GB0408867D0 - Undercut leading edge for compressor blades and related method - Google Patents

Undercut leading edge for compressor blades and related method

Info

Publication number
GB0408867D0
GB0408867D0 GBGB0408867.0A GB0408867A GB0408867D0 GB 0408867 D0 GB0408867 D0 GB 0408867D0 GB 0408867 A GB0408867 A GB 0408867A GB 0408867 D0 GB0408867 D0 GB 0408867D0
Authority
GB
United Kingdom
Prior art keywords
leading edge
related method
compressor blades
undercut leading
undercut
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.)
Withdrawn
Application number
GBGB0408867.0A
Other versions
GB2401657A (en
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of GB0408867D0 publication Critical patent/GB0408867D0/en
Publication of GB2401657A publication Critical patent/GB2401657A/en
Withdrawn legal-status Critical Current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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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
    • F01D5/14—Form or construction
    • F01D5/16—Form or construction for counteracting blade vibration
    • 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
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • 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
    • F05D2300/40—Organic materials
    • F05D2300/43—Synthetic polymers, e.g. plastics; Rubber
    • F05D2300/433—Polyamides, e.g. NYLON

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
GB0408867A 2003-04-25 2004-04-21 Compressor blade with dovetail slotted to reduce stress on the airfoil leading edge Withdrawn GB2401657A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US10/422,701 US20040213672A1 (en) 2003-04-25 2003-04-25 Undercut leading edge for compressor blades and related method

Publications (2)

Publication Number Publication Date
GB0408867D0 true GB0408867D0 (en) 2004-05-26
GB2401657A GB2401657A (en) 2004-11-17

Family

ID=32393308

Family Applications (1)

Application Number Title Priority Date Filing Date
GB0408867A Withdrawn GB2401657A (en) 2003-04-25 2004-04-21 Compressor blade with dovetail slotted to reduce stress on the airfoil leading edge

Country Status (3)

Country Link
US (1) US20040213672A1 (en)
JP (1) JP2004324648A (en)
GB (1) GB2401657A (en)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6951447B2 (en) * 2003-12-17 2005-10-04 United Technologies Corporation Turbine blade with trailing edge platform undercut
US7252481B2 (en) * 2004-05-14 2007-08-07 Pratt & Whitney Canada Corp. Natural frequency tuning of gas turbine engine blades
GB0427083D0 (en) 2004-12-10 2005-01-12 Rolls Royce Plc Platform mounted components
US20090297351A1 (en) * 2008-05-28 2009-12-03 General Electric Company Compressor rotor blade undercut
US8287241B2 (en) * 2008-11-21 2012-10-16 Alstom Technology Ltd Turbine blade platform trailing edge undercut
US8550783B2 (en) * 2011-04-01 2013-10-08 Alstom Technology Ltd. Turbine blade platform undercut
US10450872B2 (en) 2016-11-08 2019-10-22 Rolls-Royce Corporation Undercut on airfoil coversheet support member
US11834960B2 (en) * 2022-02-18 2023-12-05 General Electric Company Methods and apparatus to reduce deflection of an airfoil

Family Cites Families (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2994507A (en) * 1959-01-23 1961-08-01 Westinghouse Electric Corp Blade locking structure
GB906476A (en) * 1960-10-11 1962-09-19 Fairweather Harold G C Improvements in rotor assemblies for turbines, compressors and the like
JPS51127302A (en) * 1975-04-30 1976-11-06 Hitachi Ltd Rotor of convex type rotary machine
JPS57186004A (en) * 1981-05-13 1982-11-16 Hitachi Ltd Structure of rotor for turbo-machine
US4480957A (en) * 1983-04-14 1984-11-06 General Electric Company Dynamic response modification and stress reduction in dovetail and blade assembly
US4682935A (en) * 1983-12-12 1987-07-28 General Electric Company Bowed turbine blade
US4872810A (en) * 1988-12-14 1989-10-10 United Technologies Corporation Turbine rotor retention system
US5123813A (en) * 1991-03-01 1992-06-23 General Electric Company Apparatus for preloading an airfoil blade in a gas turbine engine
US5156528A (en) * 1991-04-19 1992-10-20 General Electric Company Vibration damping of gas turbine engine buckets
US5205713A (en) * 1991-04-29 1993-04-27 General Electric Company Fan blade damper
US5108261A (en) * 1991-07-11 1992-04-28 United Technologies Corporation Compressor disk assembly
US5302085A (en) * 1992-02-03 1994-04-12 General Electric Company Turbine blade damper
FR2716931B1 (en) * 1994-03-03 1996-04-05 Snecma Balancing and damping system of a turbomachine disc.
US5634766A (en) * 1994-08-23 1997-06-03 General Electric Co. Turbine stator vane segments having combined air and steam cooling circuits
US5573377A (en) * 1995-04-21 1996-11-12 General Electric Company Assembly of a composite blade root and a rotor
WO1997049921A1 (en) * 1996-06-21 1997-12-31 Siemens Aktiengesellschaft Rotor for a turbomachine with blades insertable into grooves and blades for a rotor
US6033185A (en) * 1998-09-28 2000-03-07 General Electric Company Stress relieved dovetail
US6457942B1 (en) * 2000-11-27 2002-10-01 General Electric Company Fan blade retainer
US6390775B1 (en) * 2000-12-27 2002-05-21 General Electric Company Gas turbine blade with platform undercut
US6520836B2 (en) * 2001-02-28 2003-02-18 General Electric Company Method of forming a trailing edge cutback for a turbine bucket
US6752594B2 (en) * 2002-02-07 2004-06-22 The Boeing Company Split blade frictional damper
US6769877B2 (en) * 2002-10-18 2004-08-03 General Electric Company Undercut leading edge for compressor blades and related method
US6902376B2 (en) * 2002-12-26 2005-06-07 General Electric Company Compressor blade with dovetail slotted to reduce stress on the airfoil leading edge

Also Published As

Publication number Publication date
US20040213672A1 (en) 2004-10-28
JP2004324648A (en) 2004-11-18
GB2401657A (en) 2004-11-17

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Legal Events

Date Code Title Description
WAP Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1)