公开(公告)号：US07371048B2

公开(公告)日：2008-05-13

申请号：US11140631

申请日：2005-05-27

申请人： James P. Downs ,  Norman F. Roeloffs ,  Edward Pietraszkiewicz ,  David Michael Kontrovitz ,  Takao Fukuda

发明人： James P. Downs ,  Norman F. Roeloffs ,  Edward Pietraszkiewicz ,  David Michael Kontrovitz ,  Takao Fukuda

IPC分类号： F01D5/18

CPC分类号： F01D5/186 ,  F01D5/187 ,  F05D2240/122 ,  F05D2240/126 ,  F05D2240/304 ,  F05D2250/711 ,  F05D2250/712

摘要： A turbine blade system for a gas turbine engine includes a turbine blade having a trailing edge region extending in a lateral direction and in a lengthwise direction from a pressure side surface to a trailing edge. The trailing edge region includes a plurality of riblets extending in the lengthwise direction from the pressure side surface toward the trailing edge. The trailing edge region defines a plurality of ejection slots each laterally disposed between two of the riblets. The plurality of riblets each define an upper surface having at least a portion in the lengthwise direction being curved relative to the pressure side surface so as to generally shield the upper surface from a high heat load propagating from the pressure side surface and to facilitate cooling air flowing from the ejection slots to flow over the upper surface.

摘要翻译： 一种用于燃气涡轮发动机的涡轮机叶片系统包括涡轮叶片，其具有在侧向方向上延伸的后缘区域以及从压力侧表面到后缘的长度方向。 后缘区域包括从压力侧表面向后缘沿长度方向延伸的多个肋条。 后缘区域限定多个排出槽，每个排出槽横向设置在两个肋之间。 多个肋条每个限定上表面，其具有相对于压力侧表面弯曲的长度方向上的至少一部分，以便将上表面大致屏蔽从压力侧表面传播的高热负荷，并促进冷却空气 从喷射槽流出以流过上表面。

公开(公告)号：US07334992B2

公开(公告)日：2008-02-26

申请号：US11140786

申请日：2005-05-31

申请人： James P. Downs ,  Norman F. Roeloffs ,  Edward F. Pietraszkiewicz

发明人： James P. Downs ,  Norman F. Roeloffs ,  Edward F. Pietraszkiewicz

IPC分类号： F01D5/18

CPC分类号： F01D5/186 ,  F01D5/187 ,  F05D2250/711 ,  F05D2250/712 ,  F05D2260/201 ,  F05D2260/202

摘要： A turbine blade cooling system for a gas turbine engine includes a turbine blade having a trailing edge, a concave side, and a convex side. The trailing edge defines at least one set of impingement holes each having a central longitudinal axis which is closer to a nearest portion of an edge of the blade at one of the concave and convex sides relative to a nearest portion of an edge of the blade at the other of the concave and convex sides. Alternatively or in addition to the foregoing, the trailing edge can define at least one set of impingement holes each having a central longitudinal axis which is angled in a direction of a flow of cooling medium toward one of the concave and convex sides relative to the other of the concave and convex sides.

摘要翻译： 用于燃气涡轮发动机的涡轮叶片冷却系统包括具有后缘，凹侧和凸侧的涡轮叶片。 后缘限定至少一组冲击孔，每组冲击孔具有中心纵向轴线，该中心纵向轴线相对于叶片的边缘的最近部分在相对于叶片的边缘的最近部分处于相对于叶片的边缘的最靠近部分处更靠近叶片的边缘的最近部分 另一个凹凸边。 或者或除了上述之外，后缘可以限定至少一组冲击孔，每组冲击孔具有中心纵向轴线，所述中心纵向轴线在冷却介质的流动方向上相对于另一组的凹凸侧面 的凹凸边。