Abstract: A rotor blade assembly for a turbine engine, including an airfoil blade including an inner diameter end and an outer diameter end, a lower blade carrier coupled to the inner diameter end of the airfoil blade and rigidly coupled to a disk via a pin, an upper blade carrier coupled to the outer diameter end of the airfoil blade, and an outer drum coupled to the upper blade carrier via a radial joint. The radial joint supports radial motion of the upper blade carrier relative to an axis extending through a center of the rotor blade assembly.

Abstract: A gas turbine engine assembly is provided. The gas turbine engine assembly includes a high-pressure compressor including a first rotor and a second compressor rotor disposed downstream from the first rotor, a high-pressure turbine coupled downstream to the compressor by a first shaft, and an air directing assembly coupled between the first and second compressor rotors for selectively channeling airflow discharged from the first compressor rotor through the first shaft. A method of assembling a gas turbine engine is also provided.

Abstract: A gas turbine engine assembly is provided. The gas turbine engine assembly includes a high-pressure compressor including a first rotor and a second compressor rotor disposed downstream from the first rotor, a high-pressure turbine coupled downstream to the compressor by a first shaft, and an air directing assembly coupled between the first and second compressor rotors for selectively channeling airflow discharged from the first compressor rotor through the first shaft. A method of assembling a gas turbine engine is also provided.

Abstract: A method for assembling a gas turbine engine includes providing a first fan assembly configured to rotate in a first rotational direction, rotatably coupling a second fan assembly to the first fan assembly, wherein the second fan assembly is configured to rotate in a second rotational direction that is opposite the first rotational direction, and coupling a lubrication system to the gas turbine engine such that a lubrication fluid is channeled through at least a portion of the second fan assembly.

Abstract: A method for assembling a gas turbine engine that includes providing a first fan assembly configured to rotate in a first rotational direction, rotatably coupling a second fan assembly to the first fan assembly, wherein the second fan assembly is configured to rotate in a second rotational direction that is opposite the first rotational direction, coupling a first shaft to the first fan assembly and to a first turbine rotor that is configured to rotate in a first rotational direction, coupling a second shaft coupled to the second fan assembly and to a second turbine rotor that is configured to rotate in a second rotational direction that is opposite the first rotational direction, and coupling a lubrication system to the gas turbine engine such that a lubrication fluid is channeled through the first shaft to lubricate at least one of the first and second fan assemblies.