公开(公告)号：US20200025093A1

公开(公告)日：2020-01-23

申请号：US16284191

申请日：2019-02-25

Applicant: ROLLS-ROYCE plc

Inventor： Lucian INGLEY ,  Emile RAYA

IPC: F02C7/24 ,  F01D25/14

Abstract: A gas turbine engine for an aircraft is provided. 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 a core casings surrounding the engine core. The engine further includes one or more engine accessories mounted adjacent to and vertically beneath the core casings. The engine further includes a heatshield positioned between the one or more engine accessories and the core casings. The heatshield contains one or more ventilation holes for channelling convectively driven flows of ventilation air around the one or more engine accessories on engine shutdown.

公开(公告)号：US20200088100A1

公开(公告)日：2020-03-19

申请号：US16568675

申请日：2019-09-12

Applicant: ROLLS-ROYCE plc

Inventor： Lucian INGLEY ,  Tony L. WIDDOWSON

IPC: F02C7/18 ,  F02C3/13

Abstract: A duct for a gas turbine engine (10), the duct comprising: a first orifice; a second orifice; and a conduit connecting the first orifice and the second orifice, the conduit being formed from a fireproof elastomer.

公开(公告)号：US20200080493A1

公开(公告)日：2020-03-12

申请号：US16540443

申请日：2019-08-14

Applicant: ROLLS-ROYCE plc

Inventor： Lucian INGLEY

IPC: F02C7/28 ,  F16J15/10 ,  F02C7/25

Abstract: An elongate compressible seal is provided for sealing between a first component and a second component, the seal comprising a plurality of elongate members each attached at a first end to an outer surface of the seal for aiding positioning of the seal.

公开(公告)号：US20190323383A1

公开(公告)日：2019-10-24

申请号：US16378931

申请日：2019-04-09

Applicant: ROLLS-ROYCE plc

Inventor： Lucian INGLEY ,  Clare L. BEWICK

IPC: F01D25/26 ,  F02C3/06

Abstract: A gas turbine engine for an aircraft is provided. The gas turbine engine comprises an engine core comprising a compressor, a combustor, a turbine, and a core shaft connecting the turbine to the compressor. The gas turbine engine further comprises a fan located upstream of the engine core, the fan comprising a plurality of fan blades, the fan generating a core airflow which enters the engine core and a bypass airflow which flows through a bypass duct surrounding the engine core. The gas turbine engine further comprises a circumferential row of outer guide vanes located in the bypass duct rearwards of the fan, the outer guide vanes extending radially outwardly from an inner ring which defines a radially inner surface of the bypass duct.

公开(公告)号：US20200141274A1

公开(公告)日：2020-05-07

申请号：US16598369

申请日：2019-10-10

Applicant: ROLLS-ROYCE plc

Inventor： Emile RAYA ,  Lucian INGLEY ,  Zahid M. HUSSAIN

IPC: F01D25/14 ,  F02C7/12 ,  F02C7/32 ,  F02K3/06

Abstract: A gas turbine engine for an aircraft is provided. 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 an aerodynamic cowl which surrounds the core casings. The engine further includes a propulsive fan located upstream of the engine core, the fan generating a core airflow which enters the core engine and a bypass airflow which enters a bypass duct surrounding the aerodynamic cowl. The engine further includes one or more engine accessories mounted in a space between the core casings and the aerodynamic cowl.

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.

公开(公告)号：US20200217247A1

公开(公告)日：2020-07-09

申请号：US16729570

申请日：2019-12-30

Applicant: ROLLS-ROYCE plc

Inventor： Lucian INGLEY

IPC: F02C3/04 ,  F02K3/06 ,  F02C7/00

Abstract: A gas turbine engine comprising: an engine core; an annular flow passage arranged around the engine core; and a bifurcation extending below the engine core and having a length dimension spanning the annular flow passage. The bifurcation comprises a housing that houses a conduit. The conduit has an inlet at an engine core end of the bifurcation and extends along the length of the bifurcation. The conduit comprises a fire-resistant material and is configured to drain fluid from the engine core and through the bifurcation to an outlet.

公开(公告)号：US20200025035A1

公开(公告)日：2020-01-23

申请号：US16378847

申请日：2019-04-09

Applicant: ROLLS-ROYCE plc

Inventor： Richard PEACE ,  Lucian INGLEY

IPC: F01D25/24 ,  F02K1/09 ,  F02K3/06

Abstract: A gas turbine engine for an aircraft is provided. The gas turbine engine comprises an engine core comprising a compressor, a combustor, a turbine, and a core shaft connecting the turbine to the compressor. The gas turbine engine further comprises a fan located upstream of the engine core, the fan comprising a plurality of fan blades, the fan generating a core airflow which enters the engine core and a bypass airflow which flows through a bypass duct surrounding the engine core. The gas turbine engine further comprises a circumferential row of outer guide vanes located in the bypass duct rearwards of the fan, the outer guide vanes extending radially outwardly from an inner ring which defines a radially inner surface of the bypass duct.