This invention belongs to the field of aero-engine cooling design and flow
heat transfer optimization technology. It provides a method,
system, configuration, and blade for constructing
turbine blade cooling fringe based on
level set topology optimization. The method includes: constructing a fluid-structure interaction (FSI)
computational model encompassing the fluid domain of the
cooling channel and the
solid domain of the blade wall; defining a
level set function to implicitly represent the two-phase region; establishing a unified set of governing equations covering the entire computational domain based on this function; introducing a velocity suppression mechanism in the
solid domain to perform single-domain
coupling solution of fluid flow and
solid heat conduction; constructing an optimization model based on the
physical field solution, with cooling performance as the objective function and fringe
volume fraction as the constraint; calculating the sensitivity of the objective function to the
level set function; using this sensitivity to drive the
level set function update to evolve the fringe boundary; iterating until convergence to output the final fringe geometry. This invention does not require pre-setting the fringe type and can automatically generate irregular fringe structures with
high heat transfer efficiency and low flow resistance.