High pitch-to-chord turbine airfoils
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United States of America Patent
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May 21, 2019
Grant Date -
Nov 3, 2011
app pub date -
Apr 28, 2010
filing date -
Apr 28, 2010
priority date (Note) -
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Abstract
A low pressure turbine engine component for use in an engine, for propelling a vehicle such as an aircraft is formed by a disk portion and a plurality of low pressure turbine blades extending outwardly from the disk portion. Each of the low pressure turbine blades has an airfoil portion with an axial chord length and a trailing edge. The low pressure turbine blades are spaced apart so that there is a pitch-to-chord ratio greater than 1.4, wherein the pitch is a distance between the trailing edges of adjacent ones of the low pressure turbine blades and the chord is the axial chord length of the blades.
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