The present disclosure relates to a combustion section (100, 500, 800, 900, 1200, 1300, 1400, 1500) for a turbine engine. The combustion section (100, 500, 800, 900, 1200, 1300, 1400, 1500) includes a wall (102, 502, 802, 902, 1202, 1302, 1402, 1502) that at least partially defines a combustion chamber (104, 504, 804, 904, 1204, 1304, 1404, 1504). A fuel nozzle (108, 508, 708, 808, 908, 1208, 1308, 1408, 1508) extends through the wall (102, 502, 802, 902, 1202, 1302, 1402, 1502) and opens into the combustion chamber (104, 504, 804, 904, 1204, 1304, 1404, 1504). The fuel nozzle (108, 508, 708, 808, 908, 1208, 1308, 1408, 1508) comprises a fuel nozzle body (110, 510, 710, 810, 910, 1210, 1310, 1410, 1510) defining a central channel (114, 514, 714, 814, 914, 1214, 1314, 1414, 1514) that exhausts into the combustion chamber (104, 504, 804, 904, 1204, 1304, 1404, 1504) at a nozzle outlet (118, 518, 818, 918, 1218, 1318, 1418, 1518). A swirler (120, 220, 320, 420, 520, 720, 820, 920, 1020, 1120, 1220, 1320, 1420, 1520, 1620, 1720) is provided within the central channel (114, 514, 714, 814, 914, 1214, 1314, 1414, 1514) and has a body centerline (122, 222, 322, 422, 522, 822, 922, 1022, 1122, 1222, 1322, 1422, 1522, 1622, 1722). The swirler (120, 220, 320, 420, 520, 720, 820, 920, 1020, 1120, 1220, 1320, 1420, 1520, 1620, 1720) is movable within the central channel (114, 514, 714, 814, 914, 1214, 1314, 1414, 1514) about a plane of movement (1378, 1478, 1578), thereby enabling adjustment of flow characteristics within the fuel nozzle (108, 508, 708, 808, 908, 1208, 1308, 1408, 1508) to influence mixing and combustion behavior within the combustion chamber (104, 504, 804, 904, 1204, 1304, 1404, 1504).