The invention relates to an axial flow compressor blade, an axial flow compressor and a gas turbine. The axial flow air compressor blade comprises a pressure side wall, a blade tip, and a flow guide structure, wherein the flow guide structure is arranged in the area, where the blade tip is located, of the pressure side wall and extends in the chordwise direction of the axial flow compressor blade,and the flow guide structure is used for increasing separation bubbles formed by airflow passing through the flow guide structure on the outer side of the top end face of the blade tip so as to reduce leakage flow at the blade tip. According to the axial flow compressor blade, the axial flow compressor and the gas turbine, the flow guide structure is arranged in the area, where the blade tip is located, of the pressure side wall, so that the shape of the pressure side wall is changed, and a preset angle is formed between the pressure side wall of the axial flow compressor blade and the end face of the top of the blade tip; and gas flows to radial gaps after being guided by the flow guide structure, so that separation bubbles generated by leakage flowing of the gas on the outer side of thetop end face of the blade tip are increased, the effective radial gaps are reduced, the leakage flow is reduced, the leakage vortex strength is weakened, losses caused by gap leakage flowing are reduced, and the performance of the axial flow compressor is improved.