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公开(公告)号：US11970277B2
公开(公告)日：2024-04-30
申请号：US18342997
申请日：2023-06-28
CPC分类号： B64D27/24 , B64C29/0033 , F01D15/10 , B64D27/026 , F05D2220/328 , F05D2220/76 , Y02T50/60
摘要： The present invention includes a hybrid propulsion system for an aircraft comprising: an engine disposed within a fuselage of the aircraft, two electrical generators disposed within the fuselage and connected to the engine, and two nacelles. Each nacelle comprises a proprotor, and each nacelle houses two electric motors connected to the proprotor. Each electrical generator is connected to the two electric motors in each nacelle. The proprotors provide lift for vertical takeoff and landing in a helicopter mode. A fan is coupled to the fuselage and connected to two additional electric motors. Each additional electric motor is connected to one of the two electric generators. The fan provides thrust for forward flight during an airplane mode. The airplane mode includes increasing power to the fan while decreasing power to the proprotors to zero.
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2.发明申请公开(公告)号：US20160258497A1
公开(公告)日：2016-09-08
申请号：US15057248
申请日：2016-03-01
CPC分类号： F16D48/06 , B64C29/0058 , B64C29/0066 , B64D35/00 , F01D15/12 , F05D2220/328 , F05D2220/90 , F05D2260/96 , F16D2500/10412 , F16D2500/50293
摘要： Systems and methods to control an amount of axial clearance within a clutch transmission system are disclosed. A propulsion system includes a clutch transmission system having clutch vibratory response clearance control logic configured to iteratively control the amount of axial clearance within the clutch transmission system so as to achieve a desired, e.g., consistent and/or limited, clutch vibratory response.
摘要翻译： 公开了一种用于控制离合器传动系统内的轴向间隙量的系统和方法。 推进系统包括具有离合器振动响应间隙控制逻辑的离合器传动系统，该离合器振动响应间隙控制逻辑被配置为迭代地控制离合器传动系统内的轴向间隙的量，以便实现期望的，例如一致的和/或有限的离合器振动响应。
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公开(公告)号：US07219490B2
公开(公告)日：2007-05-22
申请号：US11201441
申请日：2005-08-10
申请人： Sudarshan Paul Dev
发明人： Sudarshan Paul Dev
IPC分类号： F02K3/02
CPC分类号： F02K3/068 , F02C3/045 , F02C3/064 , F02C3/067 , F02C3/10 , F02C3/145 , F02C3/16 , F02C7/10 , F02K3/00 , F05D2220/323 , F05D2220/324 , F05D2220/325 , F05D2220/326 , F05D2220/327 , F05D2220/328 , F05D2220/80 , F05D2220/90 , F23R3/38 , Y02T50/672
摘要： A gas turbine engine comprising a combustion chamber section, a turbine section, and a compressor section. The turbine section surrounds the combustion chamber and the compressor section surrounds the turbine section.
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公开(公告)号：US20070012026A1
公开(公告)日：2007-01-18
申请号：US11201441
申请日：2005-08-10
申请人： Sudarshan Dev
发明人： Sudarshan Dev
IPC分类号： F02K3/04
CPC分类号： F02K3/068 , F02C3/045 , F02C3/064 , F02C3/067 , F02C3/10 , F02C3/145 , F02C3/16 , F02C7/10 , F02K3/00 , F05D2220/323 , F05D2220/324 , F05D2220/325 , F05D2220/326 , F05D2220/327 , F05D2220/328 , F05D2220/80 , F05D2220/90 , F23R3/38 , Y02T50/672
摘要： A gas turbine engine comprising a combustion chamber section, a turbine section, and a compressor section. The turbine section surrounds the combustion chamber and the compressor section surrounds the turbine section.
摘要翻译： 一种燃气轮机，包括燃烧室部分，涡轮部分和压缩机部分。 涡轮机部分围绕燃烧室并且压缩机部分围绕涡轮部分。
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公开(公告)号：US3117750A
公开(公告)日：1964-01-14
申请号：US24282562
申请日：1962-12-06
CPC分类号： F02K3/025 , F02K1/004 , F05D2220/328
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公开(公告)号：US11731772B2
公开(公告)日：2023-08-22
申请号：US15896383
申请日：2018-02-14
CPC分类号： B64D27/24 , B64C29/0033 , F01D15/10 , B64D2027/026 , F05D2220/328 , F05D2220/76 , Y02T50/60
摘要： The present invention includes a hybrid propulsion system for an aircraft comprising: one or more turboshaft engines that provide shaft power and are capable of providing thrust; at least one of: one or more electrical generators or one or more hydraulic pumps connected to a shaft of the one or more turboshaft engines; and at least two rotatable nacelles, each nacelle housing at least one of: one or more electric motors or one or more hydraulic motors each connected to a proprotor, wherein the electric motor is electrically connected to the electric generator, or the hydraulic motor is connected to the hydraulic pump, respectively, wherein the proprotors provide lift whenever the aircraft is in vertical takeoff and landing and stationary flight, and provide thrust whenever the aircraft is in forward flight.
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公开(公告)号：US10082184B2
公开(公告)日：2018-09-25
申请号：US15057248
申请日：2016-03-01
CPC分类号： F16D48/06 , B64C29/0058 , B64C29/0066 , B64D35/00 , F01D15/12 , F05D2220/328 , F05D2220/90 , F05D2260/96 , F16D2500/10412 , F16D2500/3023 , F16D2500/3026 , F16D2500/30415 , F16D2500/30426 , F16D2500/50293 , F16D2500/7041
摘要： Systems and methods to control an amount of axial clearance within a clutch transmission system are disclosed. A propulsion system includes a clutch transmission system having clutch vibratory response clearance control logic configured to iteratively control the amount of axial clearance within the clutch transmission system so as to achieve a desired, e.g., consistent and/or limited, clutch vibratory response.
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公开(公告)号：US09816394B2
公开(公告)日：2017-11-14
申请号：US14221494
申请日：2014-03-21
发明人： Frank J. Cunha , Timothy S. Snyder
CPC分类号： F01D25/14 , F01D5/187 , F01D9/041 , F05D2220/32 , F05D2220/328 , F05D2220/90 , F05D2240/12 , F05D2240/128 , F05D2260/202 , Y02T50/672 , Y02T50/676
摘要： A panel for use in a gas turbine engine exhaust case is disclosed. The panel has an airfoil section and a flow diverting structure adjacent a leading edge, wherein the flow diverting structure directs fluid flow into an area of the airfoil that lacks sufficient internal pressure for cooling fluid flow.
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公开(公告)号：US08661835B2
公开(公告)日：2014-03-04
申请号：US12648061
申请日：2009-12-28
申请人： Jorge I. Farah , Jason Hickman , Jose Cintron
发明人： Jorge I. Farah , Jason Hickman , Jose Cintron
IPC分类号： F02C7/20
CPC分类号： F02K1/822 , F02K1/002 , F02K1/04 , F02K1/80 , F02K1/82 , F02K1/825 , F05D2220/328 , F05D2220/90 , F05D2230/64 , F05D2260/30 , Y02T50/671 , Y02T50/675
摘要： A bushing for assembling an exhaust duct liner with an exhaust duct in a gas turbine engine comprises a body, a bushing opening and a first tab. The body is insertable into a duct opening in an exhaust duct. The bushing opening extends through the body to receive a shaft of a liner fastener. The first tab protrudes from the body to extend into an interior of the duct to prevent rotation of a head of the liner fastener.
摘要翻译： 用于在燃气涡轮发动机中组装具有排气管道的排气管道衬套的衬套包括主体，衬套开口和第一突出部。 身体可插入排气管道中的管道开口中。 衬套开口延伸穿过主体以接纳衬垫紧固件的轴。 第一突片从主体伸出以延伸到管道的内部，以防止衬套紧固件的头部旋转。
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公开(公告)号：US20110180620A1
公开(公告)日：2011-07-28
申请号：US12397442
申请日：2009-03-04
CPC分类号： F01D25/14 , F01D5/187 , F01D9/041 , F05D2220/32 , F05D2220/328 , F05D2220/90 , F05D2240/12 , F05D2240/128 , F05D2260/202 , Y02T50/672 , Y02T50/676
摘要： A panel for use in a gas turbine engine exhaust case is disclosed. The panel has an airfoil section and a flow diverting structure adjacent a leading edge, wherein the flow diverting structure directs fluid flow into an area of the airfoil that lacks sufficient internal pressure for cooling fluid flow.
摘要翻译： 公开了一种用于燃气涡轮发动机排气箱的面板。 面板具有邻近前缘的翼型部分和分流结构，其中分流结构将流体流引导到缺少足够的内部压力以冷却流体流动的翼型的区域中。
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