Aircraft gas turbine engine impeller with a trailing edge that is non-linear or angled or irregularly-shaped

A centrifugal compressor assembly of a gas turbine engine of an aircraft, the centrifugal compressor assembly comprising:

• an impeller comprising a hub, vanes and a shroud surrounding the hub and the vanes to form a flow path from an inducer portion at an upstream side of the impeller to an exducer portion at an impeller exit;
• a diffuser configured to direct compressed air from the impeller exit to a downstream combustor, the diffuser comprising a diffuser ring proximate to the impeller exit,
• each vane comprising, at the impeller exit, a trailing edge which is at least one of non-linear and angled,
• the shroud comprising a sloped trailing edge portion adjacent to the trailing edge of each vane, and
• the diffuser ring comprising a sloped surface adjacent to the sloped trailing edge portion of the shroud,
• wherein the sloped trailing edge portion of the shroud is sloped toward the trailing edge of each vane.