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公开(公告)号：US20170297727A1
公开(公告)日：2017-10-19
申请号：US15132298
申请日：2016-04-19
Applicant: General Electric Company
Inventor： Daniel Alan Niergarth , Randy M. Vondrell , Brandon Wayne Miller , Patrick Michael Marrinan
CPC classification number: B64D27/24 , B64D27/02 , B64D27/18 , B64D2027/026 , F02C3/04 , F02C7/20 , F02C7/36 , F02K3/04 , F05D2220/76 , Y10S903/905 , Y10S903/906 , Y10S903/907
Abstract: A propulsion system for an aircraft is provided having a propulsion engine configured to be mounted to the aircraft. The propulsion engine includes an electric machine defining an electric machine tip speed during operation. The propulsion system additionally includes a fan rotatable about a central axis of the electric propulsion engine with the electric machine. The fan defines a fan pressure ratio, RFP, and includes a plurality of fan blades, each fan blade defining a fan blade tip speed. The electric propulsion engine defines a ratio of the fan blade tip speed to electric machine tip speed that is within twenty percent of the equation, 1.68×RFP−0.518, such that the propulsion engine may operate at a desired efficiency.
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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：US20170122206A1
公开(公告)日：2017-05-04
申请号：US14927536
申请日：2015-10-30
Applicant: General Electric Company
CPC classification number: F02C7/14 , F01D25/18 , F02C7/10 , F05D2260/213 , Y02T50/676
Abstract: A gas turbine engine includes a compressor section in series flow with a turbine section. The compressor section includes one or more compressors and the turbine section includes one or more turbines, the compressor section and turbine section together defining a core air flowpath. A sump is positioned inward of the core air flowpath for containing and collecting lubrication oil. Additionally, a heat exchanger is positioned in direct thermal communication with the sump for removing heat from lubrication oil contained therein to reduce a size and/or amount of heat exchangers located radially outward of the core air flowpath.
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公开(公告)号：US20170122205A1
公开(公告)日：2017-05-04
申请号：US14924888
申请日：2015-10-28
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Bugra Han Ertas , Daniel Alan Niergarth , Brandon Wayne Miller
CPC classification number: F02C7/06 , F01D25/22 , F02K3/06 , F05D2230/90 , F05D2240/50 , F05D2240/53 , F05D2240/61 , F16C17/02 , F16C17/028 , F16C32/0607 , F16C32/0625 , F16C33/1005 , F16C33/101 , F16C2360/23 , Y02T50/671
Abstract: Embodiments of a gas bearing for aircraft engines are provided herein. In some embodiments, a gas bearing may include a first shaft; a second shaft disposed concentrically about the first shaft; and a protrusion extending from at least one of an inner surface of the first shaft or the outer surface of the second shaft to form a gap between the first shaft and the second shaft.
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公开(公告)号：US20170030220A1
公开(公告)日：2017-02-02
申请号：US14809560
申请日：2015-07-27
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Richard Schmidt , Daniel Alan Niergarth
CPC classification number: F01D25/164 , F01D9/065 , F01D25/162 , F01D25/18 , F01D25/20 , F02C7/32 , F05D2260/98 , Y02T50/671
Abstract: A gas turbine engine is provided including a shaft coupling a compressor of a compressor section to a turbine of a turbine section. An aft bearing assembly, including at least two bearings, is positioned at least partially in an aft sump and supports the shaft within the turbine section. The aft sump is configured to receive lubrication oil from a lubrication oil supply extending through at least a portion of a turbine center frame of the turbine section, and provide such lubrication to the at least two bearings of the aft bearing assembly.
Abstract translation: 提供一种燃气涡轮发动机，其包括将压缩机部分的压缩机联接到涡轮部分的涡轮机的轴。 包括至少两个轴承的后轴承组件至少部分地定位在后水槽中，并将轴支撑在涡轮部分内。 后排池被构造成从润滑油供应部分接收润滑油，所述润滑油供应源延伸穿过涡轮机部分的涡轮机中心框架的至少一部分，并且为后轴承组件的至少两个轴承提供这种润滑。
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Patent Agency Ranking
公开(公告)号：US20250101919A1
公开(公告)日：2025-03-27
申请号：US18976748
申请日：2024-12-11
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Daniel Alan Niergarth , Jorge de Luis , Douglas Downey Turner , Michael Macrorie , Keith W. Wilkinson , Arthur William Sibbach , Vincenzo Martina
Abstract: A gas turbine engine is provided having a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches and the turbine section having a drive turbine defining a drive turbine exit area (ADTExit) in square inches, the turbomachine further comprising a drive turbine shaft coupled to the drive turbine; wherein the gas turbine engine defines a maximum exhaust gas temperature (EGT) in degrees Celsius, a maximum drive turbine shaft torque (TOUT) in Newton meters, and a corrected specific power (CSP) in Newtons squared times degrees Celsius over meters squared, wherein the corrected specific power is determined as follows: ( T OUT A DTExit ) 2 * EGT A HPCExit * 1 0 - 1 1 ; wherein CSP is greater than 0.0001194×EGT2−0.103×EGT+22.14 and less than 0.0003294×EGT2−0.306×EGT+77.91; and wherein EGT is greater than 525 degrees Celsius and less than 1250 degrees Celsius.
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公开(公告)号：US20250033789A1
公开(公告)日：2025-01-30
申请号：US18912957
申请日：2024-10-11
Applicant: General Electric Company
Inventor： Daniel Alan Niergarth , Brandon Wayne Miller , Michael Robert Bonacum , John Michael Pyles
Abstract: A system and method for using a fuel with an engine, an airframe having an aircraft heat load, a fuel tank, and a fuel oxygen reduction unit are provided. The method includes receiving an inlet fuel flow in the fuel oxygen reduction unit for reducing an amount of oxygen in the inlet fuel flow; separating a fuel/gas mixture within the fuel oxygen reduction unit into an outlet gas flow and an outlet fuel flow exiting the fuel oxygen reduction unit; controlling a first portion of the outlet fuel flow to the engine; and controlling a second portion of the outlet fuel flow to the airframe to transfer heat between the second portion of the outlet fuel flow and the aircraft heat load.
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公开(公告)号：US12123350B2
公开(公告)日：2024-10-22
申请号：US17190076
申请日：2021-03-02
Applicant: General Electric Company
Inventor： Daniel Alan Niergarth , Nicholas M. Daggett , Steven Douglas Johnson , Anand P. Roday , Scott Alan Schimmels
CPC classification number: F02C7/18 , F02C7/14 , F02C7/047 , F02K3/077 , F05D2240/12 , F05D2260/213
Abstract: A three-stream engine is provided. The three-stream engine includes a fan section, a core engine disposed downstream of the fan section, and a core cowl annularly encasing the core engine and at least partially defining a core duct. A fan cowl is disposed radially outward from the core cowl and annularly encasing at least a portion of the core cowl. The fan cowl at least partially defining an inlet duct and a fan duct. The fan duct and the core duct at least partially co-extending axially on opposite sides of the core cowl. A heat exchanger disposed within the fan duct. The heat exchanger provides for thermal communication between a fluid flowing through fan duct and a motive fluid flowing through the heat exchanger.
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69.发明授权公开(公告)号：US11981419B2
公开(公告)日：2024-05-14
申请号：US17560544
申请日：2021-12-23
Applicant: General Electric Company
CPC classification number: B64C11/38 , F02K3/06 , F04D29/325 , F04D29/36 , F04D29/362 , Y02T50/60
Abstract: The variable pitch propeller assembly includes a hub. The variable pitch propeller assembly also includes a plurality of propeller blade assemblies spaced circumferentially about the hub. Each of the plurality of propeller blade assemblies configured to rotate a respective propeller blade. The variable pitch propeller assembly also includes a hydraulic fluid port assembly integrally formed and including at least three hydraulic fluid ports configured to receive respective flows of hydraulic fluid from a stationary hydraulic fluid transfer sleeve. The variable pitch propeller assembly also includes a pitch actuator assembly coupled in flow communication with at least three hydraulic fluid ports through respective hydraulic fluid transfer tubes. The pitch actuator coupled to the plurality of propeller blade assemblies to selectively control a pitch of the propeller blades. The pitch actuator assembly includes a travel stop configured to limit a rotation of at least one of the pitch actuator assemblies.
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公开(公告)号：US11945600B2
公开(公告)日：2024-04-02
申请号：US17891262
申请日：2022-08-19
Applicant: General Electric Company
Inventor： Daniel Alan Niergarth , Brandon Wayne Miller
Abstract: A fuel system is provided for an aircraft having a fuel source. The fuel system includes a fuel oxygen reduction unit defining a liquid fuel supply path, a stripping gas supply path, a liquid fuel outlet path, and a stripping gas return path, wherein the stripping gas return path is in airflow communication with the fuel source.
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