An integrated combustor nozzle for a turbomachine, comprising: a combustion liner extending along a radial direction between an inner liner segment and an outer liner segment , the combustion liner including a forward end portion , an aft end portion, a first side wall , and a second side wall , the aft end portion of the combustion liner defining a turbine nozzle , the combustion liner defining a cavity forward of the turbine nozzle , wherein the cavity extends between the first side wall and the second side wall ; an impingement cooling apparatus positioned within the cavity , the impingement cooling apparatus comprising: a flange ; and a plurality of impingement members configured to direct coolant to impinge upon at least one of the first side wall and the second side wall , wherein each impingement member of the plurality of impingement members extends from a respective inlet defined within the flange to a respective closed end , and wherein a plurality of impingement apertures are defined on each impingement member of the plurality of impingement members , wherein the plurality of impingement members comprises a first row of impingement members disposed proximate the first side wall and a second row of impingement members disposed proximate the second side wall , and wherein the first row of impingement members and the second row of impingement members diverge away from each other from an aft end to a forward end of impingement cooling apparatus . a combustion liner extending along a radial direction between an inner liner segment and an outer liner segment , the combustion liner including a forward end portion , an aft end portion, a first side wall , and a second side wall , the aft end portion of the combustion liner defining a turbine nozzle , the combustion liner defining a cavity forward of the turbine nozzle , wherein the cavity extends between the first side wall and the second side wall ; an impingement cooling apparatus positioned within the cavity , the impingement cooling apparatus comprising: a flange ; and a plurality of impingement members configured to direct coolant to impinge upon at least one of the first side wall and the second side wall , wherein each impingement member of the plurality of impingement members extends from a respective inlet defined within the flange to a respective closed end , and wherein a plurality of impingement apertures are defined on each impingement member of the plurality of impingement members , wherein the plurality of impingement members comprises a first row of impingement members disposed proximate the first side wall and a second row of impingement members disposed proximate the second side wall , and wherein the first row of impingement members and the second row of impingement members diverge away from each other from an aft end to a forward end of impingement cooling apparatus . a flange ; and a plurality of impingement members configured to direct coolant to impinge upon at least one of the first side wall and the second side wall , wherein each impingement member of the plurality of impingement members extends from a respective inlet defined within the flange to a respective closed end , and wherein a plurality of impingement apertures are defined on each impingement member of the plurality of impingement members , wherein the plurality of impingement members comprises a first row of impingement members disposed proximate the first side wall and a second row of impingement members disposed proximate the second side wall , and wherein the first row of impingement members and the second row of impingement members diverge away from each other from an aft end to a forward end of impingement cooling apparatus . <EOS>