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1.发明授权Turbomachine with separate fuel injection systems, using identical sealing joints 有权涡轮机具有单独的燃油喷射系统，使用相同的密封接头公开(公告)号：US08505311B2
公开(公告)日：2013-08-13
申请号：US12625955
申请日：2009-11-25
IPC分类号： F02C7/20
CPC分类号： F02C7/22 , F02C7/28 , F05D2230/60 , F05D2240/40 , F05D2250/70 , F05D2260/30 , F23R3/283 , F23R2900/00012
摘要： An aircraft turbomachine with a housing, and first and second fuel injection systems, where each system includes an injector fitted with an attachment plate traversed by three mounting holes positioned according to a first configuration for the first system and according to a second configuration distinct from the first for the second system. Each system also includes a reception device installed on the housing, a sealing joint interposed between the plate and the reception device, and securing screws which attach the plate on to its reception device. Sealing joints are identical for the first and second fuel injection systems.
摘要翻译： 一种具有壳体的飞机涡轮机，以及第一和第二燃料喷射系统，其中每个系统包括喷射器，该喷射器装配有由根据第一系统的第一配置定位的三个安装孔穿过的附接板，并且根据不同于 第一个为第二个系统。 每个系统还包括安装在壳体上的接收装置，插入在板和接收装置之间的密封接头，以及将板固定到其接收装置上的固定螺钉。 密封接头与第一和第二燃料喷射系统相同。
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2.发明授权System of attaching an injection system to a turbojet combustion chamber base 有权将喷射系统附接到涡轮喷气燃烧室基座的系统公开(公告)号：US07673460B2
公开(公告)日：2010-03-09
申请号：US11422177
申请日：2006-06-05
申请人： Didier Hippolyte Hernandez , Romain Nicolas Lunel , Christophe Pieussergues , David Pinchon , Guillaume Sevi
发明人： Didier Hippolyte Hernandez , Romain Nicolas Lunel , Christophe Pieussergues , David Pinchon , Guillaume Sevi
IPC分类号： F23R3/60
摘要： A system of attaching an injection system to a turbojet combustion chamber base. It comprises a deflector welded onto the chamber base. The deflector comprises an annular portion having an edge forming a retaining shoulder directed toward the front of the turbojet and the injection system comprises a collar on which is formed a retaining shoulder directed toward the rear of the turbojet and pressing against the retaining shoulder of the deflector.
摘要翻译： 将喷射系统附接到涡轮喷气燃烧室基座的系统。 它包括焊接到腔室底座上的偏转器。 偏转器包括环形部分，其具有形成朝向涡轮喷气发动机的前部的保持肩部的边缘，并且注射系统包括套环，在该套环上形成有朝向涡轮喷气发动机的后部并且抵靠导流板的保持肩部的保持肩 。
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公开(公告)号：US20060242939A1
公开(公告)日：2006-11-02
申请号：US11410068
申请日：2006-04-25
CPC分类号： F23R3/10 , F23R3/002 , F23R3/50 , F23R3/60 , F23R2900/00017
摘要： The component elements of a jet engine combustion chamber are assembled together in a manner that is designed to facilitate maintenance while also improving aerodynamic performance. In an embodiment, the outer cap and the inner cap have tongues and the chamber end wail has corresponding tongues, and the tongues of the caps are assembled to the tongues of the chamber end wall.
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4.发明授权System for injecting a mixture of air and fuel into a turbomachine combustion chamber 有权用于将空气和燃料的混合物喷射到涡轮机燃烧室中的系统公开(公告)号：US08312723B2
公开(公告)日：2012-11-20
申请号：US12333732
申请日：2008-12-12
IPC分类号： F23R3/30
CPC分类号： F23R3/14 , F23R2900/03041
摘要： A system for injecting a mixture of air and fuel into a turbomachine combustion chamber is disclosed. The system includes a fuel injector and a Venturi with an interior surface delimiting a premixing chamber. The Venturi includes an internal annular airflow cavity which is connected by air outlet ducts to the premixing chamber. The air outlet ducts open onto the interior surface of the Venturi so as to prevent to deposition of soot and the formation of coke on this surface.
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燃烧室中的系统。 该系统包括燃料喷射器和具有限定预混合室的内表面的文丘里管。 文丘里管包括一个内部环形空气流通道，通过出气管连接到预混合室。 空气出口管道通向文丘里管的内表面，以防止烟灰沉积并在该表面上形成焦炭。
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5.发明申请TURBOMACHINE WITH SEPARATE FUEL INJECTION SYSTEMS, USING IDENTICAL SEALING JOINTS 有权具有独立燃料喷射系统的涡轮机，使用标识密封接头公开(公告)号：US20100132363A1
公开(公告)日：2010-06-03
申请号：US12625955
申请日：2009-11-25
IPC分类号： F02C7/22
CPC分类号： F02C7/22 , F02C7/28 , F05D2230/60 , F05D2240/40 , F05D2250/70 , F05D2260/30 , F23R3/283 , F23R2900/00012
摘要： The present invention concerns a unit (1) for aircraft turbomachine comprising a housing (6), and first (8a) and second (8b) fuel injection systems, where each system comprises: an injector (10a, 10b) fitted with an attachment plate (16a, 16b) traversed by three mounting holes positioned according to a first configuration for the first systems and according to a second configuration distinct from the first for the second systems; a reception device (12a, 12b) installed on the housing; a sealing joint (14) interposed between the plate and the reception device; and securing screws (18a, 18b) attaching the plate on to its reception device. According to the invention, the sealing joints (14) are identical for the first and second fuel injection systems.
摘要翻译： 本发明涉及一种用于飞机涡轮机的单元（1），其包括壳体（6）和第一（8a）和第二（8b）燃料喷射系统，其中每个系统包括：装配有附接板的喷射器（10a，10b） （16a，16b）由根据第一系统的第一配置定位的三个安装孔穿过，并且根据与第一系统不同的第二配置; 安装在所述壳体上的接收装置（12a，12b） 介于所述板和所述接收装置之间的密封接头（14）; 以及将板安装到其接收装置上的固定螺钉（18a，18b）。 根据本发明，密封接头（14）对于第一和第二燃料喷射系统是相同的。
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6.发明申请公开(公告)号：US20090266080A1
公开(公告)日：2009-10-29
申请号：US12427321
申请日：2009-04-21
CPC分类号： F01D9/023 , F05D2250/311 , F23R3/06 , F23R3/50 , Y02T50/675
摘要： A turbomachine including an annular combustion chamber fitted with fuel injectors and nozzle vanes arranged at the outlet from the chamber, the number of nozzle vanes being an integer multiple of the number of fuel injectors, and the head of each injector being situated angularly half-way between the leading edges of two consecutive nozzle vanes, these leading edges being in alignment with primary air holes and/or with dilution air holes.
摘要翻译： 涡轮机包括环形燃烧室，其配备有燃料喷射器和布置在室的出口处的喷嘴叶片，喷嘴叶片的数量是燃料喷射器的数量的整数倍，并且每个喷射器的喷头位于角度中途 在两个连续的喷嘴叶片的前缘之间，这些前缘与主气孔和/或稀释气孔对准。
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公开(公告)号：US5524430A
公开(公告)日：1996-06-11
申请号：US004606
申请日：1993-01-14
摘要： A combustion chamber for a gas-turbine engine is disclosed in which the walls defining the combustion chamber may be easily attached to and removed from the engine structure. A dome member is attached to the engine structure such that it partially encloses the fuel injector nozzle in an upstream direction. The shape of the dome-member is such that it splits the incoming oxidizer flow into inner and outer flows which pass along the inner and outer sides of the combustion chamber. The inner and outer walls of the combustion chamber may be attached to an upstream end wall of the combustion chamber such that this assembly is removable as a unit from the dome member. The inner and outer walls, as well as the end wall, are releasably attached to the dome member such that the assembly can be removed from the gas-turbine engine without the necessity of removing or displacing the fuel injector nozzles or the dome member. Alternatively, the end wall of the combustion chamber is fixedly attached to the dome member while the inner and outer walls of the combustion chamber are releasably attached to the end wall. This enables the inner and outer walls to be separately removed from the gas-turbine engine, again without disturbing the fuel injector nozzles or the dome member.
摘要翻译： 公开了一种用于燃气涡轮发动机的燃烧室，其中限定燃烧室的壁可以容易地附接到发动机结构并从发动机结构中移除。 穹顶构件附接到发动机结构，使得其沿上游方向部分地包围燃料喷射器喷嘴。 圆顶构件的形状使得其将进入的氧化剂流分解成沿燃烧室的内侧和外侧通过的内部和外部流动。 燃烧室的内壁和外壁可以附接到燃烧室的上游端壁，使得该组件作为一个单元可从圆顶构件移除。 内壁和外壁以及端壁可释放地附接到圆顶构件，使得组件可以从燃气涡轮发动机移除，而不需要移除或移动燃料喷射器喷嘴或穹顶构件。 或者，燃烧室的端壁固定地附接到圆顶构件，而燃烧室的内壁和外壁可释放地附接到端壁。 这样可以使内壁和外壁分别从燃气涡轮发动机移除，同时不会干扰燃料喷射器喷嘴或穹顶构件。
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公开(公告)号：US5417069A
公开(公告)日：1995-05-23
申请号：US253912
申请日：1994-06-03
申请人： Jean-Paul D. Alary , Michel A. A. Desaulty , Christophe Pieussergues , Denis J. M. Sandelis , Pierre M. V. E. Schroer
发明人： Jean-Paul D. Alary , Michel A. A. Desaulty , Christophe Pieussergues , Denis J. M. Sandelis , Pierre M. V. E. Schroer
CPC分类号： F23R3/50 , F23R3/04 , F23R3/34 , Y02T50/675
摘要： A separator for an annular gas turbine engine combustion chamber is disclosed having a plurality of separator segments arranged in a generally annular configuration to form an annular separator extending from an upstream end wall of a combustion chamber into the combustion chamber so as to separate first and second combustion zones within the combustion chamber. Each of the separator segments has a hollow interior defined by a front wall, an outer wall, an inner wall which has at least a portion tapering or converging towards the outer wall in a direction extending away from the front wall, and first and second sides. The sides define an array of holes communicating with the hollow interior, the positioning of the array of holes on a first sides being different from that of the array of holes on the second sides such that the axes of the holes are out of alignment with each other. The first sides of one separator segment is positioned adjacent to, but spaced apart from a second sides of an adjacent separator segment. Since the array of holes on the first sides is out of alignment with the array of holes on the second sides, pressurized gas within the interior of the hollow segment will pass through the holes in the first and second sides and will impinge upon the adjacent sides so as to cool both the adjacent sides and the sides through which the gas passes.
摘要翻译： 公开了一种用于环形燃气涡轮发动机燃烧室的分离器，其具有以大致环形构造布置的多个分离器段，以形成从燃烧室的上游端壁进入燃烧室的环形分离器，以便分开第一和第二 燃烧室内的燃烧区。 每个分离器段具有由前壁，外壁，内壁限定的中空内部，内壁具有至少一部分在远离前壁延伸的方向上朝向外壁渐缩或会聚的部分，以及第一和第二侧 。 侧面限定了与中空内部连通的孔阵列，第一侧上的孔阵列的定位与第二侧上的孔阵列的定位不同，使得孔的轴线与每个孔不对齐 其他。 一个分离器段的第一侧定位成与相邻的分隔段的第二侧相邻但间隔开。 由于第一侧上的孔阵列与第二侧上的孔阵列不对齐，所以中空部分内部的加压气体将穿过第一侧和第二侧的孔并且将撞击相邻的侧面 以便冷却气体通过的相邻侧面和侧面。
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公开(公告)号：US08806872B2
公开(公告)日：2014-08-19
申请号：US13808211
申请日：2011-07-01
摘要： A procedure for igniting a combustion chamber of a turbine engine, the chamber being fed with fuel by injectors and including an igniter mechanism igniting the fuel injected into the chamber. The procedure includes an initial stage during which fuel is injected into the chamber at a constant rate while simultaneously exciting the igniter mechanism, and in event of non-ignition of the chamber at an end of the initial stage, a second stage during which a rate at which fuel is injected is increased rapidly by 20% to 30%.
摘要翻译： 用于点燃涡轮发动机的燃烧室的过程，该腔室由喷射器供给燃料，并且包括点燃喷射到腔室中的燃料的点火器机构。 该过程包括初始阶段，在该初始阶段期间，以恒定速率将燃料喷射到室中，同时激发点火器机构，并且在初始阶段结束时腔室不点燃的情况下，在第二阶段期间， 注入燃料的燃料迅速增加20％至30％。
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公开(公告)号：US08047002B2
公开(公告)日：2011-11-01
申请号：US12259714
申请日：2008-10-28
IPC分类号： F02C1/00
摘要： The present invention relates to an annular combustion chamber of a gas turbine engine comprising a casing with at least one air tapping outlet situated at the chamber inlet, a fuel supply device with a plurality of fuel injectors in the chamber distributed annularly of which at least one is situated close to said tapping outlet.The chamber is characterized in that the fuel supply device comprises a means for reducing the fuel flow rate in said injector situated close to the tapping outlet relative to the other fuel injectors.Thanks to the invention, the hot spots downstream of the combustion chamber caused by the tappings are reduced.
摘要翻译： 本发明涉及一种燃气涡轮发动机的环形燃烧室，其包括壳体，该壳体具有位于室入口处的至少一个空气出口出口，燃料供应装置具有在腔室内分布的多个燃料喷射器，其中至少一个 位于靠近所述出水口。 该室的特征在于，燃料供应装置包括用于降低相对于其它燃料喷射器位于靠近出水口的位于所述喷射器中的燃料流量的装置。 由于本发明，由于这种攻丝引起的燃烧室下游的热点减少了。
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