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公开(公告)号：US10180084B2
公开(公告)日：2019-01-15
申请号：US15209050
申请日：2016-07-13
IPC分类号： F01D25/24 , B23K31/02 , F01D25/16 , B23K101/00 , B23K101/08 , B23K101/04
摘要： The structural case has an annular body having a central axis and including a plurality of boss sections circumferentially interspaced from one another around the axis by a plurality of arcuate panel sections, each panel section having: two parallel arcuate structural flange members being axially interspaced from one another; a sheet metal wall extending between and interconnecting the two flange members; and at least one rib having an edge welded to the sheet-metal wall.
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2.发明授权公开(公告)号：US09003638B2
公开(公告)日：2015-04-14
申请号：US13792804
申请日：2013-03-11
IPC分类号： H02K15/02
CPC分类号： H02K7/1823 , H02K15/02 , H02K15/16 , Y10T29/49002 , Y10T29/49009 , Y10T29/49012
摘要： A method of assembling an electromechanical device in a gas-turbine engine, including mounting a rotor of the device on a rotor support, securing a stator of the device to a stator support, coupling the rotor support to the stator support such that said rotor is rotatable about said stator, securing the device to a bearing support, securing a bearing assembly on the low pressure shaft, coupling the device to the low pressure shaft by installing the bearing support over the bearing assembly, and drivingly engaging the rotor support to the high pressure shaft.
摘要翻译： 一种在气体涡轮发动机中组装机电装置的方法，包括将所述装置的转子安装在转子支撑件上，将所述装置的定子固定到定子支撑件，将所述转子支撑件联接到所述定子支撑件，使得所述转子是 可绕所述定子旋转，将所述装置固定到轴承支撑件上，将轴承组件固定在所述低压轴上，通过将所述轴承支撑件安装在所述轴承组件上并将所述转子支撑件与所述高压轴驱动地接合而将所述装置联接到所述低压轴 压力轴。
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公开(公告)号：US10443446B2
公开(公告)日：2019-10-15
申请号：US15908210
申请日：2018-02-28
IPC分类号： F01D25/24 , F01D25/00 , F01D11/12 , F01D11/14 , F01D21/04 , F02C7/045 , F04D29/52 , F04D29/02
摘要： A steel soft wall fan case assembly according to one embodiment configured with a thin-walled steel support structure shell including a plurality of annular axial walls of thin sheet metal reinforced by a plurality of rings interconnecting axially adjacent annular axial walls. The steel support structure shell is structurally integrated with honeycomb materials and an annular metallic inner wall. A fabric containment layer may be wrapped around one of the annular axial walls of the steel support structure shell.
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公开(公告)号：US09845729B2
公开(公告)日：2017-12-19
申请号：US14048186
申请日：2013-10-08
CPC分类号： F02C7/08 , B21D15/12 , B21D53/06 , F28D7/0041 , F28D7/082 , F28D21/001 , F28D2021/0026 , F28F1/02 , F28F1/025 , Y10T29/49357
摘要： A method of manufacturing a recuperator segment uses metal tubes deformed into air cells in a waved configuration. The air cells are stacked one to another to form a double skinned recuperator segment providing cold air passages through the respective air cells and hot gas passages through spaces between adjacent air cells.
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公开(公告)号：US09784129B2
公开(公告)日：2017-10-10
申请号：US14449507
申请日：2014-08-01
发明人： Andreas Eleftheriou , Bryan Olver , Carmen Alecu
CPC分类号： F01D25/162 , B64D2027/262 , F02C7/20 , F02K3/06 , Y02T50/672
摘要： A gas turbine engine with a rear mount assembly including link rods interconnecting the bypass duct wall and the core portion and connecting assemblies connected to the bypass duct wall. Each connecting assembly has inner and outer surfaces bordering an opening through which an outer end of a respective link rod extends. The outer surface is accessible from outside the bypass duct wall. A first locking member is engaged to the outer end in a first locked position, and includes an abutment portion located radially inwardly of the inner surface and abutting the inner surface, and an outer portion protruding radially outwardly through the opening beyond the outer surface. A second locking member is engaged the outer end in a second locked position, and has an abutment portion located radially outwardly of the outer surface and abutting the outer surface. A method of supporting a core portion is also discussed.
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公开(公告)号：US09735650B2
公开(公告)日：2017-08-15
申请号：US14667768
申请日：2015-03-25
CPC分类号： H02K7/1823 , H02K15/02 , H02K15/16 , Y10T29/49002 , Y10T29/49009 , Y10T29/49012
摘要： A method of assembling a starter/generator in a gas-turbine engine, including coupling a rotor and a stator of the starter/generator such that the rotor is rotatable with respect to the stator to drive the rotor when the starter/generator is electrically powered and to produce electrical power when the rotor is rotated, securing the stator to a bearing support, coupling the starter/generator to a low pressure shaft of the engine by installing the bearing support over a bearing assembly secured to an end of the low pressure shaft, inserting the low pressure shaft through a high pressure shaft of the engine with the end of the low pressure shaft protruding therefrom and positioning the starter/generator in proximity of an end of the high pressure shaft, and drivingly engaging the rotor to the high pressure shaft.
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公开(公告)号：US10550767B2
公开(公告)日：2020-02-04
申请号：US15188277
申请日：2016-06-21
摘要： A method of installing a segment of a recuperator within an exhaust duct of a gas turbine engine, including positioning the segment such that its exhaust inlet is in fluid flow communication with the turbine section and its exhaust outlet is adapted to deliver an exhaust flow to atmosphere, engaging its air inlet to a plenum in fluid flow communication with the compressor discharge, and engaging its air outlet to another plenum containing the combustor. One of engaging the air inlet and engaging the air outlet includes forming a rigid connection providing sealed fluid flow communication with the corresponding plenum, and the other of engaging the air inlet and engaging the air outlet includes forming a floating connection providing sealed fluid flow communication with the corresponding plenum. The floating connection allows relative movement of the segment within the exhaust duct.
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公开(公告)号：US10364823B2
公开(公告)日：2019-07-30
申请号：US15155195
申请日：2016-05-16
发明人： George Guglielmin , Joe Lanzino , Enzo Macchia , Barry Barnett , Andreas Eleftheriou , Thomas McDonough
IPC分类号： F01D5/14 , F04D29/38 , B82Y30/00 , C23C30/00 , F01D5/28 , F01D9/04 , F01D25/16 , C23C4/01 , F04D29/02 , F04D29/32
摘要： A fan blade of a gas turbine engine is disclosed which is composed of an airfoil having a leading edge and a trailing edge, and a root with a platform and a blade fixing for engaging a fan hub. The fan blade is composed of a core substrate selected from the group consisting of composites and polymers, and an entirety of the airfoil and the root of the fan blade has a nanocrystalline metal outer layer thereon which forms an outer surface fully enveloping the fan blade. The nanocrystalline metal layer formed of a nanocrystalline metal coating has an average grain size of between 10 nm and 500 nm, and the nanocrystalline metal outer layer forms a structural element of the fan blade.
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公开(公告)号：US09938855B2
公开(公告)日：2018-04-10
申请号：US14169354
申请日：2014-01-31
发明人： Daniel Alecu , Andreas Eleftheriou
CPC分类号： F01D25/14 , F02C7/18 , F02K3/06 , F05D2260/601
摘要： A turbine case cooling system and a method for supplying a cooling gas flow are provided. The cooling system has a turbine case and a turbine case cooling manifold. The cooling system also has a fluid or cooling conduit. The cooling conduit has an inlet in fluid communication with the bypass duct, and an outlet in fluid communication with the cooling manifold. The cooling conduit also has an ejector section which in use supplies a motive air flow radially into the cooling conduit to draw a bypass air flow from the bypass duct. The motive air flow mixes with the bypass air flow to form the cooling gas flow. The cooling conduit also has a diffuser section which in use conveys the cooling gas flow toward the outlet in a direction substantially perpendicular to the center axis of the gas turbine engine.
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公开(公告)号：US09376935B2
公开(公告)日：2016-06-28
申请号：US13717898
申请日：2012-12-18
CPC分类号： F01D25/162 , F02K3/06 , F05D2230/60 , Y02T50/671 , Y10T29/4932
摘要： A casing for an aircraft engine includes an outer ring and an inner hub defining an airflow passage therebetween, the outer ring having an axis defining an axial direction; a plurality of struts arranged in a circumferential array and extending radially from the inner hub to the outer ring to mount the inner hub to the outer ring; wherein the outer ring is defined by a double skin including an axially-extending annular outer skin of sheet metal concentrically surrounding and radially-spaced from an annular inner skin of sheet metal, the outer and inner skins generally parallel to one another, an annular front end ring and an annular rear end ring welded or brazed to the outer and inner skins adjacent respective front and rear edges of the skins to define an annular cavity between them, and the outer ring further comprising a plurality of circumferentially spaced axially-extending ribs interconnecting the outer and inner skins to reinforce the double skins.
摘要翻译： 一种用于飞行器发动机的壳体包括外圈和限定其间的气流通道的内毂，所述外圈具有限定轴向的轴线; 多个支柱，其布置成周向阵列并且从所述内毂径向延伸到所述外环以将所述内毂安装到所述外环; 其中所述外环由双层皮肤限定，所述双层皮肤包括与所述金属板的环形内表面同心地围绕并径向间隔开的轴向延伸的环形外皮，所述外表皮和内表皮大体上彼此平行， 端环和环形后端环，其与外表面和内表面相邻地焊接或钎焊，所述外表面和内表面邻近表皮的前后边缘以在其间限定环形空腔，并且所述外环还包括多个周向间隔开的轴向延伸的肋， 外皮和内皮加固双面皮。
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