公开(公告)号：US06270317B1

公开(公告)日：2001-08-07

申请号：US09466154

申请日：1999-12-18

申请人： Robert F. Manning ,  Gene C. F. Tsai ,  Anthony D. Di Bello

发明人： Robert F. Manning ,  Gene C. F. Tsai ,  Anthony D. Di Bello

IPC分类号： F04D2958

CPC分类号： F01D5/186 ,  F01D5/187 ,  F01D9/041 ,  F05D2260/22141 ,  Y02T50/676 ,  Y10S416/02

摘要： A turbine nozzle vane includes pressure and suction sidewalls extending between leading and trailing edges. The vane includes a pair of integral ribs defining three internal cooling channels between the leading and trailing edges. Rows of film cooling holes extend through the sidewalls, and three rows in the pressure side are inclined along the span of the airfoil at different slopes.

摘要翻译： 涡轮喷嘴叶片包括在前缘和后缘之间延伸的压力和吸力侧壁。 叶片包括在前缘和后缘之间限定三个内部冷却通道的一对整体肋。 薄膜冷却孔的行延伸穿过侧壁，并且压力侧的三排在翼型的跨度处以不同的斜率倾斜。

公开(公告)号：US06422819B1

公开(公告)日：2002-07-23

申请号：US09457652

申请日：1999-12-09

申请人： Gene C. F. Tsai ,  Sung Tung ,  Terence C. Flaherty ,  Robert F. Manning

发明人： Gene C. F. Tsai ,  Sung Tung ,  Terence C. Flaherty ,  Robert F. Manning

IPC分类号： F01D508

CPC分类号： F01D5/187 ,  F01D5/186 ,  F05D2250/12 ,  F05D2250/14 ,  F05D2260/202 ,  Y02T50/67 ,  Y02T50/673 ,  Y02T50/676

摘要： An airfoil for use in a gas turbine engine includes a pressure side and a suction side joined at a trailing edge wall that defines a trailing edge. The airfoil includes at least one cooling hole extending through the trailing edge wall so as to pass cooling fluid from the pressure side of the airfoil to the suction side.

摘要翻译： 用于燃气涡轮发动机的翼型件包括在限定后缘的后缘壁处连接的压力侧和吸力侧。 翼型件包括延伸穿过后缘壁的至少一个冷却孔，以将冷却流体从翼型的压力侧传递到吸入侧。

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。