公开(公告)号：US11732596B2

公开(公告)日：2023-08-22

申请号：US17560233

申请日：2021-12-22

Applicant: Rolls-Royce plc

Inventor： Daniel Clark ,  Michael J. Whittle ,  Carl Boettcher ,  David C. Wright

IPC: F01D5/14 ,  F01D9/06 ,  F01D5/28

CPC classification number: F01D9/065 ,  F01D5/147 ,  F01D5/282 ,  F01D5/284 ,  F05D2240/12 ,  F05D2300/6033

Abstract: A turbine vane assembly adapted for use in a gas turbine engine includes a plurality of turbine vanes, an outer vane support, and an inner vane support. The plurality of turbine vanes comprise ceramic matrix composite material and are adapted to interact with hot gases flowing through a gas path of the gas turbine engine during use of the turbine vane assembly. A spar system couples the inner vane support with the outer vane support.

公开(公告)号：US10031111B2

公开(公告)日：2018-07-24

申请号：US15346458

申请日：2016-11-08

Applicant: ROLLS-ROYCE plc

Inventor： Daniel Clark ,  David C. Wright

IPC: B24C1/04 ,  G01N29/32 ,  G01N29/04 ,  G01N29/07 ,  G01B17/02 ,  G01N29/22 ,  G01N29/44

Abstract: A method of machining an object, the method comprising: receiving a signal from an ultrasonic transducer; determining at least a first external surface of the object and a second internal surface of the object in the received signal; determining a thickness between the first external surface and the second internal surface of the object, the object comprising a first material between the first external surface and the second internal surface, and a second material between the second internal surface and a third surface, the determination of the thickness using a database including a plurality of materials and a plurality of associated acoustic wave velocities; and controlling machining of the first external surface using the determined thickness.

公开(公告)号：US20230193773A1

公开(公告)日：2023-06-22

申请号：US17560233

申请日：2021-12-22

Applicant: Rolls-Royce plc

Inventor： Daniel Clark ,  Michael J. Whittle ,  Carl Boettcher ,  David C. Wright

IPC: F01D9/06 ,  F01D5/28

CPC classification number: F01D9/065 ,  F01D5/282 ,  F01D5/284 ,  F05D2240/12 ,  F05D2300/6033

Abstract: A turbine vane assembly adapted for use in a gas turbine engine includes a plurality of turbine vanes, an outer vane support, and an inner vane support. The plurality of turbine vanes comprise ceramic matrix composite material and are adapted to interact with hot gases flowing through a gas path of the gas turbine engine during use of the turbine vane assembly. A spar system couples the inner vane support with the outer vane support.