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1. 发明授权

US06280140B1 Method and apparatus for cooling an airfoil 有权
标题翻译：用于冷却机翼的方法和装置
公开(公告)号：US06280140B1
公开(公告)日：2001-08-28
申请号：US09442922
申请日：1999-11-18
申请人： Friedrich O. Soechting , William A. Kvasnak , Thomas A. Auxier , James P. Downs , William H. Calhoun , Douglas A. Hayes
发明人： Friedrich O. Soechting , William A. Kvasnak , Thomas A. Auxier , James P. Downs , William H. Calhoun , Douglas A. Hayes
IPC分类号： F01D518
CPC分类号： F23R3/002 , F01D5/184 , F01D5/186 , F05D2250/70 , F05D2260/221 , F05D2260/2214
摘要： An apparatus and method for cooling a wall for use in a gas turbine engine is provided that includes a cooling air passage having a plurality of segments connected in series by one or more chambers, an inlet aperture, and an exit aperture. The inlet aperture connects the cooling air passage to one side of the wall. The exit aperture connects the cooling air passage to the opposite side of the wall. Cooling air on the inlet aperture side of the wall enters the cooling air passage through the inlet aperture and exits through the exit aperture.
摘要翻译：提供一种用于冷却用于燃气涡轮发动机的壁的装置和方法，其包括具有通过一个或多个室串联连接的多个段的冷却空气通道，入口孔和出口孔。入口孔将冷却空气通道连接到墙的一侧。出口孔将冷却空气通道连接到壁的相对侧。壁的入口孔侧的冷却空气通过入口孔进入冷却空气通道，并通过出口孔离开。

2. 发明授权

US06419446B1 Apparatus and method for inhibiting radial transfer of core gas flow within a core gas flow path of a gas turbine engine 有权
标题翻译：用于抑制燃气涡轮发动机的核心气体流动路径内的核心气体流的径向传递的装置和方法
公开(公告)号：US06419446B1
公开(公告)日：2002-07-16
申请号：US09468751
申请日：1999-12-21
申请人： William A. Kvasnak , Friedrich O. Soechting , Karen A. Thole , Gary A. Zess
发明人： William A. Kvasnak , Friedrich O. Soechting , Karen A. Thole , Gary A. Zess
IPC分类号： F01D904
CPC分类号： F01D9/041 , F01D5/145 , Y10S415/914
摘要： A method for inhibiting radial transfer of core gas flow away from a center radial region and toward the inner and outer radial boundaries of a core gas flow path within a gas turbine engine is provided that includes the steps of: (1) providing a flow directing structure that includes an airfoil that abuts a wall surface, said airfoil having a leading edge, a pressure side, and a suction side; and (2) increasing the velocity of the core gas flow in the area where the leading edge of the airfoil abuts the wall. Increasing the velocity of the core gas flow in the area where the leading edge of the airfoil abuts the wall impedes the formation of a pressure gradient along the surface of the airfoil that forces core gas from the center region of the core gas toward the wall. The apparatus includes apparatus for diverting core gas flow away from the area where the airfoil abuts the wall.
摘要翻译：提供了一种用于抑制核心气体流离开中心径向区域并朝向燃气涡轮发动机内的核心气体流动路径的内部和外部径向边界的径向转移的方法，其包括以下步骤：（1）提供流动导向包括邻接壁面的翼型的结构，所述翼型具有前缘，压力侧和吸力侧; 和（2）增加翼型件的前缘邻接壁的区域中的核心气流的速度。增加翼型件的前缘邻接壁的区域中的核心气流的速度阻碍沿着翼型的表面形成压力梯度，该压力梯度迫使核心气体从核心气体的中心区域朝向壁。该装置包括用于使核心气体流离开机翼抵靠壁的区域的装置。

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