Method for manufacturing turbine rotor blade

Patent metadata

Field	Value
Publication number	US-9919392-B2
Application number	US-201314650738-A
Country	US
Kind code	B2
Filing date	Dec 18, 2013
Priority date	Dec 19, 2012
Publication date	Mar 20, 2018
Grant date	Mar 20, 2018

Abstract

A method for manufacturing a turbine rotor blade wherein warping, bending and twisting of the entire rotor blade, which is provided with an excess thickness portion after a forging step, can be suppressed. In the forging step in a process for manufacturing a rotor blade ( 23 ), the forging is hot-forged such that the distance (the excess thickness amount) from the blade surface of the blade section ( 23 ) to the surface of the excess thickness section is substantially uniform along the entire periphery of a cross section of the blade section ( 23 ) and the excess thickness section ( 31 ) perpendicular to the blade length direction, and such that the amount of the excess thickness in the blade length direction, which is the thickness of the excess thickness section ( 31 ), gradually increases toward the blade tip from a prescribed position.

First claim

The invention claimed is:

1. A method for manufacturing a turbine rotor blade in which a plurality of the rotor blades are fixed to be arranged along the peripheral direction of a rotor on the outer periphery of the rotor rotatably supported in a turbine, comprising:
a forging step of providing an excess thickness section on a blade section of the rotor blade, and molding a forging, in which an excess thickness amount which is the thickness of the excess thickness section increases from a prescribed position of the blade section in a blade length direction toward a blade tip side, by die forging;
a machining step of cutting the excess thickness section from the forging and forming the blade section; and
a molding step of molding the forging, in which the excess thickness amount is substantially uniform in the entire periphery of a cross section of the blade section perpendicular to the blade length direction in at least a portion of the blade section and the excess thickness section in the blade length direction, by die forging in the forging step.

2. The method for manufacturing a turbine rotor blade according to claim 1 , wherein the prescribed position is any position between a base end section of the blade section and a center section of the blade section.

3. The method for manufacturing a turbine rotor blade according to claim 1 , wherein the prescribed position is any position between a base end section of the blade section and a position of a stub which is formed on the blade section.

4. The method for manufacturing a turbine rotor blade according to claim 1 , wherein the prescribed position is any position between a base end section of the blade section and a position of ¼ of the length of the blade section in the blade length direction.

Assignees

• Mitsubishi Hitachi Power Sys

Inventors

• Hatano Kohei
• Oyama Hiroharu
• Machida Motonari
• Haraguchi Hidetaka
• Ishii Ken
• Kamitani Keisuke
• Matsumura Takumi
• Ota Takahiro

Classifications

• F05D2230/25

  by forging · CPC title

• B21K3/04 Primary

  blades, e.g. for turbines; Upsetting of blade roots · CPC title

• B23P15/02 Primary

  turbine or like blades from one piece · CPC title

• F01D5/141

  Shape, i.e. outer, aerodynamic form (F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147) · CPC title

• F05D2220/31

  in steam turbines · CPC title