Conformal inlet apparatus for a gas turbine engine
US9777631B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Sep 30, 2011 |
| Grant date | Oct 3, 2017 |
| Priority date | — |
| Expiry date | Sep 30, 2033 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T137/0536
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An inlet apparatus for a gas turbine engine includes: a fan duct adapted to surround at least one row of rotating fan blades, the fan duct having a circular frontal area, and defining a first inlet plane; and an outer duct surrounding the fan duct, the outer duct including: a first frontal area shape at the first inlet plane which defines, cooperatively with an exterior of the fan duct, at least one lobe through which air can pass; and a second frontal area shape at a second inlet plane located axially downstream from the forward end which is circular, and which defines, cooperatively with an exterior of the fan duct, an annulus through which air can pass.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.