New Paradigms in High Pressure Combustion Dynamics Prediction and Control

ABSTRACT: The proposed work aims to build a physics-based rapid turnaround simulation capability for resolving combustion dynamics in liquid rocket engines operating at trans-critical and supercritical flow regimes. The methodology will explore both Reduced-Order Methods and Reduced-Basis Methods as potential candidates for efficient unsteady flow simulation, data storage and retrieval, and data reduction, as well as system identification and transformation of data to information and knowledge to support decision making at all levels. BENEFIT: This capability helps simulate, analyze, and predict combustion dynamics in rocket engines and gas turbine combustors at a computational cost about an order of magnitude less than what is currently needed. The increased efficiency comes with error bounds within tolerance levels that can be specified at run time. The building blocks of this methodology can also be used in data reduction and feature extraction in post processing field data from an unsteady-flow simulation. It has the potential to compress unsteady flow data to manageable levels for storage. In addition, the work will provide a basis for establishing practical means for transformation of data to knowledge to support decision making at all levels.