GB1355751A - Bladed rotor assemblies - Google Patents

Bladed rotor assemblies

Info

Publication number
GB1355751A
GB1355751A GB4063272A GB4063272A GB1355751A GB 1355751 A GB1355751 A GB 1355751A GB 4063272 A GB4063272 A GB 4063272A GB 4063272 A GB4063272 A GB 4063272A GB 1355751 A GB1355751 A GB 1355751A
Authority
GB
United Kingdom
Prior art keywords
blade
laminations
pad
filaments
root
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
GB4063272A
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.)
Raytheon Technologies Corp
Original Assignee
United Aircraft Corp
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 United Aircraft Corp filed Critical United Aircraft Corp
Publication of GB1355751A publication Critical patent/GB1355751A/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
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments
    • 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)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Composite Materials (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

1355751 Turbine bladed rotor assembly UNITED AIRCRAFT CORP 1 Sept 1972 [9 Dec 1971] 40632/72 Heading FIT The invention relates to a bladed rotor assembly, for example of a turbine, comprising a rotor disc 28 formed with a plurality of axially-extending blade-mounting slots 26 at its periphery. Each blade comprises high strength non-metallic filaments embedded in matrix material, such as carbon filaments in an epoxy matrix, and comprises an aerofoil portion 10 and a splayed root portion 14. A pad 22 is disposed on each side of the blade, each pad having a first surface 23 which engages with a blade in the region of transition between the aerofoil and root portions and a second surface which engages with a surface of the blade-mounting slot, the two surfaces of the pad converging in a direction away from the aerofoil portion, the pad during rotor operation being a main load-transferring member between the blade and the disc. The blade shown is formed of laminations 16 and 18, the filaments of the laminations 16 extending lengthwise thereof and the filaments of the laminations 18 being inclined with respect to the length of the laminations. Wedge-shaped metallic inserts 20 are disposed between the laminations so as to form the splayed root 14. The pads 22 may or may not be bonded to the blades. The surface 24 of the pad is inclined at angle 44 of 60 degrees to the plane 46 normal to the blade axis while the surface 23 is inclined at angle 48 of 45 degrees thereto.
GB4063272A 1971-12-09 1972-09-01 Bladed rotor assemblies Expired GB1355751A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US20642671A 1971-12-09 1971-12-09

Publications (1)

Publication Number Publication Date
GB1355751A true GB1355751A (en) 1974-06-05

Family

ID=22766323

Family Applications (1)

Application Number Title Priority Date Filing Date
GB4063272A Expired GB1355751A (en) 1971-12-09 1972-09-01 Bladed rotor assemblies

Country Status (8)

Country Link
US (1) US3752600A (en)
AU (1) AU456333B2 (en)
CA (1) CA959034A (en)
DE (1) DE2240970C2 (en)
FR (1) FR2164134A5 (en)
GB (1) GB1355751A (en)
IT (1) IT971617B (en)
SE (1) SE385038B (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2243193A (en) * 1990-03-19 1991-10-23 Gen Electric Gas turbine engine blade
GB2574319B (en) * 2018-04-20 2022-10-05 Safran Aircraft Engines Vane comprising a structure made of composite material and method for manufacturing the same

Families Citing this family (43)

* Cited by examiner, † Cited by third party
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US4040770A (en) * 1975-12-22 1977-08-09 General Electric Company Transition reinforcement of composite blade dovetails
US4111606A (en) * 1976-12-27 1978-09-05 United Technologies Corporation Composite rotor blade
US4343593A (en) * 1980-01-25 1982-08-10 The United States Of America As Represented By The Secretary Of The Air Force Composite blade for turbofan engine fan
US4363602A (en) * 1980-02-27 1982-12-14 General Electric Company Composite air foil and disc assembly
US4810167A (en) * 1986-12-08 1989-03-07 Hartzell Propeller Inc. Composite aircraft propeller blade
FR2608674B1 (en) * 1986-12-17 1991-04-19 Snecma CERAMIC BLADE TURBINE WHEEL
US5375978A (en) * 1992-05-01 1994-12-27 General Electric Company Foreign object damage resistant composite blade and manufacture
US5573377A (en) * 1995-04-21 1996-11-12 General Electric Company Assembly of a composite blade root and a rotor
US6290466B1 (en) 1999-09-17 2001-09-18 General Electric Company Composite blade root attachment
US6857856B2 (en) * 2002-09-27 2005-02-22 Florida Turbine Technologies, Inc. Tailored attachment mechanism for composite airfoils
US7300255B2 (en) * 2002-09-27 2007-11-27 Florida Turbine Technologies, Inc. Laminated turbomachine airfoil with jacket and method of making the airfoil
DE10326719A1 (en) * 2003-06-06 2004-12-23 Rolls-Royce Deutschland Ltd & Co Kg Compressor blade base for engine blades of aircraft engines
US20050158171A1 (en) * 2004-01-15 2005-07-21 General Electric Company Hybrid ceramic matrix composite turbine blades for improved processibility and performance
DE102004005237B4 (en) * 2004-02-03 2007-03-01 Mtu Aero Engines Gmbh Guide vane grille of a gas turbine
US7008170B2 (en) * 2004-03-26 2006-03-07 Siemens Westinghouse Power Corporation Compressor diaphragm with axial preload
DE102006049818A1 (en) * 2006-10-18 2008-04-24 Rolls-Royce Deutschland Ltd & Co Kg Fan blade made of textile composite material
GB2443482A (en) * 2006-11-02 2008-05-07 Smiths Group Plc Propeller blade retention
DE102006061916A1 (en) * 2006-12-21 2008-06-26 Rolls-Royce Deutschland Ltd & Co Kg Fan blade for a gas turbine engine
US7758307B2 (en) * 2007-05-17 2010-07-20 Siemens Energy, Inc. Wear minimization system for a compressor diaphragm
US8206118B2 (en) * 2008-01-04 2012-06-26 United Technologies Corporation Airfoil attachment
US8123463B2 (en) * 2008-07-31 2012-02-28 General Electric Company Method and system for manufacturing a blade
FR2957051B1 (en) * 2010-03-08 2012-05-11 Snecma LEATHER ATTACHING RECEIVING A BLADE FOOT IN A BROACHING
US8573947B2 (en) * 2010-03-10 2013-11-05 United Technologies Corporation Composite fan blade dovetail root
FR2963383B1 (en) * 2010-07-27 2016-09-09 Snecma DUST OF TURBOMACHINE, ROTOR, LOW PRESSURE TURBINE AND TURBOMACHINE EQUIPPED WITH SUCH A DAWN
US8794925B2 (en) 2010-08-24 2014-08-05 United Technologies Corporation Root region of a blade for a gas turbine engine
US10041354B2 (en) * 2011-09-14 2018-08-07 General Electric Company Blade and method for manufacturing blade
US9611746B2 (en) * 2012-03-26 2017-04-04 United Technologies Corporation Blade wedge attachment
US9115584B2 (en) * 2012-04-24 2015-08-25 General Electric Company Resistive band for turbomachine blade
US20150192023A1 (en) * 2012-06-08 2015-07-09 Nicholas Joseph Kray Mechanical Interlock Feature for Multi-Material Airfoils
US10633985B2 (en) * 2012-06-25 2020-04-28 General Electric Company System having blade segment with curved mounting geometry
US9664052B2 (en) 2012-10-03 2017-05-30 General Electric Company Turbine component, turbine blade, and turbine component fabrication process
FR2998827B1 (en) * 2012-12-05 2015-02-06 Snecma PROCESS FOR MANUFACTURING A TURBOMACHINE TURRET FOOT IN COMPOSITE MATERIAL AND DAWN FOOT OBTAINED BY SUCH A METHOD
US9777579B2 (en) 2012-12-10 2017-10-03 General Electric Company Attachment of composite article
US9797257B2 (en) 2012-12-10 2017-10-24 General Electric Company Attachment of composite article
US9506356B2 (en) * 2013-03-15 2016-11-29 Rolls-Royce North American Technologies, Inc. Composite retention feature
US10774660B2 (en) 2013-10-14 2020-09-15 Raytheon Technologies Corporation Blade wedge attachment lay-up
CA2936196A1 (en) 2014-01-16 2015-07-23 General Electric Company Composite blade root stress reducing shim
US10174624B1 (en) * 2014-06-05 2019-01-08 United Technologies Corporation Composite blade root lay-up
DE102015223404B4 (en) * 2015-11-26 2019-01-31 Airbus Defence and Space GmbH Tensile test, method for producing a tensile test, apparatus for carrying out a tensile test and method for carrying out a tensile test
JP6745832B2 (en) * 2018-03-29 2020-08-26 三菱重工業株式会社 Composite material blade and method for manufacturing composite material blade
JP6738850B2 (en) * 2018-03-29 2020-08-12 三菱重工業株式会社 Composite material blade and method of manufacturing composite material blade
US12078080B1 (en) 2023-04-21 2024-09-03 General Electric Company Airfoil assembly with a trunnion and spar
US11846192B1 (en) 2023-04-21 2023-12-19 General Electric Company Airfoil assembly with a trunnion and spar

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2749029A (en) * 1948-11-26 1956-06-05 Sintercast Corp America Compressor blade
US2821357A (en) * 1950-05-09 1958-01-28 Maschf Augsburg Nuernberg Ag Connection of ceramic and metallic machine parts
GB709636A (en) * 1951-05-09 1954-06-02 Rolls Royce Improvements in or relating to compressor and turbine bladed rotors
GB734157A (en) * 1952-09-04 1955-07-27 Maschf Augsburg Nuernberg Ag Improvements in or relating to ceramic rotor blades for axial flow turbines, compressor and pumps
CH317252A (en) * 1952-09-06 1956-11-15 Maschf Augsburg Nuernberg Ag Impeller for centrifugal machines with axial flow
US2950083A (en) * 1954-07-23 1960-08-23 Thompson Ramo Wooldridge Inc Blade assembly
DE1025421B (en) * 1955-10-31 1958-03-06 Maschf Augsburg Nuernberg Ag Fastening of blades made of sproated material in a metallic blade carrier
US3132841A (en) * 1958-05-12 1964-05-12 Gen Motors Corp Compressor blade and manufacture thereof
FR1281033A (en) * 1961-02-15 1962-01-08 Daimler Benz Ag Assembly of ceramic moving blades on machines with centrifugal rotors axially traversed by currents, in particular on gas turbines
NL301760A (en) * 1962-12-14
US3600103A (en) * 1969-10-06 1971-08-17 United Aircraft Corp Composite blade
US3679324A (en) * 1970-12-04 1972-07-25 United Aircraft Corp Filament reinforced gas turbine blade

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2243193A (en) * 1990-03-19 1991-10-23 Gen Electric Gas turbine engine blade
GB2574319B (en) * 2018-04-20 2022-10-05 Safran Aircraft Engines Vane comprising a structure made of composite material and method for manufacturing the same

Also Published As

Publication number Publication date
IT971617B (en) 1974-05-10
DE2240970C2 (en) 1983-01-13
DE2240970A1 (en) 1973-06-14
CA959034A (en) 1974-12-10
SE385038B (en) 1976-05-31
AU4592872A (en) 1974-03-07
AU456333B2 (en) 1974-12-12
FR2164134A5 (en) 1973-07-27
US3752600A (en) 1973-08-14

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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