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61. 发明授权

US07225623B2 Trapped vortex cavity afterburner 有权
标题翻译：被困涡流腔后燃器
公开(公告)号：US07225623B2
公开(公告)日：2007-06-05
申请号：US11209918
申请日：2005-08-23
申请人： John Michael Koshoffer
发明人： John Michael Koshoffer
IPC分类号： F02K3/10 , F23R3/18
CPC分类号： F23R3/20
摘要： A trapped vortex cavity afterburner includes one or more trapped vortex cavity stages for injecting a fuel/air mixture into a combustion zone. The trapped vortex cavity afterburner is operable to provide all thrust augmenting fuel used for engine thrust augmentation. Each stage has at least one annular trapped vortex cavity. The trapped vortex cavity afterburner may be a multi-stage afterburner having two or more trapped vortex cavity stages ganged for simultaneous ignition or operable for sequential ignition. One embodiment of the annular trapped vortex cavity is operable to raise a temperature of an exhaust gas flow through the afterburner about 100 to 200 degrees Fahrenheit. Each of the trapped vortex cavity stages may be operable to produce a single or a different amount of temperature rise of the exhaust gas flow through the afterburner. A chevron shaped trapped vortex cavity and having zig-zag shaped leading and trailing edges may be used.
摘要翻译：被捕获的涡流腔加力器包括用于将燃料/空气混合物喷射到燃烧区中的一个或多个捕获涡流空腔级。被捕获的涡流腔加力器可操作以提供用于发动机推力增加的所有推力增加燃料。每个阶段具有至少一个环形捕获的涡流腔。被捕获的涡流腔加力器可以是具有两个或更多个被捕获的涡流腔段的多级加燃器，其组合用于同时点燃或可操作用于顺序点火。环形捕获的涡流腔的一个实施例可操作以使废气流通过加力燃烧器的温度升高约100至200华氏度。每个被捕获的涡流腔段可操作以产生通过加力燃烧器的废气流的单一或不同量的温度上升。可以使用具有锯齿状的前缘和后缘的V形截面的涡流腔。

62. 发明授权

US07143583B2 Gas turbine combustor, combustion method of the gas turbine combustor, and method of remodeling a gas turbine combustor 有权
标题翻译：燃气轮机燃烧器，燃气轮机燃烧器的燃烧方法，燃气轮机燃烧器的重构方法
公开(公告)号：US07143583B2
公开(公告)日：2006-12-05
申请号：US10382500
申请日：2003-03-07
申请人： Akinori Hayashi , Shinichi Inage , Hiromi Koizumi , Isao Takehara , Kazuyuki Ito , Toshifumi Sasao , Hidetaro Murata
发明人： Akinori Hayashi , Shinichi Inage , Hiromi Koizumi , Isao Takehara , Kazuyuki Ito , Toshifumi Sasao , Hidetaro Murata
IPC分类号： F02C3/00 , F23R3/18
CPC分类号： F23R3/36 , F23R3/18 , F23R3/286 , F23R3/343
摘要： A gas turbine combustor comprises a premixed combustion burner disposed on the periphery of a pilot burner, an approximately cylindrical combustor liner disposed on the downstream side of the premixed combustion burner, which defines a combustion chamber in the liner. The gas turbine combustor is characterized by further comprising flame stabilizers radially disposed at the exit of the premixed combustion burner, and a fuel injection means with which the pilot burner is provided injects at least one of gas fuel and liquid fuel, in which a plurality of air nozzles are provided which are located outside the pilot burner and inside the premixed combustion burner, and which spout out air into the combustion chamber. Adequate combustion can be accomplished with a combustor which is capable of using gas fuel and liquid fuel, and at the same time, NOx can be reduced.
摘要翻译：燃气轮机燃烧器包括设置在引燃燃烧器的周边上的预混合燃烧器，设置在预混合燃烧器的下游侧的近似圆柱形的燃烧器衬套，其限定衬套中的燃烧室。燃气轮机燃烧器的特征在于还包括径向设置在预混合燃烧器的出口处的火焰稳定器，以及燃料喷射装置，其中提供引燃燃烧器喷射气体燃料和液体燃料中的至少一种，其中多个设置有位于引燃燃烧器外部和预混燃烧器内部的空气喷嘴，并且将空气喷射到燃烧室中。能够使用能够使用气体燃料和液体燃料的燃烧器来实现充分的燃烧，并且同时可以减少NOx。

63. 发明授权

US06976361B1 Ventilation channels in an afterburner chamber confluence sheet 有权
标题翻译：后燃室合流管通风通道
公开(公告)号：US06976361B1
公开(公告)日：2005-12-20
申请号：US10872510
申请日：2004-06-22
申请人： Thierry Cortes , Alain Page , Sébastien Baboeuf , Jacques Roche
发明人： Thierry Cortes , Alain Page , Sébastien Baboeuf , Jacques Roche
IPC分类号： F01D25/12 , F01D25/24 , F01D25/30 , F02C7/00 , F02C7/18 , F02K1/28 , F02K1/38 , F02K1/82 , F02K3/00 , F02K3/10 , F23R3/18 , F23R3/42
CPC分类号： F02K1/386 , F02K1/822 , F02K3/10 , Y02T50/675
摘要： The invention relates to ventilating the confluence sheet of an afterburner chamber of an aviation turbomachine, including, upstream from the afterburner chamber: a diffuser defined by a confluence sheet disposed inside a casing, said casing and said confluence sheet defining between them an annular channel for a cold secondary flow, upstream fuel injectors being disposed at the inlet to said diffuser and flame-catchers being disposed downstream from said upstream injectors, said confluence sheet presenting, between the radial plane containing said upstream injectors and the radial plane situated at the rear ends of said flame-catchers two bends so as to flare downstream in order to slow down the primary flow F1 downstream from said upstream injectors. An annular scoop is provided around the upstream portion of said confluence sheet in order to extract a flow of air from the cold flow, said extracted flow being injected tangentially into the primary flow via a plurality of channels formed in the wall of said confluence sheet between the scoop and said diffuser.
摘要翻译：本发明涉及对航空涡轮机的后燃室的汇流板进行通风，包括在后燃室的上游：由设置在壳体内的汇流板限定的扩散器，所述壳体和所述汇流板在它们之间限定环形通道，冷次级流，上游燃料喷射器设置在所述扩散器的入口处，并且火焰捕获器设置在所述上游喷射器的下游，所述汇合片在包含所述上游喷射器的径向平面和位于后端的径向平面之间呈现的所述火焰捕集器两个弯曲，以便向下游扩张，以便减缓所述上游喷射器下游的主流F 1。围绕所述汇合片的上游部分设置环形勺以便从冷流中提取空气流，所述提取的流通过形成在所述汇合片的壁上的多个通道切向地注入主流中，勺子和扩散器。

64. 发明申请

US20050274114A1 VENTILATION CHANNELS IN AN AFTERBURNER CHAMBER CONFLUENCE SHEET 有权
标题翻译：燃烧室反应堆中的通风通道
公开(公告)号：US20050274114A1
公开(公告)日：2005-12-15
申请号：US10872510
申请日：2004-06-22
申请人： Thierry Cortes , Alain Page , Sebastien Baboeuf , Jacques Roche
发明人： Thierry Cortes , Alain Page , Sebastien Baboeuf , Jacques Roche
IPC分类号： F01D25/12 , F01D25/24 , F01D25/30 , F02C7/00 , F02C7/18 , F02K1/28 , F02K1/38 , F02K1/82 , F02K3/00 , F02K3/10 , F23R3/18 , F23R3/42
CPC分类号： F02K1/386 , F02K1/822 , F02K3/10 , Y02T50/675
摘要： The invention relates to ventilating the confluence sheet of an afterburner chamber of an aviation turbomachine, including, upstream from the afterburner chamber: a diffuser defined by a confluence sheet disposed inside a casing, said casing and said confluence sheet defining between them an annular channel for a cold secondary flow, upstream fuel injectors being disposed at the inlet to said diffuser and flame-catchers being disposed downstream from said upstream injectors, said confluence sheet presenting, between the radial plane containing said upstream injectors and the radial plane situated at the rear ends of said flame-catchers two bends so as to flare downstream in order to slow down the primary flow F1 downstream from said upstream injectors. An annular scoop is provided around the upstream portion of said confluence sheet in order to extract a flow of air from the cold flow, said extracted flow being injected tangentially into the primary flow via a plurality of channels formed in the wall of said confluence sheet between the scoop and said diffuser.
摘要翻译：本发明涉及对航空涡轮机的后燃室的汇流板进行通风，包括在后燃室的上游：由设置在壳体内的汇流板限定的扩散器，所述壳体和所述汇流板在它们之间限定环形通道，冷次级流，上游燃料喷射器设置在所述扩散器的入口处，并且火焰捕获器设置在所述上游喷射器的下游，所述汇合片在包含所述上游喷射器的径向平面和位于后端的径向平面之间呈现的所述火焰捕集器两个弯曲，以便向下游扩张，以便减缓所述上游喷射器下游的主流F 1。围绕所述汇流板的上游部分设置环形勺，以便从冷流中提取空气流，所述提取的流通过形成在所述汇流板的壁中的多个通道切向地注入主流，勺子和扩散器。

65. 发明申请

US20050235648A1 Orbiting combustion nozzle engine 失效
标题翻译：轨道燃烧喷嘴发动机
公开(公告)号：US20050235648A1
公开(公告)日：2005-10-27
申请号：US10518767
申请日：2003-05-26
申请人： David Lior
发明人： David Lior
IPC分类号： F23R3/52 , F02B20060101 , F02C3/14 , F02C3/16 , F02C3/34 , F02C7/12 , F02C7/18 , F23R3/06 , F23R3/18 , F23R3/28 , F23R3/56
CPC分类号： F23R3/50 , F02C3/16 , F02C7/12 , F23R3/38 , F23R3/56 , Y02T50/675
摘要： An orbiting combustor nozzle (OCN) engine, having a rotating assembly comprising a co-rotating compressor and nozzle wheel enclosed within a non-rotating outer casing, defining a rotating combustion chamber, is disclosed. Combustion occurs in the combustion chamber in a vortex of gas that rotates at the same angular velocity as the rotating assembly. Also disclosed, is a method of cooling a blade of a rotating wheel, such as a turbine wheel or nozzle wheel, by projecting cool air at the base of the vane form a nozzle corotating with the blade. Such cooling is easily implemented in an OCN engine with use of an innovative annular combustor. Also disclosed is a method of countering axial backflow by use of a combustion chamber compressor.
摘要翻译：公开了一种旋转燃烧器喷嘴（OCN）发动机，其具有旋转组件，其包括旋转式压缩机和封闭在非旋转外壳内的喷嘴轮，其限定旋转燃烧室。燃烧在燃烧室中以与旋转组件相同的角速度旋转的气体涡流中发生。还公开了通过在叶片的基部处突出形成与刀片共旋转的喷嘴的冷空气来冷却诸如涡轮机轮或喷嘴轮的旋转轮的叶片的方法。这种冷却可以通过使用创新的环形燃烧器在OCN发动机中容易地实现。还公开了一种通过使用燃烧室压缩机来抵抗轴向回流的方法。

66. 发明授权

US06918256B2 Method for the reduction of combustion-driven oscillations in combustion systems and premixing burner for carrying out the method 有权
标题翻译：减少燃烧系统燃烧驱动振荡的方法和实施该方法的预混燃烧器
公开(公告)号：US06918256B2
公开(公告)日：2005-07-19
申请号：US10358312
申请日：2003-02-05
申请人： Ephraim Gutmark , Christian Oliver Paschereit
发明人： Ephraim Gutmark , Christian Oliver Paschereit
IPC分类号： F23R3/18 , F23C7/00 , F23D11/40 , F23D14/74 , F23D17/00 , F23R3/12 , F23R3/28 , F23R3/30
CPC分类号： F23R3/286 , F23C7/002 , F23C2900/07002 , F23D11/402 , F23D14/74 , F23D17/002 , F23D2210/00 , F23R2900/00014
摘要： A method and a device are described for the controlled damping of combustion-driven oscillations in a turbomachine with a burner system providing at least one burner, into which is introduced, via at least one burner nozzle arranged centrally in the burner, fuel which is intermixed with combustion inflow air flowing into the burner, to form a fuel/air mixture which is ignited in a combustion chamber following the burner system. The invention is distinguished in that the fuel nozzle is designed in the form of a burner lance, at the lance end of which fuel discharge into the burner takes place, and in that the burner lance projects into the burner in the amount of at least one third of the axial burner length.
摘要翻译：描述了一种方法和装置，用于在具有提供至少一个燃烧器的燃烧器系统的涡轮机中被控制的阻尼的阻尼，所述燃烧器系统经由布置在燃烧器中心的至少一个燃烧器喷嘴引入燃烧器中，所述燃烧器喷嘴被混合燃烧流入的空气流入燃烧器，以形成在燃烧器系统之后的燃烧室中点燃的燃料/空气混合物。本发明的区别在于，燃料喷嘴被设计成燃烧器喷枪的形式，其喷枪的喷枪端部进入燃烧器，并且燃烧器喷枪以至少一个量的量投射到燃烧器中轴向燃烧器长度的三分之一。

67. 发明申请

US20050081527A1 Methods and apparatus for film cooling gas turbine engine combustors 失效
标题翻译：用于薄膜冷却燃气涡轮发动机燃烧器的方法和装置
公开(公告)号：US20050081527A1
公开(公告)日：2005-04-21
申请号：US10688526
申请日：2003-10-17
申请人： Stephen Howell , John Jacobson , Timothy McCaffrey , Barry Barnes
发明人： Stephen Howell , John Jacobson , Timothy McCaffrey , Barry Barnes
IPC分类号： F23L15/04 , F23R3/04 , F23R3/10 , F23R3/18 , F23R3/42
CPC分类号： F23R3/10 , F23L15/04 , F23R3/04 , F23R2900/00017 , F23R2900/03042 , Y02E20/348
摘要： A method facilitates assembling a combustor for a gas turbine engine. The method includes providing a dome assembly that includes at least one cooling slot lip and at least one filler projection, wherein a gap defined between the cooling slot lip and the at least one filler projection has a height defined between cooling slot lip and the at least one filler projection that is substantially uniform through the gap. The method also includes coupling a liner assembly to the dome assembly, such that a combustion chamber is defined by the liner assembly, and coupling an inner and an outer support to the dome assembly, such that the dome assembly extends between the inner and outer supports.
摘要翻译：一种方法有利于组装用于燃气涡轮发动机的燃烧器。该方法包括提供包括至少一个冷却槽唇缘和至少一个填料突起的圆顶组件，其中限定在冷却槽唇缘和至少一个填充物突起之间的间隙具有限定在冷却槽唇缘与至少一个通过间隙基本均匀的填料突起。该方法还包括将衬套组件连接到圆顶组件，使得燃烧室由衬套组件限定，并且将内部和外部支撑件联接到圆顶组件，使得圆顶组件在内部和外部支撑件之间延伸。

68. 发明授权

US5660045A Gas turbine combustor and gas turbine 失效
标题翻译：燃气轮机燃气轮机和燃气轮机
公开(公告)号：US5660045A
公开(公告)日：1997-08-26
申请号：US502461
申请日：1995-07-14
申请人： Kazuyuki Ito , Tadayoshi Murakami , Nariyoshi Kobayashi , Shigeru Azuhata , Yoshikazu Moritomo
发明人： Kazuyuki Ito , Tadayoshi Murakami , Nariyoshi Kobayashi , Shigeru Azuhata , Yoshikazu Moritomo
IPC分类号： F02C9/28 , F23D14/02 , F23D23/00 , F23R3/12 , F23R3/16 , F23R3/18 , F23R3/28 , F23R3/30 , F23R3/34 , F23R3/46 , F02C1/00
CPC分类号： F23D23/00 , F23R3/346 , F23D2900/00008
摘要： The present invention has an object to provide a gas turbine combustor which is able to effect stable combustion in a wide range of fuel flow rate. A burner 1 is provided with fuel nozzles 31 and 32. When a fuel flow rate is small, diffusion flame is formed with fuel supplied from the nozzle 31 with a ring-shaped flame stabilizer 11. Next, fuel is supplied from the nozzle 32 to mix with air, reach to the flame stabilizer 11 and be held by the diffusion flame already formed, whereby stable premixed flames are formed in the flame stabilizer 11 from a range of low fuel air ratio. Further, when flame is propagated from the burner 1 to the burner 2, a fuel air ratio at the outer periphery side of the burner 1 is locally raised by the fuel supplied from the nozzle 31, whereby the combustion stability can be raised in a wide range of fuel flow rate and propagation of flame to adjacent burners becomes easy.
摘要翻译：本发明的目的是提供一种能够在宽范围的燃料流量下实现稳定燃烧的燃气轮机燃烧器。燃烧器1设置有燃料喷嘴31和32.当燃料流量较小时，由具有环形火焰稳定器11的喷嘴31供应的燃料形成扩散火焰。接下来，从喷嘴32供给燃料与空气混合，到达火焰稳定器11并被已经形成的扩散火焰保持，从而在低燃料空气比范围内在火焰稳定器11中形成稳定的预混火焰。此外，当火焰从燃烧器1传播到燃烧器2时，燃烧器1的外周侧的燃料空气比通过从喷嘴31供给的燃料局部地升高，从而可以在宽的范围内提高燃烧稳定性燃料流量范围和火焰传播到相邻燃烧器变得容易。

69. 发明授权

US5628181A Flashback system 失效
标题翻译：闪回系统
公开(公告)号：US5628181A
公开(公告)日：1997-05-13
申请号：US485853
申请日：1995-06-07
申请人： Gilbert O. Kraemer
发明人： Gilbert O. Kraemer
IPC分类号： F23R3/16 , F02B77/10 , F02M29/04 , F23D14/82 , F23R3/18 , F23R3/28 , F23R3/30 , F02G3/00
CPC分类号： F23R3/18 , F02B77/10 , F02M29/04 , F23D14/82 , F23R3/286
摘要： Flashback of flames in premixed combustion systems is avoided by passing premixed fuel and air prior to combustion through a series of two or more close coupled nonaligned multi-channel monoliths.
摘要翻译：在燃烧前通过一系列两个或更多个紧密耦合的非对准多通道整流体通过预混燃料和空气来避免预混合燃烧系统中的火焰的闪回。

70. 发明授权

US5617717A Flame stabilization system for aircraft jet engine augmentor using plasma plume ignitors 失效
标题翻译：使用等离子体羽流点火器的飞机喷气发动机增压器的火焰稳定系统
公开(公告)号：US5617717A
公开(公告)日：1997-04-08
申请号：US332053
申请日：1994-10-31
申请人： Joseph G. Asquith , William P. Peschel , Jacob L. Sperling
发明人： Joseph G. Asquith , William P. Peschel , Jacob L. Sperling
IPC分类号： F02C7/262 , F02C7/266 , F23R3/18 , H05H1/46 , F02K3/10
CPC分类号： F02C7/262 , F02C7/264 , F02C7/266 , F23R3/18 , H05H1/46 , F05D2270/092 , F05D2270/101
摘要： A flame stabilizing system for an augmentor, or a ramjet engine, which utilizes continuously operating microwave powered plasma plume igniters to generate a stable source of ignition for the flowing combustible mixture within the augmentor combustion chamber.
摘要翻译：一种用于增压器或冲压式喷气发动机的火焰稳定系统，其利用连续操作的微波动力等离子体羽流点火器来为增压器燃烧室内的流动可燃混合物产生稳定的点火源。

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