Rotating Detonation Engines (RDEs) and Rotating Detonation Rocket Engines (RDREs) are novel types of high speed propulsion. RDEs and RDREs are combustors that utilize the pressure rise across a continuous detonation wave to increase the stagnation pressure of the system. This results in higher energy output compared to a traditional deflagrative combustor while also being more compact in design.

Currently, our computational team rapidly changes designs to improve overall system performance. They also investigate and develop tools to improve our understanding of these engines. Our experimental team works to validate the numerical models and provide insight through 1 to 1 campaigns in the lab space.

Liquid based combustion is sought after as propellants are stored as liquids due to increasingly cold temperatures. Accurately modeling the breakup from pure liquid to small droplets is important to understand how fuel is broken up and mixed with an oxidizer.

Currently, multiphase simulations are undergoing to model the breakup from a liquid reservoir to small droplets of liquid. Experimentally, the breakup can be tested using the supersonic wind tunnel to generate a constant crossflow. Both the computational and experimental teams work together to create and validate models to more accurately model liquid breakup.

Traditional turbines use constant airflow through a rotor to spin a shaft and generate electricity. For supersonic applications, the flow must be slowed down to allow the turbine to operate properly without shocks. Instead, a ‘wavy-walled’ design can be implemented to harness the energy of the supersonic flow. A helical geometry allows shocks to form on the body which create a force, and the helical design turns the system around a shaft. This process allows energy to be captured from a constant supersonic flow.

Currently, computational efforts are investigating the design of the helical geometry to optimize the power that can be extracted from the system. Experimentally, these designs are being tested in the supersonic wind tunnel to validate the computational models.