公开(公告)号：US06616407B2

公开(公告)日：2003-09-09

申请号：US10078672

申请日：2002-02-21

申请人： David W Barrett

发明人： David W Barrett

IPC分类号： F01D518

CPC分类号： F01D9/041 ,  F01D5/189 ,  F05D2250/323 ,  F05D2260/201 ,  F05D2260/2212 ,  F05D2260/22141 ,  Y02T50/676

摘要： An air cooled guide vane (20) is provided with a stack of ducts (40) each of which converges towards its outlet end. Air flow turbulators (42) are positioned in ducts (40) and pressure losses in the air flow brought about by flowing over the turbulators (42), is recovered by the constricting effect of the ducts (40).

公开(公告)号：US06874987B2

公开(公告)日：2005-04-05

申请号：US10354038

申请日：2003-01-30

申请人： John Slinger ,  David W Barrett ,  Christopher M Robson

发明人： John Slinger ,  David W Barrett ,  Christopher M Robson

IPC分类号： F01D5/18

CPC分类号： F01D5/186 ,  F05D2250/314 ,  F05D2260/202

摘要： A gas turbine engine turbine blade (20) has cooling air holes (38) arranged in groups, the holes (38) in one group and which span that part of the leading edge (34) that spans the hottest part of the blade (20), are more closely spaced than the remainder of the holes (38), thereby ensuring the provision of the most cooling air, where it is most needed.

摘要翻译： 一种燃气涡轮发动机涡轮机叶片（20）具有一组排列的冷却空气孔（38），一组中的孔（38）并跨越前缘（34）的跨越叶片最热的部分（20）的那部分 ）比其余的孔（38）更紧密地间隔开，从而确保在最需要的地方提供最冷的空气。

公开(公告)号：US06641363B2

公开(公告)日：2003-11-04

申请号：US10206771

申请日：2002-07-29

申请人： David W Barrett ,  Philip D Robinson

发明人： David W Barrett ,  Philip D Robinson

IPC分类号： F01D1124

CPC分类号： F01D25/12 ,  F01D9/04 ,  F01D11/24 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/22141

摘要： A stage of turbine blades (40) in a gas turbine engine (10) is surrounded by an array of shroud segments (42). The upstream ends of the segments (42) have plenum chambers (54) into which cooling air is fed from a compressor (12) via one hole (66) of a pair of holes, the other being numbered (68). Air from the plenum chambers (54) passes out to film cool the interior surface of each respective segment (42). Air from holes (68) passes out to convection cool the exterior surface of each segment (42), which effect is enhanced by the provision of ribs (80) and fences (82).

摘要翻译： 燃气涡轮发动机（10）中的涡轮机叶片（40）的一个阶段由一组护罩段（42）围绕。 节段（42）的上游端具有通风室（54），冷却空气经由一对孔的一个孔（66）从压缩机（12）供给到其中，另一个被编号（68）。 来自增压室（54）的空气流出来，使各个区段（42）的内表面成膜。 来自孔（68）的空气通过对流冷却每个段（42）的外表面，该作用通过提供肋（80）和栅栏（82）来增强。