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公开(公告)号：US12134971B2
公开(公告)日：2024-11-05
申请号：US17213503
申请日：2021-03-26
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Ian Francis Prentice , Daniel Alan Niergarth
Abstract: A fan for a gas turbine engine is provided. The fan includes a plurality of fan blades, a disk, and a trunnion mechanism for attaching the fan blades to the disk. The disk can be formed of a plurality of individual disk segments, with the trunnion mechanism attaching one of the plurality of fan blades to a respective disk segment. A retention member is also provided. The retention member includes a means for catching a portion of the trunnion mechanism should a primary attachment system of the trunnion mechanism fail.
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公开(公告)号：US20240328357A1
公开(公告)日：2024-10-03
申请号：US18734131
申请日：2024-06-05
Applicant: General Electric Company
Inventor： Jeffrey Donald Clements , Daniel Alan Niergarth
IPC: F02C7/18
CPC classification number: F02C7/18 , F05D2260/232 , F05D2300/6033
Abstract: A gas turbine includes a turbomachine including a compressor section, a combustion section, and a turbine section arranged in serial flow order. The compressor section includes a high pressure compressor defining a high pressure compressor exit area (AHPCExit). The turbine section includes a low pressure turbine having at least a first stage of turbine rotor blades and a first stage of turbine stator vanes. The gas turbine engine defines a redline exhaust gas temperature (EGT), a total sea level static thrust output (FnTotal), an airfoil density (ρ) of one or both of the first stage of turbine rotor blades and the first stage of the turbine stator vanes, and a corrected specific thrust.
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公开(公告)号：US12104499B2
公开(公告)日：2024-10-01
申请号：US18330000
申请日：2023-06-06
Applicant: General Electric Company
Inventor： Scott Alan Schimmels , Daniel Alan Niergarth , Arthur William Sibbach , Brandon Wayne Miller
CPC classification number: F01D25/10 , F01D25/12 , F02C7/12 , F05D2220/32 , F05D2260/20 , F05D2260/213
Abstract: A method of regulating pressure in a thermal transport bus of a gas turbine engine, the method including: operating the gas turbine engine with the thermal transport bus having an intermediary heat exchange fluid flowing therethrough, the thermal transport bus including one or more heat source heat exchangers and one or more heat sink heat exchangers in thermal communication through the intermediary heat exchanger fluid; and adjusting a flow volume of the thermal transport bus using a variable volume device in fluid communication with the thermal transport bus in response to a pressure change associated with the thermal transport bus.
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公开(公告)号：US20240280049A1
公开(公告)日：2024-08-22
申请号：US18650586
申请日：2024-04-30
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
CPC classification number: F02C6/06 , F02C7/185 , F05D2260/213
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
O
U
T
A
D
T
E
x
i
t
)
2
*
E
G
T
A
H
P
C
E
x
i
t
*
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.-
公开(公告)号：US11994066B2
公开(公告)日：2024-05-28
申请号：US17874358
申请日：2022-07-27
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Kevin Edward Hinderliter , Daniel Alan Niergarth , Brian Gene Brzek
CPC classification number: F02C7/12 , F02C7/06 , F05D2240/50 , F05D2260/20
Abstract: A thermal management system of a gas turbine engine, the thermal management system including: a thermal transport bus configured to have a heat exchange fluid flowing therethrough and including a pump including a plurality of bearings; an auxiliary thermal bus in thermal communication with the plurality of bearings; and an auxiliary heat exchanger in thermal communication with the auxiliary thermal bus.
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Patent Agency Ranking
公开(公告)号：US20240141835A1
公开(公告)日：2024-05-02
申请号：US17978629
申请日：2022-11-01
Applicant: General Electric Company
Inventor： Daniel Alan Niergarth , Jeffrey Donald Clements , Jeffrey S. Spruill , Daniel Endecott Osgood , Erich Alois Krammer , Matthew Kenneth MacDonald , Scott Alan Schimmels
CPC classification number: F02C9/16 , F02C7/18 , F05D2260/20 , F05D2270/303
Abstract: A gas turbine engine is provided. The gas turbine engine includes: a turbomachine having 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; wherein the gas turbine engine defines a redline exhaust gas temperature (EGT) in degrees Celsius, a total sea level static thrust output (FnTotal) in pounds, and a corrected specific thrust, wherein the corrected specific thrust is greater than or equal to 42 and less than or equal to 90, the corrected specific determined as follows: FnTotal×EGT/(AHPCExit2×1000).
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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.
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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.
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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.
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公开(公告)号：US11674435B2
公开(公告)日：2023-06-13
申请号：US17361804
申请日：2021-06-29
Applicant: General Electric Company
Inventor： Nicholas M. Daggett , Gert Johannes van der Merwe , Daniel Alan Niergarth , Brian Lewis Devendorf
CPC classification number: F02C3/06 , F02C9/58 , F02K3/06 , F05D2220/32 , F05D2220/36
Abstract: A fan assembly for a gas turbine engine includes a fan disk, a trunnion, an actuation device, a fan blade, and a counterweight assembly. The trunnion is mounted to the fan disk. The actuation device is operably coupled to the trunnion. The fan blade is rotatably attached to the fan disk. The counterweight assembly includes a link arm, a lever arm, a hinge, and a counterweight. The link arm is connected to the trunnion, to the actuation device, or to both. The link arm is configured to drive rotation of the trunnion relative to the fan disk. The hinge is pivotably connected to the lever arm. The lever arm is connected to the link arm and is disposed to rotate about a connection point of the lever arm and the hinge. The counterweight is mounted to the lever arm at a location spaced from the hinge.
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