Casing for an aircraft turbofan bypass engine
US8979484B2 · kind B2 · utility
1Cited by
39References
13Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jan 5, 2012 |
| Grant date | Mar 17, 2015 |
| Priority date | — |
| Expiry date | Sep 6, 2033 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2230/237
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A casing for an aircraft turbofan bypass engine includes an outer ring, an inner hub and a plurality of struts radially extending therebetween. An annular portion of an engine core casing having an outer wall and an inner wall, is disposed between the outer ring and inner hub, forming an annular splitter supporting an upstream splitter tip structure. The annular splitter further includes an intermediate wall disposed in the annular splitter fixed to the outer wall and the struts, to distribute loads from the annular splitter box to the struts.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.