US Patent 11274558 Compressor aerofoil

A compressor aerofoil for a turbine engine includes a tip portion with a tip wall which extends from the aerofoil leading edge to the aerofoil trailing edge. The tip wall defines a squealer which extends between the leading edge the trailing edge. A shoulder is provided on one of the suction surface wall or pressure surface wall which extends between the leading edge and the trailing. A transition region tapers from the shoulder in a direction towards the tip wall. The other of the suction surface wall or pressure surface wall extends towards the tip wall.