Gas turbine blade
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United States of America Patent
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Jan 16, 2018
Issued Date -
N/A
app pub date -
Apr 2, 2015
filing date -
Apr 4, 2014
priority date (Note) -
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Abstract
A blade for a gas turbine has a leading edge and a trailing edge, which are connected by a pressure side and an intake side. In at least one segment of a stacking axis, the blade has a cross section with a profile with a common profile tangent at a leading edge region and a trailing edge region, a leading edge tangent at the leading edge, which is perpendicular to the common profile tangent, a trailing edge tangent at the trailing edge, which is perpendicular to the common profile tangent, and a camber line, which extends, at an equal distance from the pressure side and the intake side, from a center point of a leading edge circle, up to a center point of a trailing edge circle.
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