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公开(公告)号：US08490402B2
公开(公告)日：2013-07-23
申请号：US12694622
申请日：2010-01-27
IPC分类号： F02K3/10
CPC分类号： F02K3/11 , F02C7/266 , F05D2260/20 , F23D2207/00 , F23R3/20 , Y02T50/676
摘要： An afterburner chamber includes a burner ring having housed therein an annular fuel strip that is pierced by orifices and that is mounted inside an annular thermal protection tube, and an ignition spark plug penetrating into the inside of the burner ring. The protection tube and the burner ring have orifices for passing air. The chamber also includes a device for ventilating the orifices of the fuel strip that are situated in the immediate vicinity of the spark plug.
摘要翻译： 后燃室包括燃烧器环，其中容纳有由孔刺穿并且安装在环形热保护管内的环形燃料条和安装在燃烧器环内部的点火火花塞。 保护管和燃烧器环具有用于通过空气的孔。 该室还包括用于使位于火花塞附近的燃料带的孔通风的装置。
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公开(公告)号：US20130042623A1
公开(公告)日：2013-02-21
申请号：US13561218
申请日：2012-07-30
摘要： Assembly consisting of a reverse-flow combustion chamber for a turbomachine and a diffuser intended to be positioned at the outlet of a centrifugal compressor and comprising two faces running parallel to one another, the said combustion chamber comprising a first annular part configured to bear at least one injection system and a second annular part extending beyond this first part so as to form a guide canal for turning back the direction in which the gases passing through the chamber flow, with reference to the axis of rotation of the said turbomachine, the axis Y-Y of the said first part being secant with the said axis of rotation, the assembly being characterized in that the said faces of the diffuser have a curved shape which evolves parallel to that of the outer wall of the chamber at its turn-back canal.
摘要翻译： 包括用于涡轮机的反向流动燃烧室和用于定位在离心式压缩机的出口处的扩散器的组件，包括彼此平行延伸的两个面，所述燃烧室包括构造成承受至少 一个注射系统和第二环形部分延伸超出该第一部分，以便形成导向管道，用于相对于所述涡轮机的轴线YY转回通过腔室的气体流动的方向流动 所述第一部分与所述旋转轴线相切，所述组件的特征在于，所述扩散器的所述表面具有平行于所述腔室的后壁的外壁的弯曲形状。
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3.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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公开(公告)号：US07891190B2
公开(公告)日：2011-02-22
申请号：US11745161
申请日：2007-05-07
IPC分类号： F02C1/00
CPC分类号： F23R3/10 , F23R3/14 , F23R3/286 , Y02T50/675
摘要： A combustion chamber of a turbomachine is disclosed. The combustion chamber includes at least one bowl with a substantially frustoconical wall that is formed with an annular row of air injection orifices and a fuel injector arranged upstream of the bowl. The annular row of air injection orifices includes smaller-diameter orifices and larger-diameter orifices which are arranged in alternating fashion and with a uniform distribution around the axis of the bowl to produce two annular air/fuel mixture layers.
摘要翻译： 公开了一种涡轮机的燃烧室。 燃烧室包括具有基本上截头圆锥形壁的至少一个碗，其形成有环形排的空气喷射孔和布置在碗的上游的燃料喷射器。 空气喷射孔的环形排包括小直径孔和较大直径的孔，它们以交替的方式布置并且围绕碗的轴线均匀分布以产生两个环形的空气/燃料混合物层。
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5.发明授权Gas turbine engine diffuser and combustion chamber and gas turbine engine comprising same 有权燃气涡轮发动机扩散器和包括其的燃烧室和燃气涡轮发动机公开(公告)号：US07823387B2
公开(公告)日：2010-11-02
申请号：US12018585
申请日：2008-01-23
申请人： Patrice Andre Commaret , Michel Andre Albert Desaulty , Romain Nicolas Lunel , Denis Jean Maurice Sandelis
发明人： Patrice Andre Commaret , Michel Andre Albert Desaulty , Romain Nicolas Lunel , Denis Jean Maurice Sandelis
CPC分类号： F23R3/26 , F02C3/14 , F23R3/04 , F23R3/50 , Y02T50/675
摘要： A gas turbine engine diffuser defined between an external casing and an internal casing of the engine and supplied with air via an upstream annular diffuser duct is disclosed. The diffuser includes a combustion chamber of the convergent type, forming an external annular duct with the external casing and an internal annular duct with the internal casing, and a cowling partially closing off the external annular duct. The cowling is positioned toward the closed end of the combustion chamber.
摘要翻译： 公开了一种燃气涡轮发动机扩散器，其限定在发动机的外部壳体和内部壳体之间，并且经由上游环形扩散器管道供给空气。 扩散器包括会聚型的燃烧室，形成具有外部壳体的外部环形管道和具有内部壳体的内部环形管道，并且整流罩部分地封闭外部环形管道。 整流罩朝向燃烧室的封闭端。
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公开(公告)号：US07788929B2
公开(公告)日：2010-09-07
申请号：US11560151
申请日：2006-11-15
CPC分类号： F23R3/60 , F23R3/10 , F23R3/283 , F23R2900/00012 , F23R2900/03044 , Y02T50/675
摘要： A combustion chamber having a chamber end wall that presents a plurality of air and fuel injector devices, each of the devices including a bowl and a deflector mounted on a main axis forming a heat shield disposed around the bowl which flares in the gas flow direction and possesses an annular portion, the interface between the bowl and the deflector being situated on this annular portion, at least a portion of the interface being situated towards the end of the annular portion that is downstream in the gas flow direction, such that an annular cavity is defined between the deflector and the downstream annular portion of the interface. First bowl holes are formed in the annular portion to open out facing the edge of the chamber end wall that is in contact with the deflector in order to sustain a flow of air from upstream to downstream in the annular cavity.
摘要翻译： 一种具有腔室端壁的燃烧室，其具有多个空气和燃料喷射器装置，每个装置包括安装在主轴上的碗和偏转器，所述偏转器形成围绕所述碗布置的热屏蔽，所述隔热罩沿气体流动方向展开， 具有环形部分，碗和偏转器之间的界面位于该环形部分上，该界面的至少一部分朝向气体流动方向下游的环形部分的端部定位，使得环形空腔 界定在导流板和界面的下游环形部分之间。 第一碗孔形成在环形部分中，以朝向与偏转器接触的腔室端壁的边缘开口，以便在环形空腔中从上游到下游维持空气流。
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7.发明申请GAS TURBINE ENGINE DIFFUSER AND COMBUSTION CHAMBER AND GAS TURBINE ENGINE COMPRISING SAME 有权气体涡轮发动机发动机和燃烧室和包含其的燃气涡轮发动机公开(公告)号：US20080245053A1
公开(公告)日：2008-10-09
申请号：US12018585
申请日：2008-01-23
申请人： Patrice Andre COMMARET , Michel Andre Albert Desaulty , Romain Nicolas Lunel , Denis Jean Maurice Sandelis
发明人： Patrice Andre COMMARET , Michel Andre Albert Desaulty , Romain Nicolas Lunel , Denis Jean Maurice Sandelis
IPC分类号： F02K3/02
CPC分类号： F23R3/26 , F02C3/14 , F23R3/04 , F23R3/50 , Y02T50/675
摘要： The present invention relates to a gas turbine engine diffuser (30) defined between an external casing (32) and an internal casing (34) of said engine and supplied with air via an upstream annular diffuser duct (36), comprising a combustion chamber (10) of the convergent type, forming an external annular duct (28) with the external casing (32) and an internal annular duct with the internal casing (34), which diffuser comprises a cowling partially closing off the external annular duct. More specifically, the cowling is positioned toward the closed end of the combustion chamber.
摘要翻译： 本发明涉及一种限定在所述发动机的外壳（32）和内壳（34）之间的燃气轮机发动机扩散器（30），并且经由上游环形扩散器管道（36）供应空气，所述上游环形扩散器管道包括燃烧室 形成会聚型的10），与外部壳体（32）形成外部环形管道（28）和具有内部壳体（34）的内部环形管道，该扩散器包括部分地封闭外部环形管道的整流罩。 更具体地，整流罩定位成朝向燃烧室的封闭端。
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8.发明申请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混合物的设备，以及提供给这些设备的燃烧室和涡轮机公开(公告)号：US20080178597A1
公开(公告)日：2008-07-31
申请号：US11768556
申请日：2007-06-26
IPC分类号： F23R3/14
CPC分类号： F23R3/14 , Y02T50/675
摘要： The invention relates to the field of turbomachines and concerns a device (20a, 20b) for injecting a mixture of air and fuel into a combustion chamber (4) of a turbomachine (1). It relates more specifically to an injection device (20b) provided with a novel sliding bushing (30b) and with a novel annular cup (50b) for retaining the sliding bushing, making it possible to improve the air feed of the injection device.
摘要翻译： 本发明涉及涡轮机领域，涉及用于将空气和燃料的混合物喷射到涡轮机（1）的燃烧室（4）中的装置（20a，20b）。 更具体地说，涉及一种具有新型滑动套管（30b）的注射装置（20b）和用于保持滑动衬套的新型环形杯（50b），从而可以改善注射装置的空气供给 。
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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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