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    Gas turbine engine variable area exhaust nozzle
    4.
    发明授权
    Gas turbine engine variable area exhaust nozzle 有权

    公开(公告)号：US09617953B2

    公开(公告)日：2017-04-11

    申请号：US13965362

    申请日：2013-08-13

    申请人： ROLLS-ROYCE PLC

    发明人： John Richard Webster

    IPC分类号： F02K1/12 ,  F02K1/38 ,  F02K1/48

    CPC分类号： F02K1/12 ,  F02K1/386 ,  F02K1/48 ,  F05D2300/505 ,  Y02T50/672

    摘要： A gas turbine engine variable area exhaust nozzle has a plurality of first and second movable members arranged circumferentially around a fan casing extending in downstream. The first and second movable members alternate around the variable area nozzle. During cruise conditions the first and second movable members are in un-actuated positions. At take off conditions the first movable members are in an actuated position and the second movable members are in the un-actuated position. At top of climb conditions the first movable members are in the un-actuated position and the second movable members are in an actuated position. The first movable members move radially outwardly from the un-actuated position to the actuated position and the second movable members move radially inwardly from the un-actuated position to the actuated position.

    SEGMENTED MULTI-LOBE MIXER
    6.
    发明申请
    SEGMENTED MULTI-LOBE MIXER 审中-公开
    SEGMENTED MULTI LOBE MIXER

    公开(公告)号：US20160376928A1

    公开(公告)日：2016-12-29

    申请号：US14750094

    申请日：2015-06-25

    申请人： Pratt & Whitney Canada Corp.

    发明人： GUY LEFEBVRE ,  RENE PAQUET

    IPC分类号： F01D25/30 ,  B01F3/02 ,  F01D25/00

    CPC分类号： F01D25/30 ,  B01F3/026 ,  F01D25/005 ,  F02K1/386 ,  F02K1/48 ,  F05D2220/32 ,  F05D2240/40 ,  F05D2260/30 ,  F05D2260/96 ,  F05D2300/6033 ,  Y02T50/672

    摘要： A multi-lobe exhaust mixer has an annular body composed of a plurality of circumferentially adjacent lobe segments. The lobe segments may be made of a ceramic matrix composite material to reduce the weight of the mixer and ensure proper behavior when exposed to high thermal gradients. Each lobe segment may have partial lobes at circumferentially opposed ends thereof and at least one complete lobe therebetween. The partial lobes of the circumferentially adjacent lobe segments combining to conjointly form complete lobes at the junction between the circumferentially adjacent lobe segments. The partial lobes may be nested into each other to dampen vibrations.

    摘要翻译： 多叶排气混合器具有由多个周向相邻的叶片段组成的环形体。 凸角段可以由陶瓷基复合材料制成，以减小混合器的重量，并确保暴露于高热梯度时的适当行为。 每个叶片段可以在其周向相对的端部处具有部分波瓣，并且其间具有至少一个完整波瓣。 周向相邻的瓣片段的部分瓣组合成在周向相邻的瓣片段之间的连接处共同形成完整的瓣。 部分瓣可以嵌套在一起以抑制振动。

    Gas turbine engine exhaust mixer
    7.
    发明授权
    Gas turbine engine exhaust mixer 有权
    燃气轮机发动机排气混合机

    公开(公告)号：US09284915B2

    公开(公告)日：2016-03-15

    申请号：US14263098

    申请日：2014-04-28

    申请人： Pratt & Whitney Canada Corp.

    发明人： Guy Lefebvre ,  Nicolas Grivas ,  Richard Bouchard ,  Denis Leclair ,  Eric Durocher

    IPC分类号： F02K1/38 ,  F02K1/48 ,  F02K1/80 ,  F01D1/04 ,  F01D9/04

    CPC分类号： F02K1/386 ,  F01D9/04 ,  F02K1/48 ,  F02K1/80 ,  F05D2220/32 ,  F05D2230/642 ,  F05D2240/10 ,  F05D2240/127 ,  Y02T50/671

    摘要： An exhaust mixer for a gas turbine engine includes an annular wall having upstream end adapted to be fastened to an engine case and a downstream end forming a plurality of inner and outer mixer lobes. A support member interconnects at least a number of the inner lobes, and includes a circumferentially extending stiffener ring located radially inwardly from the inner lobes and a series of circumferentially spaced apart mixer struts radially extending from the inner lobes to the stiffener ring. The mixer struts have a radial length at least equal to a width of a main gas path defined between the inner lobes and the exhaust cone such that the mixer struts extend entirely through the main gas path. The stiffener ring being fixed solely to the mixer struts such as to float with respect to the exhaust cone and permit relative movement therebetween.

    摘要翻译： 用于燃气涡轮发动机的排气混合器包括具有适于紧固到发动机壳体的上游端的环形壁和形成多个内部和外部混合器凸角的下游端。 支撑构件互连至少多个内裂片，并且包括从内裂片径向向内定位的周向延伸的加强环，以及一系列周向间隔开的从内裂纹到加强环径向延伸的混合器支柱。 混合器支柱具有至少等于限定在内部叶片和排气锥体之间的主气体通道的宽度的径向长度，使得混合器支柱完全延伸穿过主气体路径。 加强环仅被固定到混合器支柱上，以便相对于排气锥体浮动并允许它们之间的相对运动。

    INTEGRATED TURBINE EXHAUST STRUTS AND MIXER OF TURBOFAN ENGINE
    9.
    发明申请
    INTEGRATED TURBINE EXHAUST STRUTS AND MIXER OF TURBOFAN ENGINE 有权
    涡轮发动机集成涡轮机排气和混合器

    公开(公告)号：US20150337761A1

    公开(公告)日：2015-11-26

    申请号：US14521888

    申请日：2014-10-23

    申请人： PRATT & WHITNEY CANADA CORP.

    发明人： Remo MARINI ,  Mark Huzzard CUNNINGHAM

    IPC分类号： F02K1/38

    CPC分类号： F02K1/386 ,  F01D9/041 ,  F01D25/30 ,  F02K1/48 ,  F05D2240/12 ,  F05D2250/61

    摘要： A turbine exhaust case (TEC) of a turbofan aeroengine includes a mixer in an annular wavy configuration having alternate crests and valleys, and a plurality of radial deswirling struts interconnecting an annular hub positioned within the mixer and selected valleys of the mixer. A plurality of secondary trailing edge struts smaller than the deswirling struts in average chord dimensions interconnect the annular hub and other selected valleys free of connection with the deswirling struts.

    摘要翻译： 涡轮风扇发动机的涡轮机排气箱（TEC）包括具有交替的波峰和谷部的环形波浪形结构的混合器，以及将位于混合器内的环形轮毂与混合器的选定谷部互连的多个径向旋转支柱。 平均弦长尺寸小于旋转支柱的多个次级后缘支柱将环形轮毂和其它选定的谷物与解旋支柱无连接。

    Turbojet engine outlet lobe mixer with guiding protrusions, and method of mixing airflows
    10.
    发明授权
    Turbojet engine outlet lobe mixer with guiding protrusions, and method of mixing airflows 有权
    涡轮喷气发动机出口叶片混合器具有引导突起，以及混合气流的方法

    公开(公告)号：US09175638B2

    公开(公告)日：2015-11-03

    申请号：US13600605

    申请日：2012-08-31

    申请人： Pierrick Mouchoux ,  Eric De Vulpillieres ,  Gaetan Jean Mabboux ,  Marion Verdier

    发明人： Pierrick Mouchoux ,  Eric De Vulpillieres ,  Gaetan Jean Mabboux ,  Marion Verdier

    IPC分类号： F02K3/077 ,  F02K1/38 ,  F02K1/48 ,  F02K1/34 ,  F02K1/46

    CPC分类号： F02K3/077 ,  B64D33/06 ,  F02K1/34 ,  F02K1/386 ,  F02K1/46 ,  F02K1/48 ,  F05D2250/184 ,  F05D2260/96

    摘要： The invention aims at providing a sufficient air exchange in the engine area without raising the static pressure in the outlet area of the air exchange duct. In order to do this, the invention provides for an outlet section capable of concentrating the outlet of the exchange airflow towards zones with smaller static pressure. A turbojet engine outlet according to the invention provides an engine cowl, which comprises an external wall of a circumferential duct in which circulates an exchange airflow of the turbines, and an airflow mixer. At the outlet, the duct delivers the exchange airflow towards the mixer for the primary and secondary airflows of the turbojet engine. The mixer presents hot and cold lobes. In particular, the engine outlet also includes guiding of the exchange airflow towards the cold lobes.

    摘要翻译： 本发明的目的是在发动机区域内提供足够的空气交换，而不会增加空气交换管道出口区域的静压力。 为了做到这一点，本发明提供一种出口部分，其能够将交换空气的出口集中到具有较小静态压力的区域。 根据本发明的涡轮喷气发动机出口提供了一种发动机整流罩，其包括周向通道的外壁，其中循环涡轮机的交换气流和气流混合器。 在出口处，管道将交换空气流朝向混合器，用于涡轮喷气发动机的一次和二次气流。 搅拌机提供冷热叶片。 特别地，发动机出口还包括朝向冷叶的交换空气的引导。