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The fatigue crack path for titanium compressor disks in rim parts of aircrafts engines D-30 and D-30Ku of the first stage of the low-pressure compressor has discussed. Based on fractographic analysis shown that the high cycle fatigue regime is the first stage for in-service damage accumulation in the titanium alloy VT3-1 used for compressor disks manufacturing procedure. This situation took place in the case of cracks propagation in the perpendicular direction to the disks radius in disks of engine D-30. In disks of engine D-30Ku crack propagation took place along the disk radius. This situation is analysed based on results of numerical estimations of material stress-state and sequence of the crack path features for two stages of high cycle and low cycle fatigue regime for disks has shown.