Compressor impeller with partially swept leading edge surface

A radial compressor of a gas turbine engine, comprising:

• an impeller including a plurality of impeller blades and a plurality of splitter blades each coupled to an impeller hub, each impeller blade of the plurality of impeller blades having a leading edge, a trailing edge opposite the leading edge in a streamwise direction, each impeller blade of the plurality of impeller blades extending in a spanwise direction from a hub at 0% span to a tip at 100% span, with the leading edge including a partially swept leading edge region defined at 70% span at the leading edge that extends to the tip, at 70% span a point at the leading edge in the partially swept leading edge region is at 0% of a mean camber line in the streamwise direction, at 80% span a second point at the leading edge in the partially swept leading edge region is between 1% to 7% with respect to the mean camber line at 70% span in the streamwise direction, at 90% span a third point at the leading edge in the partially swept leading edge region is between 7% to 12.5% with respect to the mean camber line at 70% span in the streamwise direction, and at 100% span a fourth point at the leading edge in the partially swept leading edge region is between 12.5% to 15% with respect to the mean camber line at 70% span in the streamwise direction, each splitter blade of the plurality of splitter blades positioned between an adjacent pair of the plurality of impeller blades downstream from the leading edge;
• and
• a diffuser downstream of the impeller.