US3849080A - Rotationally symmetrical hollow compound body - Google Patents

Rotationally symmetrical hollow compound body Download PDF

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Publication number
US3849080A
US3849080A US00245575A US24557572A US3849080A US 3849080 A US3849080 A US 3849080A US 00245575 A US00245575 A US 00245575A US 24557572 A US24557572 A US 24557572A US 3849080 A US3849080 A US 3849080A
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United States
Prior art keywords
compound body
outer layer
layers
drum
fiber
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Expired - Lifetime
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US00245575A
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English (en)
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H Zechmeister
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MAN AG
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Individual
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    • 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
    • B29C41/00—Shaping by coating a mould, core or other substrate, i.e. by depositing material and stripping-off the shaped article; Apparatus therefor
    • B29C41/02—Shaping by coating a mould, core or other substrate, i.e. by depositing material and stripping-off the shaped article; Apparatus therefor for making articles of definite length, i.e. discrete articles
    • B29C41/04—Rotational or centrifugal casting, i.e. coating the inside of a mould by rotating the mould
    • B29C41/042—Rotational or centrifugal casting, i.e. coating the inside of a mould by rotating the mould by rotating a mould around its axis of symmetry
    • B29C41/045—Rotational or centrifugal casting, i.e. coating the inside of a mould by rotating the mould by rotating a mould around its axis of symmetry the axis being placed vertically, e.g. spin casting
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D13/00—Centrifugal casting; Casting by using centrifugal force
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D19/00—Casting in, on, or around objects which form part of the product
    • B22D19/02—Casting in, on, or around objects which form part of the product for making reinforced articles
    • 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
    • B29C70/28—Shaping operations therefor
    • B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
    • B29C70/32—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core on a rotating mould, former or core
    • B29C70/323—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core on a rotating mould, former or core on the inner surface of a rotating mould
    • B29C70/326—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core on a rotating mould, former or core on the inner surface of a rotating mould by rotating the mould around its axis of symmetry
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12333—Helical or with helical component
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12444—Embodying fibers interengaged or between layers [e.g., paper, etc.]
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12465—All metal or with adjacent metals having magnetic properties, or preformed fiber orientation coordinate with shape
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12486—Laterally noncoextensive components [e.g., embedded, etc.]
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12736—Al-base component
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12771—Transition metal-base component
    • Y10T428/12778—Alternative base metals from diverse categories

Definitions

  • ABSTRACT A rotationally symmetrical compound body make by centrifugal casting in which the metal to be cast is poured with the aid of a rotating or stationary casting device disposed axially in a rotating drum either radially or tangentially onto the endless fibers, stable fibers or fiber matting abutting at the inner wall of the drum, whereby the outer fiber-reinforced layers of the compound body adjoining the wall of the drum are heated and cool off to room temperature only after the cooling off of the inner metallic layers; the thermal coefficient of expansion of the inner metallic layers is equal to or smaller than that of the outer layers.
  • the present invention relates to rotationally symmetrical hollow compound bodies made by centrifugal casting.
  • the present invention seeks to provide a rotationally symmetrical compound body whose metal matrix is reinforced with metallic or non-metallic fibers, which assures a safe bonding between the individual components constituting the compound body also at high circumferential speeds, at high internal pressures and temperatures. Furthermore, the compound body is to possess a low density notwithstanding a high degree of compression. Moreover, the radial deformation or distortion and bulging of the compound body is to be as small as possible in operation in order to permit its use, for example, for such applications as gas centrifuges. It is another paramount consideration for the manufacture of compound bodies that they be free from cavities and impurities or contaminations.
  • the metal to be cast is poured by means ofa rotating or stationary casting device which is axially arranged in a rotating drum, radially or tangentially onto the endless fibers, staple fibers or fiber matting lying essentially in the circumferential direction against the drum wall, whereby the outer fiber-reinforcing layers of the compound body adjacent the drum wall are heated and cool off to room temperature only after the cooling off of the inner metallic layers, whose thermal coefficient of expansion is equal to or lower than that of the outer layers.
  • the present invention is suited, on the one hand, if the matrix material of the fibers and the metallic material forming the inner layers are identical (for example, consist ofan aluminum alloy) and therefore possess the same thermal coefficient of expansion.
  • the thermal coefficient of expansion of the outer metal matrix for example, an aluminum alloy
  • the thermal coefficient of expansion of the inner plain-metal material for example, a nickel alloy
  • the advantage of the present invention resides in that a homogeneous, dense compound body free from cavities is produced in which the bonding between individual components is high.
  • the metal sprayed from the nozzles of the casting device is selectively directed whereby a dense ramiform grain structure is achieved in a predominantly tangential direction, which is again improved in that as a result of the proposed cooling conditions, i.e., to cool off the outer fiber-reinforced layer only after the inner plain-metal layer, a residual stress condition is attained at room temperature which is indicative of tangentially directed tensile stresses on the outside and tangentially directed compressive stresses on the inside.
  • the outer fiber-reinforced layers for example, a nickel alloy
  • the inner layers for example, an aluminum alloy
  • the outer layers for example, carbon fiber-reinforced Ni super alloys upon cooling freeze in the radial direction so that a heating during the rotation would not fulfill the requisite purpose. It is thereby proposed in accordance with the present invention to undertake the rotation for such length of time--without additional heating of the outer zones--until the inner layers (with the higher thermal coefficients of expansion) have solidified and hardened so that at room temperature a residual stress condition in the tangential direction is also produced.
  • a significant characteristic of the present invention resides as to the rest with the use of these materials in that during the cooling off of the compound body, compressive stresses are set up in the axial direction in the outer fiber-reinforced layers and tensile stresses in the inner metallic layers.
  • the outer layers consist, for example, of a nickel alloy reinforced with carbon fibers and the inner layer of a plain (non-reinforced) aluminum alloy, then--as already mentioned above--the thermal coefficient of expansion is smaller on the outside than at the inside; during cooling the inner layers will tend to c0ntract axially against the essentially frozen outer layers.
  • An axial residual stress condition is built-up thereby which imparts to the compound body particularly fa vorable properties when subjected to alternating bending loads, for example, with the use as centrifuging drum or the like since under bending the outer layers now subjected to tension are prevented from tearing thanks to the compressive preload.
  • the present invention is further characterized in that the transition of the outer layer to the inner layer is progressive, i.e., produces a drifting transition therebetween, and in that a clinch of both forceand form locking type is produced.
  • a compound body with this residual or inherent stress condition will not readily yield, i.e., will permit only small radial deformations under rotation or with the application of an internal pressure.
  • a compound body is produced by the present invention which is suited for high temperature used and in which the fibers are incorporated very firmly in the matrix.
  • proper consideration must be given thereby that the requirement for fiber stability in high temperature applications limits the choice among suitable material systems to those that have phase diagrams which preclude or minimize compounding, diffusive reaction with the matrix and internal oxidation.
  • the following systems are suited for the process of manufacture of the rotationally symmetrical body in accordance withthe present invention: carbon fibers or tungsten fibers in Ni -super alloys, or beryllium fibers in aluminum alloys.
  • the possibility exists to optimize the bond and compression of the components to the different intended applications by a corresponding adjustment of the rotational speeds of the drum and of the casting device.
  • Another advantage afforded by this invention resides in that the possibility exists to admix in the course of the casting process different matrix materials so that a compound body consisting of different layers can be produced, for example, of different layers the specific modulus E of which may vary in magnitude from one layer to the next.
  • the compound body as centrifuging drum, it will be desirable to cause the specific modulus E, i.e., the ratio of modulus E to density, to increase from the inside toward the outside of the body.
  • the bonding properties of such a compound body are considerably superior to those of a wound body.
  • Compound bodies in accordance with the present invention are suited, for example, for applications as revolving drums in centrifuges, as containers, as bearings and rolls or as combustion chambers or thrust nozzles in rockets. In the manufacture of rocket nozzles, it may be advisable to admix condensation coolants such as graphite.
  • the apparatus utilized in to the present invention essentially consists in that a rotating or stationary casting device extends into a drum whose bottom carries, for example, a drive pin or trunion, whereby radial or tangential nozzles are provided in the longitudinal direction of the casting device.
  • the single FIGURE is a schematic cross-sectional view of an apparatus in accordance with the formation of the rotationally symmetric body of the present invention, by means of which the process for producing the present invention can be realized.
  • reference numeral 2 designates a cylindrical drum totating about a vertical axis and closed off by means of a bottom 1.
  • a casting device 3 extends axially into the cylindrical drum 2.
  • the casting device 3 consists of a cylindrical barrel on which are provided diammetrically oppositely disposed nozzles 4 extending in the longitudinal direction.
  • a tubular member 5 terminates from above in the barrel; a mixing chamber 6 is arranged ahead of the tubular member 5, into which are fed the desired metals or alloy constituents (arrows A and B) for the corresponding alloy formation.
  • a heating device in the form of a heating coil 7 may be arranged extending along the center line of the casting device 3.
  • the nozzles 4 or slots may conveniently be arranged either radially or tangentially in the barrel shroud.
  • Arranged centrally on the bottom 1 of the drum 2 is an axially extending pin or trunion 8 which serves for the drive and support of the drum 2.
  • the schematically indicated bearing is designated by reference numeral 9.
  • a heating device 10 is inserted into the wall ofthe drum 2.
  • the drum 2 is enclosed by a ring 11.
  • the entire apparatus is surrounded by a shroud or jacket 12 (shown in dash lines) so that the casting operation can take place optionally in an evacuated or inert gas environment.
  • the process for the present invention can be explained readily after the description of the apparatus.
  • the fibers 13, for example, beryllium fibers in the form of staple fibers are inserted essentially circumferentially in several rows into a skeleton frame of matrix material hugging the wall of the drum.
  • fiber matting may be optionally inserted in a like manner.
  • the matrix material 14, for example, an aluminum alloy is fed into the mixing chamber 6 in liquid state, is homogenized therein, possibly mixed with a wetting agent so that an alloy enters the rotating casting device at a constant temperature and free from inclusions.
  • the matrix material is centrifuged through the nozzles against the rotating inner drum wall where it immediately envelopes the fibers and forms a dense compound body as a result of the high centrifugal forces which occur at that time.
  • the heating device arranged in the wall of the drum keeps the compound body at an elevated temperature.
  • another metal 15 for example, with a slightly higher specific modulus E but of approximately equal coefficients of expansions such as an aluminum titanium alloy, which compounds with the previously deposited metal matrix under proper conditions, may then be poured. These conditions have to be adjusted depending on the desired application of the compound body.
  • the outer layer should have a specific gravity higher than that of the inner layer.
  • the rotation of the drum is maintained for such length of time until the inner layers are cooled off approximately to room temperature.
  • a solidification of the inner layers may occur as a result of continued rotation under proper conditions. It is only thereafter that according to the present invention the outer layers which are essentially still plastic, are slowly cooled off to room temperature.
  • Typical examples for the casting alloy materials which can be used with the method according to the present invention are those described in the German standards DIN-NORM 1725, sheet 2, for example, for the Al-alloys material Nos. 3.2151 and 3.2l53, which are alloys of the type G-AlSi Cu containing in percent by weight 5.0 to 7.5 of Si, 3.0 to 5.0 of Cu, 0.3 to 0.6 of Mn, 01 to 0.3 of Mg and the rest essentially Al (except for the indicated permissive quantities of admixtures see in particular material No. 32153.01)
  • German standards which are alloys of the type GD-AlSi containing in percent by weight 11.0 to 13.5 of Si, to 0.4 of Mn and the rest essentially Al (except for indicated permissive admixtures--see in particular material No. 3.258205) and of the type GD-AlMg containing in percent by weight 7.0 to 10.0 of Mg, 0 to 2.5 of Si, 0.2 to 0.5 of Mn and the rest essentially Al (except for indicated permissive admixtures-see in particular material No. 3.329205).
  • Typical examples of titanium containing Al-alloys are those casting alloys described in the same German standards, for example, material Nos.
  • 3.1841 and 3.1371 which are alloys of the type G AlCu Ti, containing in percent by weight 4.5 to 5.2 of Cu, 0.15 to 0.30 of Ti and the rest essentially Al (except indicated permissive admixtures--see in particular material No. 31841.63) and of the type G-AlCuJiMg, containing in percent by weight 4.2 to 4.9 of Cu, 0.15 to 0.30 of Mg, 0.15 to 0.30 of Ti and the rest essentially Al (except for indicated permissive admixtures--see in particular material No. 3.l37l.6l
  • the cylindrical drum consists of a high heat-resistant steel, for example, of material No. 1.4922 (X20CrMoVl2-l) or of material No. 1.4981 (X8CrNiMoNb 16--16) as described in the aforementioned German standards, has a diameter of 1 in. max. and is rotated with a circumferential velocity of about v 50-200 mlsec.
  • the casting temperature of the Alalloys is about 650 C 700 C.
  • the duration of rotation 1, is dependent on the desired degree of compression of the compound body and on the cooling-off time of the compound body with an unheated and with a heated drum. However, on the average I is about l-30 min.
  • a compound body can be made by a corresponding selection of the casting material and matching of the feed of the casting device and rotational speed of the drum as well as the cooling conditions, which exhibit the optimum properties desired for the particular application.
  • the use of a further bearing of the drum is necessary with the use of a longer drum for the manufacture of longer compound bodies.
  • Rotationally symmetrical hollow compound body consisting of two layers, arranged one within the other, each part merging into the other without gaps, and characterized by the combination of the following features:
  • the inner layer essentially consists of metal selected from the group consisting of alloys on a nickel, titanium, cobalt or aluminum basis;
  • the outer layer essentially consists of a fibrous material selected from the group essentially consisting of tungsten, beryllium, steel, boron, carbon or silicon carbide fiber, which are: arranged as coiled endless fiber, staple fiber or fiber matting, whereby the spaces between the individual fibers are cast with one of the metals mentioned under (a), thereby providing a low density structure;
  • said materials of the outer and inner layers being selected such that the heat expansion coefficient of the metal inner layer is equal to or larger than that of the outer layer, and said material of said outer layer exhibits a specific modulus less than the specific modulus of said material of the inner layer;
  • the outer layer shows evidence mainly of tensile stress
  • the inner layer mainly of pressure stress so that the compound body exhibits small radial deformations under rotation or with the application of an internal pressure.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Manufacture Of Alloys Or Alloy Compounds (AREA)
  • Separation By Low-Temperature Treatments (AREA)
US00245575A 1971-04-19 1972-04-19 Rotationally symmetrical hollow compound body Expired - Lifetime US3849080A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE2118848A DE2118848C3 (de) 1971-04-19 1971-04-19 Rotationssymmetrischer, hohler Verbundkörper und Verfahren zu seiner Herstellung

Publications (1)

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US3849080A true US3849080A (en) 1974-11-19

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US00245575A Expired - Lifetime US3849080A (en) 1971-04-19 1972-04-19 Rotationally symmetrical hollow compound body

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US (1) US3849080A (fr)
JP (1) JPS5516750B1 (fr)
AT (1) AT323915B (fr)
BE (1) BE782239A (fr)
CH (1) CH566831A5 (fr)
DE (1) DE2118848C3 (fr)
DK (1) DK141355C (fr)
FI (1) FI52939C (fr)
FR (1) FR2133852B1 (fr)
GB (1) GB1393989A (fr)
NL (1) NL162003C (fr)
NO (1) NO130892C (fr)
SE (1) SE387874B (fr)

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4816347A (en) * 1987-05-29 1989-03-28 Avco Lycoming/Subsidiary Of Textron, Inc. Hybrid titanium alloy matrix composites
US4834693A (en) * 1980-06-26 1989-05-30 Avco Corporation Hybrid drive shaft
US5404639A (en) * 1980-07-02 1995-04-11 Dana Corporation Composite insulation for engine components
US5695883A (en) * 1991-09-17 1997-12-09 Tocalo Co., Ltd. Carbon member having a metal spray coating
WO2002058917A2 (fr) * 2001-01-23 2002-08-01 The Johns Hopkins University Utilisation d'un liquide pendant la centrifugation pour améliorer la consolidation d'une structure composite
EP1297400A1 (fr) * 2000-06-27 2003-04-02 The Board Of Trustees Of The Leland Stanford Junior University Rotors composites pour volants et procedes de fabrication associes
GB2509245A (en) * 2012-12-21 2014-06-25 Jaguar Land Rover Ltd Cast component with increased stiffness
CN109203508A (zh) * 2018-08-29 2019-01-15 江苏赛图新材料科技有限公司 一种纤维管卧式离心成型装置及其成型工艺
US20200305231A1 (en) * 2019-05-14 2020-09-24 Bahareh Sadeghi WLAN SENSING USING HIGH-EFFICIENCY (HE) TRIGGER-BASED (TB) PPDUs (HE TB PPDUs)
CN112246586A (zh) * 2020-09-28 2021-01-22 镇江经纬输送装备有限公司 一种在溜管内壁均匀浇注聚氨酯的工艺
CN113400542A (zh) * 2021-07-20 2021-09-17 南通天木绝缘复合材料有限公司 一种方便原料快速混合的玻璃钢格栅生产用离心浇注装置

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DE2523074A1 (de) * 1975-05-24 1976-12-02 Christensen Diamond Prod Co Verfahren und einrichtung zur herstellung verschleissfester koerper, insbesondere fuer die tiefbohrtechnik
JPS5292827A (en) * 1976-01-16 1977-08-04 Honda Motor Co Ltd Method of manufacturing structures with fiber reinforced composite parts
DE2929217A1 (de) * 1979-07-19 1983-12-01 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Rotationssymmetrischer hohler verbundkoerper
JPS5630070A (en) * 1979-08-17 1981-03-26 Honda Motor Co Ltd Manufacture of fiber-reinforced composite material
US4258756A (en) * 1979-08-27 1981-03-31 Allied Chemical Corporation Composite shell
JPS5893813U (ja) * 1981-12-18 1983-06-25 トキコ株式会社 タ−ビンメ−タ
DE3478035D1 (en) * 1984-01-27 1989-06-08 Chugai Ro Kogyo Kaisha Ltd Fiber reinforced metal alloy and method for the manufacture thereof
GB8518909D0 (en) * 1985-07-26 1985-09-04 Ae Plc Engineering components
GB2222793A (en) * 1988-09-16 1990-03-21 British Aerospace "Method of forming a fibre reinforced material"
GB9413631D0 (en) * 1994-07-06 1994-09-14 Inco Engineered Prod Ltd Manufacture of forged components
JP3650183B2 (ja) * 1995-10-13 2005-05-18 栃木富士産業株式会社 スクリューロータの加工方法
DE19737601A1 (de) * 1997-08-28 1999-03-04 Bayerische Motoren Werke Ag Verfahren zur Steigerung der Dämpfung eines Gußbauteiles aus einem Leichtmetallwerkstoff

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US1280909A (en) * 1916-02-05 1918-10-08 Metalco Company Manufacture of pipes.
US2197916A (en) * 1937-01-27 1940-04-23 Detroit Gasket & Mfg Company Gasket
US3419952A (en) * 1966-09-12 1969-01-07 Gen Electric Method for making composite material
US3427185A (en) * 1964-02-19 1969-02-11 United Aircraft Corp Composite structural material incorporating metallic filaments in a matrix,and method of manufacture
US3575783A (en) * 1968-11-13 1971-04-20 United Aircraft Corp Unidirectional fiber reinforced metal matrix tape
US3608170A (en) * 1969-04-14 1971-09-28 Abex Corp Metal impregnated composite casting method
US3682606A (en) * 1968-08-22 1972-08-08 Pechiney Ugine Kuhlmann Aluminum-steel composite

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1280909A (en) * 1916-02-05 1918-10-08 Metalco Company Manufacture of pipes.
US2197916A (en) * 1937-01-27 1940-04-23 Detroit Gasket & Mfg Company Gasket
US3427185A (en) * 1964-02-19 1969-02-11 United Aircraft Corp Composite structural material incorporating metallic filaments in a matrix,and method of manufacture
US3419952A (en) * 1966-09-12 1969-01-07 Gen Electric Method for making composite material
US3682606A (en) * 1968-08-22 1972-08-08 Pechiney Ugine Kuhlmann Aluminum-steel composite
US3575783A (en) * 1968-11-13 1971-04-20 United Aircraft Corp Unidirectional fiber reinforced metal matrix tape
US3608170A (en) * 1969-04-14 1971-09-28 Abex Corp Metal impregnated composite casting method

Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4834693A (en) * 1980-06-26 1989-05-30 Avco Corporation Hybrid drive shaft
US5404639A (en) * 1980-07-02 1995-04-11 Dana Corporation Composite insulation for engine components
US4816347A (en) * 1987-05-29 1989-03-28 Avco Lycoming/Subsidiary Of Textron, Inc. Hybrid titanium alloy matrix composites
US5695883A (en) * 1991-09-17 1997-12-09 Tocalo Co., Ltd. Carbon member having a metal spray coating
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JPS5516750B1 (fr) 1980-05-06
FI52939B (fr) 1977-09-30
DE2118848B2 (de) 1973-06-20
CH566831A5 (fr) 1975-09-30
GB1393989A (en) 1975-05-14
AT323915B (de) 1975-08-11
SE387874B (sv) 1976-09-20
BE782239A (fr) 1972-08-16
NL162003C (nl) 1980-04-15
FR2133852B1 (fr) 1976-10-29
FI52939C (fr) 1978-01-10
DE2118848C3 (de) 1974-01-17
NL162003B (nl) 1979-11-15
DK141355C (da) 1980-08-18
NL7205164A (fr) 1972-10-23
NO130892C (fr) 1975-03-05
DK141355B (da) 1980-03-03
NO130892B (fr) 1974-11-25
DE2118848A1 (de) 1972-11-02
FR2133852A1 (fr) 1972-12-01

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