公开(公告)号：US20130039773A1

公开(公告)日：2013-02-14

申请号：US13208983

申请日：2011-08-12

申请人： Stanley J. Funk ,  Edward F. Pietraszkiewicz

发明人： Stanley J. Funk ,  Edward F. Pietraszkiewicz

IPC分类号： F01D5/14 ,  B21K3/04

CPC分类号： F01D21/003 ,  F01D5/141 ,  F01D5/20 ,  F01D25/24 ,  F05D2220/32 ,  F05D2230/50 ,  F05D2240/307 ,  F05D2260/83 ,  Y10T29/49336

摘要： A method of designing a turbine blade includes the steps of forming at least two notches on a tip of a turbine blade, each of the at least two notches having a known dimension. The turbine blade has a pressure side and a suction side. The method further includes the step of operating a gas turbine engine including the turbine blade to expand a length of the turbine blade such that the tip of the turbine engages a casing. The method further includes the steps of viewing the tip of the turbine blade after the step of operating of the gas turbine engine, determining an appearance of the notches on the tip and determining a manufacturing length of the turbine blade based on the step of determining the appearance the notches.

摘要翻译： 设计涡轮叶片的方法包括以下步骤：在涡轮机叶片的尖端上形成至少两个切口，所述至少两个切口中的每一个具有已知尺寸。 涡轮叶片具有压力侧和吸力侧。 该方法还包括操作包括涡轮机叶片的燃气涡轮发动机的步骤，以使涡轮机叶片的长度膨胀，使得涡轮机的顶端接合壳体。 该方法还包括以下步骤：在操作燃气涡轮发动机的步骤之后观察涡轮叶片的尖端，确定尖端上的凹口的外观，并且基于确定涡轮叶片的步骤确定涡轮叶片的制造长度 出现缺口。