TY - GEN
T1 - A Review of Supersonic Turbines Based on Constant Volume Combustion Cycle
AU - Su, Liangjun
AU - Wen, Fengbo
N1 - Publisher Copyright:
© 2021, The Author(s), under exclusive license to Springer Nature Singapore Pte Ltd.
PY - 2021
Y1 - 2021
N2 - In this paper, in response to the current demand for new aerospace power in the aerospace field, thermodynamic performance and thermal efficiency advantages of existing constant volume combustion cycles are reviewed. The main challenge in the practical implementation of Pressure Gain Combustion (PGC) into gas turbines and aero-engine is the lack of turbomachinery that can efficiently harvest work from the PGC exhaust gas. Therefore, this paper analyzes the supersonic inflow conditions with pressure, temperature and velocity pulsations at the outlet of the detonation combustion chamber, and puts forward the difficulties brought by the inflow conditions to the design of the turbine cascade. Secondly, this paper analyzes the aerodynamic characteristics of turbine cascade passage under supersonic inlet conditions, analyzes the influence of channel shock waves on aerodynamic losses, and expounds the importance of turbine under supersonic inlet conditions in detonation combustion cycle.
AB - In this paper, in response to the current demand for new aerospace power in the aerospace field, thermodynamic performance and thermal efficiency advantages of existing constant volume combustion cycles are reviewed. The main challenge in the practical implementation of Pressure Gain Combustion (PGC) into gas turbines and aero-engine is the lack of turbomachinery that can efficiently harvest work from the PGC exhaust gas. Therefore, this paper analyzes the supersonic inflow conditions with pressure, temperature and velocity pulsations at the outlet of the detonation combustion chamber, and puts forward the difficulties brought by the inflow conditions to the design of the turbine cascade. Secondly, this paper analyzes the aerodynamic characteristics of turbine cascade passage under supersonic inlet conditions, analyzes the influence of channel shock waves on aerodynamic losses, and expounds the importance of turbine under supersonic inlet conditions in detonation combustion cycle.
KW - Constant volume combustion cycle
KW - Detonation combustion inflow condition
KW - PGC
KW - Supersonic turbine
UR - https://www.scopus.com/pages/publications/85111092440
U2 - 10.1007/978-981-33-6060-0_12
DO - 10.1007/978-981-33-6060-0_12
M3 - 会议稿件
AN - SCOPUS:85111092440
SN - 9789813360594
T3 - Lecture Notes in Electrical Engineering
SP - 169
EP - 191
BT - Proceedings of the International Conference on Aerospace System Science and Engineering 2020
A2 - Jing, Zhongliang
A2 - Zhan, Xingqun
PB - Springer Science and Business Media Deutschland GmbH
T2 - 4th International Conference on Aerospace System Science and Engineering, ICASSE 2020
Y2 - 14 July 2020 through 16 July 2020
ER -