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公开(公告)号：US20150361819A1
公开(公告)日：2015-12-17
申请号：US14604228
申请日：2015-01-23
发明人： Alan H. Epstein
CPC分类号： F01D9/041 , F01D1/023 , F01D5/148 , F01D5/225 , F01D17/162 , F02C9/20 , F02K3/075 , F02K3/077 , F04D29/563 , Y02T50/673
摘要： A gas turbine engine is provided that includes a core flow path to direct a core stream flow. A common flow path is outboard of the core flow path, where the common flow path directs both a second stream flow and a third stream flow. Another gas turbine engine is provided that includes an outer case structure around a central longitudinal engine axis. An intermediate case structure is inboard of the outer case structure, where the intermediate case structure and the outer case structure direct both a third stream flow and a second stream flow. An inner case structure is inboard of the intermediate case structure, where the inner case structure and the intermediate case structure direct a core stream flow.
摘要翻译： 提供了一种燃气涡轮发动机，其包括用于引导芯流流动的芯流动路径。 公共流动路径在核心流动路径的外侧，其中公共流动路径引导第二流和第三流。 提供另一燃气涡轮发动机，其包括围绕中心纵向发动机轴线的外壳结构。 中间壳结构在外壳结构的内侧，其中中间壳结构和外壳结构指向第三流流和第二流流。 内壳结构在中间壳结构的内侧，其中内壳结构和中间壳结构引导芯流流。
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公开(公告)号：US20150267551A1
公开(公告)日：2015-09-24
申请号：US14458619
申请日：2014-08-13
发明人： Gary D. Roberge
摘要： A gas turbine engine has a fan rotor including at least one stage, with the at least one stage delivering a portion of air into a low pressure duct, and another portion of air into a compressor. The compressor is driven by a turbine rotor, and the fan rotor is driven by a fan drive turbine. A channel selectively communicates air from the low pressure duct across a boost compressor.
摘要翻译： 燃气涡轮发动机具有包括至少一个级的风扇转子，所述至少一个级将空气的一部分输送到低压管道中，另一部分空气进入压缩机。 压缩机由涡轮转子驱动，风扇转子由风扇驱动涡轮驱动。 通道选择性地将来自低压管道的空气穿过增压压缩机。
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公开(公告)号：US20150198116A1
公开(公告)日：2015-07-16
申请号：US14595570
申请日：2015-01-13
IPC分类号： F02K1/46
CPC分类号： F02K1/1269 , F02K3/075 , F02K3/077 , F02K3/10 , F02K3/105 , F05D2240/129 , Y02T50/671
摘要： A variable area exhaust mixer is provided for a gas turbine engine. The variable area exhaust mixer includes an outer wall with a multiple of doors. Each of the multiple of doors is operable to control a passage entrance into at least one of a multiple of circumferentially arrayed vanes with a respective strut flow passage which essentially alters its bypass ratio during flight to match requirements.
摘要翻译： 为燃气涡轮发动机提供可变面积排气混合器。 可变面积排气混合器包括具有多个门的外壁。 多个门中的每一个可操作以控制通道入口到具有相应的支柱流动通道的周向排列的叶片的多个中的至少一个，其在飞行期间基本上改变其旁路比以匹配要求。
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公开(公告)号：US20150128561A1
公开(公告)日：2015-05-14
申请号：US14209687
申请日：2014-03-13
CPC分类号： F02K1/1223 , F02K1/1207 , F02K1/1238 , F02K1/15 , F02K1/80 , F02K3/075 , F02K3/077 , F02K3/115 , F05D2250/411 , F05D2260/50 , F05D2260/56 , F05D2270/051 , F05D2270/66 , Y02T50/671
摘要： An exhaust nozzle for a gas turbine engine may include a plurality of flap trains in the exhaust stream of the gas turbine engine. The flap trains are operable to selectively control three separate flow paths of gas that traverse the engine. A first stream of is the core airflow. The second stream of air is peeled off of the first stream to form a low pressure fan bypass air stream. The third stream of air traverses along the engine casing and is passed over a flap assembly to aid in cooling. The flaps are operable converge/diverge to control the multiple streams of air.
摘要翻译： 用于燃气涡轮发动机的排气喷嘴可以包括在燃气涡轮发动机的排气流中的多个翼片系列。 翼板系统可操作以选择性地控制穿过发动机的气体的三个独立的流动路径。 第一流是核心气流。 将第二气流从第一流中剥离以形成低压风扇旁路气流。 第三气流沿着发动机壳体横移并且通过翼片组件以帮助冷却。 翼片可操作地收敛/发散以控制多个空气流。
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公开(公告)号：US20150113941A1
公开(公告)日：2015-04-30
申请号：US14522819
申请日：2014-10-24
发明人： John R. Buey , Robert H. Bush , Felix Izquierdo
CPC分类号： F02K3/077 , F02K1/09 , F02K1/15 , F02K3/02 , F02K3/075 , F05D2240/12 , F05D2270/051 , F05D2270/44
摘要： A flow control device includes a first axially extending flow control surface, a second axially extending flow control surface radially offset from the first surface to define a gas flow path therebetween, the gas flow path having a downstream flow path exit, and a third axially extending flow control surface radially offset from the first surface and capable of axially translating with respect to the first and second surfaces for modifying the gas flow path and selectively closing the flow path exit. A turbofan engine includes a core flow passage, a fan bypass passage located radially outward from the core flow passage, a third stream bypass passage located radially outward from the fan bypass passage, and a flow control device that dynamically regulates the third stream bypass passage, allowing fluid flowing through the third stream bypass passage to provide thrust to the turbofan engine and reduce afterbody drag.
摘要翻译： 流量控制装置包括第一轴向延伸的流量控制表面，从第一表面径向偏移的第二轴向延伸流动控制表面以限定其间的气体流动路径，气体流动路径具有下游流动通道出口，以及第三轴向延伸 流量控制表面从第一表面径向偏移并且能够相对于第一和第二表面轴向平移，用于修改气体流动路径并选择性地关闭流动通道出口。 涡轮风扇发动机包括芯流道，从芯流道径向向外设置的风扇旁通通道，从风扇旁通通道径向向外设置的第三流旁通通道和动态调节第三流旁通通道的流量控制装置， 允许流体流过第三流旁路通道以向涡轮风扇发动机提供推力并减少后轮阻力。
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公开(公告)号：US08984891B2
公开(公告)日：2015-03-24
申请号：US12982265
申请日：2010-12-30
IPC分类号： F02K1/00 , F02K1/82 , F02C9/20 , F02K1/08 , F02K1/10 , F02K3/072 , F02K3/075 , F02K3/077 , F02K3/10 , F02K7/16
CPC分类号： F02K1/82 , F02C9/20 , F02K1/06 , F02K1/08 , F02K1/09 , F02K1/10 , F02K1/30 , F02K3/062 , F02K3/065 , F02K3/072 , F02K3/075 , F02K3/077 , F02K3/08 , F02K3/10 , F02K7/16
摘要： An aircraft gas turbine engine has a row of FLADE fan blades disposed radially outwardly of and drivingly connected to a fan in the engine's fan section. The FLADE fan blades extend across a FLADE duct circumscribing the fan section. A two dimensional air discharge passage is in fluid flow communication with the FLADE duct and with FLADE air upstream and downstream discharge slots in a divergent flap of a two dimensional exhaust nozzle. A valve fully closes the upstream slot when the downstream slot is fully opened and fully opens the upstream slot when the downstream slot is fully closed. The upstream and downstream slots may be located upstream and downstream respectfully of a nozzle discharge area in the nozzle. A sliding deck slides aft or down to open upstream slot and close downstream slot and slides forward or up to close upstream slot and open downstream slot.
摘要翻译： 飞机燃气涡轮发动机具有一排FLADE风扇叶片，其设置在发动机风扇部分中的径向向外并与风扇连接。 FLADE风扇叶片延伸穿过限制风扇部分的FLADE风管。 二维空气排放通道与FLADE管道流体流动连通，并且具有FLADE空气上游和下游排放槽，位于二维排气喷嘴的发散阀瓣中。 当下游槽完全打开时，阀完全关闭上游槽，当下游槽完全关闭时，阀完全打开上游槽。 上游和下游槽可以相对于喷嘴中的喷嘴排放区域位于上游和下游。 滑动台面向下滑动以打开上游槽，并关闭下游槽，向前或向上滑动以关闭上游槽并打开下游槽。
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公开(公告)号：US20140238043A1
公开(公告)日：2014-08-28
申请号：US14343155
申请日：2012-09-05
IPC分类号： F02C3/04
摘要： One embodiment of the present invention is a unique gas turbine engine system. Another embodiment is a unique exhaust nozzle system for a gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engine systems and exhaust nozzle systems for gas turbine engines. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.
摘要翻译： 本发明的一个实施例是独特的燃气涡轮发动机系统。 另一个实施例是用于燃气涡轮发动机的独特的排气喷嘴系统。 其他实施例包括用于燃气涡轮发动机系统和用于燃气涡轮发动机的排气喷嘴系统的装置，系统，装置，硬件，方法和组合。 本申请的其它实施例，形式，特征，方面，益处和优点将从本文提供的描述和附图中变得显而易见。
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公开(公告)号：US20140216056A1
公开(公告)日：2014-08-07
申请号：US13630164
申请日：2012-09-28
IPC分类号： F02C7/12
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.
摘要翻译： 为涡轮发动机提供热交换模块。 热交换模块包括管道和多个热交换器。 管道包括在多个同心管壁之间径向限定的流路。 流路沿轴向中心线延伸穿过第一管道端和第二管道端之间的管道。 热交换器位于流路内，围绕中心线周向布置。
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公开(公告)号：US08572947B2
公开(公告)日：2013-11-05
申请号：US12604759
申请日：2009-10-23
IPC分类号： F02K3/02
CPC分类号： F02K3/077 , B64C7/02 , B64D2033/0226 , F02K1/36 , F02K3/025 , F02K3/075 , F05D2260/601 , F05D2270/17
摘要： The present inventions include a boundary layer ejector fluidically connecting boundary layer bleed slots from an external surface of an aircraft to reduce aircraft/nacelle/pylon drag, reduce jet noise and decrease thrust specific fuel consumption. In one embodiment a boundary layer withdrawn through the boundary layer bleed slots is entrained with an exhaust flow of a gas turbine engine. In another embodiment a boundary layer withdrawn through the boundary layer bleed slots is entrained with a flow stream internal to the gas turbine engine, such as a fan stream of a turbofan. Members can be provided near an outlet of a passageway conveying the withdrawn boundary layer air to locally reduce the pressure of the fluid in which the withdrawn boundary layer air is to be entrained. A lobed mixer can be used in some embodiments to effect mixing between the boundary layer and a primary fluid of the ejector.
摘要翻译： 本发明包括边界层喷射器从飞行器的外表面流体连接边界层排放槽以减少飞机/机舱/塔架阻力，减少喷气噪声并减小推力特定燃料消耗。 在一个实施例中，通过边界层排放槽排出的边界层与燃气涡轮发动机的排气流一起被夹带。 在另一个实施例中，通过边界层排出槽排出的边界层与燃气涡轮发动机内部的流动流（例如涡扇风扇的风扇流）一起被夹带。 构件可以设置在通道的出口附近，该通道输送被排出的边界层空气，以局部地减小被排出的边界层空气被夹带的流体的压力。 在一些实施例中，可以使用裂片混合器来实现边界层和喷射器的初级流体之间的混合。
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公开(公告)号：US20130104524A1
公开(公告)日：2013-05-02
申请号：US13287446
申请日：2011-11-02
申请人： Daniel B. Kupratis
发明人： Daniel B. Kupratis
CPC分类号： F02K3/04 , F02C3/107 , F02K3/06 , F02K3/077 , Y02T50/671
摘要： A gas turbine engine comprises an outer engine case, a combustor, a high pressure spool and a low pressure spool. The combustor is disposed within the outer engine case. The high pressure spool is configured for rotation coaxially with the combustor. The low pressure spool is configured for rotation coaxially with the high pressure spool. The low pressure spool is configured to rotate at speeds faster than that of the high pressure spool during operation of the gas turbine engine. In one embodiment, the low pressure spool includes a gear system configured to rotate a low pressure compressor faster than a low pressure turbine. In another embodiment, the high pressure spool rotates outward of the combustor within the outer engine case. In another embodiment, the high pressure spool includes a drum having radially inward projecting blades and vanes and radially outward projecting fan blades.
摘要翻译： 燃气涡轮发动机包括外发动机壳体，燃烧器，高压阀芯和低压阀芯。 燃烧器设置在外部发动机壳体内。 高压阀芯构造成与燃烧器同轴旋转。 低压阀芯构造成与高压阀芯同轴旋转。 低压阀芯构造成在燃气涡轮发动机的运行期间以比高压阀芯更快的速度旋转。 在一个实施例中，低压阀芯包括被配置为比低压涡轮机更快地旋转低压压缩机的齿轮系统。 在另一个实施例中，高压阀芯在外部发动机壳体内向外旋转燃烧器。 在另一个实施例中，高压线轴包括具有径向向内突出的叶片和叶片以及径向向外突出的风扇叶片的滚筒。
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