RTX Corporation
Shaped cooling passages for turbine blade outer air seal

Abstract:

A core assembly for fabricating an air cooled engine component for a gas turbine engine includes an end portion for defining passages within a side of an engine component. The end portion defines a first cross-section. A middle portion is spaced apart from the end portion and defines passages through a middle part of the engine component. The middle portion defines a second cross-section. One of the first cross-section and the second cross-section includes a first height greater than a second height. An air cooled engine component for a gas turbine engine and a gas turbine engine are also disclosed.