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    HYBRID PROPULSION SYSTEM AND CONTROL METHOD THEREOF
    6.
    发明公开
    HYBRID PROPULSION SYSTEM AND CONTROL METHOD THEREOF 审中-公开

    公开(公告)号：EP3333401A1

    公开(公告)日：2018-06-13

    申请号：EP17205746.5

    申请日：2017-12-06

    Applicant: Rolls-Royce North American Technologies, Inc.

    Inventor： ARMSTRONG, Michael James

    IPC: F02K3/00 ,  F02K5/00 ,  F02C9/58

    CPC classification number: B64D27/24 ,  B64D27/10 ,  B64D2027/026 ,  F02C9/58 ,  F02K3/00 ,  F02K5/00 ,  F04D29/362 ,  F05D2220/7642 ,  F05D2270/061 ,  H02K7/1823

    Abstract: A system is described that includes a turbine engine including an engine fan including one or more variable-pitch blades driven by a shaft, which rotates at a rotational speed which depends on a pitch of the one or more variable-pitch blades of the engine fan. The system further includes a generator configured to produce alternating-current (AC) electricity at a particular frequency relative to the rotational speed of the shaft. The system also includes a propulsor, which includes a propulsor motor and a propulsor fan. The propulsor motor is configured to drive, based on the AC electricity produced by the generator, the propulsor fan. The system includes a controller configured to control the particular frequency of the AC electricity by at least controlling the pitch of the one or more variable-pitch blades of the engine fan and thereby the rotational speed of the generator.

    A propulsion unit for an aircraft
    8.
    发明公开
    A propulsion unit for an aircraft 审中-公开
    飞机的推进装置

    公开(公告)号：EP2578490A3

    公开(公告)日：2017-07-19

    申请号：EP12185886.4

    申请日：2012-09-25

    Applicant: Rolls-Royce plc

    Inventor： Brown, Stephen ,  Raffaelli, Lorenzo

    IPC: B64C11/00 ,  B64D33/02 ,  B64D29/02 ,  B64D33/04 ,  F02C7/042

    CPC classification number: B64C11/001 ,  B64D29/02 ,  B64D33/02 ,  B64D33/04 ,  F02C7/042 ,  F02K1/09 ,  F02K1/12 ,  F02K5/00

    Abstract: This invention relates to a propulsive unit (10) for an aircraft, comprising: a nacelle (12) which defines a duct (20) for channelling an airflow when in use and which provides an outwardly facing surface (14) of the propulsive unit (10), the outwardly facing surface (14) having an aerodynamic shape; a fan unit (16) for accelerating the airflow within the duct (20) when in use; wherein the duct (20) has an inlet (26) and an outlet (28) and the nacelle (12) is operable to adjust the either or both of the area of the inlet (26) and outlet (28) whilst substantially retaining the aerodynamic shape of the outwardly facing surface.

    Abstract translation: 本发明涉及一种用于飞行器的推进单元（10），包括：机舱（12），其限定用于在使用时引导气流的管道（20），并且提供推进单元的向外表面（14） 10），所述面向外的表面（14）具有空气动力学形状; 风扇单元（16），用于在使用时加速管道（20）内的气流; 其中所述管道（20）具有入口（26）和出口（28），并且所述机舱（12）可操作以调节所述入口（26）和所述出口（28）的所述区域中的任一者或两者， 面向外的表面的空气动力学形状。

    Rotational annular airscrew with integrated acoustic arrester
    9.
    发明公开
    Rotational annular airscrew with integrated acoustic arrester 审中-公开
    Luftschraube mit akustischem Ableiter

    公开(公告)号：EP2730501A2

    公开(公告)日：2014-05-14

    申请号：EP13192605.7

    申请日：2013-11-12

    Applicant: The Boeing Company

    Inventor： Moore, Matthew D. ,  Boren, Kelly L.

    IPC: B64C11/00

    CPC classification number: F02K5/00 ,  B64C11/001 ,  B64C11/18 ,  F01D1/24 ,  F01D5/03 ,  F01D5/225 ,  F02K1/44 ,  F02K1/827 ,  F02K3/062 ,  F02K3/072 ,  F04D29/326 ,  F05D2260/96 ,  Y02T50/672 ,  Y02T50/673 ,  Y10T137/0536

    Abstract: A propulsion system and methods are presented. A substantially tubular structure (102) comprises a central axis (104) through a longitudinal geometric center, and a first fan (108) rotates around the central axis, and comprises a first fan hub (110) and first fan blades (112). The fan hub (108) is rotationally coupled to the substantially tubular structure (102), and the first fan blades (112) are coupled to the first fan hub (110) and increase in chord length with increasing distance from the first fan hub (108). A second fan (118) is rotationally coupled to the substantially tubular structure (102) and rotates around the central axis and contra-rotates relative to the first fan (108). Second fan blades (118) are coupled to the second fan hub (120), and a nacelle (124) circumscribing the first fan (108) and the second fan (118) is coupled to and rotates with the first fan (108).

    Abstract translation: 提出了推进系统和方法。 基本上管状的结构（102）包括通过纵向几何中心的中心轴线（104），并且第一风扇（108）围绕中心轴线旋转，并且包括第一风扇毂（110）和第一风扇叶片（112）。 风扇轮毂（108）旋转地联接到基本上管状的结构（102），并且第一风扇叶片（112）联接到第一风扇轮毂（110），并且随着距离第一风扇轮毂 108）。 第二风扇（118）旋转地联接到基本上管状的结构（102）并围绕中心轴线旋转并相对于第一风扇（108）反转。 第二风扇叶片（118）联接到第二风扇轮毂（120），并且限定第一风扇（108）和第二风扇（118）的机舱（124）联接到第一风扇（108）并与第一风扇（108）一起旋转。

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