公开(公告)号：US20170356307A1

公开(公告)日：2017-12-14

申请号：US15596687

申请日：2017-05-16

Applicant: ROLLS-ROYCE plc

Inventor： Timothy J. SUMMERS ,  David SAVINGS

IPC: F01D25/24 ,  B21D22/02

CPC classification number: F01D25/24 ,  B21D22/022 ,  B21D43/003 ,  B21D53/78 ,  F05D2230/40

Abstract: An assembly for hot forming a component includes first and second location features reversibly attached to a sheet metal element that forms the component. The assembly is loaded into a high temperature forming rig by loosely locating the location features into corresponding datum features in a forming tool. As the assembly heats up, the location features locate accurately with the datum features. Thus, the assembly can be accurately located onto the tool accurately and with minimal opening of the hot forming rig, thereby improving efficiency and safety.

公开(公告)号：US20190001572A1

公开(公告)日：2019-01-03

申请号：US16016753

申请日：2018-06-25

Applicant: ROLLS-ROYCE plc

Inventor： David SAVINGS ,  Ross TREPLETON

IPC: B29C64/30 ,  B29C64/153 ,  B29C33/60 ,  B29C33/44 ,  B22F3/105 ,  B22F3/12 ,  B22F3/15 ,  B29C64/245 ,  B33Y10/00 ,  B33Y30/00

Abstract: A method of manufacturing a component comprising contacting a powder with a tooling comprising a main body and a removable element, applying a manufacturing process to the powder to form the powder into a component, removing the removable element from the tooling to form a recess, and inserting a separation tool into the recess to thereby apply a force to separate the component from the main body of the tooling. A tooling for forming a component from a powder, the tooling comprising a main body and a removable element which is removable from the main body to form a recess for the insertion of a separation tool to apply a force to separate the component from the main body of the tooling.

公开(公告)号：US20190292989A1

公开(公告)日：2019-09-26

申请号：US16284175

申请日：2019-02-25

Applicant: ROLLS-ROYCE plc

Inventor： Lucian INGLEY ,  David SAVINGS ,  William T. DITHERIDGE

IPC: F02C7/24 ,  F02C7/32 ,  F16H57/04

Abstract: A gas turbine engine is provided for an aircraft. The engine includes an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor. The engine further includes core casings surrounding the engine core. The engine further includes one or more engine accessories mounted adjacent to the core casings. The engine further includes a self-supporting heatshield positioned between the one or more engine accessories and the core casings. The heatshield is formed of ceramic matrix composite material.