Back to results
US 2012/0222398 A1Published application
Gas turbine engine with geared architecture
OwnerPeter G. Smith, Stuart S. Ochs +1inventors
InventorsPeter G. Smith, Stuart S. Ochs, Frederick M. Schwarz
Life of this patent
Estimating the term…
Abstract
A turbofan engine includes a geared architecture and a fan variable area nozzle axially movable relative to a fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation.
Claims18
A gas turbine engine comprising:
- a core nacelle defined about an engine centerline axis;
- a fan nacelle mounted at least partially around said core nacelle to define a fan bypass flow path for a fan bypass airflow;
- a fan variable area nozzle axially movable relative said fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation;
- and
- a gear system driven by a core engine within said core nacelle to drive a fan within said fan nacelle, said gear system defines a gear reduction ratio of greater than or equal to about 2.3.
2 more elements
Dependencies are inferred from the claim text.