Fuel nozzle of gas turbine combustor and manufacturing method thereof, and gas turbine combustor
[Problem] To provide a fuel nozzle for a gas turbine combustor, offering favorable durability and strength reliability. [Solving Means] A method for manufacturing a fuel nozzle for a gas turbine combustor, the method comprising: (a) fitting a fuel nozzle having an internal through hole into a through hole or a recess provided in a base plate; (b) bonding, by a fusion joint or a brazing joint, the fuel nozzle to the base plate in an interface therebetween on a surface of the base plate; and (c) following the step of (b), subjecting the fuel nozzle and the base plate to a pressure bonding process to thereby pressure bond the fuel nozzle and the base plate in the interface therebetween.
1. A method for manufacturing a fuel nozzle for a gas turbine combustor, the method comprising:
(a) fitting a fuel nozzle having an internal through hole into a through hole or a recess provided in a base plate;
(b) bonding, by a fusion joint or a brazing joint, the fuel nozzle to the base plate in an interface therebetween on a surface of the base plate; and
(c) following the step of (b), subjecting the fuel nozzle and the base plate to a pressure bonding process to thereby pressure bond the fuel nozzle and the base plate in the interface therebetween, the method further comprising:
between the step of (a) and the step of (b), (d) covering with a bottom plate a surface of the base plate, the surface being opposite to the surface in which the fuel nozzle is fitted, wherein
in the step of (b), the base plate and the bottom plate are bonded by a fusion joint or a brazing joint in an interface therebetween.
2. The method for manufacturing a fuel nozzle for a gas turbine combustor according to claim 1 , the method further comprising:
following the step of (c), (f) drilling a hole in the bottom plate to thereby causing the through hole in the fuel nozzle to pass through the bottom plate.
3. The method for manufacturing a fuel nozzle for a gas turbine combustor according to claim 1 , the method further comprising:
prior to the step of (a), (e) closing a bottom surface portion of the through hole in the fuel nozzle, wherein
following the step of (b), each of interfaces of the fuel nozzle, the base plate, and the bottom plate is vacuum evacuated using a vacuum evacuation hole formed in the bottom plate.
4. The method for manufacturing a fuel nozzle for a gas turbine combustor according to claim 3 ,
wherein the interface in each of the fuel nozzle, the base plate, and the bottom plate is subjected to a vacuum leak test using the vacuum evacuation hole.