Validating a Novel RDRE Nozzle Optimization Approach

Quadrus is pleased to present this Phase II proposal to continue development of a computational optimization approach for improving nozzle performance in rotating detonation rocket engines (RDRE). In Phase I, we demonstrated the feasibility of an advanced nozzle design optimization approach for a RDRE we call the Next-generation Enabling eXtreme Temperature RDRE, or NEXT-RDRE. NEXT-RDRE is an additively manufactured (AM) RDRE that uses the most advanced refractory materials in an optimized, lightweight configuration designed to provide excellent Isp performance while withstanding the punishing environment of detonative combustion. This Phase I effort focused on utilizing a combination of novel computational/simulation methods allowing strategic efforts to begin to define best practice for high area ratio nozzle design and optimization. Prior to our Phase I success, RDRE nozzle design and optimization was poorly understood due to unknown impacts of rotating detonation waves to fundamental gas dynamic expansion behavior. Our approach is meant to develop a best practice process in RDRE nozzle optimization, which required deep insight into how rotating detonation flow changes supersonic expansion behavior, particularly with upper stage and in-space nozzles with area ratios greater than 100. We resolved that approach by focusing on answering on the question “how much does the presence of rotating detonation waves superimposed on the primary axial flowfield affect nozzle performance?” Answering that question is directly relevant to the current goals of eliminating a primary technology gap toward fully exploiting the promise of enhanced RDRE performance. Our proposed effort will begin to collect hot fire testing data with a variety of low and moderate area ratio nozzle configurations and will lay the groundwork for extending the process to nozzle area ratios >100. Our intended near term application is to a GCP-funded RDRE development being led at MSFC.