公开(公告)号：US12146224B2

公开(公告)日：2024-11-19

申请号：US17899074

申请日：2022-08-30

Applicant: Raytheon Technologies Corporation

Inventor： Xia Tang ,  David C. Jarmon ,  James T. Beals ,  R. Wesley Jackson ,  Paul Sheedy

IPC: C23C4/10 ,  C04B41/00 ,  C04B41/52 ,  C04B41/89 ,  C23C4/11 ,  C23C4/12 ,  C23C4/129 ,  C23C4/134 ,  C23C24/08 ,  C23C28/04 ,  F01D5/28 ,  F01D25/00

Abstract: A coated article including an article having a surface; an oxidation resistant bond coat layer deposited on the surface, the oxidation resistant bond coat layer comprising a healing silica matrix and at least one oxygen scavenger forming a metal silicide network dispersed within the healing silica matrix; and a top coat layer disposed upon the oxidation resistant bond coat layer, whereby the oxidation resistant bond coat layer is operable to seal a crack in the top coat layer.

公开(公告)号：US20240116828A1

公开(公告)日：2024-04-11

申请号：US17961996

申请日：2022-10-07

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： David C. Jarmon

IPC: C04B41/45 ,  C04B35/80 ,  C04B41/00

CPC classification number: C04B41/4531 ,  C04B35/80 ,  C04B41/0072 ,  C04B41/4511 ,  C04B2235/614

Abstract: A method of making a ceramic matrix composite article includes fabricating a preform comprising a plurality of fibers arranged in an arrangement, wherein there are spaces between adjacent ones of the fibers; providing particles to the preform, whereby the particles are situated in the spaces; and applying a matrix material to the preform by atomic layer deposition to make a ceramic matrix composite article. A ceramic matrix composite article is also disclosed.

公开(公告)号：US20220411912A1

公开(公告)日：2022-12-29

申请号：US17899074

申请日：2022-08-30

Applicant: Raytheon Technologies Corporation

Inventor： Xia Tang ,  David C. Jarmon ,  James T. Beals ,  R. Wesley Jackson ,  Paul Sheedy

IPC: C23C4/10 ,  C04B41/52 ,  C04B41/89 ,  C23C24/08 ,  F01D5/28 ,  C23C28/04 ,  C23C4/11 ,  C04B41/00 ,  C23C4/129 ,  C23C4/134 ,  C23C4/12

Abstract: A coated article including an article having a surface; an oxidation resistant bond coat layer deposited on the surface, the oxidation resistant bond coat layer comprising a healing silica matrix and at least one oxygen scavenger forming a metal silicide network dispersed within the healing silica matrix; and a top coat layer disposed upon the oxidation resistant bond coat layer, whereby the oxidation resistant bond coat layer is operable to seal a crack in the top coat layer.

公开(公告)号：US20220411334A1

公开(公告)日：2022-12-29

申请号：US17861722

申请日：2022-07-11

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： David C. Jarmon

IPC: C04B35/01 ,  B28B23/00 ,  B29C70/02 ,  F02C7/20 ,  F01D5/00 ,  F01D25/24 ,  F01D25/00 ,  C04B37/00 ,  C04B35/571 ,  F23R3/00 ,  C04B35/565 ,  F23R3/60 ,  F01D9/00 ,  F01D25/30 ,  C04B35/83 ,  F23R3/28 ,  F01D11/00 ,  F02K1/82 ,  C04B35/80

Abstract: A method of forming an integral fastener for a ceramic matrix composite component comprises the steps of forming a fiber preform with an opening, forming a fiber fastener, inserting the fiber fastener into the opening, and infiltrating a matrix material into the fiber preform and fiber fastener to form a ceramic matrix composite component with an integral fastener. A gas turbine engine is also disclosed.

公开(公告)号：US20220316706A1

公开(公告)日：2022-10-06

申请号：US17846386

申请日：2022-06-22

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Michael R. Kracum ,  David C. Jarmon

IPC: F23R3/00 ,  C04B35/626 ,  C04B35/80 ,  C04B38/06 ,  F02C7/18

Abstract: A method of making an ceramic article according to an exemplary embodiment of this disclosure, among other possible things includes arranging fiber plies into a preform, inserting one or more sacrificial springs to the preform, infiltrating the preform with a matrix material to form an article, and thermally degrading the one or more sacrificial springs to form cooling holes. A ceramic article and a gas turbine engine component are also disclosed.

公开(公告)号：US20220324761A1

公开(公告)日：2022-10-13

申请号：US17850430

申请日：2022-06-27

Applicant: Raytheon Technologies Corporation

Inventor： David C. Jarmon

IPC: C04B35/80 ,  C04B35/565 ,  C04B35/571 ,  C04B35/573 ,  C04B35/634 ,  C04B35/638 ,  C04B35/83 ,  C04B37/00 ,  F01D11/00 ,  F01D25/24 ,  F23R3/00 ,  F23R3/28 ,  F23R3/60 ,  F01D5/00 ,  F01D9/00 ,  F01D25/00 ,  F01D25/30 ,  F02K1/82 ,  C04B35/01 ,  B28B1/00 ,  B28B11/12 ,  C04B35/622 ,  C04B35/64 ,  C04B35/76 ,  D03D25/00 ,  F01D25/28 ,  F02C7/28

Abstract: A gas turbine engine component includes a gas turbine engine component body formed of a ceramic matrix composite material having at least one fastener integrally formed with the gas turbine engine component body as a single-piece structure. The gas turbine engine component body initially comprises a rigidized preform structure formed from a polymer based material. The at least one fastener connects the gas turbine engine component body to an engine support structure.