Gas turbine engine having fan blades of adjustable pitch with cyclic setting
US9200594B2 · kind B2 · utility
5Cited by
15References
17Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Feb 25, 2010 |
| Grant date | Dec 1, 2015 |
| Priority date | — |
| Expiry date | Mar 22, 2033 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A fan portion of a dual flow turbojet engine including a plurality of fan blades, a disk supporting the blades and configured to be rotated relative to a stator portion of the fan, along a longitudinal axis of the fan, and a system for setting the angle of attack associated with each fan blade, the systems configured such that the angle of attack of each blade varies according to a same setting law according to the angular position of the blade relative to the stator portion, along the longitudinal axis, the same setting law being periodic with a period of P=360°/n, where n is an integer at least equal to 1.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.