A nozzle (24, 224) for a turbine system, the nozzle (24, 224) comprising: an airfoil comprising exterior surface defining a pressure side and a suction side extending between a leading edge and a trailing edge, the airfoil further defining a tip and a root; an inner sidewall (42, 242) connected to the airfoil at the tip, the inner sidewall (42, 242) including a peripheral edge (70, 80, 270, 280) defining a pressure side slash face (72, 82, 272, 282), a suction side slash face (74, 84, 274, 284), a leading edge face (76, 86, 276, 286), and a trailing edge face (78, 88, 278, 288); an outer sidewall (44, 244) connected to the airfoil at the root, the outer sidewall (44, 244) including a peripheral edge (70, 80, 270, 280) defining a pressure side slash face (72, 82, 272, 282), a suction side slash face (74, 84, 274, 284), a leading edge face (76, 86, 276, 286), and a trailing edge face (78, 88, 278, 288); and characterized in that the nozzle (24, 224) further comprises a stiffening member extending circumferentially on at least one of a radially inner side of the inner sidewall (42, 242) and a radially outer side of the outer sidewall (44, 244), wherein at least one of the inner sidewall (42, 242) pressure side slash face (72, 82, 272, 282), the inner sidewall (42, 242) suction side slash face (74, 84, 274, 284), the outer sidewall (44, 244) pressure side slash face (72, 82, 272, 282), or the outer sidewall (44, 244) suction side slash face (74, 84, 274, 284) includes a first swept surface extending at a first angle relative to an axis of the turbine system and a second swept surface extending at a second angle relative to an axis of the turbine system, the first swept surface and the second swept surface meeting at a joining line that is circumferentially aligned with the stiffening member. an airfoil comprising exterior surface defining a pressure side and a suction side extending between a leading edge and a trailing edge, the airfoil further defining a tip and a root; an inner sidewall (42, 242) connected to the airfoil at the tip, the inner sidewall (42, 242) including a peripheral edge (70, 80, 270, 280) defining a pressure side slash face (72, 82, 272, 282), a suction side slash face (74, 84, 274, 284), a leading edge face (76, 86, 276, 286), and a trailing edge face (78, 88, 278, 288); an outer sidewall (44, 244) connected to the airfoil at the root, the outer sidewall (44, 244) including a peripheral edge (70, 80, 270, 280) defining a pressure side slash face (72, 82, 272, 282), a suction side slash face (74, 84, 274, 284), a leading edge face (76, 86, 276, 286), and a trailing edge face (78, 88, 278, 288); and characterized in that the nozzle (24, 224) further comprises a stiffening member extending circumferentially on at least one of a radially inner side of the inner sidewall (42, 242) and a radially outer side of the outer sidewall (44, 244), wherein at least one of the inner sidewall (42, 242) pressure side slash face (72, 82, 272, 282), the inner sidewall (42, 242) suction side slash face (74, 84, 274, 284), the outer sidewall (44, 244) pressure side slash face (72, 82, 272, 282), or the outer sidewall (44, 244) suction side slash face (74, 84, 274, 284) includes a first swept surface extending at a first angle relative to an axis of the turbine system and a second swept surface extending at a second angle relative to an axis of the turbine system, the first swept surface and the second swept surface meeting at a joining line that is circumferentially aligned with the stiffening member.