EP0214875A1 - Dämpfungselement zur Begrenzung der Auslenkung von Rotorschaufeln einer Turbomaschine - Google Patents

Dämpfungselement zur Begrenzung der Auslenkung von Rotorschaufeln einer Turbomaschine Download PDF

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Publication number
EP0214875A1
EP0214875A1 EP86401518A EP86401518A EP0214875A1 EP 0214875 A1 EP0214875 A1 EP 0214875A1 EP 86401518 A EP86401518 A EP 86401518A EP 86401518 A EP86401518 A EP 86401518A EP 0214875 A1 EP0214875 A1 EP 0214875A1
Authority
EP
European Patent Office
Prior art keywords
flange
disc
rotor
blade
rotor disc
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.)
Granted
Application number
EP86401518A
Other languages
English (en)
French (fr)
Other versions
EP0214875B1 (de
Inventor
Denis Claude Charreron
Patrick Louis Eugène Girault
Jean Victor Firmin Reboul
Jacques Marie Pierre Stenneler
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.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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 Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0214875A1 publication Critical patent/EP0214875A1/de
Application granted granted Critical
Publication of EP0214875B1 publication Critical patent/EP0214875B1/de
Expired 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
    • 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

Definitions

  • the technical sector of the present invention is that of turbomachinery and more specifically means for fixing and limiting the angular displacement of the rotor blades.
  • vanes are fixed in a known manner to the periphery of a rotor disc and traditionally comprise, under a platform and separated from it by a stilt, a foot in the shape of a fir tree or in dovetail coming to be housed in a corresponding groove of the rotor disc.
  • a stilt for mounting reasons, when the blades are fins or peripheral heels, the designer is required to provide a large space between the foot of the blade and the bottom of the groove; This space is occupied by an axial shim which ensures correct positioning of the blade root in the grooves.
  • vanes of this type are therefore susceptible at rest to a relatively large angular deflection on either side of the radial plane comprising the major axis of the blade, this deflection being maintained at a value given by the clearance calculated between the plates -forms of adjacent blades.
  • the energy of the impact may be sufficient to lead to partial fragmentations of one or more blades, or even to their complete rupture, which also leads to destructures of the compressor stages downstream
  • patent FR 2 286 282 which shows rotor blades the platform of which is placed on the edges of a cage, the latter being formed by two flanges, one upstream, the 'other downstream connected to each other by narrow axial bars arranged under the platforms in a space out of two left free between the stilts, the blade root being threaded in a groove of the disc and the cage screwed onto the rotor disc.
  • Such a device where the blade root is not wedged in its groove has the drawbacks of allowing a significant rotation of the blade in the groove of the disc and of favoring significant vibrational phenomena between the blades and the cage on which rests platforms.
  • these devices fulfill an anti-vibration function by limiting the radial displacement of the blades, they generally do not prevent the angular movement of the latter under the effect of a shock. In addition, these devices cannot absorb the energy of the impact on a blade to transmit it and distribute it, for example over an entire disk sector where this energy would be dissipated.
  • One of the aims of the invention is therefore to limit in operation the angular movement of a blade of rotor of a turbojet engine, in particular of a fan or low pressure compressor blade and more particularly of a blade with side fins, in order to prevent the risk of overlapping of the fins under the effect of an accidental impact.
  • Another object of the invention is to provide a device which is able to withstand the energy of the shock suffered by a dawn, during an accidental ingestion of a bird in flight for example and to absorb this impact by making the 'force undergone by the disc-drum connection by a specific flange of the disc or the drum, according to a variant of the invention or by the two or three blades adjacent to that which has been impacted, according to another variant.
  • An additional object of the invention is to present a device which, in addition to the advantages mentioned above, allows the damping of vibrations undergone by the blades.
  • the invention also aims in an alternative embodiment to provide a simple means having the advantages cited and adapted to be adapted on existing rotor discs and requiring only modifications of detail of the rotor discs, easily executable in a maintenance workshop and does not require long and costly downtime of the turbojet.
  • the subject of the invention is therefore a device for limiting the auger deflection of turbine engine rotor blades of the type comprising a series of radial blades mounted on the periphery of a rotor disc, the blades comprising under a platform a separate stand of the platform by a stilt, the foot being received in a groove around the rotor disc, two adjacent grooves defining between them an ear of the disc.
  • the device comprises wedging means arranged between each pair of adjacent blades radially as high as possible on the stilt of each blade, the adjustment calculated between the wedging means and the two adjacent stilts being able to limit the angular movement of each blade around its longitudinal axis to its maximum value tolerated in autorotation.
  • the wedging means are integral with an intermediate connecting means fixed on the rotor disc and able to absorb part of the force undergone by a blade during an accidental impact and to distribute it over a angular sector of the rotor.
  • the intermediate connection means is constituted by an annular flange comprising a planar radial extension, the flange being arranged downstream of the disc and made integral with the latter and the wedging means are constituted by extensions of the radial extension of the flange, said extensions being of rectangular cross section arranged parallel to the axis of rotation of the rotor in the free spaces between each pair of adjacent stilts and produced in a single piece with said plane radial extension of the flange , the width of each of the extensions being substantially equal to that of the free space between the stilts.
  • FIG. 1 and 2 there is shown schematically a fan blade 1 with stilt 2 comprising a platform 3 whose heel 4 is mounted with play in a known manner in a groove 5 of the rotor disc 6.
  • the blade stub 4 has its faces 8 pressed by centrifugal force against the faces 9 of the upper part of the groove 5.
  • the side faces 10 of the platforms 3 of the adjacent blades as well as the faces lateral 11 of the fins 12 are substantially in contact with one another.
  • the device comprises wedging means constituted by teeth 13 carried by an intermediate connecting means 14.
  • the latter is produced in the form of a downstream annular flange comprising a planar radial circular extension 14 on the inner periphery of which are made bores 15 which allow mounting downstream of the disc 6 and the flange 16 which connects the blower stage to the first rotor stage of the low pressure compressor.
  • the disc 6, the flange 16 and the flange 14 are secured between by bolts 17 passing through the ears 18 of the disc, the bores of the flange and the bores 15 of the downstream flange constituting the intermediate connection means.
  • the teeth 13 constituting the wedging means are produced in the form of upstream extensions of the planar radial extension of the flange 14, these teeth having a substantially rectangular cross section and being arranged parallel to the axis of rotation of the rotor or, if the platform 3 is strongly inclined upstream, as shown in Figures 1 and 2, parallel to the underside of the platform.
  • These teeth 13 positioned as high as possible on the stilt fit into the space left free between the stilts, the clearance between the stilts and the tooth being calculated as small as possible in order to limit the angular movement of the blade at its maximum permissible value in autorotation.
  • the cross section of the teeth 13, the thickness of the flange 14 and the bore 15 made without play with the bolt 17 are dimensioned to give the flange a structure strong enough to transmit and resume by the bolts disc-flange connection, the force undergone by a blade during an accidental impact.
  • the flange 14 also fulfills a function of damping the vibrations undergone by the blades. To do this, it comprises on the periphery of its planar radial extension a frustoconical extension 19 inclined downstream comprising an inclined circular bearing 20 having a curvature corresponding to that of the lower downstream face 21 of the platform 3.
  • a frustoconical extension 19 inclined downstream comprising an inclined circular bearing 20 having a curvature corresponding to that of the lower downstream face 21 of the platform 3.
  • the travel limiting device provides a sealing function because it prevents recirculation between stilts.
  • the flange is arranged between the disc and the drum, or behind the flange of the drum, it will be made up of one or two semi-circular parts.
  • the flange 14 is produced in a single annular piece and disposed between the disc 6 and the flange 16, its overall structure (teeth 13 of angular setting and damping by bearing support 20 under the platform) remaining identical with the previously described variant.
  • FIG 4 there is shown another embodiment of the downstream annular flange comprising the wedging means according to the invention.
  • the flange 14 ' is not fixed to the disc by tightening bolts. It consists of a simple flat annular bearing 14 ′ carrying the teeth 13 and is centered on the external circular face 23 of the flange 16.
  • a circular groove 24 makes it possible, by a judicious adaptation of the manufacturing tolerances, to keep the flange 14 ′ axially clamped, between the two flanges of the disc-drum connection.
  • the recovery of the force undergone by a blade is effected by the adjacent blades, the whole of the flange 14 ′ moving when the blade receiving the shock strikes the tooth. 13 neighbor.
  • this embodiment allows the force to be absorbed on two or three blades because the forces are fully taken up by the adjacent blades without overloading the disc and the drum.
  • FIG. 5 there is shown schematically in perspective another embodiment of the invention seen downstream of the rotor disc.
  • the wedging means and the intermediate connecting means consist of jumpers 30 in the shape of a "U" arranged astride the upper part of each ear 18 of the disc, the base of the U constituting the means of intermediate link and being fixed to the lugs 18 by the bolts 17 of the 6-flange disc link 16 (not shown in FIG. 5), while the branches 31 of the U constitute the wedging means according to the invention. It is already known to take up the forces undergone by the blades directly by the ears of the disc, these being machined so that the clearance between them and the stilts is low enough to limit the deflection of the blades.
  • the jumpers make it possible to solve these problems because their machining is easier than that of the cells of the disc and because they allow a better limitation of the clearance because it is possible to position them very high on the ear of the disc, this being due to the dissociation of the function of limitation of clearance relative to the disc in comparison with the previous solution of direct limitation by the ears of the disc.
  • the base 30 of the rider is arranged on the upstream face of the ear 18, the lateral faces 32 of which are milled to the internal dimension of the rider. It can be seen in FIG. 5 that the usual inclination of the lateral faces 33 would allow, in the absence of a jumper, an angular movement 2 ⁇ at the stilt 2 of the blade 1.
  • the judicious choice of the thickness "e" of the branches 31 of the rider makes it possible to limit the angular movement of the blade 1 to a value at most equal to its maximum authorized value in self-rotation.
  • the advantage of such a wedging means is that it can easily be adapted to an existing rotor disc, by simple machining of the lateral faces of the lugs 32 of the rotor disc 6, which can be easily carried out in a maintenance workshop without immobilization. excessive motor and without special or complex tools.
  • This embodiment of the angular movement limitation means according to the invention therefore constitutes an improvement which is simple to implement and inexpensive to the blower or low pressure compressor rotors of existing turbomachines.
  • the counterweight 34 has on its periphery a longitudinal groove 37 cooperating with a lug 38 of the sheath 35 to allow the counterweight only one degree of freedom in radial sliding so that the counterweight is pressed under the platform 3 by the centrifugal force during the rotation of the rotor and comes to exert on the platform a force antagonistic to the vibrations which it supports.
  • the vibration damping means can consist of a frustoconical flange 40 fixed by screws 42 on the flange 16 scalloped at 41 of the drum 22, the external diameter of the trunk of cone being shaped into a round 43 to come to bear against a corresponding rounding of the lower downstream face of platform 3 (figure 8).
  • This damping means can also be used in combination with the variant of FIG. 4 with a downstream flange limiting the travel centered on the external diameter of the flange 16.
  • the damping means (flanges 14, 14 'or 40) also fulfill a sealing function between the upstream part of the stilt of the fan blade and the compressor stage located downstream.
  • FIG. 5 has the additional advantage of being adaptable to existing motors by simple machining of the ears of the disc and of greatly facilitating repair thereof during accidental ingestion.

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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)
EP86401518A 1985-07-16 1986-07-09 Dämpfungselement zur Begrenzung der Auslenkung von Rotorschaufeln einer Turbomaschine Expired EP0214875B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8510857 1985-07-16
FR8510857A FR2585069B1 (fr) 1985-07-16 1985-07-16 Dispositif de limitation du debattement angulaire d'aubes montees sur un disque de rotor de turbomachine

Publications (2)

Publication Number Publication Date
EP0214875A1 true EP0214875A1 (de) 1987-03-18
EP0214875B1 EP0214875B1 (de) 1989-03-01

Family

ID=9321331

Family Applications (1)

Application Number Title Priority Date Filing Date
EP86401518A Expired EP0214875B1 (de) 1985-07-16 1986-07-09 Dämpfungselement zur Begrenzung der Auslenkung von Rotorschaufeln einer Turbomaschine

Country Status (5)

Country Link
US (1) US4723889A (de)
EP (1) EP0214875B1 (de)
JP (1) JPS6220603A (de)
DE (1) DE3662212D1 (de)
FR (1) FR2585069B1 (de)

Families Citing this family (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3743253A1 (de) * 1987-12-19 1989-06-29 Mtu Muenchen Gmbh Axial durchstroemtes laufschaufelgitter fuer verdichter oder turbinen
FR2665726B1 (fr) * 1990-08-08 1993-07-02 Snecma Soufflante de turbomachine a amortisseur dynamique a cames.
US5205713A (en) * 1991-04-29 1993-04-27 General Electric Company Fan blade damper
US5281096A (en) * 1992-09-10 1994-01-25 General Electric Company Fan assembly having lightweight platforms
FR2715975B1 (fr) * 1994-02-10 1996-03-29 Snecma Rotor de turbomachine à rainures d'aube débouchantes axiales ou inclinées.
US5820346A (en) * 1996-12-17 1998-10-13 General Electric Company Blade damper for a turbine engine
FR2803623B1 (fr) 2000-01-06 2002-03-01 Snecma Moteurs Agencement de retenue axiale d'aubes dans un disque
JP2005009382A (ja) * 2003-06-18 2005-01-13 Ishikawajima Harima Heavy Ind Co Ltd タービンロータ、タービンディスク、及びタービン
US8469670B2 (en) * 2009-08-27 2013-06-25 Rolls-Royce Corporation Fan assembly
FR2966867B1 (fr) * 2010-10-28 2015-05-29 Snecma Ensemble de disques de rotor pour une turbomachine
FR2972759B1 (fr) * 2011-03-15 2015-09-18 Snecma Systeme d'etancheite et de retenue axiale des aubes pour une roue de turbine de turbomachine
FR2973829B1 (fr) * 2011-04-05 2013-05-24 Snecma Flasque d'etancheite pour etage de turbine de turbomachine d'aeronef, comprenant
US8967978B2 (en) * 2012-07-26 2015-03-03 Pratt & Whitney Canada Corp. Axial retention for fasteners in fan joint
FR3006364B1 (fr) * 2013-05-30 2018-07-13 Safran Aircraft Engines Roue de turbomachine, notamment pour turbine basse pression
US9790806B2 (en) * 2014-06-06 2017-10-17 United Technologies Corporation Case with vane retention feature
EP3073052B1 (de) * 2015-02-17 2018-01-24 Rolls-Royce Corporation Bläserbaugruppe
FR3075283B1 (fr) * 2017-12-15 2019-11-22 Safran Aircraft Engines Dispositif amortisseur
US10927683B2 (en) 2017-12-14 2021-02-23 Safran Aircraft Engines Damping device
FR3075282B1 (fr) * 2017-12-14 2021-01-08 Safran Aircraft Engines Dispositif amortisseur
EP3728794B1 (de) * 2017-12-18 2024-02-28 Safran Aircraft Engines Dämpfervorrichtung
FR3075284B1 (fr) * 2017-12-18 2020-09-04 Safran Aircraft Engines Dispositif amortisseur
FR3075253B1 (fr) * 2017-12-20 2019-11-22 Safran Aircraft Engines Dispositif amortisseur
FR3096730B1 (fr) * 2019-05-29 2021-04-30 Safran Aircraft Engines Ensemble pour turbomachine
WO2020239803A1 (fr) * 2019-05-29 2020-12-03 Safran Aircraft Engines Ensemble pour turbomachine
FR3096734B1 (fr) * 2019-05-29 2021-12-31 Safran Aircraft Engines Ensemble pour turbomachine
FR3096731B1 (fr) * 2019-05-29 2021-05-07 Safran Aircraft Engines Ensemble pour turbomachine
FR3126447A1 (fr) * 2021-08-30 2023-03-03 Safran Aircraft Engines Roue mobile de turbomachine comprenant une pièce de butée axiale pour amortisseur

Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB667979A (en) * 1949-07-28 1952-03-12 Rolls Royce Improvements in or relating to axial flow compressors and turbines
US2937849A (en) * 1955-10-06 1960-05-24 Gen Electric Structural dampener for turbo-blading
FR1222315A (fr) * 1959-04-25 1960-06-09 Gen Electric étage de rotor pour compresseurs et turbines
US2948505A (en) * 1956-12-26 1960-08-09 Gen Electric Gas turbine rotor
DE1112993B (de) * 1957-03-04 1961-08-24 Turbinen U Generatoren Zek Ber Verspannung von in Axialnuten des Laeufers befestigten Turbomaschinen-Laufschaufeln gegen Schwingungen in Schaufelkranzebene
US3037741A (en) * 1958-12-29 1962-06-05 Gen Electric Damping turbine buckets
US3119595A (en) * 1961-02-23 1964-01-28 Gen Electric Bladed rotor and baffle assembly
US3501247A (en) * 1967-07-07 1970-03-17 Snecma Blade fixing arrangement
GB1259750A (en) * 1970-07-23 1972-01-12 Rolls Royce Rotor for a fluid flow machine
GB1457417A (en) * 1973-06-30 1976-12-01 Dunlop Ltd Vibration damping means
GB2112466A (en) * 1981-12-30 1983-07-20 Rolls Royce Rotor blade vibration damping

Family Cites Families (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB670665A (en) * 1949-07-28 1952-04-23 Rolls Royce Improvements in or relating to compressors and turbines
US3047268A (en) * 1960-03-14 1962-07-31 Stanley L Leavitt Blade retention device
GB1093568A (en) * 1965-11-23 1967-12-06 Rolls Royce Improvements in or relating to bladed rotors such as compressor rotors
US3887298A (en) * 1974-05-30 1975-06-03 United Aircraft Corp Apparatus for sealing turbine blade damper cavities
GB1527074A (en) * 1974-09-28 1978-10-04 Rolls Royce Bladed rotors
JPS5268614A (en) * 1975-12-04 1977-06-07 Agency Of Ind Science & Technol Fixing device for snubber dynamic wing of fan with shelf
US4101245A (en) * 1976-12-27 1978-07-18 United Technologies Corporation Interblade damper and seal for turbomachinery rotor
US4182598A (en) * 1977-08-29 1980-01-08 United Technologies Corporation Turbine blade damper
US4265595A (en) * 1979-01-02 1981-05-05 General Electric Company Turbomachinery blade retaining assembly
FR2453294A1 (fr) * 1979-04-04 1980-10-31 Snecma Dispositif de fixation d'aubes sur un rotor de compresseur pour turbo-reacteur
SU836371A1 (ru) * 1979-04-09 1981-06-07 Предприятие П/Я М-5641 Рабочее колесо турбомашины
FR2502690B1 (fr) * 1981-03-27 1985-09-13 Snecma Dispositif de verrouillage d'aubes de soufflante et de fixation de capot avant d'un turboreacteur
FR2503247B1 (fr) * 1981-04-07 1985-06-14 Snecma Perfectionnements aux etages de turbine a gaz de turboreacteurs munis de moyens de refroidissement par air du disque de la roue de la turbine
FR2507679A1 (fr) * 1981-06-12 1982-12-17 Snecma Dispositif de verrouillage d'une aube de rotor de turbomachine
FR2514409B1 (fr) * 1981-10-09 1986-03-21 Snecma Dispositif d'implantation d'aubes en secteurs sur un disque de rotor de turbomachine
FR2517779B1 (fr) * 1981-12-03 1986-06-13 Snecma Dispositif d'amortissement des aubes d'une soufflante de turbomachine
FR2524932A1 (fr) * 1982-04-08 1983-10-14 Snecma Dispositif de retenue axiale de pieds d'aube dans un disque de turbomachine
FR2527260A1 (fr) * 1982-05-18 1983-11-25 Snecma Dispositif d'amortissement escamotable pour aubes d'une turbomachine
FR2535794A1 (fr) * 1982-11-08 1984-05-11 Snecma Dispositif de retenue axiale et radiale d'aubes de soufflante
FR2566061B1 (fr) * 1984-06-14 1988-09-02 Snecma Dispositif de verrouillage axial d'une aube de turbomachine

Patent Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB667979A (en) * 1949-07-28 1952-03-12 Rolls Royce Improvements in or relating to axial flow compressors and turbines
US2937849A (en) * 1955-10-06 1960-05-24 Gen Electric Structural dampener for turbo-blading
US2948505A (en) * 1956-12-26 1960-08-09 Gen Electric Gas turbine rotor
DE1112993B (de) * 1957-03-04 1961-08-24 Turbinen U Generatoren Zek Ber Verspannung von in Axialnuten des Laeufers befestigten Turbomaschinen-Laufschaufeln gegen Schwingungen in Schaufelkranzebene
US3037741A (en) * 1958-12-29 1962-06-05 Gen Electric Damping turbine buckets
FR1222315A (fr) * 1959-04-25 1960-06-09 Gen Electric étage de rotor pour compresseurs et turbines
US3119595A (en) * 1961-02-23 1964-01-28 Gen Electric Bladed rotor and baffle assembly
US3501247A (en) * 1967-07-07 1970-03-17 Snecma Blade fixing arrangement
GB1259750A (en) * 1970-07-23 1972-01-12 Rolls Royce Rotor for a fluid flow machine
GB1457417A (en) * 1973-06-30 1976-12-01 Dunlop Ltd Vibration damping means
GB2112466A (en) * 1981-12-30 1983-07-20 Rolls Royce Rotor blade vibration damping

Also Published As

Publication number Publication date
FR2585069A1 (fr) 1987-01-23
JPS6220603A (ja) 1987-01-29
JPH0377361B2 (de) 1991-12-10
US4723889A (en) 1988-02-09
FR2585069B1 (fr) 1989-06-09
DE3662212D1 (en) 1989-04-06
EP0214875B1 (de) 1989-03-01

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