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公开(公告)号：US07849693B2
公开(公告)日：2010-12-14
申请号：US11868176
申请日：2007-10-05
IPC分类号： F02C1/00
CPC分类号： F23R3/346 , F02C7/22 , F23D2900/11001 , F23D2900/11101 , F23R3/30
摘要： A fuel injector for a gas turbine engine combustion chamber is disclosed. The fuel injector includes a first fuel supply line for running at idle speed, a second, main, fuel supply line for running at speeds up to full throttle, and first and second injection orifices with which the two fuel supply lines respectively communicate. The injection orifices are arranged in a ring and the first orifices occupy a sector of the ring.
摘要翻译： 公开了一种用于燃气涡轮发动机燃烧室的燃料喷射器。 燃料喷射器包括用于以怠速运行的第一燃料供应管线，用于以高达全速节流的速度运行的第二主要燃料供应管线，以及两个燃料供应管线分别与之连通的第一和第二喷射孔。 注射孔布置成环，并且第一孔口占据环的扇形部分。
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22.发明授权Device for injecting a mixture of air and fuel, and a combustion chamber and turbomachine provided with such a device 有权用于喷射空气和燃料的混合物的装置，以及具有这种装置的燃烧室和涡轮机公开(公告)号：US07707832B2
公开(公告)日：2010-05-04
申请号：US11566330
申请日：2006-12-04
CPC分类号： F23R3/283 , F23R3/14 , Y02T50/675
摘要： A device for injecting a mixture of air and fuel into a combustion chamber of a turbomachine is disclosed. The injection device has symmetry of revolution about an axis and includes radial swirl inducers of outside diameter D2, a bowl spaced axially from the radial swirl inducers, and a support ring for supporting the injection device, which is arranged around the bowl. The bowl has a cylindrical wall extended by a flared wall, the flared wall being provided with air intake holes. The support ring includes a first cylindrical portion of outside diameter D3, connected to a second cylindrical portion of outside diameter D4 spaced axially from the first cylindrical portion, the first cylindrical portion being connected to the cylindrical wall of the bowl by a plurality of support tabs.
摘要翻译： 公开了一种用于将空气和燃料的混合物喷射到涡轮机的燃烧室中的装置。 注射装置具有围绕轴线的旋转对称性，并且包括外径D2的径向漩涡诱导器，与径向涡流诱导器轴向间隔开的碗，以及用于支撑围绕碗的喷射装置的支撑环。 碗具有由扩口壁延伸的圆柱形壁，扩口壁设有进气孔。 支撑环包括外直径D3的第一圆柱形部分，其连接到与第一圆柱形部分轴向间隔开的外径D4的第二圆柱形部分，第一圆柱形部分通过多个支撑片连接到碗的圆柱形壁 。
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23.发明申请DEVICE FOR INJECTING A MIXTURE OF AIR AND FUEL, AND COMBUSTION CHAMBER AND TURBOMACHINE BOTH EQUIPPED WITH SUCH A DEVICE 有权用于注射空气和燃料混合物的装置，以及装备有这种装置的燃烧室和涡轮二氧化碳公开(公告)号：US20080178598A1
公开(公告)日：2008-07-31
申请号：US11768603
申请日：2007-06-26
IPC分类号： F02C7/22
CPC分类号： F23R3/14 , Y02T50/675
摘要： The invention relates to the field of turbomachines and an injection device (10) for injecting a mixture of air and fuel into a combustion chamber (4) of a turbomachine (1). It is more specifically concerned with an injection device (10) equipped with two fuel circuits and relates to a novel Venturi (50) the shape of which improves the carburation.
摘要翻译： 本发明涉及涡轮机领域和用于将空气和燃料的混合物喷射到涡轮机（1）的燃烧室（4）中的注射装置（10）。 更具体地涉及配备有两个燃料回路的注射装置（10），并且涉及一种新型文丘里管（50），其形状改善了渗碳。
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24.发明申请TURBOMACHINE COMBUSTION CHAMBER ARRANGEMENT HAVING A COLLAR DEFLECTOR 有权涡轮机燃烧室安装有一个COLLAR DEFLECTOR公开(公告)号：US20080000447A1
公开(公告)日：2008-01-03
申请号：US11769464
申请日：2007-06-27
申请人： David Locatelli , Romain Nicolas Lunel , Thomas Olivier Marie Noel , Denis Jean Maurice Sandelis
发明人： David Locatelli , Romain Nicolas Lunel , Thomas Olivier Marie Noel , Denis Jean Maurice Sandelis
IPC分类号： F02C7/00
CPC分类号： F23R3/14 , F23D2211/00 , F23R3/283
摘要： The invention relates to an arrangement for a turbomachine combustion chamber, comprising a chamber end wall pierced by at least one substantially circular opening, a deflector mounted from the downstream side of the chamber end wall in the opening by means of an annulus, an injector system associated with the opening and including an annular bowl that is flared downstream, passing through said opening, and means enabling the injector system to shift off-center relative to the chamber end wall, the deflector including an annular collar extending radially inwards, and the bowl of the injector system including at its downstream end an outwardly-open annular groove radially in alignment with the collar of the deflector in such a manner as to enable it to retract into said groove in the event of the injector system shifting off-center relative to the chamber end wall.
摘要翻译： 本发明涉及一种用于涡轮机燃烧室的装置，其包括由至少一个基本上圆形的开口刺穿的室端壁，通过环形空间从开口中的室端壁的下游侧安装的偏转器， 与所述开口相关联并且包括通过所述开口向下游延伸的环形碗，以及使得所述喷射器系统能够相对于所述腔室端壁偏离偏移的装置，所述偏转器包括径向向内延伸的环形凸缘，并且所述碗 所述喷射器系统在其下游端包括径向与偏转器的轴环对准的向外开放的环形槽，以使得在喷射器系统偏离中心的情况下使其能够缩回到所述凹槽中 腔室端壁。
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25.发明申请公开(公告)号：US20070227149A1
公开(公告)日：2007-10-04
申请号：US11691835
申请日：2007-03-27
IPC分类号： F23R3/00
CPC分类号： F23R3/06
摘要： The invention relates to an annular combustion chamber of a turbomachine having an end wall and side walls (3) extending longitudinally from the end wall, situated at the upstream end (M) of the chamber (1), to an orifice for discharging a stream of combustion gases, situated at the downstream end (V) of the chamber (1), the side walls (3) comprising at least one row of openings (30) for the intake of air for diluting the stream of combustion gases.According to the invention, at least one dilution opening (30) has an upstream edge which projects toward the inside of the chamber (1) and a downstream edge which projects toward the outside of the chamber (1) and is asymmetric to the upstream edge with respect to a plane extending transversely to the wall (3), the aperture of the opening (30) having an axis oriented in an oblique direction with respect to the wall (3), this direction being oriented toward the inside (1) and toward the downstream end (V) of the chamber.
摘要翻译： 本发明涉及一种涡轮机的环形燃烧室，其具有端壁和位于室（1）的上游端（M）处的从端壁纵向延伸的侧壁（3）到用于排出流 的燃烧气体，位于室（1）的下游端（V）处，侧壁（3）包括至少一排开口（30），用于吸入空气以稀释燃烧气体流。 根据本发明，至少一个稀释开口（30）具有朝向腔室（1）的内部突出的上游边缘和朝向腔室（1）的外部突出并且与上游边缘不对称的下游边缘 相对于横向于壁（3）延伸的平面，开口（30）的孔具有相对于壁（3）在倾斜方向上定向的轴线，该方向朝向内侧（1）并且 朝向腔室的下游端（V）。
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公开(公告)号：US5642621A
公开(公告)日：1997-07-01
申请号：US561275
申请日：1995-11-21
申请人： Jean-Paul Daniel Alary , Denis Roger Henri Ansart , Yves Francois Andre Salan , Denis Jean Maurice Sandelis
发明人： Jean-Paul Daniel Alary , Denis Roger Henri Ansart , Yves Francois Andre Salan , Denis Jean Maurice Sandelis
摘要： An improved dual-head combustion chamber is disclosed having a generally annular configuration extending about a central axis with a low power head, operating during low power engine conditions and a radially displaced high power head operative under high power engine operating conditions. The low power head has N number of fuel/air injector assemblies arranged in an annular array and spaced apart in a circumferential direction about the central axis. The fuel/air injector assemblies of the low power head have an air permeability of P1. The high power head also is arranged in a generally annular array with N number of first fuel/air injector assemblies and N number of second fuel/air injector assemblies with each of the second fuel/air injector assemblies aligned with a fuel/air injector assembly of the low power head along a radius line extending from the central axis. The second fuel/air injector assemblies have an air permeability of P2 such that P2 is greater than P1 and supply a fuel/air mixture to the combustion chamber during high power operation. The first fuel/air injector assemblies located in the high power head are located circumferentially spaced between adjacent second fuel/air injector assemblies. The first fuel/air injector assemblies have an air permeability of P1 and supply fuel/air mixture to the combustion chamber during low power operation.
摘要翻译： 公开了一种改进的双头燃烧室，其具有在低功率发动机条件下操作的低功率头围绕中心轴线延伸的大体环形构造，以及在高功率发动机运行条件下操作的径向位移高功率头。 低功率头具有排列成环形阵列的N个燃料/空气喷射器组件，并且围绕中心轴在圆周方向上间隔开。 低功率头的燃料/空气喷射器组件具有P1的透气性。 大功率头还布置成具有N个第一燃料/空气喷射器组件和N个第二燃料/空气喷射器组件的大致环形阵列，其中每个第二燃料/空气喷射器组件与燃料/空气喷射器组件对准 的低功率头沿着从中心轴线延伸的半径线。 第二燃料/空气喷射器组件的透气度为P2，使得P2大于P1，并且在大功率运行期间将燃料/空气混合物供应到燃烧室。 位于高功率头部的第一燃料/空气喷射器组件位于相邻的第二燃料/空气喷射器组件之间周向间隔开。 第一燃料/空气喷射器组件具有P1的透气性并且在低功率操作期间将燃料/空气混合物供应到燃烧室。
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公开(公告)号：US09951955B2
公开(公告)日：2018-04-24
申请号：US14118393
申请日：2012-05-11
摘要： An annular combustion chamber for a turbine engine is provided. The chamber includes an annular row of fuel injectors including heads engaged in fuel injection systems mounted in openings in the chamber end wall. Each injector head includes at least one fuel-passing helical channel for causing fuel to rotate about the longitudinal axis of the head. Each injection system includes 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.
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公开(公告)号：US09175856B2
公开(公告)日：2015-11-03
申请号：US13388345
申请日：2010-08-02
CPC分类号： F23R3/06 , F23R3/50 , Y02T50/675
摘要： A combustion chamber for a turbomachine, including two coaxial walls including air inlets, each of which is configured such that its orthogonal projection, in a plane passing through the axis of the injection system closest to the inlet and perpendicular to an axial plane passing through this axis and through the axis of the combustion chamber, has an upstream edge of convex shape when seen from downstream.
摘要翻译： 一种用于涡轮机的燃烧室，包括两个包括空气入口的同轴壁，每个共同壁包括空气入口，每个同轴壁构造成使得其正交突出部在穿过喷射系统的轴线的平面中最接近入口并垂直于穿过该喷射系统的轴向平面 并且通过燃烧室的轴线从下游看时具有凸形的上游边缘。
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公开(公告)号：US08763406B2
公开(公告)日：2014-07-01
申请号：US12918946
申请日：2009-03-06
IPC分类号： F02C7/20
CPC分类号： F23R3/60 , F23R3/10 , Y02T50/675
摘要： A turbomachine combustion chamber in which a chamber end wall presents an opening for receiving a pre-vaporization bowl, and including a device for injecting air and fuel mounted on the axis thereof, the bowl being floatingly mounted relative to the chamber end wall to move in a predetermined radial direction and flaring downstream so as to form a collar, a deflector forming a thermal shield being made integrally with the bowl beside the chamber end wall so that the floating movement of the bowl-and-deflector assembly takes place in a sliding plane situated between the deflector and the chamber end wall.
摘要翻译： 一种涡轮机燃烧室，其中室端壁具有用于接收预蒸发碗的开口，并且包括用于喷射安装在其轴线上的空气和燃料的装置，所述碗相对于室端壁浮动地安装以在 预定的径向方向和向下游扩张以便形成一个套环，一个形成热屏蔽的导流板与腔室端壁旁边的碗一体制成，使得碗 - 偏转器组件的浮动运动发生在滑动平面 位于导流板和腔室端壁之间。
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30.发明授权公开(公告)号：US08661828B2
公开(公告)日：2014-03-04
申请号：US13121902
申请日：2009-10-05
CPC分类号： F01D11/005 , F01D9/023 , F02C7/28 , F16J15/0887 , Y02T50/675
摘要： A turbomachine including an annular combustion chamber, a sectorized turbine nozzle arranged at an outlet from the chamber, and a sealing mechanism interposed axially between the chamber and the nozzle, the sealing mechanism including an annular gasket that is axially resilient. The gasket includes a first axial bearing mechanism for bearing against a downstream end of the chamber and a downstream annular lip that is sectorized, each sector of the downstream lip being in alignment with a sector of the nozzle and including a second axial bearing mechanism for bearing against an upstream end of the nozzle sector.
摘要翻译： 一种涡轮机，包括环形燃烧室，布置在所述室的出口处的扇形涡轮喷嘴，以及轴向插入在所述室和所述喷嘴之间的密封机构，所述密封机构包括轴向弹性的环形垫圈。 所述垫圈包括用于支撑所述腔室的下游端的第一轴向轴承机构和被分隔开的下游环形唇缘，所述下游唇缘的每个扇形区域与所述喷嘴的扇形区段对准，并且包括用于轴承的第二轴向轴承机构 针对喷嘴部分的上游端。
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