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公开(公告)号：US20160208619A1
公开(公告)日：2016-07-21
申请号：US14602035
申请日：2015-01-21
IPC分类号： F01D5/18
摘要： An airfoil is provided. The airfoil may comprise a cross over, an impingement chamber in fluid communication with the cross over, and a first trip strip disposed on a first surface of the impingement chamber. A cooling system is also provided. The cooling system may comprise an impingement chamber, a first trip strip on a first surface of the impingement chamber, and a second trip strip on a second surface of the impingement chamber. An internally cooled engine part is further provided. The internally cooled part may comprise a cross over and an impingement chamber in fluid communication with the cross over. The cross over may be configured to direct air towards a first surface of the impingement chamber. A first trip strip may be disposed on the first surface of the impingement chamber.
摘要翻译： 提供翼型。 所述翼型件可以包括十字交叉，与所述十字架流体连通的冲击室以及设置在所述冲击室的第一表面上的第一跳闸条。 还提供冷却系统。 冷却系统可以包括冲击室，冲击室的第一表面上的第一跳闸条和在冲击室的第二表面上的第二跳闸条。 还提供内部冷却的发动机部件。 内部冷却部分可以包括与交叉流体连通的交叉和冲击室。 十字架可以构造成将空气引向冲击室的第一表面。 第一跳闸条可以设置在冲击室的第一表面上。
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公开(公告)号：US20160069189A1
公开(公告)日：2016-03-10
申请号：US14630814
申请日：2015-02-25
CPC分类号： F01D5/147 , B22C9/103 , F01D5/187 , F01D5/284 , F05D2230/21 , F05D2240/304 , F05D2240/307 , F05D2260/2212 , F05D2300/6033
摘要： A component for a gas turbine engine includes a trailing edge tip corner that at least partially defines a trailing edge cavity and a multiple of corner features within the trailing edge cavity, the multiple of corner features splayed along the trailing edge tip corner.
摘要翻译： 用于燃气涡轮发动机的部件包括后缘尖端角部，该后缘尖端角部至少部分地限定后缘腔体中的后缘腔体和多个角部特征，沿着后缘尖端角部显示多个角部特征。
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公开(公告)号：US20160032416A1
公开(公告)日：2016-02-04
申请号：US14883060
申请日：2015-10-14
发明人： Tracy A. Propheter-Hinckley , Mark F. Zelesky , Dominic J. Mongillo, Jr. , Matthew A. Devore , Steven Bruce Gautschi , Benjamin T. Fisk
CPC分类号： B22C9/04 , B22C9/10 , B22C9/24 , B22F3/1017 , B22F3/105 , B22F3/1055 , B22F5/04 , B23K15/0086 , B33Y10/00 , B33Y80/00 , C21D9/0068 , F01D5/187 , F05D2240/303 , F05D2260/201 , F05D2260/202 , F05D2260/205 , Y02P10/292 , Y02P10/295
摘要： A method of manufacturing an airfoil includes the steps of depositing multiple layers of powdered metal onto one another. The layers are joined to one another with reference to CAD data relating to a particular cross-section of an airfoil. The airfoil is produced with leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface. An exterior wall provides the exterior airfoil surface at the leading edge. An impingement wall is integrally formed with the exterior wall to provide an impingement cavity between the exterior wall and the impingement wall. Multiple impingement holes are provided in the impingement wall. The impingement holes are spaced laterally across the impingement wall.
摘要翻译： 一种制造翼型件的方法包括以下步骤：将多层粉末金属沉积在彼此上。 参考与翼型的特定横截面相关的CAD数据，这些层彼此连接。 翼型件被制造成具有通过间隔开的压力和吸力侧连接的前缘和后缘，以提供外部翼面表面。 外墙在前缘提供外部翼型表面。 冲击壁与外壁一体地形成，以在外壁和冲击壁之间提供冲击腔。 多个冲击孔设置在冲击壁上。 冲击孔横向穿过冲击壁间隔开。
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74.发明申请TURBINE AIRFOIL TIP SHELF AND SQUEALER POCKET COOLING 有权TURBINE AIRFOIL TIP SHELF和SQUEALER POCKET COOLING公开(公告)号：US20150292334A1
公开(公告)日：2015-10-15
申请号：US14748666
申请日：2015-06-24
CPC分类号： F01D5/20 , F05D2260/202 , Y02T50/673 , Y02T50/676
摘要： An airfoil includes a pressure surface and a suction surface extending from a root section of the airfoil to a tip section of the airfoil. The airfoil also includes a leading edge and a trailing edge defining a chord length of the airfoil therebetween. The airfoil further includes a tip shelf formed along the tip section of the airfoil between the pressure surface and a tip shelf wall. The tip shelf wall is spaced between the pressure surface and the suction surface and the tip shelf extends from within 10% of the chord length measured from the leading edge to within 10% of the chord length measured from the trailing edge.
摘要翻译： 翼型件包括压力表面和从翼型件的根部部分延伸到翼型件的尖端部分的抽吸表面。 翼型件还包括前缘和后缘，其在它们之间限定翼型的翼弦长度。 所述翼型件还包括沿所述翼型件的所述尖端部分在所述压力表面和尖端搁板壁之间形成的尖端架。 尖端架壁在压力表面和吸力表面之间间隔开，并且尖端架从从前缘测量的弦长的10％范围内延伸到从后缘测量的弦长的10％以内。
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75.发明申请TURBINE AIRFOIL TIP SHELF AND SQUEALER POCKET COOLING 有权TURBINE AIRFOIL TIP SHELF和SQUEALER POCKET COOLING公开(公告)号：US20150118063A1
公开(公告)日：2015-04-30
申请号：US14250166
申请日：2014-04-10
CPC分类号： F01D5/20 , F05D2260/202 , Y02T50/673 , Y02T50/676
摘要： An airfoil comprises pressure and suction surfaces extending from a root section to a tip section of the airfoil. The airfoil also comprises a leading edge and trailing edge defining a chord length therebetween. A tip shelf is formed along the tip section between the pressure surface and a tip shelf wall, the tip shelf wall being spaced between the pressure surface and the suction surface. A squealer pocket is formed along the tip section between the tip shelf wall and a squealer tip wall extending from the suction surface. The tip shelf extends from within 10% of the cord length measured from the leading edge to within 10% of the chord length measured from the trailing edge. The squealer pocket extends from within 10% of the chord length measured from the leading edge to terminate less than 85% of the chord length measured from the trailing edge.
摘要翻译： 翼型件包括从根部延伸到翼型的尖端部分的压力和吸力表面。 翼型件还包括在其间限定弦长的前缘和后缘。 沿着压力表面和尖端搁板壁之间的尖端部分形成尖端搁板，顶部搁板壁在压力表面和吸力表面之间分开。 沿尖端搁架壁和从抽吸面延伸的尖叫尖端壁之间的尖端部分形成一个尖叫口袋。 尖端架从从前缘测量的绳索长度的10％范围内延伸到从后缘测量的弦长的10％以内。 尖叫口袋从前缘测量的弦长的10％范围内延伸，以终止从后缘测得的弦长不到85％。
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