Gas turbine airfoil

An airfoil for use in a gas turbine engine, the airfoil comprising:

• a load-bearing core member extending from a leading edge portion to a trailing edge portion, and comprising a surface with a pressure side and a suction side;
• a respective honeycomb structure attached to the pressure side and/or to the suction side of the core member, and defining a plurality of outwardly opening cells;
• a first ceramic insulation material filling the cells of the respective honeycomb structure;
• a ceramic matrix composite leading edge boot comprising a generally C or U-shaped cross section, wherein two ends of the cross section define first and second edges of the leading edge boot, the leading edge boot is attached to the core along the first and second edges of the leading edge boot, and is not bonded to the core between the first and second edges of the leading edge boot;
• and
• a shoulder formed in the core member that defines a transition between the pressure and/or suction sides and the trailing edge portion, the shoulder defining a first thickness of the ceramic insulation material over the core trailing edge portion that is less than a second thickness of the ceramic insulation on the pressure and/or suction sides of the core member.

An airfoil for use in a gas turbine engine, the airfoil comprising:

• a load-bearing core member extending from a leading edge portion to a trailing edge portion, and comprising a surface with a pressure side and a suction side;
• a respective honeycomb structure attached to the pressure side and/or the suction side of the core member, and defining a plurality of outwardly opening cells;
• a ceramic insulation material filling the cells of the respective honeycomb structure;
• a ceramic matrix composite leading edge boot attached to the core member leading edge portion;
• a ceramic matrix composite trailing edge boot attached to the core member trailing edge portion;
• wherein the ceramic insulation material extends to cover the boots, the ceramic insulation material comprises an outer surface defining an airfoil shape;
• and
• wherein the respective honeycomb structure comprises short cells adjacent the leading and/or trailing edges of the core member, the short cells being shorter than most other cells of the respective honeycomb structure.