A rotor blade for a gas turbine, the rotor blade being configured for use within a row of samely configured rotor blades attached to and circumferentially spaced about a rotor disc, the rotor blade further including: an airfoil defined between a concave pressure face and a laterally opposed convex suction face, wherein the pressure face and the suction face extend axially between opposite leading and trailing edges (28, 29) and radially between an outboard tip and an inboard end, the inboard end of the airfoil attaching to a root configured for connecting the rotor blade to the rotor disc; and a midspan shroud comprising a pressure wing extending from the pressure face of the airfoil and a suction wing extending from the suction face of the airfoil; wherein the pressure wing comprises an aftward face, the aftward face facing toward an aftward direction of the gas turbine; and the suction wing comprises a forward face, the forward face facing toward a forward direction of the gas turbine; wherein the aftward face of the pressure wing includes a V-notch configuration which is formed of a near linear edge segment and a far linear edge segment that define the aftward face, said linear edge segments (114, 115) being canted relative to each other and connecting at a connecting point and forming an angle therebetween; wherein the forward face of the suction wing includes a V-notch configuration which is formed of a near linear edge segment and a far linear edge segment of the forward face, said linear edge segments (114, 115) connecting at a connection point to form an angle therebetween; wherein the pressure wing comprises a reference bending plane, said pressure wing reference bending plane running through the connecting point of the aftward face that results from a reference force directed perpendicularly against the far linear edge segment of the pressure wing; wherein the suction wing comprises a reference bending plane, said suction wing reference bending plane running through the connecting point of the suction wing that results from a reference force directed perpendicularly against the far linear edge segment of the suction wing; characterized in that, the pressure wing comprises a pressure wing chamber hollowed through a first surface thereof and offset from the reference bending plane of the pressure wing; and the suction wing comprises a suction wing chamber hollowed through a first surface thereof and offset from the reference bending plane of the suction wing; and the first surfaces of the pressure wing and the suction wing comprise one of: a circumferential face (106, 107) formed at a distal end of the pressure wing and the suction wing; and a contact face (86, 87) on each of the pressure wing and the suction wing. an airfoil defined between a concave pressure face and a laterally opposed convex suction face, wherein the pressure face and the suction face extend axially between opposite leading and trailing edges (28, 29) and radially between an outboard tip and an inboard end, the inboard end of the airfoil attaching to a root configured for connecting the rotor blade to the rotor disc; and a midspan shroud comprising a pressure wing extending from the pressure face of the airfoil and a suction wing extending from the suction face of the airfoil; wherein the pressure wing comprises an aftward face, the aftward face facing toward an aftward direction of the gas turbine; and the suction wing comprises a forward face, the forward face facing toward a forward direction of the gas turbine; wherein the aftward face of the pressure wing includes a V-notch configuration which is formed of a near linear edge segment and a far linear edge segment that define the aftward face, said linear edge segments (114, 115) being canted relative to each other and connecting at a connecting point and forming an angle therebetween; wherein the forward face of the suction wing includes a V-notch configuration which is formed of a near linear edge segment and a far linear edge segment of the forward face, said linear edge segments (114, 115) connecting at a connection point to form an angle therebetween; wherein the pressure wing comprises a reference bending plane, said pressure wing reference bending plane running through the connecting point of the aftward face that results from a reference force directed perpendicularly against the far linear edge segment of the pressure wing; wherein the suction wing comprises a reference bending plane, said suction wing reference bending plane running through the connecting point of the suction wing that results from a reference force directed perpendicularly against the far linear edge segment of the suction wing; characterized in that, the pressure wing comprises a pressure wing chamber hollowed through a first surface thereof and offset from the reference bending plane of the pressure wing; and the suction wing comprises a suction wing chamber hollowed through a first surface thereof and offset from the reference bending plane of the suction wing; and the first surfaces of the pressure wing and the suction wing comprise one of: a circumferential face (106, 107) formed at a distal end of the pressure wing and the suction wing; and a contact face (86, 87) on each of the pressure wing and the suction wing.