Fuel nozzle for gas turbine combustor

Patent metadata

Field	Value
Publication number	US-2016377294-A1
Application number	US-201615188185-A
Country	US
Kind code	A1
Filing date	Jun 21, 2016
Priority date	Jun 24, 2015
Publication date	Dec 29, 2016
Grant date	—

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.

First claim

What is claimed is:

1 . A fuel nozzle for gas turbine combustor, comprising:
a diffusion combustion burner including a diffusion fuel nozzle for spraying a diffusion combustion fuel into a combustion chamber; a premixing combustion burner including a premixing fuel nozzle for spraying a premixing fuel into a premixer; 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, wherein an outside diameter of the premixing fuel nozzle longitudinally varies in a manner to progressively increase toward the junction, and wherein 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.

2 . The fuel nozzle for gas turbine combustor according to claim 1 ,
wherein the root portion of the premixing fuel nozzle is fillet welded to the end flange.

3 . The fuel nozzle for gas turbine combustor according to claim 1 ,
wherein an outside diameter part of the premixing fuel nozzle includes the root portion which is the thickest, a step portion thinner than the root portion, and a distal end portion as thick as the step portion or thinner than the step portion.

4 . The fuel nozzle for gas turbine combustor according to claim 3 ,
wherein the root portion and the step portion are located inside the hole formed in the diffusion combustion burner support.

5 . The fuel nozzle for gas turbine combustor according to claim 3 ,
wherein a boundary region between the root portion and the step portion has an arc shape.

6 . The fuel nozzle for gas turbine combustor according to claim 3 ,
wherein the step portion has a fillet shape.

7 . The fuel nozzle for gas turbine combustor according to claim 3 ,
wherein the outside diameter part of the premixing fuel nozzle includes the root portion in a linear shape, the step portion in a fillet shape, and the distal end portion in a tapered shape.

8 . The fuel nozzle for gas turbine combustor according to claim 7 ,
wherein the step portion in the fillet shape includes a linear portion and a tapered portion.

9 . The fuel nozzle for gas turbine combustor according to claim 5 ,
wherein an inside diameter part of the hole formed in the diffusion combustion burner support has a shape conforming to a shape of the outside diameter part of the premixing fuel nozzle, and wherein the hole formed in the diffusion combustion burner support is in tight contact with the premixing fuel nozzle.

10 . The fuel nozzle for gas turbine combustor according to claim 5 ,
wherein the premixing fuel nozzle has a stress concentration factor of 2.35 or less at an area where the outside diameter part of the premixing fuel nozzle longitudinally and discontinuously varies.

Assignees

• Mitsubishi Hitachi Power Sys

Inventors

• Wadayama Yoshihide
• Kumagai Satoshi
• Wada Yasuhiro
• Takahashi Hirokazu

Classifications

• F05D2220/32

  in gas turbines · CPC title

• F23R2900/00005

  Preventing fatigue failures or reducing mechanical stress in gas turbine components · CPC title

• F23R3/343 Primary

  Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion (ignition in gas-turbine plants F02C7/264; pilot flame igniters F23Q9/00) · CPC title

• F02C7/228

  Dividing fuel between various burners · CPC title

• F23R3/286 Primary

  having fuel-air premixing devices (F23R3/30 takes precedence) · CPC title