RU2281402C2 - Металлическое изделие с выполненной за одно целое концевой полосой под сжатием и способ его изготовления - Google Patents

Металлическое изделие с выполненной за одно целое концевой полосой под сжатием и способ его изготовления Download PDF

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Publication number
RU2281402C2
RU2281402C2 RU2001121022/06A RU2001121022A RU2281402C2 RU 2281402 C2 RU2281402 C2 RU 2281402C2 RU 2001121022/06 A RU2001121022/06 A RU 2001121022/06A RU 2001121022 A RU2001121022 A RU 2001121022A RU 2281402 C2 RU2281402 C2 RU 2281402C2
Authority
RU
Russia
Prior art keywords
aerodynamic profile
strip
compressive stress
end part
metal material
Prior art date
Application number
RU2001121022/06A
Other languages
English (en)
Russian (ru)
Other versions
RU2001121022A (ru
Inventor
Дэвид Вилль м КРОЛЛ (US)
Дэвид Вилльям КРОЛЛ
Питер Джон ЛИНКО III (US)
Питер Джон ЛИНКО III
Original Assignee
Дженерал Электрик Компани
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 Дженерал Электрик Компани filed Critical Дженерал Электрик Компани
Publication of RU2001121022A publication Critical patent/RU2001121022A/ru
Application granted granted Critical
Publication of RU2281402C2 publication Critical patent/RU2281402C2/ru

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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
    • F01D5/14—Form or construction
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P9/00—Treating or finishing surfaces mechanically, with or without calibrating, primarily to resist wear or impact, e.g. smoothing or roughening turbine blades or bearings; Features of such surfaces not otherwise provided for, their treatment being unspecified
    • B23P9/02—Treating or finishing by applying pressure, e.g. knurling
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B24—GRINDING; POLISHING
    • B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
    • B24B39/00—Burnishing machines or devices, i.e. requiring pressure members for compacting the surface zone; Accessories therefor
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D7/00—Modifying the physical properties of iron or steel by deformation
    • C21D7/02—Modifying the physical properties of iron or steel by deformation by cold working
    • C21D7/04—Modifying the physical properties of iron or steel by deformation by cold working of the surface
    • 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
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/286—Particular treatment of blades, e.g. to increase durability or resistance against corrosion or erosion
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D2221/00—Treating localised areas of an article
    • C21D2221/01—End parts (e.g. leading, trailing end)
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D2221/00—Treating localised areas of an article
    • C21D2221/02—Edge parts
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49336—Blade making

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • General Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Clamps And Clips (AREA)
RU2001121022/06A 2000-07-27 2001-07-26 Металлическое изделие с выполненной за одно целое концевой полосой под сжатием и способ его изготовления RU2281402C2 (ru)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US09/627,143 2000-07-27
US09/627,143 US6672838B1 (en) 2000-07-27 2000-07-27 Method for making a metallic article with integral end band under compression

Publications (2)

Publication Number Publication Date
RU2001121022A RU2001121022A (ru) 2003-04-10
RU2281402C2 true RU2281402C2 (ru) 2006-08-10

Family

ID=24513365

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2001121022/06A RU2281402C2 (ru) 2000-07-27 2001-07-26 Металлическое изделие с выполненной за одно целое концевой полосой под сжатием и способ его изготовления

Country Status (11)

Country Link
US (2) US6672838B1 (enExample)
EP (1) EP1175956B1 (enExample)
JP (1) JP2002155702A (enExample)
CN (1) CN100519055C (enExample)
BR (1) BR0103027B1 (enExample)
CA (1) CA2353265C (enExample)
DE (1) DE60114943T2 (enExample)
MX (1) MXPA01007587A (enExample)
MY (1) MY129152A (enExample)
RU (1) RU2281402C2 (enExample)
SG (1) SG101992A1 (enExample)

Families Citing this family (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10245396A1 (de) * 2002-09-28 2004-04-15 Mtu Aero Engines Gmbh Vorrichtung und Verfahren zur Oberflächenbearbeitung von Werkstücken
FR2871399B1 (fr) * 2004-06-15 2006-09-22 Snecma Moteurs Sa Procede de reparation d'un element d'aube
US7229253B2 (en) 2004-11-30 2007-06-12 General Electric Company Fatigue-resistant components and method therefor
US7384244B2 (en) * 2004-12-16 2008-06-10 General Electric Company Fatigue-resistant components and method therefor
JPWO2006117847A1 (ja) * 2005-04-27 2008-12-18 株式会社日立製作所 マイクロガスタービン
US7217099B2 (en) * 2005-05-24 2007-05-15 General Electric Company Coated forward stub shaft dovetail slot
US20060280612A1 (en) * 2005-06-09 2006-12-14 Prevey Paul S Iii Metallic article with integral end band under compression
US7805972B2 (en) * 2005-10-12 2010-10-05 Surface Technology Holdings Ltd. Integrally bladed rotating turbo machinery and method and apparatus for achieving the same
US8024846B2 (en) * 2006-01-27 2011-09-27 General Electric Company Preparation of an article surface having a surface compressive texture
US20070281088A1 (en) * 2006-06-02 2007-12-06 United Technologies Corporation Low plasticity burnishing of coated titanium parts
US7530792B2 (en) * 2006-06-30 2009-05-12 General Electric Company Component of variable thickness having residual compressive stresses therein, and method therefor
KR20080012744A (ko) * 2006-08-03 2008-02-12 유나이티드 테크놀로지스 코포레이션 부식 코팅되는 부품의 코팅전 버니싱
US8079120B2 (en) * 2006-12-30 2011-12-20 General Electric Company Method for determining initial burnishing parameters
US8051565B2 (en) * 2006-12-30 2011-11-08 General Electric Company Method for increasing fatigue notch capability of airfoils
GB0704426D0 (en) * 2007-03-08 2007-04-18 Rolls Royce Plc Aerofoil members for a turbomachine
ES2343397B1 (es) * 2008-03-07 2011-06-13 GAMESA INNOVATION & TECHNOLOGY, S.L. Una pala de aerogenerador.
US8539659B2 (en) * 2008-04-23 2013-09-24 United Technologies Corporation Method of repairing an article
US8753065B2 (en) 2012-09-27 2014-06-17 United Technologies Corporation Method for setting a gear ratio of a fan drive gear system of a gas turbine engine
CN114292994A (zh) * 2021-12-30 2022-04-08 西北工业大学 一种薄壁叶片低塑性滚压强化方法

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SU1600899A1 (ru) * 1988-02-22 1990-10-23 Винницкий политехнический институт Способ изготовлени лопаток
US5591009A (en) * 1995-01-17 1997-01-07 General Electric Company Laser shock peened gas turbine engine fan blade edges
US5620307A (en) * 1995-03-06 1997-04-15 General Electric Company Laser shock peened gas turbine engine blade tip
US5666841A (en) * 1993-03-22 1997-09-16 Siemens Aktiengesellschaft Method for work-hardening by rolling a component
US5826453A (en) * 1996-12-05 1998-10-27 Lambda Research, Inc. Burnishing method and apparatus for providing a layer of compressive residual stress in the surface of a workpiece

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB302657A (en) * 1927-12-19 1929-03-07 Gen Electric Improvements in and relating to turbine blades
GB1127157A (en) * 1966-06-13 1968-09-11 Orenda Ltd Method for improving the fatigue resistance of turbine blades
US4839245A (en) * 1985-09-30 1989-06-13 Union Carbide Corporation Zirconium nitride coated article and method for making same
US5476363A (en) * 1993-10-15 1995-12-19 Charles E. Sohl Method and apparatus for reducing stress on the tips of turbine or compressor blades
US6215097B1 (en) * 1994-12-22 2001-04-10 General Electric Company On the fly laser shock peening
US5531570A (en) * 1995-03-06 1996-07-02 General Electric Company Distortion control for laser shock peened gas turbine engine compressor blade edges
IL117347A (en) * 1995-03-06 1999-10-28 Gen Electric Laser shock peened gas turbine engine compressor airfoil edges
US5735044A (en) * 1995-12-12 1998-04-07 General Electric Company Laser shock peening for gas turbine engine weld repair
JP3728006B2 (ja) * 1996-03-29 2005-12-21 ゼネラル・エレクトリック・カンパニイ ガスタービン機関のファンの羽根
US6005219A (en) * 1997-12-18 1999-12-21 General Electric Company Ripstop laser shock peening
US5932120A (en) * 1997-12-18 1999-08-03 General Electric Company Laser shock peening using low energy laser
US5951790A (en) * 1998-06-26 1999-09-14 General Electric Company Method of monitoring and controlling laser shock peening using an in plane deflection test coupon
JP2000087897A (ja) * 1998-09-08 2000-03-28 Hitachi Ltd ガスタービンの圧縮機翼およびガスタービン

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SU1600899A1 (ru) * 1988-02-22 1990-10-23 Винницкий политехнический институт Способ изготовлени лопаток
US5666841A (en) * 1993-03-22 1997-09-16 Siemens Aktiengesellschaft Method for work-hardening by rolling a component
US5591009A (en) * 1995-01-17 1997-01-07 General Electric Company Laser shock peened gas turbine engine fan blade edges
US5620307A (en) * 1995-03-06 1997-04-15 General Electric Company Laser shock peened gas turbine engine blade tip
US5826453A (en) * 1996-12-05 1998-10-27 Lambda Research, Inc. Burnishing method and apparatus for providing a layer of compressive residual stress in the surface of a workpiece

Also Published As

Publication number Publication date
CN1336265A (zh) 2002-02-20
SG101992A1 (en) 2004-02-27
US6893225B2 (en) 2005-05-17
MY129152A (en) 2007-03-30
CA2353265A1 (en) 2002-01-27
CA2353265C (en) 2008-10-21
DE60114943D1 (de) 2005-12-22
BR0103027A (pt) 2002-02-26
JP2002155702A (ja) 2002-05-31
US6672838B1 (en) 2004-01-06
EP1175956B1 (en) 2005-11-16
MXPA01007587A (es) 2004-07-30
BR0103027B1 (pt) 2010-05-04
US20040109767A1 (en) 2004-06-10
CN100519055C (zh) 2009-07-29
DE60114943T2 (de) 2006-08-03
EP1175956A1 (en) 2002-01-30

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MM4A The patent is invalid due to non-payment of fees

Effective date: 20070727