Investment casting method for gas turbine engine vane segment
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United States of America Patent
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Jun 23, 2015
Grant Date -
May 7, 2015
app pub date -
Nov 7, 2013
filing date -
Nov 7, 2013
priority date (Note) -
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Abstract
An investment casting method for a cast ceramic core (110), including an airfoil portion (116) shaped to define an inner surface (56) of an airfoil (52) of a vane segment (50) and an integral shell portion (122) having a backside-shaping surface (120) shaped to define a backside surface (68) of a shroud (62) of the vane segment. The backside-shaping surface has a higher elevation (132) and a lower elevation (134). The higher elevation is set apart from a nearest point (138) on the airfoil portion by the lower elevation. The airfoil portion and the shell portion are cast as a monolithic body during a single casting pour.
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