公开(公告)号：US11504813B2

公开(公告)日：2022-11-22

申请号：US16876834

申请日：2020-05-18

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

Inventor： Michael J. Whittle ,  Stephen Harris ,  Keith Sadler ,  Matthew D. Thomason ,  Andrew Norton ,  James Kell

IPC: B23P6/00 ,  F01D5/00 ,  F01D5/28 ,  G01M15/14

Abstract: A method comprises inspecting a ceramic matrix composite component assembled in a gas turbine engine to determine an extent of damage to the ceramic matrix composite component, determining a repair technique to repair the damage to the ceramic matrix composite component based on the extent of damage to the ceramic matrix composite component, and repairing the ceramic matrix composite component using the repair technique.

公开(公告)号：US20210354253A1

公开(公告)日：2021-11-18

申请号：US16876834

申请日：2020-05-18

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

Inventor： Michael J. Whittle ,  Stephen Harris ,  Keith Sadler ,  Matthew D. Thomason ,  Andrew Norton ,  James Kell

IPC: B23P6/00 ,  G01M15/14 ,  F01D5/00 ,  F01D5/28

Abstract: A method comprises inspecting a ceramic matrix composite component assembled in a gas turbine engine to determine an extent of damage to the ceramic matrix composite component, determining a repair technique to repair the damage to the ceramic matrix composite component based on the extent of damage to the ceramic matrix composite component, and repairing the ceramic matrix composite component using the repair technique.

公开(公告)号：US11415007B2

公开(公告)日：2022-08-16

申请号：US16752183

申请日：2020-01-24

Applicant: Rolls-Royce plc

Inventor： Michael J. Whittle ,  Keith Sadler ,  Matthew D. Thomason ,  Andrew Holt

IPC: F01D9/04 ,  F01D5/28 ,  F01D11/08 ,  F01D25/24 ,  F01D25/12

Abstract: A gas turbine engine includes a shroud ring, a vane ring, and a secondary flow assembly. The shroud ring extends around an associated turbine wheel and includes a carrier segment and a blade track segment comprising ceramic matrix composite materials. The blade track segment and the carrier segment defining a shroud cavity radially therebetween. The vane ring includes a heat shield comprising ceramic matrix composite materials that forms an outer platform, an inner platform, and an airfoil defining a heat shield cavity radially through the heat shield. The secondary flow assembly includes a recirculating flow circuit having a discharge tube and a vane pressurizing tube; and the secondary flow assembly is configured to cool the blade track segment. The flow circuit is further configured to pressurize the heat shield cavity thereby providing a seal against the gases from the primary gas path entering the heat shield cavity.

公开(公告)号：US20210231022A1

公开(公告)日：2021-07-29

申请号：US16752183

申请日：2020-01-24

Applicant: Rolls-Royce plc

Inventor： Michael J. Whittle ,  Keith Sadler ,  Matthew D. Thomason ,  Andrew Holt

IPC: F01D9/04 ,  F01D5/28

Abstract: A gas turbine engine includes a shroud ring, a vane ring, and a secondary flow assembly. The shroud ring extends around an associated turbine wheel and includes a carrier segment and a blade track segment comprising ceramic matrix composite materials. The blade track segment and the carrier segment defining a shroud cavity radially therebetween. The vane ring includes a heat shield comprising ceramic matrix composite materials that forms an outer platform, an inner platform, and an airfoil defining a heat shield cavity radially through the heat shield. The secondary flow assembly includes a recirculating flow circuit having a discharge tube and a vane pressurizing tube; and the secondary flow assembly is configured to cool the blade track segment. The flow circuit is further configured to pressurize the heat shield cavity thereby providing a seal against the gases from the primary gas path entering the heat shield cavity.