公开(公告)号：US20190136710A1

公开(公告)日：2019-05-09

申请号：US16234892

申请日：2018-12-28

Applicant: General Electric Company

Inventor： Andrew BREEZE-STRINGFELLOW ,  Syed Arif KHALID ,  Leroy Harrington SMITH, JR.

IPC: F01D17/16 ,  F02K1/46 ,  B64C11/00 ,  B64C11/18 ,  B64C11/46 ,  F02K3/02 ,  F02C6/20 ,  B64C11/48 ,  F01D9/02

Abstract: An unducted thrust producing system has a rotating element with an axis of rotation and a stationary element. The rotating element includes a plurality of blades, each having a blade root proximal to the axis, a blade tip remote from the axis, and a blade span measured between the blade root and the blade tip. The rotating element has a load distribution such that at any location between the blade root and 30% span the value of ΔRCu in the air stream is greater than or equal to 60% of the peak ΔRCu in the air stream.

公开(公告)号：US20160010487A1

公开(公告)日：2016-01-14

申请号：US14771975

申请日：2013-10-23

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Andrew BREEZE-STRINGFELLOW ,  Darek Tomasz ZATORSKI ,  Richard David CEDAR

IPC: F01D17/16 ,  F01D9/02

Abstract: A unshrouded vane assembly for an unducted propulsion system includes a plurality of vanes which have non-uniform characteristics configured to generate a desired vane exit swirl angle.

Abstract translation: 用于未被牵引的推进系统的无罩叶片组件包括具有不均匀特性的多个叶片，其构造成产生期望的叶片出口涡流角。

公开(公告)号：US20160333734A1

公开(公告)日：2016-11-17

申请号：US15145894

申请日：2016-05-04

Applicant: GENERAL ELECTRIC COMPANY

Inventor： William Joseph BOWDEN ,  Andrew BREEZE-STRINGFELLOW ,  Richard David CEDAR ,  Syed Arif KHALID ,  Patrick John LONNEMAN ,  Aleksander Piotr PASIECZNY ,  Daniel Lawrence TWEEDT

IPC: F01D25/04 ,  F01D5/02 ,  F01D25/24 ,  F01D9/04 ,  F04D29/32 ,  F04D29/38

CPC classification number: B64C11/14 ,  B64C2201/165 ,  B64D33/02 ,  B64D2027/005 ,  F01D5/02 ,  F01D9/041 ,  F01D25/04 ,  F01D25/24 ,  F02C6/206 ,  F02C7/05 ,  F04D29/329 ,  F04D29/38 ,  F05D2220/325 ,  F05D2220/36 ,  F05D2240/80 ,  F05D2250/184 ,  F05D2260/607 ,  F05D2260/96 ,  Y02T50/66 ,  Y02T50/671 ,  Y02T50/675

Abstract: An unducted thrust producing system is provided that can include a rotating element having an axis of rotation about a central longitudinal axis and comprising a plurality of blades attached to a spinner; a stationary element positioned aft of the rotating element; and an inlet positioned between the rotating element and the stationary element such that the inlet passes radially inward of the stationary element. The rotating element defines an annular valley positioned between a first annular crown and a second annular crown, and the inlet defines an open area positioned aft of the second annular crown.

Abstract translation: 提供了一种未引入的推力产生系统，其可以包括旋转元件，该旋转元件具有围绕中心纵向轴线的旋转轴线，并且包括附接到旋转器的多个叶片; 位于旋转元件后方的固定元件; 以及位于旋转元件和固定元件之间的入口，使得入口径向向内固定固定元件。 旋转元件限定位于第一环形冠和第二环形冠之间的环形谷，并且入口限定位于第二环形冠的后方的开放区域。

公开(公告)号：US20160333729A1

公开(公告)日：2016-11-17

申请号：US14708878

申请日：2015-05-11

Applicant: General Electric Company

Inventor： Brandon Wayne MILLER ,  Andrew BREEZE-STRINGFELLOW ,  Darek Tomasz ZATORSKI

IPC: F01D17/16 ,  F02C7/042 ,  F02K3/04

CPC classification number: F01D17/162 ,  F01D9/041 ,  F02C7/042 ,  F02K3/04 ,  F02K3/06 ,  F04D27/0246 ,  F04D27/0292 ,  F04D29/563 ,  F05D2220/36 ,  F05D2270/09 ,  Y02T50/673

Abstract: A gas turbine engine including a core engine and a fan configured in mechanical communication with the core engine is provided. The gas turbine engine also includes a plurality of outlet guide vanes positioned downstream from the fan along an axial direction defined by the gas turbine engine. The plurality of outlet guide vanes extend outwardly from an outer casing the core engine generally along the radial direction defined by the gas turbine engine. Each outlet guide vane defines a center of pressure and a pitch axis. The pitch axis of each outlet guide vane is positioned forward the center of pressure of each outlet guide vane such that in the event of a mechanical failure, the outlet guide vane defaults to a neutral position.

Abstract translation: 提供一种燃气涡轮发动机，其包括核心发动机和与该核心发动机机械连通的风扇。 燃气涡轮发动机还包括沿着由燃气涡轮发动机限定的轴向方向定位在风扇下游的多个出口导向叶片。 多个出口导向叶片通常沿着由燃气涡轮发动机限定的径向方向从核心发动机的外壳向外延伸。 每个出口导向叶片限定了压力中心和俯仰轴。 每个出口引导叶片的俯仰轴线位于每个出口引导叶片的压力中心的前方，使得在机械故障的情况下，出口引导叶片默认为中立位置。

公开(公告)号：US20150354502A1

公开(公告)日：2015-12-10

申请号：US14761698

申请日：2014-01-14

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Craig Miller KUHNE ,  Christopher Charles GLYNN ,  Randy M. Vondrell ,  Andrew BREEZE-STRINGFELLOW ,  Kurt David MURROW ,  Darek T. ZATORSKI ,  Donald Scott YEAGER ,  Nicholas Rowe DINSMORE ,  Samuel Jacob MARTIN ,  Donald Albert BRADLEY

IPC: F02K3/06 ,  F02C3/073

CPC classification number: F02C7/36 ,  F02C3/073 ,  F02C3/107 ,  F02K3/06 ,  F02K3/072 ,  F05D2260/4031 ,  Y02T50/672

Abstract: A gas turbine engine comprises a fan, a compressor, a turbine having first stage blades and second stage blades, the first stage blades rotates in a first direction and the second stage blades rotates in a second direction opposite the first direction. The first stage blades are directly adjacent to one another, a drive in operable input connection with the fan and in operable output connection with the first stage blades and the second stage blades, the first stage blades and the second stage blades driving the fan through the drive.

Abstract translation: 燃气涡轮发动机包括风扇，压缩机，具有第一级叶片和第二级叶片的涡轮机，第一级叶片沿第一方向旋转，第二级叶片沿与第一方向相反的第二方向旋转。 第一级叶片彼此直接相邻，与风扇可操作地输入连接的驱动器和与第一级叶片和第二级叶片可操作地输出连接，第一级叶片和第二级叶片驱动风扇通过 驾驶。