A combustor of a gas turbine, comprising: a first-stage combustor and a second-stage combustor, wherein the second-stage combustor is arranged downstream of the first-stage combustor and includes a second-stage combustion chamber (20; 220) extending along an axial direction; an axial lance injector; a flame stabilizer device (23; 223); wherein the axial lance injector comprises: an elongated streamlined body extending in the axial direction from the first-stage combustor into the second-stage combustion chamber (20; 220) through a transition region of the second-stage combustor, wherein the elongated streamlined body and the transition region are configured to prevent gas flowing from the first-stage combustor to the second-stage combustion chamber (20; 220) from recirculating in the transition region; a plurality of first cross-flow injection nozzles (32; 132) and a plurality of second cross-flow injection nozzles (33; 133) provided on the elongated streamlined body at respective axial locations; and wherein the flame stabilizer device (23; 223) is arranged downstream of the first cross-flow injection nozzles (32; 132) and of the second cross-flow injection nozzles (33; 133); characterized in that the flame stabilizer device (23; 223) comprises a full-load flame stabilizer at a downstream end of the elongated streamlined body and at least one partial-load flame stabilizer between the second cross-flow injection nozzles (33; 133) and the full-load flame stabilizer. a first-stage combustor and a second-stage combustor, wherein the second-stage combustor is arranged downstream of the first-stage combustor and includes a second-stage combustion chamber (20; 220) extending along an axial direction; an axial lance injector; a flame stabilizer device (23; 223); wherein the axial lance injector comprises: an elongated streamlined body extending in the axial direction from the first-stage combustor into the second-stage combustion chamber (20; 220) through a transition region of the second-stage combustor, wherein the elongated streamlined body and the transition region are configured to prevent gas flowing from the first-stage combustor to the second-stage combustion chamber (20; 220) from recirculating in the transition region; a plurality of first cross-flow injection nozzles (32; 132) and a plurality of second cross-flow injection nozzles (33; 133) provided on the elongated streamlined body at respective axial locations; and wherein the flame stabilizer device (23; 223) is arranged downstream of the first cross-flow injection nozzles (32; 132) and of the second cross-flow injection nozzles (33; 133); characterized in that the flame stabilizer device (23; 223) comprises a full-load flame stabilizer at a downstream end of the elongated streamlined body and at least one partial-load flame stabilizer between the second cross-flow injection nozzles (33; 133) and the full-load flame stabilizer. an elongated streamlined body extending in the axial direction from the first-stage combustor into the second-stage combustion chamber (20; 220) through a transition region of the second-stage combustor, wherein the elongated streamlined body and the transition region are configured to prevent gas flowing from the first-stage combustor to the second-stage combustion chamber (20; 220) from recirculating in the transition region; a plurality of first cross-flow injection nozzles (32; 132) and a plurality of second cross-flow injection nozzles (33; 133) provided on the elongated streamlined body at respective axial locations; and wherein the flame stabilizer device (23; 223) is arranged downstream of the first cross-flow injection nozzles (32; 132) and of the second cross-flow injection nozzles (33; 133); characterized in that the flame stabilizer device (23; 223) comprises a full-load flame stabilizer at a downstream end of the elongated streamlined body and at least one partial-load flame stabilizer between the second cross-flow injection nozzles (33; 133) and the full-load flame stabilizer.