TY - JOUR
T1 - Supersonic combustion induced by reflective shuttling shock wave in fan-shaped two-dimensional combustor
AU - Yamaguchi, Masato
AU - Matsuoka, Ken
AU - Kawasaki, Akira
AU - Kasahara, Jiro
AU - Watanabe, Hiroaki
AU - Matsuo, Akiko
N1 - Funding Information:
This work was subsidized by a Grand-Aid for scientific research (A) (No. 17H04971 ) and JSPS KAKENHI Grant Number JP17H04971 and Tatematsu Foundation.
Publisher Copyright:
© 2018 The Combustion Institute.
PY - 2019
Y1 - 2019
N2 - As a novel detonation combustor that differs from a pulse and a rotating detonation engine, a reflective shuttling detonation combustor (RSDC), in which detonation waves shuttle repeatedly, was proposed. In a fan-shaped two-dimensional combustor, detonation waves propagate, repeating attenuation and re-ignition by a shock reflection at the side wall. In the demonstration experiment, chemiluminescence visualization and pressure measurement with ethylene-oxygen mixture were conducted at the same time. As the result, a single shuttling wave coupled with pressure rise was observed in the combustor. The tangential velocity of the wave was 1526 ± 12 m/s and approximately 60% of the estimated Chapman-Jouguet velocity of 2513 m/s. The ratio of pressure in front of the wave to one behind the primary wave or the reflected wave was in good agreement with one-dimensional shock theory, and it was suggested that the rapid reaction behind the reflected shock wave sustained the continuous propagation of the shock wave.
AB - As a novel detonation combustor that differs from a pulse and a rotating detonation engine, a reflective shuttling detonation combustor (RSDC), in which detonation waves shuttle repeatedly, was proposed. In a fan-shaped two-dimensional combustor, detonation waves propagate, repeating attenuation and re-ignition by a shock reflection at the side wall. In the demonstration experiment, chemiluminescence visualization and pressure measurement with ethylene-oxygen mixture were conducted at the same time. As the result, a single shuttling wave coupled with pressure rise was observed in the combustor. The tangential velocity of the wave was 1526 ± 12 m/s and approximately 60% of the estimated Chapman-Jouguet velocity of 2513 m/s. The ratio of pressure in front of the wave to one behind the primary wave or the reflected wave was in good agreement with one-dimensional shock theory, and it was suggested that the rapid reaction behind the reflected shock wave sustained the continuous propagation of the shock wave.
KW - Reflected shock wave
KW - Reflective shuttling detonation combustor
KW - Shock induced combustion
UR - http://www.scopus.com/inward/record.url?scp=85049787921&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=85049787921&partnerID=8YFLogxK
U2 - 10.1016/j.proci.2018.06.210
DO - 10.1016/j.proci.2018.06.210
M3 - Article
AN - SCOPUS:85049787921
SN - 1540-7489
VL - 37
SP - 3741
EP - 3747
JO - Proceedings of the Combustion Institute
JF - Proceedings of the Combustion Institute
IS - 3
ER -