GB2001398A - Bladed Rotor for Gas Turbine Engine - Google Patents

Bladed Rotor for Gas Turbine Engine

Info

Publication number
GB2001398A
GB2001398A GB7830155A GB7830155A GB2001398A GB 2001398 A GB2001398 A GB 2001398A GB 7830155 A GB7830155 A GB 7830155A GB 7830155 A GB7830155 A GB 7830155A GB 2001398 A GB2001398 A GB 2001398A
Authority
GB
United Kingdom
Prior art keywords
gas turbine
turbine engine
bladed rotor
blade
undercut
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.)
Withdrawn
Application number
GB7830155A
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB7830155A priority Critical patent/GB2001398A/en
Publication of GB2001398A publication Critical patent/GB2001398A/en
Withdrawn legal-status Critical Current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
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • F01D5/3046—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses the rotor having ribs around the circumference

Abstract

Comprises a blade-carrying disc 15 having a thickened rim 18, and a plurality of blades 16 each attached to the disc by engagement between the thickened rim and the undercut faces 29,30 of an undercut aperture formed in the root portion 23 of the blade. A locking plate 31 is provided for each blade. <IMAGE>
GB7830155A 1977-07-22 1978-07-18 Bladed Rotor for Gas Turbine Engine Withdrawn GB2001398A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB7830155A GB2001398A (en) 1977-07-22 1978-07-18 Bladed Rotor for Gas Turbine Engine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB3080677 1977-07-22
GB7830155A GB2001398A (en) 1977-07-22 1978-07-18 Bladed Rotor for Gas Turbine Engine

Publications (1)

Publication Number Publication Date
GB2001398A true GB2001398A (en) 1979-01-31

Family

ID=26260613

Family Applications (1)

Application Number Title Priority Date Filing Date
GB7830155A Withdrawn GB2001398A (en) 1977-07-22 1978-07-18 Bladed Rotor for Gas Turbine Engine

Country Status (1)

Country Link
GB (1) GB2001398A (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0077236A1 (en) * 1981-10-09 1983-04-20 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Mounting of blades in segments on a rotor disc of a turbo machine
DE3934207A1 (en) * 1989-10-13 1991-04-25 Mtu Muenchen Gmbh ARRANGEMENT FOR FASTENING TURBO BLADES
US5018941A (en) * 1989-01-11 1991-05-28 Societe Nationale D'etude Et De Construction De Moteurs D'aviation"S.N.E.C.M.A. Blade fixing arrangement for a turbomachine rotor
GB2245033A (en) * 1990-04-03 1991-12-18 Gen Electric Turbine blade attachment structure
CN103967840A (en) * 2013-02-04 2014-08-06 航空技术空间股份有限公司 Attaching the blades of an axial turbocompressor to the compressor drum

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0077236A1 (en) * 1981-10-09 1983-04-20 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Mounting of blades in segments on a rotor disc of a turbo machine
US5018941A (en) * 1989-01-11 1991-05-28 Societe Nationale D'etude Et De Construction De Moteurs D'aviation"S.N.E.C.M.A. Blade fixing arrangement for a turbomachine rotor
DE3934207A1 (en) * 1989-10-13 1991-04-25 Mtu Muenchen Gmbh ARRANGEMENT FOR FASTENING TURBO BLADES
GB2245033A (en) * 1990-04-03 1991-12-18 Gen Electric Turbine blade attachment structure
US5131813A (en) * 1990-04-03 1992-07-21 General Electric Company Turbine blade outer end attachment structure
CN103967840A (en) * 2013-02-04 2014-08-06 航空技术空间股份有限公司 Attaching the blades of an axial turbocompressor to the compressor drum
EP2762681A1 (en) * 2013-02-04 2014-08-06 Techspace Aero S.A. Rotor drum of an axial turbomachine and corresponding turbomachine
US20140219803A1 (en) * 2013-02-04 2014-08-07 Techspace Aero S.A. Attaching the Blades of an Axial Turbocompressor to the Compressor Drum
US9739150B2 (en) * 2013-02-04 2017-08-22 Safran Aero Boosters Sa Attaching the blades of an axial turbocompressor to the compressor drum
CN103967840B (en) * 2013-02-04 2018-12-18 赛峰航空助推器股份有限公司 The blade of axial flow turbine compressor is connected to compressor drum

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Legal Events

Date Code Title Description
WAP Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1)