公开(公告)号：US06966189B2

公开(公告)日：2005-11-22

申请号：US10847864

申请日：2004-05-19

申请人： Guy Lapergue ,  Guillaume Sevi ,  Jacques Roche

发明人： Guy Lapergue ,  Guillaume Sevi ,  Jacques Roche

IPC分类号： F02C7/28 ,  F02C7/12 ,  F02C7/18 ,  F02C7/24 ,  F02K1/80 ,  F02K1/82 ,  F16J15/08 ,  F02K1/12

CPC分类号： F02K1/805 ,  F02K1/822 ,  F05D2260/10 ,  F16J15/0887 ,  Y02T50/675

摘要： A turbomachine comprising, downstream from the turbine, a post-combustion chamber defined by a thermal protection lining inside a casing defining an annular channel for a secondary flow, an annular diaphragm secured at the downstream end of said channel, said nozzle comprising a plurality of flaps hinged to the upstream end of said casing, each flap fitted on its inside face with a thermal protection plate to define a passage for cooling air delivered by said diaphragm, wherein the cooling air is provided by an annular duct defined by a first flexible annular gasket in sliding contact against the downstream inside face of the casing and against the upstream inside faces of the flaps under the pressure of the secondary flow, and defined on the inside by a second flexible annular gasket whose upstream end is fixed to the radially inner zone of the diaphragm, and whose downstream end is in sliding contact against the upstream inside face of the protection plates.

摘要翻译： 一种涡轮机，包括在涡轮下游的由燃烧室内限定的用于二次流的环形通道限定的后燃烧室，固定在所述通道的下游端的环形隔膜，所述喷嘴包括多个 翼片铰接到所述壳体的上游端，每个翼片在其内表面上安装有热保护板，以限定用于冷却由所述隔膜输送的空气的通道，其中所述冷却空气由第一柔性环形 衬垫与壳体的下游内表面滑动接触，并且在二次流动的压力下抵靠翼片的上游内表面，并且通过第二柔性环形垫圈限定在内侧，第二柔性环形垫圈的上游端固定到径向内部区域 并且其下游端与保护板的上游内表面滑动接触。

公开(公告)号：US20050252216A1

公开(公告)日：2005-11-17

申请号：US11113116

申请日：2005-04-25

申请人： Jacques Roche ,  Jacques Bunel

发明人： Jacques Roche ,  Jacques Bunel

IPC分类号： F23R3/18 ,  F02K3/11 ,  F23R3/20 ,  F02K3/10

CPC分类号： F23R3/20 ,  F02K3/11

摘要： A device for feeding air and fuel to a burner ring in an after-burner chamber comprises a plurality of flame-holder arms extending radially about the axis of the chamber from an outer casing, a burner ring made up of ring sectors mounted substantially end to end on the flame-holder arms, and means for feeding air and fuel to the burner ring sectors, said means extending between the burner ring and the outer casing of the after-burner chamber inside the flame-holder arms.

摘要翻译： 用于将空气和燃料供给到后燃烧器室中的燃烧器环的装置包括从外壳围绕室的轴线径向延伸的多个火焰保持器臂，燃烧器环，其由基本上终止于 在火焰支架臂上的端部，以及用于将空气和燃料供给到燃烧器环部分的装置，所述装置在燃烧器环和燃烧器室的外壳之间在火焰支架臂内延伸。

公开(公告)号：US07506513B2

公开(公告)日：2009-03-24

申请号：US11113116

申请日：2005-04-25

申请人： Jacques Roche ,  Jacques Bunel

发明人： Jacques Roche ,  Jacques Bunel

IPC分类号： F02K3/10

CPC分类号： F23R3/20 ,  F02K3/11

摘要： A device for feeding air and fuel to a burner ring in an after-burner chamber, including a plurality of flame-holder arms extending radially about the axis of the chamber from an outer casing, and a burner ring made up of ring sectors mounted substantially end to end on the flame-holder arms, the ring sectors containing fuel feed rail and air manifold boxes.

摘要翻译： 一种用于将空气和燃料供给到后燃烧室中的燃烧器环的装置，包括从外壳围绕室的轴线径向延伸的多个火焰保持臂，以及由基本上安装的环形部分构成的燃烧器环 在火焰支架臂端部到端部，环形部分包含燃料供给轨道和空气歧管箱。

公开(公告)号：US07367191B2

公开(公告)日：2008-05-06

申请号：US11110725

申请日：2005-04-21

申请人： Jacques Bunel ,  Jacques Roche

发明人： Jacques Bunel ,  Jacques Roche

IPC分类号： F02K3/10

CPC分类号： F01D25/246 ,  F02K3/10 ,  F23R3/20

摘要： Device for fixing a burner ring onto flameholder arms (14) in an afterburner combustion chamber of a turbojet engine, the burner ring being formed of ring sectors (12) placed more or less end to end and the ends of which are housed and guided between two circumferentially-directed parallel plates (34, 36) of the flameholder arms (14) and are immobilized between these plates (34, 36) by locking pieces (52) which are themselves held between the plates (34, 36) by immobilizing means (54, 56) engaged in aligned orifices (58, 60, 64) in the plates (34, 36) and in the locking pieces (52).

摘要翻译： 用于将燃烧器环固定到​​涡轮喷气发动机的后燃烧器燃烧室中的燃烧器臂（14）上的装置，所述燃烧器环由环形部分（12）形成，所述环形部分（12）或多或少地端对端设置，并且其端部容纳并引导在 两个圆弧方向的平行板（34,36）通过锁定件（52）固定在这些板（34,36）之间，这些片本身通过固定装置固定在板（34,36）之间 （54,56），其接合在板（34,36）和锁定片（52）中的对准孔（58,60,64）中。

公开(公告)号：US07287383B2

公开(公告)日：2007-10-30

申请号：US10898999

申请日：2004-07-27

申请人： Jacques Bunel ,  Jacques Roche ,  Bien-Aimé Rakotondrainibe ,  Stéphane Touchaud

发明人： Jacques Bunel ,  Jacques Roche ,  Bien-Aimé Rakotondrainibe ,  Stéphane Touchaud

IPC分类号： F02K3/10

CPC分类号： F23R3/20

摘要： The invention relates to a burner ring for turbofan jet engines. The ring includes an upstream annular envelope which forms a channel which is open axially in the downstream direction, and a manifold for injecting fuel into the channel. The ring includes multiple sectors connected together. Each sector has a fuel inlet which is connected to the fuel injection manifold. Part of the upstream annular envelope is in the core flow. Each sector has a connector which receives the fuel inlet and a ventilation duct which extends through the channel and upstream of the injection manifold. Each sector is fitted with an inlet for a bypass air, which air is then emitted by the ventilation duct to cool the injection manifold. A sector of downstream annular envelope is arranged downstream of the injection manifold to protect this manifold.

摘要翻译： 本发明涉及一种用于涡轮风扇喷气发动机的燃烧器环。 环包括形成在下游方向上轴向敞开的通道的上游环形外壳和用于将燃料喷射到通道中的歧管。 环包括连接在一起的多个扇区。 每个扇区具有连接到燃料喷射歧管的燃料入口。 上游环形包层的一部分处于核心流。 每个扇区具有接收燃料入口的连接器和延伸穿过通道和喷射歧管上游的通风管道。 每个扇区都安装有用于旁路空气的入口，然后由通风管道排出空气以冷却注入歧管。 下游环形外壳的一部分布置在注射歧管的下游，以保护该歧管。

公开(公告)号：US20060292504A1

公开(公告)日：2006-12-28

申请号：US11181924

申请日：2005-07-15

申请人： Sebastien Baboeuf ,  Sabine Charpenel ,  Didier Durand ,  Jacques Roche

发明人： Sebastien Baboeuf ,  Sabine Charpenel ,  Didier Durand ,  Jacques Roche

IPC分类号： F23G7/08

CPC分类号： F23R3/20

摘要： A turbojet having an after-burner chamber presenting a specific injector opening into the burner ring to provide secure ignition. The after-burner chamber has an annular fuel injection duct, an ignition spark plug, and an ignition injector installed facing the spark plug and connected to specific fuel feed means.

摘要翻译： 涡轮喷气发动机具有后燃烧器室，其具有特定的喷射器开口进入燃烧器环以提供可靠的点火。 后燃烧器室具有环形燃料喷射管道，点火火花塞和面向火花塞安装并连接到特定燃料供给装置的点火喷射器。

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。

公开(公告)号：US20050247063A1

公开(公告)日：2005-11-10

申请号：US11110725

申请日：2005-04-21

申请人： Jacques Bunel ,  Jacques Roche

发明人： Jacques Bunel ,  Jacques Roche

IPC分类号： F23R3/20 ,  F01D25/24 ,  F01D25/26 ,  F02K3/10 ,  F02K3/11

CPC分类号： F01D25/246 ,  F02K3/10 ,  F23R3/20

摘要： Device for fixing a burner ring onto flameholder arms (14) in an afterburner combustion chamber of a turbojet engine, the burner ring being formed of ring sectors (12) placed more or less end to end and the ends of which are housed and guided between two circumferentially-directed parallel plates (34, 36) of the flameholder arms (14) and are immobilized between these plates (34, 36) by locking pieces (52) which are themselves held between the plates (34, 36) by immobilizing means (54, 56) engaged in aligned orifices (58, 60, 64) in the plates (34, 36) and in the locking pieces (52).

摘要翻译： 用于将燃烧器环固定到​​涡轮喷气发动机的后燃烧器燃烧室中的燃烧器臂（14）上的装置，所述燃烧器环由环形部分（12）形成，所述环形部分（12）或多或少地端对端设置，并且其端部容纳并引导在 两个圆弧方向的平行板（34,36）通过锁定件（52）固定在这些板（34,36）之间，这些片本身通过固定装置固定在板（34,36）之间 （54,56），其接合在板（34,36）和锁定片（52）中的对准孔（58,60,64）中。

公开(公告)号：US20050086941A1

公开(公告)日：2005-04-28

申请号：US10898999

申请日：2004-07-27

申请人： Jacques Bunel ,  Jacques Roche ,  Bien-Aime Rakotondrainibe ,  Stephane Touchaud

发明人： Jacques Bunel ,  Jacques Roche ,  Bien-Aime Rakotondrainibe ,  Stephane Touchaud

IPC分类号： F23R3/18 ,  F02K3/10 ,  F23R3/20

CPC分类号： F23R3/20

摘要： The invention relates to an afterburner ring 19 for turbofan jet engines. The ring comprises an upstream annular envelope which forms a channel which is open axially in the downstream direction, and a manifold 4 for injecting fuel into the channel. The ring has sectors 20 which each comprise a sector 1 of the upstream annular envelope. Each sector 1 has a fuel inlet 35 which is connected to the injection manifold 4. Part of the upstream annular envelope is in the core flow. Each sector 20 has a connecting means which receives the fuel inlet and a ventilation duct 2 which extends through the channel along the sector 1, at a point upstream of the injection manifold 4. Each sector 1 is fitted with an inlet for bypass air, which air is then emitted by the ventilation duct 2 to cool the injection manifold 4. A sector 5 of downstream annular envelope is arranged downstream of the injection manifold 4 to protect it.

摘要翻译： 本发明涉及一种用于涡轮风扇喷气发动机的后燃器环19。 环包括形成在下游方向上轴向敞开的通道的上游环形外壳和用于将燃料喷射到通道中的歧管4。 环具有扇区20，每个扇区20包括上游环形外壳的扇区1。 每个扇区1具有连接到喷射歧管4的燃料入口35。 上游环形包层的一部分处于核心流。 每个扇区20具有接收燃料入口的连接装置和在喷射歧管4上游的一个点处沿着扇区1延伸穿过通道的通风管道2。 每个扇区1装有用于旁路空气的入口，然后由通风管道2排出空气以冷却喷射歧管4。 下游环形外壳的扇区5布置在喷射歧管4的下游以保护其。

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。