GB950527A - Improvements in a turbine driven fan rotor - Google Patents

Improvements in a turbine driven fan rotor

Info

Publication number
GB950527A
GB950527A GB34417/61A GB3441761A GB950527A GB 950527 A GB950527 A GB 950527A GB 34417/61 A GB34417/61 A GB 34417/61A GB 3441761 A GB3441761 A GB 3441761A GB 950527 A GB950527 A GB 950527A
Authority
GB
United Kingdom
Prior art keywords
walls
turbine
members
tabs
blades
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
GB34417/61A
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 GB950527A publication Critical patent/GB950527A/en
Expired legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
    • B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
    • B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
    • 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
    • F01D5/022—Blade-carrying members, e.g. rotors with concentric rows of axial blades
    • 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
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

950,527. Turbine driven fan augmentors. GENERAL ELECTRIC CO. Sept. 26, 1961 [Oct. 7, 1960], No. 34417/61. Headings F1G, F1J and F1T. A rotor for a turbine driven fan comprises a hub 10, radially inner fan blades 11 and radially outer turbine blades 13, the outer ends of the fan blades and the inner ends of the turbine blades being secured to arcuate segmental carrier members 12 interconnected by overlapping fish-plate members of U-shaped cross-section 17 to form a ring. The carrier members 12 are formed from U-shaped channel with the side walls 15 reinforced by triangular trusses 33. The carriers are joined together by fish-plate members 17 having tabs 19 loose pinned by bolts or rivets to the walls 15. The space between the two fan blades attached to each carrier 12 is filled by members 18 also having tabs 21 rigidly fixed by bolts or rivets to the walls 15. The rotor also has sealing bands 26 attached to the walls 15 by tabs 27. The bands have walls 28 co-operating with seals 32 carried by the walls 30 defining the turbine area 29.
GB34417/61A 1960-10-07 1961-09-26 Improvements in a turbine driven fan rotor Expired GB950527A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US61248A US3070284A (en) 1960-10-07 1960-10-07 Turbo-fan rotor

Publications (1)

Publication Number Publication Date
GB950527A true GB950527A (en) 1964-02-26

Family

ID=22034583

Family Applications (1)

Application Number Title Priority Date Filing Date
GB34417/61A Expired GB950527A (en) 1960-10-07 1961-09-26 Improvements in a turbine driven fan rotor

Country Status (3)

Country Link
US (1) US3070284A (en)
BE (1) BE608937A (en)
GB (1) GB950527A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110439623A (en) * 2019-08-14 2019-11-12 上海两擎机电科技合伙企业(有限合伙) Aircraft engine fan blade metal hemming edge, processing tool and processing method

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3404831A (en) * 1966-12-07 1968-10-08 Gen Electric Turbine bucket supporting structure
GB1118898A (en) * 1967-04-03 1968-07-03 Rolls Royce Fluid flow machine
GB2192237B (en) * 1986-07-02 1990-05-16 Rolls Royce Plc Gas turbine engine power turbine
US5108259A (en) * 1988-12-19 1992-04-28 General Electric Company Flexible connector for use in aircraft
US6454535B1 (en) 2000-10-31 2002-09-24 General Electric Company Blisk
CA2925842A1 (en) * 2013-10-03 2015-04-09 Franco Tosi Meccanica S.P.A. Rotor stage of axial turbine with improved chord/pitch ratio
US10119403B2 (en) 2014-02-13 2018-11-06 United Technologies Corporation Mistuned concentric airfoil assembly and method of mistuning same
US10927683B2 (en) * 2017-12-14 2021-02-23 Safran Aircraft Engines Damping device

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA584125A (en) * 1959-09-29 E. Moss Charles Blading for gas turbine engines
US2429681A (en) * 1942-02-27 1947-10-28 Griffith Alan Arnold Thrust balancing construction for turbines, compressors, and the like
US2398140A (en) * 1943-12-08 1946-04-09 Armstrong Siddeley Motors Ltd Bladed rotor
US2518660A (en) * 1944-09-07 1950-08-15 Wright Aeronautical Corp Internal-combustion engine and exhaust gas turbine therefor
US2625365A (en) * 1949-02-26 1953-01-13 Curtiss Wright Corp Shrouded impeller
US2868439A (en) * 1954-05-07 1959-01-13 Goodyear Aircraft Corp Plastic axial-flow compressor for gas turbines
US2819870A (en) * 1955-04-18 1958-01-14 Oleh A Wayne Sheet metal blade base

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110439623A (en) * 2019-08-14 2019-11-12 上海两擎机电科技合伙企业(有限合伙) Aircraft engine fan blade metal hemming edge, processing tool and processing method
CN110439623B (en) * 2019-08-14 2024-05-14 上海两擎机电科技合伙企业(有限合伙) Metal edging for aircraft engine fan blade, machining tool and machining method

Also Published As

Publication number Publication date
BE608937A (en) 1962-02-01
US3070284A (en) 1962-12-25

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