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公开(公告)号：US20200271010A1
公开(公告)日：2020-08-27
申请号：US16871660
申请日：2020-05-11
Applicant: General Electric Company
IPC: F01D17/16 , B64C11/46 , F02K3/02 , F02C6/20 , F02K1/46 , B64C11/00 , B64C11/18 , B64C11/48 , F01D9/02
Abstract: A unshrouded vane assembly for an unducted propulsion system includes a plurality of vanes which have non-uniform characteristics configured to generate a desired vane exit swirl angle.
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公开(公告)号：US10408217B2
公开(公告)日：2019-09-10
申请号：US15070268
申请日：2016-03-15
Applicant: General Electric Company
Abstract: An apparatus and method of controlling a multi-stage compressor of a gas turbine engine having a front-block of stages with variable stator vanes (VSVs), a rear block of stages downstream of the front-block, and a bleed air off-take from at least one of the stages. The method includes sensing the pressure of the bleed air from the bleed air off-take and adjusting the position of the VSV for the front-block.
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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.
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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.
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公开(公告)号：US10202865B2
公开(公告)日：2019-02-12
申请号：US14437872
申请日：2013-10-23
Applicant: General Electric Company
IPC: F01D17/16 , B64C11/18 , B64C11/46 , F02K3/02 , F02C6/20 , F02K1/46 , B64C11/00 , B64C11/48 , F01D9/02
Abstract: An unducted thrust producing system has a rotating element with an axis of rotation and a stationary element. The rotating element includes a plurality of blades each having a blade root proximal to the axis, a blade tip remote from the axis, and a blade span measured between the blade root and the blade tip. The rotating element has a load distribution such that at any location between the blade root and 30% span the value of ΔRCu in the air stream is greater than or equal to 60% of the peak ΔRCu in the air stream.
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Patent Agency Ranking
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.
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公开(公告)号：US09878501B2
公开(公告)日：2018-01-30
申请号：US14596841
申请日：2015-01-14
Applicant: General Electric Company
Inventor： Darek Tomasz Zatorski , Ian Francis Prentice , Randy M. Vondrell , Andrew Breeze-Stringfellow
CPC classification number: B29C70/34 , B29D99/0025
Abstract: A method of manufacturing a frangible laminate is provided. The method comprises constructing a reinforced polymer matrix, cutting the reinforced polymer matrix into a plurality of laminae, forming a laminate via stacking the plurality of laminae and at least one energy dissipating member, and consolidating the laminate.
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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.
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公开(公告)号：US20170138370A1
公开(公告)日：2017-05-18
申请号：US14941799
申请日：2015-11-16
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Andrew Breeze-Stringfellow , Darek Tomasz Zatorski , Syed Arif Khalid , Christopher James Kroger , Daniel Alan Niergarth
CPC classification number: F04D29/36 , B64C11/30 , F01D7/00 , F04D27/002 , F04D29/323 , F04D29/325 , F04D29/522 , F05D2220/36 , F05D2260/79 , Y02T50/671 , Y02T50/673
Abstract: A variable pitch fan for a propulsion device is provided. The variable pitch fan includes a plurality of fan blades coupled to a disk and a rotatable front hub covering the disk. Each fan blade is rotatable about a pitch axis to vary a pitch of the fan blade. The pitch is variable within a pitch range that is at least about 80° to about 130°. Each fan blade extends radially outward from the disk along a span from a root to a tip. A portion of the span adjacent the root defines a root span region, a portion of the span adjacent the tip defines a tip span region. A solidity of the variable pitch fan is at least 1.0 in the root span region.
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公开(公告)号：US20250075623A1
公开(公告)日：2025-03-06
申请号：US18242079
申请日：2023-09-05
Applicant: General Electric Company
Inventor： Tsuguji Nakano , Andrew Breeze-Stringfellow
Abstract: A rotor blade comprises an elongated body that has a pressure side and a suction side. The pressure side and suction side intersect at a leading edge and a trailing edge. The elongated body extends outward from a rotor hub. A span is described by a first straight line distance extending outward from the rotor hub along the elongated body. A chord of the elongated body is defined by a second straight-line distance extending between the leading edge and the trailing edge. At least one passageway extends through the elongated body between the pressure side and the suction side allowing a corrective flow of air to move from the pressure side to the suction side. The corrective flow of air interacts with and energizes low momentum airflow occurring along the suction side.
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