Ceramic matrix composite component cooling

A method for forming a ceramic matrix composite (CMC) airfoil for a gas turbine engine, the method comprising:

• laying up a CMC material to form an airfoil preform assembly, the airfoil preform assembly defining an airfoil shape having
• opposite pressure and suction sides extending radially along a span,
• opposite leading and trailing edges extending radially along the span, the pressure and suction sides extending axially between the leading and trailing edges, the leading edge defining a forward end of the airfoil, the trailing edge defining an aft end of the airfoil, and
• a trailing edge portion defined adjacent the trailing edge at the aft end;
• processing the airfoil preform assembly to produce a green state CMC airfoil;
• defining a pocket in the trailing edge portion;
• inserting a heat pipe into the pocket;
• wherein the pocket extends axially within the trailing edge portion;
• wherein the airfoil defines adjacent the leading edge a cavity for receipt of a flow of cooling fluid,
• wherein the pocket is defined from the cavity toward the trailing edge;
• and
• wherein a condenser portion of the heat pipe is positioned near the cavity.