A turbine blade comprising: a generally elongated airfoil having a leading edge, a trailing edge, a pressure side, a suction side on a side opposite to the pressure side, a tip at a radially outer end of the airfoil, a root coupled to a radially inner end of the airfoil for coupling the airfoil to a disc; a shroud coupled to the tip of the airfoil; wherein the shroud extends in a direction generally from the pressure side toward the suction side and when mounted in a gas turbine engine extends circumferentially with respect to an axis of the gas turbine engine; wherein the shroud is formed at least in part by a shroud base coupled to the tip of the airfoil and a knife edge seal extending radially outward from the shroud base; a flow conditioner (70, 70a, 70b) positioned on a radially outer surface of the shroud base, radially adjacent to the tip of the airfoil, the flow conditioner (70, 70a, 70b) comprising: a ramped radially outer surface positioned further radially inward than the radially outer surface of the shroud base, the ramped radially outer surface extending from a first edge to a second edge in a direction generally from the suction side to the pressure side of the airfoil, such that the first edge is positioned further radially inward than the second edge; characterized in that a plurality of coolant ejection holes are positioned on the ramped radially outer surface, the plurality of coolant ejection holes being connected fluidically to an interior of the airfoil. a generally elongated airfoil having a leading edge, a trailing edge, a pressure side, a suction side on a side opposite to the pressure side, a tip at a radially outer end of the airfoil, a root coupled to a radially inner end of the airfoil for coupling the airfoil to a disc; a shroud coupled to the tip of the airfoil; wherein the shroud extends in a direction generally from the pressure side toward the suction side and when mounted in a gas turbine engine extends circumferentially with respect to an axis of the gas turbine engine; wherein the shroud is formed at least in part by a shroud base coupled to the tip of the airfoil and a knife edge seal extending radially outward from the shroud base; a flow conditioner (70, 70a, 70b) positioned on a radially outer surface of the shroud base, radially adjacent to the tip of the airfoil, the flow conditioner (70, 70a, 70b) comprising: a ramped radially outer surface positioned further radially inward than the radially outer surface of the shroud base, the ramped radially outer surface extending from a first edge to a second edge in a direction generally from the suction side to the pressure side of the airfoil, such that the first edge is positioned further radially inward than the second edge; characterized in that a plurality of coolant ejection holes are positioned on the ramped radially outer surface, the plurality of coolant ejection holes being connected fluidically to an interior of the airfoil. a ramped radially outer surface positioned further radially inward than the radially outer surface of the shroud base, the ramped radially outer surface extending from a first edge to a second edge in a direction generally from the suction side to the pressure side of the airfoil, such that the first edge is positioned further radially inward than the second edge; characterized in that a plurality of coolant ejection holes are positioned on the ramped radially outer surface, the plurality of coolant ejection holes being connected fluidically to an interior of the airfoil.