Elliptical air opening at an upstream end of a fuel injector shroud and a gas turbine engine combustion chamber
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United States of America Patent
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Jun 21, 2016
Grant Date -
Jun 12, 2014
app pub date -
Nov 26, 2013
filing date -
Dec 12, 2012
priority date (Note) -
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Abstract
A gas turbine engine lean burn fuel injector includes a fuel injector head which has a first air swirler, a second air swirler arranged around the first air swirler, a pilot fuel injector arranged radially between the first air swirler and the second air swirler. A third air swirler arranged around the second air swirler, a fourth air swirler arranged around the third air swirler and a main fuel injector arranged radially between the third air swirler and the fourth air swirler. A shroud is arranged around the fourth air swirler. A downstream end of the shroud is generally circular in cross-section in a plane perpendicular to the axis (Y) of the fuel injector head and an upstream end of the shroud is generally elliptical in cross-section in a plane perpendicular to the axis (Y) of the fuel injector head.
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