Icephobic Flowpath for a Nose Cone and Method Therefor
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Aug 11, 2016
app pub date -
Feb 6, 2015
filing date -
Feb 6, 2015
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Abstract
A gas turbine engine is provided having a nose cone, wherein the nose cone is symmetrically disposed about an axis. The nose cone includes a leading edge and a base. A forward section is disposed between the leading edge and the base and has a radius at any axial location defined by a first equation. A transition section is disposed between the forward section and the base and has a radius at any axial location defined by a second equation. The first equation is different than the second equation.
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