公开(公告)号：US5681144A

公开(公告)日：1997-10-28

申请号：US809193

申请日：1991-12-17

申请人： Samuel Dale Spring ,  Nesim Abuaf ,  Mohammad Esmail Taslim

发明人： Samuel Dale Spring ,  Nesim Abuaf ,  Mohammad Esmail Taslim

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。