TY - GEN
T1 - Research on the Effect of Front Variable Area Bypass Injector Modulation on the Adaptive Cycle Engine Performance Based on Multi-fidelity Simulation
AU - Xu, Zhewen
AU - Tang, Hailong
AU - Cong, Jingmei
AU - Chen, Min
AU - Zhang, Jiyuan
N1 - Publisher Copyright:
© The Author(s), under exclusive license to Springer Nature Singapore Pte Ltd. 2024.
PY - 2024
Y1 - 2024
N2 - In this paper, two types of Front Variable Area Bypass Injector (FVABI) Computational Fluid Dynamics (CFD) models for axial type and rotary type are established and their operating characteristics are generated. The performance of the two types of FVABI under two operating modes is compared considering the Adaptive Cycle Engine (ACE) matching requirements. A multi-fidelity simulation model is established based on the coupling calculation of the 2-D FVABI and 0-D ACE performance model. A throttling performance control law design method is proposed based on fitting multiple data points. The effects of different modulation settings of the FVABI on the optimum control law and performance of the ACE under various operating conditions are simulated and analyzed. Simulation results indicate that, with the same mass flow modulation capacity, the axial type FVABI could realize equal or higher total pressure recovery coefficients in both ACE operation modes. Considering the collaborative modulation of other ACE components, the different FVABI modulation states could result in up to a 3.2% reduction in maximum thrust in the intermediate conditions. For the ACE constant inlet airflow throttling performance, the FVABI modulation could reduce the Specific Fuel Consumption rate (SFC) by 2% and 1.3% in the deep throttling intervals in subsonic and supersonic cruise conditions, respectively. The FVABI modulation has less effect (relative difference less than 0.2%) on SFC in the non-deep throttling interval of the throttling process.
AB - In this paper, two types of Front Variable Area Bypass Injector (FVABI) Computational Fluid Dynamics (CFD) models for axial type and rotary type are established and their operating characteristics are generated. The performance of the two types of FVABI under two operating modes is compared considering the Adaptive Cycle Engine (ACE) matching requirements. A multi-fidelity simulation model is established based on the coupling calculation of the 2-D FVABI and 0-D ACE performance model. A throttling performance control law design method is proposed based on fitting multiple data points. The effects of different modulation settings of the FVABI on the optimum control law and performance of the ACE under various operating conditions are simulated and analyzed. Simulation results indicate that, with the same mass flow modulation capacity, the axial type FVABI could realize equal or higher total pressure recovery coefficients in both ACE operation modes. Considering the collaborative modulation of other ACE components, the different FVABI modulation states could result in up to a 3.2% reduction in maximum thrust in the intermediate conditions. For the ACE constant inlet airflow throttling performance, the FVABI modulation could reduce the Specific Fuel Consumption rate (SFC) by 2% and 1.3% in the deep throttling intervals in subsonic and supersonic cruise conditions, respectively. The FVABI modulation has less effect (relative difference less than 0.2%) on SFC in the non-deep throttling interval of the throttling process.
KW - Adaptive cycle engine
KW - Control law design
KW - Engine overall performance
KW - Front variable area bypass injector
KW - Multi-fidelity simulation
UR - https://www.scopus.com/pages/publications/85200246040
U2 - 10.1007/978-981-97-3998-1_133
DO - 10.1007/978-981-97-3998-1_133
M3 - 会议稿件
AN - SCOPUS:85200246040
SN - 9789819739974
T3 - Lecture Notes in Electrical Engineering
SP - 1689
EP - 1706
BT - 2023 Asia-Pacific International Symposium on Aerospace Technology, APISAT 2023, Proceedings - Volume I
A2 - Fu, Song
PB - Springer Science and Business Media Deutschland GmbH
T2 - Asia-Pacific International Symposium on Aerospace Technology, APISAT 2023
Y2 - 16 October 2023 through 18 October 2023
ER -