Affiliation of Author(s):能源与动力学院
Journal:JOURNAL OF AIRCRAFT
Key Words:GEOMETRIC CONSERVATION LAW HIGH MACH NUMBER HYPERSONIC INLET UNSTART MECHANISM CHOKING FLUTTER WINGS ROTOR
Abstract:A two-dimensional over-under turbine-based combined-cycle inlet system that exhibits the fluid-structure interaction phenomenon is investigated at both design and off-design states. The mesh-based parallel code coupling interface is used to perform a two-way loosely coupled data exchange across the fluid-structural interfaces. Results indicate that, although the performance variation is limited at a ramjet mode with Ma(0) = 2.5, unexpected limit cycle oscillations appear accompanied by unsteady amplitudes. Moreover, a remarkable unstart delay along with the deceleration process of performance deterioration can be observed when the backpressure goes through a rapid increase, where the upward deformation of the splitter plate plays a significant role in resisting the downstream disturbance. In contrast, the fluid-structure interaction effect leads to an earlier occurrence of inlet unstart when the angle of attack varies periodically, and it induces limit cycle oscillations at a higher varying frequency. The study reveals the necessity of attaching more importance to the aeroelastic behavior of the splitter plate in the future research and operation of the over-under turbine-based combined-cycle inlet system.
ISSN No.:0021-8669
Translation or Not:no
Date of Publication:2018-09-01
Co-author:Qin, Qihao,Guo, Shuai
Correspondence Author:Xu Jinglei