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公开(公告)号：US08534076B2
公开(公告)日：2013-09-17
申请号：US12481441
申请日：2009-06-09
CPC分类号： F01D9/023
摘要： A combustor-turbine seal interface is provided for deployment within a gas turbine engine. In one embodiment, the combustor-turbine assembly a combustor, a turbine nozzle downstream of the combustor, and a first compliant dual seal assembly. The first compliant dual seal assembly includes a compliant seal wall sealingly coupled between the combustor and the turbine nozzle, a first compression seal sealingly disposed between the compliant seal wall and the turbine nozzle, and a first bearing seal generally defined by the compliant seal wall and the turbine nozzle. The first bearing seal is sealingly disposed in series with the first compression seal.
摘要翻译： 提供燃烧器 - 涡轮机密封接口用于部署在燃气涡轮发动机内。 在一个实施例中，燃烧器 - 涡轮机组件，燃烧器，燃烧器下游的涡轮喷嘴和第一柔性双重密封组件。 第一柔性双密封组件包括密封地联接在燃烧器和涡轮喷嘴之间的顺应性密封壁，密封地设置在柔性密封壁和涡轮喷嘴之间的第一压缩密封件，以及通常由柔性密封壁和 涡轮喷嘴。 第一轴承密封件与第一压缩密封件密封地设置成串联。
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公开(公告)号：US20100307166A1
公开(公告)日：2010-12-09
申请号：US12481441
申请日：2009-06-09
CPC分类号： F01D9/023
摘要： A combustor-turbine seal interface is provided for deployment within a gas turbine engine. In one embodiment, the combustor-turbine assembly a combustor, a turbine nozzle downstream of the combustor, and a first compliant dual seal assembly. The first compliant dual seal assembly includes a compliant seal wall sealingly coupled between the combustor and the turbine nozzle, a first compression seal sealingly disposed between the compliant seal wall and the turbine nozzle, and a first bearing seal generally defined by the compliant seal wall and the turbine nozzle. The first bearing seal is sealingly disposed in series with the first compression seal.
摘要翻译： 提供燃烧器 - 涡轮机密封接口用于部署在燃气涡轮发动机内。 在一个实施例中，燃烧器 - 涡轮机组件，燃烧器，燃烧器下游的涡轮喷嘴和第一柔性双重密封组件。 第一柔性双密封组件包括密封地联接在燃烧器和涡轮喷嘴之间的顺应性密封壁，密封地设置在柔性密封壁和涡轮喷嘴之间的第一压缩密封件，以及通常由柔性密封壁和 涡轮喷嘴。 第一轴承密封件与第一压缩密封件密封地设置成串联。
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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：US09080770B2
公开(公告)日：2015-07-14
申请号：US13154208
申请日：2011-06-06
CPC分类号： F23R3/06 , F23R3/54 , F23R2900/03041 , Y02T50/675
摘要： A combustor for a gas turbine engine is provided. The combustor includes an inner liner; an outer liner circumscribing the inner liner; and a combustor dome having a first edge coupled to the inner liner and a second edge coupled to the outer liner. The combustor dome forms a combustion chamber with the inner liner and the outer liner. The combustion chamber receives air flow through the inner and outer liners, and the combustor dome is configured to bifurcate the air flow at the combustor dome into a first stream directed to the inner liner and a second stream directed to the outer liner.
摘要翻译： 提供了一种用于燃气涡轮发动机的燃烧器。 燃烧器包括内衬; 限定内衬的外衬套; 以及燃烧器穹顶，其具有联接到内衬套的第一边缘和联接到外衬套的第二边缘。 燃烧室顶部形成具有内衬和外衬的燃烧室。 燃烧室接收通过内衬和外衬层的空气流，并且燃烧器圆顶被构造成将燃烧室顶部处的空气流分叉为指向内衬的第一流和指向外衬套的第二流。
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5.发明申请公开(公告)号：US20060207095A1
公开(公告)日：2006-09-21
申请号：US10774230
申请日：2004-02-05
申请人： Terrel Kuhn , William Freeman , Francis Maszk , Douglas Freiberg , Kenneth Struzek , Lawrence Kobold
发明人： Terrel Kuhn , William Freeman , Francis Maszk , Douglas Freiberg , Kenneth Struzek , Lawrence Kobold
IPC分类号： B21D53/00
CPC分类号： F23R3/002 , F23R3/06 , F23R2900/03041 , Y02T50/67 , Y02T50/675 , Y10T29/49346 , Y10T29/49716 , Y10T29/49718 , Y10T29/4973 , Y10T29/49734
摘要： A method for controlling combustor liner carbon formation on repaired combustors includes making modular effusion panel subassemblies remote from the combustor liner; removing a non-effusion or damaged panel from the combustor liner; and replacing the non-effusion or damaged panel with the modular effusion panel.
摘要翻译： 一种用于在修理的燃烧器上控制燃烧器衬套碳形成的方法包括使模块化的排气面板组件远离燃烧器衬套; 从燃烧器衬套去除非渗出或损坏的板; 并用模块化积液板更换非渗出或损坏的面板。
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公开(公告)号：US20120304647A1
公开(公告)日：2012-12-06
申请号：US13154208
申请日：2011-06-06
CPC分类号： F23R3/06 , F23R3/54 , F23R2900/03041 , Y02T50/675
摘要： A combustor for a gas turbine engine is provided. The combustor includes an inner liner; an outer liner circumscribing the inner liner; and a combustor dome having a first edge coupled to the inner liner and a second edge coupled to the outer liner. The combustor dome forms a combustion chamber with the inner liner and the outer liner. The combustion chamber receives air flow through the inner and outer liners, and the combustor dome is configured to bifurcate the air flow at the combustor dome into a first stream directed to the inner liner and a second stream directed to the outer liner.
摘要翻译： 提供了一种用于燃气涡轮发动机的燃烧器。 燃烧器包括内衬; 限定内衬的外衬套; 以及燃烧器穹顶，其具有联接到内衬套的第一边缘和联接到外衬套的第二边缘。 燃烧室顶部形成具有内衬和外衬的燃烧室。 燃烧室接收通过内衬和外衬层的空气流，并且燃烧器圆顶被构造成将燃烧室顶部处的空气流分叉为指向内衬管的第一流和指向外衬套的第二流。
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