Impeller with converging inducer

An impeller assembly for a gas turbine engine comprising:

• a rotating component comprising a plurality of impeller blades extending radially outward from a hub, wherein an axis is defined through the hub, wherein each impeller blade comprises a leading edge, a trailing edge, a blade tip, and a blade inflection point defined on the blade tip between the leading edge and the training edge,
• wherein each impeller blade comprises a radially inward tapering portion that extends from the leading edge of the respective impeller blade to the blade inflection point, wherein the radially inward direction is toward the engine axis, and a radially outward tapering portion that extends from the inflection point to a trailing edge of the respective impeller blade, wherein the radially outward direction is away from the engine axis;
• and
• a split shroud arranged about the rotating component and defining a flow path between an external surface of the hub and an internal surface of the split shroud, wherein the impeller blades are configured to be rotationally driven relative to the split shroud, wherein the split shroud comprises:
• a first shroud element and a second shroud element configured to fixedly attach to the first shroud element, wherein each of the first shroud element and the second shroud element comprise:
• a radially inward tapering portion that extends from a shroud leading edge of the respective shroud element to an inflection point, wherein the radially inward direction is toward the axis, and
• a radially outward tapering portion that extends from the inflection point to a shroud aft edge, wherein the radially outward direction is away from the axis.