GB1437510A - Compressor or turbine vane damping - Google Patents

Compressor or turbine vane damping

Info

Publication number
GB1437510A
GB1437510A GB5691673A GB5691673A GB1437510A GB 1437510 A GB1437510 A GB 1437510A GB 5691673 A GB5691673 A GB 5691673A GB 5691673 A GB5691673 A GB 5691673A GB 1437510 A GB1437510 A GB 1437510A
Authority
GB
United Kingdom
Prior art keywords
pad
vane
vanes
shroud ring
damping
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
GB5691673A
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.)
Raytheon Technologies 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
Priority to FR7344445A priority Critical patent/FR2330276A5/en
Application filed by United Aircraft Corp filed Critical United Aircraft Corp
Priority to GB5691673A priority patent/GB1437510A/en
Priority to DE2361370A priority patent/DE2361370A1/en
Publication of GB1437510A publication Critical patent/GB1437510A/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
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/614—Fibres or filaments

Abstract

1437510 Turbomachinery blade damping UNITED AIRCRAFT CORP 7 Dec 1973 56916/73 Heading FIT Damping of vibration of turbine or compressor vanes 2 is effected by positioning a compressible porous pad 24 of resilient metal wire about the outer end of the vane in a pocket defined between a radially outer shroud ring 10 and a cover ring 26, the vanes passing freely through slots 8 in the outer shroud ring. The pad may be of stainless steel wool, braided wire, metal felt, or knitted wire. The inner ends of the vanes are brazed or welded in slots 6 in an inner shroud ring 4. A single pad may cover one or more vane ends. A notch may be cut in the pad to receive the vane end.
GB5691673A 1973-12-05 1973-12-07 Compressor or turbine vane damping Expired GB1437510A (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
FR7344445A FR2330276A5 (en) 1973-12-05 1973-12-05 SHOCK ABSORBER FOR TURBINE BLADES
GB5691673A GB1437510A (en) 1973-12-05 1973-12-07 Compressor or turbine vane damping
DE2361370A DE2361370A1 (en) 1973-12-05 1973-12-10 DEVICE FOR DAMPING COMPRESSOR OR TURBINE BLADES

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR7344445A FR2330276A5 (en) 1973-12-05 1973-12-05 SHOCK ABSORBER FOR TURBINE BLADES
GB5691673A GB1437510A (en) 1973-12-05 1973-12-07 Compressor or turbine vane damping
DE2361370A DE2361370A1 (en) 1973-12-05 1973-12-10 DEVICE FOR DAMPING COMPRESSOR OR TURBINE BLADES

Publications (1)

Publication Number Publication Date
GB1437510A true GB1437510A (en) 1976-05-26

Family

ID=27185664

Family Applications (1)

Application Number Title Priority Date Filing Date
GB5691673A Expired GB1437510A (en) 1973-12-05 1973-12-07 Compressor or turbine vane damping

Country Status (3)

Country Link
DE (1) DE2361370A1 (en)
FR (1) FR2330276A5 (en)
GB (1) GB1437510A (en)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4354801A (en) * 1981-01-23 1982-10-19 Coppus Engineerng Corporation Reaction fan with noise suppression
GB2227192A (en) * 1988-12-29 1990-07-25 Gen Electric Damped gas turbine engine airfoil row
GB2436130A (en) * 2005-12-15 2007-09-19 Rolls Royce Plc Stator vane arrangement with anti-bonding layer
GB2450934A (en) * 2007-07-13 2009-01-14 Rolls Royce Plc A component with a damping filler
US8241004B2 (en) 2008-05-15 2012-08-14 Rolls-Royce, Plc Component structure
US8365388B2 (en) 2009-01-28 2013-02-05 Rolls-Royce Plc Method of joining plates of material to form a structure
US8529720B2 (en) 2008-07-24 2013-09-10 Rolls-Royce, Plc Aerofoil sub-assembly, an aerofoil and a method of making an aerofoil
US8701286B2 (en) 2010-06-02 2014-04-22 Rolls-Royce Plc Rotationally balancing a rotating part
US8920893B2 (en) 2009-01-27 2014-12-30 Rolls-Royce Plc Article with an internal structure
US8986490B2 (en) 2010-11-26 2015-03-24 Rolls-Royce Plc Method of manufacturing a component

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3235585C2 (en) * 1982-09-01 1985-11-14 Christian O. 7590 Achern Schön High-performance blowers or compressors for aggressive and / or hot media
FR2606071B1 (en) * 1986-10-29 1990-11-30 Snecma STATOR STAGE AND TURBOMACHINE COMPRESSOR COMPRISING THE SAME
FR2697285B1 (en) * 1992-10-28 1994-11-25 Snecma Blade end locking system.
FR2702242B1 (en) * 1993-03-03 1995-04-07 Snecma Free blades stage at one end.
EP2075415B1 (en) * 2007-12-27 2016-10-19 Techspace Aero Lightened annular stator structure for aircraft turboshaft engine
EP2075414A1 (en) * 2007-12-27 2009-07-01 Techspace aero Internal collar of a stator for delimiting a primary flow of an aircraft turboshaft engine

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4354801A (en) * 1981-01-23 1982-10-19 Coppus Engineerng Corporation Reaction fan with noise suppression
GB2227192A (en) * 1988-12-29 1990-07-25 Gen Electric Damped gas turbine engine airfoil row
GB2436130A (en) * 2005-12-15 2007-09-19 Rolls Royce Plc Stator vane arrangement with anti-bonding layer
GB2436130B (en) * 2005-12-15 2008-01-30 Rolls Royce Plc A vane arrangement and a method of making vane arrangement
US7837444B2 (en) 2005-12-15 2010-11-23 Rolls-Royce Plc Vane arrangement and a method of making vane arrangement
US8381398B2 (en) 2007-07-13 2013-02-26 Rolls-Royce Plc Component with a damping filler and method
GB2450934A (en) * 2007-07-13 2009-01-14 Rolls Royce Plc A component with a damping filler
GB2450934B (en) * 2007-07-13 2009-10-07 Rolls Royce Plc A Component with a damping filler
US8182233B2 (en) 2007-07-13 2012-05-22 Rolls-Royce Plc Component with a damping filler
US8857054B2 (en) 2007-07-13 2014-10-14 Rolls-Royce Plc Method of forming an aerofoil with a damping filler
US8241004B2 (en) 2008-05-15 2012-08-14 Rolls-Royce, Plc Component structure
US8529720B2 (en) 2008-07-24 2013-09-10 Rolls-Royce, Plc Aerofoil sub-assembly, an aerofoil and a method of making an aerofoil
US8920893B2 (en) 2009-01-27 2014-12-30 Rolls-Royce Plc Article with an internal structure
US8365388B2 (en) 2009-01-28 2013-02-05 Rolls-Royce Plc Method of joining plates of material to form a structure
US8701286B2 (en) 2010-06-02 2014-04-22 Rolls-Royce Plc Rotationally balancing a rotating part
US8986490B2 (en) 2010-11-26 2015-03-24 Rolls-Royce Plc Method of manufacturing a component

Also Published As

Publication number Publication date
FR2330276A5 (en) 1977-05-27
DE2361370A1 (en) 1975-06-19

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PCNP Patent ceased through non-payment of renewal fee