Gas turbine engine blade platform modification

摘要: A gas turbine engine compressor blade includes an airfoil and a root section connected to platform therebetween at least partially curved cropped corner of the platform. The shape size may avoid resonance during operation. Corner be J-shaped including straight extending from pressure side edge towards suction uncropped portion trailing method designing choosing shapes sizes for numerically analyzing determining using numerical model iteratively analyze aerodynamically with different corner. Numerical validated or component testing having one sizes.