Compressor blade and compressor

The invention relates to the field of gas turbines and provides a compressor blade and a compressor. The compressor blade comprises a blade tip, a blade root and a blade middle which axially extends from the blade root to the blade tip; the cross section of each of the blade root, the blade middle and the blade tip is parallel to XY planes, X-direction represents the axial direction, Y-direction represents the tangential direction, and the Z-direction represents the radial direction; the tailing edge of the blade tip and the tailing edge of the blade root respectively twist toward the suctionside, the tailing edge of the blade middle twists toward the pressure side, and the trailing edges on the cross sections of the blade root, the blade middle and the blade tip are sequentially arrangedaround the leading edge point in the direction of the suction side. The leading edge of the entire compressor blade remains unchanged assuredly, and airflow separation of the blade root and the bladetip can be reduced by allo