To enable the replacement of part of a turbine support 100 for a gas turbine.
The turbine support includes a body 102, a forward leg portion 114, an aft leg portion 120, and a mounting flange 108 that each extend radially outwardly from the body. The forward leg portion is located on the axially upstream side from the aft leg portion and the mounting flange. The mounting flange is substantially axially aligned with respect to the aft leg portion. This method comprises a step of cutting through at least one of the body, the aft leg portion and the mounting flange, a step of removing the forward leg portion and at least a part of the body located on the upstream from the cut portion 140 from the engine, and a step of coupling a replacement spad to a portion of the turbine support located on the downstream from the cut portion.
GUPTA BHUPENDRA K
JPS54159516A | 1979-12-17 | |||
JP2002168133A | 2002-06-14 | |||
JPH10339103A | 1998-12-22 | |||
JP2002295268A | 2002-10-09 | |||
JP2001073710A | 2001-03-21 | |||
JP2002138853A | 2002-05-17 | |||
JP2002303155A | 2002-10-18 |
WO2001051771A2 | 2001-07-19 | |||
EP1262632A1 | 2002-12-04 |
Hirokazu Ogura
Nobukazu Ito