公开(公告)号：US11964921B2

公开(公告)日：2024-04-23

申请号：US17613426

申请日：2020-05-19

Applicant: Oerlikon Surface Solutions AG, Pfäffikon

Inventor： Werner Stamm ,  Simone Friedle ,  Juergen Ramm

IPC: C04B41/45 ,  C04B35/185 ,  C04B41/00 ,  C04B41/50 ,  C04B41/53 ,  C04B41/87 ,  C04B41/91 ,  C23C14/00 ,  C23C14/02 ,  C23C14/08 ,  C23C14/32 ,  C23C14/34 ,  C23C14/58 ,  F02C7/00

CPC classification number: C04B41/4529 ,  C04B35/185 ,  C04B41/0054 ,  C04B41/4558 ,  C04B41/5031 ,  C04B41/5346 ,  C04B41/87 ,  C04B41/91 ,  C23C14/0021 ,  C23C14/021 ,  C23C14/081 ,  C23C14/325 ,  C23C14/34 ,  C23C14/5853 ,  F02C7/00 ,  C04B2235/3463 ,  F05D2220/32 ,  F05D2230/31 ,  F05D2230/90 ,  F05D2300/2112

Abstract: A method for applying a coating 1 to a surface 2 of a mullite material 3 is specified, which comprises pretreating the surface 2 of the mullite material 3 by means of a plasma-chemical process in which molecular hydrogen is excited in such a way that plasma-activated hydrogen is produced S1, and applying an aluminum oxide-containing layer 4 by means of a PVD process to the pretreated surface 2 of the mullite material 3 S2. Furthermore, a mullite material 3 with a coating and a gas turbine component with such a mullite material 3 are specified.

公开(公告)号：US20230407935A1

公开(公告)日：2023-12-21

申请号：US17845801

申请日：2022-06-21

Applicant: Goodrich Corporation

Inventor： JAMES W. RUDOLPH ,  ATTA KHAN

IPC: F16D65/12 ,  C04B41/85 ,  C04B41/45 ,  C04B35/56 ,  C04B35/52

CPC classification number: F16D65/126 ,  C04B41/85 ,  C04B41/4529 ,  C04B35/5603 ,  C04B35/52 ,  C04B2235/3817 ,  C04B2235/422 ,  F16D2200/0047 ,  F16D2200/0069 ,  F16D2200/0052 ,  F16D2200/0082 ,  B64C25/44

Abstract: A method of manufacturing a carbon structure can comprise: infiltrating the carbon structure with a silicon oxycarbide (SiOC) precursor sol; and densifying the carbon structure by chemical vapor infiltration (CVI) to form a carbon and ceramic matrix composite material, the carbon and ceramic matrix composite material comprising between 0% and 15% by weight of a plurality of ceramic particles from the ceramic compound, densifying the carbon structure including adjusting a temperature gradient across the carbon structure.

公开(公告)号：US20230406782A1

公开(公告)日：2023-12-21

申请号：US17845832

申请日：2022-06-21

Applicant: GOODRICH CORPORATION

Inventor： ATTA KHAN

IPC: C04B41/45 ,  C04B35/56 ,  C04B35/52

CPC classification number: C04B41/4529 ,  C04B35/5603 ,  C04B35/52

Abstract: A method of making a carbon-carbon composite may comprise forming a silicon oxycarbide (SiOC) precursor sol and infiltrating a fibrous preform with the SiOC precursor sol. A SiOC forming heating treatment may be performed on the fibrous preform to form SiOC particles. The fibrous preform may be densified using chemical vapor infiltration to form a densified fibrous preform.

公开(公告)号：US20230399268A1

公开(公告)日：2023-12-14

申请号：US17799739

申请日：2021-02-10

Applicant: SAFRAN CERAMICS

Inventor： Stéphane Roger André GOUJARD ,  Adrien DELCAMP ,  Cédric DESCAMPS ,  Thierry Guy Xavier TESSON ,  Charles LELEU

IPC: C04B41/45 ,  B28B11/08

CPC classification number: C04B41/457 ,  C04B41/4529 ,  B28B11/08 ,  C04B2235/614

Abstract: A method of consolidation includes placing a fibrous preform in the shaping recess of a shaping tool, and supplying the shaping tool with a gas phase to obtain a deposit in the fibrous preform, the shaping tool for the vapor phase chemical infiltration including first and second portions, having respectively first and second shaping zones surrounded by a first and second edge zones, the first and the second shaping zone defining a shaping recess to receive the fibrous preform. A gas injection port is present at least partially in the first or second edge zone and a gas outlet port is present at least partially in the first or second edge zone, the gas injection port and the gas outlet port placing the shaping recess in fluid communication with the outside of the shaping tool. Outer faces of the first and second portion are impermeable to gas.

公开(公告)号：US20180334410A1

公开(公告)日：2018-11-22

申请号：US15985736

申请日：2018-05-22

Applicant: CENTRAL SOUTH UNIVERSITY

Inventor： Yi ZENG ,  Xiang XIONG ,  Dini WANG ,  Wei SUN ,  Zhaoke CHEN ,  Yalei WANG

IPC: C04B35/83 ,  C04B41/87 ,  C04B41/45

CPC classification number: C04B35/83 ,  C04B35/52 ,  C04B35/5611 ,  C04B35/5622 ,  C04B35/806 ,  C04B41/009 ,  C04B41/4529 ,  C04B41/5057 ,  C04B41/87 ,  C04B2235/3232 ,  C04B2235/3821 ,  C04B2235/3826 ,  C04B2235/3839 ,  C04B2235/3843 ,  C04B2235/44 ,  C04B2235/5248 ,  C04B2235/608 ,  C04B2235/614 ,  C04B2235/616 ,  C04B2235/79 ,  C04B2235/80 ,  C04B41/4523 ,  C04B41/4556 ,  C04B41/507

Abstract: A method for preparing a ceramic-modified carbon-carbon composite material. The method includes preparing and thermally treating a carbon fiber preform, and depositing pyrolytic carbon on the carbon fiber preform in a chemical vapor infiltration furnace, to yield a porous carbon-carbon composite material; placing the carbon-carbon composite material deposited with the pyrolytic carbon on a zirconium-titanium powder mixture, and performing a reactive melt infiltration, to yield a carbon-carbon composite material modified by non-stoichiometric zirconium titanium carbide; and placing the carbon-carbon composite material modified by non-stoichiometric zirconium titanium carbide in a powder mixture including carbon, boron carbide, silicon carbide, silicon, and an infiltration enhancer, and performing an embedding method, to form a ceramic-modified carbon-carbon composite material.

公开(公告)号：US09884790B2

公开(公告)日：2018-02-06

申请号：US14784104

申请日：2014-11-25

Applicant: Sumitomo Electric Hardmetal Corp.

Inventor： Nozomi Tsukihara ,  Makoto Setoyama ,  Katsumi Okamura

IPC: C04B41/87 ,  C04B35/5831 ,  C04B41/52 ,  C23C30/00 ,  C04B35/58 ,  C04B35/581 ,  C04B35/645 ,  C04B41/89 ,  C04B41/00 ,  C04B41/50 ,  C01B21/064

CPC classification number: C04B41/87 ,  C01B21/0648 ,  C01P2004/61 ,  C04B35/58014 ,  C04B35/581 ,  C04B35/5831 ,  C04B35/645 ,  C04B41/009 ,  C04B41/5062 ,  C04B41/5068 ,  C04B41/52 ,  C04B41/89 ,  C04B2235/3856 ,  C04B2235/386 ,  C04B2235/3865 ,  C04B2235/3886 ,  C04B2235/5436 ,  C04B2235/5445 ,  C23C30/005 ,  C04B41/4529 ,  C04B41/455 ,  C04B41/5063 ,  C04B41/5066 ,  C04B41/5061

Abstract: A cutting tool includes a base material and a coating formed on the base material. The base material is a sintered body containing 30 to 80% by volume of cubic boron nitride, and a binder. The surface in contact with the coating, of the base material, has a plurality of convex portions made of the cubic boron nitride and a plurality of concave portions made of the binder. A surface roughness Rsub of the surface in contact with the base material, is 0.1 to 0.4 μm. A surface roughness Rsurf of an outermost surface of the coating is 0 to 0.15 μm. A surface roughness Rasurf of the outermost surface of the coating is 0 to 0.1 μm. The surface roughness Rsub of the surface in contact with the coating, of the base material, is greater than the surface roughness Rsurf of the outermost surface of the coating.

公开(公告)号：US20170278601A1

公开(公告)日：2017-09-28

申请号：US15468630

申请日：2017-03-24

Applicant: NGK INSULATORS, LTD.

Inventor： Masaki ISHIKAWA ,  Toru HAYASE ,  Yoshimasa KOBAYASHI ,  Kenji MORIMOTO

IPC: H01C7/18 ,  H01C17/30

CPC classification number: H01C7/18 ,  C04B35/453 ,  C04B41/009 ,  C04B41/52 ,  C04B41/89 ,  C04B2111/00844 ,  C04B2235/3213 ,  C04B2235/3217 ,  C04B2235/3224 ,  C04B2235/3275 ,  C04B2235/3286 ,  C04B2235/3298 ,  C04B2235/5436 ,  C04B2235/5454 ,  C04B2235/6567 ,  C04B2235/658 ,  C04B2235/6583 ,  C04B2235/663 ,  C04B2235/75 ,  C04B2235/96 ,  C23C14/086 ,  C23C14/34 ,  H01C7/102 ,  H01C7/112 ,  H01C17/30 ,  C04B41/4556 ,  C04B41/5049 ,  C04B41/4529 ,  C04B41/5027

Abstract: A voltage-nonlinear resistor element 10 includes a voltage-nonlinear resistor (referred simply as “resistor”) 20 and a pair of electrodes 14 and 16 between which the resistor 20 is interposed. The resistor 20 has a multilayer structure including a first layer 21 composed primarily of zinc oxide, a second layer 22 composed primarily of zinc oxide, and a third layer 23 composed primarily of a metal oxide other than zinc oxide. The second layer 22 is adjacent to the first layer 21 and has a smaller thickness and a higher volume resistivity than the first layer 21. The third layer 23 is adjacent to the second layer 22.

公开(公告)号：US09764992B2

公开(公告)日：2017-09-19

申请号：US14652210

申请日：2014-01-28

Applicant: TOYO TANSO CO., LTD.

Inventor： Masato Shinohara

IPC: C04B41/89 ,  C04B35/52 ,  C04B41/50 ,  C30B29/36 ,  C04B41/52 ,  C30B35/00 ,  H01L21/687 ,  C23C16/458 ,  H01L21/683 ,  C04B41/00 ,  C04B41/45 ,  C04B41/53

CPC classification number: C04B41/89 ,  C04B35/522 ,  C04B41/00 ,  C04B41/009 ,  C04B41/4529 ,  C04B41/5059 ,  C04B41/5061 ,  C04B41/52 ,  C04B41/53 ,  C23C16/4581 ,  C30B29/36 ,  C30B35/00 ,  H01L21/683 ,  H01L21/68757 ,  Y10T428/24612 ,  Y10T428/265 ,  Y10T428/30 ,  C04B41/4531 ,  C04B41/4519 ,  C04B41/5001 ,  C04B41/5346 ,  C04B41/455 ,  C04B41/5057

Abstract: Provided is a silicon carbide-tantalum carbide composite having excellent durability. A silicon carbide-tantalum carbide composite (1) includes: a body (10) whose surface layer is at least partly formed of a first silicon carbide layer (12); a tantalum carbide layer (20); and a second silicon carbide layer (13). The tantalum carbide layer (20) is disposed over the first silicon carbide layer (12). The second silicon carbide layer (13) is interposed between the tantalum carbide layer (20) and the first silicon carbide layer (12). The second silicon carbide layer (13) has a C/Si composition ratio of not less than 1.2 as measured by X-ray photoelectron spectroscopy. The second silicon carbide layer (13) has a peak intensity ratio G/D of not less than 1.0 between the G-band and D-band of carbon as measured by Raman spectroscopy.

公开(公告)号：US09725799B2

公开(公告)日：2017-08-08

申请号：US14562339

申请日：2014-12-05

Applicant: Applied Materials, Inc.

Inventor： Jennifer Y. Sun ,  Vahid Firouzdor ,  Biraja Prasad Kanungo ,  Tom K. Cho ,  Vedapuram S. Achutharaman ,  Ying Zhang

IPC: C23C14/34 ,  C23C14/08 ,  C04B41/50 ,  C23C14/46 ,  C23C14/58 ,  H01J37/32 ,  C04B41/87 ,  C04B41/89 ,  C04B41/00 ,  C04B41/52 ,  C04B35/505 ,  C04B35/622

CPC classification number: C23C14/088 ,  C04B35/00 ,  C04B35/505 ,  C04B35/62222 ,  C04B41/009 ,  C04B41/4529 ,  C04B41/5045 ,  C04B41/52 ,  C04B41/87 ,  C04B41/89 ,  C04B2235/3217 ,  C04B2235/3222 ,  C04B2235/3225 ,  C04B2235/3246 ,  C04B2235/3418 ,  C04B2235/3826 ,  C04B2235/3873 ,  C04B2235/428 ,  C04B2235/445 ,  C23C14/08 ,  C23C14/083 ,  C23C14/46 ,  C23C14/5806 ,  H01J37/32477 ,  Y10T428/26 ,  Y10T428/265 ,  C04B35/10 ,  C04B35/50 ,  C04B35/14 ,  C04B35/584 ,  C04B35/565 ,  C04B41/5032 ,  C04B41/5042 ,  C04B41/5035 ,  C04B2103/54

Abstract: A method of manufacturing an article includes providing a component for an etch reactor. Ion beam sputtering with ion assisted deposition (IBS-IAD) is then performed to deposit a protective layer on at least one surface of the component, wherein the protective layer is a plasma resistant film having a thickness of less than 1000 μm.

公开(公告)号：US09719420B2

公开(公告)日：2017-08-01

申请号：US14292969

申请日：2014-06-02

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Paul Stephen DiMascio ,  Victor John Morgan ,  Jason Robert Parolini ,  Glenn Curtis Taxacher ,  Frederic Woodrow Roberts, Jr. ,  Jacob John Kittleson ,  John McConnell Delvaux

IPC: F02C7/00 ,  B23K1/00 ,  B23P6/00 ,  B24B33/00 ,  C04B41/00 ,  C04B41/45 ,  C04B41/50 ,  C04B41/53 ,  C04B41/85 ,  C04B41/91 ,  C04B41/87 ,  C04B41/88 ,  C04B41/51 ,  C23C16/24

CPC classification number: F02C7/00 ,  B23K1/0018 ,  B23P6/002 ,  B23P6/007 ,  B24B33/00 ,  C04B41/009 ,  C04B41/4531 ,  C04B41/5025 ,  C04B41/5096 ,  C04B41/5144 ,  C04B41/53 ,  C04B41/85 ,  C04B41/87 ,  C04B41/88 ,  C04B41/91 ,  C23C16/24 ,  F05D2230/30 ,  F05D2230/90 ,  F05D2300/6033 ,  Y10T156/10 ,  Y10T428/24355 ,  C04B35/00 ,  C04B35/80 ,  C04B41/4529 ,  C04B41/4539 ,  C04B41/5133 ,  C04B41/0072

Abstract: A process of producing a ceramic matrix composite gas turbine component and a ceramic matrix composite gas turbine component are provided. The process includes modifying a surface of the ceramic matrix composite gas turbine component to produce a modified surface with a surface roughness of less than 6 micrometers. The modifying is selected from the group of techniques consisting of applying unreinforced matrix plies to the surface, vapor depositing silicon on the surface, honing the surface, applying braze paste to the surface, and combinations thereof. The component includes a modified surface including a surface roughness of less than 6 micrometers. The modified surface being selected from the group consisting of unreinforced matrix plies applied to a surface of the ceramic matrix composite gas turbine component, silicon vapor deposited on the surface, a honed surface, a braze paste applied to the surface, and combinations thereof.