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1.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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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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4.发明申请公开(公告)号：US20110179798A1
公开(公告)日：2011-07-28
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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公开(公告)号：US09091445B2
公开(公告)日：2015-07-28
申请号：US13512802
申请日：2010-12-03
申请人： Jacques Marcel Arthur Bunel , Mario Cesar De Sousa , Nicolas Christian Raymond Leblond , Guillaume Sevi , Denis Jean Maurice Sandelis , Christophe Pieussergues
发明人： Jacques Marcel Arthur Bunel , Mario Cesar De Sousa , Nicolas Christian Raymond Leblond , Guillaume Sevi , Denis Jean Maurice Sandelis , Christophe Pieussergues
CPC分类号： F23R3/50 , F02C7/266 , F23D2207/00 , F23R3/002 , F23R3/60
摘要： A turbine engine combustion chamber including at least one ignition sparkplug carried by an outer casing and extending through a guide mechanism carried by a wall forming a body of revolution of the chamber. The guide mechanism includes a tubular guide having the sparkplug passing axially therethrough, which guide is mounted with axial and transverse clearance on a chimney fastened to the wall of the chamber and opening out therein. The guide includes an annular collar engaged with clearance in an internal annular groove of the chimney. The annular collar is urged to press against a wall of the groove by a resilient member mounted in the groove.
摘要翻译： 一种涡轮发动机燃烧室，包括至少一个点火火花塞，其由外壳承载并延伸穿过由形成所述腔的旋转体的壁承载的引导机构。 引导机构包括一个管状引导件，其具有穿过其中的火花塞，该引导件以固定在腔室壁上并在其中打开的烟囱安装有轴向和横向间隙。 引导件包括与烟囱的内部环形槽中的间隙接合的环形套环。 通过安装在槽中的弹性构件推动环形套环压靠槽的壁。
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公开(公告)号：US20130118181A1
公开(公告)日：2013-05-16
申请号：US13808211
申请日：2011-07-01
IPC分类号： F02C7/264
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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7.发明授权Device for mounting an igniter plug in a combustion chamber of a gas turbine engine 有权用于将点火器塞安装在燃气涡轮发动机的燃烧室中的装置公开(公告)号：US08099963B2
公开(公告)日：2012-01-24
申请号：US12369224
申请日：2009-02-11
IPC分类号： F02C7/266
CPC分类号： F23R3/60 , F02C7/266 , F23D2207/00 , F23D2211/00 , F23R3/06 , F23R2900/00012
摘要： The present invention relates to a device for mounting an igniter plug in a combustion chamber of a gas turbine engine contained in a casing, in which the combustion chamber has an axis YY, the mounting device comprising a hollow shaft, of axis XX, a floating igniter plug sleeve absorbing expansion along an axis perpendicular to the axis XX of the hollow shaft. The device is one which further comprises a hollow shaft sleeve such that the igniter plug sleeve is housed in the hollow shaft sleeve, and means of inclining said hollow shaft sleeve relative to the axis XX. Inclining the hollow shaft sleeve allows the chamber to be inclined relative to the axis XX.
摘要翻译： 本发明涉及一种将点火器塞安装在容纳在壳体中的燃气涡轮发动机的燃烧室中的装置，其中燃烧室具有轴线YY，该安装装置包括轴线XX的空心轴，浮动 点火塞塞套沿垂直于空心轴的轴线XX的轴线吸收膨胀。 该装置还包括空心轴套筒，使得点火器塞套筒容纳在空心轴套筒中，以及使所述中空轴套相对于轴线XX倾斜的装置。 倾斜中空轴套允许腔室相对于轴线XX倾斜。
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公开(公告)号：US08069669B2
公开(公告)日：2011-12-06
申请号：US12199182
申请日：2008-08-27
IPC分类号： F02G3/00
CPC分类号： F23R3/50 , F23R2900/03042
摘要： A combustion chamber which is fitted with a separator disposed between the radially inner wall of the chamber and the inner flange of the chamber is disclosed. The separator includes a tubular portion and a fastener portion. The tubular portion is centered on the main axis of the combustion chamber, with the upstream end thereof being situated upstream from orifices in the radially inner wall of the chamber. The fastener portion is secured to the combustion chamber. The tubular portion splits the flow of air running along the radially inner wall into an inner air flow passing between the tubular portion and the inner flange of the chamber, and an outer air flow passing between the radially inner wall and the tubular portion.
摘要翻译： 公开了一种燃烧室，其装配有设置在室的径向内壁和室的内凸缘之间的隔板。 分离器包括管状部分和紧固件部分。 管状部分在燃烧室的主轴线上居中，其上游端位于腔室的径向内壁中的孔的上游。 紧固件部分固定到燃烧室。 管状部分将沿着径向内壁延伸的空气流分解成通过腔室的管状部分和内部凸缘之间的内部空气流，以及在径向内壁和管状部分之间通过的外部空气流。
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公开(公告)号：US20110203294A1
公开(公告)日：2011-08-25
申请号：US13031880
申请日：2011-02-22
CPC分类号： F23R3/283 , F23R2900/03045 , Y02T50/675
摘要： A fuel injection system for an annular combustion chamber of a turbomachine, the system comprising support means for supporting and centering a fuel injector head, and a bowl arranged downstream from the support means and including at its downstream end an annular collar that extends radially outwards and that is cooled by air impacting against its upstream radial surface, and including on said surface means for disturbing the flow of cooling air and for increasing the heat exchange area between the air and the collar.
摘要翻译： 一种用于涡轮机的环形燃烧室的燃料喷射系统，该系统包括用于支撑和定心燃料喷射头的支撑装置，以及设置在支撑装置下游的碗，并且在其下游端包括径向向外延伸的环形套环， 其被空气冲击其上游径向表面而被冷却，并且包括在所述表面上用于干扰冷却空气的流动并增加空气和轴环之间的热交换面积的装置。
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10.发明授权Chamber endwall, method of producing it, combustion chamber comprising it, and turbine engine equipped therewith 有权室内壁，其制造方法，包括其的燃烧室，以及配备有其的涡轮发动机公开(公告)号：US07954327B2
公开(公告)日：2011-06-07
申请号：US11945580
申请日：2007-11-27
CPC分类号： F23R3/002 , F23R3/04 , F23R3/283 , F23R3/50 , F23R2900/00018 , Y02T50/675 , Y10T29/49236
摘要： A combustion chamber which includes a chamber endwall which takes the form of a substantially frustoconical component including a succession of adjacent planar portions is disclosed. The invention can be applied to a combustion chamber of a turbine engine.
摘要翻译： 公开了一种燃烧室，其包括具有基本截头圆锥形部件形式的腔室端壁，其包括一系列相邻的平面部分。 本发明可应用于涡轮发动机的燃烧室。
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