Affiliation:
1. JiangSu Province Key Laboratory of Aerospace Power System , Nanjing University of Aeronautics and Astronautics , No. 29 Yudao Street , Nanjing 210016 , China
Abstract
Abstract
The over-under turbine based combined cycle (TBCC) propulsion system dynamic model is established, including the engine model and inlet model. A dual-channel inlet is designed to match the engine and the inlet performance parameters are obtained by computational fluid dynamics (CFD) calculation, which provides original data for the integrated Inlet/Engine matching model. Control plan is designed to ensure that the engine is not over-temperature, over-rotation or surging based on correlation analysis. The simulation results show that the designed control plan can keep the TBCC propulsion system continuous in thrust during the mode transition, and the thrust fluctuation is about 10%.
Funder
National Science and Technology Major Project
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