Impingement cooling apparatus support structure and method of manufacture

A turbomachine comprising:

• a compressor;
• a compressor discharge casing disposed downstream from the compressor;
• a turbine disposed downstream from the compressor discharge casing;
• and
• an annular combustion system disposed within the compressor discharge casing, the annular combustion system including a plurality of integrated combustor nozzles disposed in an annular array about an axial centerline of the turbomachine, wherein each integrated combustor nozzle comprises:
• a fuel injection panel extending radially between an inner liner segment and an outer liner segment, the fuel injection panel including a forward end portion, an aft end portion, a first side wall, and a second side wall, the aft end portion of the fuel injection panel defining a turbine nozzle, the fuel injection panel defining a cavity forward of the turbine nozzle, the cavity extending between the first side wall and the second side wall, wherein a first rib and a second rib extend from one of the first side wall or the second side wall and within the cavity, the first rib and the second rib axially spaced apart such that the cavity is partitioned into a forward cavity portion, a middle cavity portion, and an aft cavity portion, and wherein the first rib and the second rib define one or more openings such that the forward cavity portion, the middle cavity portion, and the aft cavity portion are in fluid communication;
• a fuel injector having an inlet disposed within the middle cavity portion, the fuel injector extending through one of the first side wall or the second side wall;
• and
• an impingement cooling apparatus positioned within the aft cavity portion, the impingement cooling apparatus comprising:
• a flange;
• a plurality of impingement members each extending from a respective opening defined in the flange to a respective closed end, each impingement member including an impingement wall and a solid wall spaced apart from the impingement wall, wherein each impingement member defines a plurality of impingement apertures that direct air to impinge upon one of the first side wall and the second side wall, wherein the inlet of the fuel injector receives post-impingement air from the aft cavity portion;
• and
• stand-offs extending from each impingement member of the plurality of impingement members, wherein the stand-offs space apart each impingement member of the plurality of impingement members from surrounding surfaces.