Blade structure in a gas turbine
US6887042B2 · kind B2 · utility
11Cited by
6References
2Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Dec 20, 2001 |
| Grant date | May 3, 2005 |
| Priority date | — |
| Expiry date | Oct 4, 2022 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2240/12
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
In the blade structure in a gas turbine, front-edge including angles are made large. As a result, a curve of a relative relationship between incidence angles ic1 and is1 and pressure loss becomes mild. Entrance metal angles are made small. As a result, it becomes possible to make the incidence angles small. Chord length of a tip portion of a moving blade is made large. As a result, it becomes possible to make small the deceleration on a rear surface of the tip portion of the moving blade. Accordingly, it becomes possible to make the pressure loss small, and therefore, it becomes possible to improve the turbine efficiency.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.