-
公开(公告)号：US10252797B2
公开(公告)日：2019-04-09
申请号：US15259596
申请日：2016-09-08
Applicant: General Electric Company
Inventor： Randy M. Vondrell , Matthew Ryan Polakowski , Kurt David Murrow , Glenn Crabtree , Darek Tomasz Zatorski
Abstract: An aircraft includes a fuselage, a forward wing assembly, and aft wing assembly, and a propulsion system. The propulsion system includes a first primary thrust propulsor and a first secondary thrust propulsor, the first primary thrust propulsor being different than the first secondary thrust propulsor. Both the first primary thrust propulsor and the first secondary thrust propulsor are mounted to the same one of: a starboard side of the aft wing assembly, a port side of the aft wing assembly, a starboard side of the forward wing assembly, or a port side of the forward wing assembly.
-
公开(公告)号：US10227928B2
公开(公告)日：2019-03-12
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
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.
-
公开(公告)号：US20190047718A1
公开(公告)日：2019-02-14
申请号：US16042403
申请日：2018-07-23
Applicant: General Electric Company
Abstract: An aircraft includes a fuselage; a propulsion system including a power source and a plurality of vertical thrust electric fans driven by the power source; and a wing extending from the fuselage. The plurality of vertical thrust electric fans are arranged along the wing, the wing including one or more components being moveable to selectively expose the plurality of vertical thrust electric fans, the wing further including a diffusion assembly positioned downstream of at least one vertical thrust electric fan of the plurality of vertical thrust electric fans, the diffusion assembly defining a diffusion area ratio greater than 1:1 and less than about 2:1.
-
公开(公告)号：US20190023390A1
公开(公告)日：2019-01-24
申请号：US16042299
申请日：2018-07-23
Applicant: General Electric Company
Abstract: A method for operating a vertical takeoff and landing aircraft includes modifying a first variable component of a wing associated with a first portion of the plurality of vertical thrust electric fans relative to a second variable component of the wing associated with a second portion of the plurality of vertical thrust electric fans to adjust an exposure ratio of the first portion of the plurality of vertical thrust electric fans relative to the second portion of the plurality of vertical thrust electric fans.
-
公开(公告)号：US10000293B2
公开(公告)日：2018-06-19
申请号：US14969640
申请日：2015-12-15
Applicant: General Electric Company
Inventor： Jeffrey Anthony Hamel , Kurt David Murrow
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.
-
Patent Agency Ranking
公开(公告)号：US09884687B2
公开(公告)日：2018-02-06
申请号：US14859556
申请日：2015-09-21
Applicant: General Electric Company
Inventor： Patrick Michael Marrinan , Thomas Lee Becker , Kurt David Murrow , Jixian Yao
CPC classification number: B64D27/14 , B64C1/16 , B64C21/06 , B64C2230/00 , B64D27/20 , B64D29/04 , B64D33/02 , Y02T50/166
Abstract: An aircraft including a fuselage and an aft engine is provided. The fuselage extends from a forward end of the aircraft towards an aft end of the aircraft. The aft engine is mounted to the fuselage proximate the aft end of the aircraft. The aft engine includes a fan rotatable about a central axis of the aft engine, the fan including a plurality of fan blades. The aft engine also includes a nacelle surrounding the plurality of fan blades and defining an inlet. The inlet defines a non-axis symmetric shape with respect to the central axis of the aft engine to, e.g., allow for a maximum amount of airflow into the aft engine.
-
公开(公告)号：US09777642B2
公开(公告)日：2017-10-03
申请号：US14919825
申请日：2015-10-22
Applicant: General Electric Company
Inventor： Kurt David Murrow , Andrew Breeze-Stringfellow , Randy M. Vondrell , Tsuguji Nakano , Jeffrey Anthony Hamel , Darek Tomasz Zatorski
IPC: F02C1/00 , F02C9/20 , F01D7/00 , F01D15/12 , F01D17/08 , F01D17/10 , F01D17/16 , F02K1/66 , F02K3/04 , F02K3/075 , F02C3/13 , F02C7/36 , F02C9/18 , F02C3/04 , F02C7/042
CPC classification number: F02C9/20 , F01D7/00 , F01D15/12 , F01D17/085 , F01D17/105 , F01D17/162 , F02C3/04 , F02C3/13 , F02C7/042 , F02C7/36 , F02C9/18 , F02K1/66 , F02K3/04 , F02K3/075 , F05D2220/36 , F05D2270/101 , F05D2270/303 , F05D2300/30 , Y02T50/672
Abstract: A method and system for a turbofan gas turbine engine system is provided. The gas turbine engine system includes a variable pitch fan (VPF) assembly coupled to a first rotatable shaft and a low pressure compressor LPC coupled to a second rotatable shaft. The LPC including a plurality of variable pitch stator vanes interdigitated with rows of blades of a rotor of the LPC. The gas turbine engine system also includes a speed reduction device coupled to said first rotatable shaft and said second rotatable shaft. The gas turbine engine system further includes a modulating pressure relief valve positioned between an outlet of said LPC and a bypass duct and a controller configured to schedule a position of said plurality of variable pitch stator vanes and said modulating pressure relief valve in response to an operational state of said turbofan gas turbine engine system and a temperature associated with said LPC.
-
公开(公告)号：US20170101191A1
公开(公告)日：2017-04-13
申请号：US14879217
申请日：2015-10-09
Applicant: General Electric Company
IPC: B64D33/02 , F02C7/32 , F04D29/32 , F04D29/52 , B64D27/24 , F04D29/36 , F01D15/10 , B64D27/18 , B64D27/26 , F02K3/062 , F04D29/54
CPC classification number: B64D33/02 , B64C1/16 , B64C21/06 , B64D27/18 , B64D27/20 , B64D27/24 , B64D27/26 , B64D29/04 , B64D2027/026 , B64D2033/0226 , F01D15/10 , F02C7/32 , F02K3/062 , F04D29/325 , F04D29/36 , F04D29/522 , F04D29/542 , F05D2220/323 , Y02T50/166
Abstract: A propulsion system for an aircraft is provided having an aft engine configured to be mounted to the aircraft at an aft end of the aircraft. The aft engine includes a fan rotatable about a central axis of the aft engine having a plurality of fan blades attached to a fan shaft. The aft engine also includes a nacelle encircling the plurality of fan blades and a structural support system for mounting the aft engine to the aircraft. The structural support system extends from the fuselage of the aircraft, through the fan shaft, and to the nacelle when the aft engine is mounted to the aircraft. The aft engine may increase a net thrust of the aircraft when mounted to the aircraft.
-
公开(公告)号：US20250019071A1
公开(公告)日：2025-01-16
申请号：US18515830
申请日：2023-11-21
Applicant: General Electric Company
Inventor： Kurt David Murrow , Darek Tomasz Zatorski , Matthew Timothy Franer
Abstract: An aircraft defining a vertical direction, a longitudinal direction, and a transverse direction is provided. The aircraft includes: a fuselage; a propulsion system comprising a power source and a plurality of vertical thrust electric fans driven by the power source; and a wing extending from the fuselage in the transverse direction. The wing includes a support structure that comprises a plurality of first support members and a plurality of second support members. The plurality of first support members extending at least partially between the plurality of second support members. The plurality of vertical thrust electric fans arranged between the plurality of first support members and the plurality of second support members.
-
公开(公告)号：US20240326995A1
公开(公告)日：2024-10-03
申请号：US18738167
申请日：2024-06-10
Applicant: General Electric Company
IPC: B64C29/00 , B64C3/10 , B64C3/32 , B64C3/38 , B64D27/02 , B64D27/24 , B64D27/40 , B64D29/04 , B64D31/06 , B64D33/04 , B64D35/02 , H02K7/18
CPC classification number: B64C29/0025 , B64C3/10 , B64C3/32 , B64C3/38 , B64C29/00 , B64D27/24 , B64D29/04 , B64D31/06 , B64D33/04 , B64D35/02 , B64D27/02 , B64D27/026 , B64D27/40 , F05D2220/76 , F05D2270/093 , H02K7/1823
Abstract: An aircraft defines a vertical direction and includes a fuselage and a propulsion system comprising a power source and a plurality of vertical thrust electric fans driven by the power source. A wing extends from the fuselage. The plurality of vertical thrust electric fans are arranged along a length of the wing along a lengthwise direction of the wing. The wing comprises a diffusion assembly along the lengthwise direction of the wing and includes a first diffusion member positioned downstream of at least one of the plurality of vertical thrust electric fans. The first diffusion member defines a curved shape relative to a longitudinal direction of the aircraft. The longitudinal direction is generally perpendicular to the lengthwise direction of the wing.
-
-
-
-
-
-
-
-
-
Search Results
100
records
(took 0.028 seconds)
