The Solid-gas-sound Coupling Mechanism Experiment Research Of Axial-flow Compressor Blades Non-synchronous Vibrations

The engine is the heart of the aircraft. Its performance and reliability have direct impact on the quality and safety of the aircraft. The compressor as an important part of the engine, its performance means a lot to the engine. Non-synchronous vibration of the axial-flow compressor blades will affect the performance of the compressor and reduce the reliability of the compressor, or even lead to the blade fracture and other serious consequences. So it is of important to study axial flow compressor blades non-synchronous vibration.This paper summarizes the asynchronous vibration compressor blades in domestic and foreign countries on the basis of axial compressor blades for gas-solid coupling theory test rig is optimized design, while studies of jet formation and jet properties.First, the basic knowledge of the jet to understand and master. At the same time, by changing the jet and the distance between the test plate, the jet speed and other factors, the nature of turbulent jets, is to verify the existence of vortex structures focused on the region of the outer boundary of the jet, and measuring the vortex shedding frequency is spored with the increase of the jet velocity, and concentrated in between200Hz and600Hz.Then, based on experimental measurements, calculated Strouhal number at between0.23to0.418and compare with previous studies, the results are basically the same.Finally, the axial-flow compressor blades existing gas-solid coupling theory test bench, there are some design issues, the flexible circular plate and bracket do a re-design and optimization, optimum design of circular plates sixth-order natural frequency of863Hz, the position of the annular peak on the r/D=1.28. Optimized stent basically meet the design requirements.