Gas turbine engine systems and related methods involving vane-blade count ratios greater than unity
US7984607B2 · kind B2 · utility
20Cited by
10References
8Claims
0Family size
Assignee
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Key dates
| Filing date | Sep 6, 2007 |
| Grant date | Jul 26, 2011 |
| Priority date | — |
| Expiry date | May 25, 2030 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02C3/14
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
Gas turbine engine systems and related methods involving vane-blade count ratios greater than unity are provided. In this regard, a representative turbine stage for a gas turbine engine includes a first set of rotatable blades operative to be positioned downstream of and adjacent to a first set of vanes, a number of blades of the first set of blades being less than a number of vanes of the first set of vanes.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.