Efficient, low pressure ratio propulsor for gas turbine engines
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United States of America Patent
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Mar 6, 2018
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N/A
app pub date -
Apr 24, 2015
filing date -
Jul 5, 2011
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Abstract
A gas turbine engine includes a core flow passage, a bypass flow passage, and a propulsor arranged at an inlet of the bypass flow passage and the core flow passage. The propulsor includes a row of propulsor blades. The row includes no more than 20 of the propulsor blades. The propulsor has a pressure ratio between about 1.2 and about 1.7 across the propulsor blades.
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