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    GAS TURBINE ENGINE COMPONENT AXIS CONFIGURATIONS
    11.
    发明申请
    GAS TURBINE ENGINE COMPONENT AXIS CONFIGURATIONS 审中-公开
    气体涡轮发动机组件轴配置

    公开(公告)号：US20130111923A1

    公开(公告)日：2013-05-09

    申请号：US13655128

    申请日：2012-10-18

    申请人： ICR Turbine Engine Corporation

    发明人： Frank Wegner Donnelly ,  David William Dewis ,  John D. Watson ,  Douglas W. Swartz

    IPC分类号： F02C7/143

    CPC分类号： F02C7/143 ,  F01D25/243 ,  F02C3/103 ,  F02C6/003 ,  F02C6/12 ,  F05D2250/31 ,  F05D2250/312 ,  F05D2250/313 ,  Y02T50/675

    摘要： A method is disclosed to enable the efficient physical packaging of gas turbine engine components to optimize power density, more readily integrate with other equipment and facilitate maintenance. The method illustrates dense packaging of turbomachinery by close-coupling of components, and rotation of various engine components with respect to engines and/or other engine components, and reversal of spool shaft rotational direction to suit the application. Engines can be dense-packed because of a number of features of the basic engine including the use of compact centrifugal compressors and radial inlet turbine assemblies, the close coupling of turbomachinery, the ability to rotate key components to facilitate ducting and preferred placement of other components, the ability to control spool shaft rotational direction and full power operation at high overall pressure ratios.

    摘要翻译： 公开了一种能够使燃气涡轮发动机部件的有效物理包装以优化功率密度，更容易与其他设备集成并便于维护的方法。 该方法示出了通过组件的紧密耦合以及相对于发动机和/或其他发动机部件的各种发动机部件的旋转以及卷筒轴旋转方向的反转以适应该应用的涡轮机械的密集包装。 由于基本发动机的许多特征包括使用紧凑型离心压缩机和径向进气涡轮机组件，涡轮机械的紧密耦合，旋转关键部件以促进管道的能力以及其他部件的优选放置的能力，发动机可以密集 ，能够在高整体压力比下控制卷筒轴的旋转方向和全功率运行。

    Containment casing
    12.
    发明申请
    Containment casing 审中-公开
    收容套管

    公开(公告)号：US20070031246A1

    公开(公告)日：2007-02-08

    申请号：US11416172

    申请日：2006-05-03

    申请人： Caetano Peng

    发明人： Caetano Peng

    IPC分类号： F01D11/08

    CPC分类号： F01D21/045 ,  F05D2240/14 ,  F05D2250/231 ,  F05D2250/313 ,  F05D2300/603 ,  F05D2300/702 ,  Y02T50/672

    摘要： A containment casing 1 is provided in which tubular composite layers 2, 3 are arranged in an angular staggered relationship to minimise overlap between the interstitial spacing between tubes in each respective layer 2, 3. In such circumstances, with a continuous planar layer 4, 5 on one or both sides, operational integrity is maintained with a lightweight containment casing 1 in comparison with prior arrangements but retaining resistance to fragment penetration.

    摘要翻译： 提供了一种安全壳体1，其中管状复合层2,3以角度交错关系布置，以最小化每个相应层2,3中管间间隙的重叠。 在这种情况下，在一侧或两侧具有连续的平面层4,5，与先前的布置相比，保持与轻量化的容纳壳体1的操作完整性，但保持对片段穿透的抵抗力。

    Multi-stable thrust vectoring nozzle
    14.
    发明授权
    Multi-stable thrust vectoring nozzle 失效
    多稳定推力矢量喷嘴

    公开(公告)号：US06298658B1

    公开(公告)日：2001-10-09

    申请号：US09451898

    申请日：1999-12-01

    申请人： Michael J. Bak

    发明人： Michael J. Bak

    IPC分类号： F02K100

    CPC分类号： F02K9/82 ,  F02K1/28 ,  F05D2240/128 ,  F05D2250/311 ,  F05D2250/313 ,  F05D2250/314

    摘要： A stream of primary gas flowing through a bi-stable thrust vectoring nozzle becomes attached to a first or second surface extending downstream of the nozzle, each surface incorporating one or more control ports for controlling to which surface the stream is attached, wherein relative to the longitudinal axis of the nozzle, the angle of discharge from the first surface is substantially different from the angle of discharge from the second surface, preferably with the first surface substantially aligned with the longitudinal axis of the nozzle. In one embodiment, a plurality of nozzles are arranged with the respective first surfaces substantially aligned with the longitudinal axis of the nozzle combination and each of the respective second surfaces arranged to laterally deflect a respective portion of the stream of primary gas in a respective direction along each of two orthogonal lateral axes.

    摘要翻译： 流过双稳定推力向量喷嘴的初级气体流附接到延伸到喷嘴下游的第一或第二表面，每个表面包括一个或多个控制端口，用于控制流连接到该表面，其中相对于 喷嘴的纵向轴线，来自第一表面的排出角度与从第二表面排出的角度大致不同，优选地，第一表面基本上与喷嘴的纵向轴线对准。 在一个实施例中，多个喷嘴被布置成具有相应的第一表面基本上与喷嘴组合的纵向轴线对准，并且各个相应的第二表面中的每一个布置成沿着相应的方向沿着主要气体流的相应部分横向偏转 两个正交横轴各有一个。

    Actuator device for moving a movable cowl of a thrust reverser
    19.
    发明授权
    Actuator device for moving a movable cowl of a thrust reverser 有权

    公开(公告)号：US09709003B2

    公开(公告)日：2017-07-18

    申请号：US15030848

    申请日：2014-10-23

    申请人： SAGEM DEFENSE SECURITE

    发明人： Christophe Maerky ,  Emmanuel Baudin ,  Lucien Donce

    IPC分类号： F16H25/00 ,  F02K1/76 ,  F16H25/24 ,  F16H25/22 ,  F16H25/20

    CPC分类号： F02K1/763 ,  F02K1/766 ,  F05D2250/313 ,  F05D2250/41 ,  F05D2260/52 ,  F05D2260/56 ,  F16H25/2204 ,  F16H25/2454 ,  F16H2025/2084

    摘要： The invention relates to an actuator device (8) for moving a movable cowl of a thrust reverser, including: an actuator (12) including a screw (14) and a nut (15) capable of engaging with the screw (14) such that a rotation of the screw relative to the nut translates the nut relative to the screw; a locking device (30) including a locking part (31, 57) which is movable relative to the screw (14) between a locked position in which the locking part (31, 57) prevents the rotation of the screw (14) and an unlocked position in which the locking part (31, 57) allows the rotation of the screw (14), in which the screw (14) includes a body (17) and a lock-inhibiting device (38), the lock-inhibiting device (38) including an inhibiting part (47, 48) which is movable relative to the body (17) between a first position in which the part (47, 48) allows the locking part (31, 47) to move between the locked position and the unlocked position, and a second position in which the inhibiting part (47, 48) prevents the locking part (31, 57) from moving into the locked position.

    TURBOSHAFT ENGINE EXHAUST NOZZLE HAVING ITS OUTLET PERPENDICULAR TO THE AXIS OF ROTATION OF THE ENGINE
    20.
    发明申请
    TURBOSHAFT ENGINE EXHAUST NOZZLE HAVING ITS OUTLET PERPENDICULAR TO THE AXIS OF ROTATION OF THE ENGINE 审中-公开
    涡轮发动机排气口具有发动机旋转轴线的出口

    公开(公告)号：US20160177789A1

    公开(公告)日：2016-06-23

    申请号：US14963370

    申请日：2015-12-09

    申请人： AIRBUS HELICOPTERS

    发明人： Olivier HONNORAT ,  Jan KRYSINSKI ,  Krzysztof SOBCZAK

    IPC分类号： F01D25/30 ,  F02K1/06

    CPC分类号： F01D25/30 ,  F02C3/10 ,  F02K1/06 ,  F05D2210/34 ,  F05D2210/42 ,  F05D2210/44 ,  F05D2220/329 ,  F05D2250/313 ,  F05D2250/314 ,  F05D2250/52 ,  F05D2250/712 ,  F05D2250/713

    摘要： A gas exhaust nozzle for a gas turbine, the exhaust nozzle having an annular inlet section centered on the axis of the gas turbine, a diffuser, a plenum chamber, and an expansion nozzle. The diffuser extends around the axis with a shape that diverges from the inlet section to the plenum chamber, and comprises an inner first surface and an outer first surface that are concave on the same side. The plenum chamber extends around the axis and is defined firstly by the diffuser and secondly by an outer second surface extending the inner first surface and joining the outer first surface. The plenum chamber includes a radial opening leading into the expansion nozzle, the exhaust gas leaving the expansion nozzle perpendicularly to the axis.

    摘要翻译： 一种用于燃气轮机的排气喷嘴，所述排气喷嘴具有以燃气轮机的轴线为中心的环形入口部分，扩散器，增压室和膨胀喷嘴。 扩散器围绕轴线延伸，其形状从入口部分扩散到增压室，并且包括位于同一侧上的凹入的内部第一表面和外部第一表面。 增压室围绕轴线延伸并且首先由扩散器限定，其次由延伸内部第一表面并连接外部第一表面的外部第二表面限定。 增压室包括通向膨胀喷嘴的径向开口，排出的废气垂直于轴线离开膨胀喷嘴。