Article ID | Journal | Published Year | Pages | File Type |
---|---|---|---|---|
7153855 | Chinese Journal of Aeronautics | 2017 | 8 Pages |
Abstract
The characteristics of unsteady flow in a dual-flowpath inlet, which was designed for a Turbine Based Combined Cycle (TBCC) propulsion system, and the control methods of unsteady flow were investigated experimentally and numerically. It was characterized by large-amplitude pressure oscillations and traveling shock waves. As the inlet operated in supercritical condition, namely the terminal shock located in the throat, the shock oscillated, and the period of oscillation was about 50â¯ms, while the amplitude was 6â¯mm. The shock oscillation was caused by separation in the diffuser. This shock oscillation can be controlled by extending the length of diffuser which reduces pressure gradient along the flowpath. As the inlet operated in critical condition, namely the terminal shock located at the shoulder of the third compression ramp, the shock oscillated, and the period of oscillation was about 7.5â¯ms, while the amplitude was 12â¯mm. At this condition, the shock oscillation was caused by an incompatible backpressure in the bleed region. It can be controlled by increasing the backpressure of the bleed region.
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Physical Sciences and Engineering
Engineering
Aerospace Engineering
Authors
Jun LIU, Huacheng YUAN, Yunfei WANG, Ning GE,