Cambered aero-engine inlet
US8261530B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | May 1, 2009 |
| Grant date | Sep 11, 2012 |
| Priority date | — |
| Expiry date | Jul 13, 2031 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T137/0645
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An inlet of a nacelle for channeling inlet airflow to a fan of a gas turbine engine includes a forward lip and an inner surface. The forward lip extends around a centerline axis of the engine and is adapted to accommodate a flow angle of incoming airflow. The inner surface extends from the forward lip along the centerline axis of the engine to adjacent the fan. The inner surface has a first profile above the centerline axis of the engine and a second profile below the centerline axis of the engine. The first profile and the second profile are adapted to define an inlet centerline axis that extends below the centerline axis of the engine at a face of the fan.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.