公开(公告)号：US10745803B2

公开(公告)日：2020-08-18

申请号：US16003615

申请日：2018-06-08

Applicant: Rolls-Royce High Temperature Composites Inc.

Inventor： Richard W. Kidd ,  Robert Shinavski

IPC: C23C16/34 ,  C04B35/628 ,  C04B35/80 ,  C04B35/565 ,  C23C16/30 ,  D06M11/58 ,  D06M11/80 ,  F01D25/00 ,  D06M101/16

Abstract: A method of forming a moisture-tolerant coating on a silicon carbide fiber includes exposing a silicon carbide fiber to a gaseous N precursor comprising nitrogen at an elevated temperature, thereby introducing nitrogen into a surface region of the silicon carbide fiber, and exposing the silicon carbide fiber to a gaseous B precursor comprising boron at an elevated temperature, thereby introducing boron into the surface region of the silicon carbide fiber. Silicon-doped boron nitride is formed at the surface region of the silicon carbide fiber without exposing the silicon carbide fiber to a gaseous Si precursor comprising Si. Thus, a moisture-tolerant coating comprising the silicon-doped boron nitride is grown in-situ on the silicon carbide fiber.

公开(公告)号：US20180187560A1

公开(公告)日：2018-07-05

申请号：US15896557

申请日：2018-02-14

Applicant: Rolls-Royce High Temperature Composites, Inc. ,  Rolls-Royce Corporation

Inventor： Stephen I. Harris ,  Robert J. Shinavski ,  Richard W. Kidd ,  Sungbo Shim ,  Kang N. Lee

IPC: F01D5/28 ,  C04B35/628 ,  C04B35/80 ,  F01D11/12 ,  C04B41/52 ,  C04B41/89 ,  C04B41/00 ,  C04B35/573 ,  C04B35/565 ,  C04B35/584 ,  C04B35/58 ,  C04B41/45 ,  C04B41/50

CPC classification number: F01D5/284 ,  C04B35/573 ,  C04B35/62863 ,  C04B35/62868 ,  C04B35/62894 ,  C04B35/806 ,  C04B41/009 ,  C04B41/5059 ,  C04B41/5096 ,  C04B41/52 ,  C04B41/89 ,  C04B2235/3826 ,  C04B2235/5276 ,  C04B2235/614 ,  C04B2235/616 ,  F01D5/282 ,  F01D5/288 ,  F01D11/122 ,  F05D2240/11 ,  F05D2300/222 ,  F05D2300/2261 ,  F05D2300/6032 ,  F05D2300/6033 ,  C04B35/565 ,  C04B35/584 ,  C04B35/58092 ,  C04B41/4529 ,  C04B41/4556 ,  C04B41/4527 ,  C04B41/5024 ,  C04B41/4582

Abstract: A ceramic matrix composite component for use in a gas turbine engine and method for making the same are described herein. The component includes a body and an outer region. The body includes a silicon containing ceramic composite. The outer region is on an outer surface of the body.

公开(公告)号：US20180363132A1

公开(公告)日：2018-12-20

申请号：US16003615

申请日：2018-06-08

Applicant: Rolls-Royce High Temperature Composites Inc.

Inventor： Richard W. Kidd ,  Robert Shinavski

IPC: C23C16/34 ,  C23C16/30 ,  D06M11/58 ,  D06M11/80 ,  F01D25/00

CPC classification number: C23C16/342 ,  C04B35/565 ,  C04B35/62863 ,  C04B35/62868 ,  C04B35/62884 ,  C04B35/62894 ,  C04B35/62897 ,  C04B35/806 ,  C04B2235/3826 ,  C04B2235/46 ,  C04B2235/465 ,  C04B2235/524 ,  C04B2235/5244 ,  C04B2235/616 ,  C23C16/308 ,  D06M11/58 ,  D06M11/80 ,  D06M2101/16 ,  F01D25/005 ,  F05D2300/6033

Abstract: A method of forming a moisture-tolerant coating on a silicon carbide fiber includes exposing a silicon carbide fiber to a gaseous N precursor comprising nitrogen at an elevated temperature, thereby introducing nitrogen into a surface region of the silicon carbide fiber, and exposing the silicon carbide fiber to a gaseous B precursor comprising boron at an elevated temperature, thereby introducing boron into the surface region of the silicon carbide fiber. Silicon-doped boron nitride is formed at the surface region of the silicon carbide fiber without exposing the silicon carbide fiber to a gaseous Si precursor comprising Si. Thus, a moisture-tolerant coating comprising the silicon-doped boron nitride is grown in-situ on the silicon carbide fiber.

公开(公告)号：US20160230570A1

公开(公告)日：2016-08-11

申请号：US15040527

申请日：2016-02-10

Applicant: Rolls-Royce High Temperature Composites Inc. ,  Rolls-Royce Corporation

Inventor： Stephen L. Harris ,  Robert J. Shinavski ,  Richard W. Kidd ,  Sungbo Shim ,  Kang N. Lee

IPC: F01D5/28 ,  C04B35/80

CPC classification number: F01D5/284 ,  C04B35/573 ,  C04B35/62863 ,  C04B35/62868 ,  C04B35/62894 ,  C04B35/806 ,  C04B41/009 ,  C04B41/5059 ,  C04B41/5096 ,  C04B41/52 ,  C04B41/89 ,  C04B2235/3826 ,  C04B2235/5276 ,  C04B2235/614 ,  C04B2235/616 ,  F01D5/282 ,  F01D5/288 ,  F01D11/122 ,  F05D2240/11 ,  F05D2300/222 ,  F05D2300/2261 ,  F05D2300/6032 ,  F05D2300/6033 ,  C04B35/565 ,  C04B35/584 ,  C04B35/58092 ,  C04B41/4529 ,  C04B41/4556 ,  C04B41/4527 ,  C04B41/5024 ,  C04B41/4582

Abstract: A ceramic matrix composite component for use in a gas turbine engine and method for making the same are described herein. The component comprising a body and an outer region. The body having a silicon containing ceramic composite. The outer region on an outer surface of the body.

Abstract translation: 这里描述了一种用于燃气涡轮发动机的陶瓷基复合材料组件及其制造方法。 所述部件包括主体和外部区域。 本体具有含硅陶瓷复合材料。 身体外表面上的外部区域。

公开(公告)号：US20190169740A1

公开(公告)日：2019-06-06

申请号：US16268761

申请日：2019-02-06

Applicant: Rolls-Royce Corporation ,  Rolls-Royce High Temperature Composites, Inc.

Inventor： Chong M. Cha ,  David Liliedahl ,  Richard W. Kidd ,  Ross Galligher ,  Nicholas Doan

IPC: C23C16/04 ,  C23C16/455 ,  C23C16/458 ,  C23C16/46 ,  F01D5/28 ,  C23C16/44 ,  C23C16/24 ,  C23C16/52

Abstract: A system may include a reactor vessel comprising an outer wall, a heat source thermally coupled to the reactor vessel, at least one reactor inlet in the outer wall, and at least one reactor outlet. The reactor vessel may be configured to house a porous preform in a radially central core region. The at least one reactor inlet may be configured to introduce a precursor gas to the reactor vessel to produce swirling flow of the precursor gas around the radially central core region of the reactor vessel. The at least one reactor outlet may be configured to remove exhaust gas from the reactor vessel and assist in maintaining a dynamic pressure of the reactor vessel greater than a pressure in the porous preform.

公开(公告)号：US11008652B2

公开(公告)日：2021-05-18

申请号：US16268761

申请日：2019-02-06

Applicant: Rolls-Royce Corporation ,  Rolls-Royce High Temperature Composites, Inc.

Inventor： Chong M. Cha ,  David Liliedahl ,  Richard W. Kidd ,  Ross Galligher ,  Nicholas Doan

IPC: C23C16/04 ,  C23C16/24 ,  C23C16/455 ,  C23C16/458 ,  F01D5/28 ,  C23C16/44 ,  C23C16/46 ,  C23C16/52

Abstract: A system may include a reactor vessel comprising an outer wall, a heat source thermally coupled to the reactor vessel, at least one reactor inlet in the outer wall, and at least one reactor outlet. The reactor vessel may be configured to house a porous preform in a radially central core region. The at least one reactor inlet may be configured to introduce a precursor gas to the reactor vessel to produce swirling flow of the precursor gas around the radially central core region of the reactor vessel. The at least one reactor outlet may be configured to remove exhaust gas from the reactor vessel and assist in maintaining a dynamic pressure of the reactor vessel greater than a pressure in the porous preform.

公开(公告)号：US10683764B2

公开(公告)日：2020-06-16

申请号：US15896557

申请日：2018-02-14

Applicant: Rolls-Royce High Temperature Composites, Inc. ,  Rolls-Royce Corporation

Inventor： Stephen I. Harris ,  Robert J. Shinavski ,  Richard W. Kidd ,  Sungbo Shim ,  Kang N. Lee

IPC: F01D5/28 ,  C04B35/80 ,  F01D11/12 ,  C04B35/628 ,  C04B41/89 ,  C04B41/00 ,  C04B41/52 ,  C04B35/573 ,  C04B41/50

Abstract: A ceramic matrix composite component for use in a gas turbine engine and method for making the same are described herein. The component includes a body and an outer region. The body includes a silicon containing ceramic composite. The outer region is on an outer surface of the body.