Patent ID: 9429326
Filing Date: 2016-08-30
CPC Classification: F23R

Claim Text:
1. A combustor nozzle assembly of a gas turbine comprising: a nozzle mounting base that blocks a combustor insertion opening formed in a turbine casing; a nozzle rod formed in a tubular shape, passes through the nozzle mounting base, and having a rod tip portion protruding to an inside of the turbine casing and a rod base end portion protruding to the outside of the turbine casing; a fuel pipe formed in a tubular shape, inserted as a whole into the nozzle rod, having a pipe tip portion fixed to the rod tip portion of the nozzle rod and a pipe base end portion inserted into the rod base end portion of the nozzle rod, wherein fuel is supplied to an inside of the fuel pipe through the rod base end portion, and injects the fuel from the pipe tip portion through the rod tip portion of the nozzle rod; and a seal member disposed in the rod base end portion of the nozzle rod and suppresses leakage of the fuel to a pipe tip portion side between an inner periphery side of the nozzle rod and an outer periphery side of the fuel pipe, wherein the nozzle rod comprises: a mounting portion located in the nozzle mounting base; and a cross-sectional area reduced portion provided between the mounting portion and the rod base end portion, wherein a cross-sectional area of the cross-sectional area reduced portion perpendicular to a direction that the nozzle rod extends is smaller than a maximum cross-sectional area of the mounting portion, and is also smaller than a cross-sectional area of the rod base end portion.