-
公开(公告)号：US20240003294A1
公开(公告)日：2024-01-04
申请号：US18353472
申请日：2023-07-17
Applicant: General Electric Company
Inventor： Arthur William Sibbach , Allan George van de Wall , Sean Christopher Binion , Brian Lewis Devendorf , Brandon Wayne Miller
CPC classification number: F02C7/047 , F02K3/06 , B64D33/02 , B64D2033/0233
Abstract: A turbofan engine is provided. The turbofan engine includes a fan comprising a plurality of fan blades; a turbomachine operably coupled to the fan for driving the fan, the turbomachine comprising a compressor section, a combustion section, and a turbine section in serial flow order and together defining a core air flowpath; a nacelle surrounding and at least partially enclosing the fan; an inlet pre-swirl feature located upstream of the plurality of fan blades, the inlet pre-swirl feature attached to or integrated into the nacelle; and a means for reducing ice buildup or ice formation on the inlet pre-swirl feature, the means in communication with the inlet pre-swirl feature.
-
公开(公告)号：US20230407785A1
公开(公告)日：2023-12-21
申请号：US18459925
申请日：2023-09-01
Applicant: General Electric Company
Inventor： Ethan Patrick O'Connor , Brandon Wayne Miller , Daniel Alan Niergarth , Alfred Albert Mancini
CPC classification number: F02C3/22 , C10G25/00 , F23K5/08 , B01D19/0005 , F05D2220/323 , C10G2400/08 , F05D2270/07 , C10G2300/202 , F05D2240/35 , F23K2900/05082 , B01D2257/104
Abstract: A fuel oxygen reduction unit for an engine is provided. The fuel oxygen reduction unit includes an inlet fuel line; a stripping gas source; a contactor selectively in fluid communication with the stripping gas source, the inlet fuel line, or both to form a fuel/gas mixture; and a separator that receives the fuel/gas mixture, the separator configured to separate the fuel/gas mixture into an outlet stripping gas flow and an outlet fuel flow; wherein a flow of stripping gas passes through the fuel oxygen reduction unit a single time.
-
公开(公告)号：US11788465B2
公开(公告)日：2023-10-17
申请号：US17578612
申请日：2022-01-19
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Patrick Michael Marrinan , Arthur William Sibbach , Scott Alan Schimmels , Scott David Hunter
CPC classification number: F02C6/06 , F02C6/08 , F02C7/32 , F02C9/00 , F02K3/04 , F05D2220/32 , F05D2220/76
Abstract: A gas turbine engine comprises a turbomachine defining a core flow therethrough during operation. A flow tap is provided in fluid communication with the turbomachine, wherein the flow tap is configured to receive a portion of the core flow therethrough as a bleed flow. A bleed assembly includes a machine load, a bleed flow machine, and a bleed regulator. The bleed flow machine is disposed in fluid communication with the turbomachine through the flow tap, and is configured to drive the machine load. The bleed regulator is configured to regulate a bleed output provided to the bleed flow machine by controlling a capture rate of the bleed flow by the bleed flow machine.
-
公开(公告)号：US20230265764A1
公开(公告)日：2023-08-24
申请号：US18297835
申请日：2023-04-10
Applicant: General Electric Company
Inventor： Steven Douglas Johnson , Julius John Montgomery , Brandon Wayne Miller , Robert Proctor , Bradley W. Fintel , Jeffrey Douglas Rambo
Abstract: A system for controlling blade clearances within a gas turbine engine includes a rotor disk and a rotor blade coupled to the rotor disk. Additionally, the system includes an outer turbine component positioned outward of the rotor blade such that a clearance is defined between the rotor blade and the outer turbine component. Furthermore, the system includes a heat exchanger configured to receive a flow of cooling air bled from the gas turbine engine and transfer heat from the received flow of the cooling air to a flow of coolant to generate cooled cooling air. Moreover, the system includes a valve configured to control the flow of the coolant to the heat exchanger. In this respect, the cooled cooling air is supplied to at least one of the rotor disk or the rotor blade to adjust the clearance between the rotor blade and the outer turbine component.
-
公开(公告)号：US20230228213A1
公开(公告)日：2023-07-20
申请号：US17578612
申请日：2022-01-19
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Patrick Michael Marrinan , Arthur William Sibbach , Scott Alan Schimmels , Scott David Hunter
CPC classification number: F02K3/04 , F02C9/00 , F05D2220/32 , F05D2220/76
Abstract: A gas turbine engine comprises a turbomachine defining a core flow therethrough during operation. A flow tap is provided in fluid communication with the turbomachine, wherein the flow tap is configured to receive a portion of the core flow therethrough as a bleed flow. A bleed assembly includes a machine load, a bleed flow machine, and a bleed regulator. The bleed flow machine is disposed in fluid communication with the turbomachine through the flow tap, and is configured to drive the machine load. The bleed regulator is configured to regulate a bleed output provided to the bleed flow machine by controlling a capture rate of the bleed flow by the bleed flow machine.
-
Patent Agency Ranking
公开(公告)号：US11702985B1
公开(公告)日：2023-07-18
申请号：US17724096
申请日：2022-04-19
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Daniel Alan Niergarth , Brian Gene Brzek , Kevin Edward Hinderliter , Brian Lewis Devendorf , Nathan Evan McCurdy Gibson
IPC: F02C7/12
CPC classification number: F02C7/12 , F05D2220/32 , F05D2260/20
Abstract: A thermal management system is provided for incorporation into a gas turbine engine, wherein the gas turbine engine, the aircraft, or both define a vertical direction. The thermal management system including: a thermal transport bus having a thermal fluid flowing therethrough; a plurality of heat source exchangers in thermal communication with the thermal fluid in the thermal transport bus; and a pump assembly in flow communication with the thermal transport bus, the pump assembly including: a pump; and a pump protection device positioned below the pump along the vertical direction.
-
公开(公告)号：US11685542B2
公开(公告)日：2023-06-27
申请号：US16891337
申请日：2020-06-03
Applicant: General Electric Company
Inventor： Daniel Alan Niergarth , Randy M. Vondrell , Brandon Wayne Miller , Patrick Michael Marrinan , Lawrence Chih-Hui Cheung , Nikolai N. Pastouchenko
IPC: B64D27/10 , B64D27/24 , B64D33/08 , F02K5/00 , F02C7/14 , F02C6/20 , B64C11/00 , B64C21/06 , F01D15/10 , F01D15/12 , F02K3/062 , F04D29/056 , F04D29/063 , F04D29/32 , F04D29/58 , B64D27/02
CPC classification number: B64D33/08 , B64C11/001 , B64C21/06 , B64D27/10 , B64D27/24 , F01D15/10 , F01D15/12 , F02C6/206 , F02C7/14 , F02K3/062 , F02K5/00 , F04D29/056 , F04D29/063 , F04D29/325 , F04D29/582 , B64D2027/026 , F05D2220/323 , F05D2260/213 , F05D2260/98 , Y02T50/60
Abstract: A propulsion system for an aircraft having an aft end is provided herein. The propulsion system can include an electric propulsion engine defining a central axis. The electric propulsion engine can include an electric motor, a fan rotatable about the central axis of the electric propulsion engine by the electric motor, a bearing supporting rotation of the fan, and a thermal management system. The thermal management system can include a lubrication oil circulation assembly for providing the bearing with lubrication oil. The lubrication oil circulation assembly can be driven independently of a shaft of the electric propulsion engine.
-
公开(公告)号：US20230085244A1
公开(公告)日：2023-03-16
申请号：US17475744
申请日：2021-09-15
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , David Marion Ostdiek , Darek Tomasz Zatorski
Abstract: A propulsion system is provided including an unducted rotating fan defining a fan axis; and a turbomachine disposed downstream from the unducted rotating fan, wherein the turbomachine defines a working gas flowpath flowing therethrough; wherein the propulsion system defines a third stream flowpath and an inlet passage having an inlet that is offset from the fan axis, wherein the inlet passage is configured to provide an inlet airflow to the working gas flowpath, and wherein the third stream flowpath bypasses at least a portion of the turbomachine.
-
公开(公告)号：US20230076757A1
公开(公告)日：2023-03-09
申请号：US17470032
申请日：2021-09-09
Applicant: General Electric Company
Inventor： Jeffrey Douglas Rambo , Brandon Wayne Miller , William Joseph Bowden , Matthew Thomas Beyer , Michael John Simonetti
IPC: F02C7/10
Abstract: A gas turbine engine having a waste heat recovery system is provided. The gas turbine engine includes a compressor section, a combustion section, a turbine section, and an exhaust section in serial flow order and together defining a core air flowpath, the exhaust section including a primary exhaust flowpath and a waste heat recovery flowpath parallel to the primary exhaust flowpath; and the waste heat recovery system includes a heat source exchanger positioned in thermal communication with a first portion of the waste heat recovery flowpath.
-
公开(公告)号：US20220402625A1
公开(公告)日：2022-12-22
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.
-
-
-
-
-
-
-
-
-
Search Results
357
records
(took 0.029 seconds)
