US Patent 11085308 Compressor aerofoil

A compressor aerofoil for a turbine engine includes a root portion spaced apart from a tip portion by a main body portion. The main body portion is defined by a suction surface wall having a suction surface, and a pressure surface wall having a pressure surface. The suction surface wall and the pressure surface wall meet at a leading edge and a trailing edge. The tip portion has a tip wall which extends from the aerofoil leading edge to the aerofoil trailing edge. The tip wall defines a squealer having: a first tip wall region which extends from the leading edge; a second tip wall region which extends from the trailing edge; and a third tip wall region which extends between the first tip wall region and the second tip wall region.