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    ACTIVE TURBINE TIP CLEARANCE CONTROL SYSTEM
    1.
    发明申请
    ACTIVE TURBINE TIP CLEARANCE CONTROL SYSTEM 有权
    主动涡轮提升间隙控制系统

    公开(公告)号：US20130156541A1

    公开(公告)日：2013-06-20

    申请号：US13326434

    申请日：2011-12-15

    Applicant: Andreas ELEFTHERIOU ,  Daniel ALECU

    Inventor： Andreas ELEFTHERIOU ,  Daniel ALECU

    IPC: F01D17/00 ,  F01D5/02

    CPC classification number: F01D11/20 ,  F01D11/22 ,  F01D11/24

    Abstract: An active tip clearance control (ATCC) system of a gas turbine engine includes an ejector to selectively drive an air flow passing through the ATCC system. A high pressure air flow as a motive flow of the ejector is controlled by a valve according to engine operation requirements.

    Abstract translation: 燃气涡轮发动机的主动顶尖间隙控制（ATCC）系统包括用于选择性地驱动通过ATCC系统的空气流的喷射器。 作为喷射器的动力流动的高压空气流由根据发动机操作要求的阀门控制。

    SWIRL REDUCING GAS TURBINE ENGINE RECUPERATOR
    2.
    发明申请
    SWIRL REDUCING GAS TURBINE ENGINE RECUPERATOR 有权
    涡轮减速机涡轮发动机重新启动

    公开(公告)号：US20120216544A1

    公开(公告)日：2012-08-30

    申请号：US13036463

    申请日：2011-02-28

    Applicant: Andreas ELEFTHERIOU ,  David Menheere ,  Daniel Alecu ,  Darius Jehangir Karanjia ,  Daniel Van Den Ende

    Inventor： Andreas ELEFTHERIOU ,  David Menheere ,  Daniel Alecu ,  Darius Jehangir Karanjia ,  Daniel Van Den Ende

    IPC: F02C7/10 ,  F28D7/00

    CPC classification number: F28D21/0003 ,  F02C7/08 ,  F02C7/10 ,  F02C7/143 ,  F28D9/0018 ,  F28F2250/102 ,  F28F2265/26 ,  F28F2265/30 ,  Y02T50/675

    Abstract: A gas turbine engine recuperator recuperator including exhaust passages providing fluid flow communication between an exhaust inlet and an exhaust outlet, the exhaust inlet being oriented to receive exhaust flow from a turbine of the engine and the exhaust outlet being oriented to deliver the exhaust flow to atmosphere, the exhaust passages having an arcuate profile in a plane perpendicular to a central axis of the recuperator to reduce a swirl of the exhaust flow. Air passages are in heat exchange relationship with the exhaust passages and providing fluid flow communication between an air inlet and an air outlet, design to sealingly respective plenum of the gas turbine engine.

    Abstract translation: 一种燃气涡轮发动机换热器换热器，包括排气通道，其提供排气入口和排气出口之间的流体流动连通，所述排气入口被定向成接收来自所述发动机的涡轮机的排气流，所述排气出口被定向成将排气流输送到大气 排气通道在垂直于换热器的中心轴的平面中具有弧形轮廓，以减少排气流的漩涡。 空气通道与排气通道处于热交换关系，并且在空气入口和空气出口之间提供流体流动连通，设计为燃气涡轮发动机的密封相应的气室。

    TURBINE ENGINE HEAT RECUPERATOR SYSTEM
    3.
    发明申请
    TURBINE ENGINE HEAT RECUPERATOR SYSTEM 有权
    涡轮发动机热回收系统

    公开(公告)号：US20130255268A1

    公开(公告)日：2013-10-03

    申请号：US13435051

    申请日：2012-03-30

    Applicant: Andreas ELEFTHERIOU ,  Daniel ALECU ,  David MENHEERE

    Inventor： Andreas ELEFTHERIOU ,  Daniel ALECU ,  David MENHEERE

    IPC: F02C7/10

    CPC classification number: F02C7/08 ,  F01D25/30 ,  F05D2270/17

    Abstract: A gas turbine engine recuperator system includes a heat recuperator positioned in a gas turbine exhaust gas duct for recovering heat from turbine exhaust gases to preheat a compressor flow being supplied to the combustor. A continuous bleed flow of the turbine exhaust gases is provided to bypass the heat recuperator. The continuous bleed flow of the turbine exhaust gases is adjustable to reduce turbine exhaust gas pressure loss at a high engine operation level and to provide efficient heat recovery at low and/or medium engine operation levels.

    Abstract translation: 燃气涡轮发动机换热器系统包括定位在燃气轮机废气管道中的热回收器，用于从涡轮废气回收热量以预热供应到燃烧器的压缩机流。 提供涡轮废气的连续排出流以绕过热交换器。 涡轮废气的连续排放流量是可调节的，以在高发动机操作水平下降低涡轮机废气压力损失并且在低和/或中等发动机运行水平下提供有效的热回收。

    DIFFUSING GAS TURBINE ENGINE RECUPERATOR
    4.
    发明申请
    DIFFUSING GAS TURBINE ENGINE RECUPERATOR 有权
    扩口式涡轮发动机重新起动

    公开(公告)号：US20120216543A1

    公开(公告)日：2012-08-30

    申请号：US13036428

    申请日：2011-02-28

    Applicant: Andreas ELEFTHERIOU ,  David Menheere ,  Daniel Alecu ,  Darius Jehangir Karanjia

    Inventor： Andreas ELEFTHERIOU ,  David Menheere ,  Daniel Alecu ,  Darius Jehangir Karanjia

    IPC: F02C7/10 ,  F02C7/14

    CPC classification number: F02C7/10 ,  F02C7/08 ,  F02C7/14 ,  F05D2220/32 ,  F05D2260/213 ,  F05D2260/96 ,  F28D9/0018 ,  F28D21/0003 ,  F28D2021/0026 ,  F28F13/08

    Abstract: A gas turbine engine recuperator including exhaust passages providing fluid flow communication between an exhaust inlet and an exhaust outlet, the exhaust inlet being oriented to receive exhaust flow from a turbine of the engine and the exhaust outlet being oriented to deliver the exhaust flow to atmosphere, the exhaust inlet having a smaller cross-sectional area than that of the exhaust outlet, and a cross sectional area of each exhaust passage progressively increasing from the exhaust inlet to the exhaust outlet such as to diffuse the exhaust flow. Air passages are in heat exchange relationship with the exhaust passages and provide fluid flow communication between an air inlet and an air outlet designed to sealingly engage respective plenums of the gas turbine engine.

    Abstract translation: 一种燃气涡轮发动机换热器，包括排气通道，其提供排气入口和排气出口之间的流体流动连通，所述排气入口被定向为接收来自所述发动机的涡轮机的排气流，所述排气出口被定向成将排气流输送到大气， 排气入口具有比排气出口小的横截面面积，并且每个排气通道的横截面面积从排气入口逐渐增加到排气出口，从而扩散排气流。 空气通道与排气通道处于热交换关系，并且在空气入口和设计成密封地接合燃气涡轮发动机的各个通风室的空气出口之间提供流体流动连通。

    CASING FOR AN AIRCRAFT TURBOFAN BYPASS ENGINE
    5.
    发明申请
    CASING FOR AN AIRCRAFT TURBOFAN BYPASS ENGINE 有权
    航空飞行器旁路发动机

    公开(公告)号：US20130177410A1

    公开(公告)日：2013-07-11

    申请号：US13344057

    申请日：2012-01-05

    Applicant: Andreas ELEFTHERIOU ,  David MENHEERE ,  David DENIS

    Inventor： Andreas ELEFTHERIOU ,  David MENHEERE ,  David DENIS

    IPC: F01D25/24 ,  F01D1/04

    CPC classification number: F01D9/065 ,  F01D25/162 ,  F01D25/24 ,  F05D2230/232 ,  F05D2230/237

    Abstract: A casing for an aircraft turbofan bypass engine includes an outer ring, an inner hub and a plurality of struts radially extending therebetween. An annular portion of an engine core casing having an outer wall and an inner wall, is disposed between the outer ring and inner hub, forming an annular splitter supporting an upstream splitter tip structure. The annular splitter further includes an intermediate wall disposed in the annular splitter fixed to the outer wall and the struts, to distribute loads from the annular splitter box to the struts.

    Abstract translation: 用于飞行器涡扇风扇旁路发动机的壳体包括外环，内毂和在它们之间径向延伸的多个支柱。 具有外壁和内壁的发动机芯壳的环形部分设置在外环和内毂之间，形成支撑上游分流器顶端结构的环形分流器。 环形分离器还包括设置在固定到外壁和支柱的环形分配器中的中间壁，以将负载从环形分配箱分配到支柱。

    ENGINE CASE WITH WASH SYSTEM
    6.
    发明申请
    ENGINE CASE WITH WASH SYSTEM 有权
    发动机箱与洗衣机

    公开(公告)号：US20120134777A1

    公开(公告)日：2012-05-31

    申请号：US12956405

    申请日：2010-11-30

    Applicant: Andreas ELEFTHERIOU ,  David MENHEERE ,  Richard IVAKITCH ,  Enzo MACCHIA

    Inventor： Andreas ELEFTHERIOU ,  David MENHEERE ,  Richard IVAKITCH ,  Enzo MACCHIA

    IPC: F01D25/24

    CPC classification number: F01D25/002 ,  F01D25/24

    Abstract: A gas turbine engine includes a structure defining a circumferential passage in fluid communication with an internal passage in at least one strut radially extending into the engine, circumferential passage also in fluid communication with a plurality or nozzles or jets to provide a wash manifold integrated with the engine casing structure. One or more nozzles are provided in the manifold for directing a washing fluid injected into the duct.

    Abstract translation: 燃气涡轮发动机包括限定在径向延伸到发动机中的至少一个支柱中的内部通道流体连通的圆周通道的结构，圆周通道也与多个喷嘴或喷嘴流体连通，以提供与 发动机套管结构。 在歧管中设置一个或多个喷嘴，用于引导注入到管道中的洗涤流体。

    FABRICATED INTERMEDIATE CASE WITH ENGINE MOUNTS
    10.
    发明申请
    FABRICATED INTERMEDIATE CASE WITH ENGINE MOUNTS 有权
    制造中间件与发动机安装

    公开(公告)号：US20130058778A1

    公开(公告)日：2013-03-07

    申请号：US13224379

    申请日：2011-09-02

    Applicant: Andreas ELEFTHERIOU ,  David MENHEERE ,  Quantai LIU

    Inventor： Andreas ELEFTHERIOU ,  David MENHEERE ,  Quantai LIU

    IPC: F02C7/20

    CPC classification number: F02C7/20 ,  F05D2230/232

    Abstract: A fabricated engine case has a plurality of circumferentially spaced struts radially extending between an outer case and an inner case. A mount apparatus is affixed to the outer case of the engine case. The mount apparatus is a mount base radially spaced apart from a circumferential skin of the outer case and a load bearing member extending radially inwardly to connect the mount base to an outer end of one of the struts.

    Abstract translation: 制造的发动机壳体具有在外壳和内壳之间径向延伸的多个周向间隔的支柱。 发动机壳体的外壳附着有安装装置。 安装装置是与外壳的圆周表皮径向间隔开的安装基座和径向向内延伸的承载构件，以将安装基座连接到一个支柱的外端。

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