公开(公告)号：US20160214727A1

公开(公告)日：2016-07-28

申请号：US14969640

申请日：2015-12-15

Applicant: General Electric Company

Inventor： Jeffrey Anthony HAMEL ,  Kurt David MURROW

IPC: B64D27/24 ,  B64D27/18

CPC classification number: B64D27/24 ,  B64C21/06 ,  B64D27/18 ,  B64D27/20 ,  B64D2027/026 ,  B64D2205/00 ,  Y02T50/166 ,  Y02T50/62 ,  Y10S903/905 ,  Y10S903/906 ,  Y10S903/907

Abstract: In one aspect the present subject matter is directed to a gas-electric propulsion system for an aircraft. The system may include a turbofan jet engine, an electric powered boundary layer ingestion fan that is coupled to a fuselage portion of the aircraft aft of the turbofan jet engine, and an electric generator that is electronically coupled to the turbofan jet engine and to the boundary layer ingestion fan. The electric generator converts rotational energy from the turbofan jet engine to electrical energy and provides at least a portion of the electrical energy to the boundary layer ingestion fan. In another aspect of the present subject matter, a method for propelling an aircraft via the gas-electric propulsion system is disclosed.

Abstract translation: 在一个方面，本主题涉及一种用于飞机的气电推进系统。 该系统可以包括涡轮风扇喷气发动机，耦合到涡轮风扇喷气发动机的飞机后部的机身部分的电动边界层摄入风扇，以及电动联接到涡轮风扇喷气发动机和边界的发电机 层摄取风扇。 发电机将来自涡轮风扇喷气发动机的旋转能量转换为电能，并将至少一部分电能提供给边界层摄取风扇。 在本主题的另一方面，公开了一种通过气电推进系统推进飞行器的方法。

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。