REDUCTION IN JET FLAP INTERACTION NOISE WITH GEARED TURBINE ENGINE
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United States of America Patent
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Aug 20, 2015
app pub date -
Feb 22, 2013
filing date -
Sep 28, 2012
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Abstract
A turbine engine system mounted on an aircraft wing includes a gas turbine engine having a spool, a turbine coupled with the spool, a fan coupled to be rotated about an axis through the spool, and a gear assembly coupled between the fan and spool such that rotation of the spool results in rotation of the fan at a different speed than the spool. The gas turbine engine is operable to discharge a jet plume that interacts with a flap of the aircraft wing. The gas turbine engine defines a design fan pressure ratio of 1.25-1.50 to control sound resulting from the jet plume that interacts with the flap.
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