公开(公告)号：US20250012194A1

公开(公告)日：2025-01-09

申请号：US18746279

申请日：2024-06-18

Applicant: ROLLS-ROYCE plc

Inventor： Christopher NEALE ,  James R. KINGSLEY-ROWE

IPC: F01D5/18

Abstract: A gas turbine engine component that has a web provided with an array of cooling holes distributed with respect to a first direction, wherein the cooling holes have a cross-sectional shape that varies along the first direction. The component may be configured so that the first direction corresponds to a loading distribution of the component which increases along the first direction from a low loading position to a high loading position.

公开(公告)号：US20250027419A1

公开(公告)日：2025-01-23

申请号：US18771137

申请日：2024-07-12

Applicant: ROLLS-ROYCE plc

Inventor： James R. KINGSLEY-ROWE ,  Christopher NEALE ,  Stefan J. WAGNER

IPC: F01D5/28 ,  F01D5/18

Abstract: There is provided a method of manufacturing a component of a gas turbine engine, comprising: providing a precursor component having at least one internal cooling passage configured to receive a flow of cooling air therethrough; estimating a predicted temperature profile for the component based on one or more operating parameters of the gas turbine engine, the predicted temperature profile indicating a predicted operating temperature of at least one gas-washed surface of the component; determining a thermal barrier coating (TBC) configuration for the component based on the predicted temperature profile, comprising setting a TBC thickness to be below a threshold thickness in a region of the at least one gas-washed surface of the component based on the predicted operating temperature of the at least one gas-washed surface of the component exceeding a threshold temperature; and applying a TBC to the precursor component according to the TBC configuration.