-
公开(公告)号：US09260972B2
公开(公告)日：2016-02-16
申请号：US13540752
申请日：2012-07-03
CPC分类号： F01D5/18 , F01D5/146 , F01D5/20 , F05D2240/307 , Y02T50/673 , Y02T50/676
摘要： A turbine airfoil comprises a suction sidewall, a pressure sidewall, a tip wall, and a tip leakage control channel. Each sidewall extends spanwise from an airfoil base and chordwise between a leading edge and a trailing edge. The tip wall extends chordwise from the leading edge to the trailing edge and joins respective outer spanwise ends of the suction and pressure sidewalls. The tip leakage control channel has an inlet and an outlet recessed into an outer surface of the tip wall. An inlet of the channel begins proximate a junction of the airfoil pressure sidewall and the tip wall. An outlet of the channel terminates at a recessed portion of the junction of the tip wall and the suction sidewall.
摘要翻译： 涡轮机翼片包括抽吸侧壁，压力侧壁，尖端壁和尖端泄漏控制通道。 每个侧壁从翼型基座向翼展方向延伸，并且在前缘和后缘之间并排。 尖端壁从前缘延伸到后缘，并且连接吸力和压力侧壁的相应的外翼展端。 尖端泄漏控制通道具有凹入到顶端壁的外表面中的入口和出口。 通道的入口在翼型压力侧壁和尖端壁的接合点附近开始。 通道的出口终止于尖端壁和抽吸侧壁的接合处的凹陷部分。
-
公开(公告)号：US09777582B2
公开(公告)日：2017-10-03
申请号：US14143115
申请日：2013-12-30
CPC分类号： F01D5/20 , F01D9/02 , F01D11/08 , F05D2220/32 , F05D2240/126 , Y02T50/673
摘要： An airfoil according to an exemplary aspect of the present disclosure includes, among other things, a suction sidewall and a pressure sidewall, each sidewall extending spanwise from an airfoil base and extending chordwise between a leading edge and a trailing edge. A tip wall extends chordwise from the leading edge to the trailing edge and joining respective outer spanwise ends of the suction and pressure sidewalls. A tip leakage control vane is formed with an outer surface of the tip wall and a winglet is formed at a junction between the suction sidewall and the tip leakage control vane.
-
公开(公告)号：US20150330230A1
公开(公告)日：2015-11-19
申请号：US14143115
申请日：2013-12-30
CPC分类号： F01D5/20 , F01D9/02 , F01D11/08 , F05D2220/32 , F05D2240/126 , Y02T50/673
摘要： An airfoil according to an exemplary aspect of the present disclosure includes, among other things, a suction sidewall and a pressure sidewall, each sidewall extending spanwise from an airfoil base and extending chordwise between a leading edge and a trailing edge. A tip wall extends chordwise from the leading edge to the trailing edge and joining respective outer spanwise ends of the suction and pressure sidewalls. A tip leakage control vane is formed with an outer surface of the tip wall and a winglet is formed at a junction between the suction sidewall and the tip leakage control vane.
摘要翻译： 根据本公开的示例性方面的翼型件包括抽吸侧壁和压力侧壁，每个侧壁从翼型基部伸展，并且在前缘和后缘之间延伸地延伸。 尖端壁从前缘延伸到后缘并且连接吸力和压力侧壁的相应的外翼展端。 尖端泄漏控制叶片形成有顶壁的外表面，并且在吸力侧壁和尖端泄漏控制叶片之间的接合处形成小翼。
-
公开(公告)号：US20140186190A1
公开(公告)日：2014-07-03
申请号：US14143102
申请日：2013-12-30
CPC分类号： F01D5/187 , F01D5/146 , F01D5/18 , F01D5/186 , F01D5/20 , F01D11/10 , F05D2240/307 , Y02T50/673 , Y02T50/676
摘要： An airfoil according to an exemplary aspect of the present disclosure includes, among other things, a suction sidewall and a pressure sidewall, each sidewall extending spanwise from an airfoil base and extending chordwise between a leading edge and a trailing edge. A tip wall extends chordwise from the leading edge to the trailing edge and joining respective outer spanwise ends of the suction and pressure sidewalls. A tip leakage control channel is recessed into the tip wall, the tip leakage control channel including a control channel floor that extends between a first control channel vane sidewall and a second control channel vane sidewall established by a corresponding tip leakage control vane. An internal cooling cavity is disposed between the suction sidewall and the pressure sidewall and a channel cooling aperture feeds airflow from the internal cooling cavity to the tip leakage control channel.
摘要翻译： 根据本公开的示例性方面的翼型件包括抽吸侧壁和压力侧壁，每个侧壁从翼型基部伸展，并且在前缘和后缘之间延伸地延伸。 尖端壁从前缘延伸到后缘并且连接吸力和压力侧壁的相应的外翼展端。 尖端泄漏控制通道凹入到顶端壁中，尖端泄漏控制通道包括控制通道底板，该控制通道底板在由相应的顶部泄漏控制叶片建立的第一控制通道叶片侧壁和第二控制通道叶片侧壁之间延伸。 内部冷却腔设置在吸力侧壁和压力侧壁之间，并且通道冷却孔将来自内部冷却腔的气流馈送到尖端泄漏控制通道。
-
公开(公告)号：US09957817B2
公开(公告)日：2018-05-01
申请号：US14143072
申请日：2013-12-30
CPC分类号： F01D5/20 , F01D9/02 , F01D11/08 , F01D25/12 , F05D2220/32 , F05D2240/126 , F05D2240/55 , F05D2250/294 , Y02T50/673
摘要： A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an airfoil having a tip wall that joins outer spanwise ends of a suction sidewall and a pressure sidewall, a tip leakage control channel recessed into an outer surface of the tip wall, a tip leakage control vane integrally formed on the tip wall adjacent to the tip leakage control channel and an air seal radially outward of the tip wall and positioned to minimize leakage at the tip wall.
-
公开(公告)号：US09951629B2
公开(公告)日：2018-04-24
申请号：US14143102
申请日：2013-12-30
CPC分类号： F01D5/187 , F01D5/146 , F01D5/18 , F01D5/186 , F01D5/20 , F01D11/10 , F05D2240/307 , Y02T50/673 , Y02T50/676
摘要： An airfoil according to an exemplary aspect of the present disclosure includes, among other things, a suction sidewall and a pressure sidewall, each sidewall extending spanwise from an airfoil base and extending chordwise between a leading edge and a trailing edge. A tip wall extends chordwise from the leading edge to the trailing edge and joining respective outer spanwise ends of the suction and pressure sidewalls. A tip leakage control channel is recessed into the tip wall, the tip leakage control channel including a control channel floor that extends between a first control channel vane sidewall and a second control channel vane sidewall established by a corresponding tip leakage control vane. An internal cooling cavity is disposed between the suction sidewall and the pressure sidewall and a channel cooling aperture feeds airflow from the internal cooling cavity to the tip leakage control channel.
-
公开(公告)号：US20150330229A1
公开(公告)日：2015-11-19
申请号：US14143072
申请日：2013-12-30
CPC分类号： F01D5/20 , F01D9/02 , F01D11/08 , F01D25/12 , F05D2220/32 , F05D2240/126 , F05D2240/55 , F05D2250/294 , Y02T50/673
摘要： A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an airfoil having a tip wall that joins outer spanwise ends of a suction sidewall and a pressure sidewall, a tip leakage control channel recessed into an outer surface of the tip wall, a tip leakage control vane integrally formed on the tip wall adjacent to the tip leakage control channel and an air seal radially outward of the tip wall and positioned to minimize leakage at the tip wall.
摘要翻译： 根据本公开的示例性方面的燃气涡轮发动机尤其包括具有接合吸入侧壁的外翼展端部和压力侧壁的顶端壁的翼型件，凹入到外侧表面的顶端泄漏控制通道 尖端壁，尖端泄漏控制叶片，其一体地形成在尖端泄漏控制通道附近的尖端壁上，以及位于顶端壁径向外侧的空气密封，并且定位成使得尖端壁处的泄漏最小化。
-
公开(公告)号：US20140010650A1
公开(公告)日：2014-01-09
申请号：US13540752
申请日：2012-07-03
CPC分类号： F01D5/18 , F01D5/146 , F01D5/20 , F05D2240/307 , Y02T50/673 , Y02T50/676
摘要： A turbine airfoil comprises a suction sidewall, a pressure sidewall, a tip wall, and a tip leakage control channel. Each sidewall extends spanwise from an airfoil base and chordwise between a leading edge and a trailing edge. The tip wall extends chordwise from the leading edge to the trailing edge and joins respective outer spanwise ends of the suction and pressure sidewalls. The tip leakage control channel has an inlet and an outlet recessed into an outer surface of the tip wall. An inlet of the channel begins proximate a junction of the airfoil pressure sidewall and the tip wall. An outlet of the channel terminates at a recessed portion of the junction of the tip wall and the suction sidewall.
摘要翻译： 涡轮机翼片包括抽吸侧壁，压力侧壁，尖端壁和尖端泄漏控制通道。 每个侧壁从翼型基座向翼展方向延伸，并且在前缘和后缘之间并排。 尖端壁从前缘延伸到后缘，并且连接吸力和压力侧壁的相应的外翼展端。 尖端泄漏控制通道具有凹入到顶端壁的外表面中的入口和出口。 通道的入口在翼型压力侧壁和尖端壁的接合点附近开始。 通道的出口终止于尖端壁和抽吸侧壁的接合处的凹陷部分。
-
公开(公告)号：US07581930B2
公开(公告)日：2009-09-01
申请号：US11504980
申请日：2006-08-16
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F05D2240/80 , F05D2250/74
摘要： A turbine blade system including a blade airfoil having an airfoil shape with the blade airfoil having a nominal profile substantially in accordance with normalized Cartesian coordinate values Z set forth in a table 1 below and which values are dimensionless values that are convertible to corresponding absolute distance values that define nominal airfoil profile sections and which, when joined smoothly with adjacent ones thereof, form a complete nominal airfoil shape that is substantially matched by the airfoil shape of the blade airfoil. This blade airfoil can be supported on a ring platform having a support surface with a support surface shape in the vicinity of the location at which that blade airfoil is supported thereon formed in a similar manner.
摘要翻译： 一种涡轮叶片系统，包括具有翼型形状的叶片翼型，叶片翼型件具有基本上根据下表1中所示的归一化笛卡尔坐标值Z的标称轮廓，并且哪些值是可转换为对应绝对距离值的无量纲值 其限定标称翼型轮廓部分，并且当与其相邻部分平滑地连接时，形成与叶片翼型的翼型形状基本匹配的完整的标称翼型形状。 该叶片翼型件可以支撑在具有支撑表面的支撑表面的环形平台上，支撑表面形状在该叶片翼型被支撑在其上以类似方式支撑的位置附近。
-
公开(公告)号：US20090162204A1
公开(公告)日：2009-06-25
申请号：US11504980
申请日：2006-08-16
CPC分类号： F01D5/141 , F05D2240/80 , F05D2250/74
摘要： A turbine blade system including a blade airfoil having an airfoil shape with the blade airfoil having a nominal profile substantially in accordance with normalized Cartesian coordinate values Z set forth in a table 1 below and which values are dimensionless values that are convertible to corresponding absolute distance values that define nominal airfoil profile sections and which, when joined smoothly with adjacent ones thereof, form a complete nominal airfoil shape that is substantially matched by the airfoil shape of the blade airfoil. This blade airfoil can be supported on a ring platform having a support surface with a support surface shape in the vicinity of the location at which that blade airfoil is supported thereon formed in a similar manner.
摘要翻译： 一种涡轮叶片系统，包括具有翼型形状的叶片翼型，叶片翼型件具有基本上根据下表1中所示的归一化笛卡尔坐标值Z的标称轮廓，并且哪些值是可转换为对应绝对距离值的无量纲值 其限定标称翼型轮廓部分，并且当与其相邻部分平滑地连接时，形成与叶片翼型的翼型形状基本匹配的完整的标称翼型形状。 该叶片翼型件可以支撑在具有支撑表面的支撑表面的环形平台上，支撑表面形状在该叶片翼型被支撑在其上以类似方式支撑的位置附近。
-
-
-
-
-
-
-
-
-
搜索结果
25 条记录 (耗时 0.028 秒)
