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。

公开(公告)号：US20170051680A1

公开(公告)日：2017-02-23

申请号：US14828544

申请日：2015-08-18

Applicant: General Electric Company

Inventor： Thomas Lee BECKER, JR. ,  Craig Miller KUHNE

IPC: F02C9/18

CPC classification number: F02C9/18 ,  F01D5/18 ,  F01D9/06 ,  F01D17/162 ,  F02C3/13 ,  F05D2220/32 ,  F05D2240/122 ,  F05D2240/123 ,  F05D2260/606 ,  F05D2270/10 ,  Y02T50/673 ,  Y02T50/676

Abstract: An airflow injection nozzle for a stage of airflow injection nozzles located in a turbine section of the gas turbine engine is provided. The airflow injection nozzle includes a leading end positioned opposite of a trailing end, as well as a pressure side positioned opposite of a suction side. The airflow injection nozzle includes an opening positioned on the pressure side oriented generally in a flow direction of the gas turbine engine for injecting a flow of bleed air from a compressor section of the gas turbine engine into the turbine section of the gas turbine engine.

Abstract translation: 提供了一种用于位于燃气涡轮发动机的涡轮部分中的气流喷射喷嘴级的气流喷射喷嘴。 气流喷射喷嘴包括与后端相对的前端以及与吸力侧相对设置的压力侧。 气流喷射喷嘴包括位于通常在燃气涡轮发动机的流动方向上的压力侧上的开口，用于将来自燃气涡轮发动机的压缩机部分的排出气流喷射到燃气涡轮发动机的涡轮部分。

公开(公告)号：US20160333786A1

公开(公告)日：2016-11-17

申请号：US14711047

申请日：2015-05-13

Applicant: General Electric Company

Inventor： Christopher Charles GLYNN ,  Craig Miller KUHNE ,  Brandon Wayne MILLER ,  Darek Tomasz ZATORSKI

IPC: F02C7/20 ,  F02C3/04 ,  F01D25/24 ,  F01D25/28 ,  F01D25/16

Abstract: In one aspect the present subject matter is directed to a system for supporting shafts of an indirect-drive turbofan engine. The system includes a fan frame assembly that is coaxially aligned with a centerline of the turbofan engine and positioned forward of a reduction gear that couples a low pressure rotor shaft to a fan shaft. A compressor frame assembly is aligned with the centerline aft of the reduction gear and is positioned axially between a low pressure compressor and a high pressure compressor of the turbofan engine. A turbine frame assembly is coaxially aligned with the centerline and is positioned axially between a high pressure turbine and a low pressure turbine of the turbofan engine. The turbine frame assembly rotatably supports an aft end portion of a high pressure rotor shaft and an aft end portion of the low pressure rotor shaft.

Abstract translation: 在一个方面，本主题涉及一种用于支撑间接驱动涡扇风扇发动机的轴的系统。 该系统包括与涡轮风扇发动机的中心线同轴对准并位于将低压转子轴连接到风扇轴的减速齿轮前方的风扇框架组件。 压缩机框架组件与减速齿轮的中心线后方对准并且轴向定位在涡轮风扇发动机的低压压缩机和高压压缩机之间。 涡轮机框架组件与中心线同轴对准并且轴向定位在涡轮风扇发动机的高压涡轮机和低压涡轮机之间。 涡轮机架组件可旋转地支撑低压转子轴的后端部分和低压转子轴的后端部分。