A turbine engine comprising an annular flow duct, the flow duct comprising a plurality of vanes which defines the flow duct about a turbine axis (C L ), the plurality of vanes comprising: an airfoil section comprising pressure and suction surfaces extending from a leading edge to a trailing edge ; an inner platform attached to the airfoil section along an inner flow boundary , the inner flow boundary extending from an upstream inlet region of the vanes to a downstream outlet region of the vanes; and an outer platform attached to the airfoil section along an outer flow boundary , the outer flow boundary extending from the upstream inlet region to the downstream outlet region; wherein the flow duct further comprises an inlet area (A1) and an outlet area (A2), wherein the inlet area (A1) has: an inner radius (R ID ) defined as the radial distance from the turbine axis (C L ) to the inner flow boundary at the upstream end of the inner platform , and an outer radius (R OD ) defined as the radial distance from the turbine axis (C L ) to the outer flow boundary at the upstream end of the outer platform , and the outlet area (A2) has: an inner radius (R ID ) defined as the radial distance from the turbine axis (C L ) to the inner flow boundary at the downstream end of the inner platform , and an outer radius (R OD ) defined as the radial distance from the turbine axis (C L ) to the outer flow boundary at the downstream end of the outer platform , and the inlet and outlet areas are defined as: A 1 = π R OD 2 − R ID 2 | inlet and A 2 = π R OD 2 − R ID 2 | outlet , characterized in that an area ratio (AR) of the outlet area (A2) to the inlet area (A1) is greater than 2.4 and less than 2.9. an airfoil section comprising pressure and suction surfaces extending from a leading edge to a trailing edge ; an inner platform attached to the airfoil section along an inner flow boundary , the inner flow boundary extending from an upstream inlet region of the vanes to a downstream outlet region of the vanes; wherein the flow duct further comprises an inlet area (A1) and an outlet area (A2), wherein the inlet area (A1) has: an inner radius (R ID ) defined as the radial distance from the turbine axis (C L ) to the inner flow boundary at the upstream end of the inner platform , and an outer radius (R OD ) defined as the radial distance from the turbine axis (C L ) to the outer flow boundary at the upstream end of the outer platform , and the outlet area (A2) has: an inner radius (R ID ) defined as the radial distance from the turbine axis (C L ) to the inner flow boundary at the downstream end of the inner platform , and an outer radius (R OD ) defined as the radial distance from the turbine axis (C L ) to the outer flow boundary at the downstream end of the outer platform , and the inlet and outlet areas are defined as: A 1 = π R OD 2 − R ID 2 | inlet and A 2 = π R OD 2 − R ID 2 | outlet , characterized in that an area ratio (AR) of the outlet area (A2) to the inlet area (A1) is greater than 2.4 and less than 2.9. an inner radius (R ID ) defined as the radial distance from the turbine axis (C L ) to the inner flow boundary at the upstream end of the inner platform , and an outer radius (R OD ) defined as the radial distance from the turbine axis (C L ) to the outer flow boundary at the upstream end of the outer platform , and an inner radius (R ID ) defined as the radial distance from the turbine axis (C L ) to the inner flow boundary at the downstream end of the inner platform , and an outer radius (R OD ) defined as the radial distance from the turbine axis (C L ) to the outer flow boundary at the downstream end of the outer platform , <EOS>