Combustor having a wake energizer

A turbomachine comprising:

• a compressor section;
• a turbine section;
• and
• a combustor disposed downstream from the compressor section and upstream from the turbine section, the combustor defining an axial direction, a radial direction perpendicular to the axial direction, and a circumferential direction extending around the axial direction, the combustor comprising:
• an end cover;
• an aft frame;
• a combustion liner extending between the end cover and the aft frame and defining a combustion chamber;
• at least one fuel nozzle extending from the end cover and in fluid communication with the combustion chamber;
• an outer sleeve spaced apart from and surrounding the combustion liner such that an annulus is defined therebetween, and wherein the outer sleeve defines a plurality of apertures;
• and
• a wake energizer mounted on the outer sleeve and extending radially outward from the outer sleeve, the wake energizer defining a radially outer surface, a radially inner surface, a forward surface facing the end cover, an aft surface facing the aft frame, and side surfaces connecting the forward surface and the aft surface, the wake energizer defining a plurality of passages that are each angled with respect to the axial direction and the radial direction of the combustor, the plurality of passages each extending between a respective inlet and a respective outlet, wherein a first inlet of a first passage of the plurality of passages is disposed on the radially outer surface, wherein a second inlet of a second passage of the plurality of passages is disposed on the aft surface, the outlet of each passage of the plurality of passages aligning and in fluid communication with a respective aperture of the plurality of apertures of the outer sleeve.