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公开(公告)号：US10724435B2
公开(公告)日：2020-07-28
申请号：US15625186
申请日：2017-06-16
Applicant: General Electric Company
Inventor： Christopher James Kroger , Brandon Wayne Miller , Trevor Wayne Goerig , David William Crall , Tsuguji Nakano , Jeffrey Donald Clements , Bhaskar Nanda Mondal
Abstract: A gas turbine engine includes a turbomachine and a fan rotatable by the turbomachine. The fan includes a plurality of fan blades. The gas turbine engine also includes an outer nacelle surrounding the plurality of fan blades and a plurality of part-span inlet guide vanes cantilevered from the outer nacelle at a location forward of the plurality of fan blades along the axial direction. Each of the plurality of inlet guide vanes defines an inner end along the radial direction and it is unconnected with an adjacent part-span inlet guide vane at the inner end.
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公开(公告)号：US10711797B2
公开(公告)日：2020-07-14
申请号：US15625212
申请日：2017-06-16
Applicant: General Electric Company
Inventor： Christopher James Kroger , Brandon Wayne Miller , Trevor Wayne Goerig , David William Crall , Tsuguji Nakano , Jeffrey Donald Clements , Bhaskar Nanda Mondal
Abstract: A gas turbine engine includes a turbomachine and a fan rotatable by the turbomachine. The fan includes a plurality of fan blades, each of the plurality of fan blades defining a fan blade span along a radial direction. The gas turbine engine further includes an outer nacelle surrounding the plurality of fan blades and a plurality of part-span inlet guide varies attached to the outer nacelle at a location forward of the plurality of fan blades along an axial direction. Each of the plurality of inlet guide vanes defines an IGV span along the radial direction, the IGV span being at least about five percent of the fan blade span and up to about fifty-five percent of the fan blade span.
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公开(公告)号：US20200157953A1
公开(公告)日：2020-05-21
申请号：US16196288
申请日：2018-11-20
Applicant: General Electric Company
Inventor： Nitesh Jain , David William Crall , Nicholas Joseph Kray
Abstract: A blade for a propulsion apparatus. The blade includes a body formed of a composite material and the body has opposed pressure and suction sides. The body extends in span between a root and a tip and extends in chord between a leading edge and a trailing edge. The body defines a body tip surface. A protective cover extends from near the tip of the blade toward the root of the blade along the leading edge and a trailing edge of the body. The protective cover defines a protective tip surface and an abrasive material is adhered to the protective tip surface.
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公开(公告)号：US20180100434A1
公开(公告)日：2018-04-12
申请号：US15291110
申请日：2016-10-12
Applicant: General Electric Company
Inventor： Mustafa Dindar , Joseph Donofrio , Richard David Cedar , David William Crall
CPC classification number: F02C7/057 , B64D33/02 , B64D2033/0226 , F02C3/04 , F02C7/042 , F02K3/06 , F05D2220/323 , F05D2240/127 , F05D2260/57 , Y02T50/671
Abstract: The disclosure is towards an inlet cowl for a turbine engine including a surface defining an inlet with a flow path and a method towards controlling the airflow in the flow path. The inlet cowl further includes an inlet lip and inner and outer barrels. The inlet lip confronts the inner barrel at a junction defining a gap.
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公开(公告)号：US12103702B2
公开(公告)日：2024-10-01
申请号：US17071308
申请日：2020-10-15
Applicant: General Electric Company
CPC classification number: B64D45/00 , B32B7/022 , B64C1/38 , B32B2307/558 , B32B2307/72 , B32B2307/732 , B32B2571/02 , B32B2605/18
Abstract: An aircraft defining a longitudinal direction and a lateral direction is provided. The aircraft includes a fuselage; an engine mounted at a location spaced from the fuselage of the aircraft, the engine comprising rotor blades; and at least one fuselage shield removably coupled to the fuselage at a location in alignment with the rotor blades along the lateral direction.
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Patent Agency Ranking
公开(公告)号：US11643969B2
公开(公告)日：2023-05-09
申请号：US17232259
申请日：2021-04-16
Applicant: General Electric Company
CPC classification number: F02C7/12 , F04D19/002 , F04D29/58 , F05D2220/323 , F05D2260/20
Abstract: Structures, such as compressor casings, for reducing a thermal gradient are provided. For example, a compressor case is split such that it includes first and second case segments. The first case segment extends over a first portion of the compressor case circumference and comprises a first inner structure, a first outer structure, and a first porous structure integrally formed as a monolithic component. The first porous structure is defined between the first inner structure and the first outer structure. The second case segment extends over a second portion of the compressor case circumference and comprises a second inner structure, a second outer structure, and a second porous structure integrally formed as a monolithic component. The second porous structure is defined between the second inner structure and the second outer structure. Methods of cooling structures such as compressor casings also are provided.
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公开(公告)号：US11555449B2
公开(公告)日：2023-01-17
申请号：US17088199
申请日：2020-11-03
Applicant: General Electric Company
Inventor： Mustafa Dindar , Joseph Donofrio , Richard David Cedar , David William Crall
Abstract: The disclosure is towards an inlet cowl for a turbine engine including a surface defining an inlet with a flow path and a method towards controlling the airflow in the flow path. The inlet cowl further includes an inlet lip and inner and outer barrels. The inlet lip confronts the inner barrel at a junction defining a gap.
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公开(公告)号：US20220333528A1
公开(公告)日：2022-10-20
申请号：US17232259
申请日：2021-04-16
Applicant: General Electric Company
Abstract: Structures, such as compressor casings, for reducing a thermal gradient are provided. For example, a compressor case is split such that it includes first and second case segments. The first case segment extends over a first portion of the compressor case circumference and comprises a first inner structure, a first outer structure, and a first porous structure integrally formed as a monolithic component. The first porous structure is defined between the first inner structure and the first outer structure. The second case segment extends over a second portion of the compressor case circumference and comprises a second inner structure, a second outer structure, and a second porous structure integrally formed as a monolithic component. The second porous structure is defined between the second inner structure and the second outer structure. Methods of cooling structures such as compressor casings also are provided.
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公开(公告)号：US10968771B2
公开(公告)日：2021-04-06
申请号：US15405016
申请日：2017-01-12
Applicant: General Electric Company
Abstract: A method and icing effects mitigation system are provided. The icing effects mitigation system includes a fluid duct configured to channel a first flow of fluid through the fluid duct from a duct opening to a rotatable member at least partially positioned within the fluid duct. The rotatable member includes a radially inner rotatable portion and a radially outer rotatable portion. The icing effects mitigation system also includes a duct member extending through the fluid duct in a direction approximately orthogonal to a direction of the first flow of fluid. The duct member is configured to channel a second flow of a second fluid therethrough that causes ice accreted on the duct member to shed on a trajectory that impacts the rotatable member at the radially inner portion.
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公开(公告)号：US10374477B2
公开(公告)日：2019-08-06
申请号：US15461654
申请日：2017-03-17
Applicant: General Electric Company
Inventor： Daniel Alan Niergarth , Darek Tomasz Zatorski , David William Crall
Abstract: The present disclosure is directed to an electric machine defining a longitudinal direction, a radial direction, and a circumferential direction, and an axial centerline defined along the longitudinal direction. The electric machine includes a rotor assembly that includes a plurality of carriers arranged along the circumferential direction. Each pair of carriers defines a carrier gap therebetween along the circumferential direction, and each carrier includes a rotor magnet. The rotor assembly further includes an outer ring radially outward of and surrounding the plurality of carriers along the circumferential direction, the outer ring defining a unitary structure.
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