Gas turbine engine with low fan noise
Number of patents in Portfolio can not be more than 2000
United States of America
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Jan 7, 2020
Grant Date -
Dec 17, 2015
app pub date -
Mar 11, 2014
filing date -
Mar 11, 2014
priority date (Note) -
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Abstract
In accordance with one aspect of the disclosure, a gas turbine engine, method of using and designing such is disclosed. The gas turbine engine may comprise a fan including a plurality of blades, and a variable area fan nozzle. The fan may be configured to have a design point fan tip leading edge relative flow angle βADP, and may be further configured to have an off-design point fan tip leading edge relative flow angle β at an off-design fan operating point. The variable area fan nozzle may be configured to manipulate the amount of air flowing through the fan so that the absolute value of a difference between the design point fan tip leading edge relative flow angle βADP and the off-design point fan tip leading edge relative flow angle β is in a specified range.
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