A turbomachine comprising: a compressor; a combustor operatively connected to the compressor; an end cover mounted to the combustor; and an injection nozzle assembly (38, 39, 40) operatively connected to the combustor, the injection nozzle assembly (38, 39, 40) including a fuel inlet at a first end thereof and extending to a circumferential wall (82, 166, 224, 324) at a second end thereof, a plurality of tube elements (90, 175, 230, 330) arranged in a plurality of rows that extend circumferentially about a central receiving port, a fuel inlet tube extending from the end cover to the central receiving port, and a fuel delivery plenum for distributing fuel to each of the plurality of tube elements (90, 175, 230, 330) each of the plurality of tube elements (90, 175, 230, 330) defining a fluid passage including a body having an inlet (132, 198, 244, 344) at a first end thereof and an outlet (134, 200, 245, 345) at a second end thereof, the outlet (134, 200, 245, 345) projecting beyond the circumferential wall (82, 166, 224, 324) of the injection nozzle assembly (38, 39, 40), wherein fuel flows from the fuel inlet through the fuel inlet tube to the central receiving port and into the fuel delivery plenum for distribution to each of the plurality of tube elements (90, 175, 230, 330) where it is mixed with air and introduced to the combustor wherein each of the plurality of tube elements (90, 175, 230, 330) arranged in a first row of the plurality of rows, directly adjacent the central receiving port, is angled relative to a longitudinal axis of the injection nozzle assembly (38, 39, 40) or has a region that is angled relative to the tube elements (90, 175, 230, 330) of the other rows. a compressor; a combustor operatively connected to the compressor; an end cover mounted to the combustor; and an injection nozzle assembly (38, 39, 40) operatively connected to the combustor, the injection nozzle assembly (38, 39, 40) including a fuel inlet at a first end thereof and extending to a circumferential wall (82, 166, 224, 324) at a second end thereof, a plurality of tube elements (90, 175, 230, 330) arranged in a plurality of rows that extend circumferentially about a central receiving port, a fuel inlet tube extending from the end cover to the central receiving port, and a fuel delivery plenum for distributing fuel to each of the plurality of tube elements (90, 175, 230, 330) each of the plurality of tube elements (90, 175, 230, 330) defining a fluid passage including a body having an inlet (132, 198, 244, 344) at a first end thereof and an outlet (134, 200, 245, 345) at a second end thereof, the outlet (134, 200, 245, 345) projecting beyond the circumferential wall (82, 166, 224, 324) of the injection nozzle assembly (38, 39, 40), wherein fuel flows from the fuel inlet through the fuel inlet tube to the central receiving port and into the fuel delivery plenum for distribution to each of the plurality of tube elements (90, 175, 230, 330) where it is mixed with air and introduced to the combustor wherein each of the plurality of tube elements (90, 175, 230, 330) arranged in a first row of the plurality of rows, directly adjacent the central receiving port, is angled relative to a longitudinal axis of the injection nozzle assembly (38, 39, 40) or has a region that is angled relative to the tube elements (90, 175, 230, 330) of the other rows.