction des roues de turbines
CH332271D CH332271A (de) 1954-04-05 1955-04-05 Rotor für Turbomaschinen

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US420835A US2843356A (en) 1954-04-05 1954-04-05 Turbo-machine rotor assembly

Publications (1)

Publication Number Publication Date
US2843356A true US2843356A (en) 1958-07-15

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Family Applications (1)

Application Number Title Priority Date Filing Date
US420835A Expired - Lifetime US2843356A (en) 1954-04-05 1954-04-05 Turbo-machine rotor assembly

Country Status (4)

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US (1) US2843356A (id)
BE (1) BE537113A (id)
CH (1) CH332271A (id)
FR (1) FR1121732A (id)

Cited By (33)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3199836A (en) * 1964-05-04 1965-08-10 Gen Electric Axial flow turbo-machine blade with abrasive tip
US3309058A (en) * 1965-06-21 1967-03-14 Rolls Royce Bladed rotor
US3867069A (en) * 1973-05-04 1975-02-18 Westinghouse Electric Corp Alternate root turbine blading
US4050850A (en) * 1975-01-30 1977-09-27 Bbc Brown Boveri & Company Limited Arrangement for locking parts into the rotor of a turbomachine
EP0055415A1 (en) * 1980-12-29 1982-07-07 Carrier Corporation A rotor assembly and methods of securing a rotor blade therewithin and removing a rotor blade therefrom
US4451959A (en) * 1980-12-29 1984-06-05 Elliott Turbomachinery Company, Inc. Methods for securing a rotor blade within a rotor assembly and removing a rotor blade therefrom
US4477226A (en) * 1983-05-09 1984-10-16 General Electric Company Balance for rotating member
US4527952A (en) * 1981-06-12 1985-07-09 S.N.E.C.M.A. Device for locking a turbine rotor blade
US4676723A (en) * 1986-03-26 1987-06-30 Westinghouse Electric Corp. Locking system for a turbine side entry blade
US4725200A (en) * 1987-02-24 1988-02-16 Westinghouse Electric Corp. Apparatus and method for reducing relative motion between blade and rotor in steam turbine
US4767247A (en) * 1987-02-24 1988-08-30 Westinghouse Electric Corp. Apparatus and method for preventing relative blade motion in steam turbine
US4767275A (en) * 1986-07-11 1988-08-30 Westinghouse Electric Corp. Locking pin system for turbine curved root side entry closing blades
US4898514A (en) * 1987-10-27 1990-02-06 United Technologies Corporation Turbine balance arrangement with integral air passage
US4915587A (en) * 1988-10-24 1990-04-10 Westinghouse Electric Corp. Apparatus for locking side entry blades into a rotor
FR2645902A1 (fr) * 1989-04-17 1990-10-19 Gen Electric Masselotte d'equilibrage sans boulons pour des rotors de turbine
EP0437977A1 (en) * 1990-01-18 1991-07-24 United Technologies Corporation Turbine rim configuration
US5242270A (en) * 1992-01-31 1993-09-07 Westinghouse Electric Corp. Platform motion restraints for freestanding turbine blades
US5425621A (en) * 1993-01-14 1995-06-20 Mtu Motoren- Und Turbinen-Union Muenchen Gmbh Device for axially securing moving blades and for eliminating rotor unbalances for axial-flow compressors or turbines
US5720596A (en) * 1997-01-03 1998-02-24 Westinghouse Electric Corporation Apparatus and method for locking blades into a rotor
US20090092494A1 (en) * 2007-10-04 2009-04-09 General Electric Company Disk rotor and method of manufacture
US20100183444A1 (en) * 2009-01-21 2010-07-22 Paul Stone Fan blade preloading arrangement and method
US20110229328A1 (en) * 2010-03-17 2011-09-22 Sudhir Rajagopalan Turbomachine Blade Locking Structure Including Shape Memory Alloy
US20120301298A1 (en) * 2011-05-23 2012-11-29 Rolls-Royce Plc Balancing of rotatable components
CN103195515A (zh) * 2012-01-05 2013-07-10 通用电气公司 用于涡轮的旋转节段的轴向固位的系统
US8485785B2 (en) 2007-07-19 2013-07-16 Siemens Energy, Inc. Wear prevention spring for turbine blade
US20140245752A1 (en) * 2013-01-02 2014-09-04 General Electric Company System and method for attaching a rotating blade in a turbine
JP2015513032A (ja) * 2012-03-07 2015-04-30 マン・ディーゼル・アンド・ターボ・エスイー ターボ機械のロータのためのインペラおよびこのようなインペラを備えるロータ並びにターボ機械
CN106015093A (zh) * 2016-07-13 2016-10-12 上海电气燃气轮机有限公司 一种压气机动叶轮盘的锁紧结构
EP3128131A1 (en) * 2015-08-03 2017-02-08 Doosan Heavy Industries & Construction Co., Ltd. Assembling method of turbine buckets and a fixture for turbine buckets
CN114215610A (zh) * 2021-12-01 2022-03-22 东方电气集团东方汽轮机有限公司 一种燃气轮机透平动叶轴向定位结构和安装拆解方法
US11927114B2 (en) * 2021-12-17 2024-03-12 Mitsubishi Heavy Industries Compressor Corporation Rotor of steam turbine, steam turbine, and method for fixing rotor blade
US12018590B1 (en) 2023-04-04 2024-06-25 Ge Infrastructure Technology Llc Method for turbine blade and assembly with dovetail arrangement for enlarged rotor groove
US12110809B1 (en) * 2023-04-04 2024-10-08 Ge Infrastructure Technology Llc Turbine blade and assembly with dovetail arrangement for enlarged rotor groove

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2949278A (en) * 1956-07-05 1960-08-16 Gen Motors Corp Turbine blade retention

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB166859A (en) * 1920-12-31 1921-07-28 James William Bradbeer Stokes Improvements in and relating to turbine wheels
US1619133A (en) * 1922-01-07 1927-03-01 Westinghouse Electric & Mfg Co Blade fastening
DE718939C (de) * 1936-08-09 1942-03-25 Rheinmetall Borsig Ag Gas- oder Dampfturbine
CH241993A (de) * 1944-07-19 1946-04-15 Sulzer Ag Läufer für Turbomaschinen.
GB609446A (en) * 1946-03-14 1948-09-30 Parsons C A & Co Ltd Improvements in or relating to the rotors of gas turbines or the like
GB643914A (en) * 1948-03-08 1950-09-27 Joseph Stanley Hall Improvements in and relating to turbine or like blade securing means
FR986022A (fr) * 1949-02-28 1951-07-26 Schneider & Cie Disque à aubes pour rotor de turbine dont le flux évolue à haute température
DE834408C (de) * 1950-11-23 1952-03-20 Maschf Augsburg Nuernberg Ag Vorverspannte axiale Schaufelfussbefestigung fuer Dampf- und Gasturbinen
US2686655A (en) * 1949-09-02 1954-08-17 Maschf Augsburg Nuernberg Ag Joint between ceramic and metallic parts
US2753149A (en) * 1951-03-30 1956-07-03 United Aircraft Corp Blade lock

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB166859A (en) * 1920-12-31 1921-07-28 James William Bradbeer Stokes Improvements in and relating to turbine wheels
US1619133A (en) * 1922-01-07 1927-03-01 Westinghouse Electric & Mfg Co Blade fastening
DE718939C (de) * 1936-08-09 1942-03-25 Rheinmetall Borsig Ag Gas- oder Dampfturbine
CH241993A (de) * 1944-07-19 1946-04-15 Sulzer Ag Läufer für Turbomaschinen.
GB609446A (en) * 1946-03-14 1948-09-30 Parsons C A & Co Ltd Improvements in or relating to the rotors of gas turbines or the like
GB643914A (en) * 1948-03-08 1950-09-27 Joseph Stanley Hall Improvements in and relating to turbine or like blade securing means
FR986022A (fr) * 1949-02-28 1951-07-26 Schneider & Cie Disque à aubes pour rotor de turbine dont le flux évolue à haute température
US2686655A (en) * 1949-09-02 1954-08-17 Maschf Augsburg Nuernberg Ag Joint between ceramic and metallic parts
DE834408C (de) * 1950-11-23 1952-03-20 Maschf Augsburg Nuernberg Ag Vorverspannte axiale Schaufelfussbefestigung fuer Dampf- und Gasturbinen
US2753149A (en) * 1951-03-30 1956-07-03 United Aircraft Corp Blade lock

Cited By (47)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3199836A (en) * 1964-05-04 1965-08-10 Gen Electric Axial flow turbo-machine blade with abrasive tip
US3309058A (en) * 1965-06-21 1967-03-14 Rolls Royce Bladed rotor
US3867069A (en) * 1973-05-04 1975-02-18 Westinghouse Electric Corp Alternate root turbine blading
US4050850A (en) * 1975-01-30 1977-09-27 Bbc Brown Boveri & Company Limited Arrangement for locking parts into the rotor of a turbomachine
EP0055415A1 (en) * 1980-12-29 1982-07-07 Carrier Corporation A rotor assembly and methods of securing a rotor blade therewithin and removing a rotor blade therefrom
US4400137A (en) * 1980-12-29 1983-08-23 Elliott Turbomachinery Co., Inc. Rotor assembly and methods for securing a rotor blade therewithin and removing a rotor blade therefrom
US4451959A (en) * 1980-12-29 1984-06-05 Elliott Turbomachinery Company, Inc. Methods for securing a rotor blade within a rotor assembly and removing a rotor blade therefrom
US4527952A (en) * 1981-06-12 1985-07-09 S.N.E.C.M.A. Device for locking a turbine rotor blade
US4477226A (en) * 1983-05-09 1984-10-16 General Electric Company Balance for rotating member
FR2545873A1 (fr) * 1983-05-09 1984-11-16 Gen Electric Dispositif d'equilibrage pour aube en queue d'aronde de rotor
US4676723A (en) * 1986-03-26 1987-06-30 Westinghouse Electric Corp. Locking system for a turbine side entry blade
US4767275A (en) * 1986-07-11 1988-08-30 Westinghouse Electric Corp. Locking pin system for turbine curved root side entry closing blades
US4725200A (en) * 1987-02-24 1988-02-16 Westinghouse Electric Corp. Apparatus and method for reducing relative motion between blade and rotor in steam turbine
US4767247A (en) * 1987-02-24 1988-08-30 Westinghouse Electric Corp. Apparatus and method for preventing relative blade motion in steam turbine
US4898514A (en) * 1987-10-27 1990-02-06 United Technologies Corporation Turbine balance arrangement with integral air passage
US4915587A (en) * 1988-10-24 1990-04-10 Westinghouse Electric Corp. Apparatus for locking side entry blades into a rotor
FR2645902A1 (fr) * 1989-04-17 1990-10-19 Gen Electric Masselotte d'equilibrage sans boulons pour des rotors de turbine
US5018943A (en) * 1989-04-17 1991-05-28 General Electric Company Boltless balance weight for turbine rotors
EP0437977A1 (en) * 1990-01-18 1991-07-24 United Technologies Corporation Turbine rim configuration
US5242270A (en) * 1992-01-31 1993-09-07 Westinghouse Electric Corp. Platform motion restraints for freestanding turbine blades
US5425621A (en) * 1993-01-14 1995-06-20 Mtu Motoren- Und Turbinen-Union Muenchen Gmbh Device for axially securing moving blades and for eliminating rotor unbalances for axial-flow compressors or turbines
US5720596A (en) * 1997-01-03 1998-02-24 Westinghouse Electric Corporation Apparatus and method for locking blades into a rotor
US8485785B2 (en) 2007-07-19 2013-07-16 Siemens Energy, Inc. Wear prevention spring for turbine blade
US20090092494A1 (en) * 2007-10-04 2009-04-09 General Electric Company Disk rotor and method of manufacture
US8182230B2 (en) 2009-01-21 2012-05-22 Pratt & Whitney Canada Corp. Fan blade preloading arrangement and method
US20100183444A1 (en) * 2009-01-21 2010-07-22 Paul Stone Fan blade preloading arrangement and method
US8496439B2 (en) 2010-03-17 2013-07-30 Siemens Energy, Inc. Turbomachine blade locking structure including shape memory alloy
US20110229328A1 (en) * 2010-03-17 2011-09-22 Sudhir Rajagopalan Turbomachine Blade Locking Structure Including Shape Memory Alloy
US20120301298A1 (en) * 2011-05-23 2012-11-29 Rolls-Royce Plc Balancing of rotatable components
US8974185B2 (en) * 2011-05-23 2015-03-10 Rolls-Royce Plc Balancing of rotatable components
US9051845B2 (en) * 2012-01-05 2015-06-09 General Electric Company System for axial retention of rotating segments of a turbine
EP2613000A3 (en) * 2012-01-05 2017-07-12 General Electric Company System for axial retention of rotating segments of a turbine and corresponding method
US20130177429A1 (en) * 2012-01-05 2013-07-11 General Electric Company System for axial retention of rotating segments of a turbine
CN103195515B (zh) * 2012-01-05 2016-08-17 通用电气公司 用于涡轮的旋转节段的轴向固位的系统
CN103195515A (zh) * 2012-01-05 2013-07-10 通用电气公司 用于涡轮的旋转节段的轴向固位的系统
JP2015513032A (ja) * 2012-03-07 2015-04-30 マン・ディーゼル・アンド・ターボ・エスイー ターボ機械のロータのためのインペラおよびこのようなインペラを備えるロータ並びにターボ機械
US9470092B2 (en) * 2013-01-02 2016-10-18 General Electric Company System and method for attaching a rotating blade in a turbine
US20140245752A1 (en) * 2013-01-02 2014-09-04 General Electric Company System and method for attaching a rotating blade in a turbine
EP3128131A1 (en) * 2015-08-03 2017-02-08 Doosan Heavy Industries & Construction Co., Ltd. Assembling method of turbine buckets and a fixture for turbine buckets
US10358930B2 (en) 2015-08-03 2019-07-23 DOOSAN Heavy Industries Construction Co., LTD Assembling method of a bucket and a fixture for a bucket for a turbine blade
CN106015093A (zh) * 2016-07-13 2016-10-12 上海电气燃气轮机有限公司 一种压气机动叶轮盘的锁紧结构
CN106015093B (zh) * 2016-07-13 2018-06-29 上海电气燃气轮机有限公司 一种压气机动叶轮盘的锁紧结构
CN114215610A (zh) * 2021-12-01 2022-03-22 东方电气集团东方汽轮机有限公司 一种燃气轮机透平动叶轴向定位结构和安装拆解方法
CN114215610B (zh) * 2021-12-01 2023-06-27 东方电气集团东方汽轮机有限公司 一种燃气轮机透平动叶轴向定位结构和安装拆解方法
US11927114B2 (en) * 2021-12-17 2024-03-12 Mitsubishi Heavy Industries Compressor Corporation Rotor of steam turbine, steam turbine, and method for fixing rotor blade
US12018590B1 (en) 2023-04-04 2024-06-25 Ge Infrastructure Technology Llc Method for turbine blade and assembly with dovetail arrangement for enlarged rotor groove
US12110809B1 (en) * 2023-04-04 2024-10-08 Ge Infrastructure Technology Llc Turbine blade and assembly with dovetail arrangement for enlarged rotor groove

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Publication number Publication date
CH332271A (de) 1958-08-31
BE537113A (id)
FR1121732A (fr) 1956-08-24

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