公开(公告)号：US11685542B2

公开(公告)日：2023-06-27

申请号：US16891337

申请日：2020-06-03

Applicant: General Electric Company

Inventor： Daniel Alan Niergarth ,  Randy M. Vondrell ,  Brandon Wayne Miller ,  Patrick Michael Marrinan ,  Lawrence Chih-Hui Cheung ,  Nikolai N. Pastouchenko

IPC: B64D27/10 ,  B64D27/24 ,  B64D33/08 ,  F02K5/00 ,  F02C7/14 ,  F02C6/20 ,  B64C11/00 ,  B64C21/06 ,  F01D15/10 ,  F01D15/12 ,  F02K3/062 ,  F04D29/056 ,  F04D29/063 ,  F04D29/32 ,  F04D29/58 ,  B64D27/02

CPC classification number: B64D33/08 ,  B64C11/001 ,  B64C21/06 ,  B64D27/10 ,  B64D27/24 ,  F01D15/10 ,  F01D15/12 ,  F02C6/206 ,  F02C7/14 ,  F02K3/062 ,  F02K5/00 ,  F04D29/056 ,  F04D29/063 ,  F04D29/325 ,  F04D29/582 ,  B64D2027/026 ,  F05D2220/323 ,  F05D2260/213 ,  F05D2260/98 ,  Y02T50/60

Abstract: A propulsion system for an aircraft having an aft end is provided herein. The propulsion system can include an electric propulsion engine defining a central axis. The electric propulsion engine can include an electric motor, a fan rotatable about the central axis of the electric propulsion engine by the electric motor, a bearing supporting rotation of the fan, and a thermal management system. The thermal management system can include a lubrication oil circulation assembly for providing the bearing with lubrication oil. The lubrication oil circulation assembly can be driven independently of a shaft of the electric propulsion engine.

公开(公告)号：US11485481B2

公开(公告)日：2022-11-01

申请号：US16279244

申请日：2019-02-19

Applicant: General Electric Company

Inventor： Lawrence Chih-Hui Cheung ,  Nikolai N. Pastouchenko ,  Kishore Ramakrishnan

IPC: B64C21/08 ,  B64C21/06 ,  B64D29/04 ,  B64C1/16 ,  B64D27/24 ,  B64D33/02 ,  B64D33/04 ,  B64D27/02

Abstract: An aircraft includes a fuselage extending between a forward end and an aft end; a propulsor mounted to the fuselage at the aft end of the fuselage, the propulsor comprising an outer nacelle, the outer nacelle defining an inlet to the propulsor; and a deployable assembly attached to at least one of the fuselage or the outer nacelle and moveable between a stowed position and an engaged position. The deployable assembly alters an airflow towards the propulsor or into the propulsor through the inlet defined by the outer nacelle when in the engaged position. The propulsor further comprises a tail cone, wherein the outer nacelle defines an exhaust with the tail cone, and wherein the plurality of nacelle panels are movable generally along the axial centerline to a position at least partially aft of the exhaust of the outer nacelle when in the engaged position.