公开(公告)号：US20160076460A1

公开(公告)日：2016-03-17

申请号：US14824292

申请日：2015-08-12

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Robert E. Malecki

IPC: F02C9/18 ,  F02C3/04 ,  F02C7/36 ,  F01D25/24

CPC classification number: F02C9/18 ,  B64D2033/022 ,  F01D25/24 ,  F02C3/04 ,  F02C7/05 ,  F02C7/36 ,  F02K3/06 ,  F05D2250/14 ,  F05D2250/232 ,  F05D2250/24

Abstract: A gas turbine engine includes a nacelle defining a centerline axis and an annular splitter radially inward from the nacelle. A spinner is radially inward of the nacelle forward of a compressor section. A fan blade extends from a fan blade platform. A distance X is the axial distance from a first point to a second point, wherein the first point is defined on a leading edge of the annular splitter and the second point is defined on a leading edge of the fan blade where the fan blade meets the fan blade platform. A distance H is the radial distance from the first point to the second point. The relative position of the first point and the second point is governed by the ratio of X/H≧1.5 for reducing foreign object debris (FOD) intake into the compressor section.

Abstract translation: 燃气涡轮发动机包括限定中心线轴线的机舱和从机舱径向向内的环形分配器。 旋转器在压缩机部分的前方的机舱的径向内侧。 风扇叶片从风扇叶片平台延伸。 距离X是从第一点到第二点的轴向距离，其中第一点被限定在环形分配器的前缘上，第二点限定在风扇叶片的前缘上，其中风扇叶片与 风扇叶片平台。 距离H是从第一点到第二点的径向距离。 第一点和第二点的相对位置由减少异物（FOD）进入压缩机段的X /H≥1.5的比率决定。

公开(公告)号：US20150345391A1

公开(公告)日：2015-12-03

申请号：US14663604

申请日：2015-03-20

Applicant: Shield Aerodynamics LLC

Inventor： Dennis Snyder

IPC: F02C7/047 ,  F02C7/055

CPC classification number: F02C7/055 ,  B64D33/02 ,  B64D2033/022 ,  F02C7/05 ,  Y02T50/672

Abstract: An environmental defense shield includes symmetric airfoil-shaped vanes contributing to and positioned around a plenum space and positioned in front of a turbine engine. An annular band stiffener is set into the vanes, which projects forward in a diminishing size, the vanes merging together to create or attaching to a solid nose. The environmental defense shield serves to protect the engine from debris while also smoothing airflow into the engine.

Abstract translation: 环境防护罩包括对称翼型叶片，其有助于并定位在集气室周围并位于涡轮发动机前方。 环形带加强件被设置在叶片中，叶片以尺寸减小的方式向前突出，叶片汇合在一起以产生或附着到实心的鼻子。 环保防护罩用于保护发动机免受碎片侵袭，同时还能平滑气流进入发动机。

公开(公告)号：US20150322858A1

公开(公告)日：2015-11-12

申请号：US14499753

申请日：2014-09-29

Applicant: William BOATENG

Inventor： William BOATENG

IPC: F02C7/055

CPC classification number: F02C7/055 ,  B01D2279/60 ,  B64D33/02 ,  B64D2033/022 ,  F02C7/05 ,  F02C7/052

Abstract: An aircraft engine guard, for protecting an aircraft engine against ingestion of large objects, includes a generally cone-shaped body, a base section of the rear end of the guard body and a dome section at the distal forward end of the guard body, at least three, vertical, peripherally extending walls located between the base and the dome section, with successive ones of the peripheral walls having different peripheral dimensions, peripherally cylindrical, with the dimension increasing from the base toward the dome section. A plurality of air intake openings are defined in and between the peripheral walls with at least one dimensional size which is small enough to prevent having birds from being able to pass through the guard into the aircraft engine.

Abstract translation: 用于保护飞机发动机免受大物体摄入的飞机发动机防护罩包括大致锥形的主体，防护体的后端的基部部分和防护体的远端前端处的圆顶部分， 位于基部和圆顶部分之间的至少三个垂直的周向延伸的壁，其中连续的周壁具有不同的周边尺寸，周向圆柱形，尺寸从基部朝向圆顶部分增加。 在周壁之间和周围壁之间限定多个进气口，至少一个尺寸足够小，以防止鸟类能够穿过防护罩进入飞行器发动机。

公开(公告)号：US20150300208A1

公开(公告)日：2015-10-22

申请号：US14452959

申请日：2014-08-06

Applicant: SNECMA

Inventor： Bruno Albert BEUTIN ,  Nuria LLAMAS CASTRO ,  Bruna RAMOS

IPC: F01D25/32 ,  F01D25/24

CPC classification number: F01D25/32 ,  B01D45/16 ,  F01D25/24 ,  F02C7/05 ,  F02C7/052 ,  F02C7/055 ,  F02K3/062 ,  F02K3/072 ,  F05D2220/30

Abstract: Turbine engine (110) having a nacelle (126) comprising, upstream, an air intake fairing (126a) and an element (140) for deflecting foreign objects which defines with said fairing an air intake flow path for supplying air to two coaxial flow paths, namely a radially inner and a radially outer flow path, said outer flow path being defined by a hub housing (152) and scoops, said hub housing (152) and said scoops (144) being installed downstream of the element (140) for deflecting objects, characterised in that each scoop comprises two independent portions, namely an upstream portion (144a) borne by the hub housing (152) and a downstream portion (144b) borne by the nacelle (162).

Abstract translation: 具有机舱（126）的涡轮发动机（110）包括在进气整流装置（126a）和元件（140）的上游，用于偏转用所述整流罩限定的异物，用于将空气供给到两个同轴流路 ，即径向内部和径向外部流动路径，所述外部流动路径由轮毂壳体（152）和铲斗限定，所述轮毂壳体（152）和所述铲斗（144）安装在所述元件（140）的下游，用于 偏转物体，其特征在于，每个铲斗包括两个独立的部分，即由轮毂壳体（152）承载的上游部分（144a）和由机舱（162）承载的下游部分（144b）。

公开(公告)号：US20150267555A1

公开(公告)日：2015-09-24

申请号：US14440388

申请日：2013-11-04

Applicant: SNECMA

Inventor： Romain Plante ,  Romain Coulon ,  Geoffroy De La Chapelle ,  Paul Follin ,  Florent Rognin

IPC: F01D25/04 ,  F02C7/045 ,  F01D25/24

CPC classification number: F01D25/04 ,  B64D29/06 ,  B64D33/02 ,  B64D2033/0206 ,  F01D11/125 ,  F01D11/127 ,  F01D21/045 ,  F01D25/243 ,  F01D25/246 ,  F02C7/045 ,  F02C7/05 ,  F02K3/06 ,  F05D2250/283 ,  F05D2260/96 ,  Y02T50/672

Abstract: A turbomachine casing including a substantially cylindrical wall and an annular one-piece acoustic insulation panel mounted inside the wall, the panel including an annular surface that is radially external opposite a radially internal annular surface of the wall, wherein the wall includes on its internal angular surface first projecting members which bear axially against second projecting members belonging to the external annular surface of the panel and which are fixed to these second members in a dismountable manner.

Abstract translation: 一种涡轮机壳体，其包括安装在所述壁内的基本上圆柱形的壁和环形单体隔音板，所述面板包括与所述壁的径向内部环形表面径向外侧的环形表面，其中所述壁包括在其内部角度 表面第一突出构件，其轴向地抵靠属于面板的外部环形表面的第二突出构件，并且以可拆卸的方式固定到这些第二构件。

公开(公告)号：US09046056B2

公开(公告)日：2015-06-02

申请号：US12631811

申请日：2009-12-05

Applicant: Bryan H. Lerg

Inventor： Bryan H. Lerg

IPC: F02K3/02 ,  B01D45/06 ,  F02C7/052 ,  F02K3/04 ,  F02C7/05 ,  F02C7/055

CPC classification number: F02K3/02 ,  B01D45/06 ,  F02C7/05 ,  F02C7/052 ,  F02C7/055 ,  F02K3/04 ,  F05D2250/411 ,  F05D2250/51 ,  F05D2260/607 ,  Y02T50/675

Abstract: Embodiments include an inlet particle separator system for a gas turbine engine. The inlet particle separator system includes an inertial particle separator that separates incoming air into a cleaned air flow and a scavenge flow. Embodiments may also include an ejector that provides a draw on a scavenge duct and entrains the scavenge flow into a charged flow, e.g., such as the output of a first stage fan. The ejector may have a variable output.

Abstract translation: 实施例包括用于燃气涡轮发动机的入口颗粒分离器系统。 入口颗粒分离器系统包括惯性颗粒分离器，其将进入的空气分离成清洁的空气流和扫气流。 实施例还可以包括喷射器，该喷射器在清扫管道上提供抽吸并将扫气流带入带电流，例如第一级风扇的输出。 喷射器可以具有可变输出。

公开(公告)号：US20150135947A1

公开(公告)日：2015-05-21

申请号：US14082926

申请日：2013-11-18

Applicant: BHA Altair, LLC

Inventor： Paul Sherwood Bryant ,  Michelle Fullerton Simpson

IPC: F02C7/057 ,  F02C7/05

CPC classification number: F02C7/057 ,  F02C7/05 ,  F02C7/052 ,  F05D2260/607

Abstract: Certain embodiments herein relate to systems and methods for managing turbine intake filters. In one embodiment, a system can include at least one memory configured to store computer-executable instructions and at least one control device configured to access the at least one memory and execute the computer-executable instructions. The instructions may be configured to receive information associated with a filter and identify the filter based at least in part on the information received. The instructions may be further configured to pulse the filter based at least in part on the information received.

Abstract translation: 本文中的某些实施例涉及用于管理涡轮进气过滤器的系统和方法。 在一个实施例中，系统可以包括被配置为存储计算机可执行指令的至少一个存储器和被配置为访问至少一个存储器并执行计算机可执行指令的至少一个控制设备。 指令可以被配置为接收与过滤器相关联的信息，并且至少部分地基于所接收的信息来识别过滤器。 所述指令还可以被配置为至少部分地基于所接收的信息来脉冲过滤器。

公开(公告)号：US20150040535A1

公开(公告)日：2015-02-12

申请号：US13961284

申请日：2013-08-07

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Zedic Daniel Judd ,  Yogendra Yogi Sheoran ,  Devinder N. Katariya ,  Eduardo Guerra

IPC: F02C7/05

CPC classification number: F02C7/05 ,  B64D2033/0246 ,  F02C7/052 ,  F05D2260/607 ,  Y02T50/675

Abstract: An inlet particle separator system for a vehicle engine includes a hub section, a shroud section, a splitter, and a hub suction flow passage. The shroud section surrounds at least a portion of the hub section and is spaced apart therefrom to define a main flow passageway that has an air inlet. The splitter is disposed downstream of the air inlet and extends into the passageway to divide the main flow passageway into a scavenge flow path and an engine flow path. The hub suction flow passage has a hub suction inlet port and a hub suction outlet port. The hub suction inlet port extends through the hub section and is in fluid communication with the air inlet. The hub suction outlet port extends through the splitter and is in fluid communication with the scavenge flow path.

Abstract translation: 用于车辆发动机的入口颗粒分离器系统包括轮毂部分，护罩部分，分离器和轮毂吸入流动通道。 护罩部分围绕轮毂部分的至少一部分并与其间隔开以限定具有空气入口的主流动通道。 分流器设置在空气入口的下游并延伸到通道中，以将主流动通道分成扫气流动路径和发动机流动路径。 轮毂吸入流路具有轮毂吸入口和轮毂吸出口。 轮毂吸入口延伸穿过轮毂部分并与进气口流体连通。 轮毂吸出口延伸穿过分流器并与清流流路流体连通。

公开(公告)号：US20140360217A1

公开(公告)日：2014-12-11

申请号：US13915291

申请日：2013-06-11

Applicant: BHA Altair, LLC

Inventor： Timothy John Nicholas

IPC: F02C7/18

CPC classification number: F02C7/1435 ,  F02C7/05 ,  F05D2230/60 ,  Y10T29/49229

Abstract: A cooling system for use in a turbine assembly is provided. The cooling system includes a first filter configured to remove particles entrained in a flow of intake air, an array of nozzles downstream from the first filter, and a second filter downstream from the array. The array of nozzles is configured to facilitate reducing a temperature of the intake air, and the second filter is configured to repel cooling liquid discharged from the array of nozzles while allowing cooled intake air to flow therethrough.

Abstract translation: 提供了一种用于涡轮组件的冷却系统。 该冷却系统包括第一过滤器，其构造成去除夹带在进气空气中的颗粒，第一过滤器下游的喷嘴阵列，以及阵列下游的第二过滤器。 喷嘴阵列被配置为便于降低进气的温度，并且第二过滤器被配置为排斥从喷嘴阵列排出的冷却液体，同时允许冷却的进气流过其中。

公开(公告)号：US08869537B2

公开(公告)日：2014-10-28

申请号：US12870177

申请日：2010-08-27

Applicant: Torsten Geis ,  Edward Brook

Inventor： Torsten Geis ,  Edward Brook

IPC: F02C7/00 ,  F02G3/00 ,  B01D39/00 ,  F01D17/16 ,  F01D17/02 ,  F02C9/22 ,  F02C7/05

CPC classification number: F01D17/02 ,  F01D17/16 ,  F02C7/05 ,  F02C9/22 ,  F05D2270/54 ,  F05D2270/708 ,  Y02T50/671

Abstract: A gas turbine engine and an apparatus for operating the gas turbine engine includes at least one microphone to detect the sound of impacts of particles, a recorder to record the sound of the impacts, an analyzer to analyze the sound of the impacts of the particles, and a store of sounds of impacts, the stored sounds of impacts correspond to unfavorable weather conditions. A comparator compares the sound of the impacts of particles with one or more sounds of impacts stored in the store 68 sounds of impacts and if the comparator determines that the sound of the impacts of particles matches one or more stored sounds of impacts, a signal is sent to a control system for the gas turbine engine to adjust the operation of the gas turbine engine such that it operates in a safe mode of operation.

Abstract translation: 燃气涡轮发动机和用于操作燃气涡轮发动机的装置包括至少一个麦克风，用于检测颗粒撞击的声音，用于记录撞击声的记录器，用于分析颗粒撞击的声音的分析仪， 并存储影响的声音，所存储的影响声音对应于不利的天气条件。 比较器将颗粒的影响的声音与存储在存储器68中的影响的声音的一个或多个影响声音进行比较，并且如果比较器确定颗粒的撞击的声音匹配一个或多个存储的冲击声，则信号为 发送到用于燃气涡轮发动机的控制系统以调节燃气涡轮发动机的操作，使得其在安全的操作模式下操作。