Patent ID: 10495313

Abstract:
A fuel nozzle for gas turbine combustor of the present invention includes a diffusion combustion burner including a diffusion fuel nozzle, a premixing combustion burner including a premixing fuel nozzle, an end flange to which the diffusion combustion burner and the premixing combustion burner are mechanically joined, and a diffusion combustion burner support which fixes the diffusion combustion burner to the end flange and is mounted around the premixing fuel nozzle in a manner to cover a root portion of the premixing fuel nozzle, the root portion being a junction between the premixing fuel nozzle and the end flange. An outside diameter of the premixing fuel nozzle longitudinally varies in a manner to progressively increase toward the junction. A maximum diameter of the root portion of the premixing fuel nozzle is greater than an inside diameter of a hole formed in the diffusion combustion burner support.