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公开(公告)号：US09945325B2
公开(公告)日：2018-04-17
申请号：US14646990
申请日：2013-11-06
发明人： Gary D. Roberge
CPC分类号： F02K3/115 , F01D9/065 , F02C7/06 , F02C7/14 , F02C7/18 , F02K3/06 , F02K3/105 , F05D2210/12 , F05D2240/123 , F05D2240/124 , F05D2250/182 , F05D2250/60 , F05D2260/20 , F05D2260/213 , F05D2260/4031 , F05D2260/98 , Y02T50/676
摘要： An oil cooling system and method are provided for use with respect to a lubricated mechanical system within a bypass configured gas turbine engine. A surface cooler is fluidly linked to the lubricated mechanical system to receive oil from the lubricated mechanical system for cooling and reuse. In an embodiment, the surface cooler is mounted on an existing surface within the bypass airflow path of the bypass configured gas turbine engine to provide effective cooling while avoiding the introduction of additional aerodynamic disturbances in the bypass path. In an embodiment, the surface cooler is mounted on the fan casing or on a fan exit guide vane.
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公开(公告)号：US20110056208A1
公开(公告)日：2011-03-10
申请号：US12556359
申请日：2009-09-09
申请人： James W. Norris , Alan Epstein , Gary D. Roberge , Mark W. Costa , Andrew P. Berryann , Daniel B. Kupratis
发明人： James W. Norris , Alan Epstein , Gary D. Roberge , Mark W. Costa , Andrew P. Berryann , Daniel B. Kupratis
IPC分类号： F02C3/10
CPC分类号： F02C3/107 , F02C3/145 , F02C7/32 , F02C7/36 , F02K3/105 , F05D2220/76 , Y02T50/671
摘要： A gas turbine engine comprises a fan drive gear system, a low spool connected to the fan drive gear system, and a high spool disposed aft of the low spool. The low spool comprises a rearward-flow low pressure compressor disposed aft of the fan drive gear system, and a forward-flow low pressure turbine disposed aft of the low pressure compressor. The high spool comprises a forward-flow high pressure turbine disposed aft of the low pressure turbine, a combustor disposed aft of the high pressure turbine, and a forward-flow high pressure compressor disposed aft of the combustor.
摘要翻译： 燃气涡轮发动机包括风扇驱动齿轮系统，连接到风扇驱动齿轮系统的低阀芯和位于低阀芯的后面的高阀芯。 低阀芯包括设置在风扇驱动齿轮系统后面的向后流动的低压压缩机，以及设置在低压压缩机后面的前进低压涡轮机。 高阀芯包括设置在低压涡轮机后方的前流高压涡轮机，设置在高压涡轮机后方的燃烧器和设置在燃烧器后部的前进高压压缩机。
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3.发明申请Method of improving the ignition performance of an after-burner device for a bypass turbojet, and an after-burner device of improved ignition performance 有权提高旁路涡轮喷气发动机后燃烧器装置的点火性能的方法以及提高点火性能的后燃烧器装置公开(公告)号：US20050257527A1
公开(公告)日：2005-11-24
申请号：US11063741
申请日：2005-02-24
申请人： Sebastien Baboeuf , Sabine Charpenel , Eric Maingre , Alain Page , Jacques Roche
发明人： Sebastien Baboeuf , Sabine Charpenel , Eric Maingre , Alain Page , Jacques Roche
摘要： The after-burner device receives a “hot” central primary flow from the turbine of the turbojet and a “cold” peripheral secondary flow, and it has an after-burner ignition zone situated in the secondary flow that reaches the after-burner device. A fraction of the primary flow is brought into the after-burner ignition zone in order to raise the temperature in said zone to a value that is higher than that of the secondary flow so as to encourage after-burner ignition.
摘要翻译： 后燃烧器装置从涡轮喷气机的涡轮机和“冷”外围二次流接收“热”中心主流，并且其具有位于二次流中的后燃烧器点火区域到达后燃烧器装置。 将主要流量的一部分引入后燃烧器点火区域，以将所述区域中的温度升高到高于二次流的温度，以便鼓励后燃烧器点火。
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公开(公告)号：US3779282A
公开(公告)日：1973-12-18
申请号：US3779282D
申请日：1971-11-08
申请人： BOEING CO
发明人： KLEES G
CPC分类号： F02K3/075 , F02K3/04 , F02K3/077 , F02K3/105 , F02K7/16 , F05D2220/80 , Y10T137/86863
摘要： A flow control system for inverting the positions of two adjacent constant area flow patterns within the confines of a fluid passageway having an area substantially equal to the combined area of the two separated flow patterns. The preferred embodiments involve annular first and second duct means divided into duct elements shaped and arranged such that two annular flow patterns are discharged at the exit end of the passageway in an inverted adjacent concentric relationship to that which exists at the entrance end of the passageway. Valve embodiments for optionally causing either inverted or straight through flow are also presented.
摘要翻译： 一种流量控制系统，用于将具有基本上等于两个分离的流动模式的组合面积的区域的流体通道的范围内的两个相邻恒定区域流动模式的位置反转。 优选的实施例涉及环形的第一和第二管道装置，被分成形状和布置的管道元件，使得两个环形流动图案在通道的出口端以与存在于通道的入口端处的倒置的相邻同心关系排出。 还提出了用于任选地引起倒流或直流的阀实施例。
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公开(公告)号：US20170122210A1
公开(公告)日：2017-05-04
申请号：US15412729
申请日：2017-01-23
IPC分类号： F02C7/18
CPC分类号： F02C7/185 , B64D33/08 , B64D33/10 , B64D33/12 , B64D2033/024 , F01D25/08 , F01D25/14 , F02C7/12 , F02C7/14 , F02C7/32 , F02K3/077 , F02K3/105 , F02K3/115 , F05D2260/20 , F05D2260/213 , F28D2021/0021 , F28D2021/0026 , Y02T50/675
摘要： A heat exchange module is provided for a turbine engine. The heat exchange module includes a duct and a plurality of heat exchangers. The duct includes a flowpath defined radially between a plurality of concentric duct walls. The flowpath extends along an axial centerline through the duct between a first duct end and a second duct end. The heat exchangers are located within the flowpath, and arranged circumferentially around the centerline.
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公开(公告)号：US09051056B2
公开(公告)日：2015-06-09
申请号：US13038874
申请日：2011-03-02
申请人： Robert E. Leese
发明人： Robert E. Leese
CPC分类号： B64D37/34 , F02C7/14 , F02C7/185 , F02C7/224 , F02K3/105 , F02K3/115 , F28D2021/0026 , Y02T50/671 , Y02T50/675
摘要： A fuel heat management system including a fuel line for conveying fuel, and a fuel/oil heat exchanger which receives fuel flowing through the fuel line. The fuel heat management system further comprises an oil line for circulating oil from an engine oil system to the fuel/oil heat exchanger and back to the engine oil system. The fuel/oil heat exchanger brings the oil and the fuel into heat exchange relationship. The fuel heat management system further includes an air/oil heat exchanger which receives oil flowing through the oil line, the air/oil heat exchanger bringing the oil and air into heat exchange relationship. The fuel heat management system further includes an air/fuel heat exchanger which receives fuel flowing through the fuel line, the air/fuel heat exchanger bringing the fuel and air into heat exchange relationship.
摘要翻译： 一种燃料热管理系统，包括用于输送燃料的燃料管线和接收燃料流经燃料管路的燃料/油热交换器。 燃料热管理系统还包括用于将油从发动机油系统循环到燃料/油热交换器并返回到发动机油系统的油管线。 燃油/油热交换器使油和燃料成为热交换关系。 燃料热管理系统还包括空气/油热交换器，其接收流过油管线的油，空气/油热交换器使油和空气成为热交换关系。 燃料热管理系统还包括空气/燃料热交换器，其接收流过燃料管路的燃料，空气/燃料热交换器使燃料和空气进入热交换关系。
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公开(公告)号：US5117628A
公开(公告)日：1992-06-02
申请号：US469982
申请日：1990-01-25
申请人： John M. Koshoffer
发明人： John M. Koshoffer
CPC分类号： F02K1/48 , F02K1/386 , F02K3/10 , F02K3/105 , F05D2260/20 , Y02T50/675
摘要： A mixer arrangement for a bypass type gas turbine engine is disclosed. The mixer is convoluted and generally annular and defines radially and axially extending first and second chutes adapted to receive, respectively, a hot gas stream from the engine core and a cooler gas stream from the fan duct. A pre-mixer is disposed upstream of the mixer and is also convoluted and is aligned in flow communication with the second chutes of the mixer such that the hot gas stream received by the pre-mixer is mixed with the cooler fan air stream received by the second chutes to raise the temperature of the fan air entering an afterburner section of the engine.
摘要翻译： 公开了一种用于旁路式燃气涡轮发动机的混合器装置。 混合器是回旋的并且大致环形并且限定径向和轴向延伸的第一和第二滑槽，其适于分别接收来自发动机芯的热气流和来自风扇导管的较冷气体流。 预混合器设置在混合器的上游并且还被卷积并且与混合器的第二滑槽流动连通地对准，使得由预混合器接收的热气流与由所述混合器接收的冷却器风机气流混合 第二滑槽，以提高进入发动机加燃器部分的风扇空气的温度。
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公开(公告)号：US4519208A
公开(公告)日：1985-05-28
申请号：US420914
申请日：1982-09-21
CPC分类号： F02K3/12 , F02K3/075 , F02K3/105 , Y02T50/671
摘要： The invention relates to a propulsion engine, particularly for supersonic aircraft. An internal propulsion system comprises an envelope displaying a tapered center portion, around which is coaxially mounted an external propulsion system which lacks a separate compressor. According to the invention, mechanisms are provided to divert toward the combustion chamber of the external propulsion system an adjustable fraction of the compressed air arriving from the last compressor stage of the internal propulsion system. A blower which is driven by the external turbine exhausts in parallel with the latter into an annular conduit which emerges between the internal nozzle and external nozzle and an exhaust nozzle, all of these nozzles being of variable geometry. The purpose of the invention is to improve variable cycle propulsion engines for second-generation supersonic aircraft.
摘要翻译： 本发明涉及一种推进发动机，特别是用于超音速飞行器。 内部推进系统包括显示锥形中心部分的外壳，其同轴地安装有缺少单独的压缩机的外部推进系统。 根据本发明，提供了一种机构，用于向外部推进系统的燃烧室转移从内部推进系统的最后一个压缩机级到达的压缩空气的可调部分。 由外部涡轮机驱动的鼓风机与后者平行排放到环形管道中，该管道出现在内部喷嘴和外部喷嘴之间以及排气喷嘴之间，所有这些喷嘴都具有可变的几何形状。 本发明的目的是改进用于第二代超音速飞机的可变循环推进发动机。
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公开(公告)号：US3938328A
公开(公告)日：1976-02-17
申请号：US425586
申请日：1973-12-17
申请人： Garry W. Klees
发明人： Garry W. Klees
摘要： Air breathing gas turbine engine design concepts, and methods and apparatus for providing variable engine cycles are disclosed. The preferred engine embodiments involve two flow control valve systems for internal management of air, each of which have the capacity to cross-over or invert adjacent annular flow patterns, and at least one of which is capable of switching from inverted to straight through flow.
摘要翻译： 公开了空气呼吸燃气涡轮发动机设计概念以及用于提供可变发动机循环的方法和装置。 优选的发动机实施例涉及用于内部管理空气的两个流量控制阀系统，每个流量控制阀具有交叉或反转相邻环形流动模式的能力，并且其中的至少一个能够通过流从倒流切换到直流。
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公开(公告)号：US3854286A
公开(公告)日：1974-12-17
申请号：US32976873
申请日：1973-02-05
申请人： BOEING CO
发明人： KLEES G
摘要： Air breathing gas turbine engine design concepts, methods and apparatus for providing variable bypass and variable engine cycles. The disclosed preferred embodiments involve flow control systems for internal management of air within the engine which have a capability to crossover or invert adjacent annular flow patterns without interference, necking down, or departure from the confines of an annular passageway, and which may be switched from inverted to straight through flow.
摘要翻译： 空气呼吸燃气涡轮发动机设计概念，提供可变旁路和可变发动机循环的方法和装置。 所公开的优选实施例涉及用于内部管理发动机内的空气的流量控制系统，其具有跨接或反转相邻环形流动图案的能力，而不会干涉，收缩或偏离环形通道的范围，并且可以从 倒流直流。
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