公开(公告)号：EP2971534A4

公开(公告)日：2016-11-09

申请号：EP14770159

申请日：2014-03-11

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MORIN BRUCE L ,  LORD WESLEY K

IPC: F01D5/14 ,  F02C7/24

CPC classification number: F01D25/04 ,  F01D5/02 ,  F01D5/141 ,  F01D9/02 ,  F01D17/14 ,  F02K1/15 ,  F02K1/16 ,  F05D2220/36 ,  F05D2260/96

公开(公告)号：EP2932068A4

公开(公告)日：2016-01-13

申请号：EP13861588

申请日：2013-02-20

Applicant: UNITED TECHNOLOGIES CORP

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

IPC: F02C7/12 ,  B64D27/10 ,  B64D33/02 ,  B64D33/10 ,  F01D25/12 ,  F01D25/24 ,  F02C7/052 ,  F02C7/36 ,  F02K3/00

CPC classification number: F02C7/36 ,  B64D33/02 ,  B64D33/10 ,  B64D2033/022 ,  F02C7/052 ,  F05D2220/324 ,  F05D2220/325 ,  F05D2250/44 ,  F05D2260/20 ,  Y02T50/675

Abstract: A gas turbine engine comprises an outer nacelle. A nose cone is spaced radially inward of the outer nacelle. The nose cone defines a particle separator for directing an outer air flow and an inner airflow. The inner airflow is directed through a core inlet to a compressor. The engine further comprises a drive gear system for driving at least one propeller. A variable pitch control system may alter a pitch angle of the at least one propeller. Some of the outer air flow is directed to at least one of the drive gear system and the pitch control system.

Abstract translation: 燃气涡轮发动机包括外部机舱。 鼻锥在外部机舱的径向内侧隔开。 鼻锥限定了用于引导外部空气流和内部空气流的颗粒分离器。 内部气流被引导通过核心入口到压缩机。 发动机还包括用于驱动至少一个螺旋桨的驱动齿轮系统。 可变桨距控制系统可以改变至少一个螺旋桨的桨距角。 外部空气流中的一些被引导到驱动齿轮系统和俯仰控制系统中的至少一个。

公开(公告)号：EP2820270A4

公开(公告)日：2015-12-02

申请号：EP13754643

申请日：2013-02-18

Applicant: UNITED TECHNOLOGIES CORP

Inventor： GILSON JONATHAN ,  MORIN BRUCE L ,  REBA RAMONS A ,  TOPOL DAVID A ,  LORD WESLEY K

IPC: F02C7/045 ,  F01D9/04 ,  F02C7/24 ,  F02K3/06 ,  F04D29/66

CPC classification number: F01D9/041 ,  F01D25/162 ,  F02C3/107 ,  F02K3/06 ,  F04D29/544 ,  F04D29/667 ,  F05D2220/36 ,  F05D2240/12 ,  F05D2250/191 ,  F05D2250/38 ,  F05D2260/40311 ,  F05D2260/96 ,  F05D2260/961

Abstract: A fan section for a gas turbine engine has a fan rotor with a plurality of fan blades. A plurality of exit guide vanes are positioned to be downstream of the fan rotor. The fan rotor is driven through a gear reduction relative to a turbine section. The exit guide vanes are desired to address resultant sound from interaction of wakes from the fan blades across exit guide vanes. A gas turbine engine incorporating a fan section is also disclosed.

Abstract translation: 用于燃气涡轮发动机的风扇部分具有带多个风扇叶片的风扇转子。 多个出口导向叶片位于风扇转子的下游。 风扇转子通过相对于涡轮部分的齿轮减速而被驱动。 出口导向叶片需要通过来自风扇叶片的离开引导叶片的相互作用来解决合成的声音。 还公开了一种并入风扇部分的燃气涡轮发动机。

公开(公告)号：EP2971727A4

公开(公告)日：2016-11-16

申请号：EP13878444

申请日：2013-12-18

Applicant: UNITED TECHNOLOGIES CORP

Inventor： LORD WESLEY K ,  MALECKI ROBERT E

IPC: F02K1/30 ,  B64D33/04 ,  F02C7/00 ,  F02K1/28

CPC classification number: F02K3/06 ,  B64D33/04 ,  B64D2033/0286 ,  F01D25/24 ,  F02C3/04 ,  F02K1/78 ,  F05D2220/32 ,  F05D2240/24 ,  F05D2240/35 ,  F05D2250/73

Abstract: A fan nozzle for an aircraft gas turbine engine is comprised of a core engine cowl that is disposed within a fan cowl so that an air flow area is defined therebetween. The core engine cowl and fan cowl are disposed around a horizontal central plane. The fan cowl has a substantially circular shape and is formed of an upper substantially semi-circular portion having a first radius and a lower substantially semi-circular portion having a second radius. The core engine cowl has a substantially circular shape and is formed of an upper substantially semi-circular portion having a third radius and a lower substantially semi-circular portion having a third radius. The upper substantially semi-circular portion of the core engine cowl includes a left arcuate member and a right arcuate member. The second radius is less than the first radius and the third radius is less than the fourth radius.

Abstract translation: 用于飞机燃气涡轮发动机的风扇喷嘴由设置在风扇整流罩内的核心发动机罩组成，从而在其间限定空气流动区域。 核心发动机罩和风扇罩布置在水平中心平面周围。 风扇整流罩具有大致圆形的形状，并且由具有第一半径的上部大致半圆形部分和具有第二半径的下部基本上半圆形部分形成。 核心发动机罩具有大致圆形形状，并且由具有第三半径的上部大致半圆形部分和具有第三半径的下部基本上半圆形部分形成。 核心发动机罩的上部大致半圆形的部分包括一个左弧形部件和一个右弧形部件。 第二半径小于第一半径，第三半径小于第四半径。

公开(公告)号：EP2964924A4

公开(公告)日：2016-11-09

申请号：EP14759888

申请日：2014-02-26

Applicant: UNITED TECHNOLOGIES CORP

Inventor： QIU YUAN J ,  MILLER ROBERT M ,  LORD WESLEY K ,  HENDRICKS GAVIN

IPC: F02C7/04 ,  F02C7/00 ,  F02K3/06

CPC classification number: F02C7/04 ,  B64D2033/0286 ,  F01D5/02 ,  F01D17/105 ,  F01D25/24 ,  F02C3/04 ,  F02K3/06 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2240/303 ,  F05D2250/323 ,  F05D2250/511 ,  F05D2260/40 ,  Y02T50/671

Abstract: A gas turbine engine that includes a fan nacelle and a core nacelle that provide a bypass flow path radially between. The fan nacelle has an inlet including a throat. The inlet has an inlet forward-most point. A fan is arranged in the bypass flow path and rotatable about an axis. The fan has a leading edge recessed from the inlet forward-most point an inlet length in an axial direction. A spinner has a spinner length from a spinner forward-most point to the leading edge. A ratio of the spinner length to inlet length is equal to or greater than about 0.5.

Abstract translation: 一种燃气涡轮发动机，其包括在其之间径向提供旁通流动路径的风扇机舱和核心机舱。 风扇机舱具有包括喉部的入口。 入口具有入口最前面的点。 风扇布置在旁路流动路径中并可围绕轴线旋转。 风扇具有从入口最前端凹入的前缘，其沿轴向方向入口长度。 旋转器的旋转器长度从最远点到最前沿。 旋转器长度与入口长度的比例等于或大于约0.5。

公开(公告)号：EP2812558A4

公开(公告)日：2015-11-04

申请号：EP13747051

申请日：2013-02-05

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SUCIU GABRIEL L ,  LORD WESLEY K ,  DYE CHRISTOPHER

IPC: F02K3/06 ,  F02C7/00 ,  F02K3/02 ,  F02K5/00

CPC classification number: F02C3/145 ,  F02C7/36 ,  F02K3/025 ,  F05D2250/314

Abstract: A gas turbine engine includes a propulsion unit mounted to rotate about a first axis, and a core engine mounted to rotate about a second axis, and wherein the first and second axes are non-parallel. A gas turbine engine includes a propulsion unit driven by a free turbine which is adjacent to the propulsion unit and an associated fan, and having a gas generator core engine including a compressor, combustor and turbine section. A method is also disclosed.