公开(公告)号：US08662825B2

公开(公告)日：2014-03-04

申请号：US12861560

申请日：2010-08-23

申请人： Peter T. Ireland ,  Howoong Namgoong

发明人： Peter T. Ireland ,  Howoong Namgoong

IPC分类号： F01D5/18

CPC分类号： F01D5/187 ,  F05D2250/185 ,  F05D2250/324 ,  F05D2270/17

摘要： An aerofoil blade or vane suitable for the turbine of a gas turbine engine includes an extending aerofoil portion having facing wall parts interconnected by a divider member to partially define first and second cooling fluid passage portions. The first and second passage portions are interconnected in a series fluid flow relationship by a bend passage portion. The first passage portion directs cooling fluid to the bend portion and the second passage portion exhausts cooling fluid from the bend portion. The divider member provides a localised contraction of the downstream end of the first passage portion to accelerate the cooling fluid flow before it enters the bend passage portion. The divider member provides a localised progressive series narrowing and opening of the upstream end of the second passage portion in the general direction of cooling fluid flow.

摘要翻译： 适合于燃气涡轮发动机的涡轮机的机翼叶片或叶片包括延伸的机翼部分，其具有通过分隔件互连的面对的壁部分，以部分地限定第一和第二冷却流体通道部分。 第一和第二通道部分由弯曲通道部分以串联流体流动关系相互连接。 第一通道部分将冷却流体引导到弯曲部分，第二通道部分从弯曲部分排出冷却流体。 分隔构件提供第一通道部分的下游端的局部收缩，以在其进入弯曲通道部分之前加速冷却流体流动。 分隔构件提供沿着冷却流体流动的大致方向的第二通道部分的上游端的局部渐进式系列变窄和打开。

公开(公告)号：US20110058958A1

公开(公告)日：2011-03-10

申请号：US12861560

申请日：2010-08-23

申请人： Peter T. IRELAND ,  Howoong NAMGOONG

发明人： Peter T. IRELAND ,  Howoong NAMGOONG

IPC分类号： F01D5/18

CPC分类号： F01D5/187 ,  F05D2250/185 ,  F05D2250/324 ,  F05D2270/17

摘要： An aerofoil blade or vane (1) suitable for the turbine of a gas turbine engine includes a longitudinally extending aerofoil portion (7) having facing wall parts (20, 22). The wall parts being interconnected by a generally longitudinally extending divider member (17) to partially define first and second cooling fluid passage portions (11, 15) disposed in side-by-side generally longitudinally extending relationship. The first and second passage portions being interconnected in series fluid flow relationship by a bend passage portion (13). The first passage portion is adapted to direct cooling fluid to the bend portion and the second passage portion being adapted to exhaust cooling fluid from the bend portion. The divider member has a first local thickening (33) in the region of the bend portion to provide a localised contraction of the downstream end of the first passage portion to accelerate the cooling fluid flow before it enters the bend passage portion. The divider member has a second local thickening (31) in the region of the bend portion to provide a localised progressive series narrowing and opening of the upstream end of the second passage portion in the general direction of cooling fluid flow.

摘要翻译： 适用于燃气涡轮发动机的涡轮机的机翼叶片或叶片（1）包括具有相对的壁部分（20,22）的纵向延伸的机翼部分（7）。 壁部分通过大致纵向延伸的分隔构件（17）互连，以部分地限定并排布置成大致纵向延伸的第一和第二冷却流体通道部分（11,15）。 第一和第二通道部分由弯曲通道部分（13）以串联的流体流动关系相互连接。 第一通道部分适于将冷却流体引导到弯曲部分，并且第二通道部分适于从弯曲部分排出冷却流体。 分隔构件在弯曲部分的区域中具有第一局部增厚（33），以提供第一通道部分的下游端的局部收缩，以在其进入弯曲通道部分之前加速冷却流体流动。 分隔构件在弯曲部分的区域中具有第二局部增厚（31），以提供在冷却流体流动的大致方向上的第二通道部分的上游端的局部渐进式变窄和打开。