Propulsion assembly for an aircraft comprising a stator vane integrated into an upstream part of a mounting pylon of reduced height

A propulsion assembly for an aircraft comprising a dual-flow turbine engine comprising a fan;

• an aerodynamic outer shroud acting as a nacelle arranged around the fan;
• a mounting pylon for fastening the turbine engine to a wing element of the aircraft, the propulsion assembly having a primary gas flow path;
• and a secondary gas flow path defined by an inner radial defining surface as well by an outer radial defining surface formed by the aerodynamic outer shroud, the turbine engine further including an annular row of stator vanes arranged in the secondary flow path downstream from the fan, each stator vane extending through the secondary flow path while having a tip end connected to the aerodynamic outer shroud and a root end connected to the inner radial defining surface of the secondary flow path, the mounting pylon comprising an upstream part housed in the secondary flow path and a downstream part arranged downstream from a trailing edge of the aerodynamic outer shroud, the trailing edge of the aerodynamic outer shroud is arranged entirely upstream from a leading edge of the wing element,
• wherein the upstream part of the mounting pylon housed in the secondary flow path extends radially from the inner radial defining surface, along a radial pylon height strictly less than a total radial height of the secondary flow path, and in that the upstream part of the mounting pylon extends in the downstream direction from a root part of one of the stator vanes, wherein the upstream part of the mounting pylon is radially surrounded by the secondary flow path and the downstream part of the mounting pylon is not surrounded by the secondary flow path, and wherein the one stator vane includes, radially outwards from the upstream part of the mounting pylon, a free trailing edge of the stator vane extending to the aerodynamic outer shroud.