Towards Exascale Computation for Turbomachinery Flows

TL;DR

This paper presents a scalable large eddy simulation code for turbomachinery flows, achieving exascale performance on a high-pressure turbine simulation with over a billion mesh elements, advancing towards full engine modeling.

Contribution

Developed a high-performance, scalable LES code for compressible turbomachinery flows that leverages heterogeneous architectures and achieves exascale-level performance.

Findings

Achieved 115.8 DP-PFLOPs on a large turbine cascade simulation.

Successfully simulated over 1.69 billion mesh elements and 865 billion DOFs.

Progressed towards comprehensive engine simulations with all aerodynamic and heat transfer components.

Abstract

A state-of-the-art large eddy simulation code has been developed to solve compressible flows in turbomachinery. The code has been engineered with a high degree of scalability, enabling it to effectively leverage the many-core architecture of the new Sunway system. A consistent performance of 115.8 DP-PFLOPs has been achieved on a high-pressure turbine cascade consisting of over 1.69 billion mesh elements and 865 billion Degree of Freedoms (DOFs). By leveraging a high-order unstructured solver and its portability to large heterogeneous parallel systems, we have progressed towards solving the grand challenge problem outlined by NASA, which involves a time-dependent simulation of a complete engine, incorporating all the aerodynamic and heat transfer components.