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公开(公告)号：US5980209A
公开(公告)日：1999-11-09
申请号：US884091
申请日：1997-06-27
CPC分类号： F01D5/141 , F01D5/187 , Y10S416/05
摘要： A first-stage turbine blade includes an airfoil having a profile according to Table I. The airfoil has a plurality of cooling air passages extending linearly from the root portion to the tip portion of the airfoil. The blade includes a shank having a pair of cavities in communication through the blade dovetail with a plenum in the wheel space for supplying cooling air to the passages in the airfoil. The cooling passages in the airfoil terminate in a recess at the tip portion which has an opening adjacent the trailing edge of the airfoil and along the suction side to enable egress of cooling air into the hot gas stream on the low pressure side of the airfoil. The majority of the cooling passages are turbulated. Certain of those passages are arranged in rows lying adjacent to the pressure and suction sides of the airfoil.
摘要翻译： 第一级涡轮机叶片包括具有根据表I的轮廓的翼型件。翼型件具有多个冷却空气通道，该冷却空气通道从翼部的根部直线延伸到翼型部分。 叶片包括具有一对空腔的柄，所述一对空腔通过叶片燕尾榫与在车轮空间中的增压室连通，用于向翼型中的通道供应冷却空气。 翼型件中的冷却通道终止在尖端部分处的凹部中，该凹部具有与翼型件的后缘相邻并且沿着吸力侧的开口，以使冷却空气能够排出到翼型的低压侧上的热气流中。 大部分冷却通道是混浊的。 这些通道中的某些通道排列成与翼型的压力和吸力侧相邻的排。
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公开(公告)号：US5738491A
公开(公告)日：1998-04-14
申请号：US778529
申请日：1997-01-03
CPC分类号： F01D11/18 , F01D5/147 , F01D5/187 , F01D5/20 , F01D5/28 , F05D2260/205 , F05D2260/221 , F05D2260/2322 , F05D2300/5024 , Y02T50/673 , Y02T50/676
摘要： A turbine blade includes an airfoil having a root, tip cap, and laterally opposite pressure and suction sides extending between leading and trailing edges. A cooling circuit is disposed inside the airfoil and extends from the tip cap to the root for circulating a coolant. The airfoil also includes a pair of squealer tips extending radially upwardly from the tip cap along the pressure and suction sides which are spaced apart from the leading to trailing edges to define an upwardly open tip cavity. A thermal conductor is fixedly joined to the squealer tips and extends radially inwardly to the tip cap for conducting heat thereto for removal by the coolant. The conductor preferably surrounds the tip cavity inboard of the squealer tips and is coextensive therewith for being protected thereby.
摘要翻译： 涡轮机叶片包括具有根部，顶端盖和在前缘和后缘之间延伸的横向相对的压力和吸力侧的翼型件。 冷却回路设置在翼型件的内部，并且从顶盖延伸到根部以使冷却剂循环。 翼型件还包括一对从尖端沿径向向上延伸的尖叫尖端，其沿着压力和吸力侧分开，该侧面与前至后缘间隔开以限定向上开口的尖端腔。 热导体固定地连接到尖叫尖端，并且径向向内延伸到尖端盖，用于传导热量以便被冷却剂除去。 导体优选地围绕尖叫尖端的尖端空腔，并且与其共同延伸以便被保护。
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公开(公告)号：US4826400A
公开(公告)日：1989-05-02
申请号：US947457
申请日：1986-12-29
申请人： Brent A. Gregory
发明人： Brent A. Gregory
CPC分类号： F01D5/141 , Y02T50/673 , Y10S415/914
摘要： A turbomachinary airfoil in one form comprises a pressure side and a suction side curved circumferentially outward in the direction that the suction side faces. The invention is effective for reducing both radial and circumferential boundary layer pressure gradients thereby reducing airfoil aerodynamic losses. In another form of the invention the airfoil is a vane of a turbine vane assembly having an inner and outer shroud wherein the vane in addition to being curved is leaned circumferentially outward in the direction that the suction side faces.
摘要翻译： 一种形式的涡轮机翼型包括沿吸力侧面向外周向外侧弯曲的压力侧和吸力侧。 本发明对于减小径向和周向边界层压力梯度是有效的，从而减少翼型空气动力学损失。 在本发明的另一形式中，翼型件是具有内护罩和外护罩的涡轮叶片组件的叶片，其中除了弯曲的叶片之外，叶片沿吸力侧面朝向周向外侧。
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