Shaped cooling passages for turbine blade outer air seal
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.
1. An air cooled engine component for a gas turbine engine, the air cooled engine component comprising:
a first end;
a second end;
a middle portion; and
at least one continuous internal passage extending from the first end through the middle portion to the second end, the at least one continuous internal passage including a first cross-section within the first end and the second end and a second cross-section within the middle portion,
wherein the first cross-section includes a first height and the second cross-section includes a second height, the first height being greater than the second height,
wherein the first height is uniform across the first cross-section for a first width and the second height is uniform across the second cross-section for a second width,
wherein the air cooled engine component is a single continuous engine component, and
wherein the first height is no more than twice as large as the second height.
2. The air cooled engine component as recited in claim 1 , wherein the at least one continuous internal passage comprises respective transition portions positioned between a portion of the at least one continuous internal passage located in the middle portion and respective portions of the at least one continuous internal passage located in each of the first end and the second end.