公开(公告)号：US20130340439A1

公开(公告)日：2013-12-26

申请号：US14011318

申请日：2013-08-27

申请人： GENERAL ELECTRIC COMPANY

发明人： Sanji Ekanayake ,  Alston Ilford Scipio ,  Dale J. Davis ,  Ryan Margate Pastrana

IPC分类号： F02C7/047

CPC分类号： F02C7/047 ,  F02C6/08 ,  F02C6/18 ,  F02C7/055

摘要： A system for de-icing a gas turbine engine is provided. A manifold is coupled to an inlet screen. A first conduit is coupled to a stage of the compressor and a first input of a mixing component. A second conduit is coupled to the exhaust and a second input of the mixing component. The second conduit being adapted to extract exhaust gases without increasing the pressure at the exhaust. A third conduit is coupled to the output of the mixing component and the manifold. A method for de-icing a gas turbine engine inlet screen includes determining a current temperature at the inlet screen, and determining a desired temperature at the inlet screen. If the current temperature at the inlet screen is less than the desired temperature at the inlet screen first flow rate of an air-exhaust mixture necessary to achieve the desired inlet screen temperature is calculated. The method also includes extracting an amount of exhaust gas from a turbine exhaust subsystem without increasing a pressure at the turbine exhaust subsystem, extracting an amount of air from a compressor stage, and mixing the amount of exhaust gas with the amount of air to generate an air-exhaust mixture that is conveyed to the inlet screen.

摘要翻译： 提供了一种用于除燃气涡轮发动机的系统。 歧管联接到入口屏幕。 第一导管连接到压缩机的级和混合部件的第一输入端。 第二导管连接到排气口和混合部件的第二输入端。 第二导管适于在不增加排气压力的情况下提取废气。 第三导管连接到混合部件和歧管的输出端。 一种用于除燃燃气涡轮发动机入口屏幕的方法包括确定入口屏幕处的当前温度，以及确定入口屏幕处的期望温度。 如果入口筛网处的当前温度低于进口筛网所需的温度，则计算达到所需入口筛网温度所需的排气混合物的第一流量。 该方法还包括从涡轮机排气子系统中抽取一定量的废气而不增加涡轮排气子系统的压力，从压缩机级提取一定量的空气，并将废气量与空气量混合以产生 输送到入口屏幕的排气混合物。

公开(公告)号：US08499540B2

公开(公告)日：2013-08-06

申请号：US12532026

申请日：2008-03-19

申请人： Edgar Haehner ,  Eric Royer

发明人： Edgar Haehner ,  Eric Royer

IPC分类号： F02G3/00

CPC分类号： F02C7/047 ,  F02C7/055 ,  H05B6/80 ,  H05B2214/02 ,  Y02T50/672

摘要： A de-icer device for de-icing an air inlet of a gas turbine, such as a helicopter turbine engine. The de-icer device includes an essentially metallic enclosure for admitting air into the engine, the enclosure including a first opening for admitting air into the enclosure, the first opening including a first essentially metallic grid, the enclosure further including a second opening for directing the air towards a compression stage of the gas turbine. The de-icer device further includes a wave generator for generating electromagnetic waves in the enclosure at a frequency suitable for causing ice to melt.

摘要翻译： 一种除冰装置，用于对诸如直升机涡轮发动机的燃气轮机的进气口进行除冰。 除冰器装置包括用于将空气进入发动机的基本上金属的外壳，所述外壳包括用于允许空气进入外壳的第一开口，所述第一开口包括第一基本金属网格，所述外壳还包括第二开口，用于引导 空气朝向燃气轮机的压缩级。 除冰器装置还包括用于以适于使冰融化的频率在外壳中产生电磁波的波发生器。

公开(公告)号：US20130193127A1

公开(公告)日：2013-08-01

申请号：US13359106

申请日：2012-01-26

申请人： Alston Ilford Scipio ,  Sanji Ekanayake ,  Huong Van Vu ,  Abbas Motakef

发明人： Alston Ilford Scipio ,  Sanji Ekanayake ,  Huong Van Vu ,  Abbas Motakef

IPC分类号： H05B1/00

CPC分类号： F02C7/047 ,  F02C7/052 ,  F02C7/055 ,  F02C7/057 ,  F05D2250/51

摘要： A resistive heating system for a combustion turbine susceptible to inlet air filter house component and compressor icing includes a plurality of heating panels (bundles) arranged in a substantially-planar array, adapted to be located on or adjacent to the turbine's inlet air filter house. Each heating panel is provided with one or more electrically-resistive heating elements; and a controller for selectively activating the resistive heating elements on each of the plurality of heating panels.

摘要翻译： 用于容纳入口空气过滤器壳体部件和压缩机结冰的燃气轮机的电阻加热系统包括布置在基本上平面阵列中的多个加热面板（束），其适于位于或邻近涡轮机的入口空气过滤器室。 每个加热板设置有一个或多个电阻加热元件; 以及控制器，用于选择性地激活所述多个加热板中的每一个上的电阻加热元件。

公开(公告)号：US20120125009A1

公开(公告)日：2012-05-24

申请号：US13304212

申请日：2011-11-23

申请人： Richard Jones ,  Terrell M. Jones, SR.

发明人： Richard Jones ,  Terrell M. Jones, SR.

IPC分类号： F02C7/00 ,  F02G3/00

CPC分类号： F02C7/055

摘要： An aircraft system comprising a deflector assembly including, a base having mounting apertures; an inner ring concentrically positioned within an outer ring, the inner ring and the outer ring have an annulus defined therebetween via a base plate, a plurality of rods attached within the annulus and culminating at an apex creating a conical profile; and a forward-mounted cone-shaped deflecting member. The base plate comprises a through hole allowing airflow through the deflector assembly to supply an airplane engine. The aircraft safety device system further comprises at least one locking latch for removably securing the deflector assembly to a housing of the airplane engine. The aircraft safety device is mountable inside a lip of the housing of the airplane engine. Further, the aircraft safety device provides protection for airplane engines from air born animate and inanimate objects.

摘要翻译： 一种飞行器系统，包括偏转器组件，该偏转器组件包括：具有安装孔的底座; 内圈同心地定位在外圈内，内环和外环具有通过基板在其间限定的环，多个杆附接在环形空间内并且在顶点达到顶点，产生锥形轮廓; 和前置锥形偏转构件。 基板包括通孔，允许气流通过偏转器组件以供应飞机发动机。 飞机安全装置系统还包括至少一个锁定闩锁，用于可拆卸地将偏转器组件固定到飞机发动机的壳体上。 飞机安全装置可安装在飞机发动机壳体的唇部内。 此外，飞机安全装置为空中出生的动画和无生命物体提供对飞机发动机的保护。

公开(公告)号：US20120090300A1

公开(公告)日：2012-04-19

申请号：US13274060

申请日：2011-10-14

申请人： SYLVAIN CHAMPOUX ,  Alfin Leo ,  Ilko Paunov

发明人： SYLVAIN CHAMPOUX ,  Alfin Leo ,  Ilko Paunov

IPC分类号： F01N3/18 ,  F01N3/02

CPC分类号： F02C7/055 ,  F01N3/0215 ,  F01N13/10 ,  F02B37/02 ,  F02B39/16 ,  Y02T10/144 ,  Y02T10/20

摘要： The present invention generally relates to methods and apparatus for use in exhaust manifold assemblies of large diesel engines, such as ships, locomotives and the like. In one aspect, a screen for use in an exhaust manifold assembly is provided. The screen includes a plate formed in a concave shape. The plate has a plurality of apertures and a plurality of radially oriented closed slots formed therein. The screen further includes a band on an outer perimeter of the plate. In another aspect, a reducer assembly for use in an exhaust manifold assembly is provided. In yet a further aspect, a method of using a screen in an exhaust manifold assembly is provided.

摘要翻译： 本发明一般涉及用于诸如船舶，机车等的大型柴油发动机的排气歧管组件中的方法和装置。 在一个方面，提供了一种用于排气歧管组件的屏幕。 屏幕包括形成为凹形的板。 该板具有多个孔和形成在其中的多个径向取向的闭合槽。 屏幕还包括在板的外周上的带。 在另一方面，提供了一种用于排气歧管组件的减速器组件。 在另一方面，提供了一种在排气歧管组件中使用筛网的方法。

公开(公告)号：US08079809B2

公开(公告)日：2011-12-20

申请号：US12147146

申请日：2008-06-26

申请人： Al Selder ,  Raymond A. Sutyak ,  Donald R. Piscopo ,  Joseph A. Olsen, III ,  Marc Schmittenberg

发明人： Al Selder ,  Raymond A. Sutyak ,  Donald R. Piscopo ,  Joseph A. Olsen, III ,  Marc Schmittenberg

IPC分类号： F01D25/24

CPC分类号： F02C7/28 ,  F02C3/10 ,  F02C6/20 ,  F02C7/055 ,  F16J15/46

摘要： An inflatable sealing assembly for sealing between an intake section of a turbine engine and an air inlet ring of a vehicle. The inflatable sealing assembly including a seal holder coupled to the intake section of the engine and having a first inflatable seal, a second inflatable seal, and a closed cell foam material disposed therein. The first inflatable seal and the second inflatable seal are configured when inflated to provide a seal between the intake section of the turbine engine and the air inlet ring of the vehicle and prevent foreign object debris and/or water from entering the turbine engine.

摘要翻译： 一种用于在涡轮发动机的进气部分和车辆的进气环之间进行密封的可充气密封组件。 可充气密封组件包括密封保持器，其联接到发动机的进气部分并具有第一可充气密封件，第二可膨胀密封件和设置在其中的闭孔泡沫材料。 第一可膨胀密封件和第二可充气密封件在膨胀时构造成在涡轮发动机的进气部分和车辆的进气环之间提供密封，并防止异物碎屑和/或水进入涡轮发动机。

公开(公告)号：US20100284791A1

公开(公告)日：2010-11-11

申请号：US12463597

申请日：2009-05-11

申请人： Robert Jesse Flores

发明人： Robert Jesse Flores

IPC分类号： F04D29/70 ,  B23P15/04

CPC分类号： F02C7/055 ,  B64D33/02 ,  B64D2033/022 ,  F05D2250/232 ,  Y10T29/4932

摘要： Apparatuses, systems, and methods for preventing foreign objects from being ingested into the air intake of a jet engine. Apparatuses can have a mount with an opening for fluid communication with an air intake of the engine, a generally pyramidal shaped tip, and at a generally frusto-pyramidal shaped shield between the tip and the mount. The tip and the shield can be generally conical, generally polygonal, generally elliptical, or generally lunal. A proximal end of the tip can overlap and attach to a distal end of the shield and a proximal end of the shield can overlap and attach to a distal end of the mount. The exposed lateral surface of the tip and/or the shield can be solid without openings therein. Systems can include a nacelle provided around a portion of the jet engine and a plurality of overlapping generally frusto-pyramidal guards attached to each other and the nacelle with a plurality of gussets. Methods can include attaching a generally frusto-conical mount to a portion of a nacelle surrounding the engine, attaching a proximal end of a generally frusto-conical shield to a distal end of the mount, and attaching a proximal end of a generally conical tip to a distal end of the shield.

摘要翻译： 用于防止异物被摄入喷气发动机进气口的装置，系统和方法。 设备可以具有一个安装件，该安装件具有开口，用于与发动机的空气入口，大体上锥形的尖端以及尖端和底座之间的大致截头锥形的屏蔽件流体连通。 尖端和护罩可以是大致圆锥形的，通常是多边形的，通常是椭圆形的，或者通常是空腔。 尖端的近端可以重叠并附接到护罩的远端，并且护罩的近端可以重叠并附接到安装座的远端。 尖端和/或屏蔽件的暴露的侧表面可以是固体的，其中没有开口。 系统可以包括设置在喷气发动机的一部分周围的机舱，以及多个重叠的大致截头圆锥形的防护件，其彼此连接，并且机舱具有多个角撑板。 方法可以包括将大致截头圆锥形的安装件附接到围绕发动机的机舱的一部分，将大致截头圆锥形的护罩的近端附接到安装件的远端，以及将大致圆锥形的尖端的近端附接到 屏蔽的远端。

公开(公告)号：US20100180566A1

公开(公告)日：2010-07-22

申请号：US12689554

申请日：2010-01-19

申请人： JEFFREY A. MATOS

发明人： JEFFREY A. MATOS

IPC分类号： F02C7/055

CPC分类号： F02C7/055 ,  B64D33/02 ,  B64D2033/022 ,  F05D2250/131 ,  Y10T137/0536 ,  Y10T137/0645

摘要： A retractable deflector serves to deflect birds and debris from an air intake duct of an aircraft jet engine. The intake duct has a central longitudinal axis and a forward opening for the receipt of air. The deflector includes a plurality of elongate first support members disposed on the air intake duct in spaced relation to each other and having leading ends which extend from a perimeter of said forward opening. These members are mounted for movement to extend and retract the leading ends. A second support member is coupled to the leading ends of these first support members to retain said leading ends in spaced relation. The second support member is extendible in length and configured to hold the leading ends of the first support members sufficiently close together to cause said first support members to deflect at least one of a bird and debris, when in a first, deployed position, and to allow the leading ends of the first support members to maintain a spaced-apart relation along a line which approximately corresponds to the perimeter of the air duct when in a second, retracted position.

摘要翻译： 可伸缩偏转器用于使飞机和飞机喷气发动机的进气管道上的鸟类和碎屑偏转。 入口管道具有中心纵向轴线和用于接收空气的前部开口。 偏转器包括多个细长的第一支撑构件，其布置在进气管道上，彼此间隔开并且具有从所述向前开口的周边延伸的前端。 这些构件安装成用于移动以延伸和缩回前端。 第二支撑构件联接到这些第一支撑构件的前端，以保持间隔开的前端。 第二支撑构件的长度可延伸并且构造成将第一支撑构件的前端充分靠近在一起，以使得所述第一支撑构件在处于第一展开位置时使鸟和碎屑中的至少一个偏转，并且 允许第一支撑构件的前端在处于第二缩回位置时沿着大致对应于空气管道的周边的线保持间隔开的关系。

公开(公告)号：US20100175389A1

公开(公告)日：2010-07-15

申请号：US12729831

申请日：2010-03-23

申请人： Jamison W. Janawitz ,  Bradley S. Rogers ,  James Easel Roberts ,  Thomas Shannon Eckhoff ,  Robert W. Taylor

发明人： Jamison W. Janawitz ,  Bradley S. Rogers ,  James Easel Roberts ,  Thomas Shannon Eckhoff ,  Robert W. Taylor

IPC分类号： F02C7/052 ,  B03C3/04

CPC分类号： F02C7/052 ,  B01D46/0032 ,  B01D46/02 ,  B01D46/50 ,  B03C3/017 ,  B03C3/12 ,  B03C3/41 ,  B03C3/68 ,  B03C2201/04 ,  F02C7/055 ,  F05D2260/607

摘要： An inlet air filtration system for a gas turbine includes, in an exemplary embodiment, an air plenum, and a plurality of filter elements mounted inside the air plenum, with each filter element including a support structure. The inlet air filtration system also includes a plurality of electrodes positioned proximate the plurality of filter elements, where the electrodes are coupled to a power source which supplies a voltage to the electrodes. The voltage is sufficient to establish an electrostatic field between the electrodes and the filter elements, and is sufficient to produce a corona discharge from the electrodes, wherein an amount of current applied to the filter elements is about 0.1 μA/ft2 to about 15 μA/ft2.

摘要翻译： 在示例性实施例中，用于燃气涡轮机的入口空气过滤系统包括空气增压室和安装在空气增压室内的多个过滤元件，每个过滤元件包括支撑结构。 入口空气过滤系统还包括靠近多个过滤器元件定位的多个电极，其中电极耦合到向电极提供电压的电源。 电压足以在电极和滤波器元件之间建立静电场，并且足以从电极产生电晕放电，其中施加到滤波器元件的电流量为约0.1μA/ ft 2至约15μA/ ft2。

公开(公告)号：US20100107576A1

公开(公告)日：2010-05-06

申请号：US12523684

申请日：2008-01-15

申请人： Robert R. Belyew

发明人： Robert R. Belyew

IPC分类号： B01D46/52

CPC分类号： B01D46/523 ,  B01D46/0002 ,  B64D33/02 ,  B64D2033/0246 ,  F02C7/055 ,  F05D2220/329 ,  F05D2250/711 ,  Y02T50/671

摘要： An inlet barrier filter system for mounting on an aircraft to filter air prior to intake into an engine of the aircraft includes a frame having at least two curved frame members defining an opening. A filter element has a curved inward face and is received in the opening of the frame. The filter element includes filter media having pleats. A comb is attached to the frame and includes spaced-apart teeth that support the pleats. The comb is curved to generally conform to the curved inward face of the filter element.

摘要翻译： 用于安装在飞机上以在进入飞行器的发动机之前过滤空气的入口阻挡滤清器系统包括具有限定开口的至少两个弯曲框架构件的框架。 过滤元件具有弯曲的内表面并被接收在框架的开口中。 过滤元件包括具有褶皱的过滤介质。 梳子连接到框架上，并且包括支撑褶的间隔开的齿。 梳子弯曲成大体上符合过滤元件的弯曲内表面。