公开(公告)号：US06227798B1

公开(公告)日：2001-05-08

申请号：US09451279

申请日：1999-11-30

申请人： Daniel E. Demers ,  Mark D. Gledhill ,  Aureen C. Currin ,  Gene C. F. Tsai

发明人： Daniel E. Demers ,  Mark D. Gledhill ,  Aureen C. Currin ,  Gene C. F. Tsai

IPC分类号： F01D514

CPC分类号： F01D25/12 ,  F01D5/18 ,  F01D9/041 ,  F05D2230/21 ,  F05D2240/128 ,  F05D2260/201 ,  Y02T50/676

摘要： A gas turbine engine nozzle segment includes at least two circumferentially adjacent vanes joined together along an interface between the vanes. Each of the vanes includes a hollow airfoil disposed between radially inner and outer band panels and a cooling air intake duct leading to a hollow interior of the airfoil for directing cooling air into the hollow interior. The intake duct has a duct wall protruding radially outward from the outer band panel and at least one impingement cooling hole disposed through the intake duct wall and circumferentially and radially inwardly angled. A flange portion extends circumferentially along the outer band panel and an opening in the flange portion is in fluid communication with the intake duct. The hollow airfoil, radially inner and outer band panels, intake duct wall, and flange portion are integrally formed and, preferably, integrally cast such that the vane is a single piece integrally cast vane.

摘要翻译： 燃气涡轮发动机喷嘴段包括沿叶片之间的界面连接在一起的至少两个周向相邻的叶片。 每个叶片包括设置在径向内部和外部带状面板之间的中空翼型件和通向翼型件的中空内部的冷却空气进气管道，用于将冷却空气引导到中空内部。 进气管具有从外带板径向向外突出的导管壁和至少一个冲击冷却孔，该冲击冷却孔设置成穿过进气管壁并沿周向和径向向内成角度。 凸缘部分沿着外带板沿周向延伸，并且凸缘部分中的开口与进气管道流体连通。 中空翼片，径向内外带板，进气管壁和凸缘部分一体地形成，并且优选地整体铸造，使得叶片是单件整体铸造叶片。