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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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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：US20250042558A1
公开(公告)日：2025-02-06
申请号：US18230609
申请日：2023-08-04
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：US20250042537A1
公开(公告)日：2025-02-06
申请号：US18652052
申请日：2024-05-01
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：US20240318613A1
公开(公告)日：2024-09-26
申请号：US18680469
申请日：2024-05-31
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Randy M. Vondrell , David Marion Ostdiek , Craig Williams Higgins , Alexander Kimberley Simpson , Syed Arif Khalid , Jeffrey S. Spruill , Daniel Lawrence Tweedt , William Joseph Solomon , Kevin Edward Hinderliter
Abstract: A gas turbine engine is provided. The gas turbine engine includes a turbomachine defining an engine inlet to an inlet duct, a fan duct inlet to a fan duct, and a core inlet to a core duct; a primary fan driven by the turbomachine; and a secondary fan located downstream of the primary fan within the inlet duct. The gas turbine engine defines a thrust to power airflow ratio between 3.5 and 100 and a core bypass ratio between 0.1 and 10, wherein the thrust to power airflow ratio is a ratio of an airflow through a bypass passage over the turbomachine plus an airflow through the fan duct to an airflow through the core duct, and wherein the core bypass ratio is a ratio of the airflow through the fan duct to the airflow through the core duct.
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Patent Agency Ranking
公开(公告)号：US20220259985A1
公开(公告)日：2022-08-18
申请号：US17176106
申请日：2021-02-15
Applicant: General Electric Company
Inventor： Timothy Richard DePuy , Trevor Goerig , Jeffrey D. Clements , Syed Arif Khalid
Abstract: A turbomachinery engine includes an unducted rotor assembly, a low-pressure turbine, a low-pressure shaft, a gearbox, and an engine correlation parameter. The unducted rotor assembly includes a plurality of rotor blades arranged in a single row and defining a blade diameter. The gearbox includes an input, an output, and a gear ratio. The input of the gearbox is coupled to the low-pressure shaft (which is coupled to the LPT), and the output of the gearbox is coupled to the unducted rotor assembly. The engine correlation parameter is greater than 0.17 and less than 0.83. The engine correlation parameter equals D/N/GR, where D is the blade tip diameter measured in feet, N is the stage count of the low-pressure turbine, and GR is the gear ratio of the gearbox. The unducted propulsor assembly optionally includes a disk loading within a range of 60-180 HP/ft2 at a takeoff flight condition.
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公开(公告)号：US11262144B2
公开(公告)日：2022-03-01
申请号：US15858453
申请日：2017-12-29
Applicant: General Electric Company
Abstract: A heat exchanger apparatus includes: spaced-apart peripheral walls extending between an inlet and an outlet, the peripheral walls collectively defining a flow channel which includes a diverging portion downstream of the inlet, in which a flow area is greater than a flow area at the inlet; a plurality of spaced-apart fins disposed in the flow channel, each of the fins having opposed side walls extending between an upstream leading edge and a downstream trailing edge, wherein the fins divide at least the diverging portion of the flow channel into a plurality of side-by-side flow passages; and a heat transfer structure disposed within at least one of the fins.
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公开(公告)号：US20210108595A1
公开(公告)日：2021-04-15
申请号：US17071018
申请日：2020-10-15
Applicant: General Electric Company
Inventor： Syed Arif Khalid , Andrew Breeze-Stringfellow
Abstract: A propulsion system is provided, the propulsion system including a rotor assembly configured to rotate relative to the engine centerline axis, and wherein one or more blades of the rotor assembly are configured to rotate along a blade pitch angle axis. A vane assembly is positioned in aerodynamic relationship with the rotor assembly. The vane assembly includes one or more vanes, wherein each vane includes a vane pitch angle. A controller is configured to execute operations, the operations including moving each blade to a reverse thrust position about its respective blade pitch axis, and adjusting each vane about its respective vane pitch axis when the plurality of blades is in the reverse thrust position to modify an amount of reverse thrust generated by the propulsion system.
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公开(公告)号：US10288083B2
公开(公告)日：2019-05-14
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
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：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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