SBIR-STTR Award

We propose here a series of advancements leading to the design of robust and efficient rotating detonation engines (RDE) for rocket propulsion. We will begin with a comparative study of existing test data and perform detailed computational simulations of RDE design variants, focusing on improvements in performance - primarily mixing, followed by combustion efficiency, pressure drop, nozzle geometry, heat transfer, and others. We will then test a suitably modified RDE design to confirm initial hypotheses on design. Following this, we will study variations in fuels, the effects of scaling on RDE operation and performance metrics. This project will include design, fabrication, testing, and high-fidelity computational modeling (LES and RANS, with premixed and non-premixed models). Team members at HyPerComp Inc., and Purdue University have extensive experience in RDE development from computational as well as experimental perspectives with access to state of the art tools and facilities. There is abundant worldwide interest in RDEs at the present time. This effort seeks to extend existing knowledge, using newer tools and techniques and develop a high performance device with astrong foundation in design methodology.Pressure gain combustion, rotating detonation engine, Rocket propulsion, fuel injection, efficiency, design, Experiments, high fidelity modeling

We propose here a series of advancements leading to the design of robust and efficient rotating detonation engines (RDE) for rocket propulsion. We will begin with appropriate model upgrades to existing high-fidelity computational modeling tools for accurate modeling of RDE injector with liquid propellants. We will then perform a comparative study of existing test data and perform detailed computational simulations of RDE design variants, focusing on improvements in performance - primarily mixing, followed by combustion efficiency, pressure drop, nozzle geometry, heat transfer, and others. Team members at HyPerComp Inc. have extensive experience in RDE development from computational to experimental perspectives with access to state-of-the-art tools and facilities. There is abundant worldwide interest in RDEs at the present time. This effort seeks to extend existing knowledge, using newer tools and techniques and develop a high-performance device with a strong foundation in design methodology. In Phase II, we aim to understand and quantify efficiency and scaling of rocket RDEs, by high-fidelity modeling and analysis. Physical mechanisms in rocket RDE injectors will be developed and characterized. Numerical simulations will be used to drive design variants of the liquid RDE injectors. High-fidelity computational models will be upgraded with state-of-the-art models including conjugate heat transfer, adaptive mesh refinement, accurate flux scheme for supercritical combustion etc. Conjugate heat transfer in conjunction with LES will aid in understanding heat loads on the hardware which will be utilized for designing an efficient cooling system. Adaptive mesh refinement will help in accurate detonation wave resolution while minimizing overall computational costs.