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1.发明授权Combustion chamber having a multi-hole cooling system with variably oriented holes 失效燃烧室具有具有可变定向孔的多孔冷却系统
公开(公告)号：US5775108A
公开(公告)日：1998-07-07
申请号：US633314
申请日：1996-04-17
CPC分类号： F23R3/06 , F23R3/002 , F05B2250/322 , F05B2260/202
摘要： A combustion chamber, particularly for a turbomachine, has at least one generally axially extending wall provided with a plurality of through holes defining a multi-hole cooling system for the wall. The wall also has a plurality of dilution holes which affect locally the flow of burnt gases in the chamber, and the cooling through holes are oriented according to the local flow of burnt gases in the chamber. In particular the wall is subdivided into first zones, downstream of the dilution holes, in which the through holes are oriented substantially in countercurrent to the overall flow direction of the burnt gases in the chamber, second zones and third zones which are disposed on opposite sides of the first zones and in which the orientation of the through holes is inclined both axially and circumferentially, and a fourth zone covering the remainder of the wall and in which the through holes are inclined axially in the overall flow direction of the burnt gases.
摘要翻译： 特别是用于涡轮机的燃烧室具有至少一个大致轴向延伸的壁，其设有多个限定用于壁的多孔冷却系统的通孔。 该壁还具有多个稀释孔，其局部地影响室中的燃烧气体的流动，并且冷却通孔根据腔室中的燃烧气体的局部流动而定向。 特别地，壁被分为第一区域，在稀释孔的下游，其中通孔被定向成基本上与腔室中的燃烧气体的总流动方向相反地定位，第二区域和第三区域设置在相对侧 的第一区域，并且其中通孔的方向在轴向和周向倾斜，以及覆盖壁的其余部分的第四区域，并且其中通孔在燃烧气体的整个流动方向上轴向倾斜。
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公开(公告)号：US6070412A
公开(公告)日：2000-06-06
申请号：US179896
申请日：1998-10-28
CPC分类号： F23R3/06 , F23R3/04 , F23R3/34 , Y02T50/675
摘要： The invention relates to a combustion chamber containing a number of aerohanical injectors mounted in the end of the chamber that connects the upstream end of two annular walls and which are supplied with fuel permanently during operation. The injectors are arranged in two concentric rows around the axis of symmetry and in pairs in longitudinal planes passing through the axis of symmetry. The injectors of the two rows are more or less equidistant from the outlet of the chamber and have axes directed toward the outlet. A carefully considered distribution of the primary holes, dilution holes and the air flow allows the emissions of oxides of nitrogen to be reduced.
摘要翻译： 本发明涉及一种燃烧室，其包含安装在室的端部中的多个机械式喷射器，其连接两个环形壁的上游端并且在操作期间被永久地供给燃料。 喷射器围绕对称轴线布置成两个同心排，并且成对地布置成穿过对称轴的纵向平面。 这两排的喷射器或多或少与室的出口等距离并具有指向出口的轴线。 精心考虑的主孔，稀释孔和空气流的分布允许减少氮氧化物的排放。
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3.发明授权Device for injecting a mixture of air and fuel, combustion chamber and turbomachine both equipped with such a device 有权用于喷射空气和燃料，燃烧室和涡轮机的混合物的装置，两者都装备有这种装置公开(公告)号：US07721545B2
公开(公告)日：2010-05-25
申请号：US11692441
申请日：2007-03-28
IPC分类号： F23R3/04
CPC分类号： F23R3/60 , F23R3/14 , F23R3/28 , Y02T50/675
摘要： The invention relates to a device for injecting a mixture of air and fuel into a combustion chamber of a turbomachine where the supply of air is improved. The invention relates more particularly to a new type of sliding bushing.
摘要翻译： 本发明涉及一种用于将空气和燃料的混合物喷射到提供空气供应的涡轮机的燃烧室中的装置。 本发明更具体地涉及一种新型的滑动衬套。
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公开(公告)号：US07805943B2
公开(公告)日：2010-10-05
申请号：US11275859
申请日：2006-02-01
IPC分类号： F02C7/20
摘要： A shroud for a combustion chamber bottom designed to cover fuel injectors is provided with drillings on at least one of its sides to open up the cavity within the shroud and reduce noise that it produces and combustion instabilities. The drillings also have the effect of reducing instabilities and non-uniformity of the airflow around the shroud.
摘要翻译： 设计用于覆盖燃料喷射器的用于燃烧室底部的护罩在其至少一侧上设置有钻孔，以打开护罩内的空腔并减少其产生的噪音和燃烧不稳定性。 钻孔还具有减少护罩周围气流的不稳定性和不均匀性的效果。
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公开(公告)号：US6035645A
公开(公告)日：2000-03-14
申请号：US939084
申请日：1997-09-26
申请人： Mehdi Bensaadi , Michel Andre Albert Desaulty , Sebastien Pierre Jean Pitrou , Pierre Marie Victor Emile Schroer
发明人： Mehdi Bensaadi , Michel Andre Albert Desaulty , Sebastien Pierre Jean Pitrou , Pierre Marie Victor Emile Schroer
CPC分类号： F23R3/14 , Y02T50/675
摘要： A fuel injection system is disclosed for a gas turbine engine having a fuel injector issuing a primary fuel flow during all operating modes of the gas turbine engine and a secondary fuel flow when operating parameters of the gas turbine engine exceed predetermined values. The fuel injection system includes a first air swirler, a second air swirler located rearwardly of the first air swirler and a venturi having a wall with a converging-diverging inner wall surface forming a venturi throat, the venturi being located such that the wall separates first and second air flows issuing from the first and second air swirlers and such that the primary fuel flow emanating from the fuel injector in a conical configuration does not impact against the inner wall surface of the venturi.
摘要翻译： 公开了一种用于燃气涡轮发动机的燃料喷射系统，其具有在燃气涡轮发动机的所有运行模式期间发出主燃料流的燃料喷射器和当燃气涡轮发动机的运行参数超过预定值时的次级燃料流。 燃料喷射系统包括第一空气旋流器，位于第一空气旋流器后方的第二空气旋流器和具有形成文丘里喉部的会聚发散内壁表面的壁的文氏管，文丘里管被定位成使得壁分隔开 以及从第一和第二空气旋流器发出的第二空气流，并且使得以锥形构造从燃料喷射器发出的主燃料流不会冲击文丘里管的内壁表面。
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公开(公告)号：US08047777B2
公开(公告)日：2011-11-01
申请号：US12190105
申请日：2008-08-12
CPC分类号： F02C3/08 , F02C3/14 , F04D29/444 , F05D2250/71
摘要： A turbomachine comprising an annular combustion chamber (40) with injection orifices (44); a centrifugal compressor (10) having a centrifugal downstream stage and an annular diffuser (20) comprising: a radially-oriented upstream portion (21)with diffusion passages (22) connected to the outlet of the compressor and an elbow-shaped intermediate portion (24)and a downstream portion (25) comprising a series of flow-straightening vanes (26) and inclined relative to the axis (A) of the turbomachine. In the section plane containing the axis (A) of the turbomachine and passing via the center (C) of one of said injection orifices (44), the curvilinear abscissa distance along a flow line (L) between the middle (0) of the flow path at the trailing edges of the flow-straightening vanes (26) and said center (C) is greater than or equal to three times the height (h) of said flow path.
摘要翻译： 一种涡轮机，包括具有喷射孔（44）的环形燃烧室（40）; 具有离心下游级的离心式压缩机（10）和环形扩散器（20），包括：径向定向的上游部分（21），其具有连接到压缩机出口的扩散通道（22）和肘形中间部分 24）和包括一系列流动矫直叶片（26）并相对于涡轮机的轴线（A）倾斜的下游部分（25）。 在包含涡轮机的轴线（A）并且经过所述喷射孔（44）中的一个的中心（C）的截面中，沿着沿着所述喷嘴的中间（0）之间的流动线（L）的曲线横坐标距离 在流动矫正叶片（26）和所述中心（C）的后缘处的流动路径大于或等于所述流动路径的高度（h）的三倍。
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公开(公告)号：US20090047127A1
公开(公告)日：2009-02-19
申请号：US12190105
申请日：2008-08-12
IPC分类号： F01D9/02
CPC分类号： F02C3/08 , F02C3/14 , F04D29/444 , F05D2250/71
摘要： A turbomachine comprising: an annular combustion chamber (40) with injection orifices (44); a centrifugal compressor (10) having a centrifugal downstream stage; and an annular diffuser (20) comprising: a radially-oriented upstream portion (21) with diffusion passages (22) connected to the outlet of the compressor; an elbow-shaped intermediate portion (24); and a downstream portion (25) comprising a series of flow-straightening vanes (26) and inclined relative to the axis (A) of the turbomachine. In the section plane containing the axis (A) of the turbomachine and passing via the center (C) of one of said injection orifices (44), the curvilinear abscissa distance along a flow line (L) between the middle (O) of the flow path at the trailing edges of the flow-straightening vanes (26) and said center (C) is greater than or equal to three times the height (h) of said flow path.
摘要翻译： 一种涡轮机，包括：具有喷射孔（44）的环形燃烧室（40）; 具有离心下游级的离心式压缩机（10） 和环形扩散器（20），包括：径向定向的上游部分（21），其具有连接到压缩机出口的扩散通道（22） 肘形中间部分（24）; 以及包括一系列流动整流叶片（26）并相对于涡轮机的轴线（A）倾斜的下游部分（25）。 在包含涡轮机的轴线（A）并且经过所述喷射孔（44）中的一个的中心（C）的截面中，沿着沿着所述喷射孔（44）的中间（O）的流线（L）的曲线横坐标距离 在流动矫正叶片（26）和所述中心（C）的后缘处的流动路径大于或等于所述流动路径的高度（h）的三倍。
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公开(公告)号：US5937653A
公开(公告)日：1999-08-17
申请号：US884668
申请日：1997-06-27
CPC分类号： F23R3/10 , F23R3/28 , F23R3/50 , Y02T50/675
摘要： An annular combustion chamber is disclosed for use in a gas turbine engine, the combustion chamber having an axis of symmetry, an inner annular wall, an outer annular wall, and a forward end extending between the inner and outer wall to form boundaries for the combustion chamber. The forward end of the combustion chamber has an inner ring member extending about the axis of symmetry and an outer ring member extending about the axis of symmetry and radially spaced from the inner ring member, the inner and outer ring members forming inner and outer boundaries of an annular chamber that diverges in a rearward direction. The inner and outer ring members are interconnected by a plurality of circumferentially spaced apart spacers so as to form a plurality of arcuate openings between adjacent spacers. A plurality of fuel injector assemblies are associated with the forward end of the combustion chamber, each fuel injector assembly comprising an arcuate injection manifold located in an arcuate member, in turn, located in one of the plurality of arcuate openings so as to divide the arcuate opening into an inner annular space and an outer annular space, the injection manifold having an inner array of injection orifices to inject fuel into the inner annular space, and an outer array of injection orifices to inject fuel into the outer annular space. The inner and outer ring members have a plurality of air swirlers located forwardly of the fuel injection orifices to direct air flows into the inner and outer annular spaces in counter-rotation directions around the axis of symmetry. The injection orifices are oriented so as to direct fuel into the inner and outer annular spaces generally in the same direction as the air flow in the respective annular space.
摘要翻译： 公开了一种用于燃气涡轮发动机的环形燃烧室，燃烧室具有对称轴线，内部环形壁，外部环形壁和在内壁和外壁之间延伸以形成燃烧边界的前端 房间。 燃烧室的前端具有围绕对称轴延伸的内环构件和围绕对称轴线延伸并且与内环构件径向间隔开的外环构件，内圈和外圈构件形成内圈和外边界 环形室沿向后方向分叉。 内圈和外圈构件通过多个周向间隔开的间隔件相互连接，以便在相邻间隔件之间形成多个弧形开口。 多个燃料喷射器组件与燃烧室的前端相关联，每个燃料喷射器组件包括位于弧形构件中的弓形喷射歧管，其又位于多个弓形开口中的一个中，以便将弧形 开口到内部环形空间和外部环形空间中，所述注入歧管具有注入孔的内部阵列以将燃料喷射到内部环形空间中，以及外部阵列的注入孔以将燃料喷射到外部环形空间中。 内圈和外圈构件具有位于燃料喷射孔前方的多个空气旋流器，用于引导空气流绕围绕对称轴线的反向旋转方向的内外环形空间流动。 喷射孔被定向成将燃料引导到内外环形空间中，大体上与相应的环形空间中的空气流相同。
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9.发明授权Device for actively controlling combustion instabilities and for decoking a fuel injector 失效用于主动控制燃烧不稳定性和用于对燃料喷射器进行除焦的装置
公开(公告)号：US5797266A
公开(公告)日：1998-08-25
申请号：US552015
申请日：1995-11-02
申请人： Jean-Marie Brocard , Jean-Yves Capelle , Michel Andre Albert Desaulty , Jean-Paul Perrin , Alain Michel Varizat
发明人： Jean-Marie Brocard , Jean-Yves Capelle , Michel Andre Albert Desaulty , Jean-Paul Perrin , Alain Michel Varizat
IPC分类号： G01L9/08 , F02C7/22 , F02C7/232 , F02C9/26 , F02C9/28 , F02D11/10 , F02M65/00 , F23D11/38 , F23M99/00 , F23N5/16
CPC分类号： F23D11/386 , F02C7/22 , F02C9/26 , F23M20/005 , F23N5/16 , F23R2900/00013 , F23R2900/00014 , Y02T50/677
摘要： A device for actively controlling combustion instabilities and for decokinguel injectors comprises at least one detector for measuring pressure fluctuations in a combustion or afterburner chamber, means for processing the signal output by the detector and providing, in turn, a control voltage, and at least one piezoelectric device which is disposed in a hydraulic line including a fuel injector for the supply of fuel to the combustion or afterburner chamber and which is responsive to the control voltage to generate pulses in the flow of fuel from the outlet of the fuel injector.
摘要翻译： 用于主动控制燃烧不稳定性和用于对燃料喷射器进行除焦的装置包括至少一个用于测量燃烧室或后燃室中的压力波动的检测器，用于处理由检测器输出的信号的装置，以及至少提供一个控制电压 一个压电装置，其设置在包括燃料喷射器的液压管线中，用于向燃烧室或后燃室提供燃料，并且响应于控制电压在燃料喷射器的出口处产生燃料流中的脉冲。
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10.发明授权Device for injecting a mixture of air and fuel, and 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：US07908865B2
公开(公告)日：2011-03-22
申请号：US11768556
申请日：2007-06-26
CPC分类号： 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 includes a novel sliding bushing and a novel annular cup for retaining the sliding bushing, making it possible to improve the air feed of the injection device.
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。 注射装置包括新颖的滑动衬套和用于保持滑动衬套的新型环形杯，使得可以改善注射装置的空气供给。
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