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。

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。

公开(公告)号：US20140116061A1

公开(公告)日：2014-05-01

申请号：US13660039

申请日：2012-10-25

Applicant: Barry BARNETT ,  Phillipe BONNIERE ,  Daniel ALECU

Inventor： Barry BARNETT ,  Phillipe BONNIERE ,  Daniel ALECU

IPC: F16D3/80 ,  F02C7/12

CPC classification number: F16D1/101 ,  F01D5/026 ,  F05D2260/20 ,  F16D2001/103 ,  Y02T50/675 ,  Y10T403/25 ,  Y10T464/10

Abstract: A gas turbine engine having a coupling element for coupling a first shaft to a second shaft, the second shaft being substantially axially aligned with the first shaft, the coupling element provided with an exterior surface that engages an opposing interior surface of the first shaft and an interior surface that engages an opposing exterior surface of the second shaft to facilitate torque transfer between the first shaft and the second shaft when rotated together, wherein the coupling element and at least one of the first and second shafts cooperate to define at least one fluid passageway therebetween.

Abstract translation: 一种燃气涡轮发动机，其具有用于将第一轴联接到第二轴的联接元件，所述第二轴与所述第一轴基本上轴向对齐，所述联接元件设置有与所述第一轴的相对的内表面接合的外表面， 内表面，其接合所述第二轴的相对的外表面，以便当一起旋转时促进在所述第一轴和所述第二轴之间的扭矩传递，其中所述联接元件和所述第一和第二轴中的至少一个协作以限定至少一个流体通道 之间。

公开(公告)号：US20140079530A1

公开(公告)日：2014-03-20

申请号：US13616230

申请日：2012-09-14

Applicant: Gordon FERCH ,  Daniel ALECU ,  Xiaoliu LIU ,  Barry BARNETT ,  Dileepan SIVALINGAM ,  Carmine FORGIONE

Inventor： Gordon FERCH ,  Daniel ALECU ,  Xiaoliu LIU ,  Barry BARNETT ,  Dileepan SIVALINGAM ,  Carmine FORGIONE

IPC: F01D25/14

CPC classification number: F01D15/10 ,  F02C7/12 ,  Y02T50/671 ,  Y02T50/675

Abstract: A system for cooling a generator mounted in the tail-cone of an engine. The system comprises a fairing, which receives through an inlet thereof air from a bypass duct and directs the bypass air towards a cavity of the tail-cone for cooling the generator. The bypass air is then expelled through an outlet of a support strut positioned in fluid communication with the tail-cone cavity. The fairing inlet and the strut outlet are both positioned in a plane substantially perpendicular to a longitudinal plane of the engine. In this manner, circulation of the bypass air through the fairing, the tail-cone cavity, and the strut may be achieved. The bypass air directed through the fairing further enables cooling of service lines accommodated in the fairing. A lobe mixer is further used to direct the fairing and shield the latter from core exhaust.

Abstract translation: 一种用于冷却安装在发动机尾锥中的发电机的系统。 该系统包括整流罩，其通过入口从旁路管道接收空气，并将旁路空气引导到尾锥的空腔以冷却发电机。 然后，旁路空气通过与尾锥腔流体连通的支撑支柱的出口排出。 整流罩入口和支柱出口都位于基本上垂直于发动机的纵向平面的平面内。 以这种方式，可以实现旁路空气通过整流罩，尾锥腔和支柱的循环。 引导通过整流罩的旁路空气进一步使得容纳在整流罩中的服务线的冷却。 进一步使用叶片混合器来引导整流罩并将其从核心排气屏蔽起来。

公开(公告)号：US20140077507A1

公开(公告)日：2014-03-20

申请号：US13617101

申请日：2012-09-14

Applicant: Barry BARNETT ,  Dileepan SIVALINGAM ,  Daniel ALECU ,  Xiaoliu LIU ,  Gordon FERCH ,  Carmine FORGIONE

Inventor： Barry BARNETT ,  Dileepan SIVALINGAM ,  Daniel ALECU ,  Xiaoliu LIU ,  Gordon FERCH ,  Carmine FORGIONE

IPC: H02K9/04

CPC classification number: H02K9/04 ,  F01D25/18 ,  F02C7/32 ,  Y02T50/671

Abstract: Systems and methods for pressurization of a generator in a gas turbine engine. The system may include a fluid valve for permitting or inhibiting airflow into a housing of the generator. The fluid valve may be in fluid communication with an air source within the engine, and may be configured to permit airflow into the housing of the generator when pressure within the housing is below a preset pressure threshold or range.

Abstract translation: 用于在燃气涡轮发动机中对发电机进行加压的系统和方法。 该系统可以包括用于允许或阻止气流进入发电机壳体的流体阀。 流体阀可以与发动机内的空气源流体连通，并且可以被配置为当壳体内的压力低于预设的压力阈值或范围时允许气流进入发电机的壳体。