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公开(公告)号：US06607356B2
公开(公告)日：2003-08-19
申请号：US10044249
申请日：2002-01-11
IPC分类号： F01D518
CPC分类号： F01D5/187 , F05D2260/201 , F05D2260/22141 , Y02T50/676
摘要： A turbine airfoil includes pressure and suction sidewalls having first and second flow channels disposed therebetween and separated by a longitudinally extending bridge. The bridge includes a row of inlet holes, and a row of outlet holes extends from the second channel toward the trailing edge of the airfoil. A row of turbulator ribs is disposed inside the second channel along the pressure sidewall and are longitudinally elongate and substantially colinear. The ribs face the inlet holes for crossover impingement cooling from the air channeled therefrom.
摘要翻译： 涡轮机翼片包括压力和抽吸侧壁，其具有设置在其间并由纵向延伸的桥隔开的第一和第二流动通道。 桥梁包括一排入口孔，一排出口孔从第二通道延伸到翼型的后缘。 一排湍流肋沿着压力侧壁设置在第二通道的内部，并且纵向伸长并且基本上是共线的。 这些肋面朝向入口孔，用于从其引导的空气中进行交叉冲击冷却。
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公开(公告)号：US5681144A
公开(公告)日：1997-10-28
申请号：US809193
申请日：1991-12-17
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2260/2212 , Y02T50/676
摘要： A gas turbine engine blade includes an airfoil having first and second sides and an internal passage extending longitudinally therebetween for channeling air to cool the airfoil. Respective pluralities of first and second turbulator ribs extend inwardly from at least one of the first and second airfoil sides. Adjacent ones of second ends of the first and second ribs are staggered apart longitudinally and overlap chordally for defining a gap therebetween facing transversely for turning cooling air upon flow through the gap. The gap increases convective heat transfer enhancement for reducing cooling air requirements and improving blade creep life.
摘要翻译： 燃气涡轮发动机叶片包括具有第一和第二侧面的翼型件和在其间纵向延伸的内部通道，用于引导空气以冷却翼型件。 第一和第二湍流肋的各个多个从第一和第二翼面侧面中的至少一个向内延伸。 第一和第二肋的相邻的第二端在纵向上交错分开，并且重叠在一起，用于限定横向间隙，用于在通过间隙流动时转动冷却空气。 该间隙增加了对流传热增强，以减少冷却空气需求并提高叶片蠕变寿命。
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