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US 2012/0222397 A1Published application
Gas turbine engine with low fan pressure ratio
AssigneeUnited Technologies Corporation
InventorsPeter G. Smith, Stuart S. Ochs, Frederick M. Schwarz
Life of this patent
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Abstract
A turbofan engine includes a fan variable area nozzle axially movable relative to the 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 airflow path for a fan bypass airflow having a bypass ratio greater than about six (6);
- and
- 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, the fan pressure ratio less than about 1.45.
1 more element
Dependencies are inferred from the claim text.