Impingement cooling apparatus support structure and method of manufacture

1. An integrated combustor nozzle, comprising:

a combustion liner extending radially 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, 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, the stand-offs spacing apart each impingement member of the plurality of impingement members from surrounding surfaces.

2. The integrated combustor nozzle as in claim 1 , wherein each impingement member of the plurality of impingement members includes a first solid side wall that extends between the impingement wall and the solid wall and a second solid side wall that extends between the impingement wall and the solid wall.

3. The integrated combustor nozzle as in claim 2 , wherein the stand-offs comprise side wall stand-offs, and wherein the side wall stand-offs extend from and couple the first solid side wall of an impingement member to the second solid side wall of a neighboring impingement member.

4. The integrated combustor nozzle as in claim 2 , wherein the stand-offs comprise impingement wall stand-offs, and wherein each impingement wall stand-off extends from the impingement wall of one of the plurality of impingement members and contacts one of the first side wall or the second side wall of the combustion liner.

5. The integrated combustor nozzle as in claim 2 , wherein the stand-offs comprise side wall stand-offs and impingement wall stand-offs, and wherein at least one side wall stand-off and at least one impingement wall stand-off are disposed proximate the flange on each impingement member of the plurality of impingement members, and wherein at least one side wall stand-off and at least one impingement wall stand-off are disposed proximate the closed end of each impingement member of the plurality of impingement members.

6. The integrated combustor nozzle as in claim 1 , wherein each impingement member of the plurality of impingement members defines an internal volume, wherein each impingement member of the plurality of impingement members includes a first protrusion and a second protrusion within the internal volume of the impingement member, the first protrusion extending from the impingement wall and the second protrusion extending from the solid wall, and wherein each of a plurality of cross-supports extends directly from the first protrusion through the internal volume to the second protrusion.

7. 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.

8. The turbomachine as in claim 7 , wherein each impingement member of the plurality of impingement members includes a first solid side wall that extends between the impingement wall and the solid wall and a second solid side wall that extends between the impingement wall and the solid wall.

9. The turbomachine as in claim 8 , wherein the stand-offs comprise side wall stand-offs, and wherein the side wall stand-offs extend from and couple the first solid side wall of an impingement member to the second solid side wall of a neighboring impingement member.

10. The turbomachine as in claim 8 , wherein the stand-offs comprise impingement wall stand-offs, and wherein each impingement wall stand-off extends from the impingement wall of one of the plurality of impingement members and contacts one of the first side wall or the second side wall of the fuel injection panel.

11. The turbomachine as in claim 8 , wherein the stand-offs comprise side wall stand-offs and impingement wall stand-offs, and wherein at least one side wall stand-off and at least one impingement wall stand-off are disposed proximate the flange on each impingement member of the plurality of impingement members, and wherein at least one side wall stand-off and at least one impingement wall stand-off are disposed proximate the closed end of each impingement member of the plurality of impingement members.

12. The turbomachine as in claim 8 , wherein each impingement member of the plurality of impingement members comprises cross-supports that extend between the impingement wall and the solid wall.

13. The turbomachine as in claim 12 , wherein each impingement member of the plurality of impingement members includes a first protrusion extending from the impingement wall and a second protrusion extending from the solid wall, and wherein each of a plurality of cross-supports extends directly between the first protrusion and the second protrusion.

14. The turbomachine as in claim 13 , wherein each of the plurality of cross-supports includes a first support bar and a second support bar that intersect with one another within the impingement member.

15. The integrated combustor nozzle as in claim 6 , wherein the first protrusion and the second protrusion each define a T-shaped cross-section.