Affiliation of Author(s):能源与动力学院
Journal:Tuijin Jishu
Abstract:In order to investigate the aerodynamic performance of over-under turbine-based combined-cycle (TBCC) propulsion systems over the entire range of the vehicle's Mach number, a TBCC exhaust system was subjected to computational study in full flight envelop. Steady-state wind tunnel experiments of the exhaust nozzle under typical flight conditions were carried out to validate the reliability of numerical simulation method. Flow-field structures and the wall pressure distributions were obtained and were compared with the computational results. Results indicate that flow structure of the TBCC exhaust system is complicated because the two exhaust jet streams interact with each other around the exit plane of the turbo. Optimizing geometrical parameters of the TBCC exhaust system can reduce the effects of interaction on the whole flow-field structure and thrust performance. In full flight envelop, the total thrust coefficient of the exhaust system is all higher than 0.9. The thrust performance of ramjet is relatively poor at low Mach number because of a large area of flow separation, but it has little influence on the exhaust system thrust performance. The CFD simulation results which include wall pressure distributions and wave structures of flow field agree well with the experimental data, which demonstrated that the CFD methods are effective in evaluating the aerodynamic performance of the TBCC exhaust system. © 2017, Editorial Department of Journal of Propulsion Technology. All right reserved.
ISSN No.:1001-4055
Translation or Not:no
Date of Publication:2017-12-01
Co-author:牛彦沣,许保成,陈匡世
Correspondence Author:Xu Jinglei