Gas turbine blade with tip sections offset towards the pressure side and with cooling channels
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United States of America Patent
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Mar 28, 2017
Issued Date -
N/A
app pub date -
Nov 13, 2012
filing date -
Nov 17, 2011
priority date (Note) -
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Abstract
A hollow blade including an airfoil extending along a longitudinal direction, a root, a tip, an internal cooling passage, and an open cavity defined by an end wall and a rim, together with cooling channels connecting the internal cooling passage to a pressure side. The cooling channels slope relative to the pressure side. A stack of airfoil sections of the blade at a level of the rim of the tip of the blade are offset towards the pressure side. The pressure side wall of the airfoil includes a projecting portion and cooling channels arranged in the projecting portion to open out into a terminal face of the projecting portion.
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