-
公开(公告)号：US10752371B2
公开(公告)日：2020-08-25
申请号：US15282098
申请日：2016-09-30
Applicant: General Electric Company
Inventor： Lawrence Chih-hui Cheung
IPC: B64D29/06 , B64C7/02 , B64D27/02 , F02K1/06 , B64C11/28 , B64C23/00 , F02K1/52 , B64C21/06 , B64D27/18 , B64D27/24 , B64D29/04
Abstract: The present disclosure is directed to a fan section positioned on a tail section of an aircraft, in which the fan section defines a circumferential direction, a radial direction, and an axial direction. The fan section includes a fan and a nacelle. The fan includes a plurality of fan blades and a fan shaft, in which the plurality of fan blades are rotatable with the shaft. The nacelle includes a wall at least partially enclosing the fan. The wall includes a first portion and a second portion. The first portion translates relative to the second portion between a first, closed position in which the wall of the nacelle circumferentially encloses the fan and a second, open position in which at least a portion of the fan is unenclosed by the wall of the nacelle.
-
公开(公告)号：US20180093754A1
公开(公告)日：2018-04-05
申请号：US15282056
申请日：2016-09-30
Applicant: General Electric Company
Inventor： Lawrence Chih-hui Cheung
Abstract: The present disclosure is directed to a fan section mounted to an aircraft tail section. The fan section defines a radial direction, an axial direction and a circumferential direction. The fan section includes a shaft extending generally along a longitudinal axis, and a plurality of fan blades rotatable with the shaft about the longitudinal axis. Each fan blade defines an outer end along the radial direction. One or more of the plurality of fan blades translates a respective outer end from a first radial position to a second radial position.
-
公开(公告)号：US20190176971A1
公开(公告)日：2019-06-13
申请号：US16279244
申请日：2019-02-19
Applicant: General Electric Company
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.
-
公开(公告)号：US10252791B2
公开(公告)日：2019-04-09
申请号：US15244032
申请日：2016-08-23
Applicant: General Electric Company
Abstract: An aircraft includes a fuselage extending between a forward end and an aft end. The aircraft additionally includes a propulsor mounted to the fuselage at the aft end of the fuselage, the propulsor including an outer nacelle and the outer nacelle defining an inlet. Additionally, the aircraft includes a deployable assembly attached to at least one of the fuselage or the outer nacelle, the deployable assembly movable 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 to increase an efficiency of the aft fan and/or of the aircraft.
-
公开(公告)号：US20180050810A1
公开(公告)日：2018-02-22
申请号：US15241157
申请日：2016-08-19
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: B64D33/08 , B64C21/06 , B64D27/10 , B64D27/24 , F01D15/10 , F01D15/12 , F02K3/062 , F04D29/32 , F04D29/056 , F04D29/063 , F04D29/58
Abstract: A propulsion system for an aircraft includes an electric propulsion engine. The electric propulsion engine includes an electric motor and a fan rotatable about a central axis of the electric propulsion engine by the electric motor. The electric propulsion engine also includes a bearing supporting rotation of the fan and a thermal management system. The thermal management system includes a lubrication oil circulation assembly and a heat exchanger thermally connected to the lubrication oil circulation assembly. The lubrication oil circulation assembly is configured for providing the bearing with lubrication oil. Such an electric propulsion engine may be a relatively self-sufficient engine.
-
Patent Agency Ranking
公开(公告)号：US10814959B2
公开(公告)日：2020-10-27
申请号：US15282056
申请日：2016-09-30
Applicant: General Electric Company
Inventor： Lawrence Chih-hui Cheung
Abstract: The present disclosure is directed to a fan section mounted to an aircraft tail section. The fan section defines a radial direction, an axial direction and a circumferential direction. The fan section includes a shaft extending generally along a longitudinal axis, and a plurality of fan blades rotatable with the shaft about the longitudinal axis. Each fan blade defines an outer end along the radial direction. One or more of the plurality of fan blades translates a respective outer end from a first radial position to a second radial position.
-
公开(公告)号：US10800539B2
公开(公告)日：2020-10-13
申请号：US15241168
申请日：2016-08-19
Applicant: General Electric Company
Inventor： Daniel Alan Niergarth , Randy M. Vondrell , Brandon Wayne Miller , Patrick Michael Marrinan , Lawrence Chih-hui Cheung , Nikolai N. Pastouchenko
Abstract: A propulsion system for an aircraft includes a gas turbine engine and an electric propulsion engine defining a central axis. The electric propulsion engine includes an electric motor and a fan rotatable about the central axis of the electric propulsion engine by the electric motor. The electric propulsion engine additionally includes a bearing supporting rotation of the fan and a thermal management system including a thermal fluid circulation assembly. The thermal fluid circulation assembly is in thermal communication with at least one of the electric motor or the bearing and is further in thermal communication with a heat exchanger of a thermal management system of the gas turbine engine.
-
公开(公告)号：US20180051716A1
公开(公告)日：2018-02-22
申请号：US15241137
申请日：2016-08-19
Applicant: General Electric Company
Inventor： Lawrence Chih-hui Cheung , Nikolai N. Pastouchenko , Kishore Ramakrishnan , Brandon Wayne Miller
IPC: F04D29/58 , B64D27/24 , B64D33/08 , B64D29/00 , B64C21/06 , B64C5/00 , F04D19/00 , F04D25/06 , F04D29/52 , F04D29/54 , H02K7/18
CPC classification number: F04D29/5806 , B64C21/06 , B64C2230/04 , B64D27/20 , B64D27/24 , B64D29/04 , B64D33/02 , B64D33/08 , B64D33/10 , B64D2027/026 , F04D25/02 , F04D25/06 , F05B2220/303 , F05B2220/706 , H02K7/14 , H02K7/1823 , H02K9/19
Abstract: A propulsion system for an aircraft includes an electric propulsion engine configured to be mounted at an aft end of the aircraft. The electric propulsion engine includes an electric motor and a fan rotatable about a central axis, the fan driven by the electric motor. The electric propulsion system additionally includes a cooling system operable with an airflow over the aft end the aircraft when the electric propulsion system is mounted to the aircraft. The cooling system is configured to cool the electric motor during operation of the electric propulsion engine.
-
公开(公告)号：US20200331622A1
公开(公告)日：2020-10-22
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: B64D33/08 , F02K5/00 , F02C7/14 , F02C6/20 , B64C11/00 , B64C21/06 , B64D27/10 , B64D27/24 , F01D15/10 , F01D15/12 , F02K3/062 , F04D29/056 , F04D29/063 , F04D29/32 , F04D29/58
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：US10676205B2
公开(公告)日：2020-06-09
申请号：US15241157
申请日：2016-08-19
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: B64D33/08 , F02K5/00 , F02C7/14 , F02C6/20 , B64C11/00 , B64C21/06 , B64D27/10 , B64D27/24 , F01D15/10 , F01D15/12 , F02K3/062 , F04D29/056 , F04D29/063 , F04D29/32 , F04D29/58 , B64D27/02
Abstract: A propulsion system for an aircraft includes an electric propulsion engine. The electric propulsion engine includes an electric motor and a fan rotatable about a central axis of the electric propulsion engine by the electric motor. The electric propulsion engine also includes a bearing supporting rotation of the fan and a thermal management system. The thermal management system includes a lubrication oil circulation assembly and a heat exchanger thermally connected to the lubrication oil circulation assembly. The lubrication oil circulation assembly is configured for providing the bearing with lubrication oil. Such an electric propulsion engine may be a relatively self-sufficient engine.
-
-
-
-
-
-
-
-
-
Search Results
16
records
(took 0.017 seconds)
