TY - GEN
T1 - Pressure and visualization measurements on pulsed combustion thrustor
AU - Asahara, Motomu
AU - Kasahara, Jiro
AU - Matsuoka, Ken
AU - Kawasaki., Akira
AU - Matsuo, Akiko
AU - Funaki, Ikkoh
N1 - Funding Information:
This study was financially supported by JSPS KAKENHI Grant Numbers JP19H05464, JP18KK0127, JP17H03480, JP17K18937, and by the Institute of Space and Astronautical Science of the Japan Aerospace Exploration Agency.
PY - 2020
Y1 - 2020
N2 - Pulsed combustor, it has features such as taking out work without a compressor and mixing promotion by a complicated flow field. The purpose of my research is to evaluate the thrust of a pulse combustor that substitutes this check valve with an ejector mechanism without moving parts, and to clarify the pressure-gain of pulsed combustion and grasp the combustion state with pressure and visualization measurement. Although the total pressure of exhaust gas was lower than the oxygen plenum pressure in all shots, these were almost equal in case in which the pulse combustion was stably continued. It was also found that the expansion wave and the compression wave reciprocate in the combustion section, and that the behavior of the pressure wave and the flame were synchronized. A pulse combustion cycle due to this pressure wave reciprocation was estimated, and the sound velocity obtained from this was in agreement at the order level with theoretical value.
AB - Pulsed combustor, it has features such as taking out work without a compressor and mixing promotion by a complicated flow field. The purpose of my research is to evaluate the thrust of a pulse combustor that substitutes this check valve with an ejector mechanism without moving parts, and to clarify the pressure-gain of pulsed combustion and grasp the combustion state with pressure and visualization measurement. Although the total pressure of exhaust gas was lower than the oxygen plenum pressure in all shots, these were almost equal in case in which the pulse combustion was stably continued. It was also found that the expansion wave and the compression wave reciprocate in the combustion section, and that the behavior of the pressure wave and the flame were synchronized. A pulse combustion cycle due to this pressure wave reciprocation was estimated, and the sound velocity obtained from this was in agreement at the order level with theoretical value.
UR - http://www.scopus.com/inward/record.url?scp=85091917627&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=85091917627&partnerID=8YFLogxK
U2 - 10.2514/6.2020-0923
DO - 10.2514/6.2020-0923
M3 - Conference contribution
AN - SCOPUS:85091917627
SN - 9781624105951
T3 - AIAA Scitech 2020 Forum
BT - AIAA Scitech 2020 Forum
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Scitech Forum, 2020
Y2 - 6 January 2020 through 10 January 2020
ER -