Gas turbine engine for aircraft engine
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United States of America Patent
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Nov 7, 2017
Issued Date -
N/A
app pub date -
Aug 3, 2012
filing date -
Aug 4, 2011
priority date (Note) -
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Abstract
A gas turbine stator for aircraft engines has a blade array with a plurality of blades constituted by a series of first blades and a series of second blades with different geometries; the array is formed by a plurality of sectors, each having an inner portion, an outer portion, at least one first blade and a least one second blade, and each defined by a body made in one piece; a single first blade is alternated with a single second blade for the entire circumference of the stator.
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