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1.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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2.发明授权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：US07584615B2
公开(公告)日：2009-09-08
申请号：US11063741
申请日：2005-02-24
申请人： Sébastien Baboeuf , Sabine Charpenel , Eric Maingre , Alain Page , Jacques Roche
发明人： Sébastien 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：US20050274114A1
公开(公告)日：2005-12-15
申请号：US10872510
申请日：2004-06-22
申请人： Thierry Cortes , Alain Page , Sebastien Baboeuf , Jacques Roche
发明人： Thierry Cortes , Alain Page , Sebastien Baboeuf , Jacques Roche
IPC分类号： F01D25/12 , F01D25/24 , F01D25/30 , F02C7/00 , F02C7/18 , F02K1/28 , F02K1/38 , F02K1/82 , F02K3/00 , F02K3/10 , F23R3/18 , F23R3/42
CPC分类号： F02K1/386 , F02K1/822 , F02K3/10 , Y02T50/675
摘要： The invention relates to ventilating the confluence sheet of an afterburner chamber of an aviation turbomachine, including, upstream from the afterburner chamber: a diffuser defined by a confluence sheet disposed inside a casing, said casing and said confluence sheet defining between them an annular channel for a cold secondary flow, upstream fuel injectors being disposed at the inlet to said diffuser and flame-catchers being disposed downstream from said upstream injectors, said confluence sheet presenting, between the radial plane containing said upstream injectors and the radial plane situated at the rear ends of said flame-catchers two bends so as to flare downstream in order to slow down the primary flow F1 downstream from said upstream injectors. An annular scoop is provided around the upstream portion of said confluence sheet in order to extract a flow of air from the cold flow, said extracted flow being injected tangentially into the primary flow via a plurality of channels formed in the wall of said confluence sheet between the scoop and said diffuser.
摘要翻译： 本发明涉及对航空涡轮机的后燃室的汇流板进行通风，包括在后燃室的上游：由设置在壳体内的汇流板限定的扩散器，所述壳体和所述汇流板在它们之间限定环形通道， 冷次级流，上游燃料喷射器设置在所述扩散器的入口处，并且火焰捕获器设置在所述上游喷射器的下游，所述汇合片在包含所述上游喷射器的径向平面和位于后端的径向平面之间呈现 的所述火焰捕集器两个弯曲，以便向下游扩张，以便减缓所述上游喷射器下游的主流F 1。 围绕所述汇流板的上游部分设置环形勺，以便从冷流中提取空气流，所述提取的流通过形成在所述汇流板的壁中的多个通道切向地注入主流， 勺子和扩散器。
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4.发明申请Turbo-jet engine with a protective screen of the fuel manihold of a burner ring, the burner ring and the protective screen 有权涡轮喷气发动机带有燃烧器燃油环的保护屏，燃烧器环和保护屏公开(公告)号：US20060016193A1
公开(公告)日：2006-01-26
申请号：US11177297
申请日：2005-07-11
申请人： Jacques Roche , Alain Page , Stephane Touchaud , Nicolas Pommier
发明人： Jacques Roche , Alain Page , Stephane Touchaud , Nicolas Pommier
IPC分类号： F02K3/10
CPC分类号： F23R3/20 , F02K3/11 , F05D2260/201 , F05D2260/202 , Y02T50/675
摘要： The invention concerns a double flow turbo-jet engine, including a re-heating channel of the primary flow and an ejection nozzle, the secondary flow emerging at least partially in the primary flow upstream of the re-heating channel, the re-heating channel including a burner ring, including a flame holder gutter in the form of a ring portion whereof the upstream section is situated in the secondary flow, receiving a fuel manihold and a protective tubular screen of the manihold. The invention is characterised in that the gutter includes an upstream recess linked with the secondary flow, and the screen includes, on its upstream section, at least one ventilation orifice of the space situated between the screen and the manihold.
摘要翻译： 本发明涉及一种双流涡轮喷气发动机，其包括一次流的再加热通道和喷射喷嘴，二次流在至少部分地在再加热通道上游的主流中出现，再加热通道 包括燃烧器环，包括形成环形部分的火焰保持器沟槽，其上游部分位于二次流中，接收燃油手柄和手枪的保护性管状屏障。 本发明的特征在于，沟槽包括与二次流连接的上游凹槽，并且屏幕在其上游部分上包括位于屏幕和手枪之间的空间的至少一个通风孔。
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公开(公告)号：US20060016192A1
公开(公告)日：2006-01-26
申请号：US11175191
申请日：2005-07-07
申请人： Jacques Bunel , Jacques Roche , Alain Page
发明人： Jacques Bunel , Jacques Roche , Alain Page
IPC分类号： F02K3/10
CPC分类号： F23R3/20 , F23D2211/00 , F23D2900/00018 , F23R3/283 , F23R3/30 , F23R2900/00017
摘要： The turbojet of the invention includes a combustion chamber, a channel for heating the gas stream, where the heating channel includes at least one device for injection of fuel into the gas stream, which includes an open chamber, with a U-shaped section, having at least one wall within which extend fuel-injection means, which inject the fuel in at least one direction. It is characterised by the fact that a cooling jacket is provided in the chamber, alongside the wall forming the base of its U-section, and the fuel injection device includes protection means interposed between the fuel-injection means and the wall, in a fuel-injection direction. Thus, as a result of the invention, the fuel injection device, which is bathed in a very hot environment, is protected against thermal shocks due to the projection of colder fuel onto its walls, and its life expectancy is therefore increased.
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公开(公告)号：US06976361B1
公开(公告)日：2005-12-20
申请号：US10872510
申请日：2004-06-22
申请人： Thierry Cortes , Alain Page , Sébastien Baboeuf , Jacques Roche
发明人： Thierry Cortes , Alain Page , Sébastien Baboeuf , Jacques Roche
IPC分类号： F01D25/12 , F01D25/24 , F01D25/30 , F02C7/00 , F02C7/18 , F02K1/28 , F02K1/38 , F02K1/82 , F02K3/00 , F02K3/10 , F23R3/18 , F23R3/42
CPC分类号： F02K1/386 , F02K1/822 , F02K3/10 , Y02T50/675
摘要： The invention relates to ventilating the confluence sheet of an afterburner chamber of an aviation turbomachine, including, upstream from the afterburner chamber: a diffuser defined by a confluence sheet disposed inside a casing, said casing and said confluence sheet defining between them an annular channel for a cold secondary flow, upstream fuel injectors being disposed at the inlet to said diffuser and flame-catchers being disposed downstream from said upstream injectors, said confluence sheet presenting, between the radial plane containing said upstream injectors and the radial plane situated at the rear ends of said flame-catchers two bends so as to flare downstream in order to slow down the primary flow F1 downstream from said upstream injectors. An annular scoop is provided around the upstream portion of said confluence sheet in order to extract a flow of air from the cold flow, said extracted flow being injected tangentially into the primary flow via a plurality of channels formed in the wall of said confluence sheet between the scoop and said diffuser.
摘要翻译： 本发明涉及对航空涡轮机的后燃室的汇流板进行通风，包括在后燃室的上游：由设置在壳体内的汇流板限定的扩散器，所述壳体和所述汇流板在它们之间限定环形通道， 冷次级流，上游燃料喷射器设置在所述扩散器的入口处，并且火焰捕获器设置在所述上游喷射器的下游，所述汇合片在包含所述上游喷射器的径向平面和位于后端的径向平面之间呈现 的所述火焰捕集器两个弯曲，以便向下游扩张，以便减缓所述上游喷射器下游的主流F 1。 围绕所述汇合片的上游部分设置环形勺以便从冷流中提取空气流，所述提取的流通过形成在所述汇合片的壁上的多个通道切向地注入主流中， 勺子和扩散器。
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公开(公告)号：US07631486B2
公开(公告)日：2009-12-15
申请号：US11427523
申请日：2006-06-29
IPC分类号： F02K1/28
摘要： The present invention relates to a thrust orienting nozzle, shaped in such a way as to divide a principal propulsion gas flow coming from at least one gas generator into a first flow and a second flow for an ejection in a first half-nozzle and in a second half-nozzle and comprising at least one of following two piloting means: a means of dividing the principal flow into each of the two half-nozzles, and a means of orienting the thrust vector produced by each of the two half-nozzles.The invention applies in particular to the yaw control of an aircraft without a vertical tail unit.
摘要翻译： 本发明涉及一种推力定向喷嘴，其成形为将来自至少一个气体发生器的主推进气流分成第一流和第二流，用于在第一半喷嘴中喷射 第二半喷嘴，并且包括以下两个引导装置中的至少一个：将主流分成两个半喷嘴中的每一个的装置以及使由两个半喷嘴中的每一个产生的推力矢量的方向。 本发明特别适用于没有垂直尾翼单元的飞行器的偏航控制。
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公开(公告)号：US20070284005A1
公开(公告)日：2007-12-13
申请号：US11741346
申请日：2007-04-27
申请人： Edgar BRUNET , Thomas Daris , Alain Page , Jackie Prouteau
发明人： Edgar BRUNET , Thomas Daris , Alain Page , Jackie Prouteau
IPC分类号： F16L41/00
CPC分类号： B64D33/04 , F02K1/822 , F02K1/825 , Y02T50/675 , Y10T137/85938
摘要： The present invention relates to a propulsion gas exhaust assembly, in an aircraft propelled by hot gases produced along the axis of the latter by a gas generator, comprising a duct and a nozzle, wherein said duct comprises a first cylindrical duct element (21) receiving the gases and communicating downstream with two second duct elements (22, 23), the directions of which are divergent in a first plane, each of the two duct elements communicating downstream with a third duct element (25, 27) which emerges in an axial gas-ejection half-nozzle (24, 26).
摘要翻译： 本发明涉及一种在由气体发生器沿其轴线产生的热气体驱动的飞行器中的推进气体排气组件，其包括管道和喷嘴，其中所述管道包括第一圆柱形管道元件（21），其接收 气体并与下游连通的两个第二管道元件（22,23），其两个方向在第一平面中是发散的，两个管道元件中的每一个与第三管道元件（25,27）连通，第三管道元件（25,27）以轴向 气体喷射半喷嘴（24,26）。
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9.发明申请公开(公告)号：US20070266712A1
公开(公告)日：2007-11-22
申请号：US11741338
申请日：2007-04-27
申请人： Edgar Brunet , Thomas Daris , Alain Page , Jackie Prouteau
发明人： Edgar Brunet , Thomas Daris , Alain Page , Jackie Prouteau
IPC分类号： F02K1/40
摘要： The present invention relates to a propulsion gas exhaust assembly in an aircraft propelled by hot gases produced along the axis of the latter by a gas generator, comprising a duct (21) and a nozzle (24). It is noteworthy by the fact that said duct forms a vertical elbow.
摘要翻译： 本发明涉及一种由在气体发生器沿其轴线产生的热气体推动的飞机中的推进气体排气组件，其包括管道（21）和喷嘴（24）。 值得注意的是，所述导管形成垂直弯头。
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公开(公告)号：US20070000233A1
公开(公告)日：2007-01-04
申请号：US11427523
申请日：2006-06-29
IPC分类号： F02K1/40
摘要： The present invention relates to a thrust orienting nozzle, shaped in such a way as to divide a principal propulsion gas flow coming from at least one gas generator into a first flow and a second flow for an ejection in a first half-nozzle and in a second half-nozzle and comprising at least one of following two piloting means: a means of dividing the principal flow into each of the two half-nozzles, and a means of orienting the thrust vector produced by each of the two half-nozzles. The invention applies in particular to the yaw control of an aircraft without a vertical tail unit.
摘要翻译： 本发明涉及一种推力定向喷嘴，其成形为将来自至少一个气体发生器的主推进气流分成第一流和第二流，用于在第一半喷嘴中喷射 第二半喷嘴，并且包括以下两个引导装置中的至少一个：将主流分成两个半喷嘴中的每一个的装置以及使由两个半喷嘴中的每一个产生的推力矢量的方向。 本发明特别适用于没有垂直尾翼单元的飞行器的偏航控制。
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