A bucket (120, 220) for use with a turbine, the bucket (120, 220) comprising: a dovetail for use in coupling the bucket (120, 220) to a rotor wheel of the turbine; a platform coupled to the dovetail; an airfoil extending radially outward from the platform to a tip; a pair of radially inner part-span shrouds (238, 240); a pair of radially outer part-span shrouds (242, 244); and wherein the airfoil comprises a pressure sidewall and an opposite suction sidewall, the pressure and suction sidewalls (230, 232) each extending from a leading edge to a trailing edge; wherein a first of the radially inner part-span shrouds (238, 240) extends outward from the suction sidewall of the airfoil at a first radial height (S i) above the platform, and a second of the radially inner part-span shrouds (238, 240) extends outward from the pressure sidewall of the airfoil at the first radial height (S i) above the platform; wherein a first of the radially outer part-span shrouds (242, 244) extends outward from the suction sidewall of the airfoil at a second radial height (S o) above the platform, and a second of the radially outer part-span shrouds (242, 244) extends outward from the pressure sidewall of the airfoil at the second radial height (S o) above the platform, wherein the second radial height (S o) is greater than the first radial height (S i); wherein each of the pair of radially inner part-span shrouds (238, 240) and the pair of radially outer part-span shrouds (242, 244) extends only partially between the leading and trailing edges (226, 228) of the airfoil; and characterized in that the airfoil further comprises: a pair of hollow tip cavities (302, 304) defined between the radially outer part-span shrouds (242, 244) and the tip of the airfoil, wherein the pair of hollow tip cavities (302, 304) are each shaped with a profile that substantially matches a shape of the airfoil; and a plurality of tip blind holes extending radially inward from the tip of the airfoil towards the platform and terminating radially outward from the pair of radially outer part-span shrouds (242, 244), the plurality of tip blind holes disposed between the pair of hollow tip cavities (302, 304) and the trailing edge of the airfoil; and the bucket (120, 220) further comprises a plurality of holes extending radially inwardly from each respective cavity of the pair of hollow tip cavities (302, 304) through the dovetail to enable air flow direction through the plurality of holes to provide flow ejection along the tip. a dovetail for use in coupling the bucket (120, 220) to a rotor wheel of the turbine; a platform coupled to the dovetail; an airfoil extending radially outward from the platform to a tip; a pair of radially inner part-span shrouds (238, 240); a pair of radially outer part-span shrouds (242, 244); and wherein the airfoil comprises a pressure sidewall and an opposite suction sidewall, the pressure and suction sidewalls (230, 232) each extending from a leading edge to a trailing edge; wherein a first of the radially inner part-span shrouds (238, 240) extends outward from the suction sidewall of the airfoil at a first radial height (S i) above the platform, and a second of the radially inner part-span shrouds (238, 240) extends outward from the pressure sidewall of the airfoil at the first radial height (S i) above the platform; wherein a first of the radially outer part-span shrouds (242, 244) extends outward from the suction sidewall of the airfoil at a second radial height (S o) above the platform, and a second of the radially outer part-span shrouds (242, 244) extends outward from the pressure sidewall of the airfoil at the second radial height (S o) above the platform, wherein the second radial height (S o) is greater than the first radial height (S i); wherein each of the pair of radially inner part-span shrouds (238, 240) and the pair of radially outer part-span shrouds (242, 244) extends only partially between the leading and trailing edges (226, 228) of the airfoil; and characterized in that the airfoil further comprises: a pair of hollow tip cavities (302, 304) defined between the radially outer part-span shrouds (242, 244) and the tip of the airfoil, wherein the pair of hollow tip cavities (302, 304) are each shaped with a profile that substantially matches a shape of the airfoil; and a plurality of tip blind holes extending radially inward from the tip of the airfoil towards the platform and terminating radially outward from the pair of radially outer part-span shrouds (242, 244), the plurality of tip blind holes disposed between the pair of hollow tip cavities (302, 304) and the trailing edge of the airfoil; and a pair of hollow tip cavities (302, 304) defined between the radially outer part-span shrouds (242, 244) and the tip of the airfoil, wherein the pair of hollow tip cavities (302, 304) are each shaped with a profile that substantially matches a shape of the airfoil; and a plurality of tip blind holes extending radially inward from the tip of the airfoil towards the platform and terminating radially outward from the pair of radially outer part-span shrouds (242, 244), the plurality of tip blind holes disposed between the pair of hollow tip cavities (302, 304) and the trailing edge of the airfoil; and the bucket (120, 220) further comprises a plurality of holes extending radially inwardly from each respective cavity of the pair of hollow tip cavities (302, 304) through the dovetail to enable air flow direction through the plurality of holes to provide flow ejection along the tip.