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公开(公告)号：US07661273B2
公开(公告)日：2010-02-16
申请号：US12198386
申请日：2008-08-26
IPC分类号： F02C7/20
CPC分类号： F23R3/283 , F02C3/14 , F05D2230/642 , F05D2250/70 , F05D2260/96 , F23R3/50 , F23R3/60
摘要： Turbomachine with an annular combustion chamber including at its upstream end an annular chamber bottom, and attached at its downstream end by annular flanges to a radially inner casing and outer casing, wherein the upstream end of the chamber is connected to the inner casing or outer casing by elastically deformable bridges.
摘要翻译： 具有环形燃烧室的涡轮机，其上游端部包括环形室底部，并且在其下游端通过环形凸缘附接到径向内壳体和外壳体，其中室的上游端连接到内壳体或外壳体 通过可弹性变形的桥梁。
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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：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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4.发明申请CHAMBER-BOTTOM BAFFLE, COMBUSTION CHAMBER COMPRISING SAME AND GAS TURBINE ENGINE FITTED THEREWITH 审中-公开箱体底部，包括相同的燃烧室和燃气涡轮发动机公开(公告)号：US20090019856A1
公开(公告)日：2009-01-22
申请号：US12165995
申请日：2008-07-01
IPC分类号： F23R3/42
摘要： The present invention relates to a baffle (10) for the bottom of a combustion chamber of a gas turbine engine, comprising a flat portion of wall (10a) with an opening for an injector of the combustion chamber to pass through, two longitudinal edges (10c, 10d) for the assembly to two adjacent baffles and two transverse edges (10e, 10f), wherein at least one of the edges comprises a joint cover (10d1) arranging a housing (10d10) along said edge for an edge (10′c) of an adjacent baffle (10′) so as to seal the junction between the two edges. The invention also relates to a combustion chamber incorporating said baffles.
摘要翻译： 本发明涉及一种用于燃气涡轮发动机的燃烧室的底部的挡板（10），其包括具有用于燃烧室的喷射器通过的开口的壁（10a）的平坦部分，两个纵向边缘 10e，10d），用于组装到两个相邻的挡板和两个横向边缘（10e，10f），其中至少一个边缘包括沿着所述边缘设置壳体（10d10）的接合盖（10d1），用于边缘（10' c）相邻的挡板（10'），以便密封两个边缘之间的接合部。 本发明还涉及包含所述挡板的燃烧室。
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公开(公告)号：US08490401B2
公开(公告)日：2013-07-23
申请号：US12993379
申请日：2009-04-21
CPC分类号： F23R3/283
摘要： An annular combustion chamber for a gas turbine engine includes radially inner and outer walls connected together by a chamber end wall including openings, each of which receives a fuel injection system. Heat protection deflectors are fastened to the chamber end wall. Holes are formed through the chamber end wall to pass cooling air onto an upstream face of each deflector. The inner or outer edge of a deflector presents a sealing rim engaging the respective inner or outer wall of the chamber.
摘要翻译： 用于燃气涡轮发动机的环形燃烧室包括通过包括开口的室端壁连接在一起的径向内壁和外壁，每个开口接收燃料喷射系统。 热保护导流器固定在腔室端壁上。 孔通过腔室端壁形成，以将冷却空气传递到每个偏转器的上游面上。 偏转器的内边缘或外边缘具有接合室的相应内壁或外壁的密封边缘。
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公开(公告)号：US08387395B2
公开(公告)日：2013-03-05
申请号：US11837856
申请日：2007-08-13
申请人： Patrice Andre Commaret , Jean-Michel Serge Marcel Duret , Didier Hippolyte Hernandez , David Locatelli
发明人： Patrice Andre Commaret , Jean-Michel Serge Marcel Duret , Didier Hippolyte Hernandez , David Locatelli
IPC分类号： F02C1/00
CPC分类号： F23R3/04 , F23R2900/03041 , F23R2900/03042 , Y02T50/675
摘要： An annular combustion chamber for a turbomachine is disclosed. The chamber includes an inner wall, an outer wall, and a chamber end wall disposed between the inner and outer walls in the upstream region of the chamber. The chamber end wall presents an outer fastener rim and/or an inner fastener rim, and the outer and/or inner wall presents a respective upstream fastener rim. The chamber end wall and the outer and/or inner wall are fastened together via their fastener rims. Cooling channels are made between the fastener rims and open out to the inside of the combustion chamber. Advantageously, a spacer is placed between the fastener rims, and the channels are formed in the thickness or in the sides of the spacer.
摘要翻译： 公开了一种用于涡轮机的环形燃烧室。 该室包括内壁，外壁和设置在室的上游区域中的内壁和外壁之间的室端壁。 腔室端壁呈现外紧固件边缘和/或内紧固件边缘，并且外壁和/或内壁呈现相应的上游紧固件边缘。 腔室端壁和外壁和/或内壁通过其紧固件边缘紧固在一起。 冷却通道在紧固件边缘之间形成并且向外通向燃烧室的内部。 有利地，间隔件被放置在紧固件轮缘之间，并且通道形成在间隔件的厚度或侧面中。
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公开(公告)号：US07971439B2
公开(公告)日：2011-07-05
申请号：US11859280
申请日：2007-09-21
IPC分类号： F23R3/50
摘要： An annular turbomachine combustion chamber comprising an inner wall, an outer wall, and a chamber end wall disposed between said inner and outer walls in the upstream region of said chamber, the chamber end wall presenting a central portion and an outer assembly flange, and the outer wall presenting an upstream assembly flange, the chamber end wall and the outer wall being assembled together by their assembly flanges, in which the free edge of said outer assembly flange is curved inwards. In addition, the outer face of the outer assembly flange presents a shoulder.
摘要翻译： 一种环形涡轮机燃烧室，包括设置在所述室的上游区域中的所述内壁和外壁之间的内壁，外壁和室端壁，所述室端壁呈现中心部分和外部组件凸缘， 外壁呈现上游组件凸缘，腔室端壁和外壁通过其组装凸缘组装在一起，其中所述外部组件凸缘的自由边缘向内弯曲。 此外，外部组件凸缘的外表面具有肩部。
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公开(公告)号：US08875517B2
公开(公告)日：2014-11-04
申请号：US12919772
申请日：2009-02-20
CPC分类号： F02C3/08 , F04D29/441 , F04D29/444 , F23R3/283 , F23R3/60 , Y02T50/671
摘要： A diffuser for a turbine engine that includes two annular webs extending inside one another and connected between them by substantially radial vanes, wherein the downstream peripheral edge of at least one of the webs includes indentions evenly distributed about the longitudinal axis of the diffuser.
摘要翻译： 一种用于涡轮发动机的扩散器，其包括彼此相对延伸并且通过基本上径向的叶片连接在它们之间的两个环形腹板，其中至少一个腹板的下游周边边缘包括围绕扩散器的纵向轴线均匀分布的凹陷。
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公开(公告)号：US20110056207A1
公开(公告)日：2011-03-10
申请号：US12919772
申请日：2009-02-20
CPC分类号： F02C3/08 , F04D29/441 , F04D29/444 , F23R3/283 , F23R3/60 , Y02T50/671
摘要： A diffuser for a turbine engine that includes two annular webs extending inside one another and connected between them by substantially radial vanes, wherein the downstream peripheral edge of at least one of the webs includes indentions evenly distributed about the longitudinal axis of the diffuser.
摘要翻译： 一种用于涡轮发动机的扩散器，其包括彼此相对延伸并且通过基本上径向的叶片连接在它们之间的两个环形腹板，其中至少一个腹板的下游周边边缘包括围绕扩散器的纵向轴线均匀分布的凹陷。
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公开(公告)号：US20080141680A1
公开(公告)日：2008-06-19
申请号：US11780287
申请日：2007-07-19
申请人： Antoine Robert Alain BRUNET , Patrice Andre Commaret , Didier Hippolyte Hernandez , David Locatelli
发明人： Antoine Robert Alain BRUNET , Patrice Andre Commaret , Didier Hippolyte Hernandez , David Locatelli
CPC分类号： F02C3/08 , F01D5/082 , F01D25/12 , F02C3/14 , F02C7/18 , F05D2240/14 , F05D2250/182 , F23R3/26 , Y02T50/676
摘要： System for ventilating a combustion chamber wall A system for ventilating a combustion chamber wall in a turbomachine comprising a centrifugal compressor (10) supplying, via a diffuser (12), a combustion chamber (14), this system comprising an annular case (90) arranged radially between the combustion chamber and a downstream end-piece (26) of the diffuser and that comprises a radially external wall (92) for the guidance of an air flow coming out of the diffuser, and a radially internal wall (94) delimiting with the end-piece of the diffuser a channel (88) for the air coming out of the diffuser to pass through.
摘要翻译： 用于使燃烧室壁通风的系统用于对涡轮机中的燃烧室壁进行通风的系统，包括经由扩散器（12），燃烧室（14）供应的离心压缩机（10），该系统包括环形壳体（90） 径向地布置在燃烧室和扩散器的下游端件（26）之间，并且包括径向外壁（92），用于引导从扩散器出来的空气流;以及径向内壁（94），其限定 扩散器的端部件用于从扩散器流出的空气通过的通道（88）。
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