Impingement cooling apparatus for turbomachine

1. An integrated combustor nozzle 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, 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; and

a plurality of impingement members configured to direct air to impinge upon at least one of the first side wall and the second side wall, the plurality of impingement members comprising 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, wherein a collection passageway is defined between the first row of impingement members and the second row of impingement members such that the collection passageway receives post-impingement air from gaps defined between the plurality of impingement members, wherein the first row of impingement members and the second row of impingement members diverge away from one another in a direction extending from the aft end portion towards the forward end portion of the combustion liner such that a transverse distance of the collection passage gradually increases in the direction from the aft end portion to the forward end portion, wherein the inlet of the fuel injector receives the post-impingement air from the collection passageway, 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.

2. The integrated combustor nozzle as in claim 1 , wherein each impingement member of the plurality of impingement members includes an impingement wall spaced apart from a solid wall, and wherein each of the plurality of impingement apertures are defined on the impingement wall of each respective impingement member of the plurality of impingement members.

3. The integrated combustor nozzle as in claim 2 , wherein the impingement wall of each impingement member is contoured to correspond to one of the first side wall or the second side wall of the combustion liner.

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

5. The integrated combustor nozzle as in claim 4 , wherein the impingement wall, the first solid side wall, the second solid side wall, and the solid wall of each impingement member of the plurality of impingement members collectively define an internal volume.

6. The integrated combustor nozzle as in claim 1 , wherein each impingement member in the plurality of impingement members is spaced apart from adjacent impingement members.

7. A turbomachine comprising:

a compressor;

a compressor discharge casing disposed downstream from the compressor;

a turbine disposed downstream from the compressor discharge casing;

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 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, 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 cavity, the impingement cooling apparatus comprising:

a flange; and

a plurality of impingement members configured to direct air to impinge upon at least one of the first side wall and the second side wall, the plurality of impingement members comprising 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, wherein a collection passageway is defined between the first row of impingement members and the second row of impingement members such that the collection passageway receives post-impingement air from gaps defined between the plurality of impingement members, wherein the first row of impingement members and the second row of impingement members diverge away from one another in a direction extending from the aft end portion towards the forward end portion of the combustion liner such that a transverse distance of the collection passage gradually increases in the direction from the aft end portion to the forward end portion, wherein the inlet of the fuel injector receives the post-impingement air from the collection passageway, 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.

8. The turbomachine as in claim 7 , wherein each impingement member of the plurality of impingement members includes an impingement wall spaced apart from a solid wall, and wherein each of the plurality of impingement apertures are defined on the impingement wall of each respective impingement member of the plurality of impingement members.

9. The turbomachine as in claim 8 , wherein the impingement wall of each impingement member is contoured to correspond to one of the first side wall or the second side wall of the combustion liner.

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

11. The turbomachine as in claim 10 , wherein the impingement wall, the first solid side wall, the second solid side wall, and the solid wall of each impingement member of the plurality of impingement members collectively define an internal volume.

12. The turbomachine as in claim 7 , wherein each impingement member in the plurality of impingement members is spaced apart from adjacent impingement members.

13. The integrated combustor nozzle as in claim 2 , wherein a plurality of cross-supports extend between the solid wall and the impingement wall.

14. The integrated combustor nozzle as in claim 13 , wherein a first protrusion extends from the impingement wall, a second protrusion extends from the solid wall, and each of the plurality of cross-supports extend between the first protrusion and the second protrusion.