The project was conducted by Hertzel Kadosh under the supervision of Assis. Prof. Dan Michaeles
Pulse detonation rocket engine burns the fuel and oxidizer using detonation waves. In this study, we investigate the use of a pulse detonation engine as an ignition system for ramjet or scramjet engines using liquid hydrocarbon fuels, which are known for their challenging conditions for ignition and combustion. Unlike conventional deflagration-based gas generators, in detonation engines, the combustion products are expelled behind a very strong shock wave, which has significant benefits for ignition. It increases the temperature and pressure of the fuel-air mixture and enhances mixing with the igniter’s combustion products. However, although a study on pulse detonation devices started at the 60th, a pulse detonation igniter is a new application with limited published information and knowledge. The goal of this research is to develop scientific knowledge on the main physical stages of a pulse detonation igniter. The experimental study focuses on characterizing the deflagration to detonation transition of different liquid fuels with oxygen, detonation propagation in curved tubes, and the interaction of the detonation wave with a fuel spray. Understanding these phenomena will enable the design and integration of a pulse detonation igniter.