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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：US20240229679A9
公开(公告)日：2024-07-11
申请号：US17972734
申请日：2022-10-25
Applicant: General Electric Company
Inventor： Brian Lewis Devendorf , Arthur William Sibbach
IPC: F01D25/26
CPC classification number: F01D25/265 , F05D2240/14 , F05D2260/36
Abstract: A gas turbine engine, comprising a turbomachine and a housing at least partially encasing a portion of the turbomachine, the housing having an inner surface and defining in part a void between the inner surface and the portion of the turbomachine, the housing moveable relative to the portion of the turbomachine; and an engine component selectively coupled to the portion of the turbomachine or to the housing.
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公开(公告)号：US12018594B2
公开(公告)日：2024-06-25
申请号：US18462064
申请日：2023-09-06
Applicant: General Electric Company
Inventor： Arthur William Sibbach , Aaron Michael Dziech , Scott Alan Schimmels , Robert R. Rachedi , Jeffrey Douglas Rambo , Brandon Wayne Miller
CPC classification number: F01K23/02 , F01K25/103 , F02C3/22 , F02C3/30 , F02C7/224 , F05D2220/31 , F05D2220/32 , F05D2220/72 , F05D2220/74 , F05D2240/36 , F05D2260/213
Abstract: A pericritical fluid system for a thermal management system associated with a turbine engine may include one or more sensors configured to generate sensor outputs corresponding to one or more phase properties of a pericritical fluid flowing through a cooling circuit of the thermal management system, and a controller configured to generate control commands configured to control one or more controllable components of the thermal management system based at least in part on the sensor outputs. The one or more sensors may include one or more phase detection sensors, such as an acoustic sensor.
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公开(公告)号：US20240159191A1
公开(公告)日：2024-05-16
申请号：US17987299
申请日：2022-11-15
Applicant: General Electric Company
Inventor： Arthur William Sibbach , Jeffrey Donald Clements
CPC classification number: F02C7/36 , F02C3/06 , F02K3/06 , F05D2220/36 , F05D2260/4031
Abstract: A gas turbine engine may include a turbomachine including a compressor section, a combustion section, and a turbine section arranged in serial flow order. The turbomachine defines 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 is drivingly coupled to the turbomachine, and a secondary fan assembly is disposed downstream of the primary fan within the inlet duct. The secondary fan assembly includes a first secondary fan drivingly coupled to the turbomachine in a first rotational direction, and a second secondary fan drivingly coupled to the turbomachine in a second rotational direction opposite the first rotational direction.
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公开(公告)号：US20240026901A1
公开(公告)日：2024-01-25
申请号：US18481584
申请日：2023-10-05
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Arthur William Sibbach
CPC classification number: F04D29/542 , F04D19/002
Abstract: A gas turbine engine includes a fan having a plurality of fan blades, a turbomachine operably coupled to the fan for driving the fan, the turbomachine including 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, the nacelle defining a longitudinal axis, and 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, wherein the inlet pre-swirl feature is transitionable between a first angle with respect to the longitudinal axis of the nacelle and a second angle with respect to the longitudinal axis of the nacelle.
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Patent Agency Ranking
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.
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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.
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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.
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公开(公告)号：US20230096351A1
公开(公告)日：2023-03-30
申请号：US17484429
申请日：2021-09-24
Applicant: General Electric Company
Inventor： Arthur William Sibbach
Abstract: An engine includes a fan section including a plurality of fan blade assemblies. A fan blade assembly includes a midspan shroud separating an inner portion and an outer portion of the fan blade assembly. An outer pitch of the outer portion is variable with respect to an inner pitch of the inner portion.
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公开(公告)号：US20230095723A1
公开(公告)日：2023-03-30
申请号：US17484416
申请日：2021-09-24
Applicant: General Electric Company
Inventor： Arthur William Sibbach
Abstract: A gas turbine engine includes a fan comprising fan blades. In a forward mode of operation the fan blades have a forward pitch and generate forward thrust, and in a reverse mode of operation the fan blades have a reverse pitch and generate reverse thrust. A fan drive shaft drives the fan and an electric machine is connected to the fan drive shaft. In a reverse mode of operation, the electric machine operates as a motor to convert stored electric energy into rotation of the fan drive shaft.
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