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31.发明授权Deflector for a combustion chamber endwall, combustion chamber equipped therewith and turbine engine comprising them 有权用于燃烧室端壁的偏转器，配备燃烧室和包括它们的涡轮发动机公开(公告)号：US08037691B2
公开(公告)日：2011-10-18
申请号：US11950880
申请日：2007-12-05
CPC分类号： F23R3/002
摘要： A deflector takes the form of a plate provided with a hole. The plate is a portion of a conical surface of revolution about a cone axis with a concave face and a convex face. The plate includes a contour with four sides. Two of these the sides are concentric circular arcs centered on the cone axis. The other two sides are segments of generatrices of the cone which connect the first sides. The invention is applicable to a deflector of a chamber endwall of a combustion chamber of a turbine engine.
摘要翻译： 偏转器采取带有孔的板的形式。 板是围绕具有凹面和凸面的锥轴的圆锥形表面的一部分。 该板包括四边的轮廓。 两个侧面是以锥体轴为中心的同心圆弧。 另外两侧是连接第一侧的锥体的母线段。 本发明可应用于涡轮发动机的燃烧室的室端壁的偏转器。
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公开(公告)号：US07937944B2
公开(公告)日：2011-05-10
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
IPC分类号： F02C7/22
CPC分类号： F02C3/08 , F01D5/082 , F01D25/12 , F02C3/14 , F02C7/18 , F05D2240/14 , F05D2250/182 , F23R3/26 , Y02T50/676
摘要： A system for ventilating a combustion chamber wall in a turbomachine is disclosed. The system includes a centrifugal compressor, a diffuser, a combustion chamber, and an annular case arranged radially between the combustion chamber and a downstream end-piece of the diffuser. The annular case includes a radially external wall for the guidance of an air flow coming out of the diffuser, and a radially internal wall delimiting with the end-piece of the diffuser a channel for the air coming out of the diffuser to pass through.
摘要翻译： 公开了一种用于使涡轮机中的燃烧室壁通风的系统。 该系统包括离心式压缩机，扩散器，燃烧室和径向布置在燃烧室与扩散器的下游端部之间的环形壳体。 环形壳体包括用于引导从扩散器出来的空气流的径向外壁，以及限定扩散器的端部的径向内壁，用于从扩散器流出的空气通过。
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公开(公告)号：US20110088402A1
公开(公告)日：2011-04-21
申请号：US12993379
申请日：2009-04-21
IPC分类号： F23R3/46
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：US07827798B2
公开(公告)日：2010-11-09
申请号：US11780246
申请日：2007-07-19
IPC分类号： F02C1/00
CPC分类号： F23R3/26
摘要： A system for ventilating a combustion chamber wall in a turbomachine is disclosed. The system includes a diffuser mounted at the inlet of the combustion chamber, an annular end-piece that extends downstream to an injection device for injecting ventilation air, and an annular convecting metal sheet being arranged radially between the combustion chamber and the end-piece of the diffuser in order to delimit, with an internal wall of the chamber, an annular stream for the flow of air that is stable and without separation supplying holes in the chamber and the injection device.
摘要翻译： 公开了一种用于使涡轮机中的燃烧室壁通风的系统。 该系统包括安装在燃烧室入口处的扩散器，在下游延伸到用于注入通风空气的注射装置的环形端件，以及环形对流金属片，其沿径向设置在燃烧室和末端件之间 扩散器为了界定室的内壁，用于空气流的环形流，其稳定且没有分离在腔室和注射装置中提供孔。
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35.发明申请公开(公告)号：US20080202122A1
公开(公告)日：2008-08-28
申请号：US11770309
申请日：2007-06-28
摘要： The invention relates to an arrangement for a turbomachine combustion chamber, the arrangement comprising a chamber end wall pierced by at least one opening, an injector system, and a deflector mounted on the downstream side of the chamber end wall in the opening by means of an annulus, said injector system including a pinch ring mounted on the upstream side and fastened against the annulus with the pinch ring and the annulus together defining a groove, and a bowl mounted in the opening, the bowl being made up of at least two distinct parts, at least a first part forming an end plate suitable for sliding radially in the groove, and a second part forming a bowl collar that is provided with a collar extending parallel to the chamber end wall on its downstream side, said first and second bowl parts being fastened together by means of a twist-lock coupling.
摘要翻译： 本发明涉及一种用于涡轮机燃烧室的装置，该装置包括由至少一个开口刺穿的腔室端壁，喷射器系统和偏转器，该导流器安装在开口中的腔室端壁的下游侧，借助于 所述注射器系统包括安装在上游侧的夹紧环并且紧固在所述环上，所述夹紧环和所述环一起形成凹槽，以及安装在所述开口中的碗，所述碗由至少两个不同部分 至少第一部分形成适于在该凹槽中径向滑动的端板，以及第二部分，形成一碗碗套环，该碗套环具有平行于其下游侧的室端壁延伸的轴环，所述第一和第二碗部分 通过扭锁联轴器紧固在一起。
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36.发明授权公开(公告)号：US07478534B2
公开(公告)日：2009-01-20
申请号：US11770309
申请日：2007-06-28
IPC分类号： F02C7/20
摘要： The invention relates to an arrangement for a turbomachine combustion chamber, the arrangement comprising a chamber end wall pierced by at least one opening, an injector system, and a deflector mounted on the downstream side of the chamber end wall in the opening by means of an annulus, said injector system including a pinch ring mounted on the upstream side and fastened against the annulus with the pinch ring and the annulus together defining a groove, and a bowl mounted in the opening, the bowl being made up of at least two distinct parts, at least a first part forming an end plate suitable for sliding radially in the groove, and a second part forming a bowl collar that is provided with a collar extending parallel to the chamber end wall on its downstream side, said first and second bowl parts being fastened together by means of a twist-lock coupling.
摘要翻译： 本发明涉及一种用于涡轮机燃烧室的装置，该装置包括由至少一个开口刺穿的腔室端壁，喷射器系统和偏转器，该导流器安装在开口中的腔室端壁的下游侧，借助于 所述注射器系统包括安装在上游侧的夹紧环并且紧固在所述环上，所述夹紧环和所述环在一起限定凹槽，以及安装在所述开口中的碗，所述碗由至少两个不同部分 至少第一部分形成适于在该凹槽中径向滑动的端板，以及第二部分，形成一碗碗套环，该碗套环具有平行于其下游侧的室端壁延伸的轴环，所述第一和第二碗部分 通过扭锁联轴器紧固在一起。
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公开(公告)号：US09599020B2
公开(公告)日：2017-03-21
申请号：US14115980
申请日：2012-05-04
CPC分类号： F02C7/12 , F01D5/186 , F01D5/30 , F01D9/023 , F01D9/041 , F05B2240/201 , F05D2240/81 , F05D2260/201 , F05D2260/202 , Y02T50/676
摘要： A sectorized nozzle for a turbine engine turbine including an inner sectorized annular platform and an outer sectorized annular platform connected together by radial airfoils, at least one of the platforms including a plurality of orifices for passing air in a neighborhood of its upstream end, the orifices being distributed over the circumference of the platform and opening out at their ends remote from the airfoils into a circumferential annular cavity of the sector of the platform, which cavity is closed by a metal sheet fastened to the platform sector and pierced by orifices for feeding cooling air.
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公开(公告)号：US20140116065A1
公开(公告)日：2014-05-01
申请号：US14115980
申请日：2012-05-04
IPC分类号： F02C7/12
CPC分类号： F02C7/12 , F01D5/186 , F01D5/30 , F01D9/023 , F01D9/041 , F05B2240/201 , F05D2240/81 , F05D2260/201 , F05D2260/202 , Y02T50/676
摘要： A sectorized nozzle for a turbine engine turbine including an inner sectorized annular platform and an outer sectorized annular platform connected together by radial airfoils, at least one of the platforms including a plurality of orifices for passing air in a neighborhood of its upstream end, the orifices being distributed over the circumference of the platform and opening out at their ends remote from the airfoils into a circumferential annular cavity of the sector of the platform, which cavity is closed by a metal sheet fastened to the platform sector and pierced by orifices for feeding cooling air.
摘要翻译： 一种用于涡轮发动机涡轮机的分段喷嘴，包括内部扇形环形平台和通过径向翼型件连接在一起的外部扇形环形平台，所述平台中的至少一个包括用于在其上游端附近通过空气的多个孔， 分布在平台的圆周上并且在其远离翼型的端部处开口，进入平台扇区的周向环形空腔中，该空腔被固定到平台扇区的金属片封闭，并被用于进给冷却的孔 空气。
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公开(公告)号：US20140090382A1
公开(公告)日：2014-04-03
申请号：US14118393
申请日：2012-05-11
IPC分类号： F23R3/28
摘要： An annular combustion chamber for a turbine engine, the chamber including an annular row of fuel injectors including heads engaged in fuel injection systems mounted in openings in the chamber end wall, each injector head including at least one fuel-passing helical channel for causing fuel to rotate about the longitudinal axis of the head, and each injection system including at least one swirler including air-passing channels of sections with axes that are inclined relative to the plurality axis of the swirler at an angle that is substantially equal to a helix angle of the helical channel, to within ±10°, and are oriented in a same direction as the channel about the longitudinal axis of the swirler.
摘要翻译： 一种用于涡轮发动机的环形燃烧室，所述腔室包括环形排的燃料喷射器，其包括安装在腔室端壁中的开口中的燃料喷射系统中的头部，每个喷射头包括至少一个燃料通过螺旋通道， 围绕头部的纵向轴线旋转，并且每个注射系统包括至少一个旋流器，其包括具有相对于旋流器的多个轴线倾斜的轴线的空气通过通道，其角度基本上等于螺旋角 螺旋通道在±10°以内，并且沿着与旋流器的纵向轴线的通道相同的方向定向。
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公开(公告)号：US07854126B2
公开(公告)日：2010-12-21
申请号：US11677749
申请日：2007-02-22
CPC分类号： F23R3/10 , F23C5/02 , F23R3/002 , F23R3/50 , F23R3/60 , F23R2900/00017 , F23R2900/00018 , F23R2900/00019
摘要： A one-piece combustion chamber having an end wall subdivided into sectors. The combustion chamber comprises a chamber end wall interconnecting the inner and outer walls, and it includes windows closed by removable walls, each carrying a plurality of injector systems.
摘要翻译： 一体式燃烧室，其具有细分为扇形的端壁。 燃烧室包括连接内壁和外壁的腔室端壁，并且其包括由可移除壁关闭的窗口，每个窗口承载多个喷射器系统。
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