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    THRUST REVERSER WITH FORWARD POSITIONED BLOCKER DOORS
    5.
    发明申请
    THRUST REVERSER WITH FORWARD POSITIONED BLOCKER DOORS 审中-公开
    与前进的定位挡块门相反

    公开(公告)号：US20160369743A1

    公开(公告)日：2016-12-22

    申请号：US14746380

    申请日：2015-06-22

    Applicant: Rohr, Inc.

    Inventor： Johann S. Schrell

    IPC: F02K1/56

    CPC classification number: F02K1/625 ,  F02K1/52 ,  F02K1/68 ,  F02K1/70 ,  F02K1/72 ,  F02K1/805

    Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a thrust reverser cascade, a fan ramp fairing and a blocker door. The thrust reverser cascade extends along an axial centerline from a forward cascade end to an aft cascade end. The fan ramp fairing is disposed at the forward cascade end. The fan ramp fairing is configured with a fairing surface that provides a forward boundary for bypass air flowing into the thrust reverser cascade during a first mode of operation. The blocker door is configured to completely axially overlap the fairing surface during a second mode of operation.

    Abstract translation: 为飞机推进系统提供组件。 该组件包括推力反向器级联，风扇斜坡整流罩和阻塞门。 推力反向器级联沿着轴向中心线从前级联端延伸到后级联端。 风扇斜坡整流罩设置在前级联端。 风扇斜坡整流罩配置有整流表面，其在第一操作模式期间提供流入推力反向器级联的旁路空气的前方边界。 阻挡门构造成在第二操作模式期间完全轴向地重叠整流罩表面。

    THRUST EFFICIENT TURBOFAN ENGINE
    7.
    发明申请
    THRUST EFFICIENT TURBOFAN ENGINE 有权
    高效的涡轮发动机

    公开(公告)号：US20140283500A1

    公开(公告)日：2014-09-25

    申请号：US13854225

    申请日：2013-04-01

    Applicant: United Technologies Corporation

    Inventor： Jayant Sabnis

    IPC: F02K3/00

    CPC classification number: F02C3/04 ,  F02C3/08 ,  F02C6/02 ,  F02C7/36 ,  F02K1/52 ,  F02K3/06 ,  F05D2220/36

    Abstract: A turbofan engine includes a gas generator section for generating a gas stream flow with higher energy per unit mass flow than that contained in the ambient air and a power turbine that converts the gas stream flow into shaft power. The turbofan engine further includes a propulsor section including a fan driven by the power turbine through a geared architecture at a second speed lower than the first speed for generating propulsive thrust as a mass flow rate of air through a bypass flow path. An Engine Unit Thrust Parameter defined as net engine thrust divided by a product of the mass flow rate of air through the bypass flow path, a tip diameter of the fan and the first rotational speed of the power turbine is less than about 0.15 at a take-off condition.

    Abstract translation: 涡轮风扇发动机包括气体发生器部分，用于产生具有比包含在环境空气中的每单位质量流更高的能量的气流;以及将气流转换成轴功率的动力涡轮机。 涡轮风扇发动机还包括推进器部分，其包括由动力涡轮机驱动的风扇，该风扇以低于第一速度的第二速度驱动，用于产生作为通过旁路流动路径的空气的质量流量的推进推力。 发动机单元推力参数被定义为净发动机推力除以通过旁路流路的空气的质量流量，风扇的尖端直径和动力涡轮机的第一转速的乘积在一次取样时小于约0.15 关闭条件。

    Gas turbine engine fan variable area nozzle with swivable insert system
    8.
    发明授权
    Gas turbine engine fan variable area nozzle with swivable insert system 有权
    燃气涡轮发动机风扇可变区域喷嘴与可旋转的插入系统

    公开(公告)号：US08662417B2

    公开(公告)日：2014-03-04

    申请号：US13625343

    申请日：2012-09-24

    Applicant: United Technologies Corporation

    Inventor： Edward B. Pero

    IPC: F02K1/06

    CPC classification number: F01D17/14 ,  F02K1/06 ,  F02K1/52 ,  F05D2220/36

    Abstract: An example nacelle assembly for a gas turbine engine includes a nacelle defined about an axis and defining a boundary of a fan bypass flow path. A fan variable area nozzle includes a plurality of inserts movably mounted to said nacelle. Each of the multiple of inserts is located at a circumferential position about the nacelle. The multiple of inserts are each independently moveable into the fan bypass flow path relative the nacelle to selectively vary a fan nozzle exit area.

    Abstract translation: 用于燃气涡轮发动机的示例性机舱组件包括围绕轴限定并限定风扇旁路流动路径的边界的机舱。 风扇可变区喷嘴包括可移动地安装到所述机舱的多个插入件。 多个插入件中的每一个位于围绕机舱的周向位置。 多个插入件相对于机舱独立地可移动到风扇旁路流动路径中，以选择性地改变风扇喷嘴出口区域。

    Engine Exhaust System with Directional Nozzle
    9.
    发明申请
    Engine Exhaust System with Directional Nozzle 有权
    具有方向喷嘴的发动机排气系统

    公开(公告)号：US20110131948A1

    公开(公告)日：2011-06-09

    申请号：US12303970

    申请日：2007-06-11

    Applicant: Charles Hollimon ,  John Barber ,  John Sherrer ,  Robert Laramee

    Inventor： Charles Hollimon ,  John Barber ,  John Sherrer ,  Robert Laramee

    IPC: F02K1/00

    CPC classification number: F02K1/004 ,  B64D33/04 ,  F02C7/20 ,  F02K1/36 ,  F02K1/52 ,  F02K1/805 ,  F05D2220/329 ,  F05D2230/642 ,  F05D2250/40 ,  F05D2260/54

    Abstract: An exhaust system for an aircraft has a primary exhaust duct for communicating exhaust gas from an engine exhaust exit and is configured for movement with the engine. A secondary exhaust duct is in fluid communication with the primary exhaust duct and is movably mounted to the airframe. The secondary duct has a portion selectively rotatable relative to the remainder of the secondary duct for directing the exhaust gas vector. The system has means for maintaining a generally consistent relative alignment between the primary duct and the secondary duct.

    Abstract translation: 用于飞行器的排气系统具有用于将来自发动机排气出口的废气连通并且被构造成与发动机一起运动的主排气管道。 二次排气管道与主排气管道流体连通并且可移动地安装到机身。 次级管道具有相对于辅助管道的其余部分选择性地可旋转的部分，用于引导废气向量。 该系统具有用于维持主管道和次管道之间的大致一致的相对对准的装置。

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