WO2005077858A1 - Element structurel et son procede de production - Google Patents

Element structurel et son procede de production Download PDF

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Publication number
WO2005077858A1
WO2005077858A1 PCT/EP2005/001212 EP2005001212W WO2005077858A1 WO 2005077858 A1 WO2005077858 A1 WO 2005077858A1 EP 2005001212 W EP2005001212 W EP 2005001212W WO 2005077858 A1 WO2005077858 A1 WO 2005077858A1
Authority
WO
WIPO (PCT)
Prior art keywords
material layer
hard material
structural element
ceramic
ceramic hard
Prior art date
Application number
PCT/EP2005/001212
Other languages
German (de)
English (en)
Inventor
Martin Friess
Matthias Müller
Martin Nedele
Original Assignee
Deutsches Zentrum für Luft- und Raumfahrt e.V.
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 Deutsches Zentrum für Luft- und Raumfahrt e.V. filed Critical Deutsches Zentrum für Luft- und Raumfahrt e.V.
Priority to EP05707241A priority Critical patent/EP1718578A1/fr
Publication of WO2005077858A1 publication Critical patent/WO2005077858A1/fr

Links

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
    • C04B35/515—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxide ceramics
    • C04B35/56—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxide ceramics based on carbides or oxycarbides
    • C04B35/565—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxide ceramics based on carbides or oxycarbides based on silicon carbide
    • C04B35/573—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxide ceramics based on carbides or oxycarbides based on silicon carbide obtained by reaction sintering or recrystallisation
    • 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
    • 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
    • C04B41/00—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
    • C04B41/009—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone characterised by the material treated
    • 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
    • C04B41/00—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
    • C04B41/45—Coating or impregnating, e.g. injection in masonry, partial coating of green or fired ceramics, organic coating compositions for adhering together two concrete elements
    • C04B41/4505—Coating or impregnating, e.g. injection in masonry, partial coating of green or fired ceramics, organic coating compositions for adhering together two concrete elements characterised by the method of application
    • C04B41/4523—Coating or impregnating, e.g. injection in masonry, partial coating of green or fired ceramics, organic coating compositions for adhering together two concrete elements characterised by the method of application applied from the molten state ; Thermal spraying, e.g. plasma spraying
    • C04B41/4527—Plasma spraying
    • 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
    • C04B41/00—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
    • C04B41/80—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone of only ceramics
    • C04B41/81—Coating or impregnation
    • C04B41/85—Coating or impregnation with inorganic materials
    • C04B41/87—Ceramics
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C10/00—Solid state diffusion of only metal elements or silicon into metallic material surfaces
    • C23C10/60—After-treatment
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/02—Pretreatment of the material to be coated, e.g. for coating on selected surface areas
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/97—Rocket nozzles
    • F02K9/974—Nozzle- linings; Ablative coatings
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/90—Coating; Surface treatment
    • 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

Definitions

  • the invention relates to a structural element which withstands corrosive and / or abrasive hot gas flows.
  • components made of efractory metals and alloys, such as tungsten, molybdenum, rhenium, or monolithic ceramics, such as SiC, are known to be used.
  • the monolithic ceramic which is also used for such structural elements, has the disadvantage that its dynamic and thermal shock resistance is low and that the possibilities of shaping the structural elements are also considerably restricted.
  • the invention is therefore based on the object of creating a structural element of the type described at the outset which, on the one hand, withstands corrosive and / or abrasive hot gas flows and, on the other hand, can be advantageously produced.
  • This object is achieved according to the invention in a structural element of the type described at the outset in that the structural element comprises a fiber-ceramic base body, in that the base body is formed from a C / C molded body which, in a volume region adjacent to an upper side of the base body, has an Si to C / C-SiC implemented fiber-ceramic structure and that at least a portion of the top of the base body is applied a ceramic hard material layer generated by plasma spraying.
  • the advantage of the solution according to the invention can be seen in the fact that by using a base body comprising a C / C shaped body with a volume area having a C / C-SiC structure, a very inexpensive and easily moldable base body is available and that this is available Base body can also be inexpensively provided with the ceramic hard material layer, which withstands corrosive and / or abrasive hot gas flows and at the same time has advantageous dynamic and thermal shock-resistant properties.
  • the thickness of the ceramic hard material layer is less than approximately 1 mm.
  • the thickness of the ceramic hard material layer is less than approximately 0.5 mm.
  • the thickness of the ceramic hard material layer is at least approximately 0.01 mm, more preferably approximately 0.05 mm.
  • the ceramic hard material layer has not yet been specified.
  • the ceramic hard material layer has a hardness that is greater than that of corundum.
  • Preferred materials for hard material layers are, for example, oxides and / or nitrides and / or borides.
  • the ceramic hard material layer comprises carbides.
  • Preferred carbides are, for example, boron carbides.
  • carbides are preferably carbides of the transition metals, in particular the transition metals of the fourth and / or fifth and / or sixth subgroup.
  • the invention relates to a method for producing a structural element that withstands corrosive and / or abrasive hot gas flows.
  • such a method for producing a structural element which withstands corrosive and / or abrasive hot gas flows comprises • producing a C / C shaped body from carbon fibers and a carbon-containing matrix by pyrolysis, forming a base body of the structural element by providing the C / C Molded body with a volume area adjoining an upper side of the base body with a fiber-ceramic structure converted to C / C-SiC by introducing Si in this volume area and providing at least a partial area of the upper side with a ceramic hard material layer by plasma spraying.
  • the ceramic hard material layer is preferably applied with a thickness of less than approximately 1 mm.
  • the thickness of the ceramic hard material layer is at least approximately 0.01 mm.
  • the application of the ceramic hard material layer by plasma spraying is preferably carried out by vacuum plasma spraying in order to obtain a good connection between the ceramic hard material layer and the top of the base body for the component.
  • the ceramic hard material layer is preferably produced by plasma spraying of materials which result in a hard material layer whose hardness is greater than corundum.
  • the ceramic hard material layer is produced by plasma spraying of materials which result in a hard material layer based on oxides and / or nitrides and / or borides.
  • Another advantageous method for producing the ceramic hard material layer is the plasma spraying of materials which give a hard material layer based on carbides.
  • carbides are boron carbides.
  • carbides are carbides of the transition metals, in particular the transition metals of the fourth and / or fifth and / or sixth subgroup.
  • Fig. 1 shows an embodiment of a flying object with structural elements according to the invention
  • Fig. 2 shows a cross section through a section of a wall of the structural element according to the invention.
  • An embodiment of an engine for a flying object shown in FIG. 1, designated as a whole by 10, comprises a propellant charge 14 made of solid material which is arranged in a housing 12 and which, for example, is also provided with a central duct 16.
  • a rear cone 20 adjoins a usually rear end 18 of the housing 12, in which a nozzle 22 is arranged which is penetrated by a hot gas flow 24 which forms when the propellant charge 14 burns off and in the region of the end 18 from the housing 12 exit.
  • the hot gas flow 24 enters an end 26 of the nozzle 22 on the side of the propellant and exits into the surroundings from an outlet end 28 of the nozzle, the nozzle 22 having a constriction 30 between the end 26 of the propellant and the end 28 of the outlet.
  • this jet vane 32 serves to influence the hot gas flow 24 immediately before it exits through the outlet end 28 of the nozzle 22 in order to steer the flying object.
  • the rear cone 20 additionally comprises outer, flight-stabilizing air guiding surfaces 34, also referred to as fin.
  • both an inner wall 36 guiding the hot gas flow 24 and an outer wall 38 of the thrusters 32 have a surface 40 or 42 to be provided, which withstands the corrosive and / or abrasive particles carried by the hot gas flow 24.
  • FIG. 2 An inventive construction of such an inner wall 36 or of such an outer wall 38 is shown in FIG. 2 by way of example using the example of a detail from the outer wall 38 of a jet vane 32.
  • the outer wall 38 is formed from a base body 50 which is constructed as a fiber-ceramic C / C molded body.
  • a base body 50 which is constructed as a fiber-ceramic C / C molded body.
  • Such a C / C shaped body is produced by mixing carbon fibers with a carbon-containing matrix material and pyrolyzing the matrix material to carbon.
  • the molded body 52 is implemented in a volume region 56 adjoining an upper side 54 thereof by infiltration of silicon through a fiber-ceramic structure having C / C-SiC, the formation of SiC in the volume region 56 giving the outer wall 38 greater hardness and rigidity ,
  • the volume region 56 with the fiber-ceramic structure comprising C / C-SiC thus comprises a multi-component composite material and can represent a partial region of the outer wall 38. However, the volume region 56 can also extend through the entire outer wall 38 and thus give the outer wall 38 overall greater mechanical strength.
  • the proportion of SiC in the volume range 56 is preferably up to 50%, the rest being carbon.
  • the top side 54 of the base body 50 is provided with a ceramic hard material layer 60 which is applied to the base body 50 by plasma spraying, preferably vacuum plasma spraying.
  • the ceramic hard material layer 60 forms a protective layer for the outer wall 38, which is able to withstand the corrosive and / or abrasive hot gas flow 24.
  • the ceramic hard material layer 60 preferably has a hardness which is greater than that of corundum (Al 2 O 3 ). Ceramic hard material layers which are suitable according to the invention and are harder than corundum are in particular oxides, nitrides and borides.
  • Materials suitable according to the invention for the formation of the ceramic hard material layer 60 are also boron carbides, for example B 4 C and / or transition metal carbides, preferably transition metal carbides of the elements of the fourth and / or fifth and / or sixth subgroup, such as titanium, vanadium, chromium, zirconium, Niobium, molybdenum, hafnium, tantalum and / or tungsten.
  • the layer thickness of the ceramic hard material layer is preferably less than approximately 1 mm.
  • Favorable values for the thickness of the ceramic hard material layer are less than 0.5 mm, for example between 0.1 and 0.3 mm. With hard material layers of this thickness, chipping of the ceramic hard material layer in the event of thermal alternating loads can be avoided.
  • a thruster 32 according to the invention can preferably be produced by molding a preform largely corresponding to the shape of the thruster 32 from a molding composition comprising carbon fibers and a carbon-containing matrix material and by curing the matrix material is produced as a rigid and stable preform, as described, for example, in the publication "Brake discs made of ceramic composite materials for rail vehicles", H. Pfeiffer et al., DGM MaschinenstoffThat '96, 28-31-5, 1996, Stuttgart using the example of brake discs is described.
  • Such a preform is subsequently converted into the C / C shaped body 52 by pyrolysis of the matrix material, which is either brought into the final shape of the jet vane 32 by machining, for example mechanical processing, before or after pyrolysis, or before by suitable shaping of the preform the hardening after pyrolysis already has the final shape of the jet vane 32.
  • volume region 56 comprising C / C-SiC, for example by means of the LSI method described in the above publication, the volume region 56 either being only a partial region of the outer wall 38 of the radiant body or penetrating it entirely.
  • the ceramic hard material layer 60 is applied to the upper side 54 of the base body 50 by plasma spraying, in particular vacuum plasma spraying with the materials mentioned above or with mixtures thereof, so that the jet vane 32 with the final shape is present immediately after the plasma spraying.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Materials Engineering (AREA)
  • Organic Chemistry (AREA)
  • Structural Engineering (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Plasma & Fusion (AREA)
  • Physics & Mathematics (AREA)
  • Mechanical Engineering (AREA)
  • Manufacturing & Machinery (AREA)
  • Metallurgy (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Composite Materials (AREA)
  • Inorganic Chemistry (AREA)
  • Coating By Spraying Or Casting (AREA)
  • Physical Or Chemical Processes And Apparatus (AREA)

Abstract

L'invention vise à produire un élément structurel qui résiste aux flux gazeux chauds corrosifs et/ou abrasifs, cet élément structurel devant, d'une part, résister aux flux gazeux chauds corrosifs et/ou abrasifs et, d'autre part, pouvoir être produit de manière avantageuse. L'invention est caractérisée en ce que l'élément structurel comprend un corps de base en fibres de céramique, tel que le corps de base soit constitué d'un corps moulé C/C qui présente, dans une zone volume adjacente à une face supérieure du corps de base, une structure en fibres de céramique qui réagit avec du Si pour donner du C/C-SiC et en ce qu'une couche de matière céramique à résistance mécanique élevée est produite par projection au plasma au moins sur une zone partielle de la face supérieure du corps de base. .
PCT/EP2005/001212 2004-02-13 2005-02-07 Element structurel et son procede de production WO2005077858A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP05707241A EP1718578A1 (fr) 2004-02-13 2005-02-07 Element structurel et son procede de production

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102004008452.1 2004-02-13
DE200410008452 DE102004008452B4 (de) 2004-02-13 2004-02-13 Strukturelement und Verfahren zur Herstellung desselben

Publications (1)

Publication Number Publication Date
WO2005077858A1 true WO2005077858A1 (fr) 2005-08-25

Family

ID=34813532

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2005/001212 WO2005077858A1 (fr) 2004-02-13 2005-02-07 Element structurel et son procede de production

Country Status (4)

Country Link
EP (1) EP1718578A1 (fr)
DE (1) DE102004008452B4 (fr)
NO (1) NO20050758L (fr)
WO (1) WO2005077858A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107903085A (zh) * 2017-12-01 2018-04-13 北京天宜上佳新材料股份有限公司 一种碳陶制动件的制备方法

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102004037487A1 (de) 2004-07-27 2006-03-23 Deutsches Zentrum für Luft- und Raumfahrt e.V. Strahlruder und Verfahren zur Herstellung eines Strahlruders
DE102005026635A1 (de) * 2005-06-03 2006-12-07 Deutsches Zentrum für Luft- und Raumfahrt e.V. Strukturelement und Verfahren zur Herstellung desselben

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH06345571A (ja) * 1993-06-03 1994-12-20 Tokai Carbon Co Ltd 高温耐酸化性ｃ／ｃ複合材の製造方法
JPH11171669A (ja) * 1997-12-15 1999-06-29 Ngk Insulators Ltd 炭化硼素皮膜の製造方法
EP1043290A1 (fr) * 1999-04-08 2000-10-11 Ngk Insulators, Ltd. Matière carbonée ayant une couche protectrice résistant à l'oxydation et procédé pour sa fabrication

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4735850A (en) * 1985-10-31 1988-04-05 Science Applications International Corporation Refractory composite articles

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH06345571A (ja) * 1993-06-03 1994-12-20 Tokai Carbon Co Ltd 高温耐酸化性ｃ／ｃ複合材の製造方法
JPH11171669A (ja) * 1997-12-15 1999-06-29 Ngk Insulators Ltd 炭化硼素皮膜の製造方法
EP1043290A1 (fr) * 1999-04-08 2000-10-11 Ngk Insulators, Ltd. Matière carbonée ayant une couche protectrice résistant à l'oxydation et procédé pour sa fabrication

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107903085A (zh) * 2017-12-01 2018-04-13 北京天宜上佳新材料股份有限公司 一种碳陶制动件的制备方法

Also Published As

Publication number Publication date
DE102004008452A1 (de) 2005-09-01
DE102004008452B4 (de) 2006-03-02
EP1718578A1 (fr) 2006-11-08
NO20050758D0 (no) 2005-02-11
NO20050758L (no) 2005-08-15

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