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Efficient, Low Pressure Ratio Propulsor for Gas Turbine EnginesA gas turbine engine includes a spool, a turbine coupled to drive the spool, and a propulsor that is coupled to be driven by the turbine through the spool. A gear assembly is coupled between the propulsor and the spool such that rotation of the turbine drives the propulsor at a different speed than the spool. The propulsor includes a hub and a row of propulsor blades that extends from the hub. The row includes no more than 20 of the propulsor blades.
Document ID
20150018769
Acquisition Source
Glenn Research Center
Document Type
Other - Patent
Authors
Gallagher, Edward J.
Monzon, Byron R.
Date Acquired
October 5, 2015
Publication Date
September 1, 2015
Subject Category
Aircraft Propulsion And Power
Funding Number(s)
CONTRACT_GRANT: NAS3-01138
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Patent
US-Patent-9,121,368
Patent Application
US-Patent-Appl-SN-13/484,858

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