Generalizable Data-Driven Modeling Framework for Understanding and Modeling Turbulent Combustion
Abstract
Turbulent combustion physics in aerospace systems typically features interactions between turbulence and chemical reactions that span a wide range of temporal and spatial scales. Even with the rapid advancement in high performance computing, direct numerical simulations (DNS) remain restricted to small-scale turbulent combustion problems. While large-eddy simulations (LES) are well suited to model large-scale physics, the effects of small-scale physics must be incorporated through closure models, most of which are assumption-based and cannot represent the true physics, especially at practical conditions in aerospace systems. Against this landscape, the objective of the present proposal is to formulate a systematic and generally applicable datadriven modeling framework to1) inform effective reduced-order models (ROMs) from DNS to represent subgrid-scale (SGS) or subfilter-scale (SFS) physics (referred to as DNS-ROM); and 2) enhance LES by incorporating DNS-ROM for SGS/SFS physics to enable efficient and accurate turbulent combustion simulations in aerospace systems. To achieve this goal, a hybrid LES/DNS-ROM framework is proposed with the DNS-informed SFS/SGS physics integrated into LES, which contains two major developmental components: -DNS-ROM development focuses on constructing efficient and predictive ROM(s) for SGS/SFS physics through mathematically formal model reduction formulations based on a minimal number of turbulent combustion DNS calculations to represent small-scale physics that cannot be resolved by LES. -LES/DNS-ROM coupling aims at architecting a modeling framework that can provide accurate predictions of turbulent combustion in aerospace systems. The main goal is to transfer the resolved-scale information from LES to DNS-ROM while effectively integrating the SGS/SFS information from DNS-ROM into LES for turbulent reacting flow simulations in practical aerospace systems.The proposed hybrid LES/DNS-ROM framework establishes a promising path towards novel and intelligent computational tools for turbulent combustion simulations, applicable to a wide range of aerospace systems, including liquid rocket engines, gas turbine engines, rotating detonation engines, and scramjets.
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- Feb 29, 2024
- Source ID
- FA95502310211
Entities
People
- Cheng Huang
Organizations
- Air Force Office of Scientific Research
- United States Air Force
- University of Kansas