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公开(公告)号：US20190120138A1
公开(公告)日：2019-04-25
申请号：US16134062
申请日：2018-09-18
Applicant: ROLLS-ROYCE plc
Inventor： John R. WELLS , Christopher A. MOSLEY , Nicholas GRECH
Abstract: A turbofan engine comprises a nacelle and an engine core having a core cowling. The internal surface of the nacelle and the external surface of the core cowling define a bypass duct having an exhaust end defining a bypass duct exit plane generally normal to the longitudinal axis of the engine. The core cowling extends aft of the bypass duct exit plane and has an annular or partly-annular exit ventilation nozzle located aft of a first longitudinal position and fore of a second longitudinal position, the first and second longitudinal positions being respectively fore of and either aft of or coincident with the bypass duct exit plane, the core cowling otherwise being free of exit ventilation nozzles fore of the second longitudinal position. The engine has a lower specific fuel consumption than an equivalent engine having an exit ventilation nozzle in a conventional position aft of the second longitudinal position.
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公开(公告)号：US20240328359A1
公开(公告)日：2024-10-03
申请号：US18609514
申请日：2024-03-19
Applicant: ROLLS-ROYCE plc
Inventor： Nicholas GRECH , Matthew J. WILLSHEE , Jacopo TACCONI
CPC classification number: F02C7/224 , B64D37/30 , B64D37/34 , F02C3/22 , F05D2220/323 , F05D2260/213
Abstract: A propulsive aircraft gas turbine engine comprises a turbine disposed in a gas turbine engine core flow and a recuperator heat exchanger disposed downstream of the turbine in gas turbine engine core flow, the recuperator heat exchanger being configured to transfer heat from the gas turbine engine core flow to gas turbine engine fuel. The recuperator heat exchanger is configured to accommodate a portion of the gas turbine engine core flow therethrough, the remainder being bypassed around the recuperator heat exchanger.
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公开(公告)号：US20240328351A1
公开(公告)日：2024-10-03
申请号：US18601182
申请日：2024-03-11
Applicant: ROLLS-ROYCE plc
Inventor： Nicholas GRECH , Jacopo Tacconi
Abstract: A gas turbine engine includes a core engine having a compressor, a combustor and a turbine in sequential air flow series. The engine further includes a fuel offtake configured and arranged to divert a portion of hydrogen fuel from a main fuel conduit, a burner configured and arranged to burn the portion of hydrogen fuel diverted from the main fuel conduit and a heat exchanger configured and arranged to transfer heat from exhaust gasses produced by the burner to hydrogen fuel in the main fuel conduit. At least first and second compressor bleed offtakes are at different pressure stages of the compressor, each being configured to bleed a portion of air from the compressor. At least first and second compressor bleed offtake valves are configured to control flow through the first and second bleed offtakes respectively. The burner is configured to receive bleed air from the compressor bleed offtakes.
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公开(公告)号：US20240229717A9
公开(公告)日：2024-07-11
申请号：US18379717
申请日：2023-10-13
Applicant: ROLLS-ROYCE PLC
Inventor： Chloe J. PALMER , Jacopo TACCONI , Nicholas GRECH
Abstract: A gas turbine engine fuel system includes a fuel offtake configured to divert a portion of hydrogen fuel from a main fuel conduit, a burner configured to burn the portion of hydrogen fuel diverted from the main fuel conduit, a heat exchanger configured to transfer heat from exhaust gasses produced by the burner to hydrogen fuel in the main fuel conduit and a power recovery device configured to extract power from exhaust gasses of the burner downstream of the heat-exchanger.
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Patent Agency Ranking
公开(公告)号：US20240133343A1
公开(公告)日：2024-04-25
申请号：US18379717
申请日：2023-10-12
Applicant: ROLLS-ROYCE PLC
Inventor： Chloe J. PALMER , Jacopo TACCONI , Nicholas GRECH
Abstract: A gas turbine engine fuel system includes a fuel offtake configured to divert a portion of hydrogen fuel from a main fuel conduit, a burner configured to burn the portion of hydrogen fuel diverted from the main fuel conduit, a heat exchanger configured to transfer heat from exhaust gasses produced by the burner to hydrogen fuel in the main fuel conduit and a power recovery device configured to extract power from exhaust gasses of the burner downstream of the heat-exchanger.
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公开(公告)号：US20240133340A1
公开(公告)日：2024-04-25
申请号：US18379728
申请日：2023-10-12
Applicant: ROLLS-ROYCE PLC
Inventor： Nicholas GRECH , Chloe J. PALMER , Jacopo TACCONI
IPC: F02C6/04 , F02C7/224 , F02C9/40 , H01M8/04111
CPC classification number: F02C6/04 , F02C7/224 , F02C9/40 , H01M8/04111 , F05D2220/323 , F05D2220/50 , H01M2250/20 , H01M2250/407
Abstract: A combined gas turbine engine and hydrogen fuel cell system includes a hydrogen fuelled gas turbine engine, a cryogenic liquid hydrogen fuel tank, a first fuel offtake configured and arranged to divert a portion of hydrogen fuel from a main fuel conduit, a burner configured and arranged to burn the portion of hydrogen fuel diverted from the main fuel conduit, a heat exchanger configured and arranged to transfer heat from exhaust gasses produced by the burner to hydrogen fuel in the main fuel conduit, a second fuel offtake arranged to divert a portion of hydrogen fuel from the main fuel conduit downstream of the heat exchanger, and a hydrogen fuel cell configured and arranged to produce electric power using hydrogen fuel diverted from the second fuel offtake.
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公开(公告)号：US20240229711A9
公开(公告)日：2024-07-11
申请号：US18379728
申请日：2023-10-13
Applicant: ROLLS-ROYCE PLC
Inventor： Nicholas GRECH , Chloe J. PALMER , Jacopo TACCONI
IPC: F02C6/04 , F02C7/224 , F02C9/40 , H01M8/04111
CPC classification number: F02C6/04 , F02C7/224 , F02C9/40 , H01M8/04111 , F05D2220/323 , F05D2220/50 , H01M2250/20 , H01M2250/407
Abstract: A combined gas turbine engine and hydrogen fuel cell system includes a hydrogen fuelled gas turbine engine, a cryogenic liquid hydrogen fuel tank, a first fuel offtake configured and arranged to divert a portion of hydrogen fuel from a main fuel conduit, a burner configured and arranged to burn the portion of hydrogen fuel diverted from the main fuel conduit, a heat exchanger configured and arranged to transfer heat from exhaust gasses produced by the burner to hydrogen fuel in the main fuel conduit, a second fuel offtake arranged to divert a portion of hydrogen fuel from the main fuel conduit downstream of the heat exchanger, and a hydrogen fuel cell configured and arranged to produce electric power using hydrogen fuel diverted from the second fuel offtake.
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公开(公告)号：US20230028367A1
公开(公告)日：2023-01-26
申请号：US17749908
申请日：2022-05-20
Applicant: ROLLS-ROYCE plc
Inventor： Richard G STRETTON , Michael C WILLMOT , Nicholas GRECH
Abstract: A gas turbine engine (10) for an aircraft comprises an engine core (11) comprising a turbine (19), a compressor (14), a core shaft (26), and a core exhaust nozzle (20), the core exhaust nozzle (20) having a core exhaust nozzle pressure ratio calculated using total pressure at the core nozzle exit (56); a fan (23) comprising a plurality of fan blades; and a nacelle (21) surrounding the fan (23) and the engine core (11) and defining a bypass duct (22), the bypass duct (22) comprising a bypass exhaust nozzle (18), the bypass exhaust nozzle (18) having a bypass exhaust nozzle pressure ratio calculated using total pressure at the bypass nozzle exit;
wherein a bypass to core ratio of: bypass exhaust nozzle pressure ratio core exhaust nozzle pressure ratio is configured to be in the range from 1.1 to 1.4 under aircraft cruise conditions.-
公开(公告)号：US20190323452A1
公开(公告)日：2019-10-24
申请号：US16360606
申请日：2019-03-21
Applicant: ROLLS-ROYCE plc
Inventor： John R WELLS , Christopher A MOSLEY , Nicholas GRECH
Abstract: A turbofan engine includes an outer fixed structure, the downstream terminal end of which terminates in a terminal plane substantially normal to the longitudinal axis of the engine. The radius R of the internal surface of the outer fixed structure in the terminal plane is a function R(ϕ) of azimuthal position ϕ such that the radius has a constant value R0 within a first azimuthal interval of 180°, a value greater than R0 at any azimuthal position within a second and fourth azimuthal intervals and a value less than R0 at any azimuthal position within a third azimuthal interval, the azimuthal intervals forming a total interval of 360° and the fourth interval being contiguous with the first. The engine may be mounted closer to the airframe of an aircraft than a turbofan engine having an outer fixed structure which is axisymmetric in its downstream terminal plane.
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