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    GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT
    12.
    发明申请
    GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT 审中-公开
    燃气涡轮发动机压缩机装置

    公开(公告)号：US20160290241A1

    公开(公告)日：2016-10-06

    申请号：US15184253

    申请日：2016-06-16

    申请人： United Technologies Corporation

    发明人： Karl L. Hasel ,  Joseph B. Staubach ,  Brian D. Merry ,  Gabriel L. Suciu ,  Christopher M. Dye

    IPC分类号： F02C7/36 ,  F02C3/04 ,  F02K3/06 ,  F01D5/12 ,  F01D25/24 ,  F01D9/02 ,  F01D25/28 ,  F02C7/28 ,  F02C7/06 ,  F02K3/02

    CPC分类号： F02C7/36 ,  F01D5/06 ,  F01D5/12 ,  F01D9/02 ,  F01D21/003 ,  F01D25/24 ,  F01D25/28 ,  F02C3/04 ,  F02C3/06 ,  F02C3/107 ,  F02C7/06 ,  F02C7/28 ,  F02C9/18 ,  F02K3/025 ,  F02K3/06 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2240/12 ,  F05D2240/35 ,  F05D2240/55 ,  F05D2260/40 ,  F05D2260/4031 ,  F05D2260/40311

    摘要： A gas turbine engine includes, among other things, a fan section, a core engine, a bypass passage, and a bypass ratio defined as the volume of air passing into the bypass passage compared to the volume of air passing into the core engine, the bypass ratio being greater than or equal to about 8 at cruise power. A gear arrangement is configured to drive the fan section. A compressor section includes both a first compressor section and a second compressor section. A turbine section is configured to drive the gear arrangement, and may have a low pressure turbine with four stages and a low pressure turbine pressure ratio greater than about 5:1, and a high pressure turbine with two stages. An overall pressure ratio is provided by the combination of a pressure ratio across the first compressor section and a pressure ratio across the second compressor section, and greater than about 40, measured at sea level and at a static, full-rated takeoff power. The pressure ratio across the second compressor section is greater than about 7.

    摘要翻译： 除了别的以外，燃气涡轮发动机还包括风扇部分，核心发动机，旁通通道和旁路比，其被定义为与进入核心发动机的空气体积相比进入旁路通道的空气量， 旁路比在巡航功率时大于或等于约8。 齿轮装置被配置成驱动风扇部分。 压缩机部分包括第一压缩机部分和第二压缩机部分。 涡轮部分构造成驱动齿轮装置，并且可以具有四级的低压涡轮机和大于约5:1的低压涡轮机压力比，以及具有两级的高压涡轮机。 整个压力比通过跨第一压缩机段的压力比和跨越第二压缩机段的压力比的组合提供，并且在海平面和静态的额定额定起飞功率下测量大于约40。 跨越第二压缩机部分的压力比大于约7。

    Aviation gas turbine thrust reversing device
    13.
    发明授权
    Aviation gas turbine thrust reversing device 有权
    航空燃气轮机推力换向装置

    公开(公告)号：US09328694B2

    公开(公告)日：2016-05-03

    申请号：US13979782

    申请日：2012-01-19

    申请人： Predrag Todorovic

    发明人： Predrag Todorovic

    IPC分类号： F02K1/72 ,  F02K3/02 ,  F02K1/64 ,  F02K1/70 ,  F02K1/76

    CPC分类号： F02K3/025 ,  F02K1/64 ,  F02K1/70 ,  F02K1/72 ,  F02K1/763

    摘要： The present invention relates to an aircraft gas turbine thrust-reversing device with an engine having an engine cowling, the rear area of which can be displaced in the axial direction of the engine from a closed forward thrust position into a rearwardly displaced thrust reversal position, resulting in an essentially annular free space towards a forward stationary area of the engine cowling, with the rear area of the engine cowling being functionally coupled to deflecting elements arranged in the forward thrust position within the front area of the engine cowling, with the deflecting elements during displacement of the rear area of the engine cowling being moveable on a partial-circular path facing the central axis of the engine and contactable by their rear end areas with a cowling of the core engine.

    摘要翻译： 本发明涉及一种具有发动机的发动机的飞机燃气轮机推力反向装置，发动机整流罩的后部区域可以从封闭的向前推力位置向后移动的推力反转位置沿发动机的轴向位移， 导致朝向发动机整流罩的前部静止区域的基本上环形的自由空间，发动机整流罩的后部区域功能地联接到布置在发动机整流罩前部区域内的向前推力位置的偏转元件，偏转元件 在发动机整流罩的后部区域的移动期间可以在面向发动机的中心轴线的部分圆形路径上移动，并且可由其后端区域与核心发动机的整流罩接触。

    REVERSE FLOW SINGLE SPOOL CORE GAS TURBINE ENGINE
    14.
    发明申请
    REVERSE FLOW SINGLE SPOOL CORE GAS TURBINE ENGINE 审中-公开
    反向流动单缸阀芯涡轮发动机

    公开(公告)号：US20160102634A1

    公开(公告)日：2016-04-14

    申请号：US14639164

    申请日：2015-03-05

    申请人： United Technologies Corporation

    发明人： Gabriel L. Suciu ,  Jesse M. Chandler ,  Daniel Bernard Kupratis

    IPC分类号： F02K3/04 ,  F02C7/057 ,  F02K1/00 ,  F02C3/06

    CPC分类号： F02K3/04 ,  F01D13/003 ,  F01D13/006 ,  F02C3/06 ,  F02C7/36 ,  F02K1/52 ,  F02K3/025 ,  F02K3/06 ,  F05D2220/323 ,  F05D2250/314 ,  F05D2260/4031

    摘要： A bypass housing receives a fan and defines a front end. An airflow path delivers air into an inlet duct over a limited circumferential extent of the bypass housing. An airflow path passes across a low pressure compressor rotor. An airflow path passes through a core engine, which includes a high pressure compressor rotor, a combustor, and a high pressure turbine rotor. Products of combustion downstream of the high pressure turbine rotor pass into an intermediate duct and then across a low pressure turbine rotor. The low pressure turbine rotor is positioned closer to the front end of the engine than is the high pressure turbine rotor. The low pressure turbine rotor is positioned axially intermediate the low pressure compressor rotor and the fan. The low pressure turbine rotor drives both the fan and the low pressure turbine rotor. An aircraft is also disclosed.

    摘要翻译： 旁路外壳接收风扇并限定前端。 气流路径将空气输送到旁路壳体的有限圆周范围内的入口管道中。 气流通过低压压缩机转子。 气流路径通过核心发动机，其包括高压压缩机转子，燃烧器和高压涡轮转子。 高压涡轮转子下游的燃烧产物进入中间管道，然后穿过低压涡轮转子。 低压涡轮转子比高压涡轮转子更靠近发动机前端。 低压涡轮转子轴向位于低压压缩机转子和风扇之间。 低压涡轮转子驱动风扇和低压涡轮转子。 还披露了一架飞机。

    GAS TURBINE ENGINE HAVING CONFIGURABLE BYPASS PASSAGE
    16.
    发明申请
    GAS TURBINE ENGINE HAVING CONFIGURABLE BYPASS PASSAGE 有权
    燃气涡轮发动机具有可配置的旁路通风

    公开(公告)号：US20150003959A1

    公开(公告)日：2015-01-01

    申请号：US14140940

    申请日：2013-12-26

    申请人： Rolls-Royce North American Technologies Inc.

    发明人： Robert T. DUGE

    IPC分类号： F04D27/00 ,  F02C3/04

    CPC分类号： F04D27/009 ,  F01D17/105 ,  F02C3/04 ,  F02C9/18 ,  F02K3/025 ,  F02K3/075 ,  F02K3/077 ,  F05D2260/96 ,  F05D2260/962 ,  F05D2260/963

    摘要： A gas turbine engine is disclosed which includes a bypass passage that in some embodiments are capable of being configured to act as a resonance space. The resonance space can be used to attenuate/accentuate/etc a noise produced elsewhere. The bypass passage can be configured in a number of ways to form the resonance space. For example, the space can have any variety of geometries, configurations, etc. In one non-limiting form the resonance space can attenuate a noise forward of the bypass duct. In another non-limiting form the resonance space can attenuate a noise aft of the bypass duct. Any number of variations is possible.

    摘要翻译： 公开了一种燃气涡轮发动机，其包括在一些实施例中能够被配置为用作谐振空间的旁通通道。 谐振空间可用于衰减/加强其他地方产生的噪声。 旁路通道可以以多种方式构成以形成共振空间。 例如，空间可以具有各种各样的几何形状，配置等。在一个非限制性形式中，共振空间可以衰减旁路管道前方的噪声。 在另一个非限制性形式中，共振空间可以衰减旁路管道的噪声。 任何数量的变化是可能的。

    HYDRAULIC SYSTEM FOR CONTROLLING THE ORIENTATION OF FAN BLADES
    18.
    发明申请
    HYDRAULIC SYSTEM FOR CONTROLLING THE ORIENTATION OF FAN BLADES 有权
    用于控制风扇叶片方向的液压系统

    公开(公告)号：US20140193261A1

    公开(公告)日：2014-07-10

    申请号：US14237753

    申请日：2012-08-03

    申请人： Caroline Frantz ,  Regis Michel, Paul Deldalle

    发明人： Caroline Frantz ,  Regis Michel, Paul Deldalle

    IPC分类号： B64C11/38

    CPC分类号： B64C11/38 ,  B64C11/303 ,  B64C11/308 ,  B64C11/42 ,  B64D2027/005 ,  F01D7/00 ,  F02K3/025 ,  F05D2220/324 ,  F05D2220/325 ,  F05D2220/36 ,  F05D2260/79 ,  F05D2270/64 ,  Y02T50/66 ,  Y02T50/671

    摘要： A hydraulic system for controlling orientation of fan blades in a turbine engine including at least one set of adjustable pitch fan blades actuated by actuators that are connected to a hydraulic pump, and a small pitch protection valve controlled by an associated solenoid valve to make it possible on the ground, when the orientation of the blades is substantially perpendicular to the axis of the turbine engine, to pass from a first operating zone in which a speed of pitch variation of the blades is low to a second operating zone in which a speed of pitch variation is considerably higher, wherein operating pressure of the hydraulic pump is controlled by the solenoid valve controlling the small pitch protection valve to define two outlet levels corresponding to the two operating zones.

    摘要翻译： 一种用于控制涡轮发动机中的风扇叶片的取向的液压系统，包括由连接到液压泵的致动器致动的至少一组可调俯仰风扇叶片和由相关联的电磁阀控制的小螺距保护阀 在地面上，当叶片的方向基本上垂直于涡轮发动机的轴线时，从叶片的桨距变化速度低的第一操作区域传递到第二操作区域，其中速度 间距变化相当高，其中液压泵的操作压力由控制小间距保护阀的电磁阀控制，以限定对应于两个操作区的两个出口水平。

    Gas Turbine Engine Having Fan Rotor Driven by Turbine Exhaust and With a Bypass
    19.
    发明申请
    Gas Turbine Engine Having Fan Rotor Driven by Turbine Exhaust and With a Bypass 有权
    燃气轮机发动机，风机转子由涡轮排气和旁路驱动

    公开(公告)号：US20140183296A1

    公开(公告)日：2014-07-03

    申请号：US13731371

    申请日：2012-12-31

    申请人： UNITED TECHNOLOGIES CORPORATION

    发明人： Gabriel L. Suciu ,  Jesse M. Chandler

    IPC分类号： B64D27/14 ,  F02K3/02

    CPC分类号： B64D27/14 ,  B64D27/02 ,  F02K3/025 ,  F02K3/06 ,  F02K3/077

    摘要： A gas turbine engine has a core engine incorporating a core engine turbine. A fan rotor is driven by a fan rotor turbine. The fan rotor turbine is in the path of gases downstream from the core engine turbine. A bypass door is moveable from a closed position at which the gases from the core engine turbine pass over the fan rotor turbine, and moveable to a bypass position at which the gases are directed away from the fan rotor turbine. An aircraft is also disclosed.

    摘要翻译： 燃气涡轮发动机具有并入有核心发动机涡轮机的核心发动机。 风扇转子由风扇转子涡轮机驱动。 风扇转子涡轮机处于来自核心发动机涡轮机下游的气体的路径。 旁路门可以从关闭位置移动，在该关闭位置，来自核心发动机涡轮机的气体通过风扇转子涡轮机，并且可移动到旁路位置，在该旁路位置，气体被引导离开风扇转子涡轮机。 还披露了一架飞机。