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    DEVICE FOR INDOOR AIR PURIFICATION AND STERILIZATION
    91.
    发明申请
    DEVICE FOR INDOOR AIR PURIFICATION AND STERILIZATION 审中-公开
    室内空气净化和灭菌装置

    公开(公告)号：US20120207647A1

    公开(公告)日：2012-08-16

    申请号：US13502371

    申请日：2010-10-11

    Applicant: Bu-yeol Kim

    Inventor： Bu-yeol Kim

    IPC: A61L9/015

    CPC classification number: A61L9/00 ,  A01N1/0294 ,  A61L9/014 ,  A61L9/03 ,  A61L9/205 ,  A61L9/22 ,  A61L2209/14 ,  A61L2209/212 ,  B01D35/06 ,  B03C1/002 ,  B03C3/00 ,  B03C3/017 ,  B03C3/155 ,  F02C7/05 ,  F24F13/28

    Abstract: The present invention relates to a device for indoor air purification and sterilization which excites indoor air by arc discharge to decompose bad odor and sterilize air, wherein an excited state is maintained by applying a magnetic field and the contact time between molecules activated by arc and pollutants is extended, thereby improving air purification and sterilization effects, and the noise generated by arc discharge is reduced by a silencer and ozone and static electricity are removed by a filter which removes ozone and a metal filter for removing static electricity, respectively, thereby enabling very suitable configuration for indoor air purification and sterilization.

    Abstract translation: 室内空气净化灭菌装置技术领域本发明涉及一种室内空气净化灭菌装置，其通过电弧放电激发室内空气，分解恶臭，消毒空气，其中通过施加磁场和通过电弧和污染物激活的分子之间的接触时间来维持激发状态 延长，从而提高空气净化和灭菌效果，并且通过消音器和臭氧降低由电弧放电产生的噪声，并且通过分别去除臭氧的过滤器和用于去除静电的金属过滤器去除静电，从而使得非常 适合室内空气净化灭菌的配置。

    JET ENGINE PROTECTION SYSTEM
    95.
    发明申请
    JET ENGINE PROTECTION SYSTEM 有权

    公开(公告)号：US20110095912A1

    公开(公告)日：2011-04-28

    申请号：US13007612

    申请日：2011-01-15

    Applicant: Fred Charles Sands ,  Milton D. Jantzen

    Inventor： Fred Charles Sands ,  Milton D. Jantzen

    IPC: G08B23/00

    CPC classification number: B64D33/02 ,  B64D2033/022 ,  B64D2033/0286 ,  F02C7/05 ,  Y02T50/671

    Abstract: A modern jet engine inlet protection system that protects against large birds and operates autonomously, that is dormant in routine aircraft operations, that automatically actuates its protective device(s) only at the immediate point of need, then returning it (them) to a non-interfering position, including a RADAR system and a LIDAR system which detect birds entering the intended flight path of the aircraft, and fast computer-implemented computational algorithms that track and identify those from the detected set that are (1) projected to enter a zone which would lead to ingestion by the engine, and (2) of a size large enough that they would seriously damage the engine if ingested; that includes defensive mechanisms housed in the engine nacelle cowling or center hub, or in the fuselage structure that are instantaneously actuated shortly before arriving at the point of impact to shield, deflect, reduce the size of the approaching bird to an acceptable mass, or destroy it, and, that after the ingestion threat has passed, the devices are stowed/retracted or safely jettisoned.

    APPARATUS AND METHOD OF OPERATING A GAS TURBINE ENGINE
    96.
    发明申请
    APPARATUS AND METHOD OF OPERATING A GAS TURBINE ENGINE 有权
    一种气体涡轮发动机的操作方法和方法

    公开(公告)号：US20110079015A1

    公开(公告)日：2011-04-07

    申请号：US12870177

    申请日：2010-08-27

    Applicant: Torsten Geis ,  Edward Brook

    Inventor： Torsten Geis ,  Edward Brook

    IPC: F02C7/00 ,  G06F19/00

    CPC classification number: F01D17/02 ,  F01D17/16 ,  F02C7/05 ,  F02C9/22 ,  F05D2270/54 ,  F05D2270/708 ,  Y02T50/671

    Abstract: A gas turbine engine and an apparatus for operating the gas turbine engine includes at least one microphone to detect the sound of impacts of particles, recorder to record the sound of the impacts, an analyser to analyse the sound of the impacts of the particles, and a store of sounds of impacts, the stored sounds of impacts correspond to unfavourable weather conditions. A comparator compares the sound of the impacts of particles with one or more sounds of impacts stored in the store 68 sounds of impacts and if the comparator determines that the sound of the impacts of particles matches one or more stored sounds of impacts, a signal is sent to a control system for the gas turbine engine to adjust the operation of the gas turbine engine such that it operates in a safe mode of operation.

    Abstract translation: 燃气涡轮发动机和用于操作燃气涡轮发动机的装置包括至少一个麦克风，用于检测颗粒撞击的声音，记录器记录撞击的声音，分析器来分析颗粒的撞击声;以及 存储的影响声，存储的影响声音对应于不利的天气条件。 比较器将颗粒的影响的声音与存储在存储器68中的影响的声音的一个或多个影响声音进行比较，并且如果比较器确定颗粒的撞击的声音匹配一个或多个存储的冲击声，则信号为 发送到用于燃气涡轮发动机的控制系统以调节燃气涡轮发动机的操作，使得其在安全的操作模式下操作。

    Liner panel
    97.
    发明授权
    Liner panel 有权
    衬里面板

    公开(公告)号：US07914251B2

    公开(公告)日：2011-03-29

    申请号：US11798253

    申请日：2007-05-11

    Applicant: Clare L. Pool ,  Cedric B. Harper ,  Geoffrey R. Attewell

    Inventor： Clare L. Pool ,  Cedric B. Harper ,  Geoffrey R. Attewell

    IPC: F01D25/24

    CPC classification number: F02C7/05 ,  F01D21/045 ,  F02K1/82

    Abstract: A liner panel for a fan casing of a gas turbine engine includes a honeycomb layer, a septum layer and an abradable layer. The fan casing is provided with a containment system in case of fan blade failure. In use, ice may be released from a fan blade in a first direction, and (in the case of a blade-off event) a fan blade or part of a fan blade may be released in a second direction. The panel has a compressive strength greater in the first direction than in the second direction such that the released ice will be deflected by the panel but the released fan blade or part of a fan blade will pass through the panel.

    Abstract translation: 一种用于燃气涡轮发动机的风扇壳体的衬板，包括蜂窝层，隔膜层和耐磨层。 在风扇叶片故障的情况下，风扇壳体设有容纳系统。 在使用中，冰可以沿着第一方向从风扇叶片释放，并且（在叶片关闭事件的情况下），风扇叶片或风扇叶片的一部分可以在第二方向上被释放。 面板在第一方向上的压缩强度大于第二方向，使得释放的冰将被面板偏转，但释放的风扇叶片或风扇叶片的一部分将通过面板。

    Jet engine protection system
    98.
    发明授权
    Jet engine protection system 有权
    喷气发动机保护系统

    公开(公告)号：US07871455B1

    公开(公告)日：2011-01-18

    申请号：US12814074

    申请日：2010-06-11

    Applicant: Fred Charles Sands ,  Milton D. Jantzen

    Inventor： Fred Charles Sands ,  Milton D. Jantzen

    IPC: B01D46/46

    CPC classification number: B64D33/02 ,  B64D2033/022 ,  B64D2033/0286 ,  F02C7/05 ,  Y02T50/671

    Abstract: A modern jet engine inlet protection system that protects against large birds and operates autonomously, that is dormant in routine aircraft operations, that automatically actuates its protective device(s) only at the immediate point of need, then returning it (them) to a non-interfering position, including a RADAR system and a LIDAR system which detect birds entering the intended flight path of the aircraft, and fast computer-implemented computational algorithms that track and identify those from the detected set that are (1) projected to enter a zone which would lead to ingestion by the engine, and (2) of a size large enough that they would seriously damage the engine if ingested; that includes defensive mechanisms housed in the engine nacelle cowling or center hub, or in the fuselage structure that are instantaneously actuated shortly before arriving at the point of impact to shield, deflect, reduce the size of the approaching bird to an acceptable mass, or destroy it, and, that after the ingestion threat has passed, the devices are stowed/retracted or safely jettisoned.

    Abstract translation: 一种现代化的喷气式发动机入口保护系统，可防止大型鸟类自主运行，即在常规飞机操作中休眠，仅在需要的时刻自动启动其保护装置，然后将其返回到非 包括RADAR系统和LIDAR系统，用于检测进入飞行器预期飞行路径的鸟类，以及快速计算机实现的计算算法，跟踪和识别来自（1）投影进入区域的检测到的那些 这将导致发动机摄入，以及（2）尺寸足够大，以至于如果摄入会严重损坏发动机; 其包括容纳在发动机舱罩或中心毂中的防御机构，或机身结构中，在抵达撞击点之前立即致动屏蔽，偏转，将接近的鸟的尺寸减小到可接受的质量，或破坏 并且，在摄入威胁已经过去之后，设备被收起/收回或安全地放弃。

    Ice strike sheathing ring for the fan casing of an aircraft gas turbine
    99.
    发明授权
    Ice strike sheathing ring for the fan casing of an aircraft gas turbine 有权
    用于飞机燃气轮机风扇壳的冰击护环

    公开(公告)号：US07780401B2

    公开(公告)日：2010-08-24

    申请号：US11882631

    申请日：2007-08-03

    Applicant: Olaf Lenk ,  Uwe Dickert

    Inventor： Olaf Lenk ,  Uwe Dickert

    IPC: F02C7/05

    CPC classification number: F02C7/05 ,  F01D21/00 ,  F02K3/06 ,  F04D27/0292 ,  F04D29/526 ,  F05D2300/603 ,  Y02T50/672

    Abstract: An ice strike sheathing ring (4) including several fiber compound layers for the fan casing of an aircraft gas turbine features breaking points (7) at a certain regular distance, so that, in case of destruction of the ice strike sheathing ring due to extreme ice strike, fragments of small size will be produced which together with the engine airflow will pass the exit guide vanes downstream of the fan without blocking the engine airflow or reducing engine thrust. With fiber compound layers enclosing a cavity or a core, the breaking points designed as slots (9) and/or assembly holes (8) are located in the inner wall (20) of the ice strike sheathing ring facing the engine airflow, while the outer wall (21) of the ice strike sheathing ring adjoining the fan casing is firmly attached to the latter via an adhesive film and a threaded safety connection.

    Abstract translation: 包括用于飞机燃气轮机的风扇壳体的几个纤维化合物层的冰雹护环（4）以特定的规定距离具有断裂点（7），使得在由于极端的冰雹护环而被破坏的情况下 冰雹将产生小尺寸碎片，伴随发动机气流将通过风扇下游的出口导向叶片，而不会阻塞发动机气流或减少发动机推力。 利用包围腔或芯的纤维复合层，设计成槽（9）和/或组装孔（8）的断裂点位于面向发动机气流的冰击覆盖环的内壁（20）中，而 与风扇壳体相邻的冰雹护环的外壁（21）通过粘合膜和螺纹安全连接牢固地附接到风扇外壳。

    Vane assembly with improved vane roots
    100.
    发明授权
    Vane assembly with improved vane roots 有权
    具有改进的叶根的叶片组件

    公开(公告)号：US07628578B2

    公开(公告)日：2009-12-08

    申请号：US11467413

    申请日：2006-08-25

    Applicant: Barry Barnett ,  David Denis

    Inventor： Barry Barnett ,  David Denis

    IPC: F01D5/10

    CPC classification number: F01D9/042 ,  F02C7/05 ,  F05D2260/30 ,  F05D2300/222 ,  F05D2300/43 ,  F05D2300/431

    Abstract: A vane for a vane assembly of a gas turbine engine includes a vane root connected to the airfoil portion opposite a tip thereof. The vane root includes a platform and a button portion interconnecting the platform and the airfoil position. The button portion has relatively blunt leading and trailing ends which respectively protrude beyond leading and trailing edges of the airfoil portion.

    Abstract translation: 用于燃气涡轮发动机的叶片组件的叶片包括连接到与其顶端相对的翼型部的叶根。 叶片根部包括平台和连接平台和翼型位置的按钮部分。 按钮部分具有分别突出超过翼型部分的前缘和后缘的相对钝的前端和后端。

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