Optimal mesh generation for a non-iterative grid-converged solution of flow through a blade passage using deep reinforcement learning

TL;DR

This paper introduces a deep reinforcement learning-based method for automatic, non-iterative mesh generation in CFD analysis of blade passages, achieving optimal accuracy and efficiency across various configurations.

Contribution

The paper presents a novel multi-agent DRL approach that trains a mesh generator to produce optimal meshes for diverse blade geometries without iterative tuning.

Findings

Meshes produce converged solutions at desired costs in a single simulation.

Method effectively handles complex flow phenomena like shock waves and flow separation.

Robust across various blade geometries and flow conditions.

Abstract

An automatic mesh generation method for optimal computational fluid dynamics (CFD) analysis of a blade passage is developed using deep reinforcement learning (DRL). Unlike conventional automation techniques, which require repetitive tuning of meshing parameters for each new geometry and flow condition, the method developed herein trains a mesh generator to determine optimal parameters across varying configurations in a non-iterative manner. Initially, parameters controlling mesh shape are optimized to maximize geometric mesh quality, as measured by the ratio of determinants of Jacobian matrices and skewness. Subsequently, resolution-controlling parameters are optimized by incorporating CFD results. Multi-agent reinforcement learning is employed, enabling 256 agents to construct meshes and perform CFD analyses across randomly assigned flow configurations in parallel, aiming for maximum simulation accuracy and computational efficiency within a multi-objective optimization framework. After training, the mesh generator is capable of producing meshes that yield converged solutions at desired computational costs for new configurations in a single simulation, thereby eliminating the need for iterative CFD procedures for grid convergence. The robustness and effectiveness of the method are investigated across various blade passage configurations, accommodating a range of blade geometries, including high-pressure and low-pressure turbine blades, axial compressor blades, and impulse rotor blades. Furthermore, the method is capable of identifying the optimal mesh resolution for diverse flow conditions, including complex phenomena like boundary layers, shock waves, and flow separation. The optimality is confirmed by comparing the accuracy and the efficiency achieved in a single attempt with those from the conventional iterative optimization method.