Performance Measurements of a Kerosene-Oxygen Pulse Detonation Rocket Engine at the Frequencies of 35-40Hz

Abstract

With the goal of further increasing the operation frequency of PDRE, some measures were taken and a series of experimental studies were performed on a kerosene-oxygen pulse detonation rocket engine (PDRE) model. The PDRE detonation model was constructed of a steel pipe of 850mm length (LPDRE) and 30mm (DPDRE) diameter. The model was performed with liquid kerosene as fuel, compressed oxygen as oxidizer and nitrogen as purge gas, and was ignited by a spark with low energy. The supplies of fuel, oxidizer and purge gas are controlled by solenoid valves respectively. The main performance parameters, thrust and the pressure along the length of the model were measured at the frequencies of 35-40Hz. Thrust calibration test was conducted to get more accurate thrust. The measured results showed the operation frequency of the PDRE model can reach up to 40Hz, which as we know is so far the maximum operation frequency of PDRE with solenoid valves and liquid fuel. When the operation frequency is 35Hz, the peak value of detonation wave pressure is more than 3.4 MPa and the time-averaged thrust of PDRE is 43.9N. The peak value of detonation wave pressure is about 3.2 MPa and the time-averaged thrust of PDRE is 50N while the operation frequency is 40Hz. Nomenclature PDE = Pulse detonation engine PDRE = Pulse detonation rocket engine DDT = Deflagration-to-detonation transition P1 = Pressure at position 1 along the PDRE model Pi = Pressure at position i along the PDRE model det V = detonation wave speed