公开(公告)号：WO2014109811A2

公开(公告)日：2014-07-17

申请号：PCT/US2013066531

申请日：2013-10-24

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SUCIU GABRIEL L ,  CHANDLER JESSE M ,  STAUBACH JOSEPH B ,  SUYDAM ADAM JOSEPH

CPC classification number: B64D27/14 ,  F02C7/36 ,  F02K3/06

Abstract: A gas turbine engine has a core engine incorporating a turbine, and a manifold positioned downstream of the turbine. The manifold delivers gas downstream of the turbine into at least two nacelles, with each of the nacelles receiving a fan rotor. The fan rotor is fixed to rotate with a tip turbine mounted at a radially outer location of the fan rotor, with the tip turbine being in the path of gases from the manifold. An aircraft is also disclosed.

Abstract translation: 燃气涡轮发动机具有并入涡轮的核心发动机和位于涡轮下游的歧管。 歧管将涡轮下游的气体输送到至少两个机舱中，每个机舱接收风扇转子。 风扇转子被固定以随着安装在风扇转子的径向外部位置处的尖端涡轮机旋转，其中尖端涡轮机处于来自歧管的气体的路径中。 还披露了一架飞机。

公开(公告)号：WO2014193515A3

公开(公告)日：2015-02-26

申请号：PCT/US2014023997

申请日：2014-03-12

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SUCIU GABRIEL L ,  CHANDLER JESSE M

IPC: F02K1/62 ,  F02K1/32 ,  F02K3/06

CPC classification number: F02K1/70 ,  B64D29/04 ,  B64D33/04 ,  F02C3/10 ,  F02K1/60 ,  F02K1/605 ,  F02K3/00 ,  F05D2250/314

Abstract: An engine system has a gas generator, a bi-fi wall surrounding at least a portion of the gas generator, a casing surrounding a fan, and the casing having first and second thrust reverser doors which in a deployed position abut each other and the bi-fi wall.

Abstract translation: 发动机系统具有气体发生器，围绕气体发生器的至少一部分的双壁壁，围绕风扇的壳体，以及具有第一和第二推力反向器门的壳体，所述第一和第二推力反向器门处于展开位置彼此邻接并且所述双 -fi墙。

公开(公告)号：WO2015069358A3

公开(公告)日：2015-07-16

申请号：PCT/US2014051600

申请日：2014-08-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SUCIU GABRIEL L ,  CHANDLER JESSE M

IPC: F02C7/20 ,  F01D9/04 ,  F01D25/24 ,  F02C7/24 ,  F02K1/04

CPC classification number: F02C7/20 ,  F01D25/26 ,  F01D25/28 ,  F02C3/04 ,  F02C7/24 ,  F02K1/822 ,  F05D2220/32 ,  F05D2300/20 ,  F05D2300/6033 ,  F23R3/007 ,  Y02T50/672 ,  Y02T50/675

Abstract: A gas turbine engine includes a core engine including a central engine axis and a nacelle surrounding the core engine. At least a portion of the nacelle is axially movable relative to the core engine between open and fully closed positions. A ceramic-based liner is located at an aft portion of the core engine. The ceramic-based component mechanically interfaces with the movable portion of the nacelle when the nacelle is in the fully closed position. A turbine section and a method of accommodating thermally-induced dimensional change of engine components are also disclosed.

Abstract translation: 燃气涡轮发动机包括具有中心发动机轴线和围绕核心发动机的机舱的核心发动机。 机舱的至少一部分在开放位置和完全关闭位置之间相对于核心发动机可轴向移动。 陶瓷基衬套位于核心发动机的后部。 当机舱处于完全关闭位置时，陶瓷基部件与机舱的可移动部分机械地接合。 还公开了涡轮部分和容纳发动机部件的热致尺寸变化的方法。

公开(公告)号：WO2014197056A3

公开(公告)日：2015-03-05

申请号：PCT/US2014025163

申请日：2014-03-13

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SUCIU GABRIEL L ,  CHANDLER JESSE M

IPC: F02K1/60 ,  F02K1/11

CPC classification number: F02K1/70 ,  F02K1/06 ,  F02K1/52 ,  F02K1/60 ,  F02K1/62 ,  F05D2220/323 ,  F05D2240/40

Abstract: A nozzle assembly for a dual gas turbine engine propulsion system includes a housing mountable proximate to a first bypass passage of a first gas turbine engine and a second bypass passage of a second gas turbine engine, first and second upper doors, and first and second lower doors. Each of the first and second upper doors and the first and second lower doors are pivotally mounted to the housing for movement between a stowed position and a deployed position in which airflow through the first and second bypass passages is redirected relative to respective centerline axes of the first and second gas turbine engines.

Abstract translation: 一种用于双燃气涡轮发动机推进系统的喷嘴组件，包括靠近第一燃气涡轮发动机的第一旁通通道安装的壳体和第二燃气涡轮发动机的第二旁通通道，第一和第二上部门，以及第一和第二下部 门。 第一和第二上部门以及第一和第二下部门中的每一个都枢转地安装到壳体上，以在收起位置和展开位置之间移动，在该位置中，穿过第一和第二旁路通道的气流相对于相应的中心线 第一和第二燃气涡轮发动机。

公开(公告)号：WO2014078003A3

公开(公告)日：2014-08-07

申请号：PCT/US2013065337

申请日：2013-10-17

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SUCIU GABRIEL L ,  EPSTEIN ALAN H ,  LORD WESLEY K ,  CHANDLER JESSE M

IPC: F02C7/052 ,  F02C7/12

CPC classification number: F01D25/08 ,  F02C7/052 ,  Y02T50/675

Abstract: A gas turbine engine includes a nose cone at an inlet end, and spaced radially inwardly of a nacelle. A compressor is downstream of the nose cone. A core inlet delivers air downstream of the nose cone into the compressor. An inlet particle separator includes a manifold for delivering air radially outwardly of the core inlet. Air delivered by the inlet particle separator passes over a heat exchanger before passing to an outlet.

Abstract translation: 燃气涡轮发动机在入口端处包括鼻锥，并且在机舱的径向内侧间隔开。 压缩机位于机头锥体的下游。 一个核心入口将空气锥形下游的空气输送到压缩机中。 入口颗粒分离器包括用于向核心入口径向向外输送空气的歧管。 由入口颗粒分离器输送的空气在通过出口之前通过热交换器。