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.

公开(公告)号：US11066942B2

公开(公告)日：2021-07-20

申请号：US16410632

申请日：2019-05-13

Applicant: Rolls-Royce plc

Inventor： Michael J. Whittle ,  Roderick M. Townes ,  Andrew Holt

IPC: B23P15/04 ,  F01D9/04

Abstract: A gas turbine engine includes a compressor, a combustor, and a turbine arranged around an axis. The turbine includes a turbine vane assembly. A method for creating the turbine vane assembly includes fabricating a plurality of turbine vanes comprising ceramic matrix composite material and selecting and arranging the turbine vanes to form a turbine vane assembly.