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BE766401A - VANED ROTOR FOR TURBOMACHINE - Google Patents

VANED ROTOR FOR TURBOMACHINE

Info

Publication number
BE766401A
BE766401A BE766401A BE766401A BE766401A BE 766401 A BE766401 A BE 766401A BE 766401 A BE766401 A BE 766401A BE 766401 A BE766401 A BE 766401A BE 766401 A BE766401 A BE 766401A
Authority
BE
Belgium
Prior art keywords
turbomachine
vaned rotor
vaned
rotor
Prior art date
Application number
BE766401A
Other languages
French (fr)
Inventor
B J Anderson
W E Schoenborn
Original Assignee
Gen Electric
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 Gen Electric filed Critical Gen Electric
Publication of BE766401A publication Critical patent/BE766401A/en

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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • 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
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Applications Or Details Of Rotary Compressors (AREA)
BE766401A 1970-04-30 1971-04-28 VANED ROTOR FOR TURBOMACHINE BE766401A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US3322070A 1970-04-30 1970-04-30

Publications (1)

Publication Number Publication Date
BE766401A true BE766401A (en) 1971-09-16

Family

ID=21869177

Family Applications (1)

Application Number Title Priority Date Filing Date
BE766401A BE766401A (en) 1970-04-30 1971-04-28 VANED ROTOR FOR TURBOMACHINE

Country Status (6)

Country Link
US (1) US3661475A (en)
BE (1) BE766401A (en)
CA (1) CA943467A (en)
DE (1) DE2120470A1 (en)
FR (1) FR2092118B1 (en)
GB (1) GB1340937A (en)

Families Citing this family (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE791162A (en) * 1971-11-10 1973-03-01 Penny Robert N TURBINE ROTOR
US4310286A (en) * 1979-05-17 1982-01-12 United Technologies Corporation Rotor assembly having a multistage disk
US4536129A (en) * 1984-06-15 1985-08-20 United Technologies Corporation Turbine blade with disk rim shield
US4595340A (en) * 1984-07-30 1986-06-17 General Electric Company Gas turbine bladed disk assembly
FR2679296B1 (en) * 1991-07-17 1993-10-15 Snecma SEPARATE INTER-BLADE PLATFORM FOR TURBOMACHINE ROTOR WING DISC.
US5271718A (en) * 1992-08-11 1993-12-21 General Electric Company Lightweight platform blade
FR2697051B1 (en) * 1992-10-21 1994-12-02 Snecma Turbomachine rotor comprising a disk whose periphery is occupied by oblique cells which alternate with teeth of variable cross section.
US5310318A (en) * 1993-07-21 1994-05-10 General Electric Company Asymmetric axial dovetail and rotor disk
GB9405473D0 (en) * 1994-03-19 1994-05-04 Rolls Royce Plc A gas turbine engine fan blade assembly
US6511294B1 (en) 1999-09-23 2003-01-28 General Electric Company Reduced-stress compressor blisk flowpath
US6524070B1 (en) 2000-08-21 2003-02-25 General Electric Company Method and apparatus for reducing rotor assembly circumferential rim stress
US6471474B1 (en) 2000-10-20 2002-10-29 General Electric Company Method and apparatus for reducing rotor assembly circumferential rim stress
JP2003120209A (en) * 2001-10-10 2003-04-23 Mitsubishi Heavy Ind Ltd Sealing structure of spindle bolt and gas turbine
US6764282B2 (en) * 2001-11-14 2004-07-20 United Technologies Corporation Blade for turbine engine
FR2868814B1 (en) * 2004-04-09 2009-12-18 Snecma Moteurs DEVICE FOR ASSEMBLING ANNULAR FLANGES, PARTICULARLY IN A TURBOMACHINE
US7179049B2 (en) * 2004-12-10 2007-02-20 Pratt & Whitney Canada Corp. Gas turbine gas path contour
US7360437B2 (en) * 2005-06-28 2008-04-22 General Electric Company Devices for evaluating material properties, and related processes
US20140174098A1 (en) * 2012-12-20 2014-06-26 United Technologies Corporation Turbine disc with reduced neck stress concentration

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA590294A (en) * 1960-01-05 Rolls-Royce Limited Axial-flow compressors and turbines
US2452782A (en) * 1945-01-16 1948-11-02 Power Jets Res & Dev Ltd Construction of rotors for compressors and like machines
US3291446A (en) * 1965-04-13 1966-12-13 Chrysler Corp Turbine wheel
GB1093568A (en) * 1965-11-23 1967-12-06 Rolls Royce Improvements in or relating to bladed rotors such as compressor rotors
US3383095A (en) * 1967-09-12 1968-05-14 Gen Electric Lock for turbomachinery blades
US3556675A (en) * 1969-01-29 1971-01-19 Gen Electric Turbomachinery rotor with integral shroud

Also Published As

Publication number Publication date
FR2092118B1 (en) 1974-10-11
CA943467A (en) 1974-03-12
US3661475A (en) 1972-05-09
GB1340937A (en) 1973-12-19
DE2120470A1 (en) 1971-11-11
FR2092118A1 (en) 1972-01-21

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