Patent ID: 9322280
Filing Date: 2016-04-26
CPC Classification: F01D,F05D,Y10T

Claim Text:
1. A method of designing a turbine blade, the method comprising the steps of: forming at least two notches on a tip of a turbine blade having a pressure side and a suction side, wherein each of the at least two notches have a known radius, at least one of the at least two notches is located on one of the pressure side and the suction side, and each of the at least two notches have a different radii; operating a gas turbine engine including the turbine blade to expand a radial length of the turbine blade such that the tip of the turbine blade engages a casing; rubbing the tip of the turbine blade against the casing to wear away a portion of the tip and at least a portion of at least one of the two notches; viewing the tip of the turbine blade after the step of operating of the gas turbine engine; determining an appearance of the at least two notches and the tip; and determining a manufacturing length of the turbine blade based on the step of determining the appearance the at least two notches.