Gas turbine rotor blade, gas turbine using the rotor blade, and power plant using the gas turbine
US7334993B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | May 15, 2006 |
| Grant date | Feb 26, 2008 |
| Priority date | — |
| Expiry date | May 15, 2026 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF01D5/3007
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine rotor blade capable of effectively reducing creep damage by forming a cooling through hole to cool a target area in which significant creep damage of a shroud cover is predicted based on analysis of stress and temperature acting on the gas turbine rotor blade. A gas turbine using the rotor blade, and a power plant using the gas turbine are also provided. The gas turbine rotor blade includes a blade section provided with a shroud cover at an outer peripheral end thereof, and a platform, a shank and a dovetail which are formed in integral structure to successively continue from the blade section. An inner cooling hole is formed to penetrate through the gas turbine rotor blade from the dovetail to the shroud cover. The shroud cover has a cooling through hole formed to open in an outer surface of the shroud cover and extend in communication with the inner cooling hole.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.