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1. 发明授权

US5261789A Tip cooled blade 失效
标题翻译：尖端冷却刀片
公开(公告)号：US5261789A
公开(公告)日：1993-11-16
申请号：US935065
申请日：1992-08-25
申请人： Don Butts , John G. Nourse , Robert C. Simmons
发明人： Don Butts , John G. Nourse , Robert C. Simmons
IPC分类号： F01D5/18 , F01D5/20
CPC分类号： F01D5/186 , F01D5/20 , Y02T50/672 , Y02T50/673 , Y02T50/676
摘要： A gas turbine engine blade includes an airfoil having first and second sides and a dovetail extending from the airfoil root. The airfoil includes a tip having a tip floor with first and second tip walls extending from the floor and spaced apart to define therebetween a tip pienum. The first tip wall is recessed at least in part from the airfoil first side to define an outwardly facing tip shelf, with the tip shelf and the first tip wall defining therebetween a trough. A plurality of cooling holes extend through the tip floor at the tip shelf for channeling cooling air from a flow channel inside the airfoil into the trough for cooling the blade tip.
摘要翻译：燃气涡轮发动机叶片包括具有第一和第二侧面的翼型和从翼型根延伸的燕尾榫。翼型件包括具有尖端底部的尖端，其具有从地板延伸并间隔开的第一和第二尖端壁，以在其间限定尖端。第一尖端壁至少部分地从翼型件第一侧凹入以限定向外的尖端架，其中尖端架和第一顶端壁在其间限定槽。多个冷却孔在尖端搁架处延伸穿过顶部底部，用于将冷却空气从翼型内的流动通道引导到槽中以冷却叶片尖端。

2. 发明授权

US5511946A Cooled airfoil tip corner 失效
标题翻译：冷却翼型尖端角
公开(公告)号：US5511946A
公开(公告)日：1996-04-30
申请号：US361242
申请日：1994-12-08
申请人： Ching-Pang Lee , Gary E. Wheat , Barry T. Malone , Nicholas C. Palmer , Robert C. Simmons
发明人： Ching-Pang Lee , Gary E. Wheat , Barry T. Malone , Nicholas C. Palmer , Robert C. Simmons
IPC分类号： F01D5/18
CPC分类号： F01D5/182
摘要： A gas turbine engine airfoil includes a tip corner disposed at the juncture of the airfoil tip and trailing edge, and a cooling hole extends therethrough in direct flow communication with an internal cooling passage thereof. A cross-hole extends perpendicularly into the tip corner and into the cooling hole for discharging from the airfoil a portion of cooling air channeled into the cooling hole. The airfoil tip corner is therefore cooled by the air channeled through the cross-hole received from the intersecting cooling hole.
摘要翻译：燃气涡轮发动机翼型件包括设置在翼型末端和后缘的接合处的顶角，并且冷却孔与其内部冷却通道直接流动连通地延伸穿过其中。十字孔垂直延伸到顶角并进入冷却孔，用于从翼型件排出一部分冷却空气引导到冷却孔中。因此，翼型顶端角由通过从交叉冷却孔接收的交叉孔引导的空气冷却。

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