Dual-flow turbomachine for aircraft, including structural means of rigidifying the central casing
US9157334B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Nov 2, 2010 |
| Grant date | Oct 13, 2015 |
| Priority date | — |
| Expiry date | Jan 6, 2033 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2250/30
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A turbomachine for an aircraft including a mechanism forming a case fitted in a rear extension of an inner ferrule of an intermediate casing, and positioned around a central casing. The mechanism includes a structural upstream ferrule assembled on the inner ferrule and defining a front portion of a surface internally delimiting a secondary vein, and a main case extending on the upstream ferrule towards the rear. The turbomachine further includes a structural mechanism rigidifying the central casing, surrounded by the case, and extending towards the rear between the upstream ferrule and the central casing on which these mechanisms are assembled.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.