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GB1170593A - Method of making a Bladed Rotor - Google Patents

Method of making a Bladed Rotor

Info

Publication number
GB1170593A
GB1170593A GB06873/67A GB1687367A GB1170593A GB 1170593 A GB1170593 A GB 1170593A GB 06873/67 A GB06873/67 A GB 06873/67A GB 1687367 A GB1687367 A GB 1687367A GB 1170593 A GB1170593 A GB 1170593A
Authority
GB
United Kingdom
Prior art keywords
fibres
jig
blades
alternatively
recesses
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
GB06873/67A
Inventor
Jack Palfreyman
Henry Edward Middleton
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 GB06873/67A priority Critical patent/GB1170593A/en
Priority to FR147477A priority patent/FR1575682A/fr
Priority to CH532168A priority patent/CH497641A/en
Priority to US720600A priority patent/US3515501A/en
Priority to BE713585D priority patent/BE713585A/xx
Priority to DE19681751156 priority patent/DE1751156A1/en
Publication of GB1170593A publication Critical patent/GB1170593A/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
    • F01D5/30—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
    • F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
    • F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides
    • 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
    • F01D5/12—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

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Composite Materials (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

1,170,593. Making bladed rotors; welding by fusion and pressure; brazing. ROLLS-ROYCE Ltd. 5 April, 1968 [12 April, 1967], No. 16873/67. Headings B3A and B3R. [Also in Divisions B5 and F1] A rotor blade assembly is formed by interconnecting the root portions of angularly spaced blades by at least one length of fibrous material. The rotor may be a turbine or compressor rotor of a gas turbine engine and is produced by mounting the blades 10 on a jig and rotating the jig so as to wind a large number of turns of the fibres 21 in circumferential recesses 15, 16 in the root portions 12. The fibres 21 may be of carbon or boron and may be passed through an oven (22), Fig. 1 (not shown), and an electrolytic plating bath (23) during the winding operation. In the bath (23) the fibres 21 are coated with a nickel-chromium alloy or with beryllium, cobalt, chromium, nickel, hafnium, niobium, osmium, palladium, platinum, rhenium, rhodium, tantalum or vanadium. Alternatively, the coating may be effected by spraying or vacuum deposition. After winding, the coated fibres are compacted and then bonded in the recesses 15, 16 by placing the jig with its blades 10 in an electrolytic plating bath so as to bond the fibres by the plating material. Alternatively, the bonding may be effected by hot pressing, brazing, or welding using explosion, electron beam, laser or diffusion methods. When this has been done the jig is removed and the blade assembly secured to a disc or drum by bonding or by spacer members secured to the sides of the root portions 12. The coat. ing material of the fibres may alternatively be a synthetic resin material such as an epoxy, polymide, polyquinoxaline or polythiazole resin. In this case, the fibres 21 are bonded in the recesses 15, 16 after winding by injecting further resin material. The blades 10 may be formed of conventional material or of coated fibres the same as the fibres 21.
GB06873/67A 1967-04-12 1967-04-12 Method of making a Bladed Rotor Expired GB1170593A (en)

Priority Applications (6)

Application Number Priority Date Filing Date Title
GB06873/67A GB1170593A (en) 1967-04-12 1967-04-12 Method of making a Bladed Rotor
FR147477A FR1575682A (en) 1967-04-12 1968-04-09
CH532168A CH497641A (en) 1967-04-12 1968-04-09 Bladed rotor, for the compressor or turbine of a gas turbine engine, is made by applying circumferentially, over flanged root sections of the assembled blades,
US720600A US3515501A (en) 1967-04-12 1968-04-11 Rotor blade assembly
BE713585D BE713585A (en) 1967-04-12 1968-04-11
DE19681751156 DE1751156A1 (en) 1967-04-12 1968-04-11 Blade assembly for flow machines and method for making the same

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB06873/67A GB1170593A (en) 1967-04-12 1967-04-12 Method of making a Bladed Rotor

Publications (1)

Publication Number Publication Date
GB1170593A true GB1170593A (en) 1969-11-12

Family

ID=10085214

Family Applications (1)

Application Number Title Priority Date Filing Date
GB06873/67A Expired GB1170593A (en) 1967-04-12 1967-04-12 Method of making a Bladed Rotor

Country Status (6)

Country Link
US (1) US3515501A (en)
BE (1) BE713585A (en)
CH (1) CH497641A (en)
DE (1) DE1751156A1 (en)
FR (1) FR1575682A (en)
GB (1) GB1170593A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU181073U1 (en) * 2018-01-09 2018-07-04 Федеральное государственное бюджетное образовательное учреждение высшего образования "Санкт-Петербургский государственный архитектурно-строительный университет" AXIAL COMPRESSOR DRUM TYPE ROTOR
CN114934815A (en) * 2022-05-12 2022-08-23 中国航发四川燃气涡轮研究院 Hoop type engine rotor blade ring structure made of metal matrix composite material

Families Citing this family (32)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3610772A (en) * 1970-05-04 1971-10-05 Gen Motors Corp Bladed rotor
DE2046486C3 (en) * 1970-09-21 1974-03-07 Fa. Willi Seeber, Kardaun, Bozen (Italien) Impeller for fan
FR2143561B1 (en) * 1971-06-29 1974-03-08 Snecma
GB1428365A (en) * 1972-03-15 1976-03-17 Rolls Royce Fluid flow machines
IT1066506B (en) * 1973-12-17 1985-03-12 Seeber Willi BLADE WHEEL FOR FANS AND PROCEDURE TO PRODUCE IT
GB1553038A (en) * 1977-04-28 1979-09-19 Snecma Drum for an axial flow compressor rotor and process for its manufacture
FR2448626A1 (en) * 1979-02-08 1980-09-05 Snecma IMPROVEMENT IN ROTORS OF ROTATING MACHINES
DE2915201C2 (en) * 1979-04-14 1986-02-27 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Impeller for axial flow machines, in particular compressors
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
DE3101250C2 (en) * 1981-01-16 1983-12-01 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Compressor rotor for gas turbine engines
FR2539824A1 (en) * 1983-01-26 1984-07-27 Applic Rationnelles Physiq WHEEL FOR CENTRIFUGAL COMPRESSOR AND METHOD FOR MANUFACTURING SAME
DE3446732C2 (en) * 1984-12-21 1986-10-23 Süddeutsche Kühlerfabrik Julius Fr. Behr GmbH & Co KG, 7000 Stuttgart Fan wheel
FR2605586B1 (en) * 1986-10-22 1990-11-30 Snecma BLADE HOLDER FOR LARGE-SIZED PROPELLER BLADES
DE3711764A1 (en) * 1987-04-07 1988-10-27 Mtu Muenchen Gmbh AXIAL GUIDE GRID FOR COMPRESSORS
JPH02246897A (en) * 1988-12-29 1990-10-02 General Electric Co <Ge> Aircraft propulsion device and method
DE4321173C2 (en) * 1993-06-25 1996-02-22 Inst Luft Kaeltetech Gem Gmbh Radial impeller
FR2712630B1 (en) * 1993-11-17 1995-12-15 Snecma Segmented turbomachine rotor.
DE19525829A1 (en) * 1995-07-15 1997-01-16 Abb Research Ltd Fan
FR2755468B1 (en) * 1996-11-07 1998-12-04 Snecma ROTOR STAGE OF TURBOMACHINE REINFORCED WITH FIBERS
US5971706A (en) * 1997-12-03 1999-10-26 General Electric Company Inter-rotor bearing assembly
US6213720B1 (en) 1999-06-11 2001-04-10 Alliedsignal, Inc. High strength composite reinforced turbomachinery disk
DE10218459B3 (en) 2002-04-25 2004-01-15 Mtu Aero Engines Gmbh Multi-stage axial compressor
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
FR2943985B1 (en) * 2009-04-07 2011-05-13 Airbus France AIRCRAFT TURBOMACHINE PROPELLER COMPRISING A RETAINING RING OF AUBES MOUNTED AROUND THE HUB.
US8182213B2 (en) * 2009-04-22 2012-05-22 Pratt & Whitney Canada Corp. Vane assembly with removable vanes
US8540482B2 (en) 2010-06-07 2013-09-24 United Technologies Corporation Rotor assembly for gas turbine engine
US10710317B2 (en) * 2016-06-16 2020-07-14 Rolls-Royce North American Technologies Inc. Composite rotatable assembly for an axial-flow compressor
FR3057905B1 (en) * 2016-10-25 2020-06-12 Safran Aircraft Engines TURBOMACHINE TURNING PART
US10294954B2 (en) * 2016-11-09 2019-05-21 Rolls-Royce North American Technologies Inc. Composite blisk
WO2025132987A1 (en) * 2023-12-19 2025-06-26 Lilium GmbH Bladed disk for a driven rotor of an engine of an aircraft propulsion unit, propulsion unit for an aircraft and aircraft

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA611006A (en) * 1960-12-20 P. Warnken Elmer Rotating shroud
US1544318A (en) * 1923-09-12 1925-06-30 Westinghouse Electric & Mfg Co Turbine-blade lashing
US2155231A (en) * 1936-06-01 1939-04-18 Gen Electric Fan and method of making same
US2713991A (en) * 1951-05-05 1955-07-26 A V Roe Canada Ltd Rotor blade locking device
US2873088A (en) * 1953-05-21 1959-02-10 Gen Electric Lightweight rotor construction
US2857094A (en) * 1955-07-19 1958-10-21 John R Erwin Integral plastic rotors
US3279967A (en) * 1961-04-07 1966-10-18 Carrier Corp Method of fabricating a rotor shroud
FR1455278A (en) * 1965-08-05 1966-04-01 Snecma Double-flow turbojet
GB1054608A (en) * 1965-09-16
US3403844A (en) * 1967-10-02 1968-10-01 Gen Electric Bladed member and method for making

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU181073U1 (en) * 2018-01-09 2018-07-04 Федеральное государственное бюджетное образовательное учреждение высшего образования "Санкт-Петербургский государственный архитектурно-строительный университет" AXIAL COMPRESSOR DRUM TYPE ROTOR
CN114934815A (en) * 2022-05-12 2022-08-23 中国航发四川燃气涡轮研究院 Hoop type engine rotor blade ring structure made of metal matrix composite material
CN114934815B (en) * 2022-05-12 2023-10-31 中国航发四川燃气涡轮研究院 Metal matrix composite hoop type engine rotor blade ring structure

Also Published As

Publication number Publication date
CH497641A (en) 1970-10-15
US3515501A (en) 1970-06-02
BE713585A (en) 1968-08-16
DE1751156A1 (en) 1970-10-01
FR1575682A (en) 1969-07-25

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