Gas turbine engine component with integrated heat pipe

A heat transfer apparatus for a gas turbine engine, comprising:

• a component having a wall structure defining a flow bounding surface;
• and
• a chamber formed in the component, the chamber including a wicking structure, a vapor channel, and a working fluid, wherein:
• a portion of the chamber extends beyond the remainder of the component;
• the fluid conduit has an annular outer wall;
• and
• the extended portion of the chamber has a concave saddle shape that contacts the outer wall of the fluid conduit.

A heat transfer apparatus for a gas turbine engine, comprising:

• a plurality of components arranged in a ring around the engine and extending in a generally radial direction so as to define opposed inboard and outboard ends, each component having:
• a wall structure defining a flow bounding surface;
• and
• a chamber formed in the component, the chamber including a wicking structure, a vapor channel, and a working fluid, wherein the chamber includes an evaporator end and an opposed condenser end;
• wherein, for some of the chambers, the evaporator end is positioned at the inboard end of the corresponding component, and for others of the chambers, the evaporator end is positioned at the outboard end of the corresponding component.