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    Aircraft Turbofan Engine with Multiple High-Pressure Core Modules Not Concentric with the Engine Centerline
    42.
    发明申请
    Aircraft Turbofan Engine with Multiple High-Pressure Core Modules Not Concentric with the Engine Centerline 审中-公开
    具有多个高压核心模块的飞机Turbofan发动机与发动机中心线不同轴

    公开(公告)号：US20150260127A1

    公开(公告)日：2015-09-17

    申请号：US14209679

    申请日：2014-03-13

    申请人： Arthur J. Wennerstrom

    发明人： Arthur J. Wennerstrom

    IPC分类号： F02K3/075 ,  F02K3/115

    CPC分类号： F02K3/115 ,  F01D15/10 ,  F02C6/02 ,  F05D2250/312 ,  F05D2260/85

    摘要： An aircraft turbofan engine configuration is described that has two or more high-pressure core modules operating in parallel flowpaths, each comprised of a compressor, a combustor, and a turbine, the axes of which are adjacent to but removed from the engine axis, in lieu of a single high-pressure core serving the same purpose that is coaxial with the engine axis in prior-art designs. An intercooler is included between the low-pressure compressor and the high-pressure compressor that differs from prior-art designs by being made an integral part of the fan stator rather than inserted as a separate entity. Both features offer advantages relative to prior-art designs.

    摘要翻译： 描述了一种具有两个或更多个并联流动路径的高压核心模块的飞行器涡扇风扇发动机配置，每个高压核心模块均包括压缩机，燃烧器和涡轮机，其轴线与发动机轴线相邻但是从发动机轴线移除， 代替在现有技术设计中与发动机轴线同轴的同一目的的单个高压芯。 通过制作风扇定子的整体部分而不是作为单独的实体插入，在低压压缩机和高压压缩机之间包括中间冷却器，其与现有技术设计不同。 这两个特征相对于现有技术的设计提供了优点。

    ACTUATOR MOUNTED TO TORQUE BOX
    43.
    发明申请
    ACTUATOR MOUNTED TO TORQUE BOX 有权
    执行器安装到扭矩箱

    公开(公告)号：US20150219017A1

    公开(公告)日：2015-08-06

    申请号：US14684689

    申请日：2015-04-13

    申请人： United Technologies Corporation

    发明人： Bernard W. Pudvah ,  Eugene C. Gasmen ,  Stanley Wiecko

    IPC分类号： F02C9/22 ,  F16H21/44

    CPC分类号： F02C9/22 ,  F01D17/162 ,  F04D29/563 ,  F05D2250/312 ,  F05D2250/313 ,  F05D2260/31 ,  F05D2260/56 ,  F16H21/44 ,  Y10T74/18888 ,  Y10T74/20012

    摘要： An actuator system mounted to a gas turbine engine that communicates mechanical power for positioning variable guide vanes within the gas turbine engine. The actuator system includes a torque box having components for communicating mechanical power to the variable guide vanes for positioning the vanes and an actuator mechanically coupled to provide mechanical power to the components of the torque box used to communicate the provided mechanical power to the inlet guide vanes. The actuator is mounted to the torque box via an elongate fastener extending in one direction and another elongate fastener extending in another direction.

    摘要翻译： 安装到燃气涡轮发动机的致动器系统，其传达用于在燃气涡轮发动机内定位可变导向叶片的机械动力。 致动器系统包括具有用于将机械动力传递到用于定位叶片的可变导向叶片的部件的扭矩盒，以及致动器，其机械联接以向用于将所提供的机械动力传递到入口导向叶片的扭矩箱的部件提供机械动力 。 致动器通过沿一个方向延伸的细长紧固件安装在转矩箱上，另一个细长紧固件沿另一个方向延伸。

    External segmented shell capable of correcting for rotor misalignment in relation to the stator
    44.
    发明授权
    External segmented shell capable of correcting for rotor misalignment in relation to the stator 有权
    外部分段壳体能够校正相对于定子的转子失准

    公开(公告)号：US08939712B2

    公开(公告)日：2015-01-27

    申请号：US13407948

    申请日：2012-02-29

    申请人： Jean-Francois Cortequisse

    发明人： Jean-Francois Cortequisse

    IPC分类号： F01D25/24 ,  F01D11/12 ,  F04D29/52

    CPC分类号： F01D11/122 ,  F04D29/526 ,  F05D2240/11 ,  F05D2250/312 ,  F05D2260/38 ,  F05D2300/501

    摘要： The invention relates to a housing for covering the ends of a row of rotor blades of an axial turbomachine compressor, the housing being provided with a sealing device between the blade tips and the housing. It comprises a shell segmented along its circumference, each segment being fixed to the housing by a series of elastomeric elements in a recess in the shape of a channel cut into the inner surface of the housing. In this way, in the event of misalignment of the rotor relative to the stator, the rotor blades coming into contact with sections of the shell will be able to move to compensate for this misalignment while reducing the frictional forces generated by contact between the blades and the shell. In the event of alignment being re-established the segments of the shell will be able to resume their initial position because of the elastic behavior of the elements.

    摘要翻译： 本发明涉及一种用于覆盖轴向涡轮机械压缩机的一排转子叶片的端部的壳体，该壳体在叶片尖端和壳体之间设置有密封装置。 它包括沿着其圆周分段的壳体，每个部分通过切割入壳体内表面的通道形状的凹部中的一系列弹性体元件固定到壳体。 以这种方式，在转子相对于定子不对准的情况下，与壳体的部分接触的转子叶片将能够移动以补偿该不对准，同时减少由叶片与叶片之间的接触产生的摩擦力 贝壳。 在重新建立对准的情况下，由于元件的弹性行为，壳的段将能够恢复其初始位置。

    Compressor housing and exhaust gas turbine supercharger
    45.
    发明授权
    Compressor housing and exhaust gas turbine supercharger 有权
    压缩机外壳和废气涡轮增压器

    公开(公告)号：US08919122B2

    公开(公告)日：2014-12-30

    申请号：US13511077

    申请日：2011-08-10

    申请人： Norihiko Sumi

    发明人： Norihiko Sumi

    IPC分类号： F02B33/44 ,  F02B33/02 ,  F02B37/16 ,  F04D17/10 ,  F04D29/42 ,  F02B39/00 ,  F02M25/06

    CPC分类号： F02B33/02 ,  F02B37/16 ,  F02B39/00 ,  F02M25/06 ,  F04D17/10 ,  F04D29/4206 ,  F05D2220/40 ,  F05D2250/312 ,  F05D2250/314 ,  F05D2260/606 ,  Y02T10/144

    摘要： A compressor housing includes a housing body for enclosing an impeller, an inlet portion for introducing air toward the impeller, and a port portion arranged adjacent to the inlet portion. A valve body for opening and closing a bypass passage, which bypasses the impeller, can be rested against the port portion. A connection hole, to which a return passage for returning blow-by gas of an internal combustion engine is connected, is formed in a side wall of the inlet portion. The inlet portion and the port portion have a common wall. A communication hole, which configures a part of the return passage, is formed in the common wall. The communication hole is formed such that the projection plane defined by projecting the communication hole onto a surface of the side wall having the connection hole along the axis of the communication hole is contained in the connection hole.

    摘要翻译： 压缩机壳体包括用于封闭叶轮的壳体，用于将空气引向叶轮的入口部分和邻近入口部分布置的端口部分。 用于打开和关闭绕过叶轮的旁通通道的阀体可以靠在端口部分上。 在入口部分的侧壁上形成连接有用于返回内燃机的窜气的返回通道的连接孔。 入口部分和端口部分具有共同的壁。 构成返回通道的一部分的连通孔形成在公共壁中。 连通孔形成为使连接孔沿连通孔的轴线突出于具有连接孔的侧壁的表面而限定的突出面被容纳在连接孔中。

    VARIABLE-PITCH NOZZLE FOR A RADIAL TURBINE, IN PARTICULAR FOR AN AUXILIARY POWER SOURCE TURBINE
    47.
    发明申请
    VARIABLE-PITCH NOZZLE FOR A RADIAL TURBINE, IN PARTICULAR FOR AN AUXILIARY POWER SOURCE TURBINE 审中-公开
    适用于径向涡轮机的可变喷嘴喷嘴，特别适用于辅助电源涡轮机

    公开(公告)号：US20140147278A1

    公开(公告)日：2014-05-29

    申请号：US14122490

    申请日：2012-05-31

    申请人： Jacques Demolis ,  Laurent Minel ,  Hubert Hippolyte Vignau

    发明人： Jacques Demolis ,  Laurent Minel ,  Hubert Hippolyte Vignau

    IPC分类号： F01D9/02

    CPC分类号： F01D9/02 ,  F01D17/165 ,  F05D2220/40 ,  F05D2220/50 ,  F05D2250/312

    摘要： A radial turbine nozzle of a turbine engine rotating about a central axis includes a first annular array of fixed blades and a second annular array with a same number of variable-pitch blades. The blades have pressure and suction surfaces. Each variable-pitch blade is connected to cups and is configured to be rotated by a controller about a geometric axis connecting centers of the cups. Each variable-pitch blade is mounted at a distance from the axis of the cups such that this axis of rotation is positioned facing the suction surface of the blade and substantially closer to a trailing edge than to a leading edge of that blade. The nozzle can modify the reduced flow admitted by a radial turbine in accordance with requirements of a thermodynamic cycle and produce a seal in an area of maximum load of the nozzle blades.

    摘要翻译： 围绕中心轴线旋转的涡轮发动机的径向涡轮喷嘴包括固定叶片的第一环形阵列和具有相同数量的可变桨距叶片的第二环形阵列。 叶片有压力和吸力表面。 每个可变桨距叶片连接到杯子，并且构造成由控制器围绕连接杯子中心的几何轴线旋转。 每个可变桨距叶片安装在与杯的轴线一定距离处，使得该旋转轴线定位成面向叶片的吸力表面并且基本上比该叶片的前缘更靠近后缘。 喷嘴可以根据热力学循环的要求修改由径向涡轮机允许的减小的流量，并且在喷嘴叶片的最大负载区域中产生密封。

    ACTUATOR MOUNTED TO TORQUE BOX
    49.
    发明申请
    ACTUATOR MOUNTED TO TORQUE BOX 有权
    执行器安装到扭矩箱

    公开(公告)号：US20130323028A1

    公开(公告)日：2013-12-05

    申请号：US13485325

    申请日：2012-05-31

    申请人： Bernard W. Pudvah ,  Eugene C. Gasmen ,  Stanley Wiecko

    发明人： Bernard W. Pudvah ,  Eugene C. Gasmen ,  Stanley Wiecko

    IPC分类号： F15B15/00 ,  F01D25/00

    CPC分类号： F02C9/22 ,  F01D17/162 ,  F04D29/563 ,  F05D2250/312 ,  F05D2250/313 ,  F05D2260/31 ,  F05D2260/56 ,  F16H21/44 ,  Y10T74/18888 ,  Y10T74/20012

    摘要： An actuator system mounted to a gas turbine engine that communicates mechanical power for positioning variable guide vanes within the gas turbine engine. The actuator system includes a torque box having components for communicating mechanical power to the variable guide vanes for positioning the vanes and an actuator mechanically coupled to provide mechanical power to the components of the torque box used to communication the provided mechanical power to the inlet guide vanes. The actuator is mounted to the torque box via a plurality of bolts.

    摘要翻译： 安装到燃气涡轮发动机的致动器系统，其传达用于在燃气涡轮发动机内定位可变导向叶片的机械动力。 致动器系统包括具有用于将机械动力传递到用于定位叶片的可变导向叶片的部件的扭矩盒，以及机械地联接以将机械动力提供给用于将所提供的机械动力连通到入口导向叶片的扭矩箱的部件的机械动力 。 致动器通过多个螺栓安装到扭矩箱。