A nozzle segment assembly 102 for a gas turbine engine 10 may generally include inner and outer ring support segments 116 and a nozzle fairing 104 positioned between the inner and outer ring support segments 114, 116. The nozzle fairing may be formed from a ceramic matrix composite (CMC) material and may include both an outer endwall 110 and an inner endwall 108. In addition, the nozzle fairing may include a strut vane 106 extending between the inner and outer endwalls 108, 110. The nozzle segment assembly may also include a metallic strut extending through the strut vane between the outer and inner ring supports and at least one secondary vane 112 configured to be received through at least one of the outer endwall 110 or the inner endwall 108 of the nozzle fairing 104 such that the at least one secondary vane extends between the inner and outer endwalls at a location adjacent to the strut vane.