A radial turbomachine comprising: a downstream element having an inlet, a shroud side and a hub side, wherein said downstream element is a diffuser; a centrifugal impeller comprising a hub and a plurality of blades and having an inlet, an exit, and an axis of rotation, each of said plurality of blades having a leading edge and a trailing edge and extending in a spanwise direction from said hub to a shroud side of said blade; a shroud having a face confronting said shroud sides of said plurality of blades, said shroud and said hub defining an impeller passageway; wherein said impeller is designed and configured to discharge a working fluid into said downstream element and generate a flow field in said working fluid, the flow field at said exit including a weak side proximate one of said hub and said shroud and a strong side proximate the other one of said hub and said shroud, wherein a meridional component of an absolute velocity of the flow field is greater on the strong side than the weak side; and at least one channel extending in a flow-wise direction and formed in at least one of said shroud side and said hub side of said downstream element, said at least one channel having a centerline that has a tangent line extending at an angle, α, as measured in an absolute frame of reference from a meridional reference plane extending through said axis of rotation, the radial turbomachine being characterised in that said at least one channel is selectively located adjacent the weak side of the flow field and being designed and configured to guide a portion of said weak side of said flow field in a direction that is substantially the same as α; and wherein a portion said at least one channel is located in an exit region of said impeller upstream of said trailing edges of said impeller blades to thereby guide a portion of said weak side of said flow field from said impeller to said downstream element. a downstream element having an inlet, a shroud side and a hub side, wherein said downstream element is a diffuser; a centrifugal impeller comprising a hub and a plurality of blades and having an inlet, an exit, and an axis of rotation, each of said plurality of blades having a leading edge and a trailing edge and extending in a spanwise direction from said hub to a shroud side of said blade; a shroud having a face confronting said shroud sides of said plurality of blades, said shroud and said hub defining an impeller passageway; wherein said impeller is designed and configured to discharge a working fluid into said downstream element and generate a flow field in said working fluid, the flow field at said exit including a weak side proximate one of said hub and said shroud and a strong side proximate the other one of said hub and said shroud, wherein a meridional component of an absolute velocity of the flow field is greater on the strong side than the weak side; and at least one channel extending in a flow-wise direction and formed in at least one of said shroud side and said hub side of said downstream element, said at least one channel having a centerline that has a tangent line extending at an angle, α, as measured in an absolute frame of reference from a meridional reference plane extending through said axis of rotation, the radial turbomachine being characterised in that said at least one channel is selectively located adjacent the weak side of the flow field and being designed and configured to guide a portion of said weak side of said flow field in a direction that is substantially the same as α; and wherein a portion said at least one channel is located in an exit region of said impeller upstream of said trailing edges of said impeller blades to thereby guide a portion of said weak side of said flow field from said impeller to said downstream element.