公开(公告)号：US20170175571A1

公开(公告)日：2017-06-22

申请号：US15380134

申请日：2016-12-15

Applicant: ROLLS-ROYCE plc

Inventor： Phillip J. DOORBAR ,  Gareth FRIEND ,  Kenneth F. UDALL

IPC: F01D25/00 ,  B21D11/20 ,  F01D9/02 ,  F01D25/28 ,  B23K20/02 ,  B23K20/22

CPC classification number: F01D25/005 ,  B21D11/203 ,  B22F3/15 ,  B22F5/008 ,  B22F5/106 ,  B22F7/06 ,  B22F7/062 ,  B22F2998/10 ,  B22F2999/00 ,  B23K20/023 ,  B23K20/22 ,  B23K2101/001 ,  B23K2103/166 ,  C22C32/00 ,  C22C32/0031 ,  C22C47/20 ,  C22C49/11 ,  F01D9/02 ,  F01D25/28 ,  F05D2220/32 ,  F05D2230/232 ,  F05D2230/42 ,  F05D2300/6032 ,  F16C7/02

Abstract: Method of manufacturing a metal matrix composite component includes the steps of providing a first tubular member having a first end and an opposite second end, the first tubular member's first end being formed as a first end block; positioning a metal matrix composite tubular member concentrically the first tubular member; positioning a second tubular member concentrically over metal matrix composite tubular member, second tubular member having a first end and an opposite second end, the second tubular member's second end being formed as a second end block; welding first tubular member's first end to the second tubular member's first end, and the first tubular member's second end to second tubular member's second end, to join the first and second tubular member and thereby to form a metal matrix composite preform; and consolidating metal matrix composite preform by a hot isostatic pressing process to form the metal matrix composite component.

公开(公告)号：US20200240289A1

公开(公告)日：2020-07-30

申请号：US16750134

申请日：2020-01-23

Applicant: ROLLS-ROYCE plc

Inventor： Neelambaran KARAPURATH ,  Gareth FRIEND

IPC: F01D25/02 ,  F02C7/00

Abstract: A de-icing system for one or more vanes of a gas turbine engine. The system comprises a vane comprising an electrically and thermally conductive material and a plurality of magnets located circumferentially about a rotating shaft and configured to be driven by the shaft in the circumferential direction to generate a rotating magnetic field. The vane has a composite structure that includes a core laminate layer of the thermally conductive material located between two laminate layers of titanium, stainless steel or an alloy thereof. A portion of the thermally conductive material is located within the rotating magnetic field such that the conductive material directly heated by electromagnetic induction.

公开(公告)号：US20200239146A1

公开(公告)日：2020-07-30

申请号：US16750154

申请日：2020-01-23

Applicant: ROLLS-ROYCE plc

Inventor： Gareth FRIEND ,  Neelambaran KARAPURATH

IPC: B64D15/12 ,  H05B3/10 ,  F02C7/047

Abstract: A de-icing system for one or more vanes of a gas turbine engine. The system comprises a coating of electrically conductive material on at least a portion of a vane and a plurality of magnets located circumferentially about a rotor shaft of the gas turbine engine and configured to be driven by the rotor shaft in the circumferential direction to generate a rotating magnetic field. A coiled wire is configured to remain stationary within the rotating magnetic field so as to induce a current therein, the coiled wire being connected to the coating for supplying the induced current to the electrically conductive material. In this way, the coating of electrically conductive material is heated by the induced current, for inhibiting ice accretion on the vane.