Patent ID: 9132476
Filing Date: 2015-09-15
Classification: B22C,F01D,F05D

Abstract:
1. A monolithic casting core cast during a single pour casting process and configured to define an entire interior surface of a pressure side wall, an entire interior surface of a suction side wall, and an entire pressure side surface and an entire suction side surface of a third wall of a gas turbine engine multi-wall airfoil during an investment casting process, wherein a third-wall void in the casting core forms the third wall and is oriented from a leading edge toward a trailing edge of the airfoil, wherein the monolithic casting core defines a rib gap between adjacent core sections, the rib gap configured to form a rib between two walls of the multi-wall airfoil, and wherein the monolithic casting core comprises core features in the rib gap configured to define surface features on the rib.