GB1385968A - Support structures for turbo-machine blades - Google Patents

Support structures for turbo-machine blades

Info

Publication number
GB1385968A
GB1385968A GB2884672A GB2884672A GB1385968A GB 1385968 A GB1385968 A GB 1385968A GB 2884672 A GB2884672 A GB 2884672A GB 2884672 A GB2884672 A GB 2884672A GB 1385968 A GB1385968 A GB 1385968A
Authority
GB
United Kingdom
Prior art keywords
drum
blades
roots
grooves
bars
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
GB2884672A
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.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
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 SNECMA SAS filed Critical SNECMA SAS
Publication of GB1385968A publication Critical patent/GB1385968A/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
    • 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
    • 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)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

1385968 Turbomachines; axial flow compressors SOC NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION 20 June 1972 [29 June 1971] 28846/72 Headings F1C and FIT A support structure for turbomachine blades 8 comprises a hollow casing or drum 2 of fibrous material to a surface of which axially extending metal blade-carrier bars 3 are attached side by side. The structure may be a stator, but in the arrangement shown forms a compressor rotor for a gas turbine engine. Drum 2 is constructed of helically wound, resin covered, glass or carbon fibres to which titanium bars 3 are secured by a resin based adhesive. The bars 3 are shaped to define projections 4 a , 4 b ... 4 p and recesses 5 a , 5 b ... 5 p containing reinforcing rings 10 a , 10 b , ... 10 p of fibrous material wound about the drum. The projections 4 a &c. are hollowed out at 16 to reduce weight and include axially extending dovetail grooves 7 a &c. containing the roots 9 of blades 8. Roots 9 are axially shorter than grooves 7 a &c. to permit the ends of dovetail roots 12 on spacers 11 to be mounted in the grooves. Sealing ribs 13 on spacers 11 co-operate with shroud rings 14 on the adjacent stator blades 15. Reinforcing rings 10 a &c. are omitted when the structure is a stator casing.
GB2884672A 1971-06-29 1972-06-20 Support structures for turbo-machine blades Expired GB1385968A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR7123689A FR2143561B1 (en) 1971-06-29 1971-06-29

Publications (1)

Publication Number Publication Date
GB1385968A true GB1385968A (en) 1975-03-05

Family

ID=9079504

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2884672A Expired GB1385968A (en) 1971-06-29 1972-06-20 Support structures for turbo-machine blades

Country Status (4)

Country Link
US (1) US3813185A (en)
DE (1) DE2231175C3 (en)
FR (1) FR2143561B1 (en)
GB (1) GB1385968A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0277906A2 (en) * 1987-02-02 1988-08-10 United Technologies Corporation Composite disk for supporting fan blades
RU172776U1 (en) * 2016-10-31 2017-07-24 Публичное акционерное общество "Научно-производственное объединение "Сатурн" TURBINE STATOR

Families Citing this family (33)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3904316A (en) * 1974-08-16 1975-09-09 Gen Motors Corp Turbine rotor with slot loaded blades and composite bands
GB1485032A (en) * 1974-08-23 1977-09-08 Rolls Royce Gas turbine engine casing
US3966523A (en) * 1975-08-11 1976-06-29 United Technologies Corporation Method of making filament reinforced composite rings from plural flat filamentary spiral layers
GB1549422A (en) * 1976-10-19 1979-08-08 Rolls Royce Axial flow gas turbine engine compressor
GB1553038A (en) * 1977-04-28 1979-09-19 Snecma Drum for an axial flow compressor rotor and process for its manufacture
FR2404134A1 (en) * 1977-09-23 1979-04-20 Snecma ROTOR FOR TURBOMACHINES
FR2404212A1 (en) * 1977-09-23 1979-04-20 Snecma ROTOR BALANCING DEVICE
DE3019920C2 (en) * 1980-05-24 1982-12-30 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Device for the outer casing of the rotor blades of axial turbines for gas turbine engines
DE3037388C1 (en) * 1980-10-03 1982-06-16 Deutsche Forschungs- und Versuchsanstalt für Luft- und Raumfahrt e.V., 5300 Bonn Bandage for the radial tensioning of the segments of a compressor impeller for gas turbines constructed from individual segments
GB2108628B (en) * 1981-10-28 1985-04-03 Rolls Royce Means for reducing stress in clamped assemblies
DE3407946A1 (en) * 1984-03-03 1985-09-05 MTU Motoren- und Turbinen-Union München GmbH, 8000 München DEVICE FOR PREVENTING THE SPREADING OF TITANIUM FIRE IN TURBO MACHINES, ESPECIALLY GAS TURBINE OR. GAS TURBINE JET ENGINES
US4536129A (en) * 1984-06-15 1985-08-20 United Technologies Corporation Turbine blade with disk rim shield
DE3711764A1 (en) * 1987-04-07 1988-10-27 Mtu Muenchen Gmbh AXIAL GUIDE GRID FOR COMPRESSORS
US4867644A (en) * 1987-05-15 1989-09-19 Allied-Signal Inc. Composite member, unitary rotor member including same, and method of making
FR2755468B1 (en) * 1996-11-07 1998-12-04 Snecma ROTOR STAGE OF TURBOMACHINE REINFORCED WITH FIBERS
GB9623948D0 (en) * 1996-11-18 1997-01-08 Lewmar Marine Ltd Winch
GB2456637B (en) * 1997-06-03 2010-01-13 Rolls Royce Plc A fibre reinforced metal rotor
US6213720B1 (en) 1999-06-11 2001-04-10 Alliedsignal, Inc. High strength composite reinforced turbomachinery disk
US6929453B2 (en) * 2003-12-11 2005-08-16 Siemens Westinghouse Power Corporation Locking spacer assembly for slotted turbine component
US7252481B2 (en) * 2004-05-14 2007-08-07 Pratt & Whitney Canada Corp. Natural frequency tuning of gas turbine engine blades
US7052235B2 (en) * 2004-06-08 2006-05-30 General Electric Company Turbine engine shroud segment, hanger and assembly
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
DE102008051933A1 (en) * 2008-10-09 2010-04-15 Mtu Aero Engines Gmbh Holding device for holding at least one rotor blade and method for mounting a blade ring
US8011877B2 (en) * 2008-11-24 2011-09-06 General Electric Company Fiber composite reinforced aircraft gas turbine engine drums with radially inwardly extending blades
EP2287445A1 (en) * 2009-07-16 2011-02-23 Techspace Aero S.A. Axial compressor rotor drum with composite web
WO2014163674A1 (en) * 2013-03-13 2014-10-09 Freeman Ted J Dovetail retention system for blade tracks
US9777593B2 (en) * 2015-02-23 2017-10-03 General Electric Company Hybrid metal and composite spool for rotating machinery
US10047763B2 (en) 2015-12-14 2018-08-14 General Electric Company Rotor assembly for use in a turbofan engine and method of assembling
DE102016219818A1 (en) * 2016-10-12 2018-04-12 Rolls-Royce Deutschland Ltd & Co Kg Blade assembly with ring segment or disc segment-shaped blade carrier and radially inner stiffening structure
DE102016219815A1 (en) * 2016-10-12 2018-04-12 Rolls-Royce Deutschland Ltd & Co Kg Blade assembly with ring-shaped or disk-shaped blade carrier and radially inner stiffening structure
BE1027150B1 (en) 2019-03-29 2020-10-26 Safran Aero Boosters Sa HYBRID ROTOR WITH EXTERNAL SHELL BUILT AGAINST COMPOSITE ANNULAR WALL
BE1027343B1 (en) 2019-06-07 2021-01-14 Safran Aero Boosters Sa HYBRID ROTOR WITH PLATFORM PIONEERS PENETRATING INTO THE DRUM
BE1027359B1 (en) 2019-06-11 2021-01-21 Safran Aero Boosters Sa HYBRID ROTOR WITH EXTERNAL SHELL BUILT AGAINST COMPOSITE ANNULAR WALL

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1170592A (en) * 1966-11-29 1969-11-12 Rolls Royce Aerofoil-Shaped Blades and Blade Assemblies, for use in a Fluid Flow Machine
GB1170593A (en) * 1967-04-12 1969-11-12 Rolls Royce Method of making a Bladed Rotor
US3554668A (en) * 1969-05-12 1971-01-12 Gen Motors Corp Turbomachine rotor
US3554667A (en) * 1969-08-25 1971-01-12 Gen Motors Corp Turbomachine rotor
US3625634A (en) * 1969-12-10 1971-12-07 Gen Motors Corp Turbomachine rotor

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0277906A2 (en) * 1987-02-02 1988-08-10 United Technologies Corporation Composite disk for supporting fan blades
EP0277906A3 (en) * 1987-02-02 1990-01-31 United Technologies Corporation Composite disk for supporting fan blades
RU172776U1 (en) * 2016-10-31 2017-07-24 Публичное акционерное общество "Научно-производственное объединение "Сатурн" TURBINE STATOR

Also Published As

Publication number Publication date
DE2231175A1 (en) 1973-01-18
US3813185A (en) 1974-05-28
DE2231175C3 (en) 1979-05-03
FR2143561A1 (en) 1973-02-09
FR2143561B1 (en) 1974-03-08
DE2231175B2 (en) 1978-09-14

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PCNP Patent ceased through non-payment of renewal fee