DE2120470A1 - Laufer fur eine Turbinenanlage - Google Patents

Laufer fur eine Turbinenanlage

Info

Publication number
DE2120470A1
DE2120470A1 DE19712120470 DE2120470A DE2120470A1 DE 2120470 A1 DE2120470 A1 DE 2120470A1 DE 19712120470 DE19712120470 DE 19712120470 DE 2120470 A DE2120470 A DE 2120470A DE 2120470 A1 DE2120470 A1 DE 2120470A1
Authority
DE
Germany
Prior art keywords
circumferential edge
ramp
ramps
grooves
peripheral edge
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.)
Pending
Application number
DE19712120470
Other languages
German (de)
English (en)
Inventor
Bernard loseph Danvers Mass Schoenborn William Ernest Cincinnati Ohio Anderson, (V St A )
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 DE2120470A1 publication Critical patent/DE2120470A1/de
Pending 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
    • 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)
DE19712120470 1970-04-30 1971-04-27 Laufer fur eine Turbinenanlage Pending DE2120470A1 (de)

Applications Claiming Priority (1)

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

Publications (1)

Publication Number Publication Date
DE2120470A1 true DE2120470A1 (de) 1971-11-11

Family

ID=21869177

Family Applications (1)

Application Number Title Priority Date Filing Date
DE19712120470 Pending DE2120470A1 (de) 1970-04-30 1971-04-27 Laufer fur eine Turbinenanlage

Country Status (6)

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

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0677645A1 (en) * 1994-03-19 1995-10-18 ROLLS-ROYCE plc A gas turbine engine fan blade assembly

Families Citing this family (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE791162A (fr) * 1971-11-10 1973-03-01 Penny Robert N Rotor de turbine
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 (fr) * 1991-07-17 1993-10-15 Snecma Plate-forme separee inter-aube pour disque ailete de rotor de turbomachine.
US5271718A (en) * 1992-08-11 1993-12-21 General Electric Company Lightweight platform blade
FR2697051B1 (fr) * 1992-10-21 1994-12-02 Snecma Rotor de turbomachine comprenant un disque dont le pourtour est occupé par des alvéoles obliques qui alternent avec des dents de section transversale variable.
US5310318A (en) * 1993-07-21 1994-05-10 General Electric Company Asymmetric axial dovetail and rotor disk
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 (ja) * 2001-10-10 2003-04-23 Mitsubishi Heavy Ind Ltd スピンドルボルトのシール構造およびガスタービン
US6764282B2 (en) * 2001-11-14 2004-07-20 United Technologies Corporation Blade for turbine engine
FR2868814B1 (fr) * 2004-04-09 2009-12-18 Snecma Moteurs Dispositif d'assemblage de brides annulaires, en particulier dans une 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

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0677645A1 (en) * 1994-03-19 1995-10-18 ROLLS-ROYCE plc A gas turbine engine fan blade assembly
US5580217A (en) * 1994-03-19 1996-12-03 Rolls-Royce Plc Gas turbine engine fan blade assembly

Also Published As

Publication number Publication date
GB1340937A (en) 1973-12-19
FR2092118A1 (enrdf_load_stackoverflow) 1972-01-21
FR2092118B1 (enrdf_load_stackoverflow) 1974-10-11
BE766401A (fr) 1971-09-16
US3661475A (en) 1972-05-09
CA943467A (en) 1974-03-12

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