Efficient, low pressure ratio propulsor for gas turbine engines
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United States of America Patent
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Jul 27, 2021
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N/A
app pub date -
Jul 18, 2019
filing date -
Jul 5, 2011
priority date (Note) -
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Abstract
A gas turbine engine includes a gear assembly, a bypass flow passage, a fan located upstream of the bypass flow passage, a first shaft and a second shaft, a first turbine coupled through the gear assembly to the fan, a first compressor coupled with the first shaft, and a second turbine coupled with the second shaft. The fan includes a hub and a row of fan blades that extend from the hub. The row includes a number (N) of the fan blades that is from 16 to 20, a solidity value (R) at tips of the fan blades, and a ratio of N/R that is from 12.3 to 20.
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