Taking TiAl alloy aeroengine blade as the research object

a series of problems likely to happen during the test of the vibration fatigue for aeroengine blade at high temperature and high cycle were studied

including fatigue stress monitoring at high temperature

and high frequency excitation. The closed loop of maximum stress was used to solve the high-temperature fatigue stress monitoring. The high frequency excitation was realized through design of fixture amplification. The temperature load and vibration load were applied synthetically by radiation heating and electromagnetic vibration shaker. Using the method of the vibration fatigue at high temperature and high cycle

the life test was carried out on the blade. The control accuracy of high temperature fatigue stress was better than ±2%. The median fatigue limit value of the blade with 50% reliability was 444 MPa. The life curve of the blade was obtained effectively. This test method is suitable for the high temperature and high cycle vibration fatigue test of the aeroengine blade

providing a reference to the high temperature and high cycle vibration fatigue test of the other aeroengine parts.