GB1457417A - Vibration damping means - Google Patents

Vibration damping means

Info

Publication number
GB1457417A
GB1457417A GB3128973A GB3128973A GB1457417A GB 1457417 A GB1457417 A GB 1457417A GB 3128973 A GB3128973 A GB 3128973A GB 3128973 A GB3128973 A GB 3128973A GB 1457417 A GB1457417 A GB 1457417A
Authority
GB
United Kingdom
Prior art keywords
blocks
elastomeric
disc
vibration damping
blades
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
GB3128973A
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.)
Dunlop Ltd
Original Assignee
Dunlop Ltd
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 Dunlop Ltd filed Critical Dunlop Ltd
Priority to GB3128973A priority Critical patent/GB1457417A/en
Publication of GB1457417A publication Critical patent/GB1457417A/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)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

1457417 Turbomachine blade vibration damping DUNLOP Ltd 2 July 1974 [30 June 1973] 31289/73 Heading F1T Vibration of blades 4 on a rotor disc 1, e.g. forming a compressor stage in a gas turbine engine, is dampened by precompressed elastomeric blocks 7 compressed radially between blade platform 6 and the outer surface 5 of the disc, and compressed circumferentially between adjacent blades. The compression is achieved by forcing the blocks axially into the wedge-shaped gap defined between the platforms and disc outer surface by means of bolts 8 passing through the-blocks into balancing brackets 9. The blocks 7 may be of laminated form, or may be formed by covering an elastomeric core with an elastomeric or plastics cover. Further damping may be achieved by providing elastomeric material between adjacent platform ends.
GB3128973A 1973-06-30 1973-06-30 Vibration damping means Expired GB1457417A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB3128973A GB1457417A (en) 1973-06-30 1973-06-30 Vibration damping means

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB3128973A GB1457417A (en) 1973-06-30 1973-06-30 Vibration damping means

Publications (1)

Publication Number Publication Date
GB1457417A true GB1457417A (en) 1976-12-01

Family

ID=10320925

Family Applications (1)

Application Number Title Priority Date Filing Date
GB3128973A Expired GB1457417A (en) 1973-06-30 1973-06-30 Vibration damping means

Country Status (1)

Country Link
GB (1) GB1457417A (en)

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2376958A1 (en) * 1977-01-11 1978-08-04 Rolls Royce MOBILE COMPRESSOR STAGE
US4175912A (en) * 1976-10-19 1979-11-27 Rolls-Royce Limited Axial flow gas turbine engine compressor
EP0081416A1 (en) * 1981-12-03 1983-06-15 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Damping device for the blades of a turbo machine fan
US4500255A (en) * 1981-04-24 1985-02-19 United States Of America As Represented By The Secretary Of The Air Force Spacer structure
US4541778A (en) * 1984-05-18 1985-09-17 The United States Of America As Represented By The Secretary Of The Navy Pin rooted blade biaxial air seal
US4580946A (en) * 1984-11-26 1986-04-08 General Electric Company Fan blade platform seal
FR2575220A1 (en) * 1984-12-20 1986-06-27 Gen Electric ROTOR WITH FOOT JOINT AUBE
FR2585069A1 (en) * 1985-07-16 1987-01-23 Snecma DEVICE FOR LIMITING THE ANGULAR DEBATMENT OF AUBES MOUNTED ON A TURBOMACHINE ROTOR DISK
EP0280246A1 (en) * 1987-02-24 1988-08-31 Westinghouse Electric Corporation Method of assembly of a blade arrangement for a steam turbine
US5313786A (en) * 1992-11-24 1994-05-24 United Technologies Corporation Gas turbine blade damper
US6102664A (en) * 1995-12-14 2000-08-15 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Blading system and method for controlling structural vibrations
EP1249576A2 (en) * 2001-04-10 2002-10-16 Rolls-Royce Plc Vibration damper for a gas turbine
US6682307B1 (en) * 1999-05-14 2004-01-27 Siemens Aktiengesellschaft Sealing system for a rotor of a turbo engine
EP2350459A2 (en) * 2009-03-05 2011-08-03 MTU Aero Engines GmbH Rotor for a turbomachine
EP2586967A3 (en) * 2011-10-28 2014-11-12 General Electric Company Thermal plug for turbine bucket shank cavity and related method
CN109312623A (en) * 2016-04-04 2019-02-05 纳布拉风力技术公司 Device for splice module blade

Cited By (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4175912A (en) * 1976-10-19 1979-11-27 Rolls-Royce Limited Axial flow gas turbine engine compressor
FR2376958A1 (en) * 1977-01-11 1978-08-04 Rolls Royce MOBILE COMPRESSOR STAGE
US4177013A (en) * 1977-01-11 1979-12-04 Rolls-Royce Limited Compressor rotor stage
US4500255A (en) * 1981-04-24 1985-02-19 United States Of America As Represented By The Secretary Of The Air Force Spacer structure
EP0081416A1 (en) * 1981-12-03 1983-06-15 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Damping device for the blades of a turbo machine fan
US4494909A (en) * 1981-12-03 1985-01-22 S.N.E.C.M.A. Damping device for turbojet engine fan blades
US4541778A (en) * 1984-05-18 1985-09-17 The United States Of America As Represented By The Secretary Of The Navy Pin rooted blade biaxial air seal
US4580946A (en) * 1984-11-26 1986-04-08 General Electric Company Fan blade platform seal
FR2575220A1 (en) * 1984-12-20 1986-06-27 Gen Electric ROTOR WITH FOOT JOINT AUBE
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
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
EP0280246A1 (en) * 1987-02-24 1988-08-31 Westinghouse Electric Corporation Method of assembly of a blade arrangement for a steam turbine
US5313786A (en) * 1992-11-24 1994-05-24 United Technologies Corporation Gas turbine blade damper
US6102664A (en) * 1995-12-14 2000-08-15 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Blading system and method for controlling structural vibrations
US6682307B1 (en) * 1999-05-14 2004-01-27 Siemens Aktiengesellschaft Sealing system for a rotor of a turbo engine
EP1249576A3 (en) * 2001-04-10 2003-10-08 Rolls-Royce Plc Vibration damper for a gas turbine
US6659725B2 (en) 2001-04-10 2003-12-09 Rolls-Royce Plc Vibration damping
EP1249576A2 (en) * 2001-04-10 2002-10-16 Rolls-Royce Plc Vibration damper for a gas turbine
EP2350459A2 (en) * 2009-03-05 2011-08-03 MTU Aero Engines GmbH Rotor for a turbomachine
EP2586967A3 (en) * 2011-10-28 2014-11-12 General Electric Company Thermal plug for turbine bucket shank cavity and related method
US9366142B2 (en) 2011-10-28 2016-06-14 General Electric Company Thermal plug for turbine bucket shank cavity and related method
CN109312623A (en) * 2016-04-04 2019-02-05 纳布拉风力技术公司 Device for splice module blade

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Legal Events

Date Code Title Description
PS Patent sealed
PCNP Patent ceased through non-payment of renewal fee