Turbomachine rotor blade

A rotor blade for a turbomachine, comprising:

• an airfoil defining at least one cooling passage, the airfoil further defining a camber line extending from a leading edge to a trailing edge;
• and
• a tip shroud coupled to the airfoil, the tip shroud comprising a pressure side face, a suction side face, a leading edge face, and a trailing edge face, the tip shroud and the airfoil defining a core fluidly coupled to the at least one cooling passage, the core comprising a plurality of outlet apertures, each of the plurality of outlet apertures comprising an opening defined in an exterior surface of the tip shroud,
• wherein the opening of a first outlet aperture of the plurality of outlet apertures is defined in the trailing edge face and the opening of a second outlet aperture of the plurality of outlet apertures is defined in one of the pressure side face, the suction side face, or the leading edge face, and
• wherein the first outlet aperture is oriented to exhaust cooling fluid through the opening of the first outlet aperture in a direction that is within 15 degrees of parallel to the camber line at the trailing edge and is oriented with a hot gas path direction of flow through the turbomachine, and the second outlet aperture is oriented to exhaust cooling fluid through the opening of the second outlet aperture in a direction that is greater than 15 degrees from parallel to the camber line at the trailing edge, whereby the cooling fluid exhausted through the opening of the first outlet aperture supplies additional thrust to the rotor blade and improved aerodynamic performance is facilitated.