Gas turbine engine having slim-line nacelle
US8353164B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jul 8, 2010 |
| Grant date | Jan 15, 2013 |
| Priority date | — |
| Expiry date | Aug 26, 2031 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T137/0536
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine system includes nacelle, a first boundary layer control device, a second boundary layer control device, at least one sensor, and a controller. The nacelle is defined about an axis and includes an inlet lip section, an inlet internal diffuser section, and a variable area fan nozzle moveable to influence a discharge airflow area of the nacelle. The first boundary layer control device is positioned near the inlet lip section and is actuable to introduce a first airflow at the inlet lip section. The second boundary layer control device is positioned near the inlet internal diffuser section and is actuable to introduce a second airflow at the inlet internal diffuser section. The sensor produces a signal that represents an operability condition. The controller receives the signal and simultaneously moves the variable area fan nozzle and actuates the first boundary layer control device and the second boundary layer control device in response to receiving the signal to achieve a slim-line nacelle.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.