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1.发明申请COOLED HYBRID STRUCTURE FOR GAS TURBINE ENGINE AND METHOD FOR THE FABRICATION THEREOF 审中-公开用于气体涡轮发动机的冷却混合结构及其制造方法公开(公告)号：US20100272953A1
公开(公告)日：2010-10-28
申请号：US12431547
申请日：2009-04-28
申请人： Paul Yankowich , James Hadder
发明人： Paul Yankowich , James Hadder
CPC分类号： F23M5/085 , F23M2900/05004 , F23R3/007 , F23R3/06 , F23R2900/03041 , F23R2900/03044 , Y10T428/24331
摘要： A cooled hybrid structure is provided for deployment within a gas turbine engine. In one embodiment, the cooled hybrid structure includes a woven oxide fiber sheet and an insulative oxide coating. The woven oxide fiber sheet includes an outer cold wall and an inner hot wall, which is integrally woven with the outer cold wall and which cooperates therewith to define a plurality of elongated cooling channels extending within the woven oxide fiber sheet. A plurality of impingement apertures is formed through the outer cold wall and conducts airflow into the plurality of elongated cooling channels and against the inner hot wall to convectively cool the woven oxide fiber sheet. A plurality of effusion channels is formed through the inner hot wall and through the insulative oxide coating and conducts airflow through the insulative oxide coating to provide convective cooling thereof.
摘要翻译： 提供冷却的混合结构用于部署在燃气涡轮发动机内。 在一个实施方案中，冷却的混合结构包括氧化纤维织物片和绝缘氧化物涂层。 编织氧化物纤维片材包括外部冷壁和内部热壁，其与外部冷壁整体编织并与之配合，以限定在机织氧化物纤维片材内延伸的多个细长的冷却通道。 通过外部冷壁形成多个冲击孔，并将气流传导到多个细长的冷却通道中并抵靠内部热壁以对流地冷却机织氧化物纤维片材。 通过内部热壁和绝缘氧化物涂层形成多个渗出通道，并且通过绝缘氧化物涂层传导气流以提供其对流冷却。
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公开(公告)号：US20110120133A1
公开(公告)日：2011-05-26
申请号：US12623773
申请日：2009-11-23
IPC分类号： F23D14/46
CPC分类号： F23R3/002 , F23R2900/00012
摘要： A combustor for a turbine engine is provided. The combustor includes a first liner and a second liner forming a combustion chamber. The combustion chamber is configured to receive an air-fuel mixture for combustion therein and having a longitudinal axis that defines axial and radial directions. The first liner is a first dual walled liner having a first hot wall facing the combustion chamber and a first cold wall that forms a first liner cavity with the first hot wall, the first liner cavity having first and second ends. A first liner seal is configured to seal the second end of the first liner cavity and to accommodate relative movement of the first hot wall and first cold wall generally in the axial and radial directions.
摘要翻译： 提供了一种用于涡轮发动机的燃烧器。 燃烧器包括形成燃烧室的第一衬里和第二衬套。 燃烧室被配置为接收用于在其中燃烧的空气 - 燃料混合物并且具有限定轴向和径向方向的纵向轴线。 第一衬垫是具有面向燃烧室的第一热壁的第一双壁衬套和与第一热壁形成第一衬里腔的第一冷壁，第一衬里腔具有第一和第二端。 第一衬里密封件被配置为密封第一衬里腔的第二端并且容纳通常在轴向和径向方向上的第一热壁和第一冷壁的相对运动。
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公开(公告)号：US20110023495A1
公开(公告)日：2011-02-03
申请号：US12512816
申请日：2009-07-30
IPC分类号： F02C7/12
CPC分类号： F23R3/06 , F23R3/005 , F23R2900/03041 , F23R2900/03044 , Y02T50/675
摘要： A gas turbine engine combustor is provided. An inner liner has an upstream end and a downstream end and extends in an axial direction between the upstream and downstream ends. A dual wall outer liner has a hot wall, a cold wall at least partially surrounding the hot wall, an upstream end, and a downstream end. The outer liner extends in the axial direction between the upstream and downstream ends. A dome assembly is coupled between the upstream ends of the inner and outer liners to define a combustion chamber between the inner liner and the hot wall of the outer liner. Effusion cooling holes are disposed in the hot wall, including a first row disposed at a tangential angle of between about 70° and about 90° and a second row disposed at a tangential angle of between about 0° and about 20°.
摘要翻译： 提供燃气涡轮发动机燃烧器。 内衬具有上游端和下游端，并且在上游端和下游端之间沿轴向方向延伸。 双壁外衬套具有热壁，至少部分围绕热壁的冷壁，上游端和下游端。 外衬套在上游和下游端之间沿轴向方向延伸。 圆顶组件联接在内衬和外衬垫的上游端之间，以在内衬层和外衬套的热壁之间限定燃烧室。 排出冷却孔设置在热壁中，包括设置在约70°至约90°之间的切线角度的第一排和以大约0°至大约20°之间的切线角设置的第二排。
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公开(公告)号：US20060024528A1
公开(公告)日：2006-02-02
申请号：US10909026
申请日：2004-07-30
申请人： Thomas Strangman , Bjoern Schenk , Paul Yankowich
发明人： Thomas Strangman , Bjoern Schenk , Paul Yankowich
IPC分类号： B32B19/00
CPC分类号： C04B41/52 , C04B41/009 , C04B41/89 , Y10T428/12535 , Y10T428/12611 , Y10T428/249956 , C04B41/4582 , C04B41/5031 , C04B41/5035 , C04B41/522 , C04B41/5037 , C04B41/4527 , C04B41/5045 , C04B41/5024 , C04B41/5042 , C04B35/01 , C04B35/10 , C04B35/803
摘要： A layered structure includes a substrate comprising a layer of an oxide/oxide ceramic based composite material, a first oxide layer disposed directly on the substrate and formed from a material that has no greater than about 10% porosity and is substantially impermeable by water vapor, and a second oxide layer disposed directly on the first oxide layer and having a greater porosity than the first oxide layer. Either or both the first and second oxide layers of the coating system may be deposited using a plasma spraying process, a slurry deposition process which is followed by a sintering step, or an EB-PVD process.
摘要翻译： 分层结构包括：基底，其包括氧化物/氧化物陶瓷基复合材料层，直接设置在基底上并由不大于约10％孔隙率并且基本上不透水蒸气的材料形成的第一氧化物层， 以及直接设置在第一氧化物层上并且具有比第一氧化物层更大的孔隙率的第二氧化物层。 可以使用等离子喷涂工艺，浆料沉积工艺，其后是烧结步骤或EB-PVD工艺来沉积涂料体系的第一和第二氧化物层。
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公开(公告)号：US09897320B2
公开(公告)日：2018-02-20
申请号：US12512816
申请日：2009-07-30
IPC分类号： F23R3/06
CPC分类号： F23R3/06 , F23R3/005 , F23R2900/03041 , F23R2900/03044 , Y02T50/675
摘要： A gas turbine engine combustor is provided. An inner liner has an upstream end and a downstream end and extends in an axial direction between the upstream and downstream ends. A dual wall outer liner has a hot wall, a cold wall at least partially surrounding the hot wall, an upstream end, and a downstream end. The outer liner extends in the axial direction between the upstream and downstream ends. A dome assembly is coupled between the upstream ends of the inner and outer liners to define a combustion chamber between the inner liner and the hot wall of the outer liner. Effusion cooling holes are disposed in the hot wall, including a first row disposed at a tangential angle of between about 70° and about 90° and a second row disposed at a tangential angle of between about 0° and about 20°.
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公开(公告)号：US08726631B2
公开(公告)日：2014-05-20
申请号：US12623622
申请日：2009-11-23
CPC分类号： F23R3/60 , F02C7/264 , F05D2260/201 , F23R2900/00012 , Y02T50/671 , Y02T50/675
摘要： A combustor for a gas turbine engine includes an inner liner and an outer liner circumscribing the inner liner and forming a combustion chamber therewith. The outer liner is a dual walled liner with a first wall and a second wall. A fuel igniter includes a tip portion configured to ignite an air and fuel mixture in the combustion chamber. An igniter support assembly positions the fuel igniter relative to the combustion chamber. The igniter support assembly defines a plurality of holes configured to direct cooling air toward the tip portion of the fuel igniter. The igniter support assembly includes first and second floating seals that are configured to accommodate radial and axial relative movements.
摘要翻译： 用于燃气涡轮发动机的燃烧器包括内衬和限定内衬的外衬套，并与其形成燃烧室。 外衬套是具有第一壁和第二壁的双壁衬套。 燃料点火器包括被配置为点燃燃烧室中的空气和燃料混合物的末端部分。 点火器支撑组件相对于燃烧室定位燃料点火器。 点火器支撑组件限定了构造成将冷却空气朝向燃料点火器的尖端部分引导的多个孔。 点火器支撑组件包括构造成适应径向和轴向相对运动的第一和第二浮动密封件。
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公开(公告)号：US20050247065A1
公开(公告)日：2005-11-10
申请号：US10839116
申请日：2004-05-04
申请人： Rodolphe Dudebout , Terrel Kuhn , Paul Yankowich , Frank Zupanc
发明人： Rodolphe Dudebout , Terrel Kuhn , Paul Yankowich , Frank Zupanc
摘要： A premix chamber for a combustor of a gas turbine engine comprises a cylindrical chamber having a premix chamber wall, the cylindrical chamber having a chamber inlet end longitudinally separated from a chamber outlet end along a central axis, a chamber inlet plate in communication with the premix chamber wall at the chamber inlet end, the chamber inlet plate having a fuel nozzle inlet hole disposed through the chamber inlet plate, the chamber inlet plate further comprising a plurality of swirler passages disposed through the chamber inlet plate, and the chamber outlet end being open. A method of producing turbine gas is also disclosed.
摘要翻译： 用于燃气涡轮发动机的燃烧器的预混合室包括具有预混室壁的圆柱形腔室，该圆柱形腔室具有沿着中心轴线从室出口端纵向分离的室入口端，与预混合物连通的室入口板 腔室入口板具有设置在腔室入口板上的燃料喷嘴入口孔，腔室入口板还包括多个设置在腔室入口板上的旋流器通道，腔室出口端开口 。 还公开了一种生产涡轮机气体的方法。
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公开(公告)号：US09021812B2
公开(公告)日：2015-05-05
申请号：US13560876
申请日：2012-07-27
CPC分类号： F23R3/14 , F23R3/60 , Y02T50/675 , Y10T29/49323
摘要： A combustor dome and heat-shield assembly comprises a heat-shield having a first opening therethrough. A swirler extends through the first opening and captures the heat-shield. A dome having a second opening therethrough and has an upstream side and a downstream side. The swirler extends through the second opening from the downstream side to the upstream side to capture the heat-shield on the downstream side, and a retaining clip engages the swirler to secure the swirler and the heat-shield on the dome.
摘要翻译： 燃烧器穹顶和隔热罩组件包括具有穿过其中的第一开口的隔热罩。 旋流器延伸穿过第一开口并捕获隔热罩。 具有通过其的第二开口并具有上游侧和下游侧的圆顶。 旋流器从下游侧延伸到第二开口到上游侧，以在下游侧捕获隔热罩，并且保持夹与旋流器接合以将旋流器和隔热罩固定在圆顶上。
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9.发明申请System for coupling flow from a centrifugal compressor to an axial combustor for gas turbines 有权用于将来自离心压缩机的流动耦合到用于燃气轮机的轴向燃烧器的系统公开(公告)号：US20070113557A1
公开(公告)日：2007-05-24
申请号：US11286102
申请日：2005-11-22
IPC分类号： F02C7/00
摘要： A system is provided for aerodynamically coupling air flow from a centrifugal compressor to an axial combustor. The system includes a diffuser, a deswirl assembly, combustor inner and outer annular liners, a combustor dome, and a curved annular plate. The diffuser has an inlet that communicates with the centrifugal compressor, an outlet, and a flow path that extends radially outward. The deswirl assembly has an inlet that communicates with the diffuser outlet to receive air flowing in a radially outward direction, an outlet, and a flow path configured to redirect the air in a radially inward and axial direction through the deswirl assembly outlet at an angle toward a longitudinal axis. The curved annular plate is coupled to combustor inner and outer annular liner upstream ends to form a combustor subplenum therebetween and has a first opening and a second opening formed therein, the first opening aligned with the deswirl assembly outlet to receive air discharged therefrom.
摘要翻译： 提供了一种用于将来自离心式压缩机的空气动力耦合到轴向燃烧器的系统。 该系统包括扩散器，去沫组件，燃烧器内部和外部环形衬垫，燃烧器圆顶和弯曲的环形板。 扩散器具有与离心式压缩机，出口和径向向外延伸的流路连通的入口。 洗涤组件具有与扩散器出口连通的入口，以接收沿径向向外的方向流动的空气，出口和流路，其配置成沿着径向向内和轴向方向将空气以一定的角度朝向脱水组件出口 纵轴。 弯曲的环形板联接到燃烧器的内部和外部环形衬套上游端，以在它们之间形成燃烧器子板，并且具有形成在其中的第一开口和第二开口，第一开口与脱水组件出口对准以接收从其排出的空气。
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公开(公告)号：US20140026580A1
公开(公告)日：2014-01-30
申请号：US13560876
申请日：2012-07-27
IPC分类号： F23R3/14
CPC分类号： F23R3/14 , F23R3/60 , Y02T50/675 , Y10T29/49323
摘要： A combustor dome and heat-shield assembly comprises a heat-shield having a first opening therethrough. A swirler extends through the first opening and captures the heat-shield. A dome having a second opening therethrough and has an upstream side and a downstream side. The swirler extends through the second opening from the downstream side to the upstream side to capture the heat-shield on the downstream side, and a retaining clip engages the swirler to secure the swirler and the heat-shield on the dome.
摘要翻译： 燃烧器穹顶和隔热罩组件包括具有穿过其中的第一开口的隔热罩。 旋流器延伸穿过第一开口并捕获隔热罩。 具有第二开口的圆顶具有上游侧和下游侧。 旋流器从下游侧延伸到第二开口到上游侧，以在下游侧捕获隔热罩，并且保持夹与旋流器接合以将旋流器和隔热罩固定在圆顶上。
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