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公开(公告)号：US08668448B2
公开(公告)日：2014-03-11
申请号：US12915575
申请日：2010-10-29
IPC分类号： F01D5/32
CPC分类号： F01D9/042
摘要： An example airfoil retention arrangement includes a retention assembly having a first retention segment and a second retention segment. Each of the retention segments is separately moveable to an installed position relative to an airfoil assembly and a support structure. The retention segments each have a portion position between a lip of the airfoil assembly and a collar of the support structure when the retention segments are in the installed position. The retention assembly is configured to limit radial movement of an airfoil relative to the support structure when in the installed position.
摘要翻译： 示例性翼型保持装置包括具有第一保持段和第二保留段的保持组件。 每个保持段分别可移动到相对于翼型组件和支撑结构的安装位置。 当保持段处于安装位置时，保持段各自具有在翼型组件的唇缘和支撑结构的套环之间的部分位置。 保持组件构造成在处于安装位置时限制翼型件相对于支撑结构的径向移动。
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公开(公告)号：US20120107124A1
公开(公告)日：2012-05-03
申请号：US12915575
申请日：2010-10-29
IPC分类号： F01D5/30
CPC分类号： F01D9/042
摘要： An example airfoil retention arrangement includes a retention assembly having a first retention segment and a second retention segment. Each of the retention segments is separately moveable to an installed position relative to an airfoil assembly and a support structure. The retention segments each have a portion position between a lip of the airfoil assembly and a collar of the support structure when the retention segments are in the installed position. The retention assembly is configured to limit radial movement of an airfoil relative to the support structure when in the installed position.
摘要翻译： 示例性翼型保持装置包括具有第一保持段和第二保留段的保持组件。 每个保持段分别可移动到相对于翼型组件和支撑结构的安装位置。 当保持段处于安装位置时，保持段各自具有在翼型组件的唇缘和支撑结构的套环之间的部分位置。 保持组件构造成在处于安装位置时限制翼型件相对于支撑结构的径向移动。
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公开(公告)号：US20100031665A1
公开(公告)日：2010-02-11
申请号：US12176895
申请日：2008-07-21
IPC分类号： F02C7/12
CPC分类号： F01D5/186 , F02K1/822 , F23R3/002 , F23R3/005 , F23R3/06 , F23R3/54 , F23R2900/03044 , Y02T50/675
摘要： A combustor assembly for a turbine engine includes a combustor liner, a flow sleeve and a plenum ring. The flow sleeve surrounds the combustor liner to form an annulus radially between the combustor liner and the flow sleeve. The flow sleeve has a plurality of rows of cooling holes. The plenum ring radially surrounds the combustor liner in the annulus. The plenum ring has a plurality of bypass tubes for directing axial air flow and radial flow chambers for directing radial air flow.
摘要翻译： 用于涡轮发动机的燃烧器组件包括燃烧器衬套，流动套管和增压环。 流动套筒围绕燃烧器衬套以在燃烧器衬套和流动套筒之间径向形成环形空间。 流动套筒具有多排冷却孔。 增压环径向包围环形空间中的燃烧器衬套。 气室环具有多个用于引导轴向气流的旁通管和用于引导径向气流的径向流动室。
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公开(公告)号：US08291711B2
公开(公告)日：2012-10-23
申请号：US12179671
申请日：2008-07-25
IPC分类号： F02C1/00
CPC分类号： F23R3/08 , F23R3/06 , F23R2900/03044
摘要： A combustor assembly for a turbine engine includes a combustor liner, a flow sleeve and a baffle ring. The flow sleeve surrounds the combustor liner. An annulus is formed between the flow sleeve and the combustor liner. A plurality of row of cooling holes are formed in the flow sleeve. The baffle ring radially surrounds the combustor liner and is located in the annulus.
摘要翻译： 用于涡轮发动机的燃烧器组件包括燃烧器衬套，流动套筒和挡板环。 流动套管围绕燃烧器衬套。 在流动套筒和燃烧器衬套之间形成一个环。 在流动套筒中形成多排冷却孔。 挡板环径向包围燃烧器衬套并且位于环形空间中。
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5.发明授权Combustion liner for a gas turbine engine including heat transfer columns to increase cooling of a hula seal at the transition duct region 有权用于燃气涡轮发动机的燃烧衬套包括传热塔，以增加在过渡管道区域处的呼啦密封件的冷却公开(公告)号：US08245514B2
公开(公告)日：2012-08-21
申请号：US12170602
申请日：2008-07-10
CPC分类号： F23R3/60 , F01D9/023 , F05D2240/55 , F23M5/085 , F23R3/005 , F23R2900/00012
摘要： A combustion duct assembly has a transition duct and a combustion liner having a hula seal at a downstream end that is forced within an inner wall of the transition duct. The combustion liner is held within the transition duct by the hula seal, but allowed to move relative to the transition duct. The combustion liner is formed with heat transfer columns adjacent the downstream end, and radially inwardly of the hula seal.
摘要翻译： 燃烧管道组件具有过渡管道和燃烧衬套，该燃烧衬套在下游端具有被迫在过渡管道的内壁内的呼啦密封。 燃烧衬套通过呼啦圈密封件保持在过渡管道内，但允许其相对于过渡管道移动。 燃烧衬套由邻近下游端的热传递柱和呼啦密封件的径向向内形成。
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公开(公告)号：US20100005805A1
公开(公告)日：2010-01-14
申请号：US12169994
申请日：2008-07-09
申请人： John S. Tu , Jaisukhlal V. Chokshi , Christopher R. Brdar , Randal G. McKinney , Shakira A. Ramos
发明人： John S. Tu , Jaisukhlal V. Chokshi , Christopher R. Brdar , Randal G. McKinney , Shakira A. Ramos
IPC分类号： F02C1/00
CPC分类号： F23R3/48 , F23R3/002 , F23R3/06 , F23R2900/03044
摘要： A combustion duct for a gas turbine engine has a combustion liner to receive products of combustion, and deliver the products of combustion downstream toward a turbine rotor. An outer housing is positioned radially outwardly of the combustion liner. A flow sleeve is positioned radially intermediate the outer housing and the combustion liner. A chamber radially outwardly of the flow sleeve receives cooling air. A plurality of holes through the flow sleeve deliver cooling air from the chamber against an outer periphery of the combustion liner. A plurality of tabs are associated with at least some of the holes in the flow sleeve. The tabs are positioned to extend radially inwardly on a downstream side of the holes.
摘要翻译： 用于燃气涡轮发动机的燃烧管具有燃烧衬套以接收燃烧产物，并将燃烧产物向下流向涡轮转子传送。 外壳体位于燃烧衬套的径向外侧。 流动套筒径向位于外壳体和燃烧衬套之间。 流动套管径向向外的腔容纳冷却空气。 穿过流动套管的多个孔将来自腔室的冷却空气传递到燃烧衬套的外周。 多个翼片与流动套筒中的至少一些孔相关联。 突片被定位成在孔的下游侧径向向内延伸。
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公开(公告)号：US08794006B2
公开(公告)日：2014-08-05
申请号：US13553076
申请日：2012-07-19
IPC分类号： F02C1/00
CPC分类号： F23R3/08 , F23R3/06 , F23R2900/03044
摘要： A combustor assembly for a turbine engine includes a combustor liner, a flow sleeve and a baffle ring. The flow sleeve surrounds the combustor liner. An annulus is formed between the flow sleeve and the combustor liner. A plurality of row of cooling holes are formed in the flow sleeve. The baffle ring radially surrounds the combustor liner and is located in the annulus.
摘要翻译： 用于涡轮发动机的燃烧器组件包括燃烧器衬套，流动套筒和挡板环。 流动套管围绕燃烧器衬套。 在流动套筒和燃烧器衬套之间形成一个环。 在流动套筒中形成多排冷却孔。 挡板环径向包围燃烧器衬套并且位于环形空间中。
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公开(公告)号：US08109099B2
公开(公告)日：2012-02-07
申请号：US12169994
申请日：2008-07-09
申请人： John S. Tu , Jaisukhlal V. Chokshi , Christopher R. Brdar , Randal G. McKinney , Shakira A. Ramos
发明人： John S. Tu , Jaisukhlal V. Chokshi , Christopher R. Brdar , Randal G. McKinney , Shakira A. Ramos
IPC分类号： F02C1/00
CPC分类号： F23R3/48 , F23R3/002 , F23R3/06 , F23R2900/03044
摘要： A combustion duct for a gas turbine engine has a combustion liner to receive products of combustion, and deliver the products of combustion downstream toward a turbine rotor. An outer housing is positioned radially outwardly of the combustion liner. A flow sleeve is positioned radially intermediate the outer housing and the combustion liner. A chamber radially outwardly of the flow sleeve receives cooling air. A plurality of holes through the flow sleeve deliver cooling air from the chamber against an outer periphery of the combustion liner. A plurality of tabs are associated with at least some of the holes in the flow sleeve. The tabs are positioned to extend radially inwardly on a downstream side of the holes.
摘要翻译： 用于燃气涡轮发动机的燃烧管具有燃烧衬套以接收燃烧产物，并将燃烧产物向下流向涡轮转子传送。 外壳体位于燃烧衬套的径向外侧。 流动套筒径向位于外壳体和燃烧衬套之间。 流动套管径向向外的腔容纳冷却空气。 穿过流动套管的多个孔将来自腔室的冷却空气传递到燃烧衬套的外周。 多个翼片与流动套筒中的至少一些孔相关联。 突片被定位成在孔的下游侧径向向内延伸。
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公开(公告)号：US20130000310A1
公开(公告)日：2013-01-03
申请号：US13553076
申请日：2012-07-19
CPC分类号： F23R3/08 , F23R3/06 , F23R2900/03044
摘要： A combustor assembly for a turbine engine includes a combustor liner, a flow sleeve and a baffle ring. The flow sleeve surrounds the combustor liner. An annulus is formed between the flow sleeve and the combustor liner. A plurality of row of cooling holes are formed in the flow sleeve. The baffle ring radially surrounds the combustor liner and is located in the annulus.
摘要翻译： 用于涡轮发动机的燃烧器组件包括燃烧器衬套，流动套筒和挡板环。 流动套管围绕燃烧器衬套。 在流动套管和燃烧器衬套之间形成有环。 在流动套筒中形成多排冷却孔。 挡板环径向包围燃烧器衬套并且位于环形空间中。
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公开(公告)号：US08166764B2
公开(公告)日：2012-05-01
申请号：US12176895
申请日：2008-07-21
IPC分类号： F02C1/00
CPC分类号： F01D5/186 , F02K1/822 , F23R3/002 , F23R3/005 , F23R3/06 , F23R3/54 , F23R2900/03044 , Y02T50/675
摘要： A combustor assembly for a turbine engine includes a combustor liner, a flow sleeve and a plenum ring. The flow sleeve surrounds the combustor liner to form an annulus radially between the combustor liner and the flow sleeve. The flow sleeve has a plurality of rows of cooling holes. The plenum ring radially surrounds the combustor liner in the annulus. The plenum ring has a plurality of bypass tubes for directing axial air flow and radial flow chambers for directing radial air flow.
摘要翻译： 用于涡轮发动机的燃烧器组件包括燃烧器衬套，流动套管和增压环。 流动套筒围绕燃烧器衬套以在燃烧器衬套和流动套筒之间径向形成环形空间。 流动套筒具有多排冷却孔。 增压环径向包围环形空间中的燃烧器衬套。 气室环具有多个用于引导轴向气流的旁通管和用于引导径向气流的径向流动室。
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