公开(公告)号：US20090245999A1

公开(公告)日：2009-10-01

申请号：US12055101

申请日：2008-03-25

申请人： David Allen Flodman ,  Jason David Shapiro ,  Robert Francis Manning ,  Mark Douglas Gledhill ,  Tyler Frederick Hooper

发明人： David Allen Flodman ,  Jason David Shapiro ,  Robert Francis Manning ,  Mark Douglas Gledhill ,  Tyler Frederick Hooper

IPC分类号： F01D5/18

CPC分类号： F01D5/189 ,  F05D2260/201 ,  F05D2260/202 ,  Y02T50/676

摘要： A turbine nozzle for a gas turbine engine includes: (a) spaced-apart arcuate inner and outer bands; (b) a hollow, airfoil-shaped turbine vane extending between the inner and outer bands, the interior of the vane defining at least a forward cavity and a mid-cavity positioned aft of the forward cavity; (c) a hollow impingement insert received inside the mid-cavity, the impingement insert having walls which are pierced with at least one impingement cooling hole; (d) a passage in the turbine vane at a radially outer end of the forward cavity adapted to be coupled to a source of cooling air; and (e) a passage in the inner band in fluid communication with a radially inner end of the forward cavity and a radially inner end of the impingement insert.

摘要翻译： 用于燃气涡轮发动机的涡轮喷嘴包括：（a）间隔开的弓形内部和外部带; （b）在所述内部和外部带之间延伸的中空翼型涡轮机叶片，所述叶片的内部至少限定前腔和位于所述前腔后面的中空腔; （c）容纳在中空腔内的中空冲击插入件，冲击插入件具有用至少一个冲击冷却孔刺穿的壁; （d）在所述前腔的径向外端处的涡轮叶片中的通道，其适于联接到冷却空气源; 和（e）内带中的与前腔的径向内端流体连通的通道和冲击插入件的径向内端。

公开(公告)号：US07296967B2

公开(公告)日：2007-11-20

申请号：US11224922

申请日：2005-09-13

申请人： Jason David Shapiro

发明人： Jason David Shapiro

IPC分类号： F01D5/22

CPC分类号： F01D25/12 ,  F01D11/08 ,  F01D25/246 ,  F05D2220/3212 ,  F05D2250/18 ,  F05D2260/202 ,  Y02T50/67 ,  Y02T50/676

摘要： A turbine wall includes opposite back and front sides. Film cooling holes are inclined longitudinally through the wall. Adjacent holes are spaced laterally apart and are inclined oppositely for channeling cooling air therethrough in counterflow.