US3888601A - Turbomachine with balancing means - Google Patents

Turbomachine with balancing means Download PDF

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Publication number
US3888601A
US3888601A US472815A US47281574A US3888601A US 3888601 A US3888601 A US 3888601A US 472815 A US472815 A US 472815A US 47281574 A US47281574 A US 47281574A US 3888601 A US3888601 A US 3888601A
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US
United States
Prior art keywords
face
balance weight
extending
turbomachine
opposed
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
US472815A
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English (en)
Inventor
Larry Earl Glassburn
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General Electric Co
Original Assignee
General Electric Co
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Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Priority to US472815A priority Critical patent/US3888601A/en
Priority to GB13710/75A priority patent/GB1500575A/en
Priority to DE19752514947 priority patent/DE2514947A1/de
Priority to JP50043473A priority patent/JPS50150908A/ja
Priority to IT22871/75A priority patent/IT1037742B/it
Priority to FR7515984A priority patent/FR2272260B1/fr
Priority to BE156667A priority patent/BE829439A/xx
Application granted granted Critical
Publication of US3888601A publication Critical patent/US3888601A/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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/027—Arrangements for balancing
    • 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
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S416/00—Fluid reaction surfaces, i.e. impellers
    • Y10S416/50—Vibration damping features

Definitions

  • Means for balancing a turbomachine include a plurality of balance weights made readily removable and replaceable from a rotor wheel disc by providing 0pposed tang members extending from each balance weight for slidably engaging mating grooves cut into integral hook portions which overhang the periphery of the disc.
  • This invention relates to a turbomachine with balancing means and. more particularly, to a turbomachinc which may be balanced by a plurality of circumferentially spaced apart balance weights which are easily removed and replaced.
  • rotating machinery must be balanced so that the effects of centrifugal force are uniformly distributed around each rotating part.
  • An unbalanced condition within a revolving component may lead to severe vibration and fretting, thus drastically reducing the useful life of the component.
  • rotating components are generally balanced, both dynamically and statically, by the addition of discrete balance weights to the outer periphery thereof.
  • turbomachinery of the axial flow type there is generally included a rotor wheel disc which supports a plurality of circumferentially spaced apart rotor blades about the outer periphery.
  • Each of the blades includes an airfoil or vane section through which fluid may flow for either compression or extraction of work as is well known in the art.
  • the blades may also include root portions for insertion and retention within spaced apart grooves disposed about the periphery of the rotor wheel disc.
  • turbomachinery of this type it is common practice to leave a space between the bottom of the blade root and its associated groove for the insertion of small balance weights.
  • balance weights may also be retained relative to a bolting circle around the rotor wheel disc; however, this arrangement may also prove impractical due to the inability to readily remove and replace the balance weights.
  • the turbomachine of this invention includes a balancing means and comprises a rotating member having a plurality of circumferentially spaced apart, generally axially, extending grooves disposed about the outer periphery thereof.
  • a plurality of blade members each include root and airfoil vane portions wherein the root portions are received for retention within the grooves.
  • a plurality of circumferentially spaced apart integral hook portions extend from the side of the rotating member such that each integral 2 hook portion has two opposed generally radially extending sidewalls, each one of which is intersected by a generally radially extending groove.
  • a plurality of balance weights are provided wherein each one of the balance weights has a pair of longitudinal and transverse faces intersected by a top and bottom face together with a pair of oppositely projecting tang members wherein each tang member extends from an opposing longitudinal face for engagement within a respective radially extending groove.
  • a snap ring is also provided for insertion between the hook portions and the rotating member for engagement with the bottom faces of the balance weights.
  • FIG. I is a partial perspective view in cross-section of the turbomachine and balancing means of this invention.
  • FIG. 2 is a partial cross-sectional view taken along the line 2-2 of FIG. 1.
  • FIGv 3 is a perspective view ofa single balance weight as may be used to balance the turbomachinc of FIG. 1.
  • FIG. 4 is a side view of the balance weight of FIG. 3.
  • FIG. 5 is a top view of the balance weight of FIG. 3.
  • the blade supporting structure comprises a rotor wheel disc indicated generally at 10 having an enlarged rim portion 12 and a pair of oppositely directed (axially of the rotor) faces 14 and 16. Extending through the rim portion in a generally axial direction relative to the rotor are a plurality of eircumferentially spaced apart blade receiving grooves indicated at 18. These grooves.
  • the grooves also include a wide base or bottom 24.
  • the rotor disc I0 includes a plurality of circumferentially spaced apart rotor blades or vanes 26 disposed about its periphery. Each of the rotor blades 26 ineludes an airfoil vane section 28 through which gas may flow for either compression or extraction of work in a manner well known to the art.
  • the blades 26 include platforms 32 from which root portions 30 extend in substantially inward radial directions wherein the platforms 32 generally overhang the root portions.
  • Each root portion 30 is thickened at the inner radial end to provide outwardly extending shoulders with oppositely directed. longitudinally extending, faces 34, 36.
  • the root portions 30 also include opposed transverse end faces 38, 40, together with a bottom portion 42.
  • the tables 28 are radially and circumferentially retained in a conventional manner by axial insertion of the root portions 30 within the blade receiving grooves 18, such that the oppositely directed, longitudinally extending faces 34, 36 respectively engage the longitudinally extending angled sidewalls 22, 23 of the blade receiving grooves.
  • the general overall shape of the rotor wheel disc 10 or blade receiving grooves 18 corresponds to the shape of the root portions 30 with a slight clearance between the bottom portion 42 of the blade roots and the base 24 of the grooves.
  • the longitudinally extending faces 34, 36 of the blade roots are shaped to abut and be retained against centrifugal force by the longitudinally extending angled sidewalls 22, 23 of the rotor wheel grooves 18.
  • the means for retaining rotor blades herein described is conventional and well known to the art.
  • each integral hook portion 44 has two opposed generally radially extending sidewalls 48, 50 in general respective coplanar alignment with the sidewalls 20, 21 of the blade receiving grooves.
  • Each pair of opposed sidewalls 48, 50 is respectively intersected by a pair of radially extending grooves 52, 54 for receipt of a balance weight 56 in a manner to be more fully described in the following discussion.
  • the grooves 52, 54 are illustrated as having one edge coincident with the intersection between the sidewalls 20, 21 and the rotor wheel disc face 14. However, it should be readily apparent that the grooves do not necessarily have to be arranged in this manner and may alternatively be spaced forward of the rotor wheel disc face 14.
  • FIGS. 3 through 5 there is shown an enlarged view of a single balance weight 56, which has two longitudinally extending faces 58, 60, together with two opposed transverse end faces 62, 64.
  • the longitudinal and transverse faces are intersected by a bottom face 66 and a top face 68 which respectively define the inner and outer radial limits of the balance weight 56.
  • a pair of oppositely projecting tang members 70, 72 extend respectively from the two longitudinally extending faces 58, 60, wherein the top of the tang members 70, 72 are intersected by an oblique face 74.
  • each tang member 70, 72 is illustrated as being coincident with the transverse end face 62; however, it should be readily apparent that the tangs do not necesssarily have to be arranged in this manner and may alternatively be spaced apart from the end face 62.
  • a transverse notch 76 extends between the opposed tang members 70, 72 and intersects the transverse end face 62, together with the bottom face 66.
  • each balance weight is thereafter inserted between the integral hook portions 44 by first bringing the transverse end face 62 of the balance weight into near engagement with the face 14 of the rotor wheel disc at a position underlying the space between a pair of adjacent integral hook portions.
  • the balance weight 56 must then be circumferentially aligned so that the tang members 70, 72 slidingly engage respective grooves 52, 54 upon outward radial movement of the balance weight.
  • the balance weight 56 can then be pushed radially outward into abutting engagement with the interior surface of the blade platform 32.
  • the balance weight 56 is retained from further outward radial movement during centrifugal loading by engagement of the top face 68 with the interior surface of the blade platform 32.
  • Axial movement is restrained by the engagement of the tangs 70, 72, within the grooves 52, 54 while circumferential movement is constrained by engagement of the two longitudinally extending faces 58, 60 between the radially extending sidewalls 48, 50.
  • a snap ring 78 must then be provided for insertion intermediate the overlapping lip portions 76 of the integral hooks 44 and the face 14 of the rotor wheel disc 10.
  • the top of the snap ring 78 engages the top of the notch 76 thereby restraining the individual balance weights 56 from moving radially inward when the rotor wheel disc 10 is stationary.
  • the balance weights 56 may be removed and replaced in an expeditious manner by simply removing the snap ring 78 and thereafter sliding the balance weights radially inward out of engagement with the groovess 52, 54.
  • a new balance weight may thereafter be inserted in like manner after which the snap ring 78 may be reinstalled in a conventional manner.
  • Various numerical weights may be provided for the balance weight 56 by simply adjusting the length of the longitudinally extending faces 58, 60 as indicated by the dimension A.
  • the individual rotor blades are restrained from forward axial translation out of the grooves 18 by the engagement of the end faces 38 with respect to the transverse end faces 62 of the balance weights.
  • Rearward axial translation of the individual rotor blades 26 out of their respective grooves 18 may be restrained in a conventional manner by a second snap ring 82 engaged by a second integral hook portion 80 extending from the rim portion 12.
  • the oblique surface 74 of the balance weight 56 may be eliminated along with the notch 76 whereupon the bottom face 66 of the balance weight would then be engaged by the top of the snap ring 78.
  • the blade receiving grooves 18 may be skewed in relation to the faces 14, 16 of the rotor wheel disc. In like manner, the longitudinal faces 58.
  • a turbomachine with means for balancing thereof comprising:
  • a rotating member having a plurality of circumferentially spaced apart, generally axially, extending grooves disposed about the outer periphery thereof;
  • each integral hook portion has two opposed generally radially extending sidewalls, each one of which is intersected by a generally radially extending groove;
  • balance weights each one of which has a pair of longitudinal and transverse faces intersected by a top and bottom face together with a pair of oppositely projecting tang members wherein each tang member extends from an opposing longitudinal face for engagement within a respective radially extending groove;
  • the blade members include platforms intermediate the airfoil vane portions and root portions wherein the platforms generally overhang the root portions and engage the tops of the balance weights so as to prevent outward radial movement of the balance weights during centrifugal loading.
  • the generally axially extending grooves are of the dovetail type, each having a pair of sidewalls, the inner ends of which are undercut to provide longitudinally extending angled sidewalls which operate as inwardly directed abutment faces, and
  • each blade root portion is thickened at the inner radial end to provide outwardly extending shoulders with oppositely directed longitudinally extending faces for respective engagement with the longitudinally extending angled sidewalls of the axial grooves wherein the two opposed generally radially extending sidewalls of the integral hook portions are in general respective coplanar alignment with the sidewalls of the blade receiving grooves.
  • the rotating member comprises a rotor wheel disc having an enlarged rim portion and a pair of oppositely directed faces;
  • each radially extending groove has an edge coincident with the intersection between a sidewall of the axially extending groove and a face of the rotor wheel disc;
  • one edge of both of the opposed tang members of a balance weight is coincident with a transverse end face of that balance weight.
  • each balance weight is intersected by an oblique face extending between the top face and a transverse end face of the balance weight;
  • a transverse notch extends between the bottom of the opposed tang members of each balance weight intersecting the same transverse end face as well as the bottom face of the balance weight such that the snap ring may engage the notch after the tangs of the balance weight are inserted within the radially extending grooves.
  • a balance weight for a turbomachine comprising a pair of longitudinal and transverse faces intersected by a top and bottom face together with a pair of oppositely projecting tang members wherein each tang member extends from an opposing longitudinal face.
  • the top of the opposed tang members of the balance weight are intersected by an oblique face extending between the top face and a transverse end face of the balance weight;
  • a transverse notch extends between the bottom of the opposed tang members of the balance weight intersecting the same transverse end face as well as the bottom face of the balance weight.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US472815A 1974-05-23 1974-05-23 Turbomachine with balancing means Expired - Lifetime US3888601A (en)

Priority Applications (7)

Application Number Priority Date Filing Date Title
US472815A US3888601A (en) 1974-05-23 1974-05-23 Turbomachine with balancing means
GB13710/75A GB1500575A (en) 1974-05-23 1975-04-03 Turbomachine with balancing means
DE19752514947 DE2514947A1 (de) 1974-05-23 1975-04-05 Turbomaschine mit auswuchtvorrichtung
JP50043473A JPS50150908A (no) 1974-05-23 1975-04-11
IT22871/75A IT1037742B (it) 1974-05-23 1975-04-30 Sistema di bilanciamento di turbina
FR7515984A FR2272260B1 (no) 1974-05-23 1975-05-22
BE156667A BE829439A (fr) 1974-05-23 1975-05-23 Turbomachine munie d'un dispositif d'equilibrage

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US472815A US3888601A (en) 1974-05-23 1974-05-23 Turbomachine with balancing means

Publications (1)

Publication Number Publication Date
US3888601A true US3888601A (en) 1975-06-10

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Family Applications (1)

Application Number Title Priority Date Filing Date
US472815A Expired - Lifetime US3888601A (en) 1974-05-23 1974-05-23 Turbomachine with balancing means

Country Status (7)

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US (1) US3888601A (no)
JP (1) JPS50150908A (no)
BE (1) BE829439A (no)
DE (1) DE2514947A1 (no)
FR (1) FR2272260B1 (no)
GB (1) GB1500575A (no)
IT (1) IT1037742B (no)

Cited By (40)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4033705A (en) * 1976-04-26 1977-07-05 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Blade retainer assembly
DE2841130A1 (de) * 1977-09-23 1979-04-05 Snecma Vorrichtung zum beseitigen der unwucht eines rotors
US4221542A (en) * 1977-12-27 1980-09-09 General Electric Company Segmented blade retainer
US4275990A (en) * 1977-12-17 1981-06-30 Rolls-Royce Limited Disc channel for cooling rotor blade roots
WO1982001216A1 (en) * 1980-10-02 1982-04-15 United Technologies Corp Blade to blade vibration damper
US4344740A (en) * 1979-09-28 1982-08-17 United Technologies Corporation Rotor assembly
US4355957A (en) * 1981-06-18 1982-10-26 United Technologies Corporation Blade damper
US4477226A (en) * 1983-05-09 1984-10-16 General Electric Company Balance for rotating member
USRE32339E (en) * 1980-10-02 1987-01-27 United Technologies Corporation Blade to blade vibration damper
US4732532A (en) * 1979-06-16 1988-03-22 Rolls-Royce Plc Arrangement for minimizing buzz saw noise in bladed rotors
US4803893A (en) * 1987-09-24 1989-02-14 United Technologies Corporation High speed rotor balance system
US4848182A (en) * 1987-09-08 1989-07-18 United Technologies Corporation Rotor balance system
US4890981A (en) * 1988-12-30 1990-01-02 General Electric Company Boltless rotor blade retainer
US4898514A (en) * 1987-10-27 1990-02-06 United Technologies Corporation Turbine balance arrangement with integral air passage
US4926710A (en) * 1987-09-08 1990-05-22 United Technologies Corporation Method of balancing bladed gas turbine engine rotor
FR2645902A1 (fr) * 1989-04-17 1990-10-19 Gen Electric Masselotte d'equilibrage sans boulons pour des rotors de turbine
US5049035A (en) * 1988-11-23 1991-09-17 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Bladed disc for a turbomachine rotor
US5151013A (en) * 1990-12-27 1992-09-29 United Technologies Corporation Blade lock for a rotor disk and rotor blade assembly
EP0609979A1 (en) * 1993-02-03 1994-08-10 ROLLS-ROYCE plc Balanced rotor for a gas turbine engine
US5350279A (en) * 1993-07-02 1994-09-27 General Electric Company Gas turbine engine blade retainer sub-assembly
US5582077A (en) * 1994-03-03 1996-12-10 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" System for balancing and damping a turbojet engine disk
EP1074762A2 (en) * 1999-08-05 2001-02-07 General Electric Company Apparatus and method for rotor damping
US6390777B1 (en) 1999-09-01 2002-05-21 Angelo Fan Brace Licensing, L.L.C. Quick-connect fan blade mounting assembly
US20030194318A1 (en) * 2002-04-16 2003-10-16 Duesler Paul W. Axial retention system and components thereof for a bladed rotor
US20040202544A1 (en) * 2003-04-08 2004-10-14 Henning Thomas Richard Methods and apparatus for assembling rotatable machines
JP2005220908A (ja) * 2004-02-06 2005-08-18 Snecma Moteurs ロータディスク平衡装置、そのような装置が取り付けられたディスク、およびそのようなディスクが取り付けられたロータ
US20050244272A1 (en) * 2003-10-14 2005-11-03 Vittorio Bruno Rotor balancing device and method
US20060153684A1 (en) * 2005-01-10 2006-07-13 Henning Thomas R Methods and apparatus for assembling rotatable machines
US20070148002A1 (en) * 2005-12-22 2007-06-28 Pratt & Whitney Canada Corp. Turbine blade retaining apparatus
US20090004018A1 (en) * 2007-06-27 2009-01-01 Snecma Device for axially retaining blades mounted on a turbomachine rotor disk
US20090022593A1 (en) * 2006-03-13 2009-01-22 Ihi Corporation Fan blade retaining structure
DE102007059220A1 (de) * 2007-12-07 2009-06-10 Rolls-Royce Deutschland Ltd & Co Kg Leitschaufelkranz für thermische Strömungsmaschinen, insbesondere Flugtriebwerke
FR2939832A1 (fr) * 2008-12-11 2010-06-18 Turbomeca Roue de turbine equipee d'un dispositif de retenue axiale verrouillant des pales par rapport a un disque.
KR20120092125A (ko) * 2009-10-13 2012-08-20 터보메카 디스크에 관하여 블레이드를 로크하는 축방향 유지 링이 장착된 터빈 휠
US20140140849A1 (en) * 2012-11-21 2014-05-22 Solar Turbines Incorporated Gas turbine engine compressor rotor assembly and balancing system
US20140193265A1 (en) * 2013-01-04 2014-07-10 Snecma Rotor disk including a plurality of hooks
EP3006667A1 (de) * 2014-10-09 2016-04-13 Siemens Aktiengesellschaft Turbinenlaufschaufel, Anordnung aus einer Turbinenwelle, einer Turbinenradscheibe, einer Vielzahl an Turbinenlaufschaufeln sowie einem Wuchtgewicht und Turbine
US10436224B2 (en) 2016-04-01 2019-10-08 General Electric Company Method and apparatus for balancing a rotor
US20200056482A1 (en) * 2018-08-14 2020-02-20 United Technologies Corporation Dovetail weight system for rotor balance
CN112160794A (zh) * 2020-09-18 2021-01-01 中国航发四川燃气涡轮研究院 定位组件及其涡轮盘或压气机盘、航空发动机

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2499652A1 (fr) * 1981-02-11 1982-08-13 Snecma Dispositif de correction de balourd de rotor de turbomachines
GB2250783B (en) * 1990-11-03 1995-01-04 Papst Motoren Gmbh & Co Kg Improvements in or relating to fan impellers
RU2516722C1 (ru) * 2012-11-15 2014-05-20 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения им. П.И. Баранова" Ротор с компенсатором дисбаланса
RU209925U1 (ru) * 2021-12-27 2022-03-23 Публичное Акционерное Общество "Одк-Сатурн" Узел ротора турбины большой мощности

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US2836392A (en) * 1953-06-03 1958-05-27 United Aircraft Corp Disc vibration damping means
US2957675A (en) * 1956-05-07 1960-10-25 Gen Electric Damping means
US2999668A (en) * 1958-08-28 1961-09-12 Curtiss Wright Corp Self-balanced rotor blade
US3034764A (en) * 1959-12-18 1962-05-15 Gen Electric Damping means
US3129921A (en) * 1962-07-06 1964-04-21 United Aircraft Corp Blade damping device
US3181835A (en) * 1964-01-07 1965-05-04 Carroll C Davis Blade vibration damping device
US3341174A (en) * 1967-02-27 1967-09-12 United Aircraft Corp Blade lock

Patent Citations (7)

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Publication number Priority date Publication date Assignee Title
US2836392A (en) * 1953-06-03 1958-05-27 United Aircraft Corp Disc vibration damping means
US2957675A (en) * 1956-05-07 1960-10-25 Gen Electric Damping means
US2999668A (en) * 1958-08-28 1961-09-12 Curtiss Wright Corp Self-balanced rotor blade
US3034764A (en) * 1959-12-18 1962-05-15 Gen Electric Damping means
US3129921A (en) * 1962-07-06 1964-04-21 United Aircraft Corp Blade damping device
US3181835A (en) * 1964-01-07 1965-05-04 Carroll C Davis Blade vibration damping device
US3341174A (en) * 1967-02-27 1967-09-12 United Aircraft Corp Blade lock

Cited By (60)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4033705A (en) * 1976-04-26 1977-07-05 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Blade retainer assembly
DE2841130A1 (de) * 1977-09-23 1979-04-05 Snecma Vorrichtung zum beseitigen der unwucht eines rotors
FR2404212A1 (fr) * 1977-09-23 1979-04-20 Snecma Dispositif d'equilibrage d'un rotor
US4275990A (en) * 1977-12-17 1981-06-30 Rolls-Royce Limited Disc channel for cooling rotor blade roots
US4221542A (en) * 1977-12-27 1980-09-09 General Electric Company Segmented blade retainer
US4732532A (en) * 1979-06-16 1988-03-22 Rolls-Royce Plc Arrangement for minimizing buzz saw noise in bladed rotors
US4344740A (en) * 1979-09-28 1982-08-17 United Technologies Corporation Rotor assembly
USRE32339E (en) * 1980-10-02 1987-01-27 United Technologies Corporation Blade to blade vibration damper
WO1982001216A1 (en) * 1980-10-02 1982-04-15 United Technologies Corp Blade to blade vibration damper
US4347040A (en) * 1980-10-02 1982-08-31 United Technologies Corporation Blade to blade vibration damper
US4355957A (en) * 1981-06-18 1982-10-26 United Technologies Corporation Blade damper
US4477226A (en) * 1983-05-09 1984-10-16 General Electric Company Balance for rotating member
US4848182A (en) * 1987-09-08 1989-07-18 United Technologies Corporation Rotor balance system
US4926710A (en) * 1987-09-08 1990-05-22 United Technologies Corporation Method of balancing bladed gas turbine engine rotor
US4803893A (en) * 1987-09-24 1989-02-14 United Technologies Corporation High speed rotor balance system
US4898514A (en) * 1987-10-27 1990-02-06 United Technologies Corporation Turbine balance arrangement with integral air passage
US5049035A (en) * 1988-11-23 1991-09-17 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Bladed disc for a turbomachine rotor
US4890981A (en) * 1988-12-30 1990-01-02 General Electric Company Boltless rotor blade retainer
US5018943A (en) * 1989-04-17 1991-05-28 General Electric Company Boltless balance weight for turbine rotors
FR2645902A1 (fr) * 1989-04-17 1990-10-19 Gen Electric Masselotte d'equilibrage sans boulons pour des rotors de turbine
US5151013A (en) * 1990-12-27 1992-09-29 United Technologies Corporation Blade lock for a rotor disk and rotor blade assembly
EP0609979A1 (en) * 1993-02-03 1994-08-10 ROLLS-ROYCE plc Balanced rotor for a gas turbine engine
US5350279A (en) * 1993-07-02 1994-09-27 General Electric Company Gas turbine engine blade retainer sub-assembly
US5582077A (en) * 1994-03-03 1996-12-10 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" System for balancing and damping a turbojet engine disk
EP1074762A2 (en) * 1999-08-05 2001-02-07 General Electric Company Apparatus and method for rotor damping
US6494679B1 (en) * 1999-08-05 2002-12-17 General Electric Company Apparatus and method for rotor damping
EP1074762A3 (en) * 1999-08-05 2003-12-17 General Electric Company Apparatus and method for rotor damping
US6390777B1 (en) 1999-09-01 2002-05-21 Angelo Fan Brace Licensing, L.L.C. Quick-connect fan blade mounting assembly
US20030194318A1 (en) * 2002-04-16 2003-10-16 Duesler Paul W. Axial retention system and components thereof for a bladed rotor
US6951448B2 (en) * 2002-04-16 2005-10-04 United Technologies Corporation Axial retention system and components thereof for a bladed rotor
US6908285B2 (en) 2003-04-08 2005-06-21 General Electric Company Methods and apparatus for assembling rotatable machines
US20040202544A1 (en) * 2003-04-08 2004-10-14 Henning Thomas Richard Methods and apparatus for assembling rotatable machines
US20050244272A1 (en) * 2003-10-14 2005-11-03 Vittorio Bruno Rotor balancing device and method
US6976827B2 (en) 2003-10-14 2005-12-20 Pratt & Whitney Canada Corp. Rotor balancing device and method
US7347672B2 (en) 2004-02-06 2008-03-25 Snecma Moteurs Rotor disk balancing device, disk fitted with such a device and rotor with such a disk
US20050191181A1 (en) * 2004-02-06 2005-09-01 Snecma Moteurs Rotor disk balancing device, disk fitted with such a device and rotor with such a disk
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Also Published As

Publication number Publication date
DE2514947A1 (de) 1975-12-11
GB1500575A (en) 1978-02-08
FR2272260A1 (no) 1975-12-19
FR2272260B1 (no) 1979-03-30
IT1037742B (it) 1979-11-20
BE829439A (fr) 1975-09-15
JPS50150908A (no) 1975-12-04

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