Patent ID: 10837642

Abstract:
Provided are a combustor nozzle, a gas turbine combustor, a gas turbine, a cover ring, and a combustor nozzle manufacturing method. The combustor nozzle includes: a nozzle body provided with a fuel flow passage; a cover ring that is disposed on an outer side of the nozzle body so as to form air flow passages that allow air to jet out toward a front side; and fuel injection nozzles that are provided in a leading end part of the nozzle body at predetermined intervals in a circumferential direction and extend through the cover ring so as to be able to inject fuel from the fuel flow passage toward the front side. The cover ring has an outer circumferential surface cover that covers an outer circumferential surface of the nozzle body, a leading end surface cover that covers a leading end surface of the nozzle body, and a plurality of inclined flow passages that extend through the leading end surface cover in a thickness direction and are inclined in a predetermined direction relative to a direction of a central axis.