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公开(公告)号：US09243512B1
公开(公告)日：2016-01-26
申请号：US14596815
申请日：2015-01-14
Applicant: General Electric Company
Inventor： Darek Tomasz Zatorski , Andrew Breeze-Stringfellow , Ian Francis Prentice , Randy M. Vondrell
CPC classification number: F01D21/045 , B64C11/26 , B64D2027/005 , F01D5/147 , F01D5/282 , F04D29/324 , Y02T50/66 , Y02T50/672
Abstract: A rotary machine with at least one frangible composite blade that mitigates adverse conditions associated with release of material resulting from impact damage to the composite blade is provided. The composite blade having provisions for dissipating energy, self-shredding, and predetermined release trajectory. A method for manufacturing the composite blade and assembling the blade into a rotary machine is also provided.
Abstract translation: 提供一种具有至少一个易碎复合叶片的旋转机器，其减轻与由复合叶片的冲击损坏引起的材料释放相关的不利条件。 复合叶片具有用于消耗能量，自切碎和预定释放轨迹的规定。 还提供了一种用于制造复合叶片并将叶片组装成旋转机器的方法。
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公开(公告)号：US20150284070A1
公开(公告)日：2015-10-08
申请号：US14437872
申请日：2013-10-23
Applicant: GENERAL ELECTRIC COMPANY
IPC: B64C11/48
CPC classification number: F01D17/16 , B64C11/00 , B64C11/001 , B64C11/18 , B64C11/46 , B64C11/48 , F01D9/02 , F02C6/206 , F02K1/46 , F02K3/025 , F05B2240/12 , F05B2260/96 , F05D2220/324 , F05D2220/325 , F05D2250/30 , F05D2250/51 , F05D2250/52 , F05D2260/14 , Y02E10/721 , Y02T50/66 , Y02T50/671
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.
Abstract translation: 未被压缩的推力产生系统具有带旋转轴线和静止元件的旋转元件。 旋转元件包括多个叶片，每个叶片具有靠近轴线的叶片根部，远离轴线的叶片尖端以及在叶片根部和叶片尖端之间测量的叶片跨度。 旋转元件具有负载分布，使得在叶片根部和30％之间的任何位置跨越空气流中的＆Dgr; RCu的值大于或等于空气流中的峰值＆amp; Grg; RCu的60％。
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公开(公告)号：US20250042538A1
公开(公告)日：2025-02-06
申请号：US18797158
申请日：2024-08-07
Applicant: General Electric Company
Inventor： Sara Elizabeth Carle , Daniel L. Tweedt , Syed Arif Khalid , Andrew Breeze-Stringfellow , William Bowden
Abstract: The present disclosure is generally related to aircraft having one or more unducted fan propulsors at locations within specific regions relative to an airfoil, such as a wing or horizontal stabilizer. More specifically, the specific regions are located where there is a relatively higher pressure air flow beneath the wings or above a horizontal stabilizer. That higher pressure air flow can be utilized to provide increased thrust from the unducted fan propulsor.
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公开(公告)号：US12006031B2
公开(公告)日：2024-06-11
申请号：US17366749
申请日：2021-07-02
Applicant: General Electric Company
IPC: B64C29/00 , B64C3/10 , B64C3/32 , B64C3/38 , B64D27/24 , B64D29/04 , B64D31/06 , B64D33/04 , B64D35/02 , B64D27/02 , B64D27/40 , 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.
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公开(公告)号：US20230322412A1
公开(公告)日：2023-10-12
申请号：US18121806
申请日：2023-03-15
Applicant: General Electric Company
Inventor： Daniel L. Tweedt , Andrew Breeze-Stringfellow , Syed Arif Khalid , William J. Solomon , Alexander Hills
Abstract: A flow conditioning structure is disposed about a central axis of an unducted thrust producing apparatus. The unducted thrust producing apparatus has a propeller that generates thrust in a working fluid by rotating about the central axis. The propeller is comprised of blades each with a free end. Each blade also has a leading edge where the working fluid enters during forward thrust operation. The flow conditioning structure comprises a structure forming a passage and the structure forming the passage controls a speed and a direction of the working fluid drawn into the unducted thrust producing apparatus so as to approximate operational speeds and operational directions of the working fluid entering the unducted thrust producing apparatus during operations of a vehicle.
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Patent Agency Ranking
公开(公告)号：US11300136B2
公开(公告)日：2022-04-12
申请号：US16577573
申请日：2019-09-20
Applicant: General Electric Company
Inventor： Daniel Allen Wilkin, II , Andrew Breeze-Stringfellow
Abstract: A fan for a gas turbine engine includes: an annular casing; a disk disposed inside the casing and mounted for rotation about an axial centerline, the disk including a row of fan blades extending radially outwardly therefrom; each of the fan blades including an airfoil having circumferentially opposite pressure and suction sides extending radially in span from a root to a tip, and extending axially in chord between spaced-apart leading and trailing edges, with the airfoils defining corresponding flow passages therebetween for pressurizing air; the row including no more than 21 and no less than 13 of the fan blades; and wherein each of the fan blades has a solidity defined by a ratio of the airfoil chord over a circumferential pitch of the fan blades, measured at 60% of a radial distance from the root to the tip, of less than about 1.6.
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公开(公告)号：US20220074420A1
公开(公告)日：2022-03-10
申请号：US17015400
申请日：2020-09-09
Applicant: General Electric Company
Inventor： Kyle Louis Miller , Andrew Breeze-Stringfellow
Abstract: A turbo machine, a computer-implemented method, and a computer system for operating a compressor assembly are provided. The method includes comparing a first data set and a second data set to determine a first correlation factor, comparing the first correlation factor to a first threshold that at least partially determines whether a stall precursor exists, removing mean values from the first data set and the second data set, comparing the first data set and the second data set each removed of mean values to determine a second correlation factor, and comparing the second correlation factor to the first threshold, and classifying the stall precursor as either a spike stall precursor, a modal stall precursor, or a combination stall precursor.
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公开(公告)号：US11124308B2
公开(公告)日：2021-09-21
申请号：US16042522
申请日：2018-07-23
Applicant: General Electric Company
Inventor： Kurt David Murrow , Andrew Breeze-Stringfellow
IPC: B64D27/24 , B64C29/00 , B64D29/04 , B64C3/10 , B64D27/08 , B64C3/32 , B64D35/02 , B64C3/38 , B64D33/04 , B64D31/06 , B64D27/02 , B64D27/26 , H02K7/18
Abstract: An aircraft includes a fuselage; a propulsion system including a power source and a vertical thrust propulsor driven by the power source; and a wing extending from the fuselage, the vertical thrust propulsor positioned on or at least partially within the wing, the wing including a diffusion assembly, the diffusion assembly including at least one diffusion member fixed in position and located downstream of the vertical thrust propulsor for diffusing an airflow from the vertical thrust propulsor.
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公开(公告)号：US11117675B2
公开(公告)日：2021-09-14
申请号：US16042216
申请日：2018-07-23
Applicant: General Electric Company
IPC: B64D27/24 , B64D29/04 , B64C3/10 , B64D27/08 , B64C3/32 , B64C35/02 , B64C3/38 , B64D33/04 , B64D31/06 , B64C29/00 , B64D35/02 , B64D27/02 , B64D27/26 , H02K7/18
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 a length of the wing, the wing including a variable geometry assembly extending along the length of the wing and moveable between a forward thrust position and a vertical thrust position, the variable geometry assembly at least partially covering the plurality of vertical thrust electric fans when in the forward thrust position and at least partially exposing the plurality of vertical thrust electric fans when in the vertical thrust position.
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公开(公告)号：US20210108523A1
公开(公告)日：2021-04-15
申请号：US17071019
申请日：2020-10-15
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Andrew Breeze-Stringfellow
IPC: F01D7/00
Abstract: A propulsion system according to aspects of the present disclosure is provided, the propulsion system including a rotor assembly with a plurality of blades extended radially relative to the engine centerline axis, and a vane assembly positioned in aerodynamic relationship with the rotor assembly. The vane assembly includes a plurality of vanes extended radially relative to the engine centerline axis, and the propulsion system includes a ratio of a quantity of blades to a quantity of vanes between 2:5 and 2:1.
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