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公开(公告)号：US20200025213A1
公开(公告)日：2020-01-23
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：US20200023959A1
公开(公告)日：2020-01-23
申请号：US16042141
申请日：2018-07-23
Applicant: General Electric Company
Inventor： Andrew Breeze-Stringfellow , Daniel Lawrence Tweedt , Syed Arif Khalid , Kurt David Murrow
IPC: B64C29/00
Abstract: A lift fan apparatus includes: a rotor having at least one rotatable hub carrying at least one row of blades; a duct surrounding the rotor, the duct including spaced-apart peripheral walls extending between an inlet and an exit, the peripheral walls collectively defining a flow channel which includes a diffuser disposed downstream of the rotor, in which a flow area at the exit is greater than a flow area at the rotor; and a plurality of spaced-apart splitters disposed in the diffuser, each of the splitters having opposed side walls extending between an upstream leading edge and a downstream trailing edge, wherein the splitters divide the diffuser into a plurality of side-by-side flow passages.
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23.发明授权公开(公告)号：US10399664B2
公开(公告)日：2019-09-03
申请号：US15145894
申请日：2016-05-04
Applicant: GENERAL ELECTRIC COMPANY
Inventor： William Joseph Bowden , Andrew Breeze-Stringfellow , Richard David Cedar , Syed Arif Khalid , Patrick John Lonneman , Aleksander Piotr Pasieczny , Daniel Lawrence Tweedt
IPC: B64C11/14 , B64D33/02 , F02C6/20 , F02C7/05 , F01D5/02 , F01D9/04 , F01D25/04 , F01D25/24 , F04D29/32 , F04D29/38 , B64D27/00
Abstract: An unducted thrust producing system is provided that can include a rotating element having an axis of rotation about a central longitudinal axis and comprising a plurality of blades attached to a spinner; a stationary element positioned aft of the rotating element; and an inlet positioned between the rotating element and the stationary element such that the inlet passes radially inward of the stationary element. The rotating element defines an annular valley positioned between a first annular crown and a second annular crown, and the inlet defines an open area positioned aft of the second annular crown.
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公开(公告)号：US20190204010A1
公开(公告)日：2019-07-04
申请号：US15858453
申请日：2017-12-29
Applicant: General Electric Company
CPC classification number: F28D7/005 , F02C3/04 , F02C7/14 , F02K3/06 , F05D2220/32 , F05D2240/35 , F05D2260/22141 , F28D7/10 , F28D2021/0026 , F28F1/22 , F28F13/08
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：US20190047719A1
公开(公告)日：2019-02-14
申请号：US16042522
申请日：2018-07-23
Applicant: General Electric Company
Inventor： Kurt David Murrow , Andrew Breeze-Stringfellow
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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Patent Agency Ranking
公开(公告)号：US10132323B2
公开(公告)日：2018-11-20
申请号：US14870300
申请日：2015-09-30
Applicant: General Electric Company
Inventor： Swati Saxena , Andrew Breeze-Stringfellow , Rajkeshar Vijayraj Singh , Tsuguji Nakano
Abstract: A compressor is provided including a casing, a hub, a flowpath, a plurality of blades defining a plurality of axially extending compressor stages and an endwall treatment formed in the casing on at least two downstream most stages of the plurality of compressor stages. The remaining stages of the plurality of compressor stages located upstream of the at least two downstream most stage are devoid of any endwall treatment. Each of the endwall treatments faces a tip of each blade in the at least two downstream most stages. The tip of each blade and the endwall treatment are configured to move relative to each other. The endwall treatment formed in the casing on at least two downstream most stages of the plurality of compressor stages is configured to extend a stall margin to delay stall due to ice ingestion. A method and engine application are disclosed.
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公开(公告)号：US20180073518A1
公开(公告)日：2018-03-15
申请号：US15266603
申请日：2016-09-15
Applicant: General Electric Company
Inventor： Daniel Allen Wilkin, II , Andrew Breeze-Stringfellow
CPC classification number: F04D29/384 , F01D5/14 , F02K3/06 , F04D29/322 , F04D29/324 , F04D29/34 , F04D29/522 , F05D2220/326 , F05D2220/36 , F05D2240/12 , F05D2240/14 , F05D2240/30 , F05D2250/70 , F05D2300/133 , F05D2300/603 , Y02T50/672 , Y02T50/673
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：US20180017079A1
公开(公告)日：2018-01-18
申请号：US15211730
申请日：2016-07-15
Applicant: General Electric Company
CPC classification number: F04D29/563 , F01D5/146 , F01D5/34 , F01D9/041 , F02C3/04 , F02K3/06 , F04D19/02 , F04D25/045 , F04D29/324 , F04D29/544 , F05D2220/32 , F05D2220/36 , F05D2240/12 , F05D2240/35
Abstract: A variable-cycle compressor includes: an axial-flow compressor, a flowpath downstream of the compressor, and at least one variable-cycle device operable to vary a choked flow capacity of the downstream flowpath. The compressor includes: a rotor having at least one rotor stage including a rotatable disk defining a rotor flowpath surface and an array of axial-flow rotor airfoils extending outward from the flowpath surface; at least one stator stage including a wall defining a stator flowpath surface, and an array of axial-flow stator airfoils extending away from the stator flowpath surface. At least one stage includes splitter airfoils alternating with the rotor or stator airfoils of the corresponding stage. At least one of a chord dimension of the splitter airfoils and a span dimension of the splitter airfoils is less than the corresponding dimension of the airfoils of the at least one stage.
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公开(公告)号：US20180017019A1
公开(公告)日：2018-01-18
申请号：US15211787
申请日：2016-07-15
Applicant: General Electric Company
CPC classification number: F02K3/075 , F01D5/143 , F01D5/146 , F01D9/041 , F02C9/20 , F02K3/06 , F04D29/324 , F04D29/544 , F05D2220/36
Abstract: A turbofan engine includes: a turbomachinery core; and a low-pressure turbine configured to drive a fan to produce a fan flow, the fan being configured such that at least a portion of the fan flow exits the engine without passing through a turbine. The fan includes: a rotor having at least one rotor stage including axial-flow rotor airfoils, and at least one stator stage including axial-flow stator airfoils. At least one of the rotor or stator stages includes an array of airfoil-shaped splitter airfoils alternating with the rotor or stator airfoils of the corresponding stage. At least one of a chord dimension of the splitter airfoils and a span dimension of the splitter airfoils is less than the corresponding dimension of the airfoils of the at least one stage.
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公开(公告)号：US12140035B2
公开(公告)日：2024-11-12
申请号：US17526313
申请日：2021-11-15
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Paul Hadley Vitt , Andrew Breeze-Stringfellow
Abstract: A shroud assembly for a turbine engine having a centerline axis. The shroud assembly having a shroud hanger, at least one shroud segment, and at least one biasing element extending between the two. The biasing element configured to radially bias the at least one shroud segment between an outboard position and an inboard position radially outward from the outboard position with respect to the centerline axis.
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