TURBOMACHINE NOZZLE WITH AN AIRFOIL HAVING A CURVILINEAR TRAILING EDGE

A turbomachine (10) defines an axial direction (A), a radial direction (R) perpendicular to the axial direction (A), and a circumferential direction (C) extending concentrically around the axial direction (A). The turbomachine (10) includes a nozzle (202) having an inner platform (208), an outer platform (210), and an airfoil (212). The airfoil (212) includes a leading edge (218), a trailing edge (220) downstream of the leading edge (218), a pressure side surface (224), and a suction side surface (226) opposite the pressure side surface (224). The trailing edge (220) is orthogonal with the outer platform (210) in an axial-radial plane, and the trailing edge (220) is oblique to the inner platform in the axial-radial plane.