Patent ID: 9631498
Date: 2017-04-25
CPC Classifications: F01D,F05D

Claim:
1. A method of configuring film cooling holes through which a cooling medium is ejected onto an outer surface of a gas turbine blade, comprising the steps of: calculating a direction of principal strain in the film cooling holes by means of a heat transfer analysis and a structural analysis using a finite element analysis model of the gas turbine blade for which boundary conditions have been set based on operating conditions of the gas turbine, the boundary conditions for the heat transfer analysis being one of thermal conditions including gas temperature, heat transfer coefficient, and heat radiation coefficient, and the boundary conditions for the structural analysis being one of loading conditions including pressure, centrifugal force, and acceleration; and making an angle between the direction of a longitudinal axis of the film cooling holes and the calculated direction of the principal strain less than or equal to 15 degrees; making the direction of the longitudinal axis of the film cooling holes aligned with a span direction of the gas turbine blade when the direction of principal strain is within a range of 15 degrees from the span direction of the gas turbine blade; and making the direction of the longitudinal axis of the film cooling holes aligned with a chord direction of the gas turbine blade when the direction of principal strain is within a range of 15 degrees from the chord direction of the gas turbine blade; and wherein the gas turbine blade is made of a nickel-base superalloy having anisotropy and the film cooling holes having a noncircular elliptical shape at a surface of the gas turbine blade or a section parallel to the surface of the gas turbine blade.