Patent ID: 9230055
Filing Date: 2016-01-05
CPC Classification: G06F

Claim Text:
1. A method of optimizing film cooling performance for turbomachinery components, the method comprising: defining a set of cooling hole designs, each design consisting of a predefined hole pattern including a plurality of different film cooling row patterns and placements which are a representative subset of a cooling hole pattern of an implementation pattern, and within each pattern there is axial and radial hole location variability; defining a design space by selecting process variables and limits for film cooling of turbomachinery components; defining sectors throughout the high pressure surface of a turbine vane, providing a random initial population of pressure side turbine vane cooling designs derived from the set of cooling hole designs by placing the implementation pattern represented by the predefined hole pattern of the cooling hole designs in any one of the sectors of the turbine vane; evaluating the film cooling performance of each design of the initial population of cooling designs; vary the process variables across the design space while iteratively performing in order: determining a fitness function value based on predicted heat transfer performance from 3-D CFD of each of the evaluated designs of the population of cooling designs, selecting a half of the population of cooling designs having higher fitness function values, randomly pairing designs of the selected half of the population of cooling designs to generate two new designs from each random pair of designs forming a new population of cooling designs, evaluating the film cooling performance of each design of the new population of cooling designs; and selecting a set of the cooling designs that maximizes cooling effectiveness and minimizes area-averaged heat transfer over the high pressure surface side of the turbine vane.