Ceramic matrix composite structure having integral cooling passages and method of manufacture

A green body ceramic matrix composite structure comprising:

• a top layer of ceramic matrix impregnated ceramic fibers;
• a bottom layer of ceramic matrix impregnated ceramic fibers;
• a plurality of fiber-wrapped fugitive material structures extending in a longitudinal direction between the top layer and the bottom layer, each of the fiber-wrapped fugitive material structures comprising fugitive material wrapped with a layer of ceramic matrix impregnated fiber;
• and
• an intermediate layer of ceramic matrix impregnated ceramic fibers disposed between the top layer and the bottom layer;
• the intermediate layer being disposed alternately aver and under adjacent fiber-wrapped fugitive material structures to vertically displace adjacent fiber-wrapped fugitive material structures.

A ceramic matrix composite structure comprising:

• a multi-layer ceramic matrix composite material;
• a layer of ceramic thermal insulating material disposed on the multi-layer ceramic matrix composite material;
• and
• a cooling passage formed in the multi-layer ceramic matrix composite material, the cooling passage having a longitudinal axis extending in a direction parallel to a plane of a layer of the multi-layer ceramic matrix composite material, the cooling passage bounded by a layer of ceramic matrix composite material having fibers disposed around the longitudinal axis;
• wherein the cooling passage has an outlet end extending through the layer of ceramic thermal insulating material to deliver the cooling fluid to a hot side of the ceramic matrix composite structure.

A ceramic matrix composite structure comprising:

• a layer of ceramic matrix composite material having an inner surface defining a central volume;
• a layer of ceramic thermal insulating material disposed over an outer surface of the layer of ceramic matrix composite material, the layer of ceramic thermal insulating material defining an airfoil;
• a cooling passage extending from an inlet end at the inner surface of the layer of ceramic matrix composite material, through a portion of the layer of ceramic matrix composite material, through a thickness of the layer of ceramic thermal insulating material, to an outlet end at the outer surface of the layer of ceramic thermal insulating material for the passage of a cooling fluid from the central volume to exterior of the airfoil;
• the cooling passage defined and reinforced along at least a portion of its length by a reinforcing layer of ceramic matrix composite material embedded within the layer of ceramic matrix composite material.

A ceramic matrix composite structure comprising:

• a layer of ceramic matrix composite material having a hot side surface;
• a layer of ceramic thermal insulating material disposed on the hot side surface;
• a cooling passage having a portion extending through the ceramic matrix composite material below the hot side surface for directing a flow of cooling fluid, and
• the cooling passage further comprising an outlet end extending across a thickness of the layer of ceramic thermal insulating material to the hot side surface for exhausting the flow of cooling fluid.