Fan guide vane with leading edge deicing

A gas turbine engine with a fan exit guide vane with load carrying member and leading edge deicing comprising:

• a fan located within a fan duct;
• an array of fan exit guide vanes supported within the fan duct downstream from the fan, the array of fan exit guide vanes span across the fan duct attached to a radially inner surface of the fan duct and a radially outer surface of the fan duct;
• each of the fan exit guide vanes comprising a leading edge and a trailing edge opposite chordwise from the leading edge;
• a radially inner attachment region opposite spanwise from a radially outer attachment region, the radially inner attachment region in operative communication with the radially inner surface of the fan duct, the radially outer attachment region in operative communication with the radially outer surface of the fan duct;
• a span dimension extending between the radially inner attachment region and the radially outer attachment region;
• a chord dimension extending between the leading edge and the trailing edge;
• a pressure side opposite a suction side of the fan exit guide vane;
• a load member cavity formed within at least one fan exit guide vane in the array, the load member cavity extending spanwise through the at least one fan exit guide vane from the radially inner attachment region to the radially outer attachment region;
• the load member extending through the load member cavity beyond each of the radially inner attachment region and the radially outer attachment region of the at least one fan exit guide vane;
• the load member in operative communication with the radially inner surface and the radially outer surface;
• the cooling cavity formed within the fan exit guide vane extending spanwise through the fan exit guide vane between the radially inner attachment region and the radially outer attachment region;
• a leading edge deicing structure in fluid communication with the cooling cavity and the leading edge;
• and
• at least one leading edge deicing structure flow passage is fluidly coupled with the load member cavity.

A process for supporting a structural load path in a gas turbine engine with a fan exit guide vane with load carrying member and leading edge deicing comprising:

• locating a fan within a fan duct;
• supporting an array of fan exit guide vanes within the fan duct downstream from the fan;
• attaching the array of fan exit guide vanes spanned across the fan duct to a radially inner surface of the fan duct and a radially outer surface of the fan duct;
• each of the fan exit guide vanes comprising a leading edge and a trailing edge opposite chordwise from the leading edge;
• a radially inner attachment region opposite spanwise from a radially outer attachment region;
• coupling the radially inner attachment region in operative communication with the radially inner surface of the fan duct;
• coupling the radially outer attachment region in operative communication with the radially outer surface of the fan duct;
• a span dimension extending between the radially inner attachment region and the radially outer attachment region;
• a chord dimension extending between the leading edge and the trailing edge;
• a pressure side opposite a suction side of the fan exit guide vane;
• forming a load member cavity within at least one fan exit guide vane in the array;
• extending the load member cavity spanwise through the at least one fan exit guide vane from the radially inner attachment region to the radially outer attachment region;
• extending the load member through the load member cavity beyond each of the radially inner attachment region and the radially outer attachment region of the at least one fan exit guide vane;
• coupling the load member in operative communication with the radially inner surface and the radially outer surface;
• forming the cooling cavity within the fan exit guide vane extending spanwise through the fan exit guide vane between the radially inner attachment region and the radially outer attachment region;
• coupling a leading edge deicing structure in fluid communication with the cooling cavity and the leading edge;
• and
• fluidly coupling at least one leading edge deicing structure flow passage with the load member cavity.