A tip shroud for a turbine blade , comprising: a body coupled to a radial outer end of an airfoil of the turbine blade , the airfoil including a pressure side and a suction side and the body including a leading circumferential-facing edge and a trailing circumferential-facing edge ; at least one tip rail extending radially outwardly from the body and extending along a circumferential length of the body ; a first plurality of cooling passages defined in the body and extending circumferentially therein; and at least one first edge wall arrangement along at least one of the leading circumferential-facing edge and the trailing circumferential-facing edge of the body , each first edge wall arrangement including: a first edge wall extending axially and radially outwardly from the body along the at least one of the leading circumferential-facing edge and the trailing circumferential-facing edge of the body , the first edge wall including a first circumferentially facing surface facing towards the airfoil , and, characterized in that the tip shroud further comprises an exit surface adjacent the first edge wall and facing the first circumferentially facing surface , the exit surface having an exit opening defined therein through which at least one of the first plurality of cooling passages exits the body to allow coolant exiting the exit opening in the exit surface to cool the first edge wall , wherein the exit surface is angled relative to the first circumferentially facing surface of the first edge wall in a range of 15° to 80°. a body coupled to a radial outer end of an airfoil of the turbine blade , the airfoil including a pressure side and a suction side and the body including a leading circumferential-facing edge and a trailing circumferential-facing edge ; at least one tip rail extending radially outwardly from the body and extending along a circumferential length of the body ; a first plurality of cooling passages defined in the body and extending circumferentially therein; and at least one first edge wall arrangement along at least one of the leading circumferential-facing edge and the trailing circumferential-facing edge of the body , each first edge wall arrangement including: a first edge wall extending axially and radially outwardly from the body along the at least one of the leading circumferential-facing edge and the trailing circumferential-facing edge of the body , the first edge wall including a first circumferentially facing surface facing towards the airfoil , and, characterized in that the tip shroud further comprises an exit surface adjacent the first edge wall and facing the first circumferentially facing surface , the exit surface having an exit opening defined therein through which at least one of the first plurality of cooling passages exits the body to allow coolant exiting the exit opening in the exit surface to cool the first edge wall , wherein the exit surface is angled relative to the first circumferentially facing surface of the first edge wall in a range of 15° to 80°. a first edge wall extending axially and radially outwardly from the body along the at least one of the leading circumferential-facing edge and the trailing circumferential-facing edge of the body , the first edge wall including a first circumferentially facing surface facing towards the airfoil , and, characterized in that the tip shroud further comprises an exit surface adjacent the first edge wall and facing the first circumferentially facing surface , the exit surface having an exit opening defined therein through which at least one of the first plurality of cooling passages exits the body to allow coolant exiting the exit opening in the exit surface to cool the first edge wall , wherein the exit surface is angled relative to the first circumferentially facing surface of the first edge wall in a range of 15° to 80°. <EOS>