Affiliation of Author(s):能源与动力学院
Journal:Tuijin Jishu
Abstract:In order to improve the seal and aerodynamic heating at the variable geometry throat section of RBCC inlet at high Mach number, an over/under type inlet was discussed by referring to the corresponding inlet that was previously applied to the TBCC. In the range of low Mach number, the inlet was adjusted to get a proper total contraction ratio and the same internal contraction ratio of each passage. Thus the two passages could gain similar performance parameters to reduce the mixing loss and resist the roughly same back pressure. In the range of high Mach number, the low-speed passage was closed and the high-speed passage was kept fixed. The numerical simulation results indicate when the free stream Mach number are 2.0, 2.5, 3.0, 3.5, the average Mach number of the two throat and outlet sections are similar, the deviations do not exceed 0.05 and the mass flow rate reaches about 0.7. In summary, this design enables the inlet to possess a high mass flow rate and good performance during the whole working range Ma=2~6, and the adjusting method is practical and feasible. © 2017, Editorial Department of Journal of Propulsion Technology. All right reserved.
ISSN No.:1001-4055
Translation or Not:no
Date of Publication:2017-03-01
Co-author:Guo, Rong-Rong,mxl,XT21373
Correspondence Author:jzg
Date of Publication:2017-03-01