FIN FOR INTERNAL COOLING OF VANE WALL

Gas turbine engines (100) generally comprise a first-stage nozzle guide vane (200). Temperatures in a trailing-edge area (212) of the suction-side wall (210) of such vanes (200) can exceed material and coating limits. While an insert (300) can be used to form passages (236, 238) for cooling air to flow along the inner surfaces of the vane walls (210, 220), design constraints prevent the insert (300) from extending beyond a certain point into the trailing edge of the vane (200). Accordingly, a fin (400) is disclosed for insertion downstream of the insert (300). By eliminating sudden expansion beyond the downstream end of the insert (300) and maintaining the speed of the cooling air across the trailing-edge area (212) of the suction-side wall (210), the fin (400) improves the cooling coefficient for the trailing-edge area (212), so as to prevent or reduce excessive temperatures in the trailing-edge area (212).