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公开(公告)号：US09080771B2
公开(公告)日：2015-07-14
申请号：US13509815
申请日：2010-11-15
CPC分类号： F23R3/06 , F02C7/266 , F05D2260/30 , F23D2207/00 , F23R3/60 , F23R2900/00012 , F23R2900/03044 , Y02T50/675
摘要： A combustion chamber of a gas turbine engine including a wall, a well secured to the wall, the well forming a recess for a spark plug leading into the combustion chamber, and a spark-plug guide mounted on the well to be transversally mobile relative to the axis of the well, the spark-plug guide including a cylindrical wall portion for guiding and supporting the spark plug and a seal ring mounted such as to engage slidably with a bearing surface of the well. In the combustion chamber the spark-plug guide includes a cooling chamber having openings for supplying cooling air to the chamber.
摘要翻译： 一种燃气涡轮发动机的燃烧室，其包括壁，井壁固定，形成用于引导到燃烧室中的火花塞的凹部的井以及安装在井上的火花塞导向件相对于 井的轴线，火花塞引导件包括用于引导和支撑火花塞的圆柱形壁部分和安装成可滑动地与井的支承表面接合的密封环。 在燃烧室中，火花塞引导件包括具有用于将冷却空气供应到腔室的开口的冷却室。
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公开(公告)号：US20070193248A1
公开(公告)日：2007-08-23
申请号：US11670519
申请日：2007-02-02
申请人： Florian Andre Francois BESSAGNET , Patrice Andre Commaret , Mario Cesar De Sousa , Didier Hippolyte Hernandez
发明人： Florian Andre Francois BESSAGNET , Patrice Andre Commaret , Mario Cesar De Sousa , Didier Hippolyte Hernandez
IPC分类号： F02C3/00
CPC分类号： F23R3/06 , F23D2211/00 , F23R2900/00005 , Y02T50/675
摘要： A turbomachine combustion chamber has primary and dilution air inlet orifices formed by die stamping to have edges that project into the inside of the combustion chamber, and stress relaxation and/or reduction means in the edges or in the vicinity of the edges of said orifices, said means comprising, for each orifice, one, two, or three slots formed in the edge or around a fraction of the edge of said orifice.
摘要翻译： 涡轮机燃烧室具有通过冲模形成的主要和稀释空气入口孔，其具有突出到燃烧室内部的边缘，以及在所述孔口的边缘或边缘附近的应力松弛和/或还原装置， 所述装置包括针对每个孔口形成在所述孔口的边缘或围绕所述孔口的边缘的一部分的一个，两个或三个槽。
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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：US07788928B2
公开(公告)日：2010-09-07
申请号：US11673179
申请日：2007-02-09
CPC分类号： F23R3/002 , F23R3/007 , F23R3/50 , F23R2900/00005
摘要： Annular combustion chamber of a turbomachine is provided. The combustion chamber includes an inner wall, an outer wall, a chamber bottom disposed between the walls in the upstream region of the chamber, and two attachment flanges disposed downstream of the chamber bottom and respectively enabling the walls to be attached to other parts of the turbomachine. Each wall is divided into several adjacent sectors and each sector is attached to the chamber bottom and to one of the attachment flanges. Advantageously, the adjacent sectors overlap at their lateral edges and there exists a degree of radial play between two adjacent sectors. In addition, the lateral edges of the sectors are inclined circumferentially relative to the principal axis of the combustion chamber.
摘要翻译： 提供涡轮机的环形燃烧室。 燃烧室包括内壁，外壁，设置在室的上游区域中的壁之间的室底部，以及设置在室底部下游的两个附接凸缘，并且分别使壁能够附接到腔室的其他部分 涡轮机 每个壁分成几个相邻的扇区，并且每个扇区附接到室底部和附接凸缘中的一个。 有利的是，相邻扇区在其横向边缘处重叠，并且在两个相邻扇区之间存在一定程度的径向播放。 另外，扇区的侧边缘相对于燃烧室的主轴线沿周向倾斜。
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公开(公告)号：US20070186558A1
公开(公告)日：2007-08-16
申请号：US11672236
申请日：2007-02-07
IPC分类号： F23R3/00
CPC分类号： F23R3/50 , F23R3/007 , F23R3/10 , F23R3/60 , F23R2900/00005 , F23R2900/00017 , Y02T50/675
摘要： Annular combustion chamber of a turbomachine, including an inner wall, an outer wall (28) and a chamber bottom (30) arranged between said walls in the upstream region of said chamber, in which the chamber bottom (30) is divided into several adjacent sectors (130), each sector being attached to said walls (28), these sectors (130) presenting lateral edges such that the lateral edges (130a, 130b) of two adjacent sectors overlap. More precisely, each sector (130) includes a lip (60) extending along one of its lateral edges (130a), this lip projecting relative to one of the faces of this sector and covering the lateral edge (130b) of the adjacent sector.
摘要翻译： 涡轮机的环形燃烧室，其包括内壁，外壁（28）和室底部（30），其布置在所述腔室的上游区域中的所述壁之间，其中腔室底部（30）被分成几个相邻 扇区（130），每个扇区附接到所述壁（28），这些扇区（130）呈现横向边缘，使得两个相邻扇区的横向边缘（130a，130b）重叠。 更准确地说，每个扇区（130）包括沿其一个侧边缘（130a）延伸的唇缘（60），该唇缘相对于该扇区的一个面突出并且覆盖相邻的侧边缘的侧边缘（130b） 部门。
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公开(公告)号：US20120227373A1
公开(公告)日：2012-09-13
申请号：US13509815
申请日：2010-11-15
IPC分类号： F02C7/266
CPC分类号： F23R3/06 , F02C7/266 , F05D2260/30 , F23D2207/00 , F23R3/60 , F23R2900/00012 , F23R2900/03044 , Y02T50/675
摘要： A combustion chamber of a gas turbine engine including a wall, a well secured to the wall, the well forming a recess for a spark plug leading into the combustion chamber, and a spark-plug guide mounted on the well to be transversally mobile relative to the axis of the well, the spark-plug guide including a cylindrical wall portion for guiding and supporting the spark plug and a seal ring mounted such as to engage slidably with a bearing surface of the well. In the combustion chamber the spark-plug guide includes a cooling chamber having openings for supplying cooling air to the chamber.
摘要翻译： 一种燃气涡轮发动机的燃烧室，其包括壁，井壁固定，形成用于引导到燃烧室中的火花塞的凹部的井以及安装在井上的火花塞导向件相对于 井的轴线，火花塞引导件包括用于引导和支撑火花塞的圆柱形壁部分和安装成可滑动地与井的支承表面接合的密封环。 在燃烧室中，火花塞引导件包括具有用于将冷却空气供应到腔室的开口的冷却室。
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公开(公告)号：US07942005B2
公开(公告)日：2011-05-17
申请号：US11670519
申请日：2007-02-02
申请人： Florian Andre Francois Bessagnet , Patrice Andre Commaret , Mario Cesar De Sousa , Didier Hippolyte Hernandez
发明人： Florian Andre Francois Bessagnet , Patrice Andre Commaret , Mario Cesar De Sousa , Didier Hippolyte Hernandez
CPC分类号： F23R3/06 , F23D2211/00 , F23R2900/00005 , Y02T50/675
摘要： A turbomachine combustion chamber has primary and dilution air inlet orifices formed by die stamping to have edges that project into the inside of the combustion chamber, and stress relaxation and/or reduction means in the edges or in the vicinity of the edges of said orifices, said means comprising, for each orifice, one, two, or three slots formed in the edge or around a fraction of the edge of said orifice.
摘要翻译： 涡轮机燃烧室具有通过冲模形成的主要和稀释空气入口孔，其具有突出到燃烧室内部的边缘，以及在所述孔口的边缘或边缘附近的应力松弛和/或还原装置， 所述装置包括针对每个孔口形成在所述孔口的边缘或围绕所述孔口的边缘的一部分的一个，两个或三个槽。
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公开(公告)号：US07757495B2
公开(公告)日：2010-07-20
申请号：US11670571
申请日：2007-02-02
IPC分类号： F02C7/20
CPC分类号： F23R3/50 , F23R3/10 , F23R3/60 , F23R2900/00005 , F23R2900/00017
摘要： A turbine engine annular combustion chamber includes inner and outer longitudinal walls connected upstream by a transverse chamber bottom and including a single-piece cowling covering the chamber bottom. Each of the longitudinal walls is inserted between corresponding flanges of the chamber bottom and of the cowling. The longitudinal walls, the chamber bottom and the cowling are assembled together by a plurality of first fixings between the longitudinal walls and the chamber bottom alternating with a plurality of second fixings distinct from the first fixings between the longitudinal walls and the cowling.
摘要翻译： 涡轮发动机环形燃烧室包括由横向室底部上游连接并且包括覆盖室底部的单件整流罩的内部和外部纵向壁。 每个纵向壁被插入腔室底部和整流罩的对应凸缘之间。 纵向壁，腔室底部和整流罩通过在纵向壁和腔室底部之间的多个第一固定件与多个第二固定件组装在一起，所述多个第二固定件与纵向壁和整流罩之间的第一固定件不同。
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公开(公告)号：US20080236164A1
公开(公告)日：2008-10-02
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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