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Efficient, Low Pressure Ratio Propulsor for Gas Turbine EnginesA gas turbine engine includes a gear assembly and a bypass flow passage that includes an inlet and an outlet that define a design pressure ratio between 1.3 and 1.55. A fan is arranged at the inlet. A first turbine is coupled with a first shaft such that rotation of the first turbine will drive the fan, through the first shaft and the gear assembly, at a lower speed than the first shaft. The fan includes a row of fan blades. The row includes 12-16 (N) fan blades, a solidity value (R) that is from 1.0 to 1.3, and a ratio of N/R that is from 10.0 to 16.
Document ID
20180004361
Acquisition Source
Glenn Research Center
Document Type
Other - Patent
Authors
Gallagher, Edward J.
Monzon, Byron R.
Bugaj, Shari L.
Date Acquired
August 10, 2018
Publication Date
July 3, 2018
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
Patent Application Number: US-Patent-Appl-SN-15/233,142
Patent Number: US-Patent-10,012,150
Funding Number(s)
CONTRACT_GRANT: NAS3-01138
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Patent
US-Patent-10,012,150
Patent Application
US-Patent-Appl-SN-15/233,142

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