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    Turbine exhaust plenum
    2.
    发明授权
    Turbine exhaust plenum 有权
    涡轮排风室

    公开(公告)号：US08757969B2

    公开(公告)日：2014-06-24

    申请号：US12883158

    申请日：2010-09-15

    申请人： Rohit Pruthi ,  Deepesh D. Nanda

    发明人： Rohit Pruthi ,  Deepesh D. Nanda

    IPC分类号： F01D25/24 ,  F01D25/30

    CPC分类号： F01D25/30 ,  F01D9/065 ,  F05D2250/20 ,  F05D2250/40 ,  F05D2250/70

    摘要： In accordance with one embodiment, a system includes a turbine engine including an axial-radial diffuser section disposed about a first longitudinal axis downstream in an exhaust flow path from a turbine section. The system also includes an exhaust plenum including a first plenum portion disposed about the axial-radial diffuser section, wherein the first plenum portion includes a curved wall portion that diverges away from a circumference of the axial-radial diffuser section. The exhaust plenum also includes a second plenum portion extending away from the first plenum portion downstream along a second longitudinal axis of the exhaust plenum approximately crosswise to the first longitudinal axis.

    摘要翻译： 根据一个实施例，系统包括涡轮发动机，该涡轮发动机包括轴向 - 径向扩散器部分，该轴向 - 径向扩散器部分围绕涡轮部分的排气流动路径中的第一纵向轴线设置在下游。 该系统还包括排气室，其包括围绕轴向 - 径向扩散器部分设置的第一增压室部分，其中第一增压室部分包括远离轴向 - 径向扩散器部分的圆周分开的弯曲壁部分。 排气室还包括第二增压室部分，该第二增压室部分沿排气室的第二纵向轴线远离第一集气室部分向下延伸，大致与第一纵向轴线交叉。

    TURBINE BLADE ASSEMBLY AND STEAM TURBINE
    3.
    发明申请
    TURBINE BLADE ASSEMBLY AND STEAM TURBINE 有权
    涡轮叶片组件和蒸汽涡轮机

    公开(公告)号：US20090290983A1

    公开(公告)日：2009-11-26

    申请号：US12470264

    申请日：2009-05-21

    申请人： Osamu TANAKA

    发明人： Osamu TANAKA

    IPC分类号： F01D5/22 ,  F01D5/32

    CPC分类号： F01D5/326 ,  F01D5/225 ,  F05D2220/31 ,  F05D2250/40 ,  F05D2260/50

    摘要： A turbine blade 10a which is a stop blade is provided with a cutout portion 50 which is formed in one circumferential side surface 22a of a shank portion 22 at the center in the axial direction of a turbine rotor 100, a cutout portion 60 which is formed in one circumferential side surface 22a of the shank portion 22 from one end portion 22b to the cutout portion 50 in the axial direction of the turbine rotor 100, and a through passage 70 which is formed to pass from the cutout portion 50 to an effective blade part and in which a moving member 170, which moves a stopper member 160 to the effective blade part in the cutout portion 50, is inserted.

    摘要翻译： 作为止动叶片的涡轮叶片10a设置有切口部分50，该切口部分形成在涡轮转子100的轴向中心处的柄部分22的一个周向侧表面22a中，形成有切口部分60 在轴部22的一个圆周侧表面22a中，从涡轮转子100的轴向的一个端部22b到切口部50，以及形成为从切口部50通过有效刀片的贯通通道70 将止动构件160移动到切口部50中的有效叶片部的移动构件170插入其中。

    Thermally decoupled mixer
    4.
    发明申请
    Thermally decoupled mixer 有权
    热解耦混频器

    公开(公告)号：US20080131276A1

    公开(公告)日：2008-06-05

    申请号：US11606833

    申请日：2006-11-30

    申请人： Adeyemi E. Alade ,  Paul W. Palmer

    发明人： Adeyemi E. Alade ,  Paul W. Palmer

    IPC分类号： F01D1/02

    CPC分类号： F02K1/48 ,  F02K1/38 ,  F05B2260/301 ,  F05D2250/40

    摘要： The present invention provides a mixer assembly including a mixer and a plurality of scoops attached around a circumference of the mixer element via a combination of sliding brackets and fixed brackets. The sliding brackets provide attachment and allow relative movement between the plurality of scoops and the mixer element while the fixed brackets provide only attachment between the mixer element and the plurality of scoops. The first sliding bracket includes a first flange that is fixedly mounted to the mixer element and a second flange that is biased against a surface of the scoop. A second sliding bracket is fixedly mounted to the mixer element and adjustably mounted to the scoop. The second sliding bracket includes an attachment hole and the scoop includes an adjustment slot. A fastener assembly including a spacer is received within the adjustment hole and the adjustment slot to allow relative movement between the mixer element and the scoop.

    摘要翻译： 本发明提供了一种混合器组件，其包括混合器和通过滑动支架和固定支架的组合在混合器元件的圆周周围附接的多个铲斗。 滑动支架提供附接并且允许多个铲斗和混合器元件之间的相对移动，而固定支架仅提供混合器元件和多个勺子之间的附接。 第一滑动支架包括固定地安装到混合器元件的第一凸缘和抵靠勺表面偏压的第二凸缘。 第二滑动支架固定地安装到混合器元件上并可调节地安装到勺子上。 第二滑动支架包括附接孔，勺包括调节槽。 包括间隔件的紧固件组件被容纳在调节孔和调节槽内，以允许混合器元件和铲斗之间的相对移动。

    Turbine blade tip gap reduction system for a turbine engine
    5.
    发明申请
    Turbine blade tip gap reduction system for a turbine engine 审中-公开
    涡轮发动机的涡轮叶片尖端间隙减小系统

    公开(公告)号：US20080063513A1

    公开(公告)日：2008-03-13

    申请号：US11518018

    申请日：2006-09-08

    申请人： Gennadiy Afanasiev

    发明人： Gennadiy Afanasiev

    IPC分类号： F01D25/26

    CPC分类号： F01D11/22 ,  F05D2240/11 ,  F05D2250/40

    摘要： A turbine blade gap control system configured to move a vane carrier and attached ring segments of a turbine engine axially relative to a turbine blade assembly to reduce the gaps between the tips of the turbine blades and the ring segments to increase the efficiency of the turbine engine once operating in a steady state condition. The turbine blade assembly may be formed from a plurality rows of turbine blades extending radially from a rotor, wherein each row may be formed from a plurality of turbine blades and wherein the turbine blades may have tips positioned at an acute angle relative to a rotational axis of the turbine blade assembly. A vane carrier may be positioned concentric with the rotor and positioned radially outward from the turbine blades, and a plurality of ring segments may be attached to the vane carrier.

    摘要翻译： 一种涡轮机叶片间隙控制系统，被配置为相对于涡轮机叶片组件轴向地移动涡轮机的叶片载体和附接的环段，以减小涡轮叶片和环段之间的间隙，以提高涡轮发动机的效率 一旦在稳态条件下工作。 涡轮叶片组件可以由从转子径向延伸的多排涡轮机叶片形成，其中每排可以由多个涡轮叶片形成，并且其中涡轮机叶片可具有相对于旋转轴线成锐角的尖端 的涡轮叶片组件。 叶片载体可以与转子同轴地定位并且从涡轮叶片径向向外定位，并且多个环形段可以附接到叶片载体。

    Trailing edge for an aircraft engine, of the type with moving chevrons
    9.
    发明授权
    Trailing edge for an aircraft engine, of the type with moving chevrons 失效
    飞机发动机的后缘，具有移动的人字形的类型

    公开(公告)号：US08393435B2

    公开(公告)日：2013-03-12

    申请号：US12918329

    申请日：2009-02-26

    申请人： Philipe Guerin

    发明人： Philipe Guerin

    IPC分类号： F02K1/08

    CPC分类号： F02K1/46 ,  F05D2250/11 ,  F05D2250/40 ,  F05D2250/42 ,  F05D2260/96 ,  Y02T50/671

    摘要： This trailing edge is of the type with moving chevrons (9a, 9b, 9c). It comprises actuating means able to cause these chevrons (9a, 9b, 9c) to move from a passive position in which they are directed substantially in the direction of the airflow leaving the said engine, into an active position in which at least part of each chevron is inclined with respect to this direction. This trailing edge is notable in that the said active position is derived from the said passive position by pivoting, possibly combined with a translational movement, of at least part of each chevron about an axis (Aa, Ab, Ac) substantially parallel to the said direction.

    摘要翻译： 该后缘是具有移动的人字形（9a，9b，9c）的类型。 它包括致动装置，其能够使这些人字形（9a，9b，9c）从被动地位于基本上沿离开所述发动机的气流的方向的被动位置进入活动位置，其中每个 人字形相对于这个方向倾斜。 该后缘是值得注意的，因为所述主动位置是通过绕基本上平行于所述主动位置的轴线（Aa，Ab，Ac）绕轴线（Aa，Ab，Ac）的枢轴转动（可能与平移运动相结合）而衍生的， 方向。

    Engine exhaust system with directional nozzle
    10.
    发明授权
    Engine exhaust system with directional nozzle 有权
    发动机排气系统带定向喷嘴

    公开(公告)号：US08132755B2

    公开(公告)日：2012-03-13

    申请号：US12303970

    申请日：2007-06-11

    申请人： Charles Hollimon ,  John Barber ,  John Herman Sherrer ,  Robert Laramee

    发明人： Charles Hollimon ,  John Barber ,  John Herman Sherrer ,  Robert Laramee

    IPC分类号： B64C15/12

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

    摘要： 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.

    摘要翻译： 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。