公开(公告)号：US08052767B2

公开(公告)日：2011-11-08

申请号：US13007612

申请日：2011-01-15

Applicant: Fred Charles Sands ,  Milton D. Jantzen

Inventor： Fred Charles Sands ,  Milton D. Jantzen

IPC: B01D39/00

CPC classification number: B64D33/02 ,  B64D2033/022 ,  B64D2033/0286 ,  F02C7/05 ,  Y02T50/671

Abstract: A modern jet engine inlet protection system that protects against large birds and operates autonomously, that is dormant in routine aircraft operations, that automatically actuates its protective device(s) only at the immediate point of need, then returning it (them) to a non-interfering position, including a RADAR system and a LIDAR system which detect birds entering the intended flight path of the aircraft, and fast computer-implemented computational algorithms that track and identify those from the detected set that are (1) projected to enter a zone which would lead to ingestion by the engine, and (2) of a size large enough that they would seriously damage the engine if ingested; that includes defensive mechanisms housed in the engine nacelle cowling or center hub, or in the fuselage structure that are instantaneously actuated shortly before arriving at the point of impact to shield, deflect, reduce the size of the approaching bird to an acceptable mass, or destroy it, and, that after the ingestion threat has passed, the devices are stowed/retracted or safely jettisoned.

公开(公告)号：US07963094B1

公开(公告)日：2011-06-21

申请号：US12657323

申请日：2010-01-19

Applicant: Francis J. Cupolo

Inventor： Francis J. Cupolo

IPC: F02C7/05 ,  F02C7/055

CPC classification number: F02C7/05 ,  B64D2033/022 ,  Y02T50/671

Abstract: In an aircraft turbofan or turbojet engine including a fan blade assembly mounted thereon rotating about the central axis of the engine, there are provided aerodynamically profiled rotating cutting rings arranged concentrically to the engine axis upstream of the fan blade assembly on which a bird traveling toward the engine will fragment to extravasations and evisceration to produce bird debris of a sufficiently low density to be safely ingested by the engine.

Abstract translation: 在包括安装在其上围绕发动机的中心轴线旋转的风扇叶片组件的飞行器涡轮风扇或涡轮喷气发动机中，提供了与风扇叶片组件上游的发动机轴同心布置的空气动力学异型旋转切割环， 发动机将分裂为外渗和内脏，以产生足够低密度的鸟类碎屑，以安全地被发动机摄取。

公开(公告)号：US20110076132A1

公开(公告)日：2011-03-31

申请号：US12873650

申请日：2010-09-01

Applicant: KRISTOFER JOHN BOTTOME

Inventor： KRISTOFER JOHN BOTTOME

IPC: F01B25/16

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。

公开(公告)号：US20110041474A1

公开(公告)日：2011-02-24

申请号：US12859806

申请日：2010-08-20

Applicant: Valerio Gerez ,  Claude Alain Mazur

Inventor： Valerio Gerez ,  Claude Alain Mazur

IPC: F02K9/38 ,  F01D25/00 ,  G01M15/00

CPC classification number: G07C5/0891 ,  B64D45/00 ,  B64D2033/022 ,  B64D2045/0095 ,  F01D21/003 ,  F01D21/04 ,  F02C7/05 ,  F02C7/057

Abstract: The invention relates to a method and a system for detecting the ingestion of an object by an aircraft turbine engine during a mission. The method includes the steps of acquiring during the mission digital images of the operating fan of the turbine engine, these images being acquired at an acquisition frequency proportional to the speed of rotation of the fan and to the number of blades of the fan (E10), identifying the different phases of the mission of the aircraft (E40), for each phase of the mission, comparing the images of the fan with at least one reference image corresponding to sound operation of the fan (E60), and, if necessary, identifying each abnormal image of the fan which differs from the corresponding reference image, the identification of an abnormal image of the fan corresponding to the crossing of an alert level for detecting the ingestion of an object by the turbine engine (E90).

Abstract translation: 本发明涉及一种用于在任务期间检测由飞行器涡轮发动机摄入物体的方法和系统。 该方法包括以下步骤：在任务期间获取涡轮发动机的操作风扇的数字图像，这些图像以与风扇的旋转速度成比例的获取频率和风扇的叶片数（E10）获取， 对于任务的每个阶段，识别飞机任务的不同阶段（E40），将风扇的图像与对应于风扇的声音操作（E60）的至少一个参考图像进行比较，并且如果需要， 识别与相应的参考图像不同的风扇的异常图像，识别与用于检测涡轮发动机摄入的物体的警报水平的交叉相对应的风扇的异常图像（E90）。

公开(公告)号：US07802433B2

公开(公告)日：2010-09-28

申请号：US11528219

申请日：2006-09-27

Applicant: Timothy J. Higgins

Inventor： Timothy J. Higgins

IPC: F02C7/00

CPC classification number: F02C7/042 ,  F02C7/05 ,  F02C7/052

Abstract: A method for operating a gas turbine engine including a compressor is provided. The method includes defining a predetermined concentration, placing at least one sensor in an inlet of the gas turbine engine, detecting a sand and dust concentration value using the at least one sensor; and deploying a boot to facilitate preventing particles from entering the compressor when the sand and dust concentration value equals or exceeds the predetermined concentration. The boot includes a plurality of fluid exit slots such that clean air is facilitated to be adhered to a flow path surface downstream from the boot.

Abstract translation: 提供了一种用于操作包括压缩机的燃气涡轮发动机的方法。 该方法包括定义预定浓度，将至少一个传感器放置在燃气涡轮发动机的入口中，使用该至少一个传感器检测砂尘浓度值; 并且当沙尘浓度值等于或超过预定浓度时，展开靴子以便于防止颗粒进入压缩机。 靴子包括多个流体出口槽，使得清洁空气便于粘附到靴子下游的流动路径表面。

公开(公告)号：US20100054919A1

公开(公告)日：2010-03-04

申请号：US12200087

申请日：2008-08-28

Applicant: Stephen David Hiner ,  Rahul Jaikaran Chillar ,  Bradly Aaron Kippel ,  Lisa Kamdar Ammann ,  Jack Thomas Clements ,  Marcus Carr Walters ,  Sebastien Cloarec ,  Marc Malivernay ,  Liberto Gandia

Inventor： Stephen David Hiner ,  Rahul Jaikaran Chillar ,  Bradly Aaron Kippel ,  Lisa Kamdar Ammann ,  Jack Thomas Clements ,  Marcus Carr Walters ,  Sebastien Cloarec ,  Marc Malivernay ,  Liberto Gandia

IPC: F04D29/70

CPC classification number: F01D25/32 ,  B01D45/08 ,  B01D46/0024 ,  B01D46/0031 ,  B01D46/0068 ,  B01D46/4236 ,  B01D46/4263 ,  B01D50/002 ,  B01D2277/20 ,  B01D2279/60 ,  F02C7/05 ,  F02C7/055 ,  F05D2260/96

Abstract: A system for use with an inlet of a gas turbine through which an airflow toward the gas turbine proceeds is provided and includes a first self-cleaning stage to remove dust, snow and ice from the airflow, a second water tight stage, disposed downstream from the first stage, to prevent aerosol droplets and aqueous solutions of deliquesced particulates, which include at least portions of the dust not removed by the first stage and which are re-released into the airflow from the first stage, from proceeding along the airflow and to remove solid particulates not removed by the first stage from the airflow, and a third water removal stage, disposed downstream from the second stage, to remove from the airflow aerosol droplets leaking from the second stage.

Abstract translation: 一种与燃气轮机的入口一起使用的系统，通过该进气口进入朝向燃气轮机的气流，并且包括第一自清洁台，用于从空气流中除去灰尘，雪和冰，第二防水台，设置在下游 第一阶段，以防止气溶胶微滴和潮解微粒的水溶液，其包括至少部分灰尘未被第一阶段除去并被再次释放到第一阶段的气流中，沿着气流进行到达 从气流中去除第一阶段未被除去的固体微粒，以及设置在第二阶段下游的第三除水阶段，以从第二阶段泄漏的气流中除去气溶胶微滴。

公开(公告)号：US07526921B2

公开(公告)日：2009-05-05

申请号：US11225556

申请日：2005-09-12

Applicant: Nicholas A. Williams ,  Kevin S. Dittmar

Inventor： Nicholas A. Williams ,  Kevin S. Dittmar

IPC: F02C7/20

CPC classification number: F02C7/25 ,  B64D41/00 ,  F01D25/24 ,  F02C7/045 ,  F02C7/05 ,  F02C7/20 ,  F05D2220/50 ,  Y02T50/44 ,  Y02T50/671

Abstract: An auxiliary power unit (APU) with integral firebox provides an integral unit for aircraft to utilize an APU without the use of a separate firebox. The present invention comprises a turbomachine intake air duct secured to an enclosure, the enclosure having a bleed air port extending from the combustor to outside of the enclosure, with an APU secured therein. The APU can be retrofitted to existing aircraft, or installed in newly-built aircraft.

Abstract translation: 带有整体防火箱的辅助动力装置（APU）为飞行器提供了一个整体单元，可以在不使用单独的火箱的情况下使用APU。 本发明包括一个固定在外壳上的涡轮机进气通道，该外壳具有一个从燃烧器延伸到外壳外部的排气口，其中APU固定在外壳内。 APU可以改装现有的飞机，也可以安装在新建的飞机上。

公开(公告)号：US20090067979A1

公开(公告)日：2009-03-12

申请号：US11695435

申请日：2007-04-02

Applicant: Michael Scott Braley ,  James D. Dorer ,  Gary D. Roberts

Inventor： Michael Scott Braley ,  James D. Dorer ,  Gary D. Roberts

IPC: F01D21/00

CPC classification number: F02C7/05 ,  F01D21/045 ,  F05D2300/603 ,  Y02T50/672

Abstract: A gas turbine fan blade containment assembly includes a fan case having an inner surface surrounding a jet engine fan and an outer surface. Mounted on the inner surface and across a blade containing region of the fan case is a load spreader layer for initially receiving a point load from a fan blade release (a “blade-out event”). A band layer is mounted to an outer surface of the fan case for carrying at least a portion of a hoop tensile load on the fan case resulting from the blade-out event, and separator film layer is mounted between the outer surface of the fan case and the band layer to retard the formation of stress concentrations in the band layer. In one embodiment, the load spreader layer includes a plurality of circumferentially-arrayed load spreader layer segments.

Abstract translation: 燃气轮机风扇叶片容纳组件包括具有围绕喷气发动机风扇和外表面的内表面的风扇壳体。 安装在内表面上并且跨过风扇壳体的刀片容纳区域是用于最初从风扇叶片释放（“刮刀事件”）接收点负载的负载撒布层。 带状层安装在风扇壳体的外表面上，用于承载由刮板输出事件导致的风扇壳体上的环向拉伸载荷的至少一部分，并且分离膜层安装在风扇壳体的外表面之间 和带状层，以延缓带状层中应力集中的形成。 在一个实施例中，负载撒布层包括多个周向排列的负载扩展层分段。

公开(公告)号：US07494316B2

公开(公告)日：2009-02-24

申请号：US11468036

申请日：2006-08-29

Applicant: Barry Barnett ,  David Denis

Inventor： Barry Barnett ,  David Denis

IPC: F03B11/02

CPC classification number: F01D9/042 ,  F02C7/05 ,  F05D2260/30

Abstract: A vane including a root, a tip and an airfoil portion extending between the root and the tip, the vane also including a button portion interconnecting the airfoil portion and the root. The button portion protrudes beyond a profile of the airfoil a distance less than the root. The button portion includes leading and trailing ends free of sharp edges. The leading and trailing ends respectively protrude beyond leading and trailing edges of the airfoil portion.

Abstract translation: 叶片包括根部，尖端和在根部和尖端之间延伸的翼型部分，叶片还包括将翼型部分和根部相互连接的按钮部分。 按钮部分突出超过翼型的轮廓，其距离小于根部。 按钮部分包括没有锋利边缘的前端和后端。 前端和尾端分别突出超过翼型部分的前缘和后缘。

公开(公告)号：US20070183887A1

公开(公告)日：2007-08-09

申请号：US11350494

申请日：2006-02-09

Applicant: Ioannis Alvanos ,  Bernard Andrews ,  Robert Charbonneau ,  Susan Tholen ,  Thurman Dabbs ,  Michael Bruskotter

Inventor： Ioannis Alvanos ,  Bernard Andrews ,  Robert Charbonneau ,  Susan Tholen ,  Thurman Dabbs ,  Michael Bruskotter

IPC: F04D29/70

CPC classification number: F01D25/32 ,  F02C7/05 ,  F05D2260/20 ,  F05D2260/607

Abstract: A material having a plurality of impurity collection spaces has an outer face facing into a cooling air flow stream for a gas turbine engine component. Impurities such as sand or dirt will collect in the plurality of spaces. In a disclosed embodiment, a honeycombed material is utilized.

Abstract translation: 具有多个杂质收集空间的材料具有面向燃气涡轮发动机部件的冷却空气流动流的外表面。 诸如沙子或污垢的杂质将聚集在多个空间中。 在公开的实施例中，使用蜂窝状材料。