Mitsubishi Heavy Industries Limited

Naoki Taketa

Koji Watanabe

Shinya Hashimoto

Hiroaki Kobayashi

Kazuharu Hirokawa

Yoshio Fukui

Kenta Nakamura

Norihiko Nagai

Takeshi Umehara

Takuya Hiraoka

A blade ring assembly including: a turbine blade ring extending in a circumferential direction about an axis; a component to be cooled, disposed on an inner circumferential side of the turbine blade ring; and an outer circumferential side component disposed on an outer circumferential side of the turbine blade ring. The turbine blade ring has a cooling medium intake port leading from an outer circumferential surface to an inner circumferential surface of the turbine blade ring. The outer circumferential side component includes: a first wall portion which covers at least a portion of the cooling medium intake port from the outer circumferential side of the turbine blade ring; and a second wall portion which extends from an end portion of the first wall portion on the axially downstream thereof toward the outer circumferential side of the turbine blade ring.

Blade ring assembly, gas turbine, and method for refurbishing gas turbine

In a turbine vane repairing method, a damaged spot removing step of removing a damaged spot in one shroud of two shrouds, a member disposing step of disposing a deformation curbing member which comes into contact with each of the two shrouds and curbs change in relative positions between the two shrouds, an overlay welding step of performing overlay welding with respect to a removed part from which the damaged spot is removed in the one shroud and filling the removed part after the damaged spot removing step and the member disposing step, a member detaching step of detaching the deformation curbing member from the turbine vane after the overlay welding step, and a finishing step of polishing at least a surface of a part subjected to the overlay welding in the one shroud are executed.

Turbine vane repairing method

Growing community of inventors

Tokyo, Japan

Naoki Taketa