Numerical Analysis for Fan Flutter with 3D Unsteady N-S CFD Code

摘要

Recently, the demand of making a higher load and more efficient jet engine has strengthened further. In the design of fan and compressor blades, flutter prediction is a critical factor. At present, the flutter prediction method is based on linearized theory. But the linearized theory is not good for the flutter in the high load region. Therefore, a highly accurate prediction method is necessary. A new CFD code is developed based on UPACS (JAXA CFD code). The code is capable for simulating a vibrating cascade. The code simulates simulated a transonic stall flutter, which is experienced in a rig test.