INTEGRATED COMBUSTOR NOZZLE FOR A TURBOMACHINE

An integrated combustor nozzle (100) includes a combustion liner (110) that extends radially between an inner liner segment (106) and an outer liner segment (108), the combustion liner (110) includes a forward end portion (112), an aft end portion, a first side wall (116), and a second side wall (118). The aft end portion (114) of the combustion liner (110) defines a turbine nozzle (120). The combustion liner (110) defines a cavity (126) forward of the turbine nozzle (120). The cavity (126) extends between the first side wall (116) and the second side wall (118). An impingement cooling apparatus positioned within the cavity (126). The impingement cooling apparatus includes a flange (310, 311). The impingement cooling apparatus further includes a plurality of impingement members (302) configured to direct coolant to impinge upon the first side wall (116) and the second side wall (118). Each impingement member (302) extends from a respective inlet (313) defined within the flange (310, 311) to a respective closed end (312). A plurality of impingement apertures (304) are defined on each impingement member (302).