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1. 发明申请

US20110120133A1 DUAL WALLED COMBUSTORS WITH IMPROVED LINER SEALS 有权
标题翻译：具有改进的衬里密封件的双壁混凝土搅拌机
公开(公告)号：US20110120133A1
公开(公告)日：2011-05-26
申请号：US12623773
申请日：2009-11-23
申请人： Nagaraja S. Rudrapatna , Paul Yankowich , Amy Hanson
发明人： Nagaraja S. Rudrapatna , Paul Yankowich , Amy Hanson
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。

2. 发明授权

US08726631B2 Dual walled combustors with impingement cooled igniters 有权
标题翻译：具有冲击冷却点火器的双壁燃烧器
公开(公告)号：US08726631B2
公开(公告)日：2014-05-20
申请号：US12623622
申请日：2009-11-23
申请人： Nagaraja S. Rudrapatna , Paul Yankowich , Amy Hanson
发明人： Nagaraja S. Rudrapatna , Paul Yankowich , Amy Hanson
IPC分类号： F02C7/264 , F23R3/60
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。

3. 发明授权

US08429916B2 Dual walled combustors with improved liner seals 有权
标题翻译：双壁燃烧器具有改进的衬垫密封
公开(公告)号：US08429916B2
公开(公告)日：2013-04-30
申请号：US12623773
申请日：2009-11-23
申请人： Nagaraja S. Rudrapatna , Paul Yankowich , Amy Hanson
发明人： Nagaraja S. Rudrapatna , Paul Yankowich , Amy Hanson
IPC分类号： F23D14/46 , F23R3/60
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。

4. 发明申请

US20110120132A1 DUAL WALLED COMBUSTORS WITH IMPINGEMENT COOLED IGNITERS 有权
标题翻译：双壁玻璃杯与搅拌器混合
公开(公告)号：US20110120132A1
公开(公告)日：2011-05-26
申请号：US12623622
申请日：2009-11-23
申请人： Nagaraja S. Rudrapatna , Paul Yankowich , Amy Hanson
发明人： Nagaraja S. Rudrapatna , Paul Yankowich , Amy Hanson
IPC分类号： F23R3/42 , F02C7/264
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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