Artes

Proceedings of ENCIT 2010 Copyright © 2010 by ABCM

13th Brazilian Congress of Thermal Sciences and Engineering December 05-10, 2010, Uberlandia, MG, Brazil

SINGLE-SHOT PULSED DETONATION DEVICE FOR PDE COMBUSTION SIMULATION
Carla S. T. Marques, [e-mail] Antonio C. de Oliveira, [e-mail]
Aerothermodynamic and Hypersonic Division, Institute of Advanced Studies – Department of Aerospatial Science and Technology, Rodovia dos Tamoios, km 5.5, 12228-001 São José dos Campos – SP, Brazil

Fernando B. Dovichi Filho William C. Ferraz
Aerothermodynamic and Hypersonic Division, Institute of Advanced Studies – Department of Aerospatial Science and Technology, Rodovia dos Tamoios, km 5.5, 12228-001 São José dos Campos – SP, Brazil

José B. Chanes Jr., [e-mail]
Aerothermodynamic and Hypersonic Division, Institute of Advanced Studies – Department of Aerospatial Science and Technology, Rodovia dos Tamoios, km 5.5, 12228-001 São José dos Campos – SP, Brazil

Abstract. In this work, a single-shot pulsed detonation device for experimental simulation of the PDE combustion conditions in supersonic and hypersonic flight regimes (M∞ ≤ 6) is proposed. The combustion device is composed of: ignition system, detonation tube without obstacles, divergent nozzle and test chamber. A nanosecond spark discharge has been developed to promote a direct detonation initiation or a DDT in the shortest distance possible. Pulses of approximately 25, 65 and 80 ns (FHWM) were acquired. Emission and Schlieren images were taken to characterize the spark discharge. The pulsed detonation device was planned to achieve typical specific impulse (Isp ≈ 200s) for a single-shot PDE. 1-D calculations were performed to establish the combustion conditions for experimental tests. Flight conditions between 0 and 20,000 m of altitude fueled with H2/air and C2H4/air mixtures were calculated within 0.5-1.5 atm range of initial pressure at different equivalence ratios for two nozzle