LPC exit guide vane and assembly
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United States of America Patent
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Aug 20, 2013
Grant Date -
Aug 20, 2009
app pub date -
Feb 19, 2008
filing date -
Feb 19, 2008
priority date (Note) -
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status (Latency Note)
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Abstract
A vane for a gas turbine engine includes an airfoil portion, a platform, and a first flange. The airfoil portion has first and second ends spaced apart in a first direction, and the first end of the airfoil portion defines an unshrouded tip. The platform is integrally formed at the second end of the airfoil, and is configured to define a flowpath boundary segment. The first flange extends from the platform away from the airfoil portion. The first flange defines a first circumferential extension and an adjacent second circumferential extension, each defining forward and aft faces. The first and second circumferential extensions are offset in a second direction such that the forward face of the first circumferential extension is substantially aligned with the aft face of the second circumferential extension in the second direction.
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