Gas turbine engine for aircraft engine
US9810082B2 · kind B2 · utility
10Cited by
13References
11Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Aug 3, 2012 |
| Grant date | Nov 7, 2017 |
| Priority date | — |
| Expiry date | Jul 22, 2034 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine stator for aircraft engines has a blade array with a plurality of blades constituted by a series of first blades and a series of second blades with different geometries; the array is formed by a plurality of sectors, each having an inner portion, an outer portion, at least one first blade and a least one second blade, and each defined by a body made in one piece; a single first blade is alternated with a single second blade for the entire circumference of the stator.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.