US3632460A - Epicyclic weaving of fiber discs - Google Patents

Epicyclic weaving of fiber discs Download PDF

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Publication number
US3632460A
US3632460A US3632460DA US3632460A US 3632460 A US3632460 A US 3632460A US 3632460D A US3632460D A US 3632460DA US 3632460 A US3632460 A US 3632460A
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United States
Prior art keywords
disc
fiber
fibers
woven
rotor
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Expired - Lifetime
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English (en)
Inventor
Jack Palfreyman
Henry Edward Middleton
Alan Anthony Baker
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Rolls Royce PLC
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Rolls Royce PLC
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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
    • F01D5/34—Rotor-blade aggregates of unitary construction, e.g. formed of sheet laminae
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/02—Selection of particular materials
    • F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
    • B29K2307/00—Use of elements other than metals as reinforcement
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • F05D2300/6034—Orientation of fibres, weaving, ply angle
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/611—Coating
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/612—Foam
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/615—Filler

Definitions

  • the present invention relates to the weaving of compressor or turbine discs from high-strength fiber materials.
  • the discs are woven from a single continuous fiber or bundle of fibers which pass backwards and forwards between diametrically opposed points across the disc tangential to a central aperture.
  • the fibers are woven in tension on a former using the epicycloid motion of a point on the circumference of a planet wheel in an epicyclic gear to generate the weaving pattern.
  • the fiber is coated as it is woven to provide a resin or metal matrix to anchor the weave.
  • the present invention relates to turbine and compressor rotors for gas turbine engines and includes a method of making such rotors with integral blades thereon.
  • a continuous fiber is meant to include a fiber in which two ends have been joined by an overlapping joint in which the length of overlap is at least ten fiber diameters.
  • a method of making a turbine or compressor rotor for a gas turbine engine comprises the steps of weaving a single continuous fiber or a continuous bundle of fibers onto a former in a plurality of passes between points on the circumference of the former, and on opposite sides of the center thereof, the fiber or bundle of fibers passing adjacent to the circumference of an aperture at the center of the rotor between each two points, and a radial movement being imposed on the weaving motion each time the fiber reaches the circumference of the former, with loops being formed at the end of each radially extending fiber portion, so that the radially extending fiber portions form reinforcing splines for rotor blades formed integrally with the rotor.
  • the method further includes a step of cutting the loops formed at the end of each radially extending fiber portion, and extending the cut portions of the loops circumferentially to form a shroud for each blade.
  • the fiber may be anchored at the rim of the former by providing additional material to thicken the rim.
  • the fibers are preferably held in tension throughout the weaving process and are also preferably coated with either a synthetic resin material or a metallic material.
  • fibers may be given an additional coating during the weaving process, which coating serves to hold the fiber in place.
  • the coating on the fiber may be a therrnosetting resin, for example epoxy, polyimide, polyquinoxaline, polythiazole, polybenzimidazole resins or a ladder polymer.
  • the fiber may be coated with a metal or a metal alloy, for example nickel, chromium, niobium, tantalum or an alloy of nickel and chromium.
  • a metal or a metal alloy for example nickel, chromium, niobium, tantalum or an alloy of nickel and chromium.
  • the fiber itself may be carbon, boron or silica.
  • the fibers may be coated with metal during an electrolytic process or alternatively the metal may be sprayed on in molten state, or vapor deposited.
  • the fibers are fed to a point on the circumference of a planet wheel of an epicyclic gear.
  • the point on the circumference to which the fiber is fed performs an epicycloid motion.
  • the fibers may be wound around pegs disposed on the circumference of the former or alternatively the former may comprise a disc which has been previously etched with grooves of a substantially epicycloid shape.
  • the whole of the woven disc may be filled with a filler material, for example a foamed ceramic in order to provide axial support for the fiber.
  • a filler material for example a foamed ceramic
  • the integral blade and disc may be formed with an integral shroud joining the blade tips by causing the weaving mechanism to move radially from the disc circumference outwards to fonn a flank of one blade and to then move circumferentially to the next blade and finally to move radially inwards to the circumference of the disc before performing the next pass across the disc.
  • the invention also includes a gas turbine engine provided with rotor discs woven as described above.
  • FIG. 1 illustrates diagrammatically a gas turbine engine to which the invention may be applied.
  • FIG. 2 shows a disc made by the method according to the present invention
  • FIG. 3 illustrates diagrammatically one type of machine for making discs according to the present invention
  • FIG. 4 shows how a blade may be formed integrally with the disc
  • FIG. 5 illustrates how an integral disc and blade may be provided with an integral shroud at the blade tip
  • FIG. 6 illustrates a finished blade with an integral shroud woven according to the present invention.
  • FIG. I there is shown a gas turbine engine 1 having compressor means 2, combustion equipment 3, turbine means 4 and a final nozzle 5 in flow series.
  • Both the compressor means 2 and the turbine means 4 of the gas turbine engine comprise rotor discs 6 on which are mounted a plurality of aerofoil-shaped blades.
  • One such rotor disc 6 is illustrated in FIG. 2 and comprises a plurality of fiber portions 7 of a single continuous fiber or continuous bundle of fibers, which are woven in tension between successive points on the circumference of the disc, the fiber portions passing adjacent to the circumference of a central aperture 8 of the disc.
  • the successive points on the circumference on the disc lie on opposite sides of the center of the disc, for example a fiber portion starting at.
  • the circumference at point 0 extends across the disc adjacent to the center apertures to a point b of the circumference on the opposite side of the center and then extends back across the disc adjacent to the central aperture to a point 0 on the circumference on the opposite side of the center. From there the fiber extends to point 11, and in this manner the weave is continued until the whole disc is formed.
  • FIG. 3 illustrates diagrammatically one way in which the disc may be made.
  • the fiber 20 is fed from a wheel reel 21 to a point on the circumference of a planet wheel 22 of an epicyclic gear.
  • the planet wheel 22 is attached by means of arms 23 to the driven shaft 24 of an electric motor 25 and on rotation of the shaft 24, the planet wheel 22 is driven round the internal periphery of an annulus gear 26 so that the point on the circumference on the planet wheel 22 to which the fiber is fed performs an epicycloid motion.
  • From the planet wheel 22 the fiber is fed through a tube 27 to a former 28 on which are mounted a plurality of pegs 29 around which the fiber is wound.
  • the former 28 is a flat disc having a central circular projecting boss 30 and a plurality of pegs 29 mounted around the periphery. By winding the fiber around the pegs 29 a continuous tension may be applied to the fiber portions 7 of the disc and the fiber portions will in this case be substantially straight between the pegs 29, and will also be substantially tangential to the central boss 30.
  • the pegs 29 and the former 28 are initially coated with a releasing agent to aid removal of the finished rotor.
  • the fiber portions 7' are curved, so that on rotation of the discs the resultant stress in the fiber portions is more nearly pure tension. This may be achieved by using the epicyclic gear to etch a continuous groove in the desired pattern onto a former and to subsequently feed the fibers under tension into the groove in the former.
  • the fibers are coated with either a thermosetting resin or a metal alloy, depending on the temperature of operation of the disc.
  • the fiber on the reel 21 may have been precoated.
  • the fibers are continuously coated as they are woven.
  • the coating may be applied in the fonn of very viscous liquid and the disc may be heated when complete to cure the resin.
  • the whole weaving process may take place in a vat of electrolyte so that the fiber is individually coated and at the same time continuous electrolytic deposition anchors the fiber portions which have been positioned on the former.
  • the disc may be wound and electrolytically plated when finished.
  • a plurality of circumferentially wound fibers are provided at the outer periphery of the disc to thicken the disc to provide material for withstanding the hoop stresses produced in the disc during rotation thereof and to anchor the fibers.
  • this additional material at the periphery may be'provided purely by electrolytic deposition.
  • the method described above produces an open weave in the disc, and this may in itself be sufficiently strong to withstand the stresses produced in operation. However, it may be necessary to fill in the disc, apart from the central aperture, and this may be done with a lightweight material, for example, a foamed ceramic in the case of high-temperature discs, or resin injection in the case of lower temperature discs.
  • a lightweight material for example, a foamed ceramic in the case of high-temperature discs, or resin injection in the case of lower temperature discs.
  • a plurality of aerofoil-shaped blades are attached to the disc at its outer periphery in order to complete the rotor assembly.
  • the blades may of course be made of conventional materials or may be made of fiber-reinforced resins or metals. In the case of a fiber-reinforced resin disc the blades may be bonded on with a resin bond, and in the case of a disc made from metal-coated fibers with a strengthened periphery the blades may be welded to the periphery.
  • the blades may, if desired, be made integral with the disc in various ways as shown in FIGS. 4 to 6.
  • FIG. 4 one method is illustrated wherein during the continuous winding of the disc, an additional radial movement is superimposed on the weaving motion every time a point on the circumference of the disc is reached thus forming a radial loop 40, the radii of the loops being arranged to suit the diameters of the fibers to avoid stress concentrations.
  • the whole blade disc assembly may then be formed by assembling a plurality of discs and blade segments 41 in axial juxtaposition and interposing a plurality of layers 42 of circumferentially wound fibers at the outer periphery of the disc.
  • the aerofoil shape for the blade may be finally produced by any of a plurality of methods, for example, forming a rough shape of removable expendable material around the fibers of the blade and coating their form with refractory metals or ceramics by spraying or vacuum deposition.
  • an electrically conducting wax former is made on which the fibers are positioned and the whole assembly is electroplated with a metal or metal alloy, and the wax is finally melted out leaving a hollow reinforced metal section in the required shape of the blade.
  • ends of the loops may be cut and the individual fibers bent over to project circumferentially from either side of the blade and thus form a shroud on the blade tip.
  • the radially extending fibers may be cut short at different radial lengths to provide a tapering blade section.
  • FIGS. 5 and 6 An alternative method of making a blade with a shroud is shown in FIGS. 5 and 6.
  • the fiber 50 which forms a woven disc is caused to move radially from the periphery of the disc to lie along one flank 51 of one blade and then to move circumferentially around the disc by one blade pitch and finally to move radially inwards towards the circumference of the disc to lie along one flank 52 of the next adjacent blade before traversing across the disc to the periphery on the opposite side of the disc.
  • a thin lamina section comprising a thin disc, having a plurality of portions of blade profile spaced around its circumference each having a shroud integral with the next adjacent blade profile section may be formed.
  • lamina sections may be built up with interposed layers of circumferential fibers 53 at the disc rim into a com lete blade disc assembly. Finally the whole blade disc assem ly with its shroud may be resln plated or electroplated to form the finished article as seen in FIG. 6.
  • the invention has been described referring to a single fiber element but it is clear that a plurality of fibers may be put together to form a bundle which itself is coated and the same process would apply using the bundle of fibers.
  • the fibers to be used are ideally carboniferous fibers but again other fibers such as silica fibers or boron fibers with suitable coatings may be used.
  • the blades may be made hollow and suitable provision made for feeding cooling air from the disc to the blades.
  • the blades may be made from fiber-reinforced materials and may be made by any of the processes described in our copending U.S. application Ser. No. 685 ,434, filed Nov. 24, 1967, and British application Ser. No. 16874/67.
  • a method of making a turbine or compressor rotor for a gas turbine engine comprising the steps of weaving a continuous fiber or a continuous bundle of fibers onto a former in a plurality of passes between points on the circumference of the former and on opposite sides of the center thereof, the fibers or fiber bundles being passed adjacent the circumference of an aperture at the center of the rotor between each two opposed points, and imposing radial movements on the weaving motion each time the continuous fiber or bundle of fibers reaches the circumference of the former to form'radially extending fiber portions that become reinforcing spines for rotor blades formed integrally with the rotor, forming said radially extending fiber portions with loops at their ends, cutting the loops, extending the cut portions circumferentially to form a shroud for each blade and coating said fiber or fiber bundles with a coating material.
  • the former comprises an electrically conductive wax material on which the rotor is woven, the woven rotor being electroplated and the wax former removed by melting.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Materials Engineering (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Moulding By Coating Moulds (AREA)
US3632460D 1967-06-24 1968-06-07 Epicyclic weaving of fiber discs Expired - Lifetime US3632460A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB2924467A GB1237532A (en) 1967-06-24 1967-06-24 Improvements in turbines and compresser rotors

Publications (1)

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US3632460A true US3632460A (en) 1972-01-04

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JP (1) JPS4639164B1 (forum.php)
BE (1) BE716715A (forum.php)
CH (1) CH501823A (forum.php)
FR (1) FR1579649A (forum.php)
GB (1) GB1237532A (forum.php)
SE (1) SE331940B (forum.php)

Cited By (47)

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US3787141A (en) * 1972-11-30 1974-01-22 United Aircraft Corp Filament reinforced motor assembly
US3799701A (en) * 1972-02-28 1974-03-26 United Aircraft Corp Composite fan blade and method of construction
US3827118A (en) * 1970-11-27 1974-08-06 Garrett Corp Airfoil and method of forming the same
US3903578A (en) * 1972-02-28 1975-09-09 United Aircraft Corp Composite fan blade and method of construction
US4046489A (en) * 1975-10-08 1977-09-06 Eagle Motive Industries, Inc. Aerodynamic fan blade
US4098559A (en) * 1976-07-26 1978-07-04 United Technologies Corporation Paired blade assembly
US4114962A (en) * 1975-10-14 1978-09-19 Messerschmitt-Bolkow-Blohm Gesellschaft Mit Beschrankter Haftung Connecting element for introducing forces into a structural part
US4132069A (en) * 1974-11-08 1979-01-02 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Integrated gas turbine engine-nacelle
US4191510A (en) * 1977-04-28 1980-03-04 Societe Nationale D'etude Et De Construction De Moteurs D'aviation (S.N.E.C.M.A.) Axial flow compressor rotor drum
DE3040129A1 (de) * 1980-02-27 1981-09-03 General Electric Co., Schenectady, N.Y. Als einheit aufgebaute schaufen/naben-baugruppe
US4340627A (en) * 1979-08-31 1982-07-20 Heraeus Quarzschmelze Gmbh Wound and sintered vitreous silica article and method of making
US4354804A (en) * 1979-11-30 1982-10-19 Williams Research Corporation Composite turbine wheel, method of manufacture and fixture therefor
US4395449A (en) * 1982-06-21 1983-07-26 E. I. Du Pont De Nemours And Company Preforms for reinforcement of battery grids
US4460531A (en) * 1982-05-10 1984-07-17 The Boeing Company Composite fiber reinforced propeller
US4483214A (en) * 1982-03-23 1984-11-20 The British Petroleum Company P.L.C. Method for the production of fibre reinforced articles
US4487792A (en) * 1982-06-21 1984-12-11 E. I. Du Pont De Nemours And Company Preforms for reinforcement of battery grids
US4584226A (en) * 1984-04-30 1986-04-22 Mcdonnell Douglas Corporation Load transfer structure and method of making the same
US4589176A (en) * 1983-11-25 1986-05-20 Rockwell International Corporation Fiber-composite turbine blade and method for its construction
US4747900A (en) * 1984-07-07 1988-05-31 Rolls-Royce Plc Method of manufacture of compressor rotor assembly
US4786347A (en) * 1984-07-07 1988-11-22 Rolls-Royce Plc Method of manufacturing an annular bladed member having an integral shroud
US4826645A (en) * 1984-07-07 1989-05-02 Rolls-Royce Limited Method of making an integral bladed member
US5448883A (en) * 1993-02-26 1995-09-12 The Boeing Company Ion thruster with ion optics having carbon-carbon composite elements
US5548953A (en) * 1993-02-26 1996-08-27 The Boeing Company Carbon-carbon grid elements for ion thruster ion optics
US5628622A (en) * 1994-09-14 1997-05-13 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Composite material turbine engine blade equipped with a seal and its production process
WO1998008370A3 (en) * 1996-08-26 1998-07-02 Foster Miller Inc Composite turbine rotor
EP0846845A3 (en) * 1996-12-04 2000-05-10 United Technologies Corporation Turbine engine rotor blade pair
US6232688B1 (en) 1999-04-28 2001-05-15 Allison Advanced Development Company High speed magnetic thrust disk
US6247638B1 (en) 1999-04-28 2001-06-19 Allison Advanced Development Company Selectively reinforced member and method of manufacture
US6261699B1 (en) 1999-04-28 2001-07-17 Allison Advanced Development Company Fiber reinforced iron-cobalt composite material system
US6660355B2 (en) 1999-11-25 2003-12-09 Dunlop Aerospace Limited Wear resistant articles
WO2007013892A3 (en) * 2004-11-12 2007-09-27 Univ Michigan State Composite turbomachine impeller and method of manufacture
WO2010004216A1 (fr) * 2008-07-10 2010-01-14 Snecma Aube redresseur de soufflante en composite 3d
WO2010146288A1 (fr) * 2009-06-18 2010-12-23 Snecma Element de distributeur de turbine en cmc, procede de fabrication, et distributeur et turbine a gaz l'incorporant
FR2953885A1 (fr) * 2009-12-14 2011-06-17 Snecma Aube de turbomachine en materiau composite et procede pour sa fabrication
US20110173812A1 (en) * 2010-01-21 2011-07-21 Runtech Systems Oy Method for manufacturing the impeller of a centrifugal compressor
US20110299976A1 (en) * 2010-06-07 2011-12-08 Richard Christopher Uskert Composite gas turbine engine component
WO2012175867A1 (fr) * 2011-06-21 2012-12-27 Snecma Piece de turbomachine formant redresseur de compresseur ou distributeur de turbine et procede pour sa fabrication
US20130052004A1 (en) * 2011-08-25 2013-02-28 Nicholas D. Stilin Structural composite fan exit guide vane for a turbomachine
US20140064964A1 (en) * 2012-08-29 2014-03-06 Rolls-Royce Plc Metallic foam material
CN102232019B (zh) * 2008-11-28 2014-10-15 赫拉克勒斯公司 用于制造复杂形状的复合材料部件的方法
US20150040396A1 (en) * 2011-12-01 2015-02-12 Herakles Method of fabricating a composite material turbine engine vane with incorporated platforms
US20150267329A1 (en) * 2014-03-21 2015-09-24 Goodrich Corporation Systems and methods for calculated tow fiber angle
US9506355B2 (en) 2009-12-14 2016-11-29 Snecma Turbine engine blade or vane made of composite material, turbine nozzle or compressor stator incorporating such vanes and method of fabricating same
US9677405B2 (en) 2013-03-05 2017-06-13 Rolls-Royce Corporation Composite gas turbine engine blade having multiple airfoils
US9845688B2 (en) 2013-03-15 2017-12-19 Rolls-Royce Corporation Composite blade with an integral blade tip shroud and method of forming the same
US10193430B2 (en) 2013-03-15 2019-01-29 Board Of Trustees Of Michigan State University Electromagnetic device having discrete wires
EP4428340A1 (en) * 2023-03-10 2024-09-11 Rolls-Royce plc Method for manufacturing a composite bladed disk or rotor

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US4464097A (en) * 1982-04-01 1984-08-07 General Electric Company Turbomachinery rotor and method of manufacture
US4666753A (en) * 1985-05-16 1987-05-19 United Technologies Corporation Filament wound structure for use as a torque drive
JPH05505148A (ja) * 1989-12-20 1993-08-05 エムティーユー・モトレン―ウント・タービネン―ユニオン・ミュンヘン・ジーエムビーエッチ 引張荷重が負荷される繊維技術的部材
US5413851A (en) * 1990-03-02 1995-05-09 Minnesota Mining And Manufacturing Company Coated fibers
GB2427658B (en) * 2005-06-30 2007-08-22 Rolls Royce Plc Organic matrix composite integrally bladed rotor
EP2522808A1 (en) * 2011-05-10 2012-11-14 Aella SA Turbo-engine, particularly internal combustion engine

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BE716715A (forum.php) 1968-12-02
FR1579649A (forum.php) 1969-08-29
JPS4639164B1 (forum.php) 1971-11-18
GB1237532A (en) 1971-06-30
CH501823A (fr) 1971-01-15
SE331940B (forum.php) 1971-01-18

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