[go: up one dir, main page]

WO2016043743A1 - Materiau composite a nanofils - Google Patents

Materiau composite a nanofils Download PDF

Info

Publication number
WO2016043743A1
WO2016043743A1 PCT/US2014/056193 US2014056193W WO2016043743A1 WO 2016043743 A1 WO2016043743 A1 WO 2016043743A1 US 2014056193 W US2014056193 W US 2014056193W WO 2016043743 A1 WO2016043743 A1 WO 2016043743A1
Authority
WO
WIPO (PCT)
Prior art keywords
nano
yarn
lengths
composite material
laterally
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/US2014/056193
Other languages
English (en)
Inventor
Kai Kadau
Michael Clossen-Von Lanken Schulz
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Siemens Corp
Siemens Energy Inc
Original Assignee
Siemens AG
Siemens Corp
Siemens Energy Inc
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 Siemens AG, Siemens Corp, Siemens Energy Inc filed Critical Siemens AG
Priority to PCT/US2014/056193 priority Critical patent/WO2016043743A1/fr
Publication of WO2016043743A1 publication Critical patent/WO2016043743A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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
    • C04B35/71—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
    • 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
    • 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
    • C04B35/622—Forming processes; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
    • C04B35/626—Preparing or treating the powders individually or as batches ; preparing or treating macroscopic reinforcing agents for ceramic products, e.g. fibres; mechanical aspects section B
    • C04B35/628—Coating the powders or the macroscopic reinforcing agents
    • C04B35/62844—Coating fibres
    • C04B35/62847—Coating fibres with oxide ceramics
    • C04B35/62849—Silica or silicates
    • 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
    • C04B35/622—Forming processes; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
    • C04B35/626—Preparing or treating the powders individually or as batches ; preparing or treating macroscopic reinforcing agents for ceramic products, e.g. fibres; mechanical aspects section B
    • C04B35/628—Coating the powders or the macroscopic reinforcing agents
    • C04B35/62844—Coating fibres
    • C04B35/62857—Coating fibres with non-oxide ceramics
    • C04B35/62865—Nitrides
    • C04B35/62871—Silicon nitride
    • 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
    • C04B35/622—Forming processes; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
    • C04B35/626—Preparing or treating the powders individually or as batches ; preparing or treating macroscopic reinforcing agents for ceramic products, e.g. fibres; mechanical aspects section B
    • C04B35/628—Coating the powders or the macroscopic reinforcing agents
    • C04B35/62897—Coatings characterised by their thickness
    • D—TEXTILES; PAPER
    • D03—WEAVING
    • D03D—WOVEN FABRICS; METHODS OF WEAVING; LOOMS
    • D03D15/00—Woven fabrics characterised by the material, structure or properties of the fibres, filaments, yarns, threads or other warp or weft elements used
    • D03D15/30—Woven fabrics characterised by the material, structure or properties of the fibres, filaments, yarns, threads or other warp or weft elements used characterised by the structure of the fibres or filaments
    • D03D15/33—Ultrafine fibres, e.g. microfibres or nanofibres
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/005—Selecting particular materials
    • 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
    • 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
    • F01D5/284—Selection of ceramic materials
    • 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
    • F01D9/00—Stators
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B82—NANOTECHNOLOGY
    • B82Y—SPECIFIC USES OR APPLICATIONS OF NANOSTRUCTURES; MEASUREMENT OR ANALYSIS OF NANOSTRUCTURES; MANUFACTURE OR TREATMENT OF NANOSTRUCTURES
    • B82Y30/00—Nanotechnology for materials or surface science, e.g. nanocomposites
    • 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
    • C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
    • C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
    • C04B2235/50—Constituents or additives of the starting mixture chosen for their shape or used because of their shape or their physical appearance
    • C04B2235/52—Constituents or additives characterised by their shapes
    • C04B2235/5208—Fibers
    • C04B2235/5252—Fibers having a specific pre-form
    • C04B2235/5256—Two-dimensional, e.g. woven structures
    • 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
    • C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
    • C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
    • C04B2235/50—Constituents or additives of the starting mixture chosen for their shape or used because of their shape or their physical appearance
    • C04B2235/52—Constituents or additives characterised by their shapes
    • C04B2235/5208—Fibers
    • C04B2235/526—Fibers characterised by the length of the fibers
    • 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
    • C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
    • C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
    • C04B2235/50—Constituents or additives of the starting mixture chosen for their shape or used because of their shape or their physical appearance
    • C04B2235/52—Constituents or additives characterised by their shapes
    • C04B2235/5208—Fibers
    • C04B2235/5264—Fibers characterised by the diameter of the fibers
    • 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
    • C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
    • C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
    • C04B2235/50—Constituents or additives of the starting mixture chosen for their shape or used because of their shape or their physical appearance
    • C04B2235/52—Constituents or additives characterised by their shapes
    • C04B2235/5208—Fibers
    • C04B2235/5268—Orientation of the fibers
    • 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
    • C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
    • C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
    • C04B2235/50—Constituents or additives of the starting mixture chosen for their shape or used because of their shape or their physical appearance
    • C04B2235/52—Constituents or additives characterised by their shapes
    • C04B2235/5284—Hollow fibers, e.g. nanotubes
    • C04B2235/5288—Carbon nanotubes
    • 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
    • C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
    • C04B2235/65—Aspects relating to heat treatments of ceramic bodies such as green ceramics or pre-sintered ceramics, e.g. burning, sintering or melting processes
    • C04B2235/66—Specific sintering techniques, e.g. centrifugal sintering
    • C04B2235/666—Applying a current during sintering, e.g. plasma sintering [SPS], electrical resistance heating or pulse electric current sintering [PECS]
    • 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
    • C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
    • C04B2235/70—Aspects relating to sintered or melt-casted ceramic products
    • C04B2235/96—Properties of ceramic products, e.g. mechanical properties such as strength, toughness, wear resistance
    • C04B2235/9669—Resistance against chemicals, e.g. against molten glass or molten salts
    • D—TEXTILES; PAPER
    • D01—NATURAL OR MAN-MADE THREADS OR FIBRES; SPINNING
    • D01F—CHEMICAL FEATURES IN THE MANUFACTURE OF ARTIFICIAL FILAMENTS, THREADS, FIBRES, BRISTLES OR RIBBONS; APPARATUS SPECIALLY ADAPTED FOR THE MANUFACTURE OF CARBON FILAMENTS
    • D01F9/00—Artificial filaments or the like of other substances; Manufacture thereof; Apparatus specially adapted for the manufacture of carbon filaments
    • D01F9/08—Artificial filaments or the like of other substances; Manufacture thereof; Apparatus specially adapted for the manufacture of carbon filaments of inorganic material
    • D01F9/12—Carbon filaments; Apparatus specially adapted for the manufacture thereof
    • D—TEXTILES; PAPER
    • D10—INDEXING SCHEME ASSOCIATED WITH SUBLASSES OF SECTION D, RELATING TO TEXTILES
    • D10B—INDEXING SCHEME ASSOCIATED WITH SUBLASSES OF SECTION D, RELATING TO TEXTILES
    • D10B2101/00—Inorganic fibres
    • D10B2101/10—Inorganic fibres based on non-oxides other than metals
    • D10B2101/12—Carbon; Pitch
    • D10B2101/122—Nanocarbons
    • D—TEXTILES; PAPER
    • D10—INDEXING SCHEME ASSOCIATED WITH SUBLASSES OF SECTION D, RELATING TO TEXTILES
    • D10B—INDEXING SCHEME ASSOCIATED WITH SUBLASSES OF SECTION D, RELATING TO TEXTILES
    • D10B2505/00—Industrial
    • D10B2505/02—Reinforcing materials; Prepregs
    • 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
    • F05D2300/6033—Ceramic matrix composites [CMC]
    • 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

Definitions

  • This invention is directed generally to composite materials, and more particularly to nano-yarns contained within base materials to form gas turbine engine components.
  • gas turbine engines typically include a compressor for compressing air, a combustor for mixing the compressed air with fuel and igniting the mixture, and a turbine blade assembly for producing power.
  • Combustors often operate at high temperatures that may exceed 2,260 degrees Fahrenheit.
  • Typical turbine combustor configurations expose turbine vane assemblies to these high temperatures.
  • turbine vanes must be made of materials capable of withstanding such high temperatures. Alloys and composite materials have been used to withstand exposure to these high temperatures.
  • Composite materials offer the possibility to realize the advantages of two or more materials forming the composite material.
  • One of the challenges of metal composites is the thermal mismatch of the two constituents and nonisotropic strength enhancement.
  • a nano-yarn composite material formed from a base material and at least one nano-yarn positioned within the base material for strengthening the base material is disclosed.
  • the base material may be, but is not limited to being, a ceramic matrix material or metal.
  • the nano-yarn composite material may be formed from a twist-based spinning of carbon nanotube sheets or other appropriate material.
  • the nano-yarn may form a woven structure or a knotted structure.
  • the nano-yarn composite material may be used to form components of a gas turbine engine, such as, but not limited to, airfoils, such as blades and vanes, and transitions.
  • a nano-yarn composite material may include one or more ceramic matrix materials and one or more nano-yarns positioned within the at least one ceramic matrix material.
  • the nano-yarn may form a woven structure.
  • the woven structure may include a plurality of laterally extending nano-yarn lengths in a first direction and a plurality of laterally extending nano-yarn lengths in a second direction that is generally orthogonal to the first direction.
  • the lengths of nano-yarn in the first direction may be separated from each other laterally, and the lengths of nano-yarn in the second direction are separated from each other laterally.
  • the lengths of laterally extending nano-yarn in the first and second directions may alternate position between top and bottom positions relative to each other to form the woven structure.
  • the nano-yarn may be form a knotted structure.
  • the knotted structure may include a plurality of laterally extending nano-yarn lengths in a first direction and a plurality of laterally extending nano-yarn lengths in a second direction that is generally orthogonal to the first direction.
  • the lengths of nano-yarn in the first direction may be separated from each other laterally and the lengths of nano-yarn in the second direction may be separated from each other laterally.
  • Each of the nano-yarn lengths extending in the first direction may be knotted to nano-yarn lengths extending in the second direction at intersections of the lengths of nano-yarn.
  • the nano-yarn may be formed from a twist-based spinning of carbon nanotube sheets.
  • a gas engine turbine component may be formed from a body formed from one or more nano-yarn composite materials formed from one or more ceramic matrix materials and one or more nano-yarns positioned within the ceramic matrix material.
  • the body forming the gas turbine engine component may form an airfoil usable within a gas turbine engine, wherein the airfoil may be formed from a pressure side on a first side of the airfoil and a suction side on a second side of the airfoil that faces generally in an opposite direction than that of the first side, a leading edge and a trailing edge.
  • the nano-yarn may form a woven structure, such as, but not limited to the woven structure previously described.
  • the nano-yarn may form a knotted structure, such as, but not limited to the knotted structure previously described.
  • a nano-yarn composite material may be formed from one or more metals and one or more nano-yarns positioned within the one or more ceramic matrix materials. In at least one embodiment, the nano-yarn
  • the composite material may an alloy.
  • the nano-yarn may form a woven structure, such as, but not limited to the woven structure previously described.
  • the nano-yarn may form a knotted structure, such as, but not limited to the knotted structure previously described.
  • the nano-yarn may be formed from a twist-based spinning of carbon nanotube sheets.
  • nano-yarn composite material is that the nano-yarn composite material is stronger and less brittle than a component formed solely from ceramic.
  • nano-yarn composite material Another advantage of the nano-yarn composite material is that the nano-yarn has superior elasticity and strength and high corrosion resistance. The elasticity of the nano-yarn helps reduce thermal mismatch stresses between the yarn and the matrix during service and associated thermal cycles.
  • nano-yarn composite material has a high melting point which allows sintering of the nano-structure and the ceramic matrix, either with conventional sintering techniques or by spark erosion sintering techniques which allow control of the bonding of the nano-yarn and the matrix.
  • Figure 1 is a perspective view of a gas turbine engine with one or more components formed from a nano-yarn composite material.
  • Figure 2 is a perspective view of an airfoil usable in the gas turbine engine of Figure 1 and formed from a nano-yarn composite material.
  • Figure 3 is a cross-sectional, perspective view of a turbine airfoil formed from a nano-yarn composite material and taken at section line 3-3 in Figure 2.
  • Figure 4 is a top view of a knotted structure of nano-yarn within a nano-yarn composite material.
  • Figure 5 is a top view of a woven structure of nano-yarn within a nano-yarn composite material.
  • a nano-yarn composite material 10 formed from a base material 12 and at least one nano-yarn 14 positioned within the base material 12 for strengthening the base material 12 is disclosed.
  • the base material 12 may be, but is not limited to being, a ceramic matrix material or metal.
  • the nano-yarn composite material 10 may be formed from a twist-based spinning of carbon nanotube sheets or other appropriate material.
  • the nano-yarn 14 may form a woven structure or a knotted structure.
  • the nano-yarn composite material 10 may be used to form components of a gas turbine engine, such as, but not limited to, airfoils, such as blades and vanes, and transitions.
  • the nano-yarn composite material 10 may be formed from one or more base materials 12 and one or more nano-yarns positioned within the base material 12.
  • the nano-yarn 14 may be formed from twist based spun carbon nanotube sheets.
  • the nano-yarn 14 may be a spin porous multifunctional yarn with weavability, flexibility, and durability. High guest concentrations may add functions such as energy storage, harvesting, and conversion.
  • the carbon nanotube sheets may be overlaid with up to about 99 percent guest materials.
  • the carbon nanotube sheets may be formed via carbon multiwall nanotube forests grown by chemical vapor deposition. In at least one embodiment, the carbon multiwall nanotube forest height may be about 350 nanometers.
  • the carbon nanotubes may have outer diameters of about nine nanometers.
  • the nano-yarn 14 may be formed via the forest grown carbon multiwall nanotubes that are twist-spun using methods similar to those methods used to form pure carbon nanotube yarns.
  • the carbon nanotube sheets have structure and properties that are useful for making biscrolled yarns.
  • the carbon nanotube sheets may have be an aerogel having a carbon network density of about 1 .5 mg/cm 3 , which is close to the density of air and an areal density of only about 1 to 3 g/cm 2 .
  • the carbon nanotube sheets may have a high specific strength (i.e., strength normalized by density) of up to about 144 MPa cm 3 /g.
  • the nano-yarn 14 may be formed via biscrolling with fabrication of a guest or host stack by depositing guest material onto a carbon nanotube sheet produced by twist-based spinning from a forest or forest drawn sheets. Guest materials may be deposited via an electrostatic power coating gun or other liquid free guest deposition processes such as electron beam evaporation, sputtering, and aerosol filtration.
  • the biscrolled yarn may include twisting a bilayer guest/sheet stack to make yarn such that the amount of twist of the yarn bias angle relative to yarn direction is typically between about 30 degrees and about 45 degrees.
  • the nano-yarn 14 may be ceramic coated, such as, but not limited to being, coated with between 4-nm and 18- nm thick S1O2 or Si3N .
  • the base material 12 may be, but is not limited to being, a ceramic matrix material or metal, such as, but not limited to, an alloy.
  • the base material 12 may be formed into a gas engine turbine component 16, as shown in Figures 1 -3.
  • the base material 12 may form a gas engine turbine component 16 having a body 20 configured as an airfoil 18, as shown in Figures 1 -3, a transition 34, as shown in Figure 1 , or the like.
  • the body 20 forming the gas turbine engine component 16 may form an airfoil 18 usable within a gas turbine engine 36.
  • the airfoil 18 may be formed from a pressure side 22 on a first side 24 of the airfoil 18 and a suction side 26 on a second side 28 of the airfoil 18 that faces generally in an opposite direction than that of the first side 24, a leading edge 30 and a trailing edge 32.
  • the nano-yarn 14 may form a woven structure.
  • the woven structure may include a plurality of laterally extending nano-yarn lengths 38 in a first direction 40 and a plurality of laterally extending nano- yarn lengths 42 in a second direction 44 that is generally orthogonal to the first direction 40.
  • the lengths 38 of nano-yarn 14 in the first direction 40 may be separated from each other laterally, and the lengths 42 of nano-yarn 14 in the second direction 44 may be separated from each other laterally.
  • the lengths 38, 42 of laterally extending nano-yarn 14 in the first and second directions 40, 44 alternate position between top and bottom positions 46, 48 relative to each other to form the woven structure.
  • the nano-yarn 14 may form a knotted structure.
  • the knotted structure may include a plurality of laterally extending nano-yarn lengths 38 in a first direction 40 and a plurality of laterally extending nano- yarn lengths 42 in a second direction 44 that is generally orthogonal to the first direction 42.
  • the lengths 38 of nano-yarn 14 in the first direction 40 may be separated from each other laterally, and the lengths 42 of nano-yarn 14 in the second direction 44 may be separated from each other laterally.
  • One or more of the lengths 38 of nano-yarn 14 in the first direction 40 may be knotted to one more lengths 42 of nano-yarn 14 in the second direction 44.
  • each nano-yarn length 38 extending in the first direction 40 may be knotted to nano- yarn lengths 42 extending in a second direction 44 at intersections 50 of the lengths 38, 42 of nano-yarn 14.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Ceramic Engineering (AREA)
  • Materials Engineering (AREA)
  • Manufacturing & Machinery (AREA)
  • Organic Chemistry (AREA)
  • Structural Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Inorganic Chemistry (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Composite Materials (AREA)
  • Nanotechnology (AREA)
  • Textile Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Woven Fabrics (AREA)

Abstract

L'invention concerne un matériau composite à nanofils (10) formé à partir d'un matériau de base (12) et d'au moins un nanofil (14), positionné à l'intérieur du matériau de base (12) pour renforcer le matériau de base (12). Dans au moins un mode de réalisation, le matériau de base (12) peut être, sans caractère limitatif, un matériau de matrice céramique (12) ou un métal. Le matériau composite (10) à nanofils peut être formé par la filature par torsion de feuilles de nanotubes de carbone ou d'un autre matériau approprié. Le nanofil (14) peut former une structure tissée ou une structure nouée. Le matériau composite (10) à nanofils peut être utilisé pour former des composants (16) d'une turbine à gaz tels que, sans caractère limitatif, des profils aérodynamiques (18) tels que des aubes et des ailettes, et des éléments de transition (34).
PCT/US2014/056193 2014-09-18 2014-09-18 Materiau composite a nanofils Ceased WO2016043743A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/US2014/056193 WO2016043743A1 (fr) 2014-09-18 2014-09-18 Materiau composite a nanofils

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/US2014/056193 WO2016043743A1 (fr) 2014-09-18 2014-09-18 Materiau composite a nanofils

Publications (1)

Publication Number Publication Date
WO2016043743A1 true WO2016043743A1 (fr) 2016-03-24

Family

ID=51660640

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2014/056193 Ceased WO2016043743A1 (fr) 2014-09-18 2014-09-18 Materiau composite a nanofils

Country Status (1)

Country Link
WO (1) WO2016043743A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPWO2020203484A1 (fr) * 2019-03-29 2020-10-08
US20210355952A1 (en) * 2011-07-05 2021-11-18 Raytheon Technologies Corporation Efficient, low pressure ratio propulsor for gas turbine engines

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20030214063A1 (en) * 2000-09-13 2003-11-20 Blach Yizoso Ricardo Method for the production of composite materials
WO2007015710A2 (fr) * 2004-11-09 2007-02-08 Board Of Regents, The University Of Texas System Fabrication et applications de rubans, feuilles et fils retors ou non de nanofibres
US20120085970A1 (en) * 2010-10-12 2012-04-12 Florida State University Research Foundation Composite Materials Reinforced with Carbon Nanotube Yarns
EP2581355A1 (fr) * 2011-10-11 2013-04-17 Siemens Aktiengesellschaft Céramique dotée d'un renforcement par des nanostructures
WO2014028043A2 (fr) * 2012-03-30 2014-02-20 National Institute Of Aerospace Associates Composite bn-bn multifonctionnel
WO2014137457A1 (fr) * 2013-03-08 2014-09-12 Uskert Richard C Procédé de formation d'un ensemble aile portante composite de moteur à turbine à gaz et ensemble aile portante correspondante

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20030214063A1 (en) * 2000-09-13 2003-11-20 Blach Yizoso Ricardo Method for the production of composite materials
WO2007015710A2 (fr) * 2004-11-09 2007-02-08 Board Of Regents, The University Of Texas System Fabrication et applications de rubans, feuilles et fils retors ou non de nanofibres
US20120085970A1 (en) * 2010-10-12 2012-04-12 Florida State University Research Foundation Composite Materials Reinforced with Carbon Nanotube Yarns
EP2581355A1 (fr) * 2011-10-11 2013-04-17 Siemens Aktiengesellschaft Céramique dotée d'un renforcement par des nanostructures
WO2014028043A2 (fr) * 2012-03-30 2014-02-20 National Institute Of Aerospace Associates Composite bn-bn multifonctionnel
WO2014137457A1 (fr) * 2013-03-08 2014-09-12 Uskert Richard C Procédé de formation d'un ensemble aile portante composite de moteur à turbine à gaz et ensemble aile portante correspondante

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20210355952A1 (en) * 2011-07-05 2021-11-18 Raytheon Technologies Corporation Efficient, low pressure ratio propulsor for gas turbine engines
JPWO2020203484A1 (fr) * 2019-03-29 2020-10-08
EP3950640A4 (fr) * 2019-03-29 2022-12-21 Tosoh Corporation Fibre céramique continue fixée à une couche de revêtement et son procédé de fabrication, et matériau composite à matrice céramique et son procédé de fabrication
JP2024133087A (ja) * 2019-03-29 2024-10-01 東ソー株式会社 被覆層付セラミックス連続繊維及びその製造方法、並びにセラミックマトリックス複合材料及びその製造方法
US12134584B2 (en) 2019-03-29 2024-11-05 Tosoh Corporation Coating layer-attached continuous ceramic fiber and method for producing same, and ceramic matrix composite material and method for producing same
JP7616048B2 (ja) 2019-03-29 2025-01-17 東ソー株式会社 被覆層付セラミックス連続繊維及びその製造方法、並びにセラミックマトリックス複合材料及びその製造方法
JP7729443B2 (ja) 2019-03-29 2025-08-26 東ソー株式会社 被覆層付セラミックス連続繊維及びその製造方法、並びにセラミックマトリックス複合材料及びその製造方法

Similar Documents

Publication Publication Date Title
US10563523B2 (en) Method for fabricating a ceramic matrix composite rotor blade
US7859100B2 (en) Thermal barrier coating material, thermal barrier member, and member coated with thermal barrier and method for manufacturing the same
US11796174B2 (en) CMC combustor shell with integral chutes
US10808308B2 (en) Thermal barrier coating, turbine member, and gas turbine
US20120082541A1 (en) Gas turbine engine casing
US20160215634A1 (en) Vane assembly for a gas turbine engine
US10400612B2 (en) Fiber reinforced airfoil
US9587497B2 (en) Turbine airfoil of composite material and method of manufacturing thereof
JP2017122439A (ja) ターボ機械およびターボ機械用タービンブレード
JP5514860B2 (ja) ガスタービンエンジン用のセラミック複合材料製エアフォイル及びベーン並びにセラミック複合材料製エアフォイル形成方法
JP6448791B2 (ja) ハイブリッドセラミック基複合材料
CA2853040A1 (fr) Procede de fabrication d'un secteur d'aubes directrices de turbine ou decompresseur en materiau composite pour un moteur a turbine, et turbine ou compresseur comportant de tels secteurs d'aubes directrices
US20190145269A1 (en) Ceramic component for combustion turbine engines
US20180178489A1 (en) Composite component
CN108119188A (zh) 一种陶瓷基复合材料涡轮转子叶片
EP2971569A2 (fr) Composant de turbine à gaz comportant une couche élastique
US20180030584A1 (en) Thermal barrier coating, turbine member, gas turbine, and manufacturing method for thermal barrier coating
US20080131608A1 (en) Thermal barrier coating material, thermal barrier member, and member coated with thermal barrier and method for manufacturing the same
WO2016043743A1 (fr) Materiau composite a nanofils
US8708659B2 (en) Turbine engine component having protective coating
JP5656528B2 (ja) 耐高温部材及びガスタービン
WO2019187663A1 (fr) Revêtement de protection thermique, élément de turbine, turbine à gaz et procédé de fabrication de revêtement de protection thermique
US11828195B2 (en) Fibrous preform for the aerodynamic profile of a turbomachine blade
WO2018015985A1 (fr) Élément revêtu d'isolation thermique, turbine à flux axial et procédé de production d'élément revêtu d'isolation thermique
US10280769B2 (en) Nonmetallic airfoil with a compliant attachment

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 14780972

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

122 Ep: pct application non-entry in european phase

Ref document number: 14780972

Country of ref document: EP

Kind code of ref document: A1