A gas turbine engine comprising: a compressor section comprising an outlet guide vane assembly; a mid-frame section arranged downstream of the compressor section, wherein the mid-frame section comprises an inner compressor exit diffuser, wherein a forward side of the inner compressor exit diffuser interfaces with the outlet guide vane assembly; and a turbine section arranged downstream of the mid-frame section, wherein the outlet guide vane assembly comprises: an inner shroud comprising a circular shape and extending axially, and an outlet guide vane comprising an airfoil radially extending between an airfoil root and an inner platform, wherein the inner shroud comprises a flange arranged at an aft side and extending radially downwardly, wherein the inner platform comprises a flange arranged at a forward side and extending radially downwardly, and wherein the outlet guide vane is connected to the inner shroud at an interface of the inner platform flange and the inner shroud flange, characterized in that, the inner compressor exit diffusor comprises a recess configured to adapt the connected inner platform flange and the inner shroud flange such that the connected inner shroud flange and the inner platform flange slide along the recess on the inner compressor exit diffuser in a circumferential direction when assembling the outlet guide vane assembly into the gas turbine engine. a compressor section comprising an outlet guide vane assembly; a mid-frame section arranged downstream of the compressor section, wherein the mid-frame section comprises an inner compressor exit diffuser, wherein a forward side of the inner compressor exit diffuser interfaces with the outlet guide vane assembly; and a turbine section arranged downstream of the mid-frame section, wherein the outlet guide vane assembly comprises: an inner shroud comprising a circular shape and extending axially, and an outlet guide vane comprising an airfoil radially extending between an airfoil root and an inner platform, wherein the inner shroud comprises a flange arranged at an aft side and extending radially downwardly, wherein the inner platform comprises a flange arranged at a forward side and extending radially downwardly, and wherein the outlet guide vane is connected to the inner shroud at an interface of the inner platform flange and the inner shroud flange, an inner shroud comprising a circular shape and extending axially, and an outlet guide vane comprising an airfoil radially extending between an airfoil root and an inner platform, wherein the inner shroud comprises a flange arranged at an aft side and extending radially downwardly, wherein the inner platform comprises a flange arranged at a forward side and extending radially downwardly, and wherein the outlet guide vane is connected to the inner shroud at an interface of the inner platform flange and the inner shroud flange, characterized in that, the inner compressor exit diffusor comprises a recess configured to adapt the connected inner platform flange and the inner shroud flange such that the connected inner shroud flange and the inner platform flange slide along the recess on the inner compressor exit diffuser in a circumferential direction when assembling the outlet guide vane assembly into the gas turbine engine.