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公开(公告)号：US06530227B1
公开(公告)日：2003-03-11
申请号：US09844411
申请日：2001-04-27
IPC分类号： F23R304
摘要： A one-piece deflector-flare cone assembly for a gas turbine engine combustor that facilitates extending a useful life of the combustor in a cost-effective and reliable manner is described. The one-piece assembly includes a deflector portion and a flare cone portion. The deflector portion includes an integral opening that extends through the deflector portion for receiving cooling fluid therein. The cooling opening extends circumferentially within the deflector portion. Cooling fluid discharged from the cooling opening is used for impingement cooling a portion of the flare cone portion to facilitate reducing an operating temperature and extending a useful life of the combustor.
摘要翻译： 描述了一种用于燃气涡轮发动机燃烧器的单件式偏转器 - 火炬锥形组件，其有助于以成本有效和可靠的方式延长燃烧器的使用寿命。 一体式组件包括偏转器部分和扩口锥部分。 偏转器部分包括延伸穿过偏转器部分的整体开口，用于在其中接收冷却流体。 冷却开口在偏转器部分内周向延伸。 从冷却开口排出的冷却流体用于冲击冷却火炬锥形部分的一部分，以便于降低工作温度并延长燃烧器的使用寿命。
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公开(公告)号：US06546732B1
公开(公告)日：2003-04-15
申请号：US09844205
申请日：2001-04-27
IPC分类号： F23R306
CPC分类号： F23D14/78 , F23R3/14 , F23R3/286 , F23R2900/03042
摘要： A one-piece deflector-flare cone assembly for a gas turbine engine combustor that facilitates extending a useful life of the combustor in a cost-effective and reliable manner is described. The one-piece assembly includes a deflector portion and a flare cone portion. The deflector portion includes an integral opening that extends through the deflector portion for receiving cooling fluid therein. The cooling opening extends circumferentially within the deflector portion. Cooling fluid discharged from the cooling opening is used for film cooling a portion of the deflector portion to facilitate reducing an operating temperature and extending a useful life of the combustor.
摘要翻译： 描述了一种用于燃气涡轮发动机燃烧器的单件式偏转器 - 火炬锥形组件，其有助于以成本有效和可靠的方式延长燃烧器的使用寿命。 一体式组件包括偏转器部分和扩口锥部分。 偏转器部分包括延伸穿过偏转器部分的整体开口，用于在其中接收冷却流体。 冷却开口在偏转器部分内周向延伸。 从冷却开口排出的冷却流体用于薄膜冷却偏转器部分的一部分，以便于降低工作温度并延长燃烧器的使用寿命。
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3.发明授权公开(公告)号：US07222488B2
公开(公告)日：2007-05-29
申请号：US10238542
申请日：2002-09-10
CPC分类号： F23R3/10 , F23R3/50 , F23R2900/00005 , F23R2900/00017 , F23R2900/00018 , Y02T50/675
摘要： A fabricated cowl for a double annular combustor of a gas turbine engine having a longitudinal axis extending therethrough, including an outer annular portion, an inner annular portion, and a middle annular portion. A plurality of circumferentially spaced radial slots are formed in at least one of the annular portions. The outer annular portion includes a plurality of circumferentially spaced windows of desired size formed therein, wherein a plurality of outer radial members connecting the outer annular portion and the middle annular portion are provided between adjacent windows therein. Similarly, the inner annular portion includes a plurality of circumferentially spaced windows of desired size formed therein, wherein a plurality of inner radial members connecting the inner annular portion and the middle annular portion are provided between adjacent windows therein. The cowl further includes a plurality of circumferentially spaced stiffening ribs, where each stiffening rib includes: a middle portion including a rear edge configured to substantially conform to a forward surface of the middle annular portion so that an area extending between the forward and rear edges is upstream of the middle annular portion; an outer portion including a forward edge configured to conform to a rear surface of the outer annular portion; and, an inner portion including a forward edge configured to conform to a rear surface of inner annular portion. The middle rib portion further includes a forward edge configured to extend through the radial slots when positioned in the middle annular portion, whereas the inner and outer rib portions further include a rear edge configured to extend through the radial slots when positioned in the inner and outer annular portions. Each stiffening rib is then connected to the inner, outer and middle annular portions.
摘要翻译： 一种用于燃气涡轮发动机的双环形燃烧器的制造罩，其具有延伸穿过其中的纵向轴线，包括外部环形部分，内部环形部分和中间环形部分。 多个周向间隔开的径向槽形成在至少一个环形部分中。 外环形部分包括形成在其中的多个周向隔开的所需尺寸的窗口，其中连接外环形部分和中间环形部分的多个外径向构件设置在其中的相邻窗口之间。 类似地，内部环形部分包括形成在其中的多个周向间隔开的所需尺寸的窗口，其中连接内部环形部分和中间环形部分的多个内径向构件设置在其中的相邻窗口之间。 整流罩还包括多个周向间隔开的加强肋，其中每个加强肋包括：中间部分，其包括后边缘，该后边缘构造成基本上与中间环形部分的前表面相符，使得在前边缘和后边缘之间延伸的区域是 在中间环形部分的上游; 外部，包括构造成符合所述外环形部分的后表面的前边缘; 以及内部部分，其包括构造成符合内环形部分的后表面的前边缘。 中间肋部分还包括一个前边缘，其构造成当定位在中间环形部分中时延伸穿过径向狭槽，而内部和外侧肋部分还包括后部边缘，该后部边缘被配置为当定位在内部和外侧时延伸穿过径向槽 环形部分。 然后将每个加强肋连接到内，外和中间环形部分。
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公开(公告)号：US06932093B2
公开(公告)日：2005-08-23
申请号：US10372889
申请日：2003-02-24
CPC分类号： F23D11/386 , F23D2206/10
摘要： A method facilitates washing a gas turbine engine combustor. The method comprises coupling a nozzle assembly against the combustor, wherein the nozzle assembly includes an inlet end, a discharge end, a hollow nozzle body extending therebetween, and a centerbody positioned within the nozzle body, coupling the nozzle assembly to a fluid source, and discharging an annulus of fluid from the nozzle assembly into the combustor to facilitate removing particulate matter from the combustor.
摘要翻译： 一种方法便于清洗燃气涡轮发动机燃烧器。 该方法包括将喷嘴组件联接到燃烧器上，其中喷嘴组件包括入口端，排放端，在其间延伸的中空喷嘴体和位于喷嘴体内的中心体，将喷嘴组件联接到流体源，以及 将流体的环从喷嘴组件排放到燃烧器中以便于从燃烧器中去除颗粒物质。
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公开(公告)号：US07669422B2
公开(公告)日：2010-03-02
申请号：US11460114
申请日：2006-07-26
IPC分类号： F23R3/06
CPC分类号： F23R3/06 , F23R2900/03042 , Y02T50/675 , Y10T29/4932
摘要： A combustor liner includes a liner having an upstream end and a downstream end having a longitudinal axis extending therethrough, and a plurality of cooling holes formed in the liner, the cooling holes are arranged along the longitudinal axis into a plurality of circumferentially extending rows that are variably spaced apart along the longitudinal axis.
摘要翻译： 燃烧器衬套包括具有上游端和具有延伸穿过其中的纵向轴线的下游端的衬套和形成在衬套中的多个冷却孔，所述冷却孔沿着纵向轴线布置成多个周向延伸的行， 沿着纵轴可变地间隔开。
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公开(公告)号：US20100011773A1
公开(公告)日：2010-01-21
申请号：US11460114
申请日：2006-07-26
CPC分类号： F23R3/06 , F23R2900/03042 , Y02T50/675 , Y10T29/4932
摘要： A combustor liner includes a liner having an upstream end and a downstream end having a longitudinal axis extending therethrough, and a plurality of cooling holes formed in the liner, the cooling holes are arranged along the longitudinal axis into a plurality of circumferentially extending rows that are variably spaced apart along the longitudinal axis.
摘要翻译： 燃烧器衬套包括具有上游端和具有延伸穿过其中的纵向轴线的下游端的衬套和形成在衬套中的多个冷却孔，冷却孔沿着纵向轴线布置成多个周向延伸的行， 沿着纵轴可变地间隔开。
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公开(公告)号：US07546739B2
公开(公告)日：2009-06-16
申请号：US11174746
申请日：2005-07-05
CPC分类号： F23R3/06 , F23D2207/00 , F23D2900/00014 , F23R2900/00005 , F23R2900/03044
摘要： An igniter tube assembly includes an axis of symmetry extending therethrough, an igniter tube that includes a first opening extending coaxially therethrough having a diameter sized to receive a portion of the igniter therethrough such that the igniter tube circumscribes the igniter and such that a gap is defined between the igniter tube and the igniter, a ferrule coupled to the igniter tube, and a plurality of cooling air openings extending through at least one of the igniter tube and the ferrule to facilitate channeling cooling air into the gap.
摘要翻译： 点火管组件包括延伸穿过其中的对称轴线，点火器管包括同轴地延伸穿过其中的第一开口，该第一开口具有尺寸设定成接收点火器的一部分的直径，使得点火器管限定点火器并且使得定义了间隙 在点火器管和点火器之间，耦合到点火器管的套圈和延伸穿过点火器管和套圈中的至少一个的多个冷却空气开口，以便于将冷却空气引导到间隙中。
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8.发明授权Advanced optics and optical access for laser ignition for gas turbines including aircraft engines 有权用于包括飞机发动机在内的燃气轮机的激光点火的先进光学和光学接入公开(公告)号：US08616006B2
公开(公告)日：2013-12-31
申请号：US12956207
申请日：2010-11-30
申请人： Sara Rocci Denis , Herbert Kopecek , Richard Wade Stickles , Chukwueloka Obiora Umeh , Gabor Ast , Mark Patrick Kelsey , Steven Clayton Vise , Gary Lee Leonard , Shai Birmaher
发明人： Sara Rocci Denis , Herbert Kopecek , Richard Wade Stickles , Chukwueloka Obiora Umeh , Gabor Ast , Mark Patrick Kelsey , Steven Clayton Vise , Gary Lee Leonard , Shai Birmaher
CPC分类号： F02P23/04 , F02C7/24 , F02C7/26 , F02C7/264 , F02C7/266 , F02D41/22 , F02P7/02 , F02P15/003 , F02P15/006 , F02P15/08 , F23R2900/00006
摘要： A laser ignition system for an internal combustion engine, and more specifically a gas turbine engine, is provided. The system including a laser light source configured to generate a laser beam, an ignition port configured to provide optimized optical access of the laser beam to a combustion chamber and an optical beam guidance component disposed between the laser light source and the ignition port. The optical beam guidance component is configured to include optimized optic components to transmit the laser beam to irradiate on a fuel mixture supplied into the combustion chamber to generate a combustor flame in a flame region. A method for igniting a fuel mixture in an internal combustion engine is also presented.
摘要翻译： 提供了一种用于内燃机，特别是燃气涡轮发动机的激光点火系统。 所述系统包括被配置为产生激光束的激光光源，被配置为提供激光束到燃烧室的优化光学访问的点火端口和设置在激光光源和点火端口之间的光束引导部件。 光束引导部件被配置为包括优化的光学部件以透射激光束以照射供应到燃烧室中的燃料混合物以在火焰区域中产生燃烧器火焰。 还提出了一种用于点燃内燃机中的燃料混合物的方法。
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9.发明申请Advanced Optics and Optical Access for Laser Ignition for Gas Turbines Including Aircraft Engines 有权用于包括飞机发动机在内的燃气轮机的激光点火的先进光学和光学接入公开(公告)号：US20120131927A1
公开(公告)日：2012-05-31
申请号：US12956207
申请日：2010-11-30
申请人： Sara Rocci Denis , Herbert Kopecek , Richard Wade Stickles , Chukwueloka Obiora Umeh , Gabor Ast , Mark Patrick Kelsey , Steven Clayton Vise , Gary Lee Leonard , Shai Birmaher
发明人： Sara Rocci Denis , Herbert Kopecek , Richard Wade Stickles , Chukwueloka Obiora Umeh , Gabor Ast , Mark Patrick Kelsey , Steven Clayton Vise , Gary Lee Leonard , Shai Birmaher
IPC分类号： F02C7/264
CPC分类号： F02P23/04 , F02C7/24 , F02C7/26 , F02C7/264 , F02C7/266 , F02D41/22 , F02P7/02 , F02P15/003 , F02P15/006 , F02P15/08 , F23R2900/00006
摘要： A laser ignition system for an internal combustion engine, and more specifically a gas turbine engine, is provided. The system including a laser light source configured to generate a laser beam, an ignition port configured to provide optimized optical access of the laser beam to a combustion chamber and an optical beam guidance component disposed between the laser light source and the ignition port. The optical beam guidance component is configured to include optimized optic components to transmit the laser beam to irradiate on a fuel mixture supplied into the combustion chamber to generate a combustor flame in a flame region. A method for igniting a fuel mixture in an internal combustion engine is also presented.
摘要翻译： 提供了一种用于内燃机，特别是燃气涡轮发动机的激光点火系统。 所述系统包括被配置为产生激光束的激光光源，被配置为提供激光束到燃烧室的优化光学访问的点火端口和设置在激光光源和点火端口之间的光束引导部件。 光束引导部件被配置为包括优化的光学部件以透射激光束以照射供应到燃烧室中的燃料混合物以在火焰区域中产生燃烧器火焰。 还提出了一种用于点燃内燃机中的燃料混合物的方法。
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公开(公告)号：US06557350B2
公开(公告)日：2003-05-06
申请号：US09859611
申请日：2001-05-17
申请人： Gilbert Farmer , Ella Christine Kutter , Steven Clayton Vise , John Robert Staker , Marwan Al-Roub , Tariq Kay Harris
发明人： Gilbert Farmer , Ella Christine Kutter , Steven Clayton Vise , John Robert Staker , Marwan Al-Roub , Tariq Kay Harris
IPC分类号： F02C722
CPC分类号： F23R3/50 , F23R3/283 , F23R2900/00012 , F23R2900/03044
摘要： A combustor for a gas turbine engine includes a plurality of igniter tubes that facilitate reducing temperature gradients within the combustor in a cost effective and reliable manner. The combustor includes an annular outer liner that includes a plurality of openings sized to receive igniter tubes. Each igniter tube maintains an alignment of each igniter received therein, and includes an air impingement device that extends radially outward from the igniter tube. During operation, airflow contacting the air impingement device is channeled radially inward for impingement cooling of the igniter tubes and the combustor outer liner.
摘要翻译： 用于燃气涡轮发动机的燃烧器包括多个点火器管，其以成本有效和可靠的方式有助于降低燃烧器内的温度梯度。 燃烧器包括环形外衬套，其包括多个开口，其尺寸设置成接收点火器管。 每个点火器管保持接收在其中的每个点火器的对准，并且包括从点火器管径向向外延伸的空气冲击装置。 在操作期间，接触空气冲击装置的气流径向向内引导，用于点火器管和燃烧器外衬套的冲击冷却。
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