Summary of Recent Research on Detonation Wave Engines at UTA
A survey of recent research at UTA on detonation waves related to propulsion is presented in this paper. A brief historical review of the early pulse detonation engine (PDE) research at UTA is provided to lay the background for the development of a large-scale PDE Ground Demonstrator. Also current activities related to the development of rotating detonation wave engines (RDE) are reviewed. System integration studies for both PDE- and RDE-based propulsion systems are summarized, followed by a brief description of two programs focusing on application of detonation waves to hypersonic flow simulation and power generation.
Experiences in Testing of a Large-Scale, Liquid-Fueled, Air-Breathing, Pulse Detonation Engine
A large-scale pulse detonation engine utilizing air and kerosene was constructed to demonstrate its practical implementation. Testing this ground demonstrator revealed successes and areas requiring improvement in the design, fabrication, installation and actual testing of a large PDE. Many of the challenges of translating smaller, single shot experiments have been overcome in this implementation of a 4 inch diameter detonation engine. This paper will discuss the experiences in testing the engine as a whole, and also on some of these subsystems involved. Full testing has not been completed, but successful operation provides a positive outlook for further innovation and modification.
Some perspectives on pulse detonation propulsion systems
Pulse detonation engines and rockets (PDE/Rs) can potentially revolutionize air breathing and rocket propulsion [1, 2, 3, 4, 5, 6]. While the PDE concept is over five decades old, it has recently enjoyed renewed interest, due mostly to theoretical and computational studies indicating high cycle efficiencies. When modeled by a constant volume, Humphrey cycle, the detonation engine is found to be superior to that of existing constant pressure, Brayton cycles, with claims of as much as 10–40% improvement in specific impulse [4,7, 8, 9]. The constant volume process is derived from the Zeldovich-von Neumann-Doring (ZND) model of the detonation wave as a high strength shock wave, followed by a region of chemical reaction and a subsequent isentropic rarefaction. Amongst other advantages of the PDE is simplicity, where the PDE is easy to manufacture and requires few moving parts, with the possibility of eliminating high-pressure pumps in rocket applications, or reducing turbomachinery stages in air-breathing propulsion systems.