US3887298A - Apparatus for sealing turbine blade damper cavities - Google Patents

Apparatus for sealing turbine blade damper cavities Download PDF

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Publication number
US3887298A
US3887298A US474756A US47475674A US3887298A US 3887298 A US3887298 A US 3887298A US 474756 A US474756 A US 474756A US 47475674 A US47475674 A US 47475674A US 3887298 A US3887298 A US 3887298A
Authority
US
United States
Prior art keywords
disk
face
root
blades
turbine
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
US474756A
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English (en)
Inventor
John R Hess
Joseph R Kozlin
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.)
RTX Corp
Original Assignee
United Aircraft Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by United Aircraft Corp filed Critical United Aircraft Corp
Priority to US474756A priority Critical patent/US3887298A/en
Priority to CA226,568A priority patent/CA1013676A/en
Priority to IL47321A priority patent/IL47321A/en
Priority to GB22405/75A priority patent/GB1506047A/en
Priority to SE7505935A priority patent/SE7505935L/xx
Priority to FR7516387A priority patent/FR2273163A1/fr
Priority to JP50065233A priority patent/JPS5113012A/ja
Application granted granted Critical
Publication of US3887298A publication Critical patent/US3887298A/en
Priority to BR4336/75D priority patent/BR7503391A/pt
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
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • 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
    • 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
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
    • 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

  • a radial seal plate having an inclined surface which projects into a damper cavity, extends between the neck extensions of two adjacent blades in the region between the turbine disk and the platforms of the blades; the seal plate closes off one end of the damper cavity.
  • a vibration damper having two axially extending ridges separated circumferentially by a distance exceeding the gap between the platforms defining the cavity.
  • the damper has a sloped surface adjacent to the inclined surface on the seal plate.
  • FIG. 2 is a section view taken along the line 22 as shown in FIG. 1;
  • FIG. 3 is a perspective view of the seal plate which is shown in cross section in FIG. 2;
  • FIG. 4 is a perspective view of the vibration damper which is shown in cross section in FIG. 2;
  • FIG. 5 is a section view corresponding to FIG. 2 showing alternate apparatus for axially sealing the vibration damper cavity.
  • the end walls of the damper cavity are formed by a seal plate 32 on the low pressure side of the wheel assembly and by an end plate extension 34 of a vibration damper 36 on the high pressure side of the wheel assembly.
  • the seal plate 32 includes a support section 38 having an inclined surface 40 extending from the seal plate in a direction away from the axis of rotation of the wheel assembly.
  • the vibration damper has a sloped surface 42 which is essentially parallel to the inclined surface of the seal plate and a pair of platform sealing surfaces 44 as shown in FIG. 4.
  • a low pressure sideplate 46 having a long offset 48 which extends around its circumference is bolted to a low pressure face 50 of the disk and traps the seal plate between the low pressure sideplate and the disk.
  • a high pressure sideplate 52 having a short offset 54 which extends around its circumference is bolted to a high pressure face 56 of the disk and traps the end plate of the vibration damper between the high pressure sideplate and the disk as is shown in FIG. 2.
  • each blade is inserted into a fir tree shaped slot in the disk and a seal plate is positioned against the disk between two adjacent blades with the support section 38 extending into the damper cavity 28.
  • thelow pressure sideplate 46 is affixed to the disk trapping the seal plates on the wheel assembly between the long offset48 on the sideplate and the low pressure face of the disk.
  • the seal plates are adjusted to a lowered position as represented by the dotted line in FIG. 2, and a vibration damper 36 is inserted into each damper cavity.
  • a high pressure sideplate 52 is affixed to the disk trapping the end plate extensions 34 of the vibration'dampers between the short offset 54 on the sideplate and the high pressure face of the disk. Both the seal plate and the vibration damper are free to move axially and radially within limits permitted by the turbine blades, the disk and the sideplates as shown in FIG. 2.
  • each turbine blade is restrained by the disk slot and each vibration damper is restrained by the blade platforms.
  • the sloped surface 42 of each vibration damper engages and restrains the seal plate as the plate tends to move radially.
  • Each turbine blade has sufficient clearance between the blade root and the disk slot to allow limited tangential or circumferential movement of the blade when vibrationally excited.
  • the movement of the blade is resisted by the dampers, which under the influence of centrifugal force, bear against the underside of the platform of the excited blade as well as the undersides of the next adjacent blade platforms. Frictional forces at the points of contact between the dampers and the blade platforms are energy dissipative and reduce the detrimental effects of blade vibration.
  • the seal plate bears upon the vibration damper and effectively increases the mass of the damper with a corresponding increase in the damping effects.
  • the sealing surfaces 44 on the vibration damper bear against the undersides of the two adjacent turbine blades to effect a radial seal between the platforms'of two adjacent blades andto prevent the circulation working medium, which is comprised of hot gases from the main flow path, against the rim of the disk.
  • the high and low pressure sideplates acting in a conventional manner, seal the interfaces between the turbine blade roots and the disk.
  • the seal plates on the high and low pressure sides of the disk are drawn toward the vibration damper 58 by the axial components of centrifugally generated forces.
  • the embodiment of FIG. 5 is particularly attractive where the movement of the damper within the cavity due to vibration is excessive and where such movement would detrimentally increase the amount of working medium leaking between the end plate extension of the vibration damper and the high pressure face of the disk.
  • an embodiment of the invention may include a protrusion extending from the inclined surface 40 of the seal plate shown in FIG. 3, the protrusion bearing upon the sloped surface of the vibration damper.
  • the sideplates of the present invention have a greatly reduced radial width.
  • Conventional sideplates require sufficient mass at their outer diameter to resist thermal distortion as the sideplates are subjected to unequally distributed temperatures.
  • the seal plates which cover only a local area are not subjected to the severe temperature gradients and may, therefore, be fabricated from material having a lesser thickness while experiencing less thermal distortion.
  • a wheel assembly comprising:
  • a turbine disk having a circumferentially extending rim with root connecting means spaced along the rim and first and second faces which are substantially perpendicular to the axis of rotation;
  • each blade having a root which engages the root connecting means and a platform spaced apart radially from the root by a neck extension;
  • the vibration damper further has an end plate extension which abuts the second face of the disk at the rim and the neck extensions of the two adjacent blades, and a pair of sealing surfaces, each of which is in contact with the undersurface of the platform of one of the adjacent blades, whereby the end plate extension of the vibration damper is urged against the second face of the disk by axial components of centrifugal loads during rotation of the wheel assembly and whereby the sealing surfaces of the vibration damper are held in contact with the platforms by radial components of centrifugal loads.
  • first sideplate has a circumferential offset at its periphery which engages and retains the seal plates between the offset and the first face of the disk.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US474756A 1974-05-30 1974-05-30 Apparatus for sealing turbine blade damper cavities Expired - Lifetime US3887298A (en)

Priority Applications (8)

Application Number Priority Date Filing Date Title
US474756A US3887298A (en) 1974-05-30 1974-05-30 Apparatus for sealing turbine blade damper cavities
CA226,568A CA1013676A (en) 1974-05-30 1975-05-08 Apparatus for sealing turbine blade damper cavities
IL47321A IL47321A (en) 1974-05-30 1975-05-20 Turbine engine
GB22405/75A GB1506047A (en) 1974-05-30 1975-05-22 Gas turbine having axial sealing of a turbine wheel
SE7505935A SE7505935L (sv) 1974-05-30 1975-05-26 Apparat for tetning av turbiner
FR7516387A FR2273163A1 (cs) 1974-05-30 1975-05-27
JP50065233A JPS5113012A (cs) 1974-05-30 1975-05-30
BR4336/75D BR7503391A (pt) 1974-05-30 1975-06-28 Aperfeicoamento em turbina a gas

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US474756A US3887298A (en) 1974-05-30 1974-05-30 Apparatus for sealing turbine blade damper cavities

Publications (1)

Publication Number Publication Date
US3887298A true US3887298A (en) 1975-06-03

Family

ID=23884811

Family Applications (1)

Application Number Title Priority Date Filing Date
US474756A Expired - Lifetime US3887298A (en) 1974-05-30 1974-05-30 Apparatus for sealing turbine blade damper cavities

Country Status (8)

Country Link
US (1) US3887298A (cs)
JP (1) JPS5113012A (cs)
BR (1) BR7503391A (cs)
CA (1) CA1013676A (cs)
FR (1) FR2273163A1 (cs)
GB (1) GB1506047A (cs)
IL (1) IL47321A (cs)
SE (1) SE7505935L (cs)

Cited By (51)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2289726A1 (fr) * 1974-10-29 1976-05-28 United Technologies Corp Rotor de turbine
US4088421A (en) * 1976-09-30 1978-05-09 General Electric Company Coverplate damping arrangement
US4101245A (en) * 1976-12-27 1978-07-18 United Technologies Corporation Interblade damper and seal for turbomachinery rotor
US4108571A (en) * 1976-02-11 1978-08-22 Rolls-Royce Limited Bladed rotor assembly for a gas turbine engine
FR2451451A1 (fr) * 1979-03-10 1980-10-10 Rolls Royce Rotor aube, a dispositif d'etancheite pour moteur a turbine a gaz
FR2523208A1 (fr) * 1982-03-12 1983-09-16 Snecma Dispositif d'amortissement des vibrations d'aubes mobiles de turbine
DE3307571A1 (de) * 1982-03-12 1983-09-22 United Technologies Corp., 06101 Hartford, Conn. Laufschaufeldaempfer und -daempfungsvorrichtung
US4480957A (en) * 1983-04-14 1984-11-06 General Electric Company Dynamic response modification and stress reduction in dovetail and blade assembly
EP0169800A1 (en) * 1984-07-23 1986-01-29 United Technologies Corporation Turbine cover-seal assembly
US4568247A (en) * 1984-03-29 1986-02-04 United Technologies Corporation Balanced blade vibration damper
FR2586061A1 (fr) * 1985-08-08 1987-02-13 Snecma Disque porte labyrinthe multifonction pour rotor de turbomachine
US4723889A (en) * 1985-07-16 1988-02-09 Societe Nationale D'etude Et De Constructions De Moteur D'aviation "S.N.E.C.M.A." Fan or compressor angular clearance limiting device
US4743164A (en) * 1986-12-29 1988-05-10 United Technologies Corporation Interblade seal for turbomachine rotor
US4872810A (en) * 1988-12-14 1989-10-10 United Technologies Corporation Turbine rotor retention system
US5052890A (en) * 1989-02-23 1991-10-01 Rolls-Royce Plc Device for damping vibrations in turbomachinery blades
US5201849A (en) * 1990-12-10 1993-04-13 General Electric Company Turbine rotor seal body
US5226784A (en) * 1991-02-11 1993-07-13 General Electric Company Blade damper
US5281097A (en) * 1992-11-20 1994-01-25 General Electric Company Thermal control damper for turbine rotors
US5284421A (en) * 1992-11-24 1994-02-08 United Technologies Corporation Rotor blade with platform support and damper positioning means
WO1994012772A1 (en) * 1992-11-24 1994-06-09 United Technologies Corporation Gas turbine blade seal
WO1994012773A1 (en) * 1992-11-24 1994-06-09 United Technologies Corporation Gas turbine blade damper
US5339619A (en) * 1992-08-31 1994-08-23 United Technologies Corporation Active cooling of turbine rotor assembly
US5388962A (en) * 1993-10-15 1995-02-14 General Electric Company Turbine rotor disk post cooling system
EP0709549A1 (fr) * 1994-10-26 1996-05-01 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Ensemble d'un disque rotatif et d'aubes, notamment utilisé dans un turbomachine
US5513955A (en) * 1994-12-14 1996-05-07 United Technologies Corporation Turbine engine rotor blade platform seal
US5573375A (en) * 1994-12-14 1996-11-12 United Technologies Corporation Turbine engine rotor blade platform sealing and vibration damping device
US5785499A (en) * 1996-12-24 1998-07-28 United Technologies Corporation Turbine blade damper and seal
US5827047A (en) * 1996-06-27 1998-10-27 United Technologies Corporation Turbine blade damper and seal
US5924699A (en) * 1996-12-24 1999-07-20 United Technologies Corporation Turbine blade platform seal
US6139277A (en) * 1998-12-22 2000-10-31 Air Concepts, Inc. Motorized fan
US6273683B1 (en) 1999-02-05 2001-08-14 Siemens Westinghouse Power Corporation Turbine blade platform seal
US20070258816A1 (en) * 2005-09-26 2007-11-08 Pratt & Whitney Canada Corp. Blades for a gas turbine engine with integrated sealing plate and method
US20080181779A1 (en) * 2007-01-25 2008-07-31 Siemens Power Generation, Inc. Blade assembly in a combustion turbo-machine providing reduced concentration of mechanical stress and a seal between adjacent assemblies
EP1522677A3 (en) * 2003-10-08 2008-09-03 United Technologies Corporation Blade damper
EP2058526A1 (fr) * 2007-11-12 2009-05-13 Snecma Ensemble d'une aube de soufflante et de son amortisseur, amortisseur d'aube de soufflante et méthode de calibrage de l'amortisseur
WO2010071496A1 (en) * 2008-12-18 2010-06-24 Volvo Aero Corporation Gas turbine composite workpiece to be used in gas turbine engine
DE102009011879A1 (de) * 2009-03-05 2010-09-16 Mtu Aero Engines Gmbh Integral beschaufelter Rotor und Verfahren zur Herstellung eines integral beschaufelten Rotors
US8128371B2 (en) 2007-02-15 2012-03-06 General Electric Company Method and apparatus to facilitate increasing turbine rotor efficiency
US20120301298A1 (en) * 2011-05-23 2012-11-29 Rolls-Royce Plc Balancing of rotatable components
US20130064668A1 (en) * 2011-09-08 2013-03-14 II Anthony Reid Paige Turbine rotor blade assembly and method of assembling same
US20130108446A1 (en) * 2011-10-28 2013-05-02 General Electric Company Thermal plug for turbine bucket shank cavity and related method
US20130323058A1 (en) * 2012-05-31 2013-12-05 Solar Turbines Incorporated Turbine damper
US20130323031A1 (en) * 2012-05-31 2013-12-05 Solar Turbines Incorporated Turbine damper
EP2848770A1 (de) * 2013-09-17 2015-03-18 MTU Aero Engines GmbH Laufradschaufel einer axialen Strömungsmaschine und Dämpfungselement
EP2873807A1 (de) * 2013-11-18 2015-05-20 Siemens Aktiengesellschaft Abdeckplatte, Laufschaufel, Radscheibe, Bolzen und Gasturbine
WO2017123206A1 (en) * 2016-01-12 2017-07-20 Siemens Aktiengesellschaft Flexible damper for turbine blades
US20170314397A1 (en) * 2016-04-27 2017-11-02 MTU Aero Engines AG Turbomachine blade assembly
US20180274381A1 (en) * 2017-03-23 2018-09-27 General Electric Company Gas turbine engine component incorporating a seal slot
US10202853B2 (en) 2013-09-11 2019-02-12 General Electric Company Ply architecture for integral platform and damper retaining features in CMC turbine blades
US10648352B2 (en) 2012-06-30 2020-05-12 General Electric Company Turbine blade sealing structure
CN111448365A (zh) * 2017-12-12 2020-07-24 赛峰直升机发动机公司 用于涡轮机转子轮叶的减振器

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US2985426A (en) * 1954-07-15 1961-05-23 Rolls Royce Bladed rotor construction for axialflow fluid machine
US2998959A (en) * 1955-09-29 1961-09-05 Rolls Royce Bladed rotor of axial-flow fluid machine with means to retain blades in position on rotor
US3112915A (en) * 1961-12-22 1963-12-03 Gen Electric Rotor assembly air baffle
US3181835A (en) * 1964-01-07 1965-05-04 Carroll C Davis Blade vibration damping device
US3610778A (en) * 1968-08-09 1971-10-05 Sulzer Ag Support for rotor blades in a rotor
US3751183A (en) * 1971-12-02 1973-08-07 Gen Electric Interblade baffle and damper

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2985426A (en) * 1954-07-15 1961-05-23 Rolls Royce Bladed rotor construction for axialflow fluid machine
US2998959A (en) * 1955-09-29 1961-09-05 Rolls Royce Bladed rotor of axial-flow fluid machine with means to retain blades in position on rotor
US3112915A (en) * 1961-12-22 1963-12-03 Gen Electric Rotor assembly air baffle
US3181835A (en) * 1964-01-07 1965-05-04 Carroll C Davis Blade vibration damping device
US3610778A (en) * 1968-08-09 1971-10-05 Sulzer Ag Support for rotor blades in a rotor
US3751183A (en) * 1971-12-02 1973-08-07 Gen Electric Interblade baffle and damper

Cited By (83)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2289726A1 (fr) * 1974-10-29 1976-05-28 United Technologies Corp Rotor de turbine
US4108571A (en) * 1976-02-11 1978-08-22 Rolls-Royce Limited Bladed rotor assembly for a gas turbine engine
US4088421A (en) * 1976-09-30 1978-05-09 General Electric Company Coverplate damping arrangement
US4101245A (en) * 1976-12-27 1978-07-18 United Technologies Corporation Interblade damper and seal for turbomachinery rotor
FR2451451A1 (fr) * 1979-03-10 1980-10-10 Rolls Royce Rotor aube, a dispositif d'etancheite pour moteur a turbine a gaz
GB2116641A (en) * 1982-03-12 1983-09-28 United Technologies Corp Blade damper seal
DE3307571A1 (de) * 1982-03-12 1983-09-22 United Technologies Corp., 06101 Hartford, Conn. Laufschaufeldaempfer und -daempfungsvorrichtung
FR2523208A1 (fr) * 1982-03-12 1983-09-16 Snecma Dispositif d'amortissement des vibrations d'aubes mobiles de turbine
US4473337A (en) * 1982-03-12 1984-09-25 United Technologies Corporation Blade damper seal
US4480959A (en) * 1982-03-12 1984-11-06 S.N.E.C.M.A. Device for damping vibrations of mobile turbine blades
EP0089272A1 (fr) * 1982-03-12 1983-09-21 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Roue de rotor de turbine comportant un dispositif d'amortissement des vibrations d'aubes
US4480957A (en) * 1983-04-14 1984-11-06 General Electric Company Dynamic response modification and stress reduction in dovetail and blade assembly
US4568247A (en) * 1984-03-29 1986-02-04 United Technologies Corporation Balanced blade vibration damper
EP0169800A1 (en) * 1984-07-23 1986-01-29 United Technologies Corporation Turbine cover-seal assembly
US4659285A (en) * 1984-07-23 1987-04-21 United Technologies Corporation Turbine cover-seal assembly
US4723889A (en) * 1985-07-16 1988-02-09 Societe Nationale D'etude Et De Constructions De Moteur D'aviation "S.N.E.C.M.A." Fan or compressor angular clearance limiting device
FR2586061A1 (fr) * 1985-08-08 1987-02-13 Snecma Disque porte labyrinthe multifonction pour rotor de turbomachine
EP0214876A1 (fr) * 1985-08-08 1987-03-18 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Disque porte labyrinthe multifonction pour rotor de turbomachine
US4668167A (en) * 1985-08-08 1987-05-26 Societe National D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Multifunction labyrinth seal support disk for a turbojet engine rotor
WO1988005121A1 (en) * 1986-12-29 1988-07-14 United Technologies Corporation Interblade seal for turbomachine rotor
US4743164A (en) * 1986-12-29 1988-05-10 United Technologies Corporation Interblade seal for turbomachine rotor
US4872810A (en) * 1988-12-14 1989-10-10 United Technologies Corporation Turbine rotor retention system
US5052890A (en) * 1989-02-23 1991-10-01 Rolls-Royce Plc Device for damping vibrations in turbomachinery blades
US5201849A (en) * 1990-12-10 1993-04-13 General Electric Company Turbine rotor seal body
US5226784A (en) * 1991-02-11 1993-07-13 General Electric Company Blade damper
US5339619A (en) * 1992-08-31 1994-08-23 United Technologies Corporation Active cooling of turbine rotor assembly
US5281097A (en) * 1992-11-20 1994-01-25 General Electric Company Thermal control damper for turbine rotors
US5284421A (en) * 1992-11-24 1994-02-08 United Technologies Corporation Rotor blade with platform support and damper positioning means
WO1994012772A1 (en) * 1992-11-24 1994-06-09 United Technologies Corporation Gas turbine blade seal
WO1994012773A1 (en) * 1992-11-24 1994-06-09 United Technologies Corporation Gas turbine blade damper
US5388962A (en) * 1993-10-15 1995-02-14 General Electric Company Turbine rotor disk post cooling system
EP0709549A1 (fr) * 1994-10-26 1996-05-01 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Ensemble d'un disque rotatif et d'aubes, notamment utilisé dans un turbomachine
FR2726323A1 (fr) * 1994-10-26 1996-05-03 Snecma Ensemble d'un disque rotatif et d'aubes, notamment utilise dans une turbomachine
US5599170A (en) * 1994-10-26 1997-02-04 Societe Nationale D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. Seal for gas turbine rotor blades
US5513955A (en) * 1994-12-14 1996-05-07 United Technologies Corporation Turbine engine rotor blade platform seal
US5573375A (en) * 1994-12-14 1996-11-12 United Technologies Corporation Turbine engine rotor blade platform sealing and vibration damping device
US5827047A (en) * 1996-06-27 1998-10-27 United Technologies Corporation Turbine blade damper and seal
US5785499A (en) * 1996-12-24 1998-07-28 United Technologies Corporation Turbine blade damper and seal
US5924699A (en) * 1996-12-24 1999-07-20 United Technologies Corporation Turbine blade platform seal
US6139277A (en) * 1998-12-22 2000-10-31 Air Concepts, Inc. Motorized fan
US6273683B1 (en) 1999-02-05 2001-08-14 Siemens Westinghouse Power Corporation Turbine blade platform seal
EP1522677A3 (en) * 2003-10-08 2008-09-03 United Technologies Corporation Blade damper
US7484936B2 (en) 2005-09-26 2009-02-03 Pratt & Whitney Canada Corp. Blades for a gas turbine engine with integrated sealing plate and method
US20070258816A1 (en) * 2005-09-26 2007-11-08 Pratt & Whitney Canada Corp. Blades for a gas turbine engine with integrated sealing plate and method
US7762780B2 (en) 2007-01-25 2010-07-27 Siemens Energy, Inc. Blade assembly in a combustion turbo-machine providing reduced concentration of mechanical stress and a seal between adjacent assemblies
US20080181779A1 (en) * 2007-01-25 2008-07-31 Siemens Power Generation, Inc. Blade assembly in a combustion turbo-machine providing reduced concentration of mechanical stress and a seal between adjacent assemblies
US8128371B2 (en) 2007-02-15 2012-03-06 General Electric Company Method and apparatus to facilitate increasing turbine rotor efficiency
FR2923557A1 (fr) * 2007-11-12 2009-05-15 Snecma Sa Ensemble d'une aube de soufflante et de son amortisseur, amortisseur d'aube de soufflante et methode de calibrage de l'amortisseur
RU2476683C2 (ru) * 2007-11-12 2013-02-27 Снекма Узел вентиляторной лопатки с амортизатором, амортизатор вентиляторной лопатки и способ калибровки амортизатора
US8113783B2 (en) 2007-11-12 2012-02-14 Snecma Assembly of a fan blade and of its damper, fan blade damper and method for calibrating the damper
US20090123286A1 (en) * 2007-11-12 2009-05-14 Snecma Assembly of a fan blade and of its damper, fan blade damper and method for calibrating the damper
EP2058526A1 (fr) * 2007-11-12 2009-05-13 Snecma Ensemble d'une aube de soufflante et de son amortisseur, amortisseur d'aube de soufflante et méthode de calibrage de l'amortisseur
WO2010071496A1 (en) * 2008-12-18 2010-06-24 Volvo Aero Corporation Gas turbine composite workpiece to be used in gas turbine engine
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SE7505935L (sv) 1975-12-01
GB1506047A (en) 1978-04-05
IL47321A0 (en) 1975-07-28
FR2273163A1 (cs) 1975-12-26
CA1013676A (en) 1977-07-12
IL47321A (en) 1977-07-31
BR7503391A (pt) 1976-04-27
JPS5113012A (cs) 1976-02-02

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