FUEL INJECTOR
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United States of America Patent
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Issued Date -
Jun 27, 2019
app pub date -
Feb 28, 2019
filing date -
Feb 28, 2019
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Abstract
A fuel injection system for a gas turbine engine comprises; a pilot fuel injector section and a main airblast fuel injector section, the main airblast fuel injector section having an aft end facing a combustion chamber. A surface of the injection system exposed to air flow through an injection system is non-axisymmetric or non-planar in a reference circumferential plane and/or is configured to generate controlled and varying acoustic impedance at or adjacent the aft end where, in use, the air flow collides with an oncoming acoustic wave.
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