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1.发明授权Flame holder for an afterburner duct of a jet engine with a spacer shoe, afterburner duct, and jet engine comprising an afterburner duct 有权用于具有间隔鞋，后燃器管道和喷气发动机的喷气发动机的后燃器管道的火焰保持器，其包括后燃器管公开(公告)号：US08307658B2
公开(公告)日：2012-11-13
申请号：US12394570
申请日：2009-02-27
CPC分类号： F23R3/20
摘要： A flame holder for an afterburner duct of a jet engine, including an arm in the form of a gutter forming a cavity, a shield for protecting the cavity of the arm from heat, and an air supply baffle housed in the cavity, is disclosed. The arm, the protective shield, and the air supply baffle are held together by a one-piece spacer shoe.
摘要翻译： 公开了一种用于喷气发动机的后燃器管道的火焰保持器，包括形成空腔的沟槽形式的臂，用于保护臂的空腔免受热的屏蔽以及容纳在空腔中的供气挡板。 手臂，防护罩和供气挡板通过一体式隔离鞋保持在一起。
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公开(公告)号：US20130299472A1
公开(公告)日：2013-11-14
申请号：US13981237
申请日：2012-01-24
摘要： A method for perforating a wall, includes calculating mechanical stresses applied on the wall for a use of the wall. The method further includes perforating an orifice in a first determined zone of the wall, the perforation being made using a tool with a cross-section dependent on the mechanical stresses calculated in the first determined zone.
摘要翻译： 用于穿孔墙壁的方法包括计算施加在墙壁上的用于壁的应用的机械应力。 该方法还包括在壁的第一确定区域中穿孔，穿孔使用具有取决于在第一确定区域中计算的机械应力的横截面的工具来制造。
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3.发明授权Device for mounting an air-flow dividing wall in a turbojet engine afterburner 有权用于在涡轮喷气发动机后燃器中安装气流分隔壁的装置公开(公告)号：US07908868B2
公开(公告)日：2011-03-22
申请号：US11693339
申请日：2007-03-29
申请人： Jacques Marcel Arthur Bunel , Alain Pierre Page , Jacques Andre Michel Roche , Yann Vuillemenot
发明人： Jacques Marcel Arthur Bunel , Alain Pierre Page , Jacques Andre Michel Roche , Yann Vuillemenot
IPC分类号： F02K3/10
CPC分类号： F02K3/10 , F05D2240/14 , F05D2240/90 , F05D2260/30
摘要： A device for mounting a dividing wall for separating the main air stream and the bypass air in a bypass turbojet engine afterburner is disclosed. The device includes an attachment unit which attaches the upstream end of the wall to a guide vane casing and a supporting unit which supports the downstream end of the wall provided on flame holder arms of the afterburner radially on the inside of the dividing wall.
摘要翻译： 公开了一种用于安装用于在旁路涡轮喷气发动机后燃器中分离主空气流和旁路空气的分隔壁的装置。 该装置包括附接单元，其将壁的上游端附接到导向叶片壳体和支撑单元，该支撑单元在分隔壁的内侧径向地支撑设置在加力燃烧器的火焰保持器臂上的壁的下游端。
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公开(公告)号：US09291171B2
公开(公告)日：2016-03-22
申请号：US13522854
申请日：2011-01-19
CPC分类号： F04D29/624 , F01D9/04 , F01D25/246 , F04D29/441 , F05D2250/52
摘要： An assembly including a diffuser and an airflow rectifier at an outlet of a centrifugal compressor of a turbine engine, the diffuser being substantially in a shape of a radially positioned double annular disc, and the rectifier being a double toroidal part, arranged as an extension of the double disc of the diffuser and curved such as to divert the airflow in the downstream direction of the engine. The rectifier is attached to the diffuser by a connection positioned immediately adjacent to the contact surface of the two parts and is removable using a standard tool, excluding any other supporting mechanism.
摘要翻译： 一种在涡轮发动机的离心式压缩机的出口处包括扩散器和气流整流器的组件，扩散器基本上是径向定位的双环形盘的形状，并且整流器是双环形部分，被布置为 扩散器的双盘并弯曲，以便在发动机的下游方向上转动气流。 整流器通过紧邻两个部件的接触表面的连接件附接到扩散器，并且使用标准工具可拆卸，不包括任何其他支撑机构。
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5.发明申请ANNULAR COMBUSTION CHAMBER FOR A TURBINE ENGINE INCLUDING IMPROVED DILUTION OPENINGS 有权涡轮发动机的环形燃烧室，包括改进的泄油口公开(公告)号：US20130333387A1
公开(公告)日：2013-12-19
申请号：US14001429
申请日：2012-02-20
申请人： Nicolas Christian Raymond Leblond , Jacques Marcel Arthur Bunel , Dominique Maurice Jacques Lains
发明人： Nicolas Christian Raymond Leblond , Jacques Marcel Arthur Bunel , Dominique Maurice Jacques Lains
IPC分类号： F23R3/00
CPC分类号： F23R3/002 , F23R3/06 , F23R3/50 , F23R2900/03041 , F23R2900/03042 , Y02T50/675
摘要： An annular wall for an annular turbine engine combustion chamber, including one annular row of dilution orifices including larger area orifices and smaller area orifices, and a multi-perforation formed from micro-perforations distributed as an upstream row, a downstream row, and at least one intermediate row interrupted by the orifices, a geometric ratio being defined as the quotient obtained by dividing the maximum spacing L between any two points on the edge of the orifice measured along a direction parallel to an axis of the wall by the maximum spacing 1 between any two points on the edge of this orifice measured along a direction perpendicular to the axis, the geometric ratio of the larger area orifices being greater than or equal to 1, and the geometric ratio of the smaller area orifices being greater than the geometric ratio of the larger area orifices.
摘要翻译： 一种用于环形涡轮发动机燃烧室的环形壁，包括一个环形排的稀释孔，其包括较大的面积孔和较小的面积孔，以及由作为上游排，下游排和至少分布的微穿孔形成的多孔 一个由孔中断的中间行，几何比率被定义为通过将沿着平行于壁的轴线的方向测量的孔口边缘上的任何两个点之间的最大间隔L除以最大间距L而获得的商， 沿着垂直于轴线的方向测量该孔口的边缘上的任何两个点，较大面积孔口的几何比率大于或等于1，并且较小面积孔口的几何比率大于 较大面积的孔。
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6.发明申请COMBUSTION CHAMBER FOR AN AIRCRAFT ENGINE, AND METHOD FOR ATTACHING AN INJECTION SYSTEM IN A COMBUSTION CHAMBER OF AN AIRCRAFT ENGINE 有权用于飞机发动机的燃烧室和用于在飞机发动机的燃烧室中连接喷射系统的方法公开(公告)号：US20130152603A1
公开(公告)日：2013-06-20
申请号：US13819113
申请日：2011-08-12
CPC分类号： F23R3/60 , F23R3/14 , F23R3/28 , F23R3/283 , F23R2900/00017 , Y10T29/49323
摘要： A combustion chamber in which the injection system is attached so as to prevent any axial motion of the injection system, the combustion chamber includes: a baffle including a tubular portion having a first upstream end surrounded by a first radially projecting collar; and an injection system including a bowl which includes a cylindrical portion inserted into the tubular portion, the cylindrical portion including a second upstream end surrounded by a second radially projecting collar, the second collar axially bearing against the first collar, wherein the combustion chamber includes a clamp which axially clamps the first and the second collars against one another, and a fastener which retains the clamp clamped on either side of the first and second collars.
摘要翻译： 一种燃烧室，其中所述注射系统被附接以便防止所述注射系统的任何轴向运动，所述燃烧室包括：挡板，其包括管状部分，所述管状部分具有由第一径向突出的套环包围的第一上游端; 以及包括碗的注射系统，所述注射系统包括插入到所述管状部分中的圆柱形部分，所述圆柱形部分包括被第二径向突出的套环包围的第二上游端，所述第二套环轴向地抵靠所述第一套环，其中所述燃烧室包括 将第一和第二套环彼此轴向夹紧的夹具以及将夹具夹紧在第一和第二套环的任一侧上的紧固件。
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公开(公告)号：US20120255275A1
公开(公告)日：2012-10-11
申请号：US13512802
申请日：2010-12-03
申请人： Jacques Marcel Arthur Bunel , Mario Cesar De Sousa , Nicolas Christian Raymond Leblond , Guillaume Sevi , Denis Jean Maurice Sandelis , Christophe Pieussergues
发明人： Jacques Marcel Arthur Bunel , Mario Cesar De Sousa , Nicolas Christian Raymond Leblond , Guillaume Sevi , Denis Jean Maurice Sandelis , Christophe Pieussergues
CPC分类号： F23R3/50 , F02C7/266 , F23D2207/00 , F23R3/002 , F23R3/60
摘要： A turbine engine combustion chamber including at least one ignition sparkplug carried by an outer casing and extending through a guide mechanism carried by a wall forming a body of revolution of the chamber. The guide mechanism includes a tubular guide having the sparkplug passing axially therethrough, which guide is mounted with axial and transverse clearance on a chimney fastened to the wall of the chamber and opening out therein. The guide includes an annular collar engaged with clearance in an internal annular groove of the chimney. The annular collar is urged to press against a wall of the groove by a resilient member mounted in the groove.
摘要翻译： 一种涡轮发动机燃烧室，包括至少一个点火火花塞，其由外壳承载并延伸穿过由形成所述腔的旋转体的壁承载的引导机构。 引导机构包括一个管状引导件，其具有穿过其中的火花塞，该引导件以固定在腔室壁上并在其中打开的烟囱安装有轴向和横向间隙。 引导件包括与烟囱的内部环形槽中的间隙接合的环形套环。 通过安装在槽中的弹性构件推动环形套环压靠槽的壁。
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公开(公告)号：US07861531B2
公开(公告)日：2011-01-04
申请号：US12053091
申请日：2008-03-21
IPC分类号： F02C1/00
摘要： An annular fairing for covering the annular chamber end wall of a turbomachine combustion chamber, and in particular of an airplane turbojet. The fairing presents openings for passing fuel injectors that are supported by the chamber end wall. The fairing is subdivided into a plurality of adjacent sectors, each sector presenting inner and outer fastener edges capable of being fastened on either side of said chamber end wall. Each sector includes a lip on one of its side edges, which lip is connected to the remainder of the sector by a step, said lip being designed to over the side edge of the adjacent sector.
摘要翻译： 用于覆盖涡轮机燃烧室的环形室端壁的环形整流罩，特别是飞机涡轮喷气发动机。 整流罩提供用于通过由腔室端壁支撑的燃料喷射器的开口。 整流罩细分为多个相邻的扇区，每个扇区呈现能够紧固在所述腔室端壁两侧的内部和外部紧固件边缘。 每个扇区在其一个侧边缘上包括唇缘，该唇缘通过台阶连接到扇形的其余部分，所述唇缘设计成在相邻扇区的侧边缘之上。
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公开(公告)号：US09599342B2
公开(公告)日：2017-03-21
申请号：US14001429
申请日：2012-02-20
申请人： Nicolas Christian Raymond Leblond , Jacques Marcel Arthur Bunel , Dominique Maurice Jacques Lains
发明人： Nicolas Christian Raymond Leblond , Jacques Marcel Arthur Bunel , Dominique Maurice Jacques Lains
CPC分类号： F23R3/002 , F23R3/06 , F23R3/50 , F23R2900/03041 , F23R2900/03042 , Y02T50/675
摘要： An annular wall for an annular turbine engine combustion chamber, including one annular row of dilution orifices including larger area orifices and smaller area orifices, and a multi-perforation formed from micro-perforations distributed as an upstream row, a downstream row, and at least one intermediate row interrupted by the orifices, a geometric ratio being defined as the quotient obtained by dividing the maximum spacing L between any two points on the edge of the orifice measured along a direction parallel to an axis of the wall by the maximum spacing l between any two points on the edge of this orifice measured along a direction perpendicular to the axis, the geometric ratio of the larger area orifices being greater than or equal to 1, and the geometric ratio of the smaller area orifices being greater than the geometric ratio of the larger area orifices.
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10.发明授权Combustion chamber for an aircraft engine, and method for attaching an injection system in a combustion chamber of an aircraft engine 有权用于飞机发动机的燃烧室，以及用于将喷射系统附接到飞机发动机的燃烧室中的方法公开(公告)号：US09310083B2
公开(公告)日：2016-04-12
申请号：US13819113
申请日：2011-08-12
CPC分类号： F23R3/60 , F23R3/14 , F23R3/28 , F23R3/283 , F23R2900/00017 , Y10T29/49323
摘要： A combustion chamber in which the injection system is attached so as to prevent any axial motion of the injection system, the combustion chamber includes: a baffle including a tubular portion having a first upstream end surrounded by a first radially projecting collar; and an injection system including a bowl which includes a cylindrical portion inserted into the tubular portion, the cylindrical portion including a second upstream end surrounded by a second radially projecting collar, the second collar axially bearing against the first collar, wherein the combustion chamber includes a clamp which axially clamps the first and the second collars against one another, and a fastener which retains the clamp clamped on either side of the first and second collars.
摘要翻译： 一种燃烧室，其中所述注射系统被附接以便防止所述注射系统的任何轴向运动，所述燃烧室包括：挡板，其包括管状部分，所述管状部分具有由第一径向突出的套环包围的第一上游端; 以及包括碗的注射系统，所述注射系统包括插入到所述管状部分中的圆柱形部分，所述圆柱形部分包括被第二径向突出的套环包围的第二上游端，所述第二套环轴向地抵靠所述第一套环，其中所述燃烧室包括 将第一和第二套环彼此轴向夹紧的夹具以及将夹具夹紧在第一和第二套环的任一侧上的紧固件。
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