Stationary blade in gas turbine and gas turbine comprising the same
US6887039B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jul 10, 2002 |
| Grant date | May 3, 2005 |
| Priority date | — |
| Expiry date | Jul 10, 2022 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02C7/28
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A stationary blade of a gas turbine, which can reduce thermal stress produced at a portion in the vicinity of a rear edge of an inner shroud of the stationary blade. The stationary blade is positioned adjacent to at least one of moving-blade disks in an axial direction of the gas turbine. A concave portion is provided in the inner shroud in a manner such that the concave portion is formed in the vicinity of a rear edge of the inner shroud and on an inner-peripheral face of the inner shroud, where cooling air passes along the inner-peripheral face which faces a rotation shaft of the moving-blade disks; and a protruding portion which protrudes towards the rotation shaft is formed at the rear edge of the inner shroud.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.