GB1272200A - Axial-flow turbomachine rotors - Google Patents

Axial-flow turbomachine rotors

Info

Publication number
GB1272200A
GB1272200A GB56216/70A GB5621670A GB1272200A GB 1272200 A GB1272200 A GB 1272200A GB 56216/70 A GB56216/70 A GB 56216/70A GB 5621670 A GB5621670 A GB 5621670A GB 1272200 A GB1272200 A GB 1272200A
Authority
GB
United Kingdom
Prior art keywords
axial
recesses
mounting portion
bosses
turbomachine rotors
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
GB56216/70A
Inventor
Rowland Leroy Stedfeld
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 GB1272200A publication Critical patent/GB1272200A/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
    • F01D5/02—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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor

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)

Abstract

1,272,200. Turbomachine rotors. GENERAL MOTORS CORP. Nov. 26, 1970 [Dec. 10, 1969], No.56216/70. Heading F1T. An axial-flow turbine or compressor rotor is formed by a series of abutting rings 10 each of which has a blade mounting portion 18 and an axially extending flange portion 19 reinforced by a wrap 34 of glass or boron fibres in an epoxy resin matrix. Each mounting portion 18 has angularly spaced bosses 24 on its inner surface, aerofoil slots 28 being machined through the bosses 24 to receive the roots 27 of blades 26. The latter are brazed or welded in position, flutes 30 and recesses 31 being provided on each root 27 to improve the joint. Adjacent rings 10 interengage by means of lips 20 and recesses 22 and may be secured together by electron beam welding at 23 or by a tie bolt (15), Fig. 1 (not shown).
GB56216/70A 1969-12-10 1970-11-26 Axial-flow turbomachine rotors Expired GB1272200A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US88392069A 1969-12-10 1969-12-10

Publications (1)

Publication Number Publication Date
GB1272200A true GB1272200A (en) 1972-04-26

Family

ID=25383588

Family Applications (1)

Application Number Title Priority Date Filing Date
GB56216/70A Expired GB1272200A (en) 1969-12-10 1970-11-26 Axial-flow turbomachine rotors

Country Status (3)

Country Link
US (1) US3625634A (en)
CA (1) CA927751A (en)
GB (1) GB1272200A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0017567A1 (en) * 1979-04-04 1980-10-15 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Device for fixing blades to the rotor of the compressor of a turbojet plant
EP2287445A1 (en) 2009-07-16 2011-02-23 Techspace Aero S.A. Axial compressor rotor drum with composite web

Families Citing this family (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2143561B1 (en) * 1971-06-29 1974-03-08 Snecma
DE2150741C3 (en) * 1971-10-12 1973-11-22 Messerschmitt Boelkow Blohm The rotor blades of a rotary wing aircraft are suspended from the rotor head without flapping or pivot joints
US3904316A (en) * 1974-08-16 1975-09-09 Gen Motors Corp Turbine rotor with slot loaded blades and composite bands
GB1553038A (en) * 1977-04-28 1979-09-19 Snecma Drum for an axial flow compressor rotor and process for its manufacture
IT1135752B (en) * 1981-04-17 1986-08-27 Nuovo Pignone Spa IMPROVEMENTS IN THE POWER STAGE OF A GAS TURBINE
US4566700A (en) * 1982-08-09 1986-01-28 United Technologies Corporation Abrasive/abradable gas path seal system
US4483054A (en) * 1982-11-12 1984-11-20 United Technologies Corporation Method for making a drum rotor
DE3316535A1 (en) * 1983-05-06 1984-11-08 MTU Motoren- und Turbinen-Union München GmbH, 8000 München TURBO COMPRESSOR WITH INLET COVER
US4648802A (en) * 1984-09-06 1987-03-10 Pda Engineering Radial flow rotor with inserts and turbine utilizing the same
US4867644A (en) * 1987-05-15 1989-09-19 Allied-Signal Inc. Composite member, unitary rotor member including same, and method of making
US4919594A (en) * 1987-05-15 1990-04-24 Allied-Signal Inc. Composite member, unitary rotor member including same, and method of making
US5632600A (en) * 1995-12-22 1997-05-27 General Electric Company Reinforced rotor disk assembly
DE19650260A1 (en) * 1996-12-04 1998-06-10 Asea Brown Boveri Rotor for turbomachinery
GB2456637B (en) * 1997-06-03 2010-01-13 Rolls Royce Plc A fibre reinforced metal rotor
US6217283B1 (en) * 1999-04-20 2001-04-17 General Electric Company Composite fan platform
US6213720B1 (en) 1999-06-11 2001-04-10 Alliedsignal, Inc. High strength composite reinforced turbomachinery disk
DE10259822B4 (en) * 2002-12-19 2009-01-02 Siemens Ag Electric machine with bandaged, deep-cooling winding
DE10358421A1 (en) * 2003-12-13 2005-07-07 Mtu Aero Engines Gmbh Rotor for a turbomachine
DE102006011513A1 (en) 2006-03-10 2007-09-13 Rolls-Royce Deutschland Ltd & Co Kg Inlet cone of a fiber composite material for a gas turbine engine and method for its production
DE102006015838A1 (en) * 2006-04-03 2007-10-04 Rolls-Royce Deutschland Ltd & Co Kg Axial compressor e.g. high pressure compressor, for gas turbine engine, has rotor drum that is formed from rotor rings with fiber belts and is made from high temperature resistant fibers that are bedded with polymer e.g. polyamide
US8011877B2 (en) 2008-11-24 2011-09-06 General Electric Company Fiber composite reinforced aircraft gas turbine engine drums with radially inwardly extending blades
EP2204541B1 (en) * 2008-12-24 2012-03-07 Techspace Aero S.A. Rotor stage of an integral bladed compressor drum of an axial turbomachine and corresponding manufacturing method.
UA111842C2 (en) * 2011-07-19 2016-06-24 Елліотт Компані Assembly and method of attaching stub shaft to drum of axial compressor rotor shaft
US8777576B2 (en) 2011-08-22 2014-07-15 General Electric Company Metallic fan blade platform
GB201611674D0 (en) * 2016-07-05 2016-08-17 Rolls Royce Plc A turbine arrangement
CN111550435A (en) * 2020-05-25 2020-08-18 中国航发沈阳发动机研究所 Multistage rotor disk connection structure

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR980131A (en) * 1951-05-08
US2143466A (en) * 1937-12-31 1939-01-10 Westinghouse Electric & Mfg Co Turbine apparatus
FR907059A (en) * 1946-09-20 1946-02-28 High temperature gas turbine
US2803397A (en) * 1952-05-20 1957-08-20 Gen Motors Corp Compressor wheel
GB1170592A (en) * 1966-11-29 1969-11-12 Rolls Royce Aerofoil-Shaped Blades and Blade Assemblies, for use in a Fluid Flow Machine
US3403844A (en) * 1967-10-02 1968-10-01 Gen Electric Bladed member and method for making
US3519368A (en) * 1968-09-03 1970-07-07 Gen Electric Composite turbomachinery rotors

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0017567A1 (en) * 1979-04-04 1980-10-15 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Device for fixing blades to the rotor of the compressor of a turbojet plant
FR2453294A1 (en) * 1979-04-04 1980-10-31 Snecma DEVICE FOR FIXING BLADES ON A COMPRESSOR ROTOR FOR A TURBO-REACTOR
EP2287445A1 (en) 2009-07-16 2011-02-23 Techspace Aero S.A. Axial compressor rotor drum with composite web

Also Published As

Publication number Publication date
US3625634A (en) 1971-12-07
CA927751A (en) 1973-06-05

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PLNP Patent lapsed through nonpayment of renewal fees