Abstract: A turbomachine defines an axial direction, a radial direction perpendicular to the axial direction, and a circumferential direction extending concentrically around the axial direction. The turbomachine includes a nozzle having an inner platform, an outer platform, and an airfoil. The airfoil includes a leading edge, a trailing edge downstream of the leading edge, a pressure side surface, and a suction side surface opposite the pressure side surface. The trailing edge is orthogonal with the outer platform in an axial-radial plane and the trailing edge is oblique to the inner platform in the axial-radial plane.

Abstract: A turbomachine defines an axial direction, a radial direction perpendicular to the axial direction, and a circumferential direction extending concentrically around the axial direction. The turbomachine includes a nozzle having an inner platform, an outer platform, and an airfoil. The airfoil includes a leading edge, a trailing edge downstream of the leading edge, a pressure side surface, and a suction side surface opposite the pressure side surface. The trailing edge defines a circular arc between the inner platform and the outer platform.

Abstract: A rotor blade of a turbomachine includes an airfoil. The airfoil includes a root and a tip which define a span of the airfoil therebetween. The airfoil also includes a leading edge and a trailing edge downstream of the leading edge along a flow direction. The leading edge and the trailing edge each extend across the span of the airfoil from the root to the tip. The airfoil further includes a pressure side surface and a suction side surface. The pressure side surface and the suction side surface are continuous about the trailing edge and collectively define an arc centered on the trailing edge. The arc has a semi-major axis and a semi-minor axis. The semi-major axis and the semi-minor axis of the arc define an axis ratio, and the axis ratio varies over the span of the airfoil.

Abstract: A turbomachine defines an axial direction, a radial direction perpendicular to the axial direction, and a circumferential direction extending concentrically around the axial direction. The turbomachine includes a nozzle having an inner platform, an outer platform, and an airfoil. The airfoil includes a leading edge, a trailing edge downstream of the leading edge, a pressure side surface, and a suction side surface opposite the pressure side surface. The trailing edge is orthogonal with the outer platform in an axial-radial plane and the trailing edge is oblique to the inner platform in the axial-radial plane.

Abstract: A turbomachine defines an axial direction, a radial direction perpendicular to the axial direction, and a circumferential direction extending concentrically around the axial direction. The turbomachine includes a nozzle having an inner platform, an outer platform, and an airfoil. The airfoil includes a leading edge, a trailing edge downstream of the leading edge, a pressure side surface, and a suction side surface opposite the pressure side surface. The trailing edge defines a circular arc between the inner platform and the outer platform.

Abstract: A rotor blade of a turbomachine includes an airfoil. The airfoil includes a root and a tip which define a span of the airfoil therebetween. The airfoil also includes a leading edge and a trailing edge downstream of the leading edge along a flow direction. The leading edge and the trailing edge each extend across the span of the airfoil from the root to the tip. The airfoil further includes a pressure side surface and a suction side surface. The pressure side surface and the suction side surface are continuous about the trailing edge and collectively define an arc centered on the trailing edge. The arc has a semi-major axis and a semi-minor axis. The semi-major axis and the semi-minor axis of the arc define an axis ratio, and the axis ratio varies over the span of the airfoil.