A gas turbine engine comprising: a compressor section; a combustor connected to the compressor section by a primary flowpath; a turbine section connected to the combustor section by the primary flowpath; a plurality of rotor blades (220; 420) arranged circumferentially about an engine centerline, at least one of the rotor blades including a platform, a root extending radially inward from the platform, and a blade extending radially outward and at least partially spanning the primary flowpath; at least one shroud component radially outward of the plurality of rotor blades (220; 420), the shroud being abradable relative to the blade; and the blade including a contoured tip portion configured to interfere with said shroud during a rub event, characterized in that: the contoured tip portion includes at least a first sloped region, a second sloped region downstream of the first sloped region, and a third sloped region downstream of the second sloped region, wherein the first sloped region has a negative slope in the downstream direction that is approximately equal to a corresponding slope of the shroud relative to the engine centerline, the corresponding slope of the shroud being radially outward of the first sloped region, and wherein the second sloped region has a substantially steeper slope than the first sloped region, relative to the engine centerline, and the third sloped region has a slope, relative to the engine centerline, that is approximately equal to the first sloped region; and the shroud comprises a sculpted pocket radially outward of the tip portion, the sculpted pocket including a rear facing flowpath step at a forward edge of the sculpted pocket, and a forward facing flowpath turn at an aft edge of the sculpted pocket, wherein the forward facing flowpath turn is less than ninety degrees. a compressor section; a combustor connected to the compressor section by a primary flowpath; a turbine section connected to the combustor section by the primary flowpath; a plurality of rotor blades (220; 420) arranged circumferentially about an engine centerline, at least one of the rotor blades including a platform, a root extending radially inward from the platform, and a blade extending radially outward and at least partially spanning the primary flowpath; at least one shroud component radially outward of the plurality of rotor blades (220; 420), the shroud being abradable relative to the blade; and the blade including a contoured tip portion configured to interfere with said shroud during a rub event, the contoured tip portion includes at least a first sloped region, a second sloped region downstream of the first sloped region, and a third sloped region downstream of the second sloped region, wherein the first sloped region has a negative slope in the downstream direction that is approximately equal to a corresponding slope of the shroud relative to the engine centerline, the corresponding slope of the shroud being radially outward of the first sloped region, and wherein the second sloped region has a substantially steeper slope than the first sloped region, relative to the engine centerline, and the third sloped region has a slope, relative to the engine centerline, that is approximately equal to the first sloped region; and the shroud comprises a sculpted pocket radially outward of the tip portion, the sculpted pocket including a rear facing flowpath step at a forward edge of the sculpted pocket, and a forward facing flowpath turn at an aft edge of the sculpted pocket, wherein the forward facing flowpath turn is less than ninety degrees.