公开(公告)号：US20240344255A1

公开(公告)日：2024-10-17

申请号：US18134941

申请日：2023-04-14

Applicant: Raytheon Technologies Corporation

Inventor： Robin H. Fernandez

IPC: D04H18/00 ,  C04B35/628 ,  C04B35/64 ,  C04B35/657 ,  C04B35/80

CPC classification number: D04H18/00 ,  C04B35/62884 ,  C04B35/64 ,  C04B35/657 ,  C04B35/80 ,  C04B2235/5244 ,  C04B2235/5256 ,  C04B2235/614 ,  C04B2235/616

Abstract: A tooling assembly for debulking a fibrous preform includes a first tooling fixture comprising a plurality of receiving holes, and a second tooling fixture comprising a plurality of pins projecting toward the first tooling fixture, each of the plurality of pins corresponding to and extending towards one of the plurality of receiving holes. The second tooling fixture is engageable with the first tooling fixture to define an inner volume therebetween, the inner volume configured to support the preform during debulking while a compressive force is applied thereto.

公开(公告)号：US12115486B2

公开(公告)日：2024-10-15

申请号：US17618214

申请日：2020-06-30

Applicant: SAFRAN CERAMICS

Inventor： Benjamin Lacombe ,  Gildas Garnier

IPC: B01D46/24 ,  B28B1/00 ,  B33Y10/00 ,  B33Y80/00 ,  C04B35/628 ,  C04B35/657 ,  C04B35/78 ,  C04B38/00

CPC classification number: B01D46/24491 ,  B01D46/2429 ,  B01D46/24492 ,  B01D46/2455 ,  B01D46/2482 ,  B01D46/2484 ,  B33Y80/00 ,  C04B35/62884 ,  C04B35/657 ,  C04B35/78 ,  C04B38/0051 ,  C04B38/0074 ,  B28B1/001 ,  B33Y10/00 ,  C04B2235/3826 ,  C04B2235/422 ,  C04B2235/52

Abstract: A porous ceramic structure intended to form the reinforcement of a ceramic matrix composite component, the structure having a connected porosity delimited by an internal surface which includes a plurality of first points, each first point being associated with a second point aligned with this first point along a normal to the internal surface taken at the first point, the structure being divisible into a plurality of unit volumes of a size less than or equal to 5 mm3 in each of which: a characteristic pore length, corresponding to the maximum of the distance separating each first point from its associated second point, is less than or equal to 0.5 mm; and a porosity ratio is greater than or equal to 50%.

公开(公告)号：US20240327294A1

公开(公告)日：2024-10-03

申请号：US18420051

申请日：2024-01-23

Applicant: UCHICAGO ARGONNE, LLC

Inventor： Dileep Singh ,  Beihai Ma

IPC: C04B35/56 ,  C04B35/626 ,  C04B35/628 ,  C04B35/65 ,  C04B35/657

CPC classification number: C04B35/5618 ,  C04B35/6262 ,  C04B35/62655 ,  C04B35/62675 ,  C04B35/62842 ,  C04B35/65 ,  C04B35/657 ,  C04B2235/3217 ,  C04B2235/3232 ,  C04B2235/3839 ,  C04B2235/402 ,  C04B2235/425 ,  C04B2235/6021 ,  C04B2235/6026 ,  C04B2235/604 ,  C04B2235/616 ,  C04B2235/656 ,  C04B2235/664

Abstract: A method of forming a MAX Phase composite can include forming a precursor powder into a discrete shape to thereby form a green body; heating the green body at a pre-sintering temperature to partially reduce the oxide present in the green body to thereby form a pre-sintered preform; and performing reactive infiltration by heating the pre-sintered preform in the presence of an infiltrating material comprising an A-group element to an infiltration temperature suitable for transforming the infiltrating material to a molten state, wherein the molten infiltrating material reacts with the pre-sintered preform to thereby form the MAX Phase composite

公开(公告)号：US12071380B2

公开(公告)日：2024-08-27

申请号：US17412686

申请日：2021-08-26

Applicant: Rolls-Royce High Temperature Composites Inc.

Inventor： Sungbo Shim ,  Pathikumar Sellappan

IPC: C04B35/80 ,  C04B35/626 ,  C04B35/628 ,  C04B35/657 ,  F01D5/28 ,  F01D25/00

CPC classification number: C04B35/80 ,  C04B35/62655 ,  C04B35/62863 ,  C04B35/62886 ,  C04B35/62894 ,  C04B35/657 ,  F01D5/284 ,  F01D25/005 ,  C04B2235/3418 ,  C04B2235/3826 ,  C04B2235/386 ,  C04B2235/3865 ,  C04B2235/5244 ,  C04B2235/5252 ,  C04B2235/612 ,  C04B2235/616 ,  C04B2235/9669

Abstract: A method to form a machinable ceramic matrix composite comprises forming a porous ceramic multilayer on a surface of a fiber preform. In one example, the porous ceramic multilayer comprises a gradient in porosity in a direction normal to the surface. In another example, the porous ceramic multilayer includes low-wettability particles having a high contact angle with molten silicon, where an amount of the low-wettability particles in the porous ceramic multilayer varies in a direction normal to the surface. After forming the porous ceramic multilayer, the fiber preform is infiltrated with a melt, and the melt is cooled to form a ceramic matrix composite with a surface coating thereon. An outer portion of the surface coating is more readily machinable than an inner portion of the surface coating. The outer portion of the surface coating is machined to form a ceramic matrix composite having a machined surface with a predetermined surface finish and/or dimensional tolerance.

公开(公告)号：US12024473B2

公开(公告)日：2024-07-02

申请号：US17339185

申请日：2021-06-04

Applicant: Raytheon Technologies Corporation

Inventor： Olivier H. Sudre

IPC: C04B35/80 ,  C04B35/628 ,  C04B35/65 ,  C04B35/657 ,  F01D5/28 ,  F01D9/02 ,  F01D11/00 ,  F23R3/00

CPC classification number: C04B35/80 ,  C04B35/62863 ,  C04B35/62884 ,  C04B35/652 ,  C04B35/657 ,  F01D5/284 ,  F01D9/02 ,  F01D11/00 ,  F23R3/002 ,  C04B2235/3826 ,  C04B2235/5244 ,  C04B2235/5252 ,  C04B2235/614 ,  C04B2235/616 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/30 ,  F05D2240/35 ,  F05D2240/55 ,  F05D2300/20

Abstract: A method for making a ceramic matrix composite component includes densifying a fibrous preform of the component with a ceramic matrix to form an intermediate component; infiltrating a hole in the intermediate component with an infiltrate material comprising a solid and a metallic alloy whose reaction forms a carbide, silicide, boride or combination thereof, heating the infiltrate material to a temperature in excess of a melting point of the metallic alloy; and sequentially cooling regions of the hole starting from an interior end of the hole to the outer surface of the intermediate component to form a solidified through-thickness reinforcement element. The hole extends in a through-thickness direction and is open to an exterior surface of the intermediate component.

公开(公告)号：US11873257B2

公开(公告)日：2024-01-16

申请号：US17632660

申请日：2020-07-31

Applicant: SAINT-GOBAIN CENTRE DE RECHERCHES ET D'ETUDES EUROPEEN

Inventor： Jérôme Brulin ,  Jérôme Sant

IPC: C04B35/563 ,  C04B35/565 ,  C04B35/626 ,  C04B35/64 ,  C04B35/657 ,  F41H5/04

CPC classification number: C04B35/563 ,  C04B35/565 ,  C04B35/6264 ,  C04B35/64 ,  C04B35/657 ,  F41H5/0414 ,  C04B2235/3821 ,  C04B2235/3826 ,  C04B2235/428 ,  C04B2235/604 ,  C04B2235/6581 ,  C04B2235/782 ,  C04B2235/786

Abstract: An antiballistic armor-plating component, includes a ceramic body made of a material including, as percentages by volume, between 20% and 75% of boron carbide, between 5% an d 30% of a metallic silicon phase or of a metallic phase including silicon and between 20% and 70% of silicon carbide and wherein, as percentages by volume: more than 60% of the grains with an equivalent diameter greater than 60 micrometers are boron carbide grains, the boron carbide grains with an equivalent diameter greater than 30 micrometers represent more than 20%, the silicon carbide grains with an equivalent diameter greater than or equal to 10 micrometers represent more than 10%, the silicon carbide grains with an equivalent diameter less than 10 micrometers represent more than 10%.

公开(公告)号：US11802089B2

公开(公告)日：2023-10-31

申请号：US17048478

申请日：2019-04-04

Applicant: SAFRAN CERAMICS

Inventor： Aurélia Clerambourg ,  Emilie Mendez ,  Eric Philippe ,  Denis Vicien

IPC: C04B35/565 ,  C04B35/628 ,  C04B35/657 ,  C04B35/80 ,  F01D25/00 ,  C04B35/573 ,  C04B35/584

CPC classification number: C04B35/565 ,  C04B35/573 ,  C04B35/584 ,  C04B35/62834 ,  C04B35/62892 ,  C04B35/657 ,  C04B35/80 ,  F01D25/00 ,  C04B2235/3826 ,  C04B2235/422 ,  C04B2235/428 ,  C04B2235/5244 ,  C04B2235/5256 ,  C04B2235/5436 ,  C04B2235/5445 ,  C04B2235/616 ,  F05D2230/20 ,  F05D2300/6033 ,  F05D2300/614

Abstract: A process for manufacturing a ceramic matrix composite part, includes infiltrating a fibrous structure including a powder composition with a melt infiltration composition including at least silicon in order to form a ceramic matrix in the porosity of the fibrous structure, the powder composition including at least silicon carbide particles, wherein the silicon carbide particles have a bimodal size distribution with a first set of silicon carbide particles having a first average size and a second set of silicon carbide particles having a second average size smaller than the first average size, the number of particles in the first set being greater than the number of particles in the second set.

公开(公告)号：US11634362B2

公开(公告)日：2023-04-25

申请号：US16650636

申请日：2018-10-09

Applicant: SAINT-GOBAIN CENTRE DE RECHERCHES ET D'ETUDES EUROPEEN

Inventor： Isabelle Cabodi ,  Pierrick Vespa ,  Laurent Battu ,  Olivier Citti

IPC: C04B35/48 ,  C04B35/657 ,  C04B35/626

Abstract: A process for the manufacture of a refractory block including more than 80% zirconia, in percentage by weight based on the oxides. The process includes the following successive stages: melting, under reducing conditions, of a charge including more than 50% zircon, in percentage by weight, such as to reduce the zircon and obtain a molten material, application of oxidizing conditions to the molten material, casting of the molten material, and cooling until at least partial solidification of the molten material in the form of a block. Also, the process can include heat treatment of the block.

公开(公告)号：US20220388912A1

公开(公告)日：2022-12-08

申请号：US17339185

申请日：2021-06-04

Applicant: Raytheon Technologies Corporation

Inventor： Olivier H. Sudre

IPC: C04B35/80 ,  F01D5/28 ,  F01D9/02 ,  F01D11/00 ,  F23R3/00 ,  C04B35/628 ,  C04B35/657 ,  C04B35/65

Abstract: A method for making a ceramic matrix composite component includes densifying a fibrous preform of the component with a ceramic matrix to form an intermediate component; infiltrating a hole in the intermediate component with an infiltrate material comprising a solid and a metallic alloy whose reaction forms a carbide, silicide, boride or combination thereof, heating the infiltrate material to a temperature in excess of a melting point of the metallic alloy; and sequentially cooling regions of the hole starting from an interior end of the hole to the outer surface of the intermediate component to form a solidified through-thickness reinforcement element. The hole extends in a through-thickness direction and is open to an exterior surface of the intermediate component.

公开(公告)号：US20220106213A1

公开(公告)日：2022-04-07

申请号：US17429525

申请日：2020-02-11

Applicant: SAINT-GOBAIN CENTRE DE RECHERCHES ET D'ETUDES EUROPEEN

Inventor： Isabelle CABODI ,  Pierrick Fabien VESPA

IPC: C03B5/43 ,  C04B35/48 ,  C04B35/484 ,  C04B35/657

Abstract: Fused cast refractory product including, as weight percentages on the basis of the oxides and for a total of 100%: ZrO2: balance to 100%, Hf2O: