公开(公告)号：US06435813B1

公开(公告)日：2002-08-20

申请号：US09568441

申请日：2000-05-10

申请人： Harold Paul Rieck, Jr. ,  Omer Duane Erdmann

发明人： Harold Paul Rieck, Jr. ,  Omer Duane Erdmann

IPC分类号： F01D906

CPC分类号： F01D25/12 ,  F01D5/188 ,  F05D2260/201 ,  F05D2260/205

摘要： An airfoil for use in a gas turbine engine. The airfoil includes a body having an interior surface defining a hollow cavity in the airfoil having an inlet and an outlet. The airfoil also includes a partition within the cavity dividing the cavity into a first cooling passage and a second cooling passage. The first cooling passage communicates with the inlet for delivering cooling air to the first passage and the second cooling passage communicates with the outlet for exhausting cooling air from the second passage. The partition has a cooling hole therein extending between the first passage and the second passage permitting cooling air to pass from the first passage to the second passage. The cooling hole is sized and positioned with respect to the interior surface of the airfoil for directing cooling air toward a portion of the interior surface of the airfoil so the cooling air impinges upon the portion. Thus, cooling air entering the inlet of the cavity travels through the first passage for cooling the body by convective heat transfer, through the cooling hole for impinging upon the portion of the interior surface of the body, through the second passage to cool the body by convective heat transfer, and out the outlet of the cavity.

摘要翻译： 用于燃气涡轮发动机的翼型件。 翼型件包括具有限定在翼型件中的空腔的内表面的主体，其具有入口和出口。 翼型件还包括在空腔内的分隔件，其将空腔分成第一冷却通道和第二冷却通道。 第一冷却通道与用于将冷却空气输送到第一通道的入口连通，第二冷却通道与出口连通，以从第二通道排出冷却空气。 分隔件具有在第一通道和第二通道之间延伸的冷却孔，允许冷却空气从第一通道传递到第二通道。 冷却孔的尺寸和相对于翼型件的内表面定位，用于将冷却空气引导到翼型件的内表面的一部分，使得冷却空气冲击该部分。 因此，进入空腔入口的冷却空气穿过第一通道，用于通过对流热传递冷却主体，通过冷却孔冲击身体内表面的一部分，穿过第二通道，以通过第二通道冷却身体 对流传热，并从腔的出口出来。

公开(公告)号：US06431820B1

公开(公告)日：2002-08-13

申请号：US09796967

申请日：2001-02-28

申请人： Robert John Beacock ,  Omer Duane Erdmann ,  Robert Edward Athans ,  Harold Paul Rieck, Jr.

发明人： Robert John Beacock ,  Omer Duane Erdmann ,  Robert Edward Athans ,  Harold Paul Rieck, Jr.

IPC分类号： F01D906

CPC分类号： F01D5/188 ,  F01D9/041 ,  F01D25/12 ,  F05D2260/201 ,  F05D2260/205 ,  Y02T50/671 ,  Y02T50/676

摘要： A turbine for a gas turbine engine including a turbine nozzle assembly that facilitates reducing an operating temperature of rotor blades in a cost-effective and reliable manner is described. Each rotor blade includes a tip that rotates in close proximity to a shroud that extends circumferentially around the rotor assembly. The turbine nozzle assembly includes a plurality of turbine vane segments that channel combustion gases to downstream rotor blades. Each turbine vane segment extends radially outward from an inner platform and includes a tip, a root, and a body that extends therebetween. The turbine vane segment tip is formed integrally with an outer band that mounts the vane segments within the gas turbine engine. The outer band is in flow communication with a cooling fluid source, and includes at least one opening.

摘要翻译： 描述了一种用于燃气涡轮发动机的涡轮机，其包括涡轮喷嘴组件，其有助于以成本有效且可靠的方式降低转子叶片的操作温度。 每个转子叶片包括尖端，该尖端沿着围绕转子组件周向延伸的护罩紧密地旋转。 涡轮喷嘴组件包括多个涡轮叶片段，其将燃烧气体引导到下游转子叶片。 每个涡轮叶片段从内平台径向向外延伸，并包括在其间延伸的尖端，根部和本体。 涡轮叶片节段末端与将叶片段安装在燃气涡轮发动机内的外带一体地形成。 外带与冷却流体源流动连通，并且包括至少一个开口。