Partial exit centrifugal compressor

A gas turbine engine comprising:

• a fan;
• a combustor section;
• a turbine section;
• and
• a compressor section, wherein the compressor section comprises an impeller assembly comprising:
• an impeller hub having an impeller leading edge and an impeller trailing edge;
• and
• a plurality of bifurcated impeller blades arranged on the impeller hub and extending from the impeller leading edge to the impeller trailing edge, each bifurcated impeller blade having a bifurcated pressure side and a bifurcated suction side;
• wherein the bifurcated pressure side and the bifurcated suction side of each bifurcated impeller blade separate at a bifurcation point and extend to the impeller trailing edge,
• wherein a reduced flow channel is defined between adjacent bifurcated impeller blades,
• wherein a blocked zone is defined within each bifurcated impeller blade between the bifurcated pressure side and the bifurcated suction side and extending from the bifurcation point to the impeller trailing edge, and
• wherein each of the bifurcated pressure side and the bifurcated suction side extend tangentially from the bifurcation point at different radii of curvature and extend to different points at the impeller trailing edge.