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公开(公告)号：US20230378827A1
公开(公告)日：2023-11-23
申请号：US18085962
申请日：2022-12-21
申请人： General Electric Company , General Electric Deutschland Holding GmbH , General Electric Company Polska Sp. z o.o.
发明人： Bugra Han Ertas , Joseph John Zierer, JR. , Vandana Prabhakar Rallabandi , David Allan Torrey , David William Crall , Mohamed Osama , Adam Tomasz Pazinski , Arthur William Sibbach
CPC分类号： H02K1/20 , H02K5/203 , H02K7/1823 , H02K21/14 , F02C6/00
摘要： An airgap cooling system (140) for an electric machine (100), the electric machine (100) including a rotor assembly (102) rotatably mounted within a stator assembly (120) and defining an airgap (130) therebetween, wherein the stator assembly (120) comprises a lamination stack (124). The airgap cooling system (140) includes a plurality of distribution passages (142) that extend through the lamination stack (124); a plurality of discharge passages (150) that extend between the plurality of distribution passages (142) and the airgap (130); a cooling manifold (160) defining an annular distribution plenum (164) in fluid communication with the plurality of distribution passages (142), wherein the cooling manifold (160) is configured for receiving a cooling fluid (144) and directing the cooling fluid (144) into the distribution plenum (164), through the distribution passage (142) and the discharge passage (150), and into the airgap (130).
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公开(公告)号：US11814174B2
公开(公告)日：2023-11-14
申请号：US17071379
申请日：2020-10-15
IPC分类号： F01D9/04 , F01D5/30 , F01D5/14 , F01D5/18 , F01D7/00 , F01D15/10 , F01D15/12 , F02K5/00 , F02K3/06 , F02C6/20 , F02C9/00 , F02C9/22 , F02C7/26 , F02C7/32 , F02C7/36 , F02C3/113 , B32B7/022 , B64C1/38 , B64D45/00 , F01D17/16 , F01D25/12 , F02C7/264 , F02K1/66 , F02K1/76
CPC分类号： B64D45/00 , B32B7/022 , B64C1/38 , F01D5/146 , F01D5/187 , F01D5/30 , F01D5/3007 , F01D7/00 , F01D9/041 , F01D15/10 , F01D15/12 , F01D17/162 , F01D25/12 , F02C6/206 , F02C7/264 , F02C7/32 , F02C7/36 , F02C9/00 , F02C9/22 , F02K1/66 , F02K1/76 , B32B2307/558 , B32B2307/72 , B32B2307/732 , B32B2571/02 , B32B2605/18 , F02C3/113 , F05D2220/323 , F05D2220/325 , F05D2230/60 , F05D2240/12 , F05D2240/24 , F05D2240/60 , F05D2250/37 , F05D2260/201 , F05D2260/30 , F05D2260/4031 , F05D2260/70 , F05D2270/05 , F05D2270/051 , F05D2270/121 , F05D2270/304 , F05D2270/71 , F05D2270/81
摘要： 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 a plurality of rotor blades; and a fuselage shield attached to or formed integrally with the fuselage at a location in alignment with the plurality of rotor blades along the lateral direction, the fuselage shield comprising a first layer defining a first density and a second layer defining a second density, the first density being different than the second density.
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公开(公告)号：US20180363678A1
公开(公告)日：2018-12-20
申请号：US15625212
申请日：2017-06-16
发明人： Christopher James Kroger , Brandon Wayne Miller , Trevor Wayne Goerig , David William Crall , Tsuguji Nakano , Jeffrey Donald Clements , Bhaskar Nanda Mondal
CPC分类号： F04D29/563 , F01D9/041 , F02C3/04 , F02C7/04 , F02K3/06 , F04D29/542 , F04D29/545 , F04D29/684 , F05D2220/32 , F05D2240/12 , F05D2240/122 , F05D2250/182 , F05D2250/184 , F05D2260/14
摘要： 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：US20180269737A1
公开(公告)日：2018-09-20
申请号：US15461654
申请日：2017-03-17
CPC分类号： H02K1/30 , F01D1/00 , F01D15/10 , F04D19/002 , F05D2220/32 , H02K1/2793 , H02K7/1823 , H02K21/24
摘要： 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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公开(公告)号：US20180195408A1
公开(公告)日：2018-07-12
申请号：US15405016
申请日：2017-01-12
摘要： 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：US20150252683A1
公开(公告)日：2015-09-10
申请号：US13625924
申请日：2012-09-25
CPC分类号： F01D11/24 , F01D11/20 , F01D25/24 , F02C6/08 , F05D2250/323 , F05D2250/324
摘要： Active clearance control ejector systems and methods are disclosed. An example system may include an air ejector; an entrance pipe arranged to supply compressor bleed air to the air ejector; an inlet duct arranged to supply fan bypass air to the air ejector; and a supply pipe arranged to receive ejector outlet air from the air ejector and supply the ejector outlet air to an active clearance control system. The ejector outlet air may include a mixture of the compressor bleed air and the fan bypass air. The air ejector may include a venturi arranged to conduct the compressor bleed air therethrough, thereby drawing the fan bypass air into the air ejector.
摘要翻译： 公开了主动间隙控制喷射器系统和方法。 示例性系统可以包括空气喷射器; 入口管，布置成将压缩机排放空气供应到空气喷射器; 入口管道，其布置成将风扇旁路空气供应到空气喷射器; 以及供应管，布置成从喷射器接收喷射器出口空气，并将喷射器出口空气供应到主动间隙控制系统。 喷射器出口空气可以包括压缩机排出空气和风扇旁路空气的混合物。 空气喷射器可以包括文丘里管，其布置成将压缩机排气通过其中，从而将风扇旁路空气抽入空气喷射器。
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公开(公告)号：US20230003129A1
公开(公告)日：2023-01-05
申请号：US17363102
申请日：2021-06-30
摘要： Composite airfoils and methods for forming composite airfoils are provided. For example, a composite airfoil of a gas turbine engine comprises opposite pressure and suction sides extending radially along a span from a root to a tip, which define opposite radial extremities of the airfoil. The composite airfoil further comprises a body section and a tip section, which includes the tip, that each extend radially along the span. The composite airfoil is formed from a composite material comprising fibers disposed in a matrix material. The tip section has a tip fiber volume, and the body section has a body fiber volume that is greater than the tip fiber volume. Another composite airfoil comprises a tip cap applied over the tip that tapers from a first end to a second end such that each of the pressure and suction side walls of the tip cap narrows from a first thickness to a second thickness.
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公开(公告)号：US11434781B2
公开(公告)日：2022-09-06
申请号：US16161233
申请日：2018-10-16
摘要： An airfoil defining a span extending between a root and a tip. The airfoil includes a frangible airfoil portion extending between a leading edge and a trailing edge and extending between the tip and a fusion line along the span. The frangible airfoil portion includes a first material defining a first modulus of elasticity and further defines an internal cavity. The airfoil includes a residual airfoil portion coupled to the frangible airfoil portion extending from the fusion line to the root along the span and including a second material defining a second modulus of elasticity greater than the first modulus of elasticity. The residual airfoil portion meets the frangible airfoil portion at the fusion line.
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公开(公告)号：US20210339867A1
公开(公告)日：2021-11-04
申请号：US17071379
申请日：2020-10-15
摘要： 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 a plurality of rotor blades; and a fuselage shield attached to or formed integrally with the fuselage at a location in alignment with the plurality of rotor blades along the lateral direction, the fuselage shield comprising a first layer defining a first density and a second layer defining a second density, the first density being different than the second density.
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公开(公告)号：US20210231054A1
公开(公告)日：2021-07-29
申请号：US17088199
申请日：2020-11-03
摘要： 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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