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    Aircraft, propulsion system, and system for taxiing an aircraft
    12.
    发明公开
    Aircraft, propulsion system, and system for taxiing an aircraft 审中-公开
    飞机推进系统和系统用于飞行器的辊

    公开(公告)号：EP2452878A3

    公开(公告)日：2015-01-14

    申请号：EP11250897.3

    申请日：2011-11-16

    申请人： Rolls-Royce Corporation

    发明人： Burns, Donald ,  Rajashekara, Kaushik

    IPC分类号： B64D27/16 ,  B64D41/00 ,  F02C7/32 ,  F02C7/36

    CPC分类号： B64D27/16 ,  B64D41/00 ,  B64D2041/005 ,  B64D2205/00 ,  F02C3/113 ,  F02C7/32 ,  F02C7/36 ,  F05D2220/50 ,  Y02T50/44 ,  Y02T50/823 ,  Y02T90/36

    摘要： A propulsion system (18) for an aircraft, comprising:
    a gas turbine engine having at least a high pressure (HP) spool (24) and a low pressure (LP) spool (26), wherein the LP spool (26) is operative to drive a propulsor (28); and
    a hybrid auxiliary power unit (APU) (22) mechanically coupled to both the HP spool (24) and the LP spool (26), wherein the hybrid APU (22) includes an APU compressor (60); an APU turbine (64); and a fuel cell (62) fluidly disposed between the APU compressor (60) and the APU turbine (64), wherein the fuell cell (62) is operative to receive as an oxidant air pressurized by the APU compressor (60); to generate electrical power using a fuel and the oxidant; to heat the air pressurized by the APU compressor (60); and to discharge the heated pressurized air into the APU turbine (64), wherein the hybrid APU (22) is operative to supply rotational power to both the HP spool (24) and the LP spool (26).

    ANGETRIEBENES FLUGGERÄT, INSBESONDERE ALS NURFLÜGLER UND/ODER MIT GERINGER RADARSIGNATUR AUSGEBILDETES FLUGGERÄT
    13.
    发明公开
    ANGETRIEBENES FLUGGERÄT, INSBESONDERE ALS NURFLÜGLER UND/ODER MIT GERINGER RADARSIGNATUR AUSGEBILDETES FLUGGERÄT 有权
    动力飞行仪器，特别是作为一个飞翼和/或低雷达信号飞行大队经过培训

    公开(公告)号：EP2582581A2

    公开(公告)日：2013-04-24

    申请号：EP11785286.3

    申请日：2011-06-14

    申请人： EADS Deutschland GmbH

    发明人： BICHLER, Bartholomäus ,  DORNWALD, Jochen ,  WEDEKIND, Gerhard

    IPC分类号： B64D33/02 ,  B64C39/10 ,  B64D27/16

    CPC分类号： B64D33/02 ,  B64C39/10 ,  B64C2039/105 ,  B64D27/16 ,  B64D2033/0286

    摘要： The invention relates to an aircraft (10), comprising a fuselage body, a wing body (12), and at least one drive flow passage (16), which extends from an air inlet (18) directed forward (+x) on the body surface (14) via a jet engine (20) through the body (12) to a propelling nozzle (22) that opens toward the rear (-x) on the body surface (14). In order to enable greater design freedom in regard to the shape of the body (12), in particular in the manner of a flying wing having improved flight properties compared to known aircrafts, and/or to achieve an extreme reduction in the radar signature of the aircraft (10), at least one part of the jet engine (20), in particular the entire jet engine (20), is arranged upstream of the air inlet (18) as viewed in the flying direction (+x) of the aircraft (10) and the drive flow passage (16) has curvature sections (24, 28) designed and arranged suitably therefor.