Core component having toroidal structures

A component for a gas turbine engine comprising:

• a first end;
• a second end generally opposite the first end;
• a flow chamber disposed along a stacking axis between the first end and the second end and defined by an internal surface of the component, the flow chamber comprising:
• a first chamber located at the first end and having a substantially toroidal cross section;
• a second chamber located between the first chamber and the second end and having a toroidal cross section;
• a first pedestal extending through a central portion of the first chamber in a first direction;
• and
• a second pedestal extending through a central portion of the second chamber in a second direction, wherein the first direction and the second direction are oriented at a non-zero degree angle with respect to each other.

A core comprising:

• a first end;
• a second end spaced opposite from the first end;
• a stacking axis extending through the first end and the second end;
• a first disc located between the first end and the second end, the first disc having a first generally planar surface;
• and
• a second disc located between the first disc and the second end, the second disc having a second generally planar surface;
• wherein the first generally planar surface and the second generally planar surface are oriented along the stacking axis at a non-zero degree angle with respect to each other.