公开(公告)号：US20230193769A1

公开(公告)日：2023-06-22

申请号：US17560202

申请日：2021-12-22

Applicant: Rolls-Royce plc

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

IPC: F01D9/04 ,  F01D25/00

CPC classification number: F01D9/041 ,  F01D25/005 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2240/12 ,  F05D2300/20

Abstract: A turbine vane assembly for use in a gas turbine engine includes turbine vanes, a segmented inner vane support, and an outer vane support. The turbine vanes are arranged around a central axis of the engine. The inner vane support is arranged radially inwardly of the turbine vanes. The outer vane support includes a full-hoop outer support ring located radially outward of the plurality of turbine vanes and extends entirely circumferentially about the central axis. The outer vane support further includes a plurality of discrete support spars coupled to the full-hoop outer support ring and extending radially inward from the full-hoop outer support ring through an interior cavity of a respective turbine vane.

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：US11773735B2

公开(公告)日：2023-10-03

申请号：US17560202

申请日：2021-12-22

Applicant: Rolls-Royce plc

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

IPC: F01D9/04 ,  F01D25/00

CPC classification number: F01D9/041 ,  F01D25/005 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2240/12 ,  F05D2300/20

Abstract: A turbine vane assembly for use in a gas turbine engine includes turbine vanes, a segmented inner vane support, and an outer vane support. The turbine vanes are arranged around a central axis of the engine. The inner vane support is arranged radially inwardly of the turbine vanes. The outer vane support includes a full-hoop outer support ring located radially outward of the plurality of turbine vanes and extends entirely circumferentially about the central axis. The outer vane support further includes a plurality of discrete support spars coupled to the full-hoop outer support ring and extending radially inward from the full-hoop outer support ring through an interior cavity of a respective turbine vane.

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.