A method to determine the size of notch on first stage blade of compressor with a stress concentrated factor (K t) of three is briefly introduced

which is required for foreign object damage (FOD)testing of aeroengines.It is based on 8-node and 20-node finite element appoaches respectively.The 8-node super-parameter element approach is used to calculate the stress distribution of a whole blade without and with notch

and the 20-node 3D iso-parameter finite element programm is applied to computation of local stress distribution around a notch of blade.The practical testing techniques and test results are also presented.