Patent attributes
A composite turbine blade and fan blade assembly for use in a turbo machine such as a gas turbine engine. The turbine blade assembly includes a plurality of metallic turbine blades secured to a rotor disk and forming an outer shroud assembly. A fiber reinforced composite fan blade assembly includes an annular ring with a plurality of fan blades extending there from. The annular ring has a conical shape to allow for easy installation over the outer shroud assembly, and is secured to the outer shroud assembly to force the fan blade assembly to rotate with the turbine blades, yet allow for a slight radial movement between the fan blades and the turbine blades. The turbine blades are formed of a high temperature super alloy to allow for use in a gas turbine engine, and the fan blade assembly is made from a fiber reinforced composite to allow for higher rotational speeds and smaller diameters for smaller gas turbine engines without exceeding allowable stress limits.
