GB1124560A - Turbomachine rotors - Google Patents

Turbomachine rotors

Info

Publication number
GB1124560A
GB1124560A GB36789/67A GB3678967A GB1124560A GB 1124560 A GB1124560 A GB 1124560A GB 36789/67 A GB36789/67 A GB 36789/67A GB 3678967 A GB3678967 A GB 3678967A GB 1124560 A GB1124560 A GB 1124560A
Authority
GB
United Kingdom
Prior art keywords
blades
blade
root
stalk
side plates
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
GB36789/67A
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.)
Motors Liquidation Co
Original Assignee
Motors Liquidation 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 Motors Liquidation Co filed Critical Motors Liquidation Co
Publication of GB1124560A publication Critical patent/GB1124560A/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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

1,124,560. Turbines. GENERAL MOTORS CORP. Aug. 10, 1967 [Dec. 8, 1966], No.36789/67. Heading F1T. Hollow sheet metal blades 14 are retained in position on the rotor 5 of a turbine or like machine by the engagement of flared root portions 18, 19 on each blade between the profiled faces of adjacent platforms 13 having stalks 11 and roots 10 mounted in axial slots 7 in the rotor rim 6. A plug 21 welded in position stiffens the root of each blade, a passage 23 in the plug permitting cooling air to flow to the blade interior from an annular chamber defined between annular side plates 41, 43. A boss 26 on each stalk 11 prevents the blades moving radially inwards. Each stalk is lightened by drillings 31, 33 and is retained axially in position in the slot 7 by a tang 29 on its root 10. The blades may be of porous material, to assist cooling, except in the regions of plugs 21, the outer ends of the blades being closed by metal caps 25. The side plates 41, 43 engage at their outer peripheries in slots 37, 38, respectively, in the platforms 13.
GB36789/67A 1966-12-08 1967-08-10 Turbomachine rotors Expired GB1124560A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US60013666A 1966-12-08 1966-12-08

Publications (1)

Publication Number Publication Date
GB1124560A true GB1124560A (en) 1968-08-21

Family

ID=24402454

Family Applications (1)

Application Number Title Priority Date Filing Date
GB36789/67A Expired GB1124560A (en) 1966-12-08 1967-08-10 Turbomachine rotors

Country Status (2)

Country Link
US (1) US3471127A (en)
GB (1) GB1124560A (en)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3741681A (en) * 1971-05-28 1973-06-26 Westinghouse Electric Corp Hollow turbine rotor assembly
US4688992A (en) * 1985-01-25 1987-08-25 General Electric Company Blade platform
GB2251897B (en) * 1991-01-15 1994-11-30 Rolls Royce Plc A rotor
US5277548A (en) * 1991-12-31 1994-01-11 United Technologies Corporation Non-integral rotor blade platform
GB0521242D0 (en) * 2005-10-19 2005-11-23 Rolls Royce Plc A blade mounting
EP2336572B1 (en) * 2009-12-14 2012-07-25 Techspace Aero S.A. Shroud or section of shroud in two parts for a vane diffuser of an axial compressor
US20120156045A1 (en) * 2010-12-17 2012-06-21 General Electric Company Methods, systems and apparatus relating to root and platform configurations for turbine rotor blades
US8740573B2 (en) * 2011-04-26 2014-06-03 General Electric Company Adaptor assembly for coupling turbine blades to rotor disks
US10125619B2 (en) * 2015-11-19 2018-11-13 General Electric Company Rotor assembly for use in a turbofan engine and method of assembling

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE350318A (en) * 1928-04-06
US2873947A (en) * 1953-11-26 1959-02-17 Power Jets Res & Dev Ltd Blade mounting for compressors, turbines and like fluid flow machines
US2828940A (en) * 1953-12-30 1958-04-01 United Aircraft Corp Cooled turbine blade
BE551145A (en) * 1955-09-26
NL222612A (en) * 1956-11-30
US3002675A (en) * 1957-11-07 1961-10-03 Power Jets Res & Dev Ltd Blade elements for turbo machines
US3294364A (en) * 1962-01-02 1966-12-27 Gen Electric Rotor assembly

Also Published As

Publication number Publication date
US3471127A (en) 1969-10-07

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