A turbomachine, particularly an aircraft engine, having a rotor, which is mounted rotatably around its longitudinal axis in a stator, and which has at least one row of rotating blades, which is formed by a plurality of rotating blades, is disclosed, wherein the stator has at least one abradable layer, and wherein each rotating blade has a blade tip that is lowered radially inward, at least in sections, proceeding from a leading edge on the side of the rotating blades in the direction of a trailing edge on the side of the rotating blades, and with a blade tip region that extends downstream from the leading edge runs into the abradable layer during operation of the turbomachine.