WO1991001284A1 - Carbon-carbon composite - Google Patents

Carbon-carbon composite Download PDF

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Publication number
WO1991001284A1
WO1991001284A1 PCT/GB1990/001153 GB9001153W WO9101284A1 WO 1991001284 A1 WO1991001284 A1 WO 1991001284A1 GB 9001153 W GB9001153 W GB 9001153W WO 9101284 A1 WO9101284 A1 WO 9101284A1
Authority
WO
WIPO (PCT)
Prior art keywords
carbon
elements
composite according
preform
interwoven
Prior art date
Application number
PCT/GB1990/001153
Other languages
French (fr)
Inventor
Maurice James Evans
Ronald Fisher
Original Assignee
Dunlop Limited
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 Dunlop Limited filed Critical Dunlop Limited
Priority to EP90911643A priority Critical patent/EP0484410B1/en
Priority to DE69010911T priority patent/DE69010911T2/en
Publication of WO1991001284A1 publication Critical patent/WO1991001284A1/en

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Classifications

    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
    • C04B35/71—Ceramic products containing macroscopic reinforcing agents
    • C04B35/78—Ceramic products containing macroscopic reinforcing agents containing non-metallic materials
    • C04B35/80—Fibres, filaments, whiskers, platelets, or the like
    • C04B35/83—Carbon fibres in a carbon matrix
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
    • F16D69/00—Friction linings; Attachment thereof; Selection of coacting friction substances or surfaces
    • F16D69/02—Composition of linings ; Methods of manufacturing
    • F16D69/023—Composite materials containing carbon and carbon fibres or fibres made of carbonizable material
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
    • F16D65/00—Parts or details
    • F16D65/02—Braking members; Mounting thereof
    • F16D65/12—Discs; Drums for disc brakes
    • F16D65/125—Discs; Drums for disc brakes characterised by the material used for the disc body
    • F16D65/126—Discs; Drums for disc brakes characterised by the material used for the disc body the material being of low mechanical strength, e.g. carbon, beryllium; Torque transmitting members therefor

Definitions

  • This invention relates to a carbon fibre composite and a method for the manufacture of a carbon fibre composite such as may be used for the manufacture of articles such as carbon brake discs.
  • one object of the present invention is to provide a preform and method of making a free-standing carbon fibre preform which does not require the use of a jig to maintain compression of the preform whilst in a furnace.
  • a carbon-carbon composite has a reinforcement of carbon fibres derived from a preform of carbon fibre or carbon fibre precursor material and wherein said preform is a compound fabric in which interwoven elements of carbon fibre or carbon fibre precursor material extend through substantially the whole thickness of the preform.
  • Preferably said preform is a compound fabric comprising at least 10 and more preferably at least 20 plies of carbon fibre or carbon fibre precursor material.
  • Each ply may be of a woven construction but the provision of one or more plies of another type of construction, such as a knitted construction, is not excluded.
  • the elements of the body, and including the interwoven elements are in the form of yarns.
  • the yarns may be single, folded or cabled yarns. They may be twisted or may be bereft of twist apart from any necessary producer twist for maintaining the filaments of a yarn together during a weaving or other processing operation.
  • Yarns may be singles yarns or may be folded.
  • the yarns preferably have a twist in the range 80 to 300 turns per metre (t.p.m. ).
  • All yarns or like elements of the preform e g the warp and weft elements of each constituent ply of woven fabric in the body and the interwoven elements which hold the fabric plies together preferably have a tex of greater than 750 and more preferably greater than 1,000.
  • the warp elements preferably have a tex of greater than three times that of the weft elements.
  • At least some, and preferably all, of the interwoven elements are arranged to extend through the entire thickness of the "stack" of plies of the compound fabric.
  • Positioning of the interwoven elements may be achieved during a solid weaving operation concurrent with formation of constituent woven plies or it may be achieved by taking a stack of pre-woven plies which are then secured together by the provision of interwoven elements.
  • the interwoven elements extending in a direction through the thickness of a stack of woven fabric plies typically may be provided in pairs arranged to extend side-by-side between a neighbouring pair of warp elements of a ply of the stack. Successive pairs of interwoven elements may be spaced transversely across the preform by at least one and more typically at least two elements, typically warp yarns, of a woven ply.
  • the elements of said pairs of interwoven elements may be arranged to extend to and fro through the thickness of the stack of plies in an offset, out-of-phase relationship whereby the two elements are in side-by- side contact only at a position between the surface plies of the stack.
  • the elements for the warp of each notional ply of woven fabric and those for interweaving said plies typically may be yarns of a multi-strand construction.
  • a yarn element used for the weft of the woven fabric plies typically may be of a single strand construction.
  • said carbon precursor material typically may be of oxidised polyacrylonitrile (PAN).
  • PAN oxidised polyacrylonitrile
  • Other suitable carbon precursor materials include pitch and rayon.
  • the invention further provides a carbon-carbon composite article such as a brake disc comprising a carbon-carbon composite of the invention and in which said reinforcement comprises interwoven elements of carbon fibre extending through substantially the whole thickness of the article, or axial thickness of the disc in the case of a composite brake disc.
  • a carbon-carbon composite article such as a brake disc comprising a carbon-carbon composite of the invention and in which said reinforcement comprises interwoven elements of carbon fibre extending through substantially the whole thickness of the article, or axial thickness of the disc in the case of a composite brake disc.
  • the preform for the composite may have a thickness of at least 25 mm prior to carbonisation.
  • the carbonised preform may be densified by the Carbon Vapour Deposition technique or the resin/pitch technique followed by charring.
  • the invention further provides a carbon-carbon composite in which said reinforcement is derived from a preform assembly comprising a plurality of said preforms arranged in a superimposed and interconnected relationship.
  • the preforms may be interconnected for example by bonding or otherwise secured together such as by mechanical fastening means.
  • present invention provides a method for forming a carbon-carbon composite comprising providing a preform comprising a compound fabric formed from elements of carbon fibre or carbon fibre precursor material which extend through substantially the whole thickness of the preform and then treating said preform to provide a carbonised and densified preform.
  • Figure 1 is a cross-section through the thickness of a carbon fibre preform of the reinforcement of a carbon-carbon composite in accordance with the subject invention, the cross-section being taken in a transverse direction perpendicular to the direction in which warp yarns extend in the preform
  • Figure 2 is a cross-section through the thickness of the preform in a plane perpendicular to that of Figure 1.
  • a carbon-carbon composite has a reinforcement derived from the compound, solid-woven preform shown in Figures 1 and 2.
  • this preform has only six interwoven plies though typically a preform suitable for the formation of a carbon brake disc would have at least ten and more typically at least twenty interwoven plies of woven material.
  • the yarns are not shown to scale; as described below they are all of a bulky type and in practice occupy a greater proportion of the cross-sectional area than apparent from these Figures.
  • the preform 10 comprises six interwoven fabric plies each having warp elements 11 interwoven with weft elements 12.
  • the six interwoven plies are interwoven by the individual interlock elements 13a,13b.
  • the interlock elements 13a,13b are provided in side-by-side pairs relationship between neighbouring warp elements (see the two interlock elements 13a, 13b provided between the neighbouring warp elements 14,15 of Figure 1), and successive pairs of interlock elements are spaced by two warp elements- (see elements 15,16) which lie between successive pairs of the interlock elements 13a,13b.
  • the interlock elements 13a,13b each extend through the entire thickness of the preform and are uniformly offset in the warp direction. That is, as seen in Figure 2, one of the interlock elements, 13a, extends over the weft element 12a of a woven ply at an upper surface of the preform and the other, second interlock element 13b extends over the next weft element 12b. In consequence the two interlock elements of each pair 13a,13b are in side-by-side contact at a position 17 lying mid-way between the upper and lower surfaces of the preform.
  • the six plies are woven concurrent with interweaving of the interlock elements to result in one piece of. compound fabric.
  • the warp elements 11 are each yarns of a multi- stranded construction wherein each strand comprises a plurality of yarns.
  • Each warp yarn is composed of four strands laid together with little or no folding twist and the yarn assembly of the strands has a tex of 5352.
  • each strand has a tex of 1338.
  • Each strand in turn is composed of 15 individual yarns, the individual yarns having a tex of 89.2.
  • the filaments of each individual yarn have a twist of 270 t.p.m. and the individual yarns of each strand have a twist of 80 t.p.m..
  • the weft elements 12 are comprised by yarns of a single strand construction, corresponding to one of the four strands of the warp yarn, and has the same tex, i e 1338. Similarly, the strand is made up of 15 individual yarns each of tex 89.2. The twist levels in the strand and individual yarns also corresponds.
  • the interlocking elements 13a,13b are of like construction and are in the form of yarns which have a tex of 1822.
  • Each interlocking yarn comprises three strands each of 607 tex and each such strand is formed from seven individual- yarns each of 86.7 tex.
  • the filaments of each individual yarn have a twist of 270 t.p.m., the individual yarns have a twist of 80 t.p.m. in each strand and each strand has a negligible twist in the interlocking yarn.
  • a compound fabric constructed as described above from oxidised pan yarns had an initial thickness of 21 mm (for six plies) and a fibre volume of 47%. This fabric was then carbonised at a temperature of 1020°C for four hours under a load of 0.5 lb/sq in (0.0034 MPa) . After carbonising the fabric had a thickness of 17.25 mm and a fibre volume of 27%. The resulting carbonised preform was then subject to densification either by CVD or resin/pitch impregnation followed by charring to produce a carbon-carbon composite, and without any need for provision of conventional jig means.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Composite Materials (AREA)
  • Materials Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Manufacturing & Machinery (AREA)
  • Mechanical Engineering (AREA)
  • Structural Engineering (AREA)
  • Organic Chemistry (AREA)
  • Woven Fabrics (AREA)
  • Ceramic Products (AREA)
  • Braking Arrangements (AREA)

Abstract

A carbon-carbon composite incorporates a reinforcement of carbon fibres derived from a preform which is in the form of a compound fabric in which interwoven elements of carbon fibre or carbon fibre precursor material extend through substantially the whole thickness of the preform.

Description

CARBON-CARBON COMPOSITE
This invention relates to a carbon fibre composite and a method for the manufacture of a carbon fibre composite such as may be used for the manufacture of articles such as carbon brake discs.
In the manufacture of carbon brake discs by the Chemical Vapour Deposition (CVD) method it is customary to compress a stack of layers of carbon fibre fabric in a suitable jig before loading the stack, in the jig, into the CVD furnace. The jig requires time to assemble and takes up valuable space in the furnace, and one object of the present invention is to provide a preform and method of making a free-standing carbon fibre preform which does not require the use of a jig to maintain compression of the preform whilst in a furnace.
According to one aspect of the present invention a carbon-carbon composite has a reinforcement of carbon fibres derived from a preform of carbon fibre or carbon fibre precursor material and wherein said preform is a compound fabric in which interwoven elements of carbon fibre or carbon fibre precursor material extend through substantially the whole thickness of the preform.
Preferably said preform is a compound fabric comprising at least 10 and more preferably at least 20 plies of carbon fibre or carbon fibre precursor material. Each ply may be of a woven construction but the provision of one or more plies of another type of construction, such as a knitted construction, is not excluded.
Typically the elements of the body, and including the interwoven elements, are in the form of yarns. The yarns may be single, folded or cabled yarns. They may be twisted or may be bereft of twist apart from any necessary producer twist for maintaining the filaments of a yarn together during a weaving or other processing operation.
Yarns may be singles yarns or may be folded. The yarns preferably have a twist in the range 80 to 300 turns per metre (t.p.m. ).
All yarns or like elements of the preform, e g the warp and weft elements of each constituent ply of woven fabric in the body and the interwoven elements which hold the fabric plies together preferably have a tex of greater than 750 and more preferably greater than 1,000.
In each or at least some of the woven fabric plies the warp elements preferably have a tex of greater than three times that of the weft elements.
At least some, and preferably all, of the interwoven elements are arranged to extend through the entire thickness of the "stack" of plies of the compound fabric.
Positioning of the interwoven elements may be achieved during a solid weaving operation concurrent with formation of constituent woven plies or it may be achieved by taking a stack of pre-woven plies which are then secured together by the provision of interwoven elements.
The interwoven elements extending in a direction through the thickness of a stack of woven fabric plies typically may be provided in pairs arranged to extend side-by-side between a neighbouring pair of warp elements of a ply of the stack. Successive pairs of interwoven elements may be spaced transversely across the preform by at least one and more typically at least two elements, typically warp yarns, of a woven ply. The elements of said pairs of interwoven elements may be arranged to extend to and fro through the thickness of the stack of plies in an offset, out-of-phase relationship whereby the two elements are in side-by- side contact only at a position between the surface plies of the stack. Preferably there is a balanced construction in which the side-by-side contact occurs at a position mid-way through the thickness of the stack and such that at. a surface ply the elements appear in a uniform alternating disposition.
The elements for the warp of each notional ply of woven fabric and those for interweaving said plies typically may be yarns of a multi-strand construction. In contrast a yarn element used for the weft of the woven fabric plies typically may be of a single strand construction.
When the woven fabric is formed from yarns of carbon precursor material, said carbon precursor material typically may be of oxidised polyacrylonitrile (PAN). Other suitable carbon precursor materials include pitch and rayon.
The invention further provides a carbon-carbon composite article such as a brake disc comprising a carbon-carbon composite of the invention and in which said reinforcement comprises interwoven elements of carbon fibre extending through substantially the whole thickness of the article, or axial thickness of the disc in the case of a composite brake disc.
The preform for the composite may have a thickness of at least 25 mm prior to carbonisation. The carbonised preform may be densified by the Carbon Vapour Deposition technique or the resin/pitch technique followed by charring.
The invention further provides a carbon-carbon composite in which said reinforcement is derived from a preform assembly comprising a plurality of said preforms arranged in a superimposed and interconnected relationship. The preforms may be interconnected for example by bonding or otherwise secured together such as by mechanical fastening means.
In yet another of its aspects th" present invention provides a method for forming a carbon-carbon composite comprising providing a preform comprising a compound fabric formed from elements of carbon fibre or carbon fibre precursor material which extend through substantially the whole thickness of the preform and then treating said preform to provide a carbonised and densified preform.
One embodiment of the present invention will now be described, by way of example only, with reference to the accompanying diagrammatic drawings in which:- Figure 1 is a cross-section through the thickness of a carbon fibre preform of the reinforcement of a carbon-carbon composite in accordance with the subject invention, the cross-section being taken in a transverse direction perpendicular to the direction in which warp yarns extend in the preform, and Figure 2 is a cross-section through the thickness of the preform in a plane perpendicular to that of Figure 1. A carbon-carbon composite has a reinforcement derived from the compound, solid-woven preform shown in Figures 1 and 2. For convenience of illustration this preform has only six interwoven plies though typically a preform suitable for the formation of a carbon brake disc would have at least ten and more typically at least twenty interwoven plies of woven material. In Figures 1 and 2 the yarns are not shown to scale; as described below they are all of a bulky type and in practice occupy a greater proportion of the cross-sectional area than apparent from these Figures.
The preform 10 comprises six interwoven fabric plies each having warp elements 11 interwoven with weft elements 12.
The six interwoven plies are interwoven by the individual interlock elements 13a,13b. The interlock elements 13a,13b are provided in side-by-side pairs relationship between neighbouring warp elements (see the two interlock elements 13a, 13b provided between the neighbouring warp elements 14,15 of Figure 1), and successive pairs of interlock elements are spaced by two warp elements- (see elements 15,16) which lie between successive pairs of the interlock elements 13a,13b.
The interlock elements 13a,13b each extend through the entire thickness of the preform and are uniformly offset in the warp direction. That is, as seen in Figure 2, one of the interlock elements, 13a, extends over the weft element 12a of a woven ply at an upper surface of the preform and the other, second interlock element 13b extends over the next weft element 12b. In consequence the two interlock elements of each pair 13a,13b are in side-by-side contact at a position 17 lying mid-way between the upper and lower surfaces of the preform.
The six plies are woven concurrent with interweaving of the interlock elements to result in one piece of. compound fabric.
The warp elements 11 are each yarns of a multi- stranded construction wherein each strand comprises a plurality of yarns. Each warp yarn is composed of four strands laid together with little or no folding twist and the yarn assembly of the strands has a tex of 5352. Thus, each strand has a tex of 1338. Each strand in turn is composed of 15 individual yarns, the individual yarns having a tex of 89.2. The filaments of each individual yarn have a twist of 270 t.p.m. and the individual yarns of each strand have a twist of 80 t.p.m..
The weft elements 12 are comprised by yarns of a single strand construction, corresponding to one of the four strands of the warp yarn, and has the same tex, i e 1338. Similarly, the strand is made up of 15 individual yarns each of tex 89.2. The twist levels in the strand and individual yarns also corresponds.
The interlocking elements 13a,13b are of like construction and are in the form of yarns which have a tex of 1822. Each interlocking yarn comprises three strands each of 607 tex and each such strand is formed from seven individual- yarns each of 86.7 tex. The filaments of each individual yarn have a twist of 270 t.p.m., the individual yarns have a twist of 80 t.p.m. in each strand and each strand has a negligible twist in the interlocking yarn.
A compound fabric constructed as described above from oxidised pan yarns had an initial thickness of 21 mm (for six plies) and a fibre volume of 47%. This fabric was then carbonised at a temperature of 1020°C for four hours under a load of 0.5 lb/sq in (0.0034 MPa) . After carbonising the fabric had a thickness of 17.25 mm and a fibre volume of 27%. The resulting carbonised preform was then subject to densification either by CVD or resin/pitch impregnation followed by charring to produce a carbon-carbon composite, and without any need for provision of conventional jig means.

Claims

CLAIMS :
1. A carbon-carbon composite having a reinforcement of carbon fibres derived from a preform of carbon fibre or carbon fibre precursor material and wherein said preform is a compound fabric in which interwoven elements of carbon fibre or carbon fibre precursor material extend through substantially the whole thickness of the preform.
2. A carbon-carbon composite according to claim 1 wherein said preform comprises interwoven plies of warp and weft elements.
3. A carbon-carbon composite according to claim 2 wherein the interwoven elements are provided in pairs arranged to extend side-by-side between neighbouring pairs of warp elements.
4. A carbon-carbon composite according to claim 3 wherein the elements of a pair of interwoven elements extend to and fro through the thickness of said preform in an offset, out-of-phase relationship in which the two elements are in side-by-side contact only at a position substantially mid-way between the surfaces of the preform.
5. A carbon-carbon composite according to any one of the preceding claims wherein at least some of the interwoven elements extend through the entire thickness of said preform.
6. A carbon-carbon composite according to claim 5 wherein all of the interwoven elements extend through the entire thickness of said preform.
7. A carbon-carbon composite according to any one of the preceding claims wherein said compound fabric comprises at least ten fabric plies.
8. A carbon-carbon composite according to any one of the preceding claims wherein elements of interwoven fabric plies and interwoven elements each have a tex greater than 750.
9. A carbon-carbon composite according to claim 8 wherein the warp and weft elements of a woven fabric ply and the interwoven elements each have a tex of greater than 1,000.
10. A carbon-carbon composite according to any one of the preceding claims wherein elements of fabric plies and interwoven elements are comprised by yarns.
11. A carbon-carbon composite according to claim 10 wherein the warp yarn of a woven fabric ply comprises a plurality of strands each comprised by a plurality of individual yarns.
12. A carbon-carbon composite according to claim 10 or claim 11 wherein a weft yarn of a woven fabric ply comprises a single strand of a plurality of individual yarns.
13. A carbon-carbon composite according to any one of claims 10 to 12 wherein an interlocking yarn comprises a plurality of strands each comprised by a plurality of yarns.
14. A carbon-carbon composite according to any one of the preceding claims wherein said reinforcement is derived from a preform assembly comprising a plurality of said preforms arranged in a superimposed interconnected relationship.
15. A carbon-carbon composite according to claim 14 wherein said superimposed preforms are interconnected by bonding.
16. A carbon-carbon composite according to claim 15 wherein said superimposed preforms are interconnected by mechanical fastening means.
17. A carbon-carbon composite substantially as hereinbefore described with reference to the accompanying drawings.
18. A carbon-carbon composite article comprising a carbon-carbon composite according to any one of the preceding claims, said reinforcement comprising interwoven elements of carbon fibre which extend through substantially the whole thickness of the article.
19. A carbon brake disc comprised by a carbon-carbon composite article according to claim 18 wherein the interwoven elements of carbon fibre extend through substantially the whole axial thickness of the disc.
PCT/GB1990/001153 1989-07-25 1990-07-25 Carbon-carbon composite WO1991001284A1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP90911643A EP0484410B1 (en) 1989-07-25 1990-07-25 Carbon-brake disk
DE69010911T DE69010911T2 (en) 1989-07-25 1990-07-25 CARBON BRAKE DISC.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB8917002.1 1989-07-25
GB8917002A GB2234533B (en) 1989-07-25 1989-07-25 Carbon-brake disc

Publications (1)

Publication Number Publication Date
WO1991001284A1 true WO1991001284A1 (en) 1991-02-07

Family

ID=10660600

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/GB1990/001153 WO1991001284A1 (en) 1989-07-25 1990-07-25 Carbon-carbon composite

Country Status (6)

Country Link
EP (1) EP0484410B1 (en)
JP (1) JPH04506953A (en)
AU (1) AU6068690A (en)
DE (1) DE69010911T2 (en)
GB (1) GB2234533B (en)
WO (1) WO1991001284A1 (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0803487A2 (en) * 1996-04-26 1997-10-29 Nippon Oil Co. Ltd. Process for producing carbonaceous preform
WO2017046538A1 (en) * 2015-09-18 2017-03-23 Safran Aircraft Engines Part made of a composite material

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DE2704378A1 (en) * 1976-02-03 1977-08-11 Commissariat Energie Atomique METHOD FOR MANUFACTURING THREE-DIMENSIONAL FABRIC PARTS
GB2040805A (en) * 1979-01-09 1980-09-03 Europ Propulsion Reinforced laminated structure
GB1587516A (en) * 1977-11-02 1981-04-08 Courtaulds Ltd Reinforcing fabric

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DE2704378A1 (en) * 1976-02-03 1977-08-11 Commissariat Energie Atomique METHOD FOR MANUFACTURING THREE-DIMENSIONAL FABRIC PARTS
GB1587516A (en) * 1977-11-02 1981-04-08 Courtaulds Ltd Reinforcing fabric
GB2040805A (en) * 1979-01-09 1980-09-03 Europ Propulsion Reinforced laminated structure

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0803487A2 (en) * 1996-04-26 1997-10-29 Nippon Oil Co. Ltd. Process for producing carbonaceous preform
EP0803487A3 (en) * 1996-04-26 1998-06-03 Nippon Oil Co. Ltd. Process for producing carbonaceous preform
WO2017046538A1 (en) * 2015-09-18 2017-03-23 Safran Aircraft Engines Part made of a composite material
FR3041343A1 (en) * 2015-09-18 2017-03-24 Snecma PIECE OF COMPOSITE MATERIAL
CN108137418A (en) * 2015-09-18 2018-06-08 赛峰飞机发动机公司 Composite material component
US10913687B2 (en) 2015-09-18 2021-02-09 Safran Aircraft Engines Composite material part
CN108137418B (en) * 2015-09-18 2021-05-25 赛峰飞机发动机公司 Composite material part

Also Published As

Publication number Publication date
DE69010911D1 (en) 1994-08-25
AU6068690A (en) 1991-02-22
GB8917002D0 (en) 1989-09-13
EP0484410A1 (en) 1992-05-13
DE69010911T2 (en) 1994-11-24
GB2234533B (en) 1994-04-06
JPH04506953A (en) 1992-12-03
EP0484410B1 (en) 1994-07-20
GB2234533A (en) 1991-02-06

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