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81. 发明申请

US20160201566A1 LARGE DISPLACEMENT HIGH TEMPERATURE SEAL 审中-公开
标题翻译：大排量高温密封
公开(公告)号：US20160201566A1
公开(公告)日：2016-07-14
申请号：US14913215
申请日：2014-09-10
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Gary J. Dillard
IPC分类号： F02C7/28 , F01D25/30 , F01D11/00 , F16J15/06 , F16J15/02
CPC分类号： F02C7/28 , F01D11/005 , F01D25/30 , F02K1/805 , F02K1/82 , F02K1/825 , F05D2220/32 , F05D2220/90 , F05D2240/12 , F05D2240/55 , F05D2250/12 , F05D2250/14 , F16J15/021 , F16J15/06 , Y02T50/671
摘要： A seal assembly is provided for a gas turbine engine. This seal assembly includes a tadpole seal with a bulb and a tail, where the tail is directed toward a backwall. The seal assembly also includes a faying extension that at least partially extends into the channel and into contact with the bulb. An exhaust duct is also provided for a gas turbine engine. This exhaust duct includes a seal assembly between a first exhaust duct section and a second exhaust duct section. The seal assembly includes a tadpole seal with a bulb and a tail, where the tail is directed upstream.
摘要翻译：为燃气涡轮发动机提供密封组件。该密封组件包括具有灯泡和尾部的t ole密封，尾部朝向后壁。密封组件还包括至少部分地延伸到通道中并与灯泡接触的引线延伸部。还提供了用于燃气涡轮发动机的排气管道。该排气管道包括在第一排气管段和第二排气管段之间的密封组件。密封组件包括具有灯泡和尾部的t ole密封，尾部朝向上游。

82. 发明申请

US20150285158A1 AIRCRAFT VAPOUR TRAIL CONTROL SYSTEM 有权
标题翻译：飞机蒸汽拖车控制系统
公开(公告)号：US20150285158A1
公开(公告)日：2015-10-08
申请号：US14644799
申请日：2015-03-11
申请人： ROLLS-ROYCE PLC
发明人： Malcolm HILLEL , Peter SWANN , Andrew Martin ROLT , Paul FLETCHER
IPC分类号： F02C9/20 , B64D31/06 , B64D33/04 , F02K1/76
CPC分类号： F02C9/20 , B64D31/06 , B64D33/04 , F02K1/1207 , F02K1/16 , F02K1/76 , F02K1/825 , F02K3/075 , F05D2220/323 , F05D2270/08 , F05D2270/311 , F05D2270/312 , F05D2270/313 , Y02T50/677
摘要： The invention concerns an aircraft propulsion control system in which a gas turbine engine has an actuable flow opening for control of flow to or from a portion of the engine. One or more sensor is arranged to sense a condition indicative of vapour trail formation by the exhaust flow from the engine. A controller is arranged to control actuation of the flow opening so as to reduce the efficiency of the engine upon sensing of said condition by the one or more sensor. In one example, the flow opening is a variable area fan nozzle.
摘要翻译：本发明涉及一种飞机推进控制系统，其中燃气涡轮发动机具有用于控制流向或来自发动机的一部分的流动的可启动流动开口。一个或多个传感器被布置成通过来自发动机的排气流感测指示蒸气轨道形成的状况。控制器被布置成控制流动开口的致动，以便在通过一个或多个传感器检测到所述状态时降低发动机的效率。在一个示例中，流动开口是可变区域风扇喷嘴。

83. 发明授权

US08708647B2 Liner for a turbine section, a turbine section, a gas turbine engine and an aeroplane provided therewith 有权
标题翻译：用于涡轮机部分的涡轮机部分，涡轮机部分，燃气涡轮发动机和与其配备的飞机
公开(公告)号：US08708647B2
公开(公告)日：2014-04-29
申请号：US12518101
申请日：2006-12-06
申请人： Arne Boman
发明人： Arne Boman
IPC分类号： F01D25/12
CPC分类号： F02K9/64 , F02C7/12 , F02K1/82 , F02K1/822 , F02K1/825 , F02K9/972
摘要： A liner for a turbine section includes a first wall, a plurality of webs interconnected with and projecting from the first wall, and a plurality of cooling channels, each of the cooling channels being delimited by two adjacent webs and the first wall, wherein each cooling channel presents a height corresponding to the height of its delimiting webs, and a width corresponding to the distance between its delimiting webs. At least one of the cooling channels has a width/height ratio of below 5 or/and the material of the webs has a higher thermal conductivity than the material of the first wall. A turbine section, a gas turbine engine and an aeroplane provided with such a liner are also disclosed.
摘要翻译：用于涡轮部分的衬套包括第一壁，与第一壁互连并且从第一壁突出的多个腹板和多个冷却通道，每个冷却通道由两个相邻腹板和第一壁限定，其中每个冷却通道具有对应于其分隔腹板的高度的高度，以及对应于其分隔腹板之间的距离的宽度。冷却通道中的至少一个具有低于5的宽度/高度比或/和幅材的材料具有比第一壁的材料更高的热导率。还公开了一种涡轮机部分，燃气涡轮发动机和设有这种衬管的飞机。

84. 发明授权

US08544255B2 Device for reducing turboprop infrared emissions 有权
标题翻译：减少涡桨螺旋桨红外辐射的装置
公开(公告)号：US08544255B2
公开(公告)日：2013-10-01
申请号：US12933217
申请日：2009-03-16
申请人： Yves Durand
发明人： Yves Durand
IPC分类号： F02C7/08
CPC分类号： B64D33/04 , F02K1/825 , F05D2220/325
摘要： According to the invention, fresh air at the turboprop outlet is captured and mixed with the warm airflow created by said turboprop to lower the temperature, via a device having a tubular sleeve able to slide into the tubular duct while hot gases flow therethrough and which can switch from an inner position to a projecting position.
摘要翻译：根据本发明，涡轮螺旋桨发生器出口处的新鲜空气被捕获并与由所述涡轮螺旋桨发生器产生的温暖气流混合，以通过具有能够滑入管状管道的管状套筒的装置降低温度，同时热气体流过其中，从内部位置切换到突出位置。

85. 发明申请

US20130232949A1 PRESSURE BALANCED AREA CONTROL OF HIGH ASPECT RATIO NOZZLE 审中-公开
标题翻译：高比例喷嘴的压力平衡区域控制
公开(公告)号：US20130232949A1
公开(公告)日：2013-09-12
申请号：US13416676
申请日：2012-03-09
申请人： Gary J. Dillard
发明人： Gary J. Dillard
IPC分类号： F02K1/44 , B23P11/00 , F02K1/40
CPC分类号： F02K1/825 , F02K1/40 , F02K1/44 , Y10T29/49323
摘要： An apparatus for minimizing signature of an engine having an exhaust gas path and a fan gas path includes a casing, and a liner disposed within the casing. The exhaust gas path passes within the liner and the fan gas path passes between the liner and the casing. The casing is disconnected into an upstream portion and a downstream portion, each portion in registration with the liner, such that there are minimum pressure imbalances caused by the exhaust gas path, the fan gas path and ambient on the downstream portion.
摘要翻译：一种用于使具有排气路径和风扇气体路径的发动机的签名最小化的装置包括壳体和设置在壳体内的衬套。废气路径在衬套内通过，并且风扇气体通道在衬套和套管之间通过。壳体被分离成上游部分和下游部分，每个部分与衬里对齐，使得由排气路径，风扇气体路径和下游部分的环境引起的最小压力不平衡。

86. 发明授权

US08141366B2 Gas turbine engine with variable area fan nozzle 有权
标题翻译：具有可变面积风扇喷嘴的燃气轮机
公开(公告)号：US08141366B2
公开(公告)日：2012-03-27
申请号：US12193822
申请日：2008-08-19
申请人： Sean P. Zamora , Michael Joseph Murphy
发明人： Sean P. Zamora , Michael Joseph Murphy
IPC分类号： F02K1/00
CPC分类号： F02K3/077 , F02K1/42 , F02K1/46 , F02K1/825 , F02K3/075
摘要： A nozzle section of a gas turbine engine includes a regulator system in fluid communication with a secondary flow duct and a tertiary flow duct to selectively regulate communication of secondary airflow into the tertiary flow duct.
摘要翻译：燃气涡轮发动机的喷嘴部分包括与二次流动管道和三次流动管道流体连通的调节器系统，以选择性地调节二次气流到三次流动管道的连通。

87. 发明授权

US08061145B2 Arrangement for propelling an aircraft, aircraft and outlet nozzle for a jet engine 失效
标题翻译：用于推动喷气发动机的飞机，飞机和出口喷嘴的布置
公开(公告)号：US08061145B2
公开(公告)日：2011-11-22
申请号：US12067112
申请日：2005-09-27
申请人： Bernhard Gustafsson
发明人： Bernhard Gustafsson
IPC分类号： F02K1/00
CPC分类号： B64D33/04 , F02K1/40 , F02K1/825 , F05D2250/14 , F05D2260/20 , Y02T50/672 , Y02T50/675
摘要： The invention relates to an arrangement for propelling an aircraft comprising a jet engine and an outlet nozzle arranged downstream of the jet engine. The jet engine is of a type which generates an internal core flow and an external fan flow. A part of the outlet nozzle has an internal surface which defines a gas duct for the fan flow. The aforementioned part of the outlet nozzle includes a wall structure that is arranged at a distance from the internal surface such that it separates the gas duct for the fan flow from an internal gas duct for the core flow.
摘要翻译：本发明涉及一种用于推进飞机的装置，其包括喷气发动机和布置在喷气发动机下游的出口喷嘴。喷气式发动机是产生内部气流和外部风扇流的类型。出口喷嘴的一部分具有限定用于风扇流动的气体管道的内表面。出口喷嘴的上述部分包括壁结构，该壁结构设置在距离内表面一定距离处，使得其将用于风扇流的气体管道与用于芯流的内部气体管道分离。

88. 发明授权

US07900460B2 Outlet device for a jet engine and a jet engine comprising such an outlet device 失效
标题翻译：用于喷气发动机的出口装置和包括这种出口装置的喷气式发动机
公开(公告)号：US07900460B2
公开(公告)日：2011-03-08
申请号：US11718431
申请日：2005-10-20
申请人： Melker Härefors
发明人： Melker Härefors
IPC分类号： F02K1/00
CPC分类号： F02K1/006 , B64C15/02 , B64D33/04 , F02K1/002 , F02K1/12 , F02K1/40 , F02K1/44 , F02K1/825 , F02K3/025
摘要： An outlet device for a jet engine includes an outlet nozzle and a plurality of guide vanes arranged movably in the outlet nozzle for guiding a gas from the jet engine for the purpose of steering a craft equipped with the jet engine. At least one of the guide vanes can be adjusted into such a position that hot parts of the engine located inside the outlet nozzle are at least substantially concealed seen from the outlet side of the outlet nozzle.
摘要翻译：用于喷气发动机的出口装置包括出口喷嘴和可移动地布置在出口喷嘴中的多个导叶，用于引导来自喷气发动机的气体，用于转向装备有喷气发动机的飞行器。导向叶片中的至少一个可以被调节到这样的位置，即位于出口喷嘴内部的发动机的热部分至少从出口喷嘴的出口侧看起来基本上被隐藏。

89. 发明申请

US20110016844A1 DEVICE FOR REDUCING TURBOPROP INFRARED EMISSIONS 有权
标题翻译：减少湍流红外辐射的装置
公开(公告)号：US20110016844A1
公开(公告)日：2011-01-27
申请号：US12933217
申请日：2009-03-16
申请人： Yves Durand
发明人： Yves Durand
IPC分类号： F02C7/00
CPC分类号： B64D33/04 , F02K1/825 , F05D2220/325
摘要： According to the invention, fresh air (E) at the turboprop outlet is captured and mixed with the warm airflow (F) created by said turboprop to lower the temperature.
摘要翻译：根据本发明，涡轮螺旋桨发动机出口处的新鲜空气（E）被捕获并与由所述涡轮螺旋桨发生器产生的温暖气流（F）混合以降低温度。

90. 发明申请

US20100278641A1 LINER FOR A TURBINE SECTION, A TURBINE SECTION, A GAS TURBINE ENGINE AND AN AEROPLANE PROVIDED THEREWITH 有权
标题翻译：涡轮部分内燃机，涡轮部分，气体涡轮发动机和提供给它的飞机
公开(公告)号：US20100278641A1
公开(公告)日：2010-11-04
申请号：US12518101
申请日：2006-12-06
申请人： Arne Boman
发明人： Arne Boman
IPC分类号： F04D29/58 , F04D29/42
CPC分类号： F02K9/64 , F02C7/12 , F02K1/82 , F02K1/822 , F02K1/825 , F02K9/972
摘要： A liner for a turbine section includes a first wall, a plurality of webs interconnected with and projecting from the first wall, and a plurality of cooling channels, each of the cooling channels being delimited by two adjacent webs and the first wall, wherein each cooling channel presents a height corresponding to the height of its delimiting webs, and a width corresponding to the distance between its delimiting webs. At least one of the cooling channels has a width/height ratio of below 5 or/and the material of the webs has a higher thermal conductivity than the material of the first wall. A turbine section, a gas turbine engine and an aeroplane provided with such a liner are also disclosed.
摘要翻译：用于涡轮部分的衬套包括第一壁，与第一壁互连并且从第一壁突出的多个腹板和多个冷却通道，每个冷却通道由两个相邻腹板和第一壁限定，其中每个冷却通道具有对应于其分隔腹板的高度的高度，以及对应于其分隔腹板之间的距离的宽度。冷却通道中的至少一个具有低于5的宽度/高度比或/和幅材的材料具有比第一壁的材料更高的热导率。还公开了一种涡轮机部分，燃气涡轮发动机和设有这种衬管的飞机。

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