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    Pre-filter or coalescer mounted on pulse cartridge tripod
    81.
    发明授权
    Pre-filter or coalescer mounted on pulse cartridge tripod 有权
    安装在脉冲盒三脚架上的预过滤器或聚结器

    公开(公告)号：US08801826B2

    公开(公告)日：2014-08-12

    申请号：US13417358

    申请日：2012-03-12

    Applicant: Etienne Rene Pascal Jarrier

    Inventor： Etienne Rene Pascal Jarrier

    IPC: B01D46/00

    CPC classification number: F02C7/05

    Abstract: A filter arrangement is provided for filtering fluid flow in a turbine inlet system. The filter arrangement includes a support structure extending along an elongated axis within the turbine inlet system. A pulse or static cartridge filter for filtering a fluid flow is mounted on the support structure, with the support structure extending from an end of the cartridge filter. A pre-filter for filtering and/or coalescing the fluid flow is provided and is supported by the cartridge filter. A method of filtering fluid flow in the turbine inlet system is also provided.

    Abstract translation: 提供了一种用于过滤涡轮入口系统中的流体流动的过滤装置。 过滤器装置包括沿涡轮进口系统内的细长轴线延伸的支撑结构。 用于过滤流体流的脉冲或静态滤芯过滤器安装在支撑结构上，其中支撑结构从筒式过滤器的端部延伸。 提供用于过滤和/或聚结流体流的预过滤器，并且由过滤器支撑。 还提供了一种过滤涡轮入口系统中的流体流动的方法。

    METHOD FOR OPERATING A STATIC GAS TURBINE, AND INTAKE DUCT FOR INTAKE AIR OF A GAS TURBINE
    82.
    发明申请
    METHOD FOR OPERATING A STATIC GAS TURBINE, AND INTAKE DUCT FOR INTAKE AIR OF A GAS TURBINE 有权
    运行静态气体涡轮机的方法，以及吸入气体涡轮机进气的方法

    公开(公告)号：US20140196437A1

    公开(公告)日：2014-07-17

    申请号：US14233626

    申请日：2012-07-13

    Applicant: Oliver Schneider

    Inventor： Oliver Schneider

    IPC: F02M35/10

    CPC classification number: F02M35/10 ,  F02C7/05 ,  F02C7/052

    Abstract: An ambient air intake duct of a static gas turbine is provided, having at least one filter, which is arranged in the intake duct, for cleaning the ambient air (A) that can flow through the intake duct. A method for operating a static gas turbine which is equipped with a filter for cleaning the ambient air (A) is also provided. To rapidly provide a higher level of gas turbine power to a generator, it is provided that, by means of a bypass or by means of flaps arranged downstream of the filter, partially to completely unfiltered ambient air (A) can temporarily flow into the compressor inlet.

    Abstract translation: 提供了一种静态燃气轮机的环境空气进气管道，其具有布置在进气管道中的至少一个过滤器，用于清洁可流过进气管道的环境空气（A）。 还提供了一种用于操作配备有用于清洁周围空气（A）的过滤器的静态燃气轮机的方法。 为了快速地向发电机提供更高水平的燃气轮机功率，通过旁路或通过布置在过滤器下游的翼片部分地完全未过滤的环境空气（A）可临时流入压缩机 进口。

    Turbine Inlet Air Filter System with Elbow Access Gate
    84.
    发明申请
    Turbine Inlet Air Filter System with Elbow Access Gate 有权
    带弯头门的涡轮进气过滤系统

    公开(公告)号：US20140017068A1

    公开(公告)日：2014-01-16

    申请号：US13547136

    申请日：2012-07-12

    Applicant: Oswaldo Herrera

    Inventor： Oswaldo Herrera

    IPC: B01D46/00 ,  F01D25/00

    CPC classification number: F02C7/05 ,  F05D2230/72

    Abstract: The present application provides a turbine inlet air filter system for filtering a flow of air about a compressor. The turbine inlet air filter system may include an inlet filter house and an inlet duct extending from the inlet filter house to the compressor. The inlet duct may include an air elbow with an elbow gate thereon.

    Abstract translation: 本申请提供了一种用于过滤围绕压缩机的空气流的涡轮机入口空气过滤器系统。 涡轮进口空气过滤器系统可以包括入口过滤器室和从入口过滤器室延伸到压缩机的入口管道。 入口管道可以包括其上具有弯头门的空气弯头。

    GAS TURBINE ENGINE
    85.
    发明申请
    GAS TURBINE ENGINE 有权
    气体涡轮发动机

    公开(公告)号：US20140017067A1

    公开(公告)日：2014-01-16

    申请号：US13914882

    申请日：2013-06-11

    Applicant: ROLLS-ROYCE PLC

    Inventor： Richard Geoffrey STRETTON ,  Nicholas HOWARTH

    IPC: B64C11/00

    CPC classification number: B64C11/001 ,  B64D27/00 ,  B64D2027/005 ,  F02C3/067 ,  F02C7/04 ,  F02C7/05 ,  F02K3/025 ,  F02K3/04 ,  F05D2220/323 ,  F05D2220/325 ,  F05D2240/302 ,  F05D2250/324 ,  F05D2250/51 ,  Y02T50/66 ,  Y02T50/671 ,  Y02T50/673

    Abstract: A gas turbine engine (10) having an axial flow direction (X) therethrough in use. The gas turbine engine (10) comprises one or more rotor stages each comprising at least one rotor blade (120) having a root portion (122). The gas turbine engine (10) comprises a shroud (122) located upstream of one or more of the rotor stages relative to the axial flow direction (X). The shroud (122) defines a through passageway (128) extending between an inlet (130) and an outlet (132) which comprises a diffuser region (138). The diffuser region (138) is configured to reduce the axial velocity of air exiting the outlet (132) relative to air entering the diffuser portion (138) in use, wherein the outlet (132) is located such that air exiting the outlet (132) is directed substantially to the root portion (122) only of the rotor blades (120).

    Abstract translation: 一种在使用中具有轴流动方向（X）的燃气轮机（10）。 燃气涡轮发动机（10）包括一个或多个转子级，每个转子级包括至少一个具有根部（122）的转子叶片（120）。 燃气涡轮发动机（10）包括相对于轴向流动方向（X）定位在一个或多个转子级的上游的护罩（122）。 护罩（122）限定在入口（130）和包括扩散器区域（138）的出口（132）之间延伸的通道（128）。 扩散器区域（138）构造成在使用时相对于进入扩散器部分（138）的空气减少离开出口（132）的空气的轴向速度，其中出口（132）定位成使得离开出口（132）的空气 ）仅基本上指向转子叶片（120）的根部（122）。

    Containment casing for an aero engine
    86.
    发明授权
    Containment casing for an aero engine 有权
    航空发动机的集装箱

    公开(公告)号：US08591172B2

    公开(公告)日：2013-11-26

    申请号：US12873650

    申请日：2010-09-01

    Applicant: Kristofer John Bottome

    Inventor： Kristofer John Bottome

    IPC: F01D25/24

    CPC classification number: F02C7/05 ,  F01D21/045 ,  F01D25/26 ,  F05D2220/36 ,  F05D2240/14 ,  Y02T50/672

    Abstract: A containment assembly for a turbo fan engine, has a casing arranged in use around a rotatable fan, to form a duct for the fan and a liner element disposed on an interior surface between the casing and blades of a rotatable fan. The liner element includes a body portion mounted in a recess in the casing and a wall portion arranged to form part of an inner wall of the duct. The wall portion and the body portion being attached and defining a containment cavity therebetween for containment of a detached fan blade fragment in use, wherein the wall portion has a moveable portion movable between a first configuration in which it lies substantially flush with the inner wall of the duct, and a second configuration in which it provides an opening through which a fan blade fragment can enter the containment cavity.

    Abstract translation: 用于涡轮风扇发动机的容纳组件具有围绕可旋转风扇布置的壳体，以形成用于风扇的管道和布置在可旋转风扇的壳体和叶片之间的内表面上的衬垫元件。 衬垫元件包括安装在壳体中的凹部中的主体部分和布置成形成管道的内壁的一部分的壁部分。 壁部分和主体部分被连接并且在其间限定了容纳空腔，用于在使用中容纳分离的风扇叶片片段，其中壁部分具有可移动部分的可移动部分，第一构造与第一构造基本上与 管道和第二构造，其中它提供了风扇叶片片段可以通过该开口进入容纳空腔的开口。

    System and method for conditioning air flow to a gas turbine
    88.
    发明授权
    System and method for conditioning air flow to a gas turbine 有权
    调节到燃气轮机的气流的系统和方法

    公开(公告)号：US08465573B2

    公开(公告)日：2013-06-18

    申请号：US13253273

    申请日：2011-10-05

    Applicant: Michael Adelbert Sullivan ,  Huong Van Vu ,  Bhalchandra Arun Desai ,  Eric M. Lafontaine ,  Mark Andrew Cournoyer

    Inventor： Michael Adelbert Sullivan ,  Huong Van Vu ,  Bhalchandra Arun Desai ,  Eric M. Lafontaine ,  Mark Andrew Cournoyer

    IPC: B01D46/00

    CPC classification number: F02C7/05 ,  F02C7/143 ,  F05D2250/70 ,  F05D2250/71 ,  F05D2300/522 ,  F28F13/14

    Abstract: A system for conditioning air flow to a gas turbine includes a filter housing and a conditioning media inside the filter housing to adjust the temperature of the air flowing through the filter housing. At least one of a depth or a density of the conditioning media varies across the filter housing. A method for conditioning air flow to a gas turbine includes flowing air through a filter housing connected to the gas turbine and flowing the air across a conditioning media in the filter housing. The method further includes conditioning the air flow to reduce the temperature difference of the air exiting the filter housing across a dimension of the filter housing.

    Abstract translation: 用于调节到燃气轮机的空气流的系统包括过滤器壳体和过滤器壳体内部的调节介质，以调节流过过滤器壳体的空气的温度。 调节介质的深度或密度中的至少一个在过滤器壳体上变化。 用于调节到燃气轮机的空气流的方法包括使空气流过连接到燃气轮机的过滤器壳体并使空气流过过滤器壳体中的调节介质。 该方法还包括调节空气流量以减小过滤器壳体的空气在过滤器壳体的尺寸上的温度差。

    FAN STAGGER ANGLE FOR DIRT REJECTION
    89.
    发明申请
    FAN STAGGER ANGLE FOR DIRT REJECTION 有权
    风扇防护角风扇角

    公开(公告)号：US20130011266A1

    公开(公告)日：2013-01-10

    申请号：US13176473

    申请日：2011-07-05

    Applicant: Edward J. Gallagher ,  Becky E. Rose ,  Lisa I. Brilliant

    Inventor： Edward J. Gallagher ,  Becky E. Rose ,  Lisa I. Brilliant

    IPC: F01D5/14

    CPC classification number: F02C7/36 ,  F01D5/141 ,  F01D15/12 ,  F01D21/045 ,  F01D25/34 ,  F02C7/05 ,  F02K3/06 ,  Y02T50/673

    Abstract: A gas turbine engine includes a spool, a turbine coupled to drive the spool, a propulsor coupled to be rotated about an axis by the turbine through the spool, and a gear assembly coupled between the propulsor and the spool such that rotation of the turbine drives the propulsor at a different speed than the spool. The propulsor includes a hub and a row of propulsor blades that extend from the hub. Each of the propulsor blades has a span between a root at the hub and a tip, and a chord between a leading edge and a trailing edge. The chord forms a stagger angle α with the axis, and the stagger angle α is less than 15° at a position along the propulsor blade that is within an inboard 20% of the span.

    Abstract translation: 燃气涡轮发动机包括阀芯，联接以驱动阀芯的涡轮机，被连接以通过阀芯绕涡轮机绕轴旋转的推进器，以及联接在推进器和阀芯之间的齿轮组件，使得涡轮机驱动 推进器的速度不同于阀芯。 推进器包括从轮毂延伸的轮毂和一排推杆叶片。 每个推进器叶片具有在轮毂的根部与顶端之间的跨度，以及前缘和后缘之间的弦。 弦与轴线形成交错角α，并且在沿着推进刀片的位置处的交错角α小于15°，该推进角度在跨度的20％内。

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