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    System and method for preventing objects from entering the intake of a jet engine
    64.
    发明授权
    System and method for preventing objects from entering the intake of a jet engine 有权
    用于防止物体进入喷气发动机进气口的系统和方法

    公开(公告)号：US09581084B2

    公开(公告)日：2017-02-28

    申请号：US14847709

    申请日：2015-09-08

    申请人： Thomas Lucian Hurlburt

    发明人： Thomas Lucian Hurlburt

    IPC分类号： F02C7/055 ,  F02C7/047 ,  B64D33/02

    CPC分类号： F02C7/055 ,  B64D33/02 ,  B64D2033/022 ,  B64D2033/0286 ,  F02C7/047 ,  F05D2220/323 ,  F05D2260/80

    摘要： A system for preventing objects from entering the intake of a jet engine including a deflector mounted to the turbine shaft and including a de-icing device to minimize collection of ice on the deflector. The deflector includes a sensor in one embodiment for measuring object strikes so that comprehensive impact data may be obtained to generate an impact report so that measures can be taken to minimize object impacts.

    摘要翻译： 一种用于防止物体进入喷气发动机的入口的系统，该系统包括安装在涡轮机轴上的偏转器，并且包括除冰装置以最小化导流板上的冰的收集。 在一个实施例中，偏转器包括用于测量物体撞击的传感器，从而可以获得综合影响数据以产生影响报告，以便采取措施来最小化物体影响。

    De-Icing Splitter for an Axial Turbine Engine Compressor
    65.
    发明申请
    De-Icing Splitter for an Axial Turbine Engine Compressor 有权
    用于轴流涡轮发动机压缩机的除冰分流器

    公开(公告)号：US20170043877A1

    公开(公告)日：2017-02-16

    申请号：US15233340

    申请日：2016-08-10

    申请人： Safran Aero Boosters SA

    发明人： David Bouillon ,  Clément Collin ,  Guillaume Terlinden

    IPC分类号： B64D15/04 ,  F01D25/02 ,  B64D33/02

    CPC分类号： B64D15/04 ,  B64D33/02 ,  B64D2033/0233 ,  F01D25/02 ,  F02C7/047 ,  F05D2220/323 ,  Y02T50/671

    摘要： A de-icing and anti-icing splitter for an axial turbine engine low-pressure compressor has an external annular wall delimiting the secondary or bypass flow, and an internal annular wall; notably an external stator shroud; delimiting the primary or main stream. The upstream edge of the internal wall is fixed to the upstream annular hook of the external wall. The splitter has a series of notches which pass radially through the internal wall to allow de-icing fluid to circulate through the hook. The notches may form crescents. The splitter becomes simpler while at the same time maintaining optimal efficiency.

    摘要翻译： 用于轴向涡轮发动机低压压缩机的除冰和防冰分流器具有限定次级或旁路流的外部环形壁和内部环形壁; 特别是外部定子护罩; 划分主流或主流。 内壁的上游边缘固定在外壁的上游环形钩上。 分流器具有一系列凹口，其径向通过内壁，以允许除冰液体通过钩子循环。 缺口可能会形成新月。 分离器变得更简单，同时保持最佳效率。

    JET ENGINE, FLYING OBJECT, AND METHOD OF OPERATING A JET ENGINE
    66.
    发明申请
    JET ENGINE, FLYING OBJECT, AND METHOD OF OPERATING A JET ENGINE 审中-公开
    喷气发动机，飞行对象和操作喷气发动机的方法

    公开(公告)号：US20170009665A1

    公开(公告)日：2017-01-12

    申请号：US15121187

    申请日：2015-02-18

    申请人： MITSUBISHI HEAVY INDUSTRIES, LTD.

    发明人： Yoshihiko UENO ,  Shojiro FURUYA

    IPC分类号： F02C9/32 ,  F02C7/04 ,  F02C7/22 ,  F02K7/00

    CPC分类号： F02C9/32 ,  B64D33/02 ,  F02C7/04 ,  F02C7/222 ,  F02C7/232 ,  F02C9/44 ,  F02K7/00 ,  F02K7/14 ,  F02K7/18 ,  F05D2220/323 ,  F05D2220/80 ,  F05D2240/35 ,  F05D2250/90 ,  F05D2270/306 ,  F23N1/002 ,  F23N2037/02 ,  F23N2037/10 ,  F23N2041/20 ,  F23R3/28

    摘要： A jet engine has an inlet which takes in air, a combustor which combusts fuel by using the air, and a fuel control section which controls supply of the fuel. The combustor has a fuel supplying section which supplies the fuel, injectors which inject the fuel. Each injector contains openings which inject the fuel. The fuel supplying section supplies the fuel to the injector in a flow rate according to a command of an autopilot. The fuel control section controls the injectors such that the number of the openings which inject the fuel or flow-path cross-section areas of the pipes which send the fuel in case of the low-speed is more than the number of the openings which inject the fuel or the flow-path cross-section areas of the pipes which send the fuel in case of the high-speed.

    摘要翻译： 喷气发动机具有吸入空气的入口，通过使用空气燃烧燃料的燃烧器，以及控制燃料供给的燃料控制部。 燃烧器具有供给燃料的燃料供给部，喷射燃料的喷射器。 每个喷射器包含喷射燃料的开口。 燃料供给部根据自动驾驶员的指令以流量将燃料供给到喷射器。 燃料控制部分控制喷射器，使得在低速的情况下喷射燃料的燃料或流路横截面积的发射燃料的数量大于喷射的开口的数量 在高速的情况下发送燃料的管道的燃料或流路横截面区域。

    HEAT EXCHANGER
    67.
    发明申请
    HEAT EXCHANGER 有权
    热交换器

    公开(公告)号：US20170003080A1

    公开(公告)日：2017-01-05

    申请号：US15125710

    申请日：2015-03-11

    申请人： BAE SYSTEMS PLC

    发明人： Colin Whaites ,  Stephen John Richard Smith ,  Andrew Mark Townsley

    IPC分类号： F28D7/00 ,  B64D33/02 ,  B64D13/00

    CPC分类号： F28D7/0008 ,  B64D13/00 ,  B64D33/02 ,  B64D2033/024 ,  F01D9/02 ,  F01D9/04 ,  F01D25/12 ,  F02C7/14 ,  F02C7/185 ,  F05D2260/213 ,  F05D2300/5024 ,  F28D7/0058 ,  F28D2021/0021 ,  Y02T50/676

    摘要： A heat exchanger (2) comprising a duct (4) through which a first fluid (e.g. a coolant such as ram air) may flow, and one or more vanes (18) disposed within the duct (4) and configured to disrupt the flow of the first fluid through the duct (4). Each vane (18) comprises one or more flow channels (24) through which a second fluid (e.g. a fluid to be cooled, such as engine coolant) may flow so as to transfer heat between the first fluid flowing through the duct (4) and the second fluid flowing through the one or more flow channels (24). The flow channels (24) within the vanes (18) are separated from the duct (4) by a channel wall such that fluid cannot flow between the duct (4) and the flow channels (24).

    摘要翻译： 一种热交换器（2），其包括管道（4），第一流体（例如，诸如冲压空气的冷却剂）可以流过该管道，以及设置在管道（4）内并且构造成破坏流体的一个或多个叶片 的第一流体通过管道（4）。 每个叶片（18）包括一个或多个流动通道（24），第二流体（例如待冷却的流体，例如发动机冷却剂）可以流过该流动通道，以便在流过管道（4）的第一流体之间传递热量， 并且所述第二流体流过所述一个或多个流动通道（24）。 叶片（18）内的流动通道（24）通过通道壁与管道（4）分离，使得流体不能在管道（4）和流动通道（24）之间流动。

    Generator for flight vehicle
    69.
    发明授权
    Generator for flight vehicle 有权
    飞机发电机

    公开(公告)号：US09517843B2

    公开(公告)日：2016-12-13

    申请号：US14095613

    申请日：2013-12-03

    申请人： Rolls-Royce North American Technologies, Inc.

    发明人： Kenneth M. Pesyna ,  Robert A. Ress, Jr.

    IPC分类号： B64D41/00 ,  B64D27/20 ,  B64D33/00 ,  B64D33/02 ,  F01D15/10

    CPC分类号： B64D41/00 ,  B64D27/20 ,  B64D33/00 ,  B64D33/02 ,  F01D15/10

    摘要： A flight vehicle includes a fuselage and a gas turbine engine. The gas turbine engine is coupled to the fuselage to provide thrust when air surrounding the flight vehicle is admitted to the gas turbine engine and combusted with fuel. The flight vehicle further includes a generator coupled to the gas turbine engine to provide power to equipment included in the vehicle.

    摘要翻译： 飞行器包括机身和燃气涡轮发动机。 燃气涡轮发动机联接到机身，以在飞行器周围的空气被允许进入燃气涡轮发动机并用燃料燃烧时提供推力。 飞行器车辆还包括联接到燃气涡轮发动机的发电机以向车辆中包括的设备提供动力。

    NACELLE INLET HAVING AN ANGLE OR CURVED AFT BULKHEAD
    70.
    发明申请
    NACELLE INLET HAVING AN ANGLE OR CURVED AFT BULKHEAD 审中-公开
    具有角度或弯曲的AFT BULKHEAD的NACELLE入口

    公开(公告)号：US20160356180A1

    公开(公告)日：2016-12-08

    申请号：US14729420

    申请日：2015-06-03

    申请人： The Boeing Company

    发明人： Eric D. Bol

    IPC分类号： F01D25/24

    CPC分类号： F01D21/045 ,  B64D29/00 ,  B64D33/02

    摘要： A construction of a nacelle inlet aft bulkhead has a curved or angled cross-section configuration between a connection of an outer edge of the aft bulkhead to an outer barrel of the nacelle inlet and a connection of an inner edge of the aft bulkhead to an inner barrel of the nacelle inlet. The curved or angled cross-section configuration of the aft bulkhead gives the bulkhead flexibility to avoid serious damage to the bulkhead in high load cases such as an fan blade off event. The curved or angled cross-section configuration also removes the need for a spring ring attached between the aft bulkhead and the inner barrel of the nacelle inlet. The curved or angled cross-section configuration also provides design flexibility to terminate the outer barrel of the nacelle inlet at an optimized location rearwardly to increase laminar air flow over the nacelle and reduce drag.

    摘要翻译： 机舱入口后舱壁的结构在后舱壁的外边缘与机舱入口的外筒的连接与后舱壁的内边缘与内舱壁的内边缘的连接之间具有弯曲或成角度的横截面构造 机舱的入口。 后舱壁的弯曲或倾斜的横截面构造给出了舱壁的灵活性，以避免在诸如风扇叶片关闭事件的高负载情况下严重损坏舱壁。 弯曲或成角度的横截面构造也消除了安装在舱壁与机舱入口的内筒之间的弹簧环的需要。 弯曲或成角度的横截面构造还提供设计灵活性，以便在优化的位置向后终止机舱入口的外筒，以增加机舱上的层流空气流动并减少阻力。