TY - GEN
T1 - Influence of Total Inlet Temperature on Flow Combustion Characteristics of Combustor
AU - Zhang, Hao
AU - Jia, Shengxi
AU - Yan, Mi
AU - Huang, Meng
N1 - Publisher Copyright:
© (2023) by Aussino Academic Publishing House All rights reserved.
PY - 2023
Y1 - 2023
N2 - When air breathing hypersonic aircraft is flying in wide velocity range, the inflow conditions change greatly, which leads to the change of air flow conditions at the inlet of combustor and affects the flow and combustion characteristics of combustor. In view of the above problems, the combustion, turbulence, burning rate and mass transfer models suitable for the flow field calculation of scramjet combustor were selected, and the influence of different total temperature on the flow field characteristics of the optimized configuration of solid fuel scramjet combustor was studied. The results show that the change of the total inlet temperature has little influence on the combustion efficiency of the optimized combustor configuration. High total inflow temperature will cause the Mach number in the combustor to oscillate along the axial direction and increase the total pressure loss, but it will also increase the thrust of the combustor.
AB - When air breathing hypersonic aircraft is flying in wide velocity range, the inflow conditions change greatly, which leads to the change of air flow conditions at the inlet of combustor and affects the flow and combustion characteristics of combustor. In view of the above problems, the combustion, turbulence, burning rate and mass transfer models suitable for the flow field calculation of scramjet combustor were selected, and the influence of different total temperature on the flow field characteristics of the optimized configuration of solid fuel scramjet combustor was studied. The results show that the change of the total inlet temperature has little influence on the combustion efficiency of the optimized combustor configuration. High total inflow temperature will cause the Mach number in the combustor to oscillate along the axial direction and increase the total pressure loss, but it will also increase the thrust of the combustor.
KW - Combustor
KW - Flow Combustion
KW - Numerical Simulation
KW - Solid Fuel Scramjet
UR - http://www.scopus.com/inward/record.url?scp=85186526091&partnerID=8YFLogxK
U2 - 10.52202/070275-0012
DO - 10.52202/070275-0012
M3 - Conference contribution
AN - SCOPUS:85186526091
T3 - 11th International Symposium on Project Management, ISPM 2023
SP - 78
EP - 87
BT - 11th International Symposium on Project Management, ISPM 2023
A2 - Cheng, Changbo
A2 - Zhang, Henry
PB - Aussino Academic Publishing House
T2 - 11th International Symposium on Project Management, ISPM 2023
Y2 - 16 June 2023 through 17 June 2023
ER -