GB1259750A - Rotor for a fluid flow machine - Google Patents

Rotor for a fluid flow machine

Info

Publication number
GB1259750A
GB1259750A GB3574570A GB3574570A GB1259750A GB 1259750 A GB1259750 A GB 1259750A GB 3574570 A GB3574570 A GB 3574570A GB 3574570 A GB3574570 A GB 3574570A GB 1259750 A GB1259750 A GB 1259750A
Authority
GB
United Kingdom
Prior art keywords
shanks
adjacent
rotor
elongated plate
bulbous
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
Application number
GB3574570A
Inventor
Wilfred Henry Wilkinson
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
Priority to GB3574570A priority Critical patent/GB1259750A/en
Publication of GB1259750A publication Critical patent/GB1259750A/en
Expired 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

1,259,750. Turbomachine rotors. ROLLSROYCE Ltd. July 23, 1970, No.35745/70. Heading F1T. Vibration of turbine or like rotor blades having platforms 14 spaced from respective root portions 11 by radially extending shanks is damped by flexible channel-shaped sheet metal members 16 disposed between adjacent shanks. Each member 16 is held in contact with the rotor disc by being trapped between the roots 11 of adjacent blades and is provided with an elongated plate 20 having a central portion 21 secured to the base 22 of the member 16. Each plate 20 has a bulbous portion 23 extending generally circumferentially from its opposite ends to engage the adjacent blade shanks. Thus in operation the centrifugal loads on members 16 cause forces in a generally circumferential direction to be transmitted to the shanks by bulbous portions 23 to effect vibration damping. In a modification, Fig. 6 (not shown), the channel-shaped member 16 is integrally connected to elongated plate 20 by a radial rib (24).
GB3574570A 1970-07-23 1970-07-23 Rotor for a fluid flow machine Expired GB1259750A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB3574570A GB1259750A (en) 1970-07-23 1970-07-23 Rotor for a fluid flow machine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB3574570A GB1259750A (en) 1970-07-23 1970-07-23 Rotor for a fluid flow machine

Publications (1)

Publication Number Publication Date
GB1259750A true GB1259750A (en) 1972-01-12

Family

ID=10381103

Family Applications (1)

Application Number Title Priority Date Filing Date
GB3574570A Expired GB1259750A (en) 1970-07-23 1970-07-23 Rotor for a fluid flow machine

Country Status (1)

Country Link
GB (1) GB1259750A (en)

Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
US4177013A (en) * 1977-01-11 1979-12-04 Rolls-Royce Limited Compressor rotor stage
US4182598A (en) * 1977-08-29 1980-01-08 United Technologies Corporation Turbine blade damper
US4326835A (en) * 1979-10-29 1982-04-27 General Motors Corporation Blade platform seal for ceramic/metal rotor assembly
FR2503247A1 (en) * 1981-04-07 1982-10-08 Snecma IMPROVEMENTS IN TURBINE GAS TURBINE STAGES WITH AIR-COOLED MEANS OF THE TURBINE WHEEL WHEEL
DE3245069A1 (en) * 1981-12-14 1983-06-16 United Technologies Corp., 06101 Hartford, Conn. BLADE VIBRATION DAMPER AND EQUIPPED BLADE AND DISC ASSEMBLY
US4470756A (en) * 1982-04-08 1984-09-11 S.N.E.C.M.A. Device for axial securing of blade feet of a gas turbine disk
US4473337A (en) * 1982-03-12 1984-09-25 United Technologies Corporation Blade damper seal
US4516910A (en) * 1982-05-18 1985-05-14 S.N.E.C.M.A. Retractable damping device for blades of a turbojet
US4580946A (en) * 1984-11-26 1986-04-08 General Electric Company Fan blade platform seal
FR2585069A1 (en) * 1985-07-16 1987-01-23 Snecma DEVICE FOR LIMITING THE ANGULAR DEBATMENT OF AUBES MOUNTED ON A TURBOMACHINE ROTOR DISK
FR2669686A1 (en) * 1990-11-28 1992-05-29 Snecma BLOWER ROTOR WITH BLADES WITHOUT PLATFORMS AND SHOES RECONSTRUCTING THE VEIN PROFILE.
US5415526A (en) * 1993-11-19 1995-05-16 Mercadante; Anthony J. Coolable rotor assembly
GB2344383A (en) * 1998-12-01 2000-06-07 Rolls Royce Plc Damping vibration of gas turbine engine blades
US6457935B1 (en) * 2000-06-15 2002-10-01 Snecma Moteurs System for ventilating a pair of juxtaposed vane platforms
US7374400B2 (en) * 2004-03-06 2008-05-20 Rolls-Royce Plc Turbine blade arrangement
EP2372094A3 (en) * 2010-04-05 2014-06-25 Pratt & Whitney Rocketdyne, Inc. Non-Integral Platform and Damper for a gas turbine engine blade
EP2836682A4 (en) * 2012-01-31 2016-06-01 United Technologies Corp Turbine blade damper seal
EP2570599B1 (en) * 2011-09-19 2020-05-06 General Electric Company Compressive stress system and method for a gas turbine engine

Cited By (29)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
US4177013A (en) * 1977-01-11 1979-12-04 Rolls-Royce Limited Compressor rotor stage
US4182598A (en) * 1977-08-29 1980-01-08 United Technologies Corporation Turbine blade damper
US4326835A (en) * 1979-10-29 1982-04-27 General Motors Corporation Blade platform seal for ceramic/metal rotor assembly
FR2503247A1 (en) * 1981-04-07 1982-10-08 Snecma IMPROVEMENTS IN TURBINE GAS TURBINE STAGES WITH AIR-COOLED MEANS OF THE TURBINE WHEEL WHEEL
EP0062558A1 (en) * 1981-04-07 1982-10-13 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Stage of a gas turbine jet engine with air cooling means for the turbine rotor disc
DE3245069A1 (en) * 1981-12-14 1983-06-16 United Technologies Corp., 06101 Hartford, Conn. BLADE VIBRATION DAMPER AND EQUIPPED BLADE AND DISC ASSEMBLY
US4473337A (en) * 1982-03-12 1984-09-25 United Technologies Corporation Blade damper seal
US4470756A (en) * 1982-04-08 1984-09-11 S.N.E.C.M.A. Device for axial securing of blade feet of a gas turbine disk
US4516910A (en) * 1982-05-18 1985-05-14 S.N.E.C.M.A. Retractable damping device for blades of a turbojet
US4580946A (en) * 1984-11-26 1986-04-08 General Electric Company Fan blade platform seal
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
EP0214875A1 (en) * 1985-07-16 1987-03-18 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Damping element limiting the angular deflection of turbo machine rotor vanes
FR2585069A1 (en) * 1985-07-16 1987-01-23 Snecma DEVICE FOR LIMITING THE ANGULAR DEBATMENT OF AUBES MOUNTED ON A TURBOMACHINE ROTOR DISK
FR2669686A1 (en) * 1990-11-28 1992-05-29 Snecma BLOWER ROTOR WITH BLADES WITHOUT PLATFORMS AND SHOES RECONSTRUCTING THE VEIN PROFILE.
EP0488874A1 (en) * 1990-11-28 1992-06-03 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Fan rotor with blades without platforms and fillers reconstructing the streamline profile
US5161949A (en) * 1990-11-28 1992-11-10 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.M.C.A." Rotor fitted with spacer blocks between the blades
US5415526A (en) * 1993-11-19 1995-05-16 Mercadante; Anthony J. Coolable rotor assembly
GB2344383B (en) * 1998-12-01 2002-06-26 Rolls Royce Plc A bladed rotor
US6267557B1 (en) 1998-12-01 2001-07-31 Rolls-Royce Plc Aerofoil blade damper
GB2344383A (en) * 1998-12-01 2000-06-07 Rolls Royce Plc Damping vibration of gas turbine engine blades
US6457935B1 (en) * 2000-06-15 2002-10-01 Snecma Moteurs System for ventilating a pair of juxtaposed vane platforms
US7374400B2 (en) * 2004-03-06 2008-05-20 Rolls-Royce Plc Turbine blade arrangement
EP2372094A3 (en) * 2010-04-05 2014-06-25 Pratt & Whitney Rocketdyne, Inc. Non-Integral Platform and Damper for a gas turbine engine blade
EP2570599B1 (en) * 2011-09-19 2020-05-06 General Electric Company Compressive stress system and method for a gas turbine engine
EP2836682A4 (en) * 2012-01-31 2016-06-01 United Technologies Corp Turbine blade damper seal
US10113434B2 (en) 2012-01-31 2018-10-30 United Technologies Corporation Turbine blade damper seal
US10907482B2 (en) 2012-01-31 2021-02-02 Raytheon Technologies Corporation Turbine blade damper seal

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Legal Events

Date Code Title Description
PS Patent sealed
PLE Entries relating assignments, transmissions, licences in the register of patents
PCNP Patent ceased through non-payment of renewal fee