FR2451452A1 - BLADE ROTOR, WITH VIBRATION DAMPER, FOR A GAS TURBINE ENGINE - Google Patents

BLADE ROTOR, WITH VIBRATION DAMPER, FOR A GAS TURBINE ENGINE

Info

Publication number
FR2451452A1
FR2451452A1 FR8004450A FR8004450A FR2451452A1 FR 2451452 A1 FR2451452 A1 FR 2451452A1 FR 8004450 A FR8004450 A FR 8004450A FR 8004450 A FR8004450 A FR 8004450A FR 2451452 A1 FR2451452 A1 FR 2451452A1
Authority
FR
France
Prior art keywords
gas turbine
vibration damper
turbine engine
blade
plates
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.)
Pending
Application number
FR8004450A
Other languages
French (fr)
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Publication of FR2451452A1 publication Critical patent/FR2451452A1/en
Pending legal-status Critical Current

Links

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

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'INVENTION CONCERNE UN ROTOR AUBE, A AMORTISSEUR DE VIBRATIONS DES AUBES, POUR MOTEUR A TURBINE A GAZ, DONT LA PERIPHERIE DU DISQUE 15 COMPORTE DES CANNELURES DANS LESQUELLES SONT FIXEES LES AUBES 16, CHAQUE AUBE COMPORTANT UN PLATEAU 20 ABOUTANT LES PLATEAUX DES AUBES ADJACENTES POUR FORMER UNE PAROI ANNULAIRE. DES ASSEMBLAGES AVANT ET ARRIERE DE SEGMENTS DE PLAQUES 31 ET 23 SONT FIXES AU DISQUE DE FACON A S'APPLIQUER AUX FACES AVANT ET ARRIERE DE CE DERNIER. DES POIDS AMORTISSEURS SEPARES 36 AVANT ET ARRIERE SONT FIXES AUX PLAQUES AVANT ET ARRIERE, RESPECTIVEMENT, DE FACON A POUVOIR SE DEPLACER SUFFISAMMENT, RADIALEMENT ET VERS L'EXTERIEUR, POUR ETABLIR UN CONTACT DE FROTTEMENT AVEC LES SURFACES INTERNES DES PLATES-FORMES ET AMORTIR AINSI LES VIBRATIONS DES AUBES. L'INVENTION, PRINCIPALEMENT DESTINEE AUX MOTEURS D'AERONEFS, EST EGALEMENT APPLICABLE A TOUS AUTRES MOTEURS A TURBINE A GAZ.THE INVENTION CONCERNS A BLADE ROTOR, WITH A BLADE VIBRATION DAMPER, FOR A GAS TURBINE ENGINE, THE PERIPHERY OF THE DISC 15 INCLUDES FLUDS IN WHICH THE BLADES 16 ARE FIXED, EACH VANE INCLUDING A PLATE 20 ABUTTING THE BLADE PLATES. ADJACENT TO FORM AN ANNULAR WALL. FRONT AND REAR ASSEMBLIES OF PLATE RINGS 31 AND 23 ARE ATTACHED TO THE DISC SO AS TO APPLY TO THE FRONT AND REAR SIDES OF THE LATTER. 36 SEPARATE FRONT AND REAR SHOCK ABSORBER WEIGHTS ARE ATTACHED TO THE FRONT AND REAR PLATES RESPECTIVELY SO AS TO MOVE SUFFICIENTLY, RADIALLY AND OUTSIDE, TO ESTABLISH FRICTION CONTACT WITH THE INTERNAL AND INNER SURFACES OF THE PLATES. THE VIBRATIONS OF THE DAWS. THE INVENTION, PRIMARILY INTENDED FOR AIRCRAFT ENGINES, IS ALSO APPLICABLE TO ALL OTHER GAS TURBINE ENGINES.

FR8004450A 1979-03-10 1980-02-28 BLADE ROTOR, WITH VIBRATION DAMPER, FOR A GAS TURBINE ENGINE Pending FR2451452A1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB7908522A GB2043797A (en) 1979-03-10 1979-03-10 Bladed Rotor for Gas Turbine Engine

Publications (1)

Publication Number Publication Date
FR2451452A1 true FR2451452A1 (en) 1980-10-10

Family

ID=10503801

Family Applications (1)

Application Number Title Priority Date Filing Date
FR8004450A Pending FR2451452A1 (en) 1979-03-10 1980-02-28 BLADE ROTOR, WITH VIBRATION DAMPER, FOR A GAS TURBINE ENGINE

Country Status (5)

Country Link
JP (1) JPS55123303A (en)
DE (1) DE3008890A1 (en)
FR (1) FR2451452A1 (en)
GB (1) GB2043797A (en)
IT (1) IT1130017B (en)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4347040A (en) * 1980-10-02 1982-08-31 United Technologies Corporation Blade to blade vibration damper
USRE32339E (en) * 1980-10-02 1987-01-27 United Technologies Corporation Blade to blade vibration damper
US4872810A (en) * 1988-12-14 1989-10-10 United Technologies Corporation Turbine rotor retention system
DE102010015211B4 (en) 2010-04-16 2013-06-20 Mtu Aero Engines Gmbh Damping element for damping blade vibrations, blade and rotor
FR2972482B1 (en) * 2011-03-07 2016-07-29 Snecma TURBINE STAGE FOR AIRCRAFT TURBOMACHINE HAVING IMPROVED SEAL BETWEEN THE FLASK DOWN AND THE TURBINE BLADES BY MECHANICAL RETENTION
DE102011100221B4 (en) * 2011-05-02 2017-03-09 MTU Aero Engines AG Integrally bladed rotor body, process and turbomachine

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2999668A (en) * 1958-08-28 1961-09-12 Curtiss Wright Corp Self-balanced rotor blade
US3181835A (en) * 1964-01-07 1965-05-04 Carroll C Davis Blade vibration damping device
FR1579923A (en) * 1968-08-09 1969-08-29
FR2164196A5 (en) * 1971-12-02 1973-07-27 Gen Electric
FR2265987A1 (en) * 1974-03-28 1975-10-24 United Aircraft Corp
US4101245A (en) * 1976-12-27 1978-07-18 United Technologies Corporation Interblade damper and seal for turbomachinery rotor

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2999668A (en) * 1958-08-28 1961-09-12 Curtiss Wright Corp Self-balanced rotor blade
US3181835A (en) * 1964-01-07 1965-05-04 Carroll C Davis Blade vibration damping device
FR1579923A (en) * 1968-08-09 1969-08-29
FR2164196A5 (en) * 1971-12-02 1973-07-27 Gen Electric
FR2265987A1 (en) * 1974-03-28 1975-10-24 United Aircraft Corp
US4101245A (en) * 1976-12-27 1978-07-18 United Technologies Corporation Interblade damper and seal for turbomachinery rotor

Also Published As

Publication number Publication date
GB2043797A (en) 1980-10-08
JPS55123303A (en) 1980-09-22
DE3008890A1 (en) 1980-09-11
IT8020480A0 (en) 1980-03-10
IT1130017B (en) 1986-06-11

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