Gas turbine blade and method for producing such blade
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United States of America Patent
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Jul 26, 2022
Grant Date -
Dec 17, 2020
app pub date -
Jan 8, 2019
filing date -
Jan 11, 2018
priority date (Note) -
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Abstract
A gas turbine blade having a casted metal airfoil, the airfoil has a main wall defining at least one interior cavity, having a first side wall and a second side wall, which are coupled to each other at a leading edge and a trailing edge, extending in a radial direction from a blade root to a blade tip and defining a radial span from 0% at the blade root to 100% at the blade tip. The main airfoil has a radial span dependent chord length defined by a straight line connecting the leading edge and the trailing edge as well as a radial span dependent solidity ratio of metal area to total cross-sectional area. Solidity ratios in a machined zone of the airfoil from 80% to 85% of span are below 35%, in particular all solidity ratios in the zone.
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