A nozzle segment assembly for a gas turbine engine, the nozzle segment assembly comprising: an outer ring support segment and an inner ring support segment; a nozzle fairing positioned between the inner and outer ring support segments (114, 116), the nozzle fairing being formed from a ceramic matrix composite material, the nozzle fairing including an outer endwall configured to be positioned adjacent to the outer ring support segment and an inner endwall configured to be positioned adjacent to the inner ring support segment, the nozzle fairing further comprising a strut vane extending between the inner and outer endwalls (108, 110); a metallic strut extending through the strut vane between the outer and inner ring supports (116, 114); and at least one secondary vane configured to be received through at least one of the outer endwall or the inner endwall of the nozzle fairing such that the at least one secondary vane extends between the inner and outer endwalls (108, 110) at a location adjacent to the strut vane, characterized in that the outer endwall defines an outer slot and the inner endwall defines an inner slot, wherein separate portions of the at least one secondary vane are configured to be received within the outer and inner slots, and the at least one secondary vane extends radially between an outer vane end and an inner vane end, the at least one secondary vane being configured to extend through the inner and outer slots (144, 146) such that the outer vane end extends radially outwardly from the outer endwall and the inner vane end extend radially inwardly from the inner endwall, wherein the at least one secondary vane comprises a mounting tab extending from the outer vane end, the mounting tab defining a through-hole configured to receive a mounting pin for coupling the at least one secondary vane to the outer ring support. an outer ring support segment and an inner ring support segment; a nozzle fairing positioned between the inner and outer ring support segments (114, 116), the nozzle fairing being formed from a ceramic matrix composite material, the nozzle fairing including an outer endwall configured to be positioned adjacent to the outer ring support segment and an inner endwall configured to be positioned adjacent to the inner ring support segment, the nozzle fairing further comprising a strut vane extending between the inner and outer endwalls (108, 110); a metallic strut extending through the strut vane between the outer and inner ring supports (116, 114); and at least one secondary vane configured to be received through at least one of the outer endwall or the inner endwall of the nozzle fairing such that the at least one secondary vane extends between the inner and outer endwalls (108, 110) at a location adjacent to the strut vane, characterized in that the outer endwall defines an outer slot and the inner endwall defines an inner slot, wherein separate portions of the at least one secondary vane are configured to be received within the outer and inner slots, and the at least one secondary vane extends radially between an outer vane end and an inner vane end, the at least one secondary vane being configured to extend through the inner and outer slots (144, 146) such that the outer vane end extends radially outwardly from the outer endwall and the inner vane end extend radially inwardly from the inner endwall, wherein the at least one secondary vane comprises a mounting tab extending from the outer vane end, the mounting tab defining a through-hole configured to receive a mounting pin for coupling the at least one secondary vane to the outer ring support.